"pressure & void distributions in converging-diverging
TRANSCRIPT
. .
.cIfHERlfi REPOR f
Accession flo._ . _ _ _
Contract Program or Project Title: Light Water Practor Thermal Hydrculic DevelopmentProg ram
Subject of this Document: Informal Report, "P re : nore and Void Distributions lu aConverging-Diverging Rn zle with Nonequ i. librium WaterVapor Generation"
Type of Document- In formal Iteport
Author (s): G. A. Ziumer, B .J .C . Wu, W. J . Leonhzu d t , N . /Ja ua f , and Os C . J on es , J r .
Date of Documnt: April 1979
Responsible f;RC Individual and I!RC Office er Division: Dr. '. Y, usuDivision of Reactor Safety Er searchSyctems Er gineering BrrnchU.S. Nuclear Regulatory CotraissionWas hi ng t o n , D.C. 20555
- _ _ _ - .._ --. - - - - - - -
This document was prepared primarily for preliminary or internal use.It has not received full review and approval. Since 1.here may besubstantive changes, this document should not be considtred final.
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Brookhaven flational Laboratory 3SIOL !".Upton,11Y 11973
Associated Universities, Inc.
for theU.S. 'lepartmenL o f Energy
Prepared forU.S. I!uclear Regulatory Cocmission
Washington, D. C. 20555 i r
Under interagency Agreement EY-76-C-02 -00lG 9 [, bs i /fiRC FIil flo. le 3045
'
liiIERI!1 REf' ORT
7907110,4I3
c 'll-NUREG -26003
INFORMAL REPORT
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PRESSURE AND VOID DISTRIBUTIONS IN A CONVERGING-DIVERGINGv
N0ZZLE WITH NONEQUILIBRIUM WATER VAPOR bENERATION-
49
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if;a' G. A. ZIMMER, B.J.C. Wu, W. J. LEONHARDT
N. ABUAF AND 0. C. JONES, JR .
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3 REACTOR SAFETY EXPERIMENTAL MODELING GROUP
DATE PUBLISHED - APRIL 1979
DEPARTMENT OF NUCLEAR ENERGY BROOKHAVEN NATIONAL LABORATORY
'. UPTON. NEW YORK 11973
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Prepared for the U.S. Nuclear Regulatory CommissionOfEce of Nuclear Regulatory Research
Contract No. EY 76 C-02-0016
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Tlns r ; .r t w as prepared as an ai( on ni of w or k sponsori d in t he l'nited Stateseni. Neither the l?ruted Ntairs nar abe t 'niscil Siairs Nu lear ReculatoryG rrin
( :. :n n u.in. nor ans of their emjdos r es, nor a ny of their ( intrattor <, sulx ora t r a< ton,I fir ir f'In g dos 00%, in Ik t'V alls w.II ra lli s , riE j)f f'ss 41r i'Hj pltf'E |, t er assilllit'% a rlY 10 4.l!
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+ t a its or rey.nubihrv f.>r the a e urar s . ( ornpleteness or u < f ulne w of a ns infornia-tion, appar aius, proilu, t i,r prrn co d m 1. scil, or irpr ese nr4 t hat its use w oubt notn trince pr it a rciv ow nc.! rights
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BNL-N UREG- 26003INFORMAL REPORT*
LIMITED DISTRIBUTION
PRESSURE AND VOID DISTRIBUTIONS IN A CONVERGING-DIVERGING
N0ZZLE WITH NONEQUILIBRIL?f NATER VAPOR GENERATION
.
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C. A. Zimmer, B.J.C. Wu, l' . J. Leonhardt
N. Abuaf and O. C. Jones, Jr.
C. Jones, Jr.: Principal Investigator''.
Thermal Hydraulic Development DivisionDepartment of Nuclear EnergyBrookhaven National Laboratory
Upton, New York 11973
APRIL 1979
Prepared for the U.S. Nuclear Regulatory CommissionOffice of Nuclear Reactor Regulation
,
Contract No. EY- 7 6- C-0 2-0 016FIN NO. A-3045
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NOTICE: This document contains preliminary information and was preparedprir.arily for interim use. Since it may be subj e c t to revision
or correction and does not represent a final report, it shouldnot be cited as reference without the expressed consent of *_heauthor (s),
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ABSTRACT
A steady water loop with well contro11ea flow and thermodynamic condi-
tions was designed, built, and made operational for the measurement of the
net vapor generation rates under nonequilibrium conditons. The test section
consists of a converging-diverging nozzle with 49 pressure taps and obser-,
vation window at the exit. Pressure distributions and photographic obser-%
*
vations were recorded under various flashing conditions. The effect of the
various parameters such as inlet pressure, inlet temperature, mass flux, and
back pressure on the pressure distributions and flashing regimes was investi-
gated and is reported here. For flashing under high back pressures, a sharp
increase in pressure (condensation shock) was observed in the diverging
section. For lower back pressures, although the pressure distributions in
the converging section were identical to the single phase calibration data,
constant pressure region was observed all along the diverging section ofa
the nozzle. With y-densitometry, the chordal averaged void fraction profiles
were also measured along the centerline axis of the test section under
various flashing conditions and are reported herein.
The neasured pressure distributions were combined with the centerline
axial void fraction profiles to calculate the volumetric vapor generation
rates under nonequilibrium conditions..
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TABLE OF CONTENTS
ABSTRACT, 1. . . . . . . . . . . . . . . . . . .
LIST OF FIGURES iv. . . . . . . . . . . . . . . . .
LIST OF TABLFS. viii. . . . . . . . . . . . . . . . .
.
ix?:0 !1:NCT.ATURE . . . . . . . . . . . . . . . . . . .
s
1'
1. INTF.0Di'CTION . . . . . . . . . . . . . . . . .
22. REVIEW OF LITERATURE . . . . . . . . . . . . . . .
43. EXPERIMI:::TAL TECha'IQUES . . . . . . . . . . . . . .
43.1 Flow Loop . . . . . . . . . . . . . . .
63.2 Test Section . . . . . . . . . . . . . . .
3.3 Loop Operation ConditiaTs and Instrumentation 10. . . .
134. DATA ACQl'ISITION . . . . . . . . . . . . . . . .
'.1 General Data Acquisition System 13. . . . . . . . . .
14'.2 Static Pressure Measurement Set-Up. . . . . . . .
a.3 y-Densitometer for Void Fraction Measurements 17. . .
5 RESULTS AND DISCCSSION 22. . . . . . . . . . . . .
. . . . . . . . . . . 225.1 Single Phase Calibration
5.2 Pressure Distributions Under Flashing Conditions 28. . .
5.2.1 Reproducibility Studies. 35. . . . . .
5.2.2 Operational Effects (Effect of Back Pressure) 35
5.2.3 Parametric Effects 39. . . . . . . . .
5.2.4 Flashing Urstream of the Throat 52. . . . .
5.3 Void Fraction Measurements Under Flashing Conditons 57-
. .
5.3.1 Flashing Close to the Throat 57. . . . . .
5.3.2 Flasi. ng Upstream of the Throat 68 Y. . . . .
5.4 Calculations of Net Vapor Generation Rates Under Flashing71Conditions . . . . . . . . . . . . . . . .
6 SL7 NARY AND CONCLUSIONS 78. . . . . . . . . . . . . .
7 ACKNOWLEDGEMENTS. 80. . . . . . . . . . . . . . . .
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TABLE OF CONTENTS (Con':'d)
628 REFERENCES. . . . . . . . . . . . . . . . . . .
N3TES TO THE APPENDICES 84. . . . . . . . . . . . . .
.
Appendix A. Single Phase Calibration Data 86. . . . . . . .
Appendix B. Pressure Distribution Data Under Flashing'
112Conditions and Some Photographic Observations. . .
Appendix C. Pressure and Void Fraction DistributionsUnder Flashing Conditions 156. . . . . . . .
.
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LIST OF FIGURES
Figure
3.1 Schema tic of BNL Heat Transfer Facility(BNL Neg. No. 1-1246-79).
1.2 Inside Dimensions of TS-2 (BNL Neg. No. 10-243-780) .
3.3 Deviation From Design of TS-2 Inside Dimensions(BNL Neg. No. 10-244-78). .
4.1 Schematic Representation of y-Densitometer(BNL Neg. No. 3-1016-79'
4.2 Calibration of the Test Section doth Empty (Air)and Full of Water as a Function of Axial Distance(BNL Neg. No. 3-1018-79)
4.3 Calibration of the Test Section Both Empty (Air)and Full of Uater as a Function of Radial Distanceat a Fixed Axial Position (BNL Neg. No. 3-1020-79)
5.1 Typical Pressure Distributions Along TS-2 for theSingle-Phase Flow Hydrodynamic Calibration Runs(BNL Neg. No. 3-1017-79)
5.2 Dimensionless Pressure Distr 4oution for TS-2. Datais Averaged for all the Hydrodynamic Calibration RunsPerformed (BNL Neg. No. 3-1022-79)
5.3 Typical Representation of an Isothermal FlashingExperimert in the p-T Diagram (BNL Neg. No. 3-1027-79)
5.4 Pressure Distributions Under Flashing and NonflashingCond it ions in TS-2 (BNL Neg. No. 3-1019-79)
5.5 Dinensionless Pressure Dis cibutions in TS-2 UnderFlashing Conditions as Compared to Single-Phase Hydro- -
dynamic Calibration Data (BNL Neg. No. 3-1021-79)
5.6 Comparison of Pressure Distribution in Two Experiments &
to Show the Reproduciblity of the Results at Low Mass
Fluxes, G = 3.03 Mg/m s (BNL Neg. No. 3-1029-79)
5.7 Comparison of Pressure Distributions in Two Experimentsto Show Reproducibility of the Results at High Mass Flux,
G = 4.45 Mg/m s (BNL Neg. No, 3-1028-79)
-iv- ,
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LIST OF FIGURES (Cont'd)
Ficure
5.M Pressure Distributions Showing the Effect of CondensingTank Back Pressure for Identical Nozzle Inlet Conditions(BNL Nes;. No. 3-]031-79)
.
5.9 Photographic Observations for the Experimental ConditionsPresented in Fig. (5.8). In these and all following photo-graphs, the diameter of both the front and rear windows is,
50 mm. (BNL Neg. No. 1-919-79).
5.10 Effect of Mass Flux on Pressure Distributions for IdenticalNozzle Inlct Conditions Ubich are Close to the Onset ofFlashing in the Test Section (BNL Neg. No. 3-1032-79).
T.11 Photographic Observations for the Experimental ConditionsPresented in Fig. (5.10) (BNL Neg. No. 1-922-79).
5.12 Effect of Mass Flux on the Pressure Distributions in thec action (BNL Neg. No. 3-10: 79)Test
3.11 Photographic Observations for the Experimental ConditionsPresented in Fig. (5.12) (BNL Neg. No. 1-918-79).
3.1/ Effect of Nozzle Inlet Temperature at Constant4
(p - p (T )) on the Pressure Distri'sution ing
the Test Section (BNL ':eg. No. 3-1030-79).
5.1 i Photographic Observations for Experimental ConditionsPresented in Fig. (5.14) (BNL Neg. No. 1-921-79).
5.16 Effect of Noze.le Inlet Temperature at Constant(p - p (T )) on the Pressure Distributiong
in the Nozzle (BNL Neg. No. 3-1037-79).
- 5.17 Effect of Nozzle Inlet Temperature at Constant(p - p (T )) on the Pressure Distributiong
in the Nozzle (BNL Neg. No. 3-1035-79)..
5.19 Effect of Nozzle Inlet Temperature at Constant(p - p (T )) on the Pressure Distributiong
in the Nozzle (BNL Neg. No. 3-1034-79).
5.19 Photographic Observations for Experimental ConditionsPresented in Fig. (5.16) and (5.18? (BNL Neg. No. 1-920-79).
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LTST OF PIGIIRES (Coni'd)
Picure
5.20 Effect of Nozzle Inlet Pressure on the PressureDistributions in the Test Section (BNL Neg. No.^,-1036-79)
.
5.21 Effect of Nozzle Inlet Pressure on the PressureDistributions in the Test Section (BNL Neg. No.
3-1023-79) v
5.22 Effect of Nozzle Inlet Pressure on the PressureDistributions i: the Test Section (BNL Neg. No.
1-1025-79)
5.23 Pressure Distributions in the Test Section WhilePlashine Onset is Upstream of the Nozzle Throat(DNL Neg. No. 3-1024-79)
* aDP / '.p U'5.24 Nondimensional Pressure Distribution DP =
oin the Test Section Phile tne Flashing Onset isUpstream of the Nozzle Throat (BNL Nen. No. 3-1026-79)
5 . .' 5 Pressure and Axial Void Fracti n Distributions inthe Test Section. Plot of the difference between thedimensionle..s measured pressure drop and the non-dimensional presau e drop measured in the single
*phase calibration (DDP = DP - DP ) as a function of
a caxial distance (BNL ' eg. 'o. 3-1645-79).
5 . .' 6 Pressure and Axial Void Fraction Distributions in theTest Section. Plot of the Difference Detween theDimensionless measured pressure drop and the non-d tnensional pressure drop measur ed in the single
: *phase calibration (DDP = DP - DP ) as a function of
m c
axial distance (BNL Neg. t. 3-1544-79).,
5.27 Pressure and Axial Void Fraction Distributions in'
the Test Section. Plot of the difference between thedimensionless measured pressure drop anci the non-dimensional pressure drop measured in the single
* *phase calibration (DDP = DP - DP ) as a function of
m ca:cial dist .nce (BNL Neg. No. 3-1643-79).
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LIST OF FIGURFS (Cont'd)
Figure
5.23 Pressure and Axial Void Fraction Distributions inthe Test Section. Plot of the difference between thedimensionless neasured pressure ' rop and the non-dinensional pressure drop neasured in the single
* *phase calibration (DDP = DP - DP ) as a function of.
a e
axial distance (BNL Neg. No. 3-1642-79).
5.29 Pressure and Axial Void Fraction Dist ributions in#
the Test Section. Plot of the difference between thedimensionless measured pressure drop snd the non-dimensional pressure drop measured in the single
*
phase calibration (DDP = DP - DP ) as a function ofn e
axial distance (BNL Neg. No. 3-1110-79).
5.30 Pressure and Axial Void Fraction Distributions inthe Test Section. Plot o f the dif f erence between thedimensionless measured pressure drop and the non-dinensional pressure drop measured in the single
*phase calibration (DDP = DP - DP ) as a function of
n c
axial distance (BNu Neg. No. 3-1131-79).
5.31 Pressure and Axial Void rraction Distributions inthe Test Section. Plot of the difference between thedimensionless measured pressure drop and the non-dinensional pressure drop measured in the single
* *phase calibration (DDP = DP - DP ) as a function of
n e
axial distance (BNL Ne7. No. 3-1112-79).
5.12 Pressure and Axial Void Traction Distributions i t. .heTest Section Nith Flashing Occurring I'pstream of the Nozzle
Throa_. Plot of the Difference Between the Dimensionless
,Ueasured Pressure Drop and the Nondinensional PressureDrop Measured in the Single Phase Calibration,
* *(DDP = DP - DP ) as a Function of Axial Distance,
m ed
(BNL Neq. No. 3-1108-79).
3.33 Pressure and Axial Void Fraction Distributions in theTest Section With Flashing Occurring Upstream of the Nozzie
Throat. Plot of the Difference Between the Dinensionless*!easured Pressure Drop and the Nondimensional PressureDrop Measured in the Single Phase Calibration,
* *
(DDP = DP - DP ) as a Function of Axial Distance.- Lm e c '; L /i G.
(BNL Neg. No. 3-1109-79). 'i J >
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LIST OF FICURLS (Cont'd)
figurc
5. % fop: !!easured Pres,sure (o) and Void Fraction (D) Distrihu-tions in the Converging Part of the Test Section in Runs82/H21 and the Least Square Polynomial Fit to Da t a .
~
F. > t t o m e Calculated :4et vapor Generation Rate Based on the'
Ieast square Fit to the a and p Data. (BNL Neg. No . 3 -12 26-7 9) .
3.35 Top: ?feasured Pressure (o) and Void Fraction (t2) Distri-butlens in the Converging Part of the Test Section in RunsR$/812 and the Least-Square Polynomial Fit to the Data.
I:o t t om Calculated !;et Vapor Generation Rate Based on theLeast-Square Fit to the a and p Da ta . (BNL Neg. No. 3-1225-79).
LIST OF TABLES
TABLE 1 Operational Range of the Facility
TABLE T1 lest S ec t '.on Instrumentation
TABLE ITT Typical Pressure Drop Data
TABLE I; Calibtation Cata for the Test Section BothEmpty (Air), I and Full of Water, I(Date 1-19-79)y, 7
TAELE V Summary of Experimental Conditions
A. Hot and Cold Calibration -
B. Flashing Experiments
IABLE VI Void Fraction Distribution Data -
-vili- .-
C, } J .) U
.
NOMENCLATURE
A,A+ nozzle cross sectional area, and throat area,respectively
C distribution parameterg
D diameter.
DP pressure differential between the test section inlet (tap 1)and a specific tap location along the nozzle. (This difference,
does not include any gravitational head effects.)
* '
DP/LsU', dimensionless pressure dif f erentialDP -
o* *
DP - DPDPP =
m c
C mass flux
g acceleration of gravity
I number of counts for a specific period of time at a givenF.
location while the test section is empty (full of air)
I number of counts for a specific period of time at a givenF
location while the test section is full of water
I,, number of counts for a specific period of time at a given'# location under two-phase conditions
j volumetric flux
L axial length
p pressure
R radial coordinate
T temperature
U test section inlet velocity = G/A po - in in
,
u velocity
V drift velocity of vapor
x quality
Z axial coordinate along the nozzle
0b'-ix- t i )
;n't E!;CL\TU R E (Cont'd)
1 '/o i d fraction
m:isn of vapor generated per unit time per unit volume.,
of nlxture
C density.
attenuation coefficientL ',
a surface tension.
Subscrf>ts
cone mixture
single phase calibration<
et con ter. sing tank (test section discharge)
f saturated liquid
g *;aturated vapor
in test section inlet
? If qt fd
neasure,Ia
;at sataration
va,or<
superscript
* d mensionless-
Symbol
trea averaged quancity<6
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1. INTRODUCTION
Severrl experimental, as well as analytical investigations have been
undertaken to date in order to calculate the discharge flow rates of two-
phase mixtures from pipes, nozzles, and orifices accurately. This problem
-
presents itself tu the safety analysis of water cooled nuclear reactors and
also in the safe storage and handling of liquid cryogens in space appli-.
cations.
During a hypothetical Loss-Of-Coolant Accident (LOCA) of a nuclear reac-
tor, the flow is expc ted to be choked at the break. The discharge flow
rate affec s the heat transfer in the core, the depressurization rate of the
containment vessel, and it dictates the design requirements of the Emergency
Cote Cooling System 'ECCS). Theoretical models have been proposed, and
large computer codes have been developed, to predict the critical f?ow rates
and their depentence on she upst c a .. thermodynamic and flow conditions, as
well as the pipe size and component geometry. At prevent, there is no
general model or correlation for critical flows which considers both thermal
nonequilibrium and relative velocities between the phases and which is valid
for a wide range of pipe lengthe, diameters, and upstream conditions,
including subcooled liquid. A modeling effort in conjunction with
.well-controlled experiments is currently being undertaken at Brookhaven
National Laboratory to investigate and measure the actual vapor generation#
rates under nonequilibrium conditions. The purpose of this report is to
describe the test facility, including the venturi test section and loop
instrumentation, as sell as to present the experimental results and photo-
graphic observat'.ons acquired to date under nonequilibrium flashing condi-
tions. ! !)J s'T> s
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2 REVIEU OF TIIE LITERATURE
Extensive analytical and experimental work has ',een reported on the
two-phase critical flows in the last three decades. Thorough reviews have
been presented by Hsu (1972) and Saha (1978). The latter summarized the.
various available critical flow models and emphasized the ef fects of thermal
nonequilibrium and relative velocities between the phases, which become .
prominent under certain conditions. Jince the objective of the present
research was the determination of the vapor generation rates under ncnequi-
librium conditions, we will concentrate on pertinent experimental work in
the literature.
To study flashing flows and critical flow conditions, researchers have
u.;ed several kinds of test facilities. Some use an upstream vessel con-
taining a saturated or subcooled liquid, which expands and may vaporize in
the test section. Others have used systems where the two phases are gener-
ated separately and then mixed together before being introduced into the
test section. UI.en either system is operated as a once-through experiment,
the flow f rom the test section discharges into a downstream container whose
pressure can be adjusted independently of the upstream conditions. When
either system is operated as a steady closed loop, the control of the
downst ream pressure independently of the upstream conditions becomes more
difficult to achieve due to the hydrodynamic coupling rf the test sectiona
with the loop. In this report, we will consider only experiments conducted,
'.
with subcooled or saturated inlet conditions. The various test sections
investigated to date can be classified as: first, long tubes and nozzles; ,
second, short tubes and short nozzles; and third, orifices.
-2-, r.,
L '|# Q)N*
{.>>
1 ng tubes and nozzles can be characterized by L/D s 40 (Seynhaeve
1977). Sumh experiments were conducted by Ishin, May, and DaCruz (1957),
James (1962), Fauske (1965), Rencreux and ohaeve (1974), Ardron andm
Ackerman (1978), etc. Reocreux (1974) was the first researcher to provide
pressure measurements, as well as void f rac tion Jistrit ..c ionn which allow
the direct calculation of the vapor generation rat n , provided a specific#
slip model is adopted. In all of the experiments conducted with long straight
pipes, the frictional effects are equally important as the vapor g 'nera tion
rate to the enoking condition, and thus the vapor generation ef f e an not
be singled out easily.
Short tubes and nozzles with 1 < L/D < 40 have been extensively luvccef-
gated by Silver (1948), Zaloudek (1963), Fauske anu llenry (1971), and
Schrock, St rknan and Brown (1977). Similar choked flow experiments were
also reported by Simoneau (197 5) and llendrick, Simoneau, and Barrows (1976)
with cryogenic liquids. Although the e:periments in this group with a
converging diverging nozzle can provide information on the flashing incep-
tion, and choking conditions, no detailed void fraction measurements were
performed to allow the determination of vapor generation rates in any of the
experiments in the literature.
Experiments with orifices were usually conducted using orifices with
L/D < 1 placed in a uniform cross section tube, and the j et has been investi-
gated by several authors. More recently, Seynhaeve (1977) measured axial,
and radial void f rac tions of the j et, in addition to the pressure distri-
butions.
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3. EXPERIMENTAL TECllNIQUES
3.1. Flow Loop
'Ibe main flow loop presented in Fig. (3.1) is constructed from "three
inch" nominal (7.6 cm) ,tainless steel pipe. Iligh purity water is circu-
lated through the loop using a centrifugal pump rated at 1500 R/ min at a head ,
of 600 kPa.
Starting from th" pump, the fluid passes through a flow control station
where t r.o flow rate can be controlled from 3 to 950 R/ min and measured with
an accuracy of 1/2 percent of full scale. Excess flow f rom the pump is
directed to secondary loops for cooling, purification and simple Lypass flow
routing. Af ter tite flow .ite is set and measurcd, the fluid passes through
the heater system where up to 520 kW of heat can be added to the water, and
the outlet temperature can be regulated to + 0.3 C over the entire controlled
flow range.
Leaving the Seater systen, the fluid passer through the test section.
A pressurizer is connected to the main loop between the heat c system and
the test section and, when valved in, the pressurizer fixes the inlet
pressure to the test section. Alternately, the pressurizer may be isolated
from the loop and in this fashion, the pressure in the loop is controlled by -
pump ' low rate. Thus, two modes of operation are possible: the pressure9
control'.ed and the flow controlled modes. Once the fluid has passed through
the test section, it enters a condensing tank where a cooling spray is
utilized to condense the vapor and to fix the tank temperature. Since the
pressure in the tank is essentially the same as in thc tuoi section exit,
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L3 r
PURlFIED COOL!NG <U CONOENS:NG' 's
SC HE M ATIC 9 TANKW ATE R TOWER
BNL h'STORAGE
HE AT TRANSFERFACILITY Iggg j s
d' '~-._COOLING
PUMPd T.V.
f FIBER OPTICd L d b*- -
J TEST PROBEq jSECTIONU q
M AKC-UP d'
FLOWO CONTROL-e
9 I3ri i U C
t__ _
HX -
el f ll- ATTENUATION%
I V| FLOW
Y BOOSTER m MEASUREl ' I DENSITOMETER
a 6 >': ,'
PUMP {
| (I"*
PURIFIC ATION - *
]I 2OOkWUNIT
)!I' ' ' 'FILTERS 2OO kW 2 6
I |ABSOR8ER
)|g(OEIONIZER IOOkW|CEO xIDIZ E R
I 20kW )| M@h[ ,T ;' 8
L_-____ _J L120 kW
HEATERS PRESSURIZiR,
M AIN
( "* ' PUYI
:
::.J'
'''Figure 3.1 Schematic of BNL Heat Transf c r Facility
(BNL Neg. No. 1-1246-79).
E
the es :d r ing tank and pressurizer can be used together to fix the pressure
drop a ross the test s tion.
The fluid travels, after leaving the condensing tank, tack to the pump,
and, depending on conditions, cooling wTter can be added to this flow to
prevent cavitation in the pump. Cooling water is provided from excess pump~
flow and is cooled by shell and tube heat exchangers tied to a 730 kW.
cool ng tower,.
purification of the t .u t fluid is accomplished during initial filling
of the test loop. The water is deoxidized, deionized and passed through
0.22 micron filters. In addition, about 40 t/ min of excess pump flow is
passed through the purification station as a polishing procedure during flow
loop operation.
3.2. Test Seccion
The test section is made of stainless steel with a total length of
78.7 cm, including a symmetrical converging / diverging portion of 55.9 cm
length and inside diameters of 5.1 cu at the ends and 2.5 cm at the throat.
The wall thickness varies only from 0.57 mm to 0.60 mm over the entire tube
length. "Intrimiks" were used to accurately map the interior dimension of
TS-2. The data taken have been reduced e.id analyzed and are summarized in
Figs. (3.2) and (3.3). A reference datum was established as the flange face
.
on the inlet to the test section assembly. Figure (3.2) shows the mean
inside diameter plotted as a function of the axial distance from the ref-
erence datum. Each point is the mean of four measurements made at a parti-
cular axial distance with the "intrimik" rotated 90 in each case. The
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b | .1
. . .
Cm
20 25 30 35 40 45 50 55 60 65 70 75 80 852I ,+T'''''T''"''',''''T'''''T'''3~T' ''3''''~T'''''''' T''''T'~'' T "'T ' ~T' ').
|4
!2.0 - I40fffft
\ge" }
/ 15
(4INSf DE DIMENSIONS y ]3.9 * TEST SECTION 2 (TS-2) 4 st ~
) ]1 5
18 - N /,
1
}t ,
I IDEAL DIAMETER FROM DESIGN I " 4D
t.7 -
\ g'SPECIFICATIONS% * ME AN ME ASURED DIAMETER I
j jc 1 T3 2(MAX ME ASURED DEVI ATION I
i U 1 FROM MEAN)j
$.6 \ J qw I
1 402 k |
2 '
11.5 - I 4A a E
o IJ
I|*
y $.4 L 'gI 1
& H 35E 1
1.3 b I 'g
s 11
1.2 -
-
__ 3c<3, 1 <
[N 1.1 -
11
=g/ 1
1.0 f
F l' O{A
vs-l L " ' l " " 1 L-l--l 1 I 1- " J "" "-I" 1"s' m '
O 8 12 16 20 24 28 32
AXIAL DISTANCE FROM REFERENCE DATUM, in.
Figure 3.2 Inside Dimensions of TS-2 (PJ;L Neg. No. 10-243-780)
cm20 25 30 35 40 45 50 55 60 65 70 75 80 65
+ l.O -f/ r T ~T T T i T- F~~'1'' -
<, ,
TEST SECTION 2 (TS-2) !t
!
|i*
..
| i I..
, . . . I Iq
j ~+ 0. 5 -
'
.. l .I*
l l.l *..% *
.I.. .* * * , , * .. . . . .., .'
g .... ... .. .I
,. . .. .-
. - *S. ,A .. . . . . ,
1-
e . ... . .-
js . . -
y: s o _,,-
. . t
_ _ . _ . _ _-
y c ..l. '..gu ..
!,, * *5 *
m, -a . ,
I*gI !ul i.
v ii
i
l 1
- 0. 5 ]g<x e
O icr .
STRAIGHT CONVERCING I DIVERGING STRAIGHT fSECTION SECTION SECTION S ECTION j
6
4
i
1
-J-1.0 Q e ! I I i 1 1- 1 I ' ' ' ' '
8 10 12 14 16 18 20 22 24 26 28 30 32 34
AXI AL DISTANCE FPCM REFERENCE DATUM,in
f
Figure 3.3 Ih vlat ion From Design of TS-2 Inside Dinensions(BNL Neg. No. 10-244-78).
?--
e.
CD * . .
" error bars" show the maximum deviation from the mean encountered at each
point. The solid line plotted is the actual design dimensions for the test
section that were specified prior to construction. A point by point compari-
son of the design versus the measured dimensions is given in Fig. (3.3), and
shows that most of the measured dimensions deviate less than one-half a
percent from the design.
Tha test section design and construction was performed in three levels,
each with an increased complexity in instrumentation. In the first level,
49 wall pressure taps (0.4 mm in diameter) were installed on 1.27 cm center.
along the length of the venturi, in addition to a set of observation windows
located 30 cm downstream of the test section exit, which allowed photo-
graphic observations by flash photography. Taps 1, 2, and 3 are in the
constant area entrance of the converging section, while Taps 47, 48, and 49
are at the exit of the diverging section. If we take Tap 1 as the origin of
the axial coordinate, as designed, Tap 25 is located 30.61 cm downstream.
However, as constructed, the throat determined from the actual diameter
measurements reported above is located at 30.48 cm downstream of Tap 1.
This fact implies that Tap 25 is 0.13 cm downstream of the geometric throat.
An additional pressure tap, 50, is located at 159 cm upstream of the test
section inlet tap 1. The gauge pressure at Tap 50, with + ect to the
atmospheric pressure, is constantly monitored at the control panel, and it
provides the needed information to calculate the absolute pressure at the,
test section inlet within an accuracy of < 1 percent. The temperature is
monitored by means of two platinum resistance thermometers, one located near
pressure Tap 50 for the flow inlet conditions and one at the condensing tank
for the flow outlet conditions.
-9-
:>v|~- f '? ?_ : 1
In the second level, a s.agle channel (i.e., single beam) gamma densi-
tometer which can be traversed virtually everywhere within the test section
was added for chordal averaged void fiaction measurements. As the system
develops, the single beam densitometer will be replaced by two banks of five
beams each for more ef ficient data taking and cross correlation. A statio-
nary hydrofoli-like probe containing ten pairs of local sensors is planned
to be the third level of construction, and it will allow the measurement of
local void fractions and phase velocities across a particular diameter.
To date, pressure distribution, as well as void fraction distribution
data have been taken, and the flashing regimes were recorded photographi-
cally by means of a flash and a still camera arrangement located downstream
of the test section outlet.
3.3. Loop Operation Conditions and Instrumentation
The operational range of the facility is summarized in Table I. The
inlet pressure and temperature can be varied from 100-1000 kPa and from room
temperature to 150 C respectively. The inlet mass flux covers a range of
1.1-7.9 Mg/m s. Theae operation limits cover an approximate Reynolds number
6range of 10 -10 based on test section inlet conditions. The various loop
instrumentation, including ranges and accuracies, are tabulated in Table II.
Pressure measurements are accomplished by means of Statham gauges, cachi
calibrated to an accuracy better than 0.1 percent of the reading. The
temperatures are measured by thermocouples and RTD's, and the flow ra te
measurements are obtained by two Cox turbine flow meters, upstream of the
test section in the subcooled flow region.
-10-'
|o l ' !, ,'
vnL.
.
.
TABLE I
OPERATIONAL RANGE OF THE FACILITY
Test Section Inlet Pressure 100 - 1000 kPa
Test Section Inlet Temperature 20 - 150 C
Mass Flux 1.1 - 7.9 Mg/n s
Reynolds Number Based on10 - 10
Inlet Conditions
I.
Converging Test Section Inlet Conditions FronSubcooled To Low Oualities
.
-11- "; , '. , .f].': i1; ;
TAB LE II
=
TEST SECTION INSTRUMENTATION
QUALITY MEASURED TYPE OF SENSOR RANCE ACCURACY
Temperature Resistance Temp. Detector (RTD) -200 to 500 C 1.2% 0 200 C
Differential Strain Cage Ap Transducer 4 to 500 kPa 1% of ReadingPressure
My Flow Rate Turbine Meter 3 to 950 t/ min 0.5% Full Scale
Void Fraction Gamma Densitometer 0 to 1 5% Steady State(Thulium / Cad-Telluride) (future 5% per
1 ms)
J~~ . _
, r-
C7n
,.:,.* * '
4 DATA ACQUISITION
4.1 General Data Acquisition System
The centralized Data Acquisition and Data Analysis System (DADAS) wast
- designed as a real time digital data system with multiterminal multitasking
capability. The system was constructed around a Hewlett packard 9640 system.
consisting of a 21MX minicomputer with 112 kilowords of central memory, 7.5
megaward cartridge discs, 9 track magnetic tape transport and paper tape
I/0. Central control of the system is accomplished with a CRT terminal
while the 3 satellite stations employ silent 700 terminals. Tabular and
graphical presentat.'n of data is achieved with a Varian electrostatic
printer / plotter capable of listing 600 lpm and plotting 1.6 ips. Interface
of the ADC systems is both direct, an interface per device, and via the
universal interf ace bus, IEEE standard 488.
Three levels of ADC speed and resolution are incorporated within DADAS.
The slow speed, high resolution system employs an integrating digital
voltmeter with microvolt resolution and 300 channel guarded crossbar scan-
*
ner. The through-put rate of this system is up to 18 measurements per
second with high common mode voltage rejection capability. The intermediate
speed system is a 15 bit (+ 10.24 volts) multiplexed ADC with a 50 kHz
through-put rate. The system employs a single programmable gain amplifier
and a signal conditioning amplifier and tilter per channel. The system has*
high common mode voltage rejection capability and can be connected directly
to experiments. The high speed system is also a 15 bit (i 10.24 volt)
multiplexed ADC with a 500 kHz through-put rate. The system has eight input
-13-
E ~7 EJ/s C, q ,;
4
channels with simultaneous sample and hold amplifiers. This system was
designed specifically f or digitiz ing analog tapes.
.
4.2. Static pressure Measurement Set-Up
Each of the 49 pressure taps on the test section can be connected to -
cither of two manifolds, one a common high side the other a common low side,.
via two hand operated toggle valves to the low or high pressure sides of a
nrcssure t ransducer bank. The differential pressure between two locations
along the test section can be measured by connecting the two taps to the low
and high sides of the pressure transducer. Six Statham pressure tranaducers
with the ranges of 17, 34, 69, 170, 340, and 690 kpa (2.5, 5, 10, 25, 50,
100 psi) were connected in parallel to the two pressure measuring manifolds
through two solenoid valves. A third solenoid valve in each transducer
allows the shorting of the high and low pressure lines and thus provides a
means of measuring and monitoring the zero point stability of the transducer
preceding every '.p measurement. The solenoid valves are de-igned for a 200
psi differential pressure and were tested prior to installation. Once the
pressure taps were manually connected to the high and low pressure mani-two
folds, the computer controlled procedure described below was initiated for
the recording of the data.
Each measurement started with the pressure gauge shorted to record the
zero t.p output. The pressure differential between the two taps was then -
measured across the 690 kpa (100 usi) range transducer. Once the pressure
differential was calculated, the system automatically selected a pressure
transducer such that the DP to be measured would fall between 25 and 75
-14-
,,
'I | .
percent of the full range of the particular transducer chosen. With the
chosen transducer, the computer first measured the gauge's zero output when
shorted, then took 20 consecutive DP readings, averaged them, and calcula ted
their standard deviation. The same sequence was repeated once again and the
.
new average of 20 new readings was compared to the last one calculated. If
the two consecutive averages were within one percent of each other, the
measurement was accepted and printed out as a data point. At the same time,
the instantaneous flow rate and other flow variables of interest were also
recorded. On the other hand, if the two consecutive nyerages did not
satisfy the acceptance criterion, the computer repeated this procedure until
the criterion was met or until 15 sets of 20 readings each utre made and the
last output was printed ae the data point. This procedure permitted the
measurement of static pressures with an accuracy of 1 percent of the reading
as quoted in Teble If, It also allowed us to detect the presence of large
pressure fluctuations at the onset of flashing or condensation. At other
locations, such fluctuations were not observed and the readings converged
smoothly. It should be noted that since the pressure transducers were
located at the same horizontal level, gravity effects due to the elevation
difference of the pressure taps were canceled out in the measurements. The
pressure data reported here represent the difference, at two pressure taps,
of the sum of the static pressure and gravational head. A typical output
for an experiment is presented in Table III, which depicts the data acqui-
sition format with the tap identity, pressure data, as well as various other
instantaneous flow parameters of interest.
-15-,
I , a|'f.' .
s r 's
TABLE III
TYPICAL PRESSURE DROP DATA
BNL FLASillNG FLOWS EXPERIMENTPRESSURE DROP DATA FROM
TEST SECTION # 2
RUN NUMBER 74
LOOP FLOW TEMPERATURES (DEG C) PRESSURE (KPA) VELOCITY REYNOLDS DIFFERENTI AL PRESSURITAPS LTR/SEC FLOW METER TS INLET COND T|.:iK TS INLIT COND TANK CM SEC NUMBER MEASURED DIMENS10NLE5
1-3 10.36 9G.3 99.3 87.9 285.9 55.5 510.4 .SG5E+0G .00 .001-5 10.35 96.3 99.3 87.9 284.7 55.5 509.8 . 864 E + 06 2.38 .:?l-7 10.39 96.3 99.4 88.0 284.5 55.4 511.6 .867E+0G 6.21 49l-9 10.37 96.3 99.3 87.8 25J.8 55.4 510.6 .SGGE+06 10.95 .87|-11 10.39 96.3 99.3 87.8 284.6 55.5 511.4 .867E+06 18.39 1.451-13 10.36 96.3 99.4 87.9 284.8 55.5 510.3 .865E+0G 26.64 2.121-15 10.38 96.3 99.3 87.9 284.7 55.5 511.2 866E+0G 36.44 2.39l-17 10.37 9G.3 99.4 87.7 284.0 55.5 5'O.7 .866E+0G 56.23 4.4G1-19 10.36 96.3 99.4 87.6 283.8 55.6 510.1 .865E+06 73.37 5.841-20 10.36 9G.3 99.4 87.9 284.2 55.6 510.1 .SGSE+06 87.11 6.931-21 10,39 9G.3 99.3 87.8 284.4 55.6 511.5 .867E+06 104.25 8.251-22 10.36 96.3 99.3 87.9 284.G 55.6 510.3 .865E+0G 127.88 10.161-23 10.39 96.3 99.3 87.8 285.2 55.6 511.3 .GG7E+0G 147.31 11.061-24 10.36 96.3 99.3 87.8 284.0 55.6 510.3 .865E+06 176.15 14.001-25 10.36 96.3 99.4 87.6 283.5 55.6 S10.0 ,865E+06 209.24 16.571-2G 10.34 96.3 99.3 87.6 284.8 55.8 509.2 .863E+06 696.18 15.661-27 10.39 96.3 99.3 87.9 285.4 55.8 511.5 .867E+06 195.73 15.481-2S 10.37 96.3 99.3 87.8 285.5 55.7 510.5 .SSSE+06 196.05 15.571-29 10.37 96.3 99.3 87.8 285.8 55.8 510.7 .SGGE+06 195.34 15.501-31 10.39 96.3 99.3 87.7 283.8 55.8 511.7 .867E+0G 194.48 15.371-33 10.39 9G.3 99.3 87.9 284.0 55.7 511.4 .867E+06 194.10 15.361-35 10.35 96.3 99.3 88.0 284.8 55.7 509.9 .8G4E+0G 193.55 15.411-37 10.38 96.3 99.3 88.2 285.2 55.7 511.0 .966E+06 193.37 15.331-39 10.3S 96.3 99.4 88.1 285.7 55.7 510.9 .866E+06 192.95 15.301-41 10.34 96.3 99.3 87.8 284.0 55.7 509.4 .8G3E+06 192.72 15.371-43 10.38 96.3 99.3 87.8 284.4 55.7 511.1 .86GE+06 192.72 15.271-45 10.3R 96.3 99.3 88.1 284.6 55.7 511.2 .866E+06 191.99 15.201-47 10.35 96.3 99.3 87.8 283.6 55.8 509.7 .864E+06 191.92 15.29l-49 10.39 9C.3 99.3 88.2 284.6 55.7 511.6 .867E+06 192.15 15.1950-1 10.37 96.3 99.3 88.1 284.5 55.5 510.5 .865E+06 17.94 1.42
mx
h
-16-
~:: :.
C22 . .
4.3. y-Densitometer for Void Fraction Measurements
The single channel y densitometer set up presented in Fig. (4.1) was
used for the void fraction measurements. Thu11um-170, obtained as 99.999
percent pure Thulium Oxide powder, sealed in an aluminum cylinder formed the
,basic material of the y-source. The present source was purchased from
Amersham Corporation and was irradiated at the Iligh Flux Beam Reactor at
Brookhaven National Laboratory. The source strength was kept at a few
millicuries due to the presence of high energy-ac tivity (1.12 MeV), which is
due to trace amounts (s 70 ppm) of Scandium impurity present in the source
material and which caused difficulties from the llealth Physics and Safety
point-of-view. The source capsule is placed in a " lead pig," with a colli-
mator opening of 2.5 mm in diameter, which determines the size of the y beam.
The detector consisted of a Cadmium Telluride crystal (2.5 x 2.5 mm) mounted
on a regular BNC connector. The CdTe detector was connected to "off-the-
shelf" radiation electronic components (Tennelec), consisting of a preampli-
fier (TC 164), a high voltage power supply (TC 948) for the bias voltage
(150 V), a linear amplifier (IC 203 BLR), a single channel analyzer (TC
440), a T 541 Timer and a scaler (TC 540A). The single channel analyzer was
used in the differential discriminator mode of operation and the energy
window was set around 84 kev with a dispersion range of + 10 kev. The TC 541
timer was altered by Tennelee to include time intervals as short as 0.1 msec
and as long as 54 sec. The y source holder and detector were set on a
traversing mechanism, which allowed both axial and radial traverses along
the test section. The axial and radial reposicioning of the y beam by the
traversing mechanism can be accomplished with an accuracy of + 0.05 mm.
-J7-
h / [, bk)
i
.
POWERSUPPLY
n
b 6 AMPLIFIERD00 DETECTOR SINGLE
] O CHANNEL-
LJ A N ALY Z E R"
c-11 "
D D PREg 0 AMPLIFIER ISOURCE g SCALER0 00 o
b TIMER
Figure 4.1 Schematic Representation of Y-Densitometer( B:IL ?le n . '!o . 1-1016-79)
-18-
U. . t u ; . , f'!! Um u,
1
.
The chordal averaged void fracilon were calculated from the following
relation:
I,,
ln J- -
p Im E
a=1- (y)O I
Ec F
in IE
where cx is the chordal-ave. aged void f rac tion, I and I are the numberF. , F
of counts during a preset period of time when the test section is " empty",
i.e., full of air (attenuation due to stainless steel walls only) and full
of water respectively, and I is the number of counts during the same20,
preset period of time under two-phase flow conditions. p is the water
odensity at the calibration temperature, (20 C) and p,m is the water density
>.
at the temperature where the experiment was being conducted.
The calibration of the test section along the axis was performed with
the test section empty and full of water at 20 C (Table IV). F'gura (4.2)
presents the calibration data, as well as the calculated values (solid
squares) derived from the physical measurements of wall thickness and inside
diameter along the nozzle. For these calculations, the attenuation coef-
-1ficients for steel was taken as a = 2.7 cm and for water p =
st w
0.167 ca" both values are listed for a 100 kev y-energy level (Reactor,
physics Constants, 1963). All calculated values were normalized to the
entrance of the nozzle when the test section was empty, which provided a
value of I = 2854 c/54 s. The calibrations were also repeated on different- o
days, and the repeatability of the results are satisfactory, as long as the
source decay is taken into consideration. Radial calibration data were
recorded at a given axial location (Z = 183 mm) and are presented in Fig.
-19- r <,,a f.'- , - Os:'
TABLE IV
CALIBRATION OF Tile TEST SECTION BOTil EMPTY (AIR), I E''"9 FUl.L OF WATER, 1 (Date 1- 19-7 9)
7
i
|i
j "{IA' AXIAL1 ( GT 10 N I counts /54s I c unts/54s LOCATION I c unts/54s I C ""'" "
p E F E( c m) Z(mm)__
:, .1 941 2045 304.8 1239 1856
l n . "3 964 2053 307.2 1286 1944
35.7 976 1994 309.8 1307 2061,
a1.3 1019 2027 312.3 1360 2188
106.7 1017 1974 314.8 1371 2122
'$1.1 1110 2047 317.6 1374 2165
'i.4 1125 2035 319.9 1396 2161i
'32.9 1147 2009 322.5 1419 2220
X3. I 1206 2021 325.2 1427 2199
'13.7 1260 2031 327.7 1406 2189
259.I 1260 1989 330.2 1354 2155
271.8 1328 2060 332.6 1337 2077,
274.3 1337 2062 335.I 1280 2076
276.9 1341 2059 360.8 1210 2025
)79.4 1313 2039 386.0 1 +6 2019
231.9 1338 2031 411.4 1180 2044
'd4. 4 1352 2061 436.8 1113 2013
''37.0 1366 .271 462.3 1081 1989
| '89.5 1378 2101 488.6 1039 2002
292.0 1367 2027 513.1 1003 2011
| 294.5 1355 2063 538.5 1009 2038
I 297.3 1338 2009 563.8 957 2082
| 299.6 1318 1986 576.5 961 2078
! 102.2 1278 1932
I
-20-
r ; ^
'| _ _ ! a' L
.
THROATg TAP N o. 5 10 15 20 25 30 35 40 45 49
iiiiiiii iiiiii iiii iii iii iiii ii liiiiiiiiQ -
a) -
'
2xlO3 4dg _
_
~
$-
EMPTY CALIBRATION (ROOM TEMP.) -
__
cc-
FULL CALIBRATION (ROOM TEMP.) }uJ
l.5x103''
m __
Z - q -
~
o -
au_
_
E5 10 - u -3oo D -[O a
2 i i i i iz 8xlOO 10 20 30 40 50 60
Z- AXI AL DISTANCE (cm)
Figure 4.2 Calibrction of the Test Section Both Empty (Air)and Full of Water as a Function of Axial Distance(BNL Neg. No. 3-1018-79)
',
'! ~. ..-.
(4. 3 ) . The circles at R = 0, which in the axial location, corresponds to
the ca l ibra t ion rmasurement s reported in Fig. 4. 2 a t Z = 18 3 r:m . 1he repro-
duc ibili ty of t he results is very good.
In Figs. (4.2) and (4 . 3 ) , the bars present the standard deviations of
ten consecutive measurements. The accuracy of the system (N 4 percent) is.
1by the stat istical error dI , due to the low rate oftill gov e r n eti I r-e' I
counta which in turn is caused by the low source ac tivity. Increasing the
.curre strength to higher actisity level should improve the statistical
irrors by increasing the number of counts per second.
5 RE'iULTS AND DISCI!SSION
In t his sec tion, results will be presented for the single phase nozzle
calibration experiments, as well as pressure and void fraction distributions
ind photographic observations under various flashing regimes. All the
experi..ents reported herein are tabulated in Table V with their respec-
flux and corresponding condensing tank condi-tive inlet conditions, mass
tions.
5.1. Single phase Calibration
TFe hydrodynamic calibration of the test section was done to Jetermine
the performance characteristics under single phase flow .nditions and to-
obtain the axial distribution of the effective nozzle cross-sectional area.
Three main parameters were varied during these calibration tests: the
,
mass flux (1.6-7.9 Mg/m'sec), the inlet pressure (300-1000 kPa), and the
inlet tcaperature (23-149 C). These experiments covered Reynolds numbers
-22- ,,
b | !- .' fj;)a r
i ___
__ l
2OOO~~
f .-S N_
- .--
-
_
1~~
E MPTY~
-
-
-
.
.
mFULL --
$ !-- --
-T _T -~ h'1 "1 ~~N-_177 -. NN
W -- yg _.
Z l000aOo
.
y-CALIBR ATIONZ = 183 mm
O I I
2.0 0 2.0RADI AL DISTANCE , R (cm)
Figure 4.3 Calibration of the Test Section Both Empty (Air)a nd Ful 1 o f k'a t e r a s a Function cf Radial Distanceat a Fixed Axial Position (CNL Neg. No. 3-1020-79)
-23-,,
} {, U
TABLE V
SL??tARY OF EXPERIMENTAL CONDITIONS
A. (Hl.D ! Il0T CALIIC ATION
.__ _ _ _ _ _ -
et("C)in( C)G(Hg/m s) p! Rl'N p et(kPa) T
in(kPa)T
l_
\
1 ----- ----- ---- --- - - - - -
2 371 26.4 1.56 354 26.3
3 36S 26.8 3.13 345 26.2
361 27.2 4.71 331 26.6..
5 351 27.6 6.28 311 27.4|
6 682 27.7 7.01 647 27.2
7 691 27.3 6.30 657 27.3
h 695 26.9 4.71 652 26.8
9 709 27.1 3.13 674 26.6
10 711 27.0 1.56 683 27.0
11 688 27.7 6.26 632 27.6
12 1033 19.2 7.0i 973 29.1
|13 1031 29.4 7.88 961 29.3
14 337 23.0 6.25 316 22.9
13 343 22.9 4.74 339 22.9
Ia 365 66.3 3.08 309 66.1
37 36, 64.1 1.56 322 63.9I
_____ ____ ___ _____
33 _____
1, 337 94.4 5.49 324 94.5
32 ''7 11.6 4.71 352 12,
33 315 11.9 6.29 326 11.9
3 '4 336 12.3 3.15 369 12.3,
36 293 69.1 3.08 306 68.9
62 692 148.4 2.33 646 148.4
70 213 54.0 3.35 201 48.6
71 211 54.4 3.34 203 48.8
_
-24-
E, } L NDb
B. FLASHING EXPERIMENTS
RUN pg(kPa) Tg( C) G(Mg/m s) p (kPa) T ( C)i
.
20 281. 98.3 4.90 245. 98.2
21 393. 100.6 6.01 136. 100.4
22 170. 100.2 3.04 125. 100.1 .
23 130. 99.4 1.81 121. .3
24 160. 98.0 3.05 122. 97.8
25 247. 97.4 4.52 125. 97.3
26 386. 97.8 6.02 132. 97.7
27 326. 130.0 2.95 299. 129.6
28 566. 131.7 5.90 316. 131.4
29 488. 123.5 5.77 210. 115.4
30 375. 125.1 4.50 206. 1 14.7
31 ---- ----- ---- ---- -----
35 287. 99.4 4.96 250. 99.2
37 296. 100.3 4.94 170. 100.0
38 117. 100.3 2.05 112. 99.8
39 136. 100.5 2.25 112. 100.1
g 40 168. 100.3 3.02 112. 100.0
41 250. 100.2 4.54 115. 99.8
42 194. 99.6 3.79 114. 99.4
43 287. 100.2 4.97 121. 99.9
44 271. 99.9 4.50 10 1. 99.9
45 308. 99.8 4.97 99. 10 0.0
46 223. 99.9 3.79 99. 99.947 ---- ----- --- ---- -----
_
-25-
~f ',,
B. FLASilING EXPERIMENTS
(Cont'd)
i
RU!. p (kPa) T ( C) G(Mg/m s) p (kPa) T ( C) .
F
j 48 183. 99.9 3.04 100 99.9
I 49 146. 99.9 2.27 99 99.7I
50 142. 99.8 2.04 101 99.9
| 51 ---- ----- ---- --- --- -
i 52 381. 123.5 4.48 254 123.5
53 395. 123.6 4.45 249 123.6
54 525. 123.6 5.96 252 123.7
55 293. 123.6 2.99 251 123.6
56 261. 123.2 2.20 252 123.6
57 263. 124.7 2.04 256 123.9
58 254. 123.3 2.98 174 110.2
59 254. 123.1 2.98 174 110.2
60 264. 125.8 2.93 186 112,5
61 259. 123.8 2.98 162 108.8
63 739. 148.7 5.85 464 148.7
64 609. 148.8 4.40 463 148.8
65 ---- ----- ---- --- -----
66 521. 148.8 2.94 463 14 8.8
67 502. 148.6 c.22 463 148.7
68 395. 143.5 1.24 185 118.0
69 399. 144.3 1.23 188 118.5
_
-26-
E ~/ f I', s O' . ~> u .) U.
B. FLASHING EXPERIMENTS
(Cont'd)
RUN p (kPa) T ( C) G(Mg/m s) p (kPa) T ( C)
72 ---- -- - ---- ---- -----
73 275. 99.4 4.90 56. 87.9.
731 281. 99.4 4.88 52. 88.0
732 285. 99.4 4.93 52. 87.9
733* 288. 99.4 4.91 53, 88.2
734* 287. 99.4 4.91 54. 88.0*
735 287. 99.4 4.91 55. 88.1*
736 287. 99.4 4.90 54. 88.0
737* 287. 99.4 4.91 54. 87.9
74 285. 99.3 4.90 56. 87.9
75 395. 99.3 6.04 57. 88.5
761 396. 99.3 6.04 60. 88.7
762 393. 99.3 6.05 62. 88.0
763 392. 99.3 6.06 65. 88.0
77 157. 99.3 3.06 65. 88.7
771 157. 99.4 3.03 69. 88.3
78 138. 99.3 2.61 71. 88.0
782 138. 99.3 2.61 71. 88.1
79 124. 99.4 2.27 72. 88.2
791 126, 99.4 2.26 73. 88.1
792 126. 99.4 2.26 83. 88.1
80 585. 148.3 4.36 436. 143.5
803 579. 148.3 4.32 432. 143.5
81 493. 148.3 2.91 432. 144.0
811 493. 148.3 2.91 432. 144.7
814 492. 148.3 2.91 428. 144.1
82 376. 142.3 2.36 174. 111.6
823 377. 142.4 2.32 176. 110.9
83 352. 140.0 2.30 150. 107.9
833 348. 139.5 2.29 145. 107.1|
_.L
*Runs 731 through 737 are subsets of Run 13 as are other runs in thehundreds subsets of their decade base. -27-
r or ( . (7'
,/ ;- ..,
e
from 9 x 10 to 9 x 10 , based on test section inlet conditions. The raw
data for all the single phase calibration experiments are presented in
Appendix A. Typical pressure drop results with respect to the inlet and as
a function of axial distance are presented in Fig. (5.1) for several flow
conditions. In the converging section, the flow acceleration is accompanied.
by a pressure drop. The deceleration in the diverging section results in an
expected pressure recovery. The unrecovered pressure loss at the nozzle
exit is representative of the friction losses. Figure (5.2) is a plot of
the nondimensionalized pressure drop data obtained from 19 different experi-
ments. The quantities p and U are the density and the velocity at the in-g
let of the test section. The dots represent the average of the pressure
drop, and the bars the standard deviation of all the experiments performed.
This maximum deviation is < 5 percent in the converging section, reaches 6
percent at the throat, and reaches a maxinum of 10 percent in the diverging
section. The single curve corresponds to the pressure distribution due to
acceleration only, and was calculated from the geometrical inside diameter
measurements. This hydrodynamic calibration provides an ef fective hydro-
dynamic area distribution for the test section and will be used for compari-
son with :he flashing data.
5.2. Pressure Distributions Under Flashing Conditions
Referring to a p-T disgram such as that in Fig. (5.3), showing the
equilibrium vapor pressure p of the liquid, the isothermal expansion of
the test liquid in the nozzle may be represented by a vertical line A-B.
Here, point A designates the nozzle inlet condition (p1 ,T1 ) and point B
-28-
b [ I, bi
g(kPa) Tg(C) p (kPa)SYMBOL RUN G(Mg/m s) p,,
O 10 1.56 711 27 683
[] 9 3.13 709 27.1 674
Q 8 4.71 695 26.9 652
A 7 6.30 691 27.3 657x 6 7.01 682 27.7 647
.
FLOW ^ ^ ~ ' ' " ~''"'""''"'" ~~~ ~ ~ ~ ~ "' "''''''''' '" ' " "-
~ ' ' ~ '
PRESS' 5' 9' lh'lY'21 2'5 $9 ' 3' 3 ' 37' ' 41 ' 45' 49' ' ' ' '
$ 0o o o
AAA#
10 0 -*^ 0
a, o,0o og o ,a
xn_ x o a^xa5 x0 0o o x^xa- 200 - xn x _oo a ^xZ x 0Q x x
to 300 - a ^x _
Exg x
0 400 -_
eO- x
500 -_
I ' ' ' ' I600O 10 20 30 40 50 60
AXI AL DISTANCE (cm)
.
Figure 5.1 Typical Pressure Distributions Along TS-2 for theSingle-Phase Flow Hydrodynamic Calibration Runs(BNL Neg. No. 3-1017-79)
h[b ~
-29-
~
TAP NUMBERl 5 9 13 17 21 25 29 33 37 41 45 49
0 i i i i i i i i i i i i i i i i i
,
3 - -
NO '
D-
q.
ca 6 -
hNc.
-o 9 -.
n
c.12 -
15-
-
|8 --
1 I I | |
0 10 20 30 40 50 60
AXIAL DISTANCE (cm)
Figure 5.2 Dimensionless Pressure Distribution for TS-2 Datais Averaged for all the Hydrodynamic Calibration RunsPerformed (BNL Neg. No. 3-1022-79)
-30-
i' () c'
600 i i i I
aINLETo TAP # 25 (THROAT)O TAP 44 24 (l.27 cm UPSTREAM OF THROAT)
500 --
- ^A
.
; 400 --
c.xv
wTD(ntnwC
-a 300 -
LIQUID
0
200 --
oB
.10 0 - -
VAPOR
SAT URATION LINE
' ' ' 'O90 10 0 110 12 0 130
TEMPER ATURE (C)
Figure 5.3 Typical Representation of an Isothermal FlashingExperiment in the n-T Diagram (BNL Neg. No. 3-1027-79)
-31-
1/b bl O .'h
that at the throat. The distance A-B is directly related to the mass flux G
through the nozzle. Thus, for a given inlet condition, the saturation line
may be crossed in the expansion if G is above a certain value,.
Figure (5.4) presents typical pressure distributions obtained at inlet
temperature of 100 C and four flow rates. At the low mass flux. 1.81 Mg/m s.
(Run 23), very little or almost no flashing was observed at all, and the
results are very similar to the single phase calibration data. At the -
highest mass flux, 6.01 Mg/m s (Run 21), the pressure is observed to drop in
tne converging section up to the throat and level off from there onwards in
9the diverging section. At intermediate mass fluxes, 4.90 Mg/m's (Run 20)
2and 5.90 Mg/m s (Run 28) the results show a constant pressure region down-
stream of the throat followed by a pressure recovery region in the diverging
section of the test section. This suddtn pressure increase in the diverging
section is caused by a condensation region to accommodate the back pressure
imposed on the system. The dimensionless form of the pressure drop data
presented in Fig. (5.4) are plotted in Fig. (5.5) vs the axial distance
along the test section. The observations about the pressure recovery
regions in the diverging section mentioned above are more obvious in this
figure. The good agreement of the low mass flux pressure distribution
results with the single phase calibration curve was interpreted to mean that
no vapor was present in the pressure lines after the flashing experiments.~
Similar experiments with flashing flows were also conducted at inlet
temperatures of 124,130, and 150 C for various flow rates and are tabulated
in Appendix B. If one were t7 plot all these experiments on a p-T diagram
like Fig. (5.3), it would be found that the saturation line was crossed at a
-32-
, a
b''f)im:C!',3 i -
c.t.(kPa)in(C)SYMBOL RUN G(Mg/m s) p. (kPa) T pin
Q 23 1.81 130 99.4 121
0 28 5.90 566 131.7 316
A 20 4.90 281 98.3 245
O 21 6.01 393 100.6 136
. ... ~ .... ~ ~ .. ~ .~ ~ ~ " ''' ~'~ " '' ~ ~'- - ~ ~ ~ .. ~ . ~ ... . . .... ..... ..FLOW
.I '7 2,1 !2',5!$9,d3,37!dl 45! 49PRESS''> > > > > > > ,
,
TAP No.o 6o; ## # #
$ ^^^ a0 0
a Oo a O*a o
50 - o a Oo^ o O- oO O AO o a o o oa a a a o,2E o a
1 10 0 - o aoO aE oO aw 15 0 - oe ^~DM ^^^^^^^^^^^^^^^ ^ ^^ ^ n$ 200 -
Z oQ.
250 -
o
| I I 99 9 n b n n n b o o n le
0 10 20 30 40 50 60AXIAL DISTANCE (cm)-
Figure 5.4 Pressure Distributiens Under Flashing and NonflashingConditions in TS-2 (BNL Neg. No. 3-1019-79)
~
L\ ~j' I {,o
TAP NUMBERI 5 9 13 17 21 25 29 33 37 41 45 49
'' ' ' ' ' ' ' ' ' ' ' ' ''''''''''0 % I I I i l
o
3 - 08 O5 -
'o g6 - ff -
woY
% H
-lN 9- -
osL / OO y
o4" 12 -
1
-/o
I1 b 4 oa oo EXP 23 p a a"^"^8^"^^^ -15 EXP 22 i\aO O O O O O _O O O O O O
a EXP 20 i fEXP 21 (
18 -
h-
1 I I I I
O 10 20 3D 40 50 60AXIAL DISTANCE (cm)
.
Figure 5.5 Dimensionless Pressure Distributions in TS-2 UnderF11shing Conditions as Compared to Single-Phase Ilydro-dynamic Calibration Data (BNL Neg. No. 3-1021-79)
'(<
L COC-34- L,f ,
location upstream and close to the throat in each experiment. Thus we
cencluded that in most of the experiments reported, flashing occurred at a
location upstream but close to the threat. In some later experiments, the
flashing front was moved well upstream of the throat.
. 5.2.1. Reproducibility Studies
To check the repeatability of the data, several runs were performed at
nearly identical inlet conditions and flow ra tes. Figure (5.6) shows the
comparison between the pressure distributions obtained in the two experi-
ments for p 168 kPa, T 100 C, and mass flux of 3.03 x 10= =
1
kg/m sec. Experiments were also performed at a higher mass flux 4.45 x 10
kg/m see and T = 123"C and p 390 kPa. Figure (5.7) depicts the=
f
pressure distributions for these letter cases, i.e., Exp s . 52 and 53. The
results at these mass fluxes are reproducible to within 2 percent.
5.2.2. Operational Effects (Effect of Back Pressure)
In one set of experiments, flashing was initiated with the condensing
tank liquid level (defined as the location of the free surface below the top
of the tank) equal to zero, i.e., almost a solid loop condition. Decreasing
the condensing tank liquid level, i.e., increasing the size of the steam
cavity in the condensing tank, changed the downstream (condensing tank)
pressure and affected the flashing conditions and pressure distriubutions
although the flow rate and inlet conditions were held constant. Figure
(5.8) depicts the pressure distribution results for these experiments, Runs
35, 37, and 43. The pressure distributions in the converging section and
mass fluy are observed to be independent of the downstream pressure, whicP
imply that the flow is choked. Run 35 depicts the above-mentioned constant
h 'i b bl [',
-35-
RUN G(!!g/m s) p.in(kPa) in(C)T c.t.(kPa)p
22 3.04 170 100.2 12540 3.02 168 100.3 112
.
FLOW + --
TAPS '1 ' ' ' $ '' ' ' 1'0 ' ' ' ^ 1'S ' ' ' ' 2'0 ' ' ' ' 2'5 ' ' ' ' 3'0 ' ' ' ' 3'S ' ' ' ' /O ' ' ' ' I5 ' ' ' 4 9. m+0+o -b,N @ Na e o,
e
eN- 6 -f4 o Sm s
*O Ol O lo-P- Lco6 6 -
X$ 6 27a o mm .. .
] 3 o o o ],
co -
y- -
N-N ng o
RUN NJMBER SYMBOL- ,_."22 0 ~ c'
5 40 + 2
LN-
w-
|au =W GI I e i r
0.0 10.0 20.0 30.0 40.0 52.2 E0.3AXIAL DISTANCE (CM)
Figure 5.6 Comparison of Pressure Distribution in Two Experimentsto Show the Reproduciblity of the Results at Low Mass
Fluxes, G = 3.03 Mg/m s (P;NL Neg. No. 3-1029-79)
-36-
E, } i bb
2RUN G(Mg/m s) pin ('(Pa) in(C) c.t.(kPa)T p
52 4.48 381 123.5 25453 4.45 395 123.6 249
-
FLOW +
TAPS '1 ' '$''''I'O''''1'S''''2'0''''2'5''''S2''''$5''''la''''IS'''49,e 3 -?
5 E*
ee
e8F_ _ P'
s ac, o3o o
0 1
-P_ _g-^8 DaD o LnD o -
- -
- -o- enx 3~ u> ag4 G
6_ RUN NLMBER SYMSOL yo3 - 52 0 o
j 53 + o Ec
6 6 6 5"+ ++
-ge608 $$ $ o o
Ne o,
N O" C1 I I i i I
2.0 12.0 22.0 33.0 40.0 53.2 62.0AXIAL DISTANCE (CM)
Figure 5.7 Comparison of Pressure Distributions in Two Experimentsto Show Reproducibility of the Results at High Mass Flux,
G = 4.45 Mg/m s (BNL Neg. No. 3-1028-79)
-37-
C,;b! { | ?) ,,
.
,
RtJN G(!!g/m"s) p (kPa) Th(C) p ,kPa),
35 4.96 287 99.4 25037 4.94 296 100.3 17043 4.97 287 100.2 120
; _ _ _ _ - ,
l FLCW +t
'I- T~TP T I I I I i i r I ii1 iiiT I i1 1 i i T T 7 r l ' T TT I 1 T T T T T 1 TT r i T -*
b r.S 1 5 10 15 20 25 30 35 40 45 a9,"-"
,. ,,
a !, u is,N - -s,
e ;
I*
v1 me tu,1 , ~.
N j "sgO o o t 1)
o i m-y g
* *..C- ,
T~5 o o %(U w i -
iD -
m e o
~ , _ i, r'-cx ow- u, i .
g $ n e 9 * * * 0 t '-C9 " +
I RUN NUMBER SYMBOL |y 'N1 35 0g| 37 + j-
43 X:
G4 :e
$ , , , -, -T
2,0 10.2 22.0 32.0 42.0 52.s 4''
AXIAL DISTANCE (CM)
Figure 5.8 Pressure Distributions Showing the Effect of Condensing;
Tank Back Pressure for Identical Nozzle Inlet Conditions(BNL Neg. No. 3-1031-79)
-38-n,
.,
bi''; / ,,
pressure region downstream of the throat followed by a sudden pressure rise,
which seems to correspond to a condensation region as previously described.
Runs 37 and 43 are almost identical although the condensing tank pressure is
lower in Run 43.
The photographic observations perrormed during these experiments are
presented in Fig. (5.9). For Run 35, the bubble sizes are minute, and their
number density is very large. Decreasing the back pressure increases the
vapor generated in Runs 37 and 43. During Run 43, the windows were covered
with a water film, and the interior of the tube was invisible. This drastic
difference in observed appearance between Runs 37 and 43, does not notice-
ably affect the pressure distributions presented in Fig. 5.8.
5.2.3. Parametric Effects
inletThe effects of the flow parameters, i.e., inlet pressure, p.in,
temperature, T and mass flux, G, in the flashing regimes and pressure,
distributions were also investigated and will be presented below. Figure
(5.10) presents the results when p Ind T were kept constant and the mass
flux was varied cloae to conditions of flashing onset in the nozzle. This
is equivalent to lengthening or shortening the line A-B in Fig. (5.3),
moving the point B near the p curve. The pressure distribution in theg
converging part follows very closely the single phase calibration. Down-
stream of the throat the vapor genera tion manif ests itself as a deviation in
the pressure distribution. This region is followed by a pressure increase
caused by the sudden collapse of the bubbles and followed by a pressure
recovery zone typical of single phase flows in divergent pipes. Figure
(5.11) depicts the photographic observations for these two cases. Although
-39-
,I,|.[ 's ! \,
4 Y jgiQ3f gd O U h tdGk [. "A L;::t
r ,
2r
- - - - ,-.
1
#f h.
/ m ; . .. , W. 3- . . <' ,.j.-
g. - ">
s. . wc- . 3..v v t.e *,.,</. ,* a
4rg ; & A.. . .',
p. -,
4,- ( , '
s a g $ .qvy);)._ , p|;.; 31j*
4
4 :/ ec . .m,1
. n--7
' g g, ,
A
md,~ (/ ,kj ,, -,.17\sy,artp"'
rd W 2,
y -
_,4 s
_ _ _ . __ a - _t
A.RUN NO. 35 B.RUN NO. 37
n- _ ___ , -3|
| <
j<
..
/
: b'
.
'
| SCALE 1:1-- ___.~..-a
C . RUN NO. 4 3
Figure 3.9 Photographic Observations for the Expe rimental Cond itionsPresented in Fig. (5.8). In these and all the followingphotographs, the diameter of both the front and rearwindows is 50 mm. (B NI, Ne g . No. 1-919-79).
-/0-4
bfo fi ? c')u/
9
c.t.(kPa)RUN G(Mg/m's) p in(C)in(kPa) T p
49 2.27 146 99.9 9950 2.04 142 99.8 101
.
FLCW -+>~
iIg iiI e i I I i1 I iiii.I ii1 iI i L .I I i 1 iiiI i.I i | I 1 . I ITPP5 'l d 12 15 20 25 33 35 40 45 49
e
"
3 .[?o'e e3-,
$ e s= e s* . .
|++
. +.+o o+
_ +O. g 3 _y
+ 0W gc; + o oC *
O+D D+
-N- ".-o+ +gy gg.
O !+ oo W23 j o o -
u I O O
.."d -
A - rPy
~ ht;
G
RUN NLMSER SYMSOLg m49 0 -
"
m oN 53 + s!!
N ~Emiu3 , o
G1 i i I I i e
2.3 10.2 20.0 32.2 22.2 53.2 62.0AXIRL DISTANCE (CM)
Figure 5.10 Ef f ect of Mass Flux on Pressure Distributions for IdenticalNozzle Inlet Conditions Which are Close to the Onset ofFlashing in the Test Section (BNL Neg. No. 3-1032-79).
-41-
?E / } ~i ?,r / s, ./sJ
b'ET jzw R (O. P) P G|wib (*O h p p?)97 P
4 Jr <- u'. .. 3 % Sq ra
'.
0'b b$ b[M$bbkd Y b
SCALE 1:1-.,_
4
Ce, . , - Q , * 4-
*, [# , <$.
.
. ,. -,- ,
,.v 3L.~
, , f , ;, f* *
}};ff.)>.'~*,;,'%' . . ;
Q *.'' * , ' .?
, , a ' '.. . . . .. K' w|,5 ; ys
.
.- *
- ; . .c. p .,.s. .,...... $ .
. %g %Ltm.
< .
--
RU N NO. 49 RUN NO. 49
, . q;. Oi
'
.. j_
y p n.
A. /* . ,, .- ,/ #
, .ff '*. ..
.' '5:'Qj ;.. p,
_
{ - .,
s.
(O.~
*y3, !d ;:^ ' ; >s ,
g , .jd., 4- "O .g,
' ;{s&.f.P 4,pp61:-t"O. |s-
,- , g ,.
. _. -- -
RUN NO 50 RUN NO.50
Figure 5.11 Photographic Observations for rtie Experimental ConditionsPresented f.n Fig. (5.10) (B';L tieg. !;a . 1-922-79).
-42-
(j k
the appearance of the bubbles was found to be intermittent, this fact was
not apparent in the pressure measurements due to the time response of our
pressure manifolds and to our long averaging times. In Fig. (5.12), we
present the typical effect of a more substantial change in mass flux for an
inlet temperature of 123 C and an inlet pressure of 260 kPa. At a mass flux
Eof 2.04 Mg/m s (Run 57), one observes the onset of flashing, which intensi-
fled to violent flashing at a mass flux of 2.98 Mg/m s (Run 61). The
corresponding photographic observations are presented in Fig. (5.13).
The effect of changing the inlet temperature from 100 to 150 C was
also investigated while maintaining a fixed initial overpressure, p -
g
psn (Tg) . This corresponds to moving the point A parallel to the satu-
ration curve p in Fig. (5.3) and keeping the mass flux unchanged. Forsa
constant values of the pressure difference between the inlet pressure and
the saturation pressure at the inlet temperature, i.e., p -psn (Th) 'g
the effect of inlet temperature on the pressure distributions was not very
pronounced for the various flashing experiments. This behavior was to be
expected , s2 nce the driving potential, i.e. , (p - p ) was not changed in
these runs. Figure (5.14) represents these results for Exp. 67 (T =g
149.2 C, p = 503.3 kPa) Exp. 56 (T = 123.5 C, p = 136.5 kPa) and Exp.g g g
39, while the mass flux is 2.20 x 10 kg/m see for the experimental condi-
tions close to the onset of flashing. The photographic observations for
Exps. 39 and 56 are presented in Fig. (5.15). One observes that the effect
of inlet temperature is small as long as the inlet pressure is adjusted for
constant subcooling at the inlet. The same observation will be valid for
the following results. Figures (5.16), (5.17), and (5.18) show similar
results for progressively higher mass fluxes, and Fig. (5.19) shew
-43-
.'r T7"< r*\ tj | J
h(C) p (kPa)g(kPa)RUN G(!!,;/m s) p T, ,
57 2.04 263 124.7 25658 2.98 254 123.3 17461 2.98 259 123.8 162
i
| FLOW -+'~ ' ~
,
I^PS 'l ' ' ' $ ' ' ' ' 1'0 ' ' '1'5''''I0''''iS''''3'0''''3'5''''4'0''''a'5' '49s s
* k9G A O O O o O O NO
3y O O
| * O| * O
N I g O O N
w]~'
+ O s* *
i y oO | O7 } V T
3-, u, J ,_ g _DU 57yv en~D -
-,
-
QJ -
+4 'N+ * + + . +.. y , . + ,.
-* % ccGS
-J RUN NUMBER SYMBOL _
57 O m~
o 58 + "w;w61 X
. mw- awi ecW Ci i 1 i i ,
1.0 1C.0 20.0 30.0 40.0 50.0 60.0RXIAL DISTANCE (CM)
Figure 5.12 Eff ect of Mass Flux on the Pressure Distributions in thd,Test Section (BNL Neg. No. 3-1033-79) L. | 1
-44-
J[05"(Afki![,,!'CDs [.q ,(,*'r'm, ,)-
, , ,
c '. %n.
% ngt ? -
> o .' . . j i f 'p q !) l, , m,j-- ]f . dq , 1 }'
,4 a 31, , >0 , - . , . pVs f,J' y | } } ! *-| g g..r.-
. <
'4 t|, ,%W N,.'ai t) o;f
.,
it 5 %d ?
- L uy \ ,
. u a
- .' .-
. .g- ~ .:-g,
y M r,. p :' : '
;;a4sp ,- vzy . - e --
$ih :@I|/.-.
-
.i.. .,a s{f' f..eCc.. : - 3|I |'.M '. ' u . ,, f
'
- ,_ ,
.,#,
f .cl g<. [ . r .e ," ',[1 :* * t s4... .
,,
.,P,,' ' _. 4'y g- .
s- ,* .2 . < :-'
t$.n''. '. s . aY . . , - - c+;
^. . ,
b nA_r
n., *: 2c. . . ,e
_
yN, . q g ,m. <j.
, . .c
,, .,
. . :.- ..,1, -
._
twy 11a j , y. . ..
- ,.. ,
. g, < y w +sja;*-,
-
...
T geq;;1a-
t *. t%. - u . Mi '
r7 ::.sfp s O ' -se'
,
.. er 2c., 4_c-
RUN NO.57 RUN NO.57
-. - .. . . . . .
J'#
*A
., . n <gayy Q4,? ~
't
..
y si. a.f. . p. ,gs%.e" 9i<If~2Y*. ' '"
. w n.x A- * \t*g r.
,
~ ,J ;'~{);T, .;;f. ,, e.gy q 1.23 ,-. . .
/re m. %. , rv -;" p > m; e"g.'s{%*-Mrs %v.e .. : ,-
.
, ; ;f, < "
w c e;i; :,:. G;.%, [r\w:v9 is ;y n .I;c. ,
_
. WW '(V |''?).' f?R|W ; MY
"*v
QNU :||.
x 6w :. -fn J.f p:s. - u-:- 37.
A .y .gg-
(. ' .3 \'
SCALE 1:1_
R U N N O. 61
Figure 5.13 Photographic Observations for the Experim. ental ConditionsPresented in Fig. (5.12 ) (B:;I. ',eg. 50. 1-918 79).
:, 3 -
f 1
9
RUN G(Mg/m"s) p (kPa) T (C) p (kPa)
67 2.22 502 148.6 46356 2.20 261 123.2 25239 2.25 136 100.5 112
i ,_ -> r LC, +
IPPS 1 ii$i 12 15 22 25 32 35 42 45 49.1 i iiI ie ..I i ia ! 1 & ii,I I i1 +.I i,I I i | I iiiiI - I i i
a onx 9a-
Wo e-
oa 9 ,N* , go -
IQ * x x r
8 G xm N-
e o x *c3 g c
C 3 x C1 0g
N- - ." .-,
Xy 5 27omI
. a cnx+;+ ~
--
X--; 2h
m- r, ;
C9
RUN NUMBER SYMSOLm m-1 67 o ~
m nN 56 + t"
i 39 X
Pl _:"m
to a,
1 i i-
| T' C-
2.2 12.2 22.2 32.2 42.2 52.2 62.2AXIAL DISTANCE (CM)
Figurc 5.14 Effect of Nozzle Inlet Temperature at Constant
(p, -p (Tg)) on the Pressure Distribution inthe Test Section (BNL Neg. No. 3-1030-79).
-46-
i. . l | ! 'Q,r
|lL .)>
...
.' . > q,J""''
9 0 A.m.t2...' [# i e' NP7gg ,4, . . . . ,,4 - . -e.; >; , ,
> .4 . " * ! i [j g.si
u L ,u - . ,ts
u . . u c.; u a @4 f,
40..sgv~-
SCALE 1:1--. -. .
v 't
,b4 oYtf $*+6g; .;:g s.h' g:.u ,
~NMu% ,hi . i ' .
,.
- .
,, .. . . . .
-.'* ' . .,.'
.h g' ,\b'
:| [ _
*
y g '..*; .
e p ,
t. ,'
. . *..., .
,
. ";% .
, J.y5' . '(?
Vygg_ ?&. ,
R UN NO. 56 RUN NO.56
lX ,19 .:g,, ;
#p ,t?M ,
,
a..
,s_-~. , , ,.
*
. s.,.,
. \.
.; *.
: ,.; -..
' -.
. .t .- =.' .,
.
., ' ** a.* *.>
4s ..
. 7. .e~, . . ..
.. ,.
.ggg g
ggygge ,.
<. .v .e _ ._
RUN NO. 39 RUN NO. 39
Figure 5.15 Photographic Observations for Experimental ConditionsPresented in Fig. (5.14) (BNI. ';eg. ?:o . 1-921-79).
-t7-
i:, ti r',.
m' /_. ,.
')
C.L.(kPa)RUN G(Mg/m's) p.in(kPa) T. (C) pin
66 2.94 521 148.8 46355 2.99 293 123.6 25127 2.95 326 130.0 299
~
'
FLCW ->I I | I i 1 ,I I I I I i1 . 1 I I 1 1 6 ii1 r 1 i i1 I I ii 1 3 1 - 4 I -
ifPS I $1 12 l'5 22 2d c2 35 a2 45 49o Fs} E**3x a N
x'xa 'Gix
3 xv
N_ *s o 1."oUxy o o
O 3 o * OO o i| Tm x x
o |'x
P, 9 o 4L -
) UTXW 0 x
?o 7x
7" 9 2 "W++3D O*
am m
~3
.
- r.,s y_N?a
! RUN NUMBER SYMBOL -
, _ . , '- SS OE0, 55 a-
27 X {,
I N-
wq siy t i:
Se i , ,,
2.2 12.2 22.2 32.2 a2.2 52.2 E2.2RXIRL DISTRNE {CM)
Figure 5.16 Effect of Nozzle Inlet Temperature at Constant(p -p (Tg)) on the Pressure Distributiong g
in the Nozzle (BNL Neg. No. 3-1037-79).
i. i [ \ \)\J ' '-48- g
,
g (C)RUN G(Mg/m s) pg(kPa) T p (kPa), ,
22 3.04 170 100.2 12524 3.05 160 98 122
FLCW +~
TPS l'''5''''1'0''''1'S''''2'0''''2'5''''3'2''''3'5''''la''''I5'''a'9-+o+$+*+b rQ CG +S. G
e
| *
~4 e ."M * 8
o * *
o.T + o 7,
-P-- +, gX$@ LnT+ o
T + o*] +6 $ $ $b ],
c3 -
x~~ '~N sC53 =
,_, RUN NUMBER 3YMBOL._,~~ 22 0 o
G 24 + g
G- ,ou , oa
, , , i a,
2.0 10.2 22.0 32.0 42.0 50.0 62.0AXIAL DISTANCE (CM)
Figure 5.17 Effect of Nozzle Inlet 'Iemperature at Constant(p ~EsM (Th)) n the Pressure Distributienhin the Nozzle (BNL Neg. No. 3-1035-79).
-49-
f)/ [, ()b_
?
RUN G(t!g/m s) pin in(C)# p "c.t.
44 4.50 271 99.9 10152 4.48 381 123.5 25464 4.40 609 148.8 463
--
FLGW + ~
iI I I Ji I iit I i iiiil i I iiiI I | | 1 ii1 e ii1 1 1 i e ] ,[ ,,1 i [v .,S 1 5 la 15 2'O 2'5 30 35 40 45 dC'w" -a n, _Po e oo e o
a
M
w]~
e -m.w" o
g aC O7 7
6-P- _ ~ -
^ !S mcC aw33 4 -
- --
M P' ~w+
-w -
e" 63
3RUN NUMBER SYMBOL- y
w- 44 g a
j 52 + Y t$j64 X 0 2 8 2 * A 6 $ $g x+ 3 + 3x x *~ , ~s- w
2 ER1 i l I i . "
2.0 10.0 20.0 30.0 40.0 50.0 52.0AXIRL DISTANCE (CM)
Figure 5.18 Effect of Nozzle Inlet Ter.perature at Constant(p ~Em (Ty }} on the Pressure Distributionhin the No7zle (BNL Neg. No. 3-1034-79).
-50-
. . , . .
a
!! { {f''- [ f f G. p'0gh
,
j Ub" Dr 00. ,.
u u u t i n g g 'g g
SCALE 1:1
..;w%- ,pa - g_. m ,- -,
7:7*~ W '
%- N~5'%- &:gf 44 e .. + 4% .f.f.fe.hT 31 + 4 . h} .J
-.s .: 5 n
q$.; /ywyk;%.-A
g- ,.
)ps 94:Dh[[;tyrjd
' e .g * ~ .:-
k".twy',,^'yd$;-
.
MkY4-
-iE^'hr4~.grjj'*b@).;-:- y -u $. $
.
2:
h%of ' f.b.Q% ,D.3-v , ,',4 ' {_,,
e.g: .- |. n R |''y * .% . ?' !! -
. .,ah-*
.. ,y ,r 1 s.4
- o-
.
J;Y_' wwm ;. L iu
_
RUN NO. 55 RUN NO.55
g= -
.
n -~- - - g
- o
!"h jnh'* * 5 g. k.g||' h ' 2|$ h p i. f .',&y}jqs0.m z,w. . 1
j,-h$kk,fk-. ye , .. /N4 -
. .. .
V:gi' '?b.. ' ,$ . *: p, -ja y ;7.
- <s gA -
.,4-
< %. g. .~, ; - > s.e. . .e .., .. a, s,
3--
p r m ,.3, . ~msfr% 9g ,, y p A: p . . s.- *. i y. . .n'
'k# YhR }|y {'W;<,]~-{'Y,% . . ,< Q; :.e+ g ,v .
. , - .?:,f''
'
.f. p.,s,$. ,,.%es
: eg 9: . &,#z 2 #p ~s.
' - %*. . . .-c'y:: s<- .., f. .,m..
q,$5, f.[ - g.$y . ,
_ /_ -:17, ,
.
,,
1/&' z--. - -'
"'' N NO. 5 2 RUN NO.52
Figure 5.19 Photographic Observations for Expe, uental ConditionsPresented in Fig. (5.16) and (5.18) (BNL Neg. No. 1-920-79).
,
b'*^
_
photographic observations for Exp. 55 and 52.
Finally, the influence of variation of p i.e., moving the point A in,
Fig. (5.3) up and down without changing anything else, was studied. A
slight variation of the inlet pressure was found to affect the pressure
distributions and flashing regimes for identical inlet temperatures and mass
fluxes. This dependence and sensitivity is more pronounced at low ma ss
fluxes, Fig. (5.20) (Runs 55 and 58 with an inlet temperature of 123.5 C and
2mass flux of 2.98 Mg/m s). A variation of the inlet pressure from 293 kPa
(Run 55 ) to 254 kPa (Run 58) shows a marked variation in the pressure
*distributions in the diverging section of the nozzle. This strong depen-
dence observed for the low mass fluxes does not repeat itself at the higher
mass fluxes, 3.04 and 4.96 Mg/m sec, as presented in Figs. (5.21) and (5.22)
for an inlet temperature of 100 C.
5.2.4 Flashing L'pstream of the Throat
In all the experiments presented above, flashing occurred in the
vicinity of the throat. By controlling the flow conditions, we were able to
approach saturation conditions at the inlet of the test section. The
pressur > J1stribution ru orded under this condition is presented in Fig.
(5.23). The continuous pressure decrease in the convergir.g, as well as the
divergirq cections of the nozzle, '. s reminiscent of ti,e supereritical flows
in supersonic nozzles in classical gasdynamics. The onset or flashing,
which is accompanied with a strong deviation in the pressure distribution as
conpared to the single phase ca lib ra t '.on , is depicted in ris.
*Note tlat in these two ex; e rimen ts, the condensing tank pressure alsovaried from 174 kPa (Exp. 5 5) to 251 kPa (Exp. 55).
' ,'
dO! "-52-
')
RUN G(Mg/m's) pin (kPa) Tin (C) c.t.(kPa)p
55 2.99 293 123.6 25158 2.98 254 123.3 174
.
j
[ FLOW +~
TAPS '1 ' ' ' $ ' ' ' ' 1'2 ' ' ' ' 1'5 ' ' ' ' 2'2 ' ' ' ' 2'5 ' ' ' ' 3'2 ' ' ' ' 3'5 ' ' ' ' 4'2 ' ' ' ' 4 5 ' ' ' 4 9-@ oe 3o e sa s u,
$
eN_ e ."M + Gm a
O o C7 0e
-% -C) -o g
X$ EToT 3 o WD 0 o ooo -
o- -
ca -
.-_'.y~ +++X *y N+ + + + + + + + + ++
i sC53 ~
RUN NUMBER SYMBOL,_.,_.
~~ 55 O "*o 58 + 2
- ~w- -Q
# i I e 1
0.2 12.2 22.2 32.2 42.2 52.2 62.0AXIAL DISTANCE (CM)
Figure 5.20 Effect of Nozzle Inlet Pressure on the PressureDistributions in the Test Section (BSL Neg. No.
3-1036-79)
-53-t r e,,,
b, ._ ) \! -
p (kPa)RUN G(tig/m s) pg(kPa) Tg(C)22 3.04 170 100.2 12548 3.04 183 99.9 100
FLCW +
g iiigiiiiig i i ggi
iiiiiiiii'S'''' 3'0''''3'5''''20''''IS'''492g 2
q+0+g go e sN G N
e
eN e "
.
" o CCD C
O ' O~D o Te
[g __m_lytX$ o
T o + W+
g+e e G G 9o _. _-
1, 0 =a =
RUN NUMBER SYMSOL_g _
22 O N'~
S 48 + g
- Nw- ow -
COI i i 1 I ,
2.3 12.2 20.0 30.0 42.0 50 0 62.2AXIAL DISTANCE (CM)
Figure 5.21 Effect of Nozzle Inlet Pressure on the PressureDistributions in the Test Section (_BNL Neg. No.3-1023-79)
-54-. , , ,
J
4
2RUN G(Mg/m s) pin (kPa) Tin (C) c.t.(kPa)p
45 4.97 308 99.8 9937 4.94 296 100.3 17043 4.97 287 100.2 121
FLOW + -
TRPS l'''d''''1'2''''l'S''''2'0''''IS''''32''''3'5''''/0''''25' '49'
-e e* --"6*
@" es
a
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N Ce ca OT T
- ~ 5- -
m-y.70 Do
o LD23
"_ D 2x -~m'
I~wgw 1a$ 5 $ $ $ 8 8 $ $ $ $ $ 5"
RUN NUMSER SYMSOLyN" 45 0 -y
'
?, 37 4 s'43 X
Ne -gw|Q G
c'. 2 1a.2 2a.a iz.a 4a.a s'a. a g'a. I'
AXIAL DISTANCE (CM)
Figure 5.22 Effect of Nozzle Inlet Pressure on the PressureDistributions in the Test Section (BNL Neg. No.
3-1025-79)
-55-
L r ..)!o U0u
2
c.t.(kPa)in(kPa) Tin (C)RUN G(Mg/m s) p p
69 1.23 399 144.3 188
-
FLOW rf
TAPS l ' ' ' $ ' ' ' ' 1'0 ' ' ' ' 1'S ' ' ' ' 2'0 ' ' ' ' 2'S ' ' ' ' 3'0 ' ' ' ' 3'5 ' ' ' ' AO ' ' ' ' IS ' ' ' 4 9o+ =mm , , , _.
I2 # 52MU 5 Q
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i
y_ RUN NUMBER 69 _ ;;;,
E 8
5- -nw ;
CI i i i i
3.0 10.0 20.0 30.0 I0.0 50.0 60.0RXIRL DISTANCE LCM)
.
Figure 5.23 Pressure Distributions in the Test Section WhileFlashing Onset is Upstream of the Nozzle Throat(BNL Neg. No. 3-1024-79)
-56-
t,I (10t
/
(5.24). This pressure distribution plot nondimensionalized with the inlet
dynamic head of the flow provides an accurate way of determining the onset
of vapor generation. For this experiment, it was found that flashing
started near pressure Tap 13 (15 cm upstream of the throat).
5.3 Void Fraction :teasurements Under Flashing Conditions
The axial distribations of the diametrical aieraged void fractions were
also measured together witii the static pressures under various flashing
conditions and are presented in this section (Table VI).
5.3.1. Flashing Close to the Throat
Figures (5.25A) and (5.253) present the results for an inlet temperature
and pressure of 99 C and 394 kPa and a mass flux of 6.05 Mg/m s. The
pressure profile is constant in the diverging section, and th< .id profiles
follow an alioost linear variation in Fig. (5.25B). The (+) symbols are the
void fraction data, and the crossed circles in Fig. (5.25B) give the dif-
ference between the two-phase and single phase dimensionless pressure
distributions. The dimensionless pressure was defined as the local pressure
*drop divided by the inlet dynamic pressure of the flow. DP is the dimension-
m
,less local pressure drop with respect to the nozzle inlet measured under
flashing conditions and DP is the corresponding pressure drop measured
during the single phase calibration experiments. The onset of flashing can
be determined either from the void fraction measurements or from the point
of departure of the dimensionless pressure distribution from the single
phare calibration curve.
Reducing the mass flux to 4.91 Mg/m s and to 3.06 Mg/m s while keeping
-57- y <
itn'
p (kPa)RUN G(tig/m s) p g(kPa) Tg(C),
69 1.23 399 144.3 188
_-
FLCW +1 I I T T T~T I I I I i i i i I i I i| | 1 iil i TT I i i i i iT i i TT d
ihPS 1 ITTd1 10 15 20 2'S 30 35 40 45 49' = - -am a- a_ ,-_ , . . . . - ,--c.- .
,_-~ x
*i
a3 _ ,
ou
x
0-~ U ol - x5 s
NM
.8, Mx.. m ~ * *N,' , u , e
N |i
I
gj _ RUN NUMBER 69iI
ruN j
Iis ;u-
,
D -r i i i . 1
0.0 10.0 20.0 30.0 40.0 50.0 60.0
nXI AL DIS fnN(:E { EM ) -
* 9
Figure 5.24 Nondimensional Pressure Distribution DP = DP/lp U'gin the Test Section While the Flashing Onset is
Upstream of the Nozzle Throat (BNL Neg. No. 3-1026-79)
-58-
.,,.*I () i)
TABI.E VI
Vo1D FRACTION DISTRIBUTION DATA
FIASIIING EXPERIMENTS
RUN p (kPa) T1 ( C) G(Mg/m s) p (kPa) T ( C)
730 285 99.4 4.91 54 88.0
740 285 99.4 4.91 54 88.0
762 394 99.3 6.05 61 88.3
770 157 99.3 3.05 67 88.5
771 157 99.3 3.05 67 88.5
780 138 99.3 2.61 71 88.1
781 138 99.3 2.61 71 88.1
792 125 99.4 2.26 76 88.1
793 125 99.4 2.26 76 83.1801 582 148.3 4.34 434 143.5
802 582 148.3 4.34 434 143.5
812 493 '48.3 2.91 431 144.4
813 493 14 .3 2.91 431 144.4
821 376 142.3 2.34 175 111.3322 376 142.3 2.34 175 111.3
831 350 140.0 2.30 147 107.5
832 350 140.0 2.30 147 107.5
-59-
" 'f. 1
lij
.-
FLOW +
igir iig,,,iiiii1 ' 2 2 ' ' ' ' 2'5' ' ' ' i2 ' ' ' ' IS' ' ' ' la ' ' ' ' AS ' ' ' 4 91 1 gs ., -Pg .'''... g
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RUN NU"SER 761 P5AT 2.............'c- 12.8 LPS .... ... "
99.3 DEG C .
355.4 kPA TS INLET _mw"~- E3.3 KPA CON TANK h
| uuN i i I i i i
g
e.e 1e.e 2a.e 32.e ee.e 52.e 62.cA. AXIAL DISTANCE (CM)
-
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TAPS ) ' ' ' $ ' ' ' ' 12 ' ' ' ' 15' ' ' ' 2 2 ' ' ' ' 25' ' ' ' $2 ' ' ' ' 35 ' ' ' ' /2' ' ' ' /5' ' ' 4 9:1 -(-..............mnT!??[I}'.{IIII
G : ::::: I ! IzI:
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.o .@ - ~,Tis
N ' & p]6 m 71+
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5- . ng, ++, + + + + a,
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aj - + RUN NUPSER 762M RUN NUMSER 761y
o , i , i i 1
12.0 22.0 ?? O 40.2 52.0 62.2B. 0.0 AXIAL DIS!ANCE (CM)
rigure 5.25 Pressure and axial void fraction distributions in the test sec-tion. Plot of the difference between the dimensionless measured pressure
drop and the nondimensional pressure drop measured in the single phase* u
calibration (DDP = DP - DP ', as function of axial distance.m <_
(BNL Neg. No. 3-1644-79). -60-
E|I . C (-f /,
the inlet temperature co1stant S 99 C we obtained similar results, which
are presented in Figs. (5.26) and (5.27). The onset of flashing is close
to, but upstream of the nozzle throat. The linear variation of the void
f raction with axial distance in the diverging section, combined with the
constant pressures observed in Fig. (5.26A) and the fac t that the test
section diameter also varied linearly, seems to imply the presence of a
nearly constant area liquid j et at the core surrounded by a steam envelope.,
When the mass flux is further reduced to 3.05 Mg/m~s, the pressure profile
in the diverging section ctarts to show a slight recovery (Fig. 5.27A),
which is accompanied in the void fraction profiles by a region where the
voids are constant (Fig. 5.27B). If one still reduces the mass flux to 2.61
Mg/m s, the pressure distributions observed in Fig. (5.28A), show a sudden
pressure recovery in the diverging section which may be considered as a
condensation front. This fact is clearly observed in Fig. (5.28B), which
shows an increase in the void fraction followed by a decrease to the all
liquid situat ion. The dimensionless profiles of DDp plotted on the same
f i c,u r e also show the pressure deviations from the single phase calibration
which closely follow the evaporation and conder.sation f ronts. Still low-
ering the mass flux to 2.26 Mg/m e brings us to a situation which is close
to the onset of flashing. Figure 6.29A) depicts the pressure distribution
which is very close to the single phase calibration results, and the void
fraction distribution presented in Fig. (5.29B) shows a very slight rise
close to the throat, but otherwise remains mostly liquid throughout the test
secticn. A similar sequence of events was also observed in experiments at
an inlet temperature of 148.3 C for two mass fluxes 4.34 Mg/m s (Fig. 5.30A
and 5.30B) and 2.91 Mg/m s (Fig. 5.31Aa and Fig. 5 ?lB). The high mass flux
-61-.. |i st
,
'i \; ,
~
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ThP5 1 ' d ' ' ' ' I'0 '''15''''ia''''IS''''I2''''IS''''la''''/5'''49n_ ."
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7, " 2w-
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, cdcn 10.4 LPS
93.3 DEG Co 284.6 KPA TS INLET ~
_9"" 55.6 KPA CON TAN < nw U4
i i i IG)
0.2 10.0 22.2 32.0 42,0 52.0 62.2
A. AXIAL DISTANCE (CM)
FLOW +
ws i ' ' ' d ' ' ' i e' ' ' ' i s' ' ' ' 2e ' ' 'is' '"se' ' ' 'ss' ' ' ' 4 e""is' ' ' 49~I! IIIIIsissiirit I IIII I-N
nl. -...........azier: 3
- ~ifa
|!
- - , m
5._' _.gi=
r.n
a
or3 , "
k;s ~ e" f,- -.
.- I
.
[y- ".* P*
=re .,,
= *wc| '_. .
.,
l
L5"'
5{ *. '. . . ;. p,- 3. .
... c.,
., . , ,
o; . ,
I+ RUN NUMETR 742
';p| M Ru'J NU'arER 74 |,,c . ,- - , , , , ,
P0 !/.? 22.0 32.0 47.0 52.0 62.0B. Ax!pL DISTANCE (CM)
Figure 5.26 Pressure and axial void fraction distri~uutions in the test sec-tion. Plot of the difference between the dimensionless measured pressuredrop and the nondimensional pressure drop measured in the single phase
* *calibration (DDP == DP - DP ) as function of axial distance.
m c c , ,
I t,'y ','(BNL Neg. No. 3-1645-79). ,
-62-
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iiiii.5 22 25 32 3"5 . i iiit iii1 iii 1 r 1 1 i>>> t iitrTr4ii1 12 1 42 45 49if.PS 1
Pm. . * ... yy c-o =..,
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, r.
.u,
t.e : .e ::.e ,:.: 42.c s?.: s2.
A. p .y t. a. '._ n '. . n "uc ( r v. ). m o
--m
F, rto 4N._' --~ '
ii.n1 i i i .iTT i ii i . : T , rry
M 7TTTriie is ze 2,s 32 35 a es a ..tres i~. .......:. .....,, !,- ,,. . 1 .,1 ,1 : , : 1 ... 2 ,
a. r _:
, -.
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I- * o.
,
-
:: i m-
.
.1
-
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;, oa.- , -.
. = F-. .u ;; .,,
.....~ ? ?." -
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...N
P,i .s. . -m . > -:.~ ..,- - -. . . .
,, . .
c. i. ..
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| M PGN Nu-SER 77 | I
~ , JlQ q- -__.-.~~T
e.e u.e z?.e : .a u.e s .e c:.B. AXIRL DISTANCE (CM)
Figure 5.27 Pressure and axial void fraction distributions in the test sec-tion. Plot of the difference between the dimensionless measured pressure
drop and the nondimensional pressure drop measured in the single phase* *
calibration (DDP = DP - DP ) as function of axial distance.a c ci, , I. u -(BNL Neg. No. 3-1643-79), i //-63-
FLOW +
TAPS 1 ' ' ' $ ' ' ' ' I'0 ' ' ' ' I'S ' ' ' ' 2'0 ' ' ' ' 2'5 ' ' ' ' 3'2 ' ' ' ' 55' ' ' ' l0 ' ' ' ' /5 ' ' ' 4 9 o"- .
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m
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m 137.7 KPA T5 INLET e ~"co ' 71.2 KPR CCN TANK
U'oI J I I i I
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A. AXIAL DISTANCE (CM)
-
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l ' ' ' $ ' ' ' ' I'0' ' ' ' I'S' ' ' ' 20' ' ' ' 2;5' ' ' ' 3'2' ' ' ' 55' ' ' ' /0' ' ' ' IS' 49TAPS
s =...InntIf.[{l!!IIsaix: Is1IIrIsiJ-5* -...--m n ~-
e ...
",a smm
-
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, a,,
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EIm
- y.~- ,
n ,
a ++
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g., + , , , o4*+,+ + ++ . .
na
y, + RUN NUMBER 782M RUN NU-0ER 782
,,o , i
, , . i
0.0 10.0 22.2 32.0 22.0 52.2 52.2
B. AXIAL DISTANCE (CM)
Figure 5.28 Pressure and axial void fraction distributions in the test sec-
tion. Plot of the difference between the dimensionless neasured pressuredrop and the nondimensional pressure drop measured in the single phase
* *calibration (DDP = DP - DP ) as function of axial distance,
m c
(BNL Neg. No. 3-1642-79). -64- (,El. u ./U7 / ,,i
-
_~
FLOW +
TAPS l'''$''''I'0''''1'5''''2'0''''25''''ia ' ' ' ' iS' ' ' ' la' ' ' ' i5' ' ' 4 9G_ -?
@ '''s,, O'
,*._==., ,,.....'
. 's a" s M" 2g ..
a a=' ", IT PSAT .''
-N_ . " -@ LA
Tx4 eSo ,8
~D ewW
* ,. _ -?* -
g- . .
O E
on , .mg RUN NUMBER 79 2
4.8 LPS99.4 DEG C
m_ 124.3 KPA TS INLET _;;72.0 KPA CON TANKg y
G, i i i T i
10.0 20.0 32.0 42.0 50.0 62.0A. 0.0 AXIAL DISTANCE (CM)
I
FLOW + ,
TAPS l'''$''''I'0''''1'5''''iO'''MN'''Sa''''iS''''/2''''IS'''I9f'Ifffff5fI }&IIIIIIIIIIffI!!?i 5fi f "- (G su s=8 af t-.me
= -. ~.
.
~. _?o Dis
O GmIJ. - - en p~ '12 m r-
TI
o DN- - oNm
.?,d M' ' ' ' + * . . . _g-g_ . . . . .. . , ,, =,G
RUN NUMBER 792y_+ RUN NUMSERM 79y
u , , , , , ,
0.0 10.0 20.0 30.0 40.0 50.0 E0.0B. AXIAL DISTANCE (CM)
Figure 5.29 Pressure and axial void fraction distributions in the test sec-tion. Plot of the difference between the dimensionless measured pressuredrop and the nondimensional pressure drop measured in the single phase
* *calibration (DDP = DP - DP ) as function of axial distance,
m C
(BNL Neg. No. 3-1110-79). -65- L,..
U / ,'! -.r
-
FLOW +
l ' ' ' $ ' ' ' ' I'0' ' ' ' I'5' ' ' ' 20' ' ' ' IS' ' ' ' ia ' ' ' ' iS' ' ' ' /a' ' ' ' /5' ' ' 4 9InP5m
-"g-= ===.., g
= = . , " . , ,=
E G~*
N- Eg g
~e . OO a xT
* ~"n .
m~
g3z, esm -
'u .-......,.....aa===" .m... -D .
_,
,m-2-m
e .o
-$9
"1 RUN NUMEEH 82 ea*
S 9. E, LPS
148. 3 DEC C~_ SES.1 KPd 15 ItLET -p" 435.7 nF4 EON LANK n
$ Gi
, , , i i
e.e i2.e za.e 3a.e 40.e Sa.e 60.e
A. AXIAL DISTANCE (CM)
-~
FLOW +
77,4,iiir}0''''I'S''''I0'''''S''''I2''''iS''''la''''/5'''49'
E'q.========a..avesttsg{} jtg: 13: ::: 33: 3:1: 13 2 ] -[U
.
*w - E , _._
* *.ca *+e2 m
.
= .
sO .m n .O.- ,p70 " . . "
G r-7
""m,,,"" 1* ==".=,,.n D* a
_ ** ~~N' .s., .* **ea
d.~
..., - o. . .
_m- - n, ,,
ao
g- + RUN N'JMSER 801M RUN Nur8ER 80
go , , , , , ,
0.0 10.0 22.0 30.0 40.0 50.0 00.0B- AXIAL DISTANCE (CM)
Figure 5.30 Pressure and axial void fraction distributions in the test sec-tion. Plot of the difference between the dimensionless measured pressure
drop and the nondimensional pressure drop measured in the single phase* *
calibration (DDP = DP - DP ) as function of axial distance. . , ' ,
m C 11 .
(BNL Neg. No. 3-1111-79). -66- 'I!'
FLOW +
l'''d''''I'0''''th''''70''''/5''''s0''''iS''''/0''''/5'''49TRPS *m -
g- == ..,, ,u
==,,*s,u
e"'uN. i
E$ PSAT ", =,=''' Oaa ,m". 0ap
*.m _. .mP. guqo ,.. .
u>o .~
D a -.
_ ~
m Ng g- g'~wo
-
C- 1m
RUN NUMBER 81 I m, Sw 6.4 LPS
148.3 DEG Cm493.4 KPA TS INLET
432.3 KPA CON TANK I"v-
""lcw G
W i i , i i i
0.0 10.0 20.0 30.0 40.0 52.0 60.0A. AXIAL DISTANCE [CM)
FLOW +
l ' ' ' $ ' ' ' ' I'0' ' ' ' I'E ' ' ' 'ia ' ' ' ' I5' ' ' ' 38 ' ' ' 35 ' ' ' ' ia' ' ' ' /5 ' ' ' 4 9TRPS: : : I !: I: III13 1g-.====um==mgn==sevffff ! ]IIII :S
o e n ou
"s
;- -' s
,,..-
.
_ _____
sO -mO- - m I
N r-ygOIDn
-
- .
y~ . . ___.-,
+. . .g *+.. .
f.rC? ~. ;+ . . mm-. . .
. *.m
o
g_ + RUN NUMBER 812A RUN NUMBER 81g
m i , , , ,
10.0 20.0 30.0 40.0 50.0 60.0B.0.0 AXIAL DISTANCE (CM)
Figure 5.31 Pressure and axial void fraction distributions in the test sec-tion. Plot of the difference between the dimensionless measured pressure
drop and the nondimensional pressure drop measured in the single phase* *
calibration (DDP = DP - DP ) as function of axial distance,n c
(BNL Neg. No. 3-1112-79). - 67 - r - .c,
t t ,, u-
I! ti / i
run presented in Fig. (5.30A) and (5.30B) shows an almost constant pressure
distribution in the diverging section with a steeper rise in the void
fraction profiles and higher void fraction values at the exit of the nozzle.
The i mass flux run presented in Fig. (5.31A) and (5.31B) depicts a
vaporization zone in the diverging section downstream of the throat followed
by a condensation region which reduces the void fraction (Fig. 5.31b) and
causes a pressure recovery close to the test section exit (Fig. 5.31a). -
5.3.2. Flahning Upstream of the Throat
Additional data was also recorded with the flashing front upstream of
the throat. Figures (5 '2) and (5.33) present the results for two mass
fluxes 2.34 and 2.30 Mg/m s at an inlet temperature of 140 C. Figure
(5.32A) depicts the pressure distribution for which Fig. (5.32B) presents
the void fraction profiles. The pressure distribution shows a decrease in
the converging, as well as in the diverging sections of the nozzle. How-
ever, the slope seems not to be continuous at the throat in contrast to what
is usually presented in the literature. The void fraction profiles show
that at the test section inlet, the void fraction was around 10 percent, and
the vapor generation increases along the test section, causing a void
fraction of almost unity at the exit of the venturi. The DDp plot shows
clearly the drastic deviation of the dimensionless pressure profiles from
the single phase calibration curve. Figures (5.33A) and (5.33B) present
similar results obtained at a mass flux of 2.22 'l/m s and an inlet temper-
ature of 140 C. The results of those two experiments were used to cal-
culate the net vapor generation rates under nonequilibrium conditions, and
the methodology followed will be presented in the next section.
-68-
-.-
1/' - : t ('
lUU' "
-
FL0u +-
PSATTAPS 1'''$ 'I'O''''th''''iO''''IS''''I0''''SS''''/0 ' ' AS' ' ' J9'
*o" """ "a s m
ea,,=.. cae2
s.,"
= *", .is- *
caM e Oo
T m.,- - "=,, -5-m
Dx3 . m
a u Ui] n=, -g
_-, , ,- -
~Ug
~ E
["
- ia
0- ."a
-a;- .,= n
RUN NU".8ER 823 ms. cain 5.0 LPS
142.4 DEG C377.0 KPA TS INLE1 _g
~
-'# 175.6 KPA CON TAW 2e . , , , , ,
0.0 ie.0 20.0 30.e 40.0 50.0 ce.0
A. AXIAL DISTANCE (Cri)
FLOW +
l ' ' ' s ' ' ' ' I'0' ' ' ' I'S' ' ' 'I0' ' ' ' 2'S' ' ' ' 3'0' ' ' ' 3'S' ' ' ' /0' ' ' ' /5' ' ' 4 9 _TAPS
Jr....-m........m s...mg;=1........---.-----..+.-.- yG+ + un
U N 4m *~m, ,
-
'm. - f*~- + yW*u,
=m+" " m
o ,,O- =,"
- ,Dm
+ ca r~) g "8,
+ mi- "O3
+ *Y 13x c3
./ - - m- cno- .'p*g+ wno
+ + + +,
+ + +* * _.co _ N
O fJCa
g_ + RUN NUMOER 821X RUN NUMBER 623y
ea , , , , , ,
10.0 20.0 30.0 J 2. 0 50.0 60.0B. 0.0 AXIAL DISTANCE (CN)
Figere 5.32 Pressure and axial void fraction distributions in the test sec-tion with flashing occurring upstream of the nozzle throat. Plot of thedifference between the dimensionless measured pressure drop and thenondimensiona) pressure drop measured in the single phase calibration,
* *(DDP = DP - DP ) as a function of axial distance (BNL Neq'. No,
m C-69- ) ,;3-1108-79). r '. ,. i
FL0u +
,3 i,igiiiiiii1 . g i i ijgi i i i iS' ' ' ' 3'0' ' ' ' IS' ' ' ' i0' ' ' ' /5' ' ' 4 9g
,ea,- == ....,,==.., ,
oa
*a,.
F- ". ."*
u " cam O
O , TT
-?~n Y-xg
". , g m,u..v e-*e
n,=m, _-D-
,- ==, ~N[ * *
-m * *=O ' m e,
E e*irm~_
RUN NUMBER 833 nm Gw 4.9 LPS
139.5 DEG C347.6 KPA TS INLET _g
~" 145.2 KPA CON TANK ,
2 =i i i i
, .
e.e 10.e 20.0 30.0 40.e 50.0 60.0
A. AXIAL DISTANCE (CM)
--
FLOW +
s ' ' ' $ ' ' ' ' l'0' ' ' ' l'5' ' ' ' I0' ' ' ' I5' ' ' ' 3'0' ' ' ' 35' ' ' ' /0' ' ' ' /5', ' ' 4 9 _IAPS
G......................n;.................s.....,ny ,
.E
_ .ea+
_
_m .
d= +mu .
u+ m
O ,
-k ny "O- ,
= ca r7g ,u 7*
g.*/ {.L * ==,s G+ +. p
~ y=~w~ * ,
,**o' . . ,"n a,,## + + . +. ,uIl G
". . esca
"ac
m ., + RUN NUMBER 831
g X RUN NUMBER 0331 i i g y g
0.0 10.0 20.0 30.0 40.0 50.0 60.08. AX1AL 015TANCE (Ct1)
Figure 5.33 Pressure and axial void fraction distributions in the test sectionwith flashing occurring upstream of the nozzle throat. Plot of thedif ference between the dimensionless measured pressure drop and thenondimensional pressure drop measured in the single phase calibration,
* *
(DDP = DP - DP ) as a function of axial distance. (BNL Neg. No.m c
-70- E, 7 i ;n-3-1109-79). i) ..<- t
5.4 Calculations of Net Vapor Generation Rates Under Flashing Conditions
In this section, we shall present the method with which a cross-section-
averaged net vapor generation rate per unit volume r may be determined from
the measured pressure and void fraction distribtulons along the test sec-
tion. We recall the following definitions of cross-section-averaged quanti-
ties.
.
Mixture density,
>+ < (1 - a) o > (2)<p> = <apv 2
tu ss flux of vapor,
(3)<G > = <ap u>v vv
Liquid mass flux,
<G ) = < (1 - a ) p u> (4)7
Total mass flux,
<G> = <G > + <G > ( 5)v t
Total volume flux,
<j > = < au > + < (1 - a ) u > (6)
Quality,
< x > = (G > / <G> (7)v
We shall assume that the densities p and p of the vapor and liquidg
.
phases are given by the saturation values corresponding to the local pres-
sure p, and therefore, are constant over a cross-section. Moreover, we
' L.-71- '
chall assume that the vapor drift velocity
= u -j (8)Vgj v
is also constant over a cross-section. Combining Eqs. (7) and (3) and using
the drift velocity, Eq. (8) we have
<x> <G> = <ap j> + <ap V >
(9).
=p (<aj> + <a>V ).
<aj >/<a> <j >, we may writ eIntroducing the distribution parameter C =g
<x> <C) =p (C <a><j> + <a>V )
which may be expressed as
-.
<1 - x><G><x><G><xy <G,> = p <a> C + +V ,
y o p p gj ,_
when Eqs. (6), (3), and (4) are inserted. Solving for the cross-section-
averaged quality <x> and replacing the liquid and vapor densities with their
saturation values, we get finally
.
-72-
r,*i- ,,
' ? *N
- p p V ~<a> C E+ E E3
op <G>
<x>=----- g _
(10).
p -p ,
E1- :a>Co p
g
The vapor drift velocity is assumed to be given by the expression for the
churn-turbulent upflow of a bubbly mixture,
- 1/4og(p -p )g ,
K (11)V "=,gj _2v
-
g-
where the coef ficient K = 1.41 according to Kroeger and Zuber (1968). For a
given set of test section inlet conditions, we may assume that C remainsg
constant in the test section, and that the variation of the liquid density og
is negligible. Thus V varies only weakly with p , and we shall assume
V to be roughly constant in the test section as well. Hence <x> may be
considered as an explicit function of the local cross-section averaged void
fraction, the vapor density and mixture mass flux.
From conservation of vapor mass, we have
f = <C>d<x>/dz (12),
which leads to, after dropping the symbol < >,
-73-
I, : .t .
i , e =.
dp V
dz , @p (1 - aC ) d bap
da EE bCxo dp dz G dza
C (13)r -
#1 - aC (p -p )/p
g g
where we have replaced dp /dz by [(dp /dp)(dp/dz)]. The quantities da/dz
and dp/dz in Eq. (13) may be obtained from the experiments, and dp /dp is
given 'oy the equation of state of the vapor, or the steam table. We note,
from the mixture continuity equation
1 dG 1 dA 1 d(A/A+)*G dz A dz j +) dz
To account for the frictional effects in an approximate manner, the effec-
+tive cross-sectional area distribution (A/A )eff determined from single
phase calibrations instead of the geometrical area distribution were used in
the reported calculations. This is probably a good assumption in the
convergent section where the favora' ole pressure gradient is expected to keep
the wall boundary layers thin and attached. Greater uncertainty arises when
such a procedure is applied to the divergent part of the test section where
the boundary layer displacement in two-phase flow may be significantly
different from the single-phase flow under adverse pressure gradients.
Thus, all terms in Eq. (13) may be evaluated as a function of z and the net
vapor generation rate may be calculated.
-74-
'|| ' JJ
Figures (5.34) and (3.35) show the two examples of r thus determined
for the convergent part of the test section. In these figures, the top
graph displays the measured pressure and void distributions in the experi-
ments. In addition, least-square polynomial fits to the measured data are
also shown for comparison. The deriatives of a and p may be evaluated along
the fitted polynomials, instead of through the actual data points, which may
lead to considerable scatter. The r values calculated from Eq. (13) are,*
exhibited in the bottom graphs. It is seen that P 's o f the order of 10'v
kg/m s are attained in these experiments, which are in approximately the
same range as those found in p.eocreux's (1974) experimente.
It was found that the value of T was dominated by far by the variation
of a with z in these experiments. For example, for Runs 82/821 at z = 254
mm, the value of the three terms in the numerator in Eq. (13) are
(Gx/a)da/dz = 22.53 kg/m s,
(Gx/p ) (1 - aC ) (do /dp) (dp/dz) = - 2.66 kg/m s,g
3
(as Vg gj/C)dG/dz = 0.33 kg/m s,
where V = 0.21 m/s.
Thus, the term involving dG/dz, which is directly proportional to the drift
velocity assumed, contributes about one percent to the value of r . Any
uncertainty in the assumption of V is expected to lead to insignificant
*In Fig. (5.35), the sudden turn in the r curve at z: 260 mm may be traced
y
back to the discontinuity in the slope of the two pieces of 3-deg. poly-nomial fit to the experimental data at the intersection of the two poly-nomials. For this preliminary evaluation of data, a better curve fit, whichmay yield a smoother transition from one polynomial to another has not beenattempted.
-75-
E ~. f- 1 |1.}| o's
O.4400i i i
Psat0
@n nOP o
P 350 -- O.2 a
(kPa) g a aG o O '
n Ao a
1 I i300 OI I I
ff'
RUN 82/82140 -
~
KI'v O---
kg h3 I*ms
- 14.1020 -
~
l I0
0 10 20 30
AXIAL DISTANCE (cm)
Figure 5.34 Top: Measured Pressure (o) and Void Fraction (C) Distribe-tions in the Converging Part of the Test Section in Runs82/821 and the Least Square Polynomial Fit to Data.Bo t tota: Calculated Net Vapor Generation Rate Based on tr.eLeast Square Fit to the a and p Data. (BNL Neg. No. 3-1226-79).
-
-76- ' 'i ,
I I I
_Ps
350 -- 0.4b
- o
p- O
- a
. (kPa) -
g- 0.2_
0- a a
300 3 n 0-
- O
I I I
O
10 0 ; ,
_
RUN 83,832_
_
_
_
__
P-v 50 -
kg T
(m s/| ~~
3_
-
_
_
__
' I IOO 10 20 30
AXIAL DISTANCE (cm)
Figure 5.35 Top: Measured Pressure (o) and Void Fraction (D) Distri-butions in the Converging Part of the Test Section in Runs83/832 and the Least-Equare Polynomial Fit to the Data.Bo t tom: Calculated Net Vapor Generation Rate Based on theLeast-Square Fit to the a and p Data. (BNL Neg. No . 3-1225-79) .
-77-
f..' i i i'' )t! s -
errors in P thus determined. In Fig. (5.34), we have also shown F 's calcu-v v
lated for zero drift velocity and a ten-fold increase in V (taking K = 0
and 14.1, respectively, in Eq. (11)). The difference between the three
curves are indeed small. Hence, it may be concluded that void fraction and
pressure distribution measuremerits are adequate for the determination of*
cross-section averaged vapor generation rates.
6. SUMMARY AND CONCLUSIONS
In order to measure the steady state vapor generation rates urder
nonequilibrium conditions, a flow loop with well controlled flow and thermo-
dynamic conditions was designed, built and made operaticaal. The test
section canaisting of a converging-diverging nozzle was first calibrated
hydrodynamically with single phase flows. Pressure distributions were
recorded along the test section and photographic observations made at the
exit of the test section under various flashing regimes. With flashing
occurring close to, but upstreata of the throat, the pressure distribution in
the converging section was observed to follow closely the single phase
calibration results. In tha diverging section of the nozzle, either a
continuous constant pressure distribution was observed all along this region
or the constant pressure was followed by a sudden pressure increase (co nd en-
ntion shock) and a single phase-like pressure recovery.
Variation of the back pressure revealed a choked flow pattern in the
converging section of the nozzle. Depending on the back pressure, the
pressure distributions in the diverging sections showed the presence of a
condensation shock. In the absence of condensation shocks in the test
-78-
,
\
section, marked variations were seen in the photographic observations at
different back pressures, but corresponding variations were not o b oe rv ed in
pressure dintributions.
During the investigation of the parametric effects, the mass flux and
inlet pressures were found to have a stronger effect on the pressure distri-
butions and photographic observations than variations in the inlet tempera-
tures under constant p -p (Tg) conditions. These paranetric effectsg
were riore visible at low mass fluxes at the onset of flashing than at higher
ones. The flashing onset was also observed to be an intermittent phenom-
enon.
F] ashing was also initiated upstream of the nozzle throat, and the
pressure distributions depicted a continuous decrease in the converging, as
well as diverging section. The onset of flashing was accompanied with a
strong deviation in the pressure distribution as compared to the s in gl e
phase calibration.
Using a single beam y-densitometer, the axial distributions of the
d iametrical averaged void f ractions were measured and compared to the static
pressure measurements performed under the same condtions. At high mass
fluxes with flashing occurring close to the throat , the constant pressure
distributions in the diverging section of the nozzle were accompanied by a
1inear increase in the void fraction. Since the test section diameter
changed linearly, it is suggested that a constant diameter liquid jet
existed in the diverging section. At lower mass fluxes, the constant
pressure distribution was followed by a pressure recovery. The corres-
pending void fraction profiles depicted an a-increase reaching a mximum,
-79-
j |}1: ~'t9) / - t
then decreasing to zero, i.e., an all-liquid condition. This fact shows the
presence of a condensation region in the diverging section.
Also reported were void fraction profiles with the flashing f ro n t well
upstreaa of the nozzle throat. These measurements conbined with the pres-
sure distributions were used in calculating the net vapor genera tion rates
under '' ashing conditions in the converging section of the nozzla. The y
densitometry system will be improved for the next series of experiments, by
increasing the s t ret.mth of the source, thereby increasing the number of
counts per unit time to minimize the intrinsic statistical error. In addition,
radial profiles will be recorded. Experiments will be conducted according
to a proposed matrix, which includes given re.ges of the various parameters
of interest, i.e, p T G, and onset of flashing., ,g 1
7. ACKNOWLEDGEMENTS
The authors would like to thank all the members of the Data Systems and
Operations Group, namely Messrs. James H. Klein, John R. Klages,
Carl E. Schwarz, Joh J. Barry, and Donald Becker for their valuable help
during the construction and operation of the experimental facility and to
Mr. Thomas P. Feierabend for his essential contributions in the electronic
.
instrumentation.
Special appreciation is due to Ms. Nancy Schneider for typing the
manuscript and for her ef forts in preparing the report.
Our thanks to William Fbssenger of the welding shop for his imagi-
nation and dedication in putting the pieces together and to Dennis Rhodes
and Edward McGilley of the electrical shop who ingeniously sorted out the
-80-
,|', b ..
maze of electrical connections and made the pumps pump. We would also 'tke
to express our gratitude to Eugene C. Mohlmann for the expeditious mannec in
wh.1ch he handled our rush orders, z.nd specially to Herb Banks for his
invaluable help with our purchases and negotiations with the various ven-
dors. Dr. Hobart W. Kraner's suggestions, help and guidance on the y-source.
and y-densirometer development were also most welcome at critical moments and
are well appreciated.
-81-
! (>'.
F) 7 i/ i t -a
8. REFERENCES
1. Hsu, Y.Y., " Review of Critical Flow, Propagation of Pressure Pulse andSonic Velocity," NASA TND-6814, 1972.
2. Ssha, P., " Review of Two-Phase Steam-Water Critical Flow Models WithEmphasis on Thermal Nonequilibrium," NUREC/CR-0417, BNL-NUREG-50907,1978.
.
3. Seynhaeve, J. M., " Critical Flow Through Orifices," Paper presented at theEuropean Two-Phase Flow Group Meeting, Grenoble, 1977.
4 Isbin, H. S., Moy, J . E . , a nd Da Cru z , A.J.R., "Two-Phase Steam-WaterCritical Flow," AIChE J3, 36], 1957.
5. James, R., " Steam-Water Critical Flow Through Pipes," Proc. Instn. Mech.
Engrs., 176, 2, 741-748, 1962.
6. Ardron, K. H. and Ackerman, M. C., " Studies of the Critical Flow of SubcooledWater in a Pipe," Paper presented at the CSNI Specialist Meeting onTransient Two-Phase Flow, Paris, 1978
7. Reoereux, M. and Seynhaeve, J. M., "Ecoulements diphasiques eau-vapeur:essais comparatifs de debits critiques," Acta Technica Belgica EPE VolX, 3-4, 115-137, 1974.
8. Fauske, H. K., "The Discharge of Saturated Water Through Tubes," Chem. Eng.Prog. Sym. Ser., 61, 210-216, 1965.
9. Reocreux, M., Contribution a l' etude des debits critiques en ecoulementsdiphasiques cau-vapeur, These de Doctora t, Universite Scientifique etMedicale de Grenoble, 1974.
10. Silver, R. S., " Temperature and Pressure Phenomena in the Flow of SaturatedLiquids," Proceedings of the Royal Society of Londou, Series A, Vol.194, 17, 1948.
11. Zaloudek, F. R., "The Critical Flow of Hot Water Through Short Tubes,"HW-77594, 1963.
12. Fauske, H. K. and Henry, R. E., "The Two-Phase Critical Flow of One-Component Mixtures in Nozzles Orifices and Short Tubes," J. of HeatTransfer, 464, 1971.
13. Schrock, V. E., Starkman, E. S., and Brown, R. A., " Flashing Flow of
Initially Subcooled Water in Convergent Divergent Nozzles," presentedat the ASME-AIChE Heat Transfer Conference, St. Louis, MO, 1976.
-82
<i
\ \_ '5'~,,"i.
REFERENCES (Cont'd)
14. Simoneau, R. J., " Pressure Distribution in a Converging-DivergingNozzle During Two-Phase Choked Flow of Subcooled Nitrogen," NASATMX-71762, 1975.
15. Hendricks, R. C., Simoneau, R. J., and Burrows, R. F., "Two-Phase ChokedFlow of Subcooled Oxygen and Nitrogen," NASA TN 3-8169, 1976.
16. Reactor Physics Constants, ANL-5800, 1963.
17. Kroeger, P. G. and Zuber, N., "An Analysis of the Effects of VariousParameters in the Average Void Fractions in Subcooled Boiling," Int. J.Heat Mass Transfer, 11.211, 1968.
.
4
-83-
r .-
D/S f !.I ,s
NOTES TO THE APPENDICES
1. In Runs 1-36, run average values of the flow rate, the test section
inlet temperatures and pressures, the condensing tank temperatures and
pressures, as well as the turbine flow meter temperatures were hand.
inputted, and thus they do not show any variations during the experi-
ment.
2. In Runs 20-43, run average values of the flow rate, the test section
inlet temperatures and pressures, the condensing tank temperatures and
pre;>sures, as well as the turbine flow meter temperatures were hand
inputted, and thus they do not show any variations during the experi-
ment.
3. In Runs 44-69, run average values of the test section inlet and con-
densing tank pressure were hand inputted, and thus they do not show any
variations during the experiment.
4 The Differential Pressure Measured in in (kPa) and can be expressed
as:
Differential Pressure Measured = DP(kPa)
" ( " "E + PE -PNth Tap Sth Tap - Tap 1 Tap 1
Thus to obtain the local static pressure at every tap, one has to
subtract the gravitational head from the presented data, p is the .
average density in the manifold (N Room Temperaf tre)..
5. The dimensionless pressure differential is defined as the differential
pressure measured divided by the test section inlet dynamic pressure.A 9
DP = DP/yp U~c
p is the density, and U is the velocity at the test section irlet.
-84-
#4
.
LEGEND FOR DATA PRESENTED
Swl. FIAStillC Fl.DVS nPt R I NENTrRt.NNI Nf; l'N8 W li4TA FMUW
11.TT btLilOW e2
RI'N N'Ja bER 64
tDnf Fl.OW TFwi ERATL'Rt3 (DFD Cl FRF W RE (IPAD VM DCITV RPY=nt ns DIPM RWTI AL FRt22:tRRTAFS LT RALC Pt/W Mt1rR TS inLLT LUk D T A% L TS INLLT CU1p TANE LM $1f ALNBtX IILASikle D I RE% lONLIM
t-2 9.61 IM.8 148.s I48.8 64 6 . 2 464.7 474.0 .!!7f 07 .e9 .nl
1-4 9.62 33h.O 148.7 ;4n.7 f49.2 404.7 473.h . i l 7t. 0 7 .79 .U8t-$ 9.61 134.0 law.7 14s.7 tA9.2 464.7 473.5 .117t.H7 2.ip . 26 '
t-7 9 . f. 2 th.D 149.7 14 P1. 7 f49.2 464.7 473.'s .Il7L.u7 5.04 . 4 't
- -
. N mLow ptess. side Evaluated at Diff. y1 ss.
Higit ptess. side Test Section in kPaInfet (inetuding
gutvity Itcadsee p. 15)
u
Dif f. piess. nondincutsionali:edby .Lutet dynamle ptes sate.
G+ p; -p .u ; ,: ! n .,
kd r './,~.,_' '
~pU.; -I tyv,. ,j v_
u 1 - /^~ 4 4 .s ijf. j
DimensLonfess Single Pitase CalibuttLondiff. picss. see Fig. 5.2
Diff. ptess. measuted = 34.5 rPaP.tes s . dtop calculatea.
Ptessate cap * ftom ideal flow_ _y~llentatt ptof Lfc \
l {. |Ptn: .rt ;4
, 2s- 3, is""rr" is <, , , r r i, ms 2, - 2s- r4- z .s ~,-
,m.s r r ,,- is 2 4
.,. ,
,r-g y- .-
.,,
' '% '''''! , Expt. data points ,i',,s.
-
- r,a ;-,
,=- o.dy 9 '
,
* '-_m. c- %
l '
q: b3 :i.
_-.n -
.P, [[ P
;;r Satstatton ptess. 2*,
et T . . _l - -
-. . .., Ln u ?_w w ;nt, u ew , .> vru. ue 9.6 LF$2 9. 6 LPS
*
l,,. :ss.e etc cine.e ~.c c -
*,.**U9. 2 KA T5 tv.E1 Q ~~ Et9. 2 K'A 15 f v.ET *.
r .54.7 a-a tw taw~
J6u 4c4.7 mm ctw se% _A
e.e r. e 22. t 38.8 de.e sr.g Et.t g'. B * 18.2 22.0 3P. f 42.f 52.8 EI f
AxlAL DISIONCE ICM) pylAL D:S!ANCE ICM)
Run No. and expt. conditions Dimensionfess expt. data
Eft i tf!/ ! | /,
.
APPENDIX A
SINGLE PilASE CALIBRATION DATA
.
-86-
: < oc -| c \ist
.-_. __
SIM1ARY OF EXPERIMENTAL CONDITIONS
A. COLD 6 IlOT CALIBRATION
RUN p (kPa) T ( C) G(Mg/m s) p (kPa) T ( C)
1 ----- ----- ---- --- - - - - -
2 371 26.4 1.56 354 26.3'
3 368 26.8 3.13 345 26.2
4 361 27.2 4.71 331 26.6
5 351 27.6 6.28 311 27.4
6 682 27.7 7.01 647 27.2
7 691 27.3 6.30 657 27.3
8 695 26.9 4.71 652 26.8
9 709 27.1 3.13 674 26.6
10 711 27.0 1.56 683 27.0
11 688 27.7 6.26 632 27.6
12 1033 29.2 7.01 973 29.1
13 1031 29.4 7.88 961 29.3
14 337 23.0 6.25 316 22.9
15 348 22.9 4.74 339 22.9
16 365 66.3 3.08 309 66.1
17 367 64.1 1.56 322 63.9
18 ----- ----- ---- --- -----
19 337 94.4 5.49 324 94.5
32 327 11.6 4.71 352 12.
33 315 11.9 6.29 326 11.9
34 336 12.3 3.15 369 12.3
36 293 69.1 3.08 308 68.9
62 692 148.4 2.33 646 148.4
70 213 54.0 3.35 201 48.6
71 211 54.4 3.34 203 48.8
-87-
E'c e tJ i .) |\j
w . siy ty . p* . c j 3 ,c., ., p w
6 1 Q'* i /rn-tj .-
.
. :.w.
hi d
'U..f U.1 b C; t 1. O M[ T N*' U M''Qb.'l . eM
.
BkL FiAtllhC F10hs f]tPERIllEhTPRI%i ME FRor UAT A FMua
T DT SECTION e2
RiN h(NBER 2
L.00P IlOV TTTRATURIN (DEG CD PMNWRE OPA) VIIDCITY RF% CLDS DIFI'lTifh7i Al. PDl?MllETJS I T U5EC HMw KFTER F 1hlII CohD TA.n1 TS thLET CohD TA)l! 01 Sil' hlRi1ER Musl > ED Di sFMIOP LN
1-4 3.18 M.4 2G.4 26.3 770.9 353.7 1%.6 . 914 3' * M .37 .13
1-5 3.lW 26.4 26.4 M.3 37d.9 39.7 1% 6 9141 * M .in .nh
-' 3 . 1 88 26.4 26.4 26.3 370.9 3s3.7 1%.6 .914t M .do .32
1-7 3.ik 26.4 ;o.4 26.3 373.9 353.7 156. f. .914T*Ds 52 42
4-W 3.IN 26,4 26.4 26.3 3 70 .9 351.7 156.6 .9adi+0s .f i .523-9 3.14 26.4 26.4 26.3 370.9 353.7 1%.6 .9 4 4L *M .93 76
1.* l.29s0 3 . 1 18 26.4 M.4 26.3 37a.9 353.7 l%.6 .914t*e5
1.57' 1.2%l-13 3.lM 2.4 26.4 M.3 370.9 353.7 1 % . F. ,9141 *M
9141 M 2.e3 1. f sl-.2 3.1= 26.4 26.4 26.3 370.9 30.7 1%.s
*
i-13 3.in 26.4 26.4 2* . 3 370.9 3s3.7 156.6 > ldl *M 2.34 1. f"4
1-14 3.lu 26.4 26.4 26.3 37a.9 353.7 i%.6 .9i4T.05 2. *a s ?. %
l-15 3.1% M.4 26.4 26.3 37a.9 ys3.7 156 . F. . 914F M 3.3% 2.72
1-16 3.6h 26.4 26,4 26.3 376e.9 3s3.7 1%.6 .9;4i*C5 4.e2 3.271-17 3..k M.4 76.4 26.3 37o.9 3%).7 i%.6 91st*os 4.% 3.h ?
l6N 3.iM .% . 4 26.4 26.3 37u,9 3s3.7 1%.6 .9141 -M 5.E2 4.73
..'1 3..x 26.4 26.4 26.3 370.9 353.7 s % .6 . e n dl *M 6 64 s.da*
n-2a 3.1x 28. 4 26.4 .o.3 37o.9 3s3.7 i % . f. 9 i 4 ; .i.( s. . u i e. , 5 2
1-21 3.I= 26.4 26.4 26.3 370.9 3s3.7 l<c.6 91 e L * M 9.4 S -* 7
|-?) 3.iw 26.4 M.4 26.3 370.9 351.7 i%.r .n i I M s i .r w 9. .r#
l-21 3.iw 25.4 26.4 26.3 37a.9 3 *.1,7 g % . r. . 914 F .M il.s; sa ( o
I4 3.1% 26.4 26.4 26.3 370.9 353.7 3*6.6 9:4F M 6.w 13 . t. s
1-25 3.14 25.4 26.4 26.3 373.9 3s3.7 e 5r. 6 9,44 .M 70. 6., je.wi
1-M 3.1= 26.4 29.4 26.3 370,9 ?s1.7 a sA . f. 914 I * o 'i 6 7 . i =~ 13.w?
l-27 3.1h 26.4 26.4 26.1 37a.9 39.7 1% .6 .9131=o5 a d . 7ts 12.o;
J-24 J . . ie 26.4 26.4 2r, . 3 37o.9 3s1.7 g%,6 ,9 s a s .M 12.66 lo.4%1-29 3. t '. 26.4 2,.4 26.3 370.9 3s1.7 g%.6 914t.os l i ss. S . *, e
1-30 1..s 26.4 26.4 26.3 370.9 353.7 156.6 914t=o5 9.e1 7.94
,7. 2 i-31 3.in M.4 26.4 p. 3 376.9 3s3.7 3%.6 . 9 ,t .M m.y,s
-32 3.in 26,4 76.4 26,3 37g,9 ysi,7 gg,c ,9 i dy.n s n,ny _
1-31 3.l* 26.4 M.4 2.3 370.9 3<3.7 1%.6 914 F . M 7.2s s'..+l-14 3 lw M.4 26.4 M.3 3'o.9 39.7 1%.6 . 9 i.F.m e, . s 4 s.s .
* 141-3% 3. . .w 26.4 M. 4 2.3 370.9 3s1.7 1 % . r. .9:45 m
A . 2.*ws.. 4.%. - 3r. 3.as 26.4 M.4 2r. 3 3m.9 3s3,7 i sr. . t. .9:4,.us
IOP 3.1% M.4 26.4 M.3 370.9 3S3.7 1%.f el *M 5 . r, i 4 %
|-?% 3.1% M.4 M .4 36.3 37a 9 3s3.7 g % .v. 9,4r .M s.e3 . . .
1-3s 3.:s 3,., 26.4 2c.3 3mi.9 39.7 i% 6 . 4>.e5 4,7w y,n
J-40 3 .1 == 26.4 36.4 26.3 370,9 3s1,7 3 5r. 6 ,9g4p.p5 4, r. ; y ~4
l-48 3.15 26.4 26.4 M.3 370.9 3s1,7 [ V . r. ,9 . .o M 4,4g y , e <j
#-42 3.14 26.4 26.4 2r. 3 3 7a , d, 39.7 gg,6 ,9 , .s c . M 4,og 3,y,
l**3 1.ls 2r. 4 26.4 2G.3 3?H.9 3%1.7 a v . t. _914 F .M 4.03 3.;7
e*-8 3.ld 20 4 26.4 26.3 3 7a.9 3'3.' 1 % . f. .9 6 4F *M '. N 3 3, . I l3,sj .,3
9 3 41.es1-4s 3.ie 26.4 26.4 2r . 3 3 o.9 3s3,9 g g , r, ,9,4i.a
e5 3,51 ,%7e-46 3.lu 26.4 26.4 26.3 3?a.9 39. ' %6J-47 3.1% M .4 26.4 2r.3 370.9 ?%3.7 i'6.6 .9i4F.M 3,2s * r.4
.
t-4* 3.nu 2r. 4 26.4 26.3 37a 9 3 *.1. "' 1 % . f. 9 6 4F=M 3.s7 2. me6-49 3.1w M.4 26.4 26.J 37a.9 39.7 1%.6 .9i4F *M 3.73 2 . g. 3
S&& 3.18 26.4 26.4 26.3 370.9 353.7 1%.6 .vi4E*as I . ast I.l2
- - - - -p---- _ _
_--
r e. , i; r. c. ,n1 . , m in. .ivT rrrme m ,n- 1 m - -- r m - rr7 i~
:- 5 i 5, r le 15 , ,2r 15 32 35 <a as 49 w5 6.. 5.. itis a ,- 2e 45 M 25 42 45 ds
[ . ..., d [- 4.y 7* * 1* *.,
%,% - ; ..'i* .... .=*
,.. '',
q e, ==,..=" 3 .
. A, ) ,e.. |s sr ,o 4 lu .
[ o et3 = =e*
l_m o.m , * e_ e 'a,~ T. - *
76 'im =28**
sm . 2,om T j..D
..
,._ 3 ,
-E, .C ' ?["
e . s!
e s- e* *
# "G i
A;4.
I( I( u vu 2u sceut 2 .
* 3. 2 LPS * * 3. 2 L P'5
26.e 02C C ZE . ' N.C. o "t. 9 G *$ N ET~ Ft.9 KNI Ti |m.ET
2* M 3. 7 nPr. c3h past ,. .** .; a , w : s,4
e.e it.s 2t.s vs, 7 . 2 2 , _ __ _ ._ _ . _ ___ ,._ _ . ,$ _ _ _
_
ar.e sz.e Er.e ee .r a 2r e 32 e er.e se e 62 e
AxlAL O!SIRNCE (CM] RXiR. OlS!P'CE (CM)
-88-
-
f fe
dO
'3k{~ . n~ ,,
e r*= . 5~' I ,1
'\d: ,
h \.., , ,a ~~ % >G 3o
Bht FI. As11IM FIDW f kPrillllDTF ACA1IvE libil' I)4T A FRull
fl5T StCTION s2
Rtw lit sibER 3
UDP ilfW Ti pWFRATUNE'; IDEG CD P' EMi'Rf HP A) VEIDCIT Y |lFY% OLDS DIFFTIOTI AL PRIMI lifTAPS LTiv5LC Flow sETEM TS l>L1T CtshD T A> E TS s *LtT OMJ T AAI Cls Slr M mMER llFAS6 k.LJJ Di smiostr S
I-4 6.TJ 26.R M.s 26.2 36k.2 345.4 314.6 . lhv ed4 . %) ..e3-5 6.13 M. N M.R M,2 36M 2 34% 4 3[4,6 . ] M NDO6 4.0) .21
6M,2 34%.4 3[4,6 , l h 5t e n% L .f 4 . 3.13*6 6.TJ 26.h 26.k 26,23,C.N . 2_ 345.4 3 i d . r. .4k9+*% 2.?e .%'|-7 6.33 J, . e ye, . n Or, ,
l-N 6. 3' A ?o . es M.h 26.2 36N.2 34% 4 314 . r. . nsiS t.o6 3.44 69l*9 6 . '''J 26.k 26.M 26_2 36h.2 34%,4 364.6 .145)*06 4.30 .NI3*l0 6.3A 26.h N.H 26.2 38.M . 2 345,4 3|4.6 . iM9 *E% 6 H') 1.39l-il 6.31 26.h 26,N 26 2 Y bs . 2 345.4 314.6 . lNV 64 6. 9-' l.40
9. 0' !.*'1-17 6. 7J 2 6 . 85 26.H 26.2 364.2 345.4 314.6 . l h 51 *'%3" . U 3' 2 **2l-13 6.3 ) 26.h 26.H 26.2 3',# . 2 345.4 314.6 . lhV * n6
|-!4 G ,73 26. te M.N M.2 38,W . 2 34%.4 314 . t' .lw9 66 12.32 ? . 4 's1-i$ 6. 73 26.h 'a . . M M.2 ?64.2 345.4 314.6 . i k% +i6 14.!3 2.92'-16 6. 13 M.* 26.= 26.2 3'k.2 3d%.4 314.6 i = R *6 17.01 3.411-17 6.39 M.h M. N 26,2 36M,2 145,4 314.6 .1 % ' t * * W 2".6h 4.16l-14 6.39 26.k 26.w 26.2 3rM.2 345.4 314.6 . w %' H L 2%.D4 5**.-1-19 6.39 26.h M.s 2r. . ? 36ei . 2 34% 4 314.6 . i m '.; . % 2%.77 %.*>l .N 6.39 26.h 26.N %.2 364.2 34 ( 4 3g4,6 , g h Q e t W, 33.h2 6 kl1-21 6. ?) 26.8 26.m 26.2 3rk.2 3 *L 4 344.6 .thM*% 11.(4 7.943 .'2 6.Js M.M M.h 26.2
3.'.4. 2345.4 314.6 . s h V %% 44.74 9hi
1-23 6.33 Mh M.s 26.2 38 4 . 2 345.4 314.6 . ! w M *o6 Sp.hl lu.211-24 6.3 M.h 26,a M,2 3 . 51 , 2 345.4 3 i 4. r, , g n y .on 74,41 | 4. bl-25 6.?J M.N N.N 2a. 2 KN.2 34%.4 3 [ 4 , f, . i s '.) e 6 4 '12. 3% j%.ps
t-M 6 . ^, A M,h 26.N 26.2 36'4.2 34%.4 314. r. iw' L ett 73.ko 14.66l-27 6.31 26.H M. h 26.2 364.2 34%,4 334,6 . g o. y . i 6 f. i . 7 7 g ? e4
l- 2% 6.39 26.h 26.H 26.2 3r.% . 2 345.4 3|4.6 i>% et% M . 56 |0.443-29 6. 71 26. a4 76.m 20 , 36w.2 345.4 314 . r. . g > q . i( 46,2| *a , 3 e
1-3H 6. H 26.8 26,k 26,2 3. ,it . 2 345.4 3:4 . e_ .14 9 * t0 4d.62 ** . 1 %l-31 6.37 M.E 26.h 26.2 3(h.2 345.4 34 . t. ; Av.06 3es pd 1. .' 7l-32 6.3s M.N N . st 26.2 3(.R , 2 345,4 3 5 4, r, , = y e g4 3 7,(. 4 f. , % 7l-3J 6.33 26 M 26.M 28' 2 36%.2 34%.4 34,0 . g h siisu 2'J . 'y r.e1A * Il 6.?1 2 'i . N 26,M 2_ ' 3f%,2 24$,4 ' 5 4 , r, , hy e(% 27,2% 5,4 e
I - '1 % 6. 3 e M.# 26.h M2 36h,? 34s.4 ag,6 , i g y . o6 2( g 5 a. , e u
l-16 6 . "h 26.W M,8 26,2 3e ,ne . 2 345.4 3 | 4, g, , ] w ( 3 . i .6 23,go 4,( %
l-37 6.38 26.h 26.N M.2 3(4.2 3A%.4 3 4 r. ,1 % % e t C 21.72 4.37l-3% 6.3, 26.e M,w M.2 36as . 2 34s 4 3;4,6 ,g %,.p6 2a.21 o7l - TJ 6.31 M . ms 26,k 26.2 34.u ,2 Li% ,4 334.6 . t h '. ). * * 6 ! M . I.'4 3.kn3-4d 6.37 M.* 26,4 M? 3 ;ss . 2 345.4 314,6 .;ky .n6 17. f 4. 3.561-41 6.37 26.h X , se ? .' 36% y 34s.4 3i4,6 , ; % y . .( g6.7| ..3..-42 6.31 N.h y,x 2c.2 y4 2 345.4 31. 6 sw V e(% 1%.91 1.21
6 - 4.1 6. ? e 26.h M.h M.2 y s , ,. 345,.I 314.6 i AN *o' 1%.13 1. 5'%l-44 6. H 2 .k 26.k M,2 yw.2 34s.4 3 i d . t. . t h 4 t6 14.31 ' . 611-4% 0.Ts 26, ti M,b 2e * 36h,2 345,4 3g4,6 ;ky.40 11.7% 2,713-46 6.Ts 2v. . h 2s. . k M._ 36w.7 us,4 3 i . , g, , j nc , p . % 33,p2 3 , (. 26-47 6.39 M.N 26.w M.? 3a .w . 2 34'. 4 3;4.6 , ; w q .,4 32,42 2. ? e3-4M r. . Ts M. h 26. ns 2r. 2 3'.g
yw 345, 4 3 g a , (, , g g g.iC ll.M 2.3d1-49 6. 3'4 26.N 25. . H 26.2 3e 2 345.4 344.6 . l b st.%% 16.9N 2.44Su-l 6.39 26.8 26.b 26.2 3e,w . 2 345.4 J14.6 .lb$t*e6 6.21 1.25
_ _ _ _ _-- _ _ _ _ . _ _ _ _ _ _ . _ _ . _ _
- g- - - - - - - - ,_ _ _ .u,F, ,
.T'~rr'TT W T - ' t {. t 7 1 -'T-- T-~yrt . t T y 7 - r m m r- - rr t -r. . 32 35 d2 45 'S ,#,5 1.. 4....18. l . . . . , . ,_1 - ".
IS d > V a '2 d5 0vs ! $ ie 15 22 25* .
..... ,,.. Q-
-]{.". .. **** ...N a,,,..e
,
....,,.. x, '.*.m..
-r r_~ .
f ... h2 2 0 ,.'* *.. o .o
. o 4
,
' ,
.. - . n... a- O_ .o . r
y- . -.{'M 'Op - .
.
. - . -5
. ,
/Ih |ci
~
/ i
.'
2.
. fo- - - - - - - - . \ e._ _ _ _ _ __._._- -
,
a-_ as,
~
o , p. MR 3 F 'N h7 Y A 3, ,33 g,g ;ps s * 6. 4 M J|Os. e ac c n.e nc =
na 15 N t f ~ ". M2 *^ ! MI I._ m. 2 a
* '-
385 8 '?^ C2% M d''
'4 L . n?A C 'M NA |, , - - -,- ----T . . .
- J & *%g _____7 _-g. .g.- -y- -
--7
re Ir t ze t ne <t.* St. e u.a tt it t !! E 'I t "E ' 2. e urM ! nL O l S K"t I Cril M R OlS!XE ICM1
>,
-89-.i! ! /. |,
pF=s 9 '/' '% P Uf..!a u.y an '- c'.-m. nI k
'ri ,Il ;
[! Os, yy u i d ud (IE NP145&f%G fifVT 1X' RI11l'hT
TkCN ed IFP- | AT A i kuil1)ST S&ffiOD 8 2
31 E M~4BI3 4
1Dr# F1DV Trit rD ATilll5 fLfL Cl FRI%7kE #LFAl VDMITY Rn 4nLPS DIFT11rn.TIAL Pkf W RF
TAFS LT R /STE F1th atT12 TS lh1ET CvhD T A%I TS thLLT CLAls 1Aht Cm Sir bl ehtJt Itt A.NI R O trl4Lw iustr E
l-4 9. f.6 27.4 27.2 26.6 % I .4 331.9 4 72.5 .?hlE*06 .99 . (*9
l-5 9 . fw 2*.4 27.2 26.6 %I.4 333.9 472.5 .2#1L*06 2.34 =?l
1-6 9.60 27.4 27.2 26.6 363.4 331.8 472.5 . ?h l T * L6 4 01 .M
l-7 9.f4 27.4 27.2 26.6 361.4 331.9 472.5 .?*.I L6 5.53 . 4's
4-6 9 . f.0 27.4 27.2 26.6 361,4 33|.0 47?.5 .? hit =06 6.72 .h*
l-9 9.60 27.4 27.2 26.5 % 1. 4 331.9 472.5 - 2k i f t* 9.74 .*7
l-le 9.60 27.4 27.2 2(i . 6 3f> l . 4 331.8 472.5 'tiP*% 16.20 1.4%
l-11 9 . f 44 27.4 27.2 26.6 361.4 331.0 472.5 .?h i t 66 16.01 1.43
6-12 9M 27.4 27.2 2f . 6 361.4 331.0 472.5 .?AiF t6 21.81 1 '* %''% . T 4 23.01 2.05
|-13 9.M 27.4 27.2 26.b 361.4 331.9 472.5=.""h.L 06 "'1t . 4 R 2.(4
1-14 9 f.e 27.4 27.2 26.6 361.4 331.0 4 72.5
l-15 9. f A 27.4 27.2 26.6 36i.4 331.0 472.5 2 A I L *ttf. 32.40 ?.69
l-16 9.00 27.4 27.2 26.6 301.4 J3. 0 472.5 .>*f*D6 37.56 1 3%
l-17 9 (M 27.4 27.2 26.6 361.4 311.0 472.5 _2h:E+f6 4 7 . .'4 4.22
' .141-18 9 60 27.4 27.2 2f. 6 361.4 331.0 472.5 .24.E+H6 57. M.5 .I
1-19 9. f4 27.4 27.2 26.6 361.4 33..H 472.5 . ?k i f. * % 65.15
l-?O 9.60 27.4 27.2 26.6 361.4 33i.9 472.3 .311 06 77.92 f. 95
1-21 9.60 27.4 27.2 2f, . 6 361.4 331.0 472.5 ?k;l *E6 91.39 5 a6
1-22 9.f4 27.4 27.2 26.6 361.4 338.9 472.5 . 2% . E * . 6 Il2.26 la.02
1-23 9. f.0 27.4 27.2 26 6 361.4 311.0 472.5 . "'% i f a t 6 119.26 let r.4
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APPENDIX B
PRESSURE DISTRIBUTION DATA UNDER FLASHING CONDITIONS
SOME PHOTOGRAPHIC OBSERVATIONS
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-112-
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B. FLASIIING EXPERIMENTS
RUN pg(kPa) Tin E "
ct ct
20 281. 98.3 4.90 245. 98.221 393. 100.6 6.01 136. 100.422 170. 100.2 3.04 125. 100.123 130. 99.4 1.81 121. 99.324 160. 98.0 3.05 122. 97.825 247. 97.4 4.52 125. 97.326 386. 97.8 6.02 132. 97.7
27 326. 130.0 2.95 299. 129.628 566. 131.7 5.90 316. 131.429 488. 123.5 5.77 210. 115.430 375. 125.1 4.50 206. 114.731 ---- ----- ---- --- -----
35 287. 99.4 4.96 250. 99.2
37 296. 100.3 4.94 170. 100.038 117. 100.3 2.05 112. 99.839 136. 100.5 2.25 112. 100.140 168. 100.3 3.02 112. 100.041 250. 100.2 4.54 115. 99.842 194. 99.6 3.79 114, 99.4
43 287. 100.2 4.97 121. 99.944 271. 99.9 4.50 101. 99.945 308. 99.8 4.97 99. 100.046 223. 99.9 3.79 99. 99.947 ---- ----- ---- --- -----
-113-t
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B. Fl. ASHING EXPERIMENTS
(Cont'd)
RUN p (kPa) T, ( C) C(Mg/m s) p (kPa) T ( C)
48 183. 99.9 3.04 100 99.9
49 146. 99.9 2.27 99 99.7
50 142. 99.8 2.04 101 99.9
51 ---- ----- ---- --- --- -
52 381. 123.5 4.48 254 123.5
53 395. 123.6 4.45 249 123.6
54 525. 123.6 5.96 252 123.7
55 293. 123.6 2.99 251 123.6
56 261. 123.2 2.20 252 123.6
57 263. 124.7 2.04 256 123.9
58 254. 123.3 2.98 174 110.2
59 254. 123.1 2.98 174 110.2
60 264. 125.8 2.93 186 112.5
61 259. 123.8 2.98 162 108.8
63 739. 148.7 5.85 464 148.7
64 609. 148.8 4.40 463 148.8
65 ---- ----- ---- --- -----
66 521. 148.8 2.94 463 148.8
67 502. 148.6 2.22 463 148./
68 395. 143.5 1.24 185 118.0
69 399. 144.3 1.23 188 118.5
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__ _ _ _ _ .,_____,__,Z 2 - -T .
17.9 AP f 'f.E 02.0_
-
T--- 1 - - ' T- 7P. E 1f.0 2P. f N.E d2.8 9. 9 fLE f.E 12.9 2P . f -
Axl AL DISTPCE (CM) AxlAL DISTANCE (EMI
~155-
[? / ' I d/- , .
APPENDIX C
.
PRESSURE AND VOID FRACTION DISTRIBUTIONS
UNDER FLASllING CONDITIONS
~156-
q / -) ibb~7f i_
FI.ASIIING EXPERIMENTS
RUN p (kPa) T ( C) G(Mg/m s) p (kPa) T ( C)
72 ---- ---- ---- ---- -----
73 275. 99.4 4.90 56. 87.9*
731 281. 99.4 4.88 52. 88.0*
732 285. 99.4 4.93 52. 87.9
733* 288. 99.4 4.91 53. 88.2
734* 287. 99.4 4.91 54. 88.0*
735 287. 99.4 4.91 55. 88.1*
736 287. 99.4 4.90 54. 88.0*
737 287. 99.4 4.91 54. 87.9
74 285. 99.3 4.90 56. 87.9
75 395. 99.3 6.04 57. 88.5
761 396. 99.3 6.04 60. 88.7
762 393. 99.3 6.05 62. 88.0
763 392. 99.3 6.06 65. 88.0
77 157. 99.3 3.06 65. 88.7
771 157. 99.4 3.03 69. 88.3
78 138. 99.3 2.61 71. 88.0
782 138. 99.3 2.61 71. 88.1
79 124. 99.4 2.27 72. 88.2
791 126. 99.4 2.26 73. 88.1
792 126. 99.4 2.26 83. 88.1
80 585. 148.3 4.36 436. 143.5
803 579. 148.3 4.32 432. 143.5
81 493. 148.3 2.91 432. 144.0
811 493. 148.3 2.91 432. 144.7
814 492. 148.3 2.91 428. 144.1
82 376. 142.3 2.36 174. 111.6
823 377. 142.4 2.32 176. 110.9
83 352. 140.0 2.30 150. 107.9
833 348. 139.5 2.29 145. 107.1
*Runs 731 through 737 are subsets of gun 73 as age othez guns in thehundreds subsets of their decade base- -157- 3t<L iu/ iU/J s
But. FI ASHlho FthWS EllPFRillDffFilm 1kt DRor 14TA FMr>st
Tf.37 M CT ION e2
RUN NLuBfA 73
IM P FIDW TFart R Af t|RES IDEG CD FRt1SI'RE IIFat VilDCITT REINOLDS DIFFTRFNTIAL PRF%l'RETAPS Lik/SLC FLOW utTth TS INLt:7 CohD TAJit TS INLM C041J T AlfX (W SEC W i|M M.4 NEANLkLD Di nim ink t.F.ss
1-3 18.44 M.4 99.4 6N.9 275.2 55.6 514.e. 3 72 E .+ s4
.e4 .07l-5 10.40 96.3 99.4 84.3 275.3 56.3 512.0 . ust: 06 3.57 .241-7 Itl . 4 4 %.3 99.4 67.7 275.3 56.1 514.3 . W 72L *I4 6.53 .51l-9 lu.40 %.4 99.4 h7.8 275.2 56.2 512.3 86'Jt +o6 11.04 .N71-11 l't. 4 2 %.3 99.4 87.7 275.4 56.4 513.3 . 3 7ur u6 6e.63 1.46|-13 16.41 %.3 99.4 hel . 4 275.7 55.6 513.5 . N71 F *m 27.i% 2.121-15 11.47 %.3 99.4 M 7. u 274.5 55.9 515.3 . s 74 t. = im 36.92 2. b 'sI - I t. 13.31 %. 3 99.4 $7.9 275.3 56.8 511.5 . h6 71' . 06 42.% 3.doI-17 10.42 %. 3 99.4 67.u 274.0 56.0 513.2 . e 7til tiei 56. wit 4.47l-l# lu 46 %.3 99.4 s7.8 274.h 55.8 515.2 .s741' 06 67.13 5.?31 - l 's lin ,4 5 %.3 99.4 NW.3 275.1 55.5 514.4 .6721. i6 74.03 5. 7*11*%* 14.43 %.3 99.4 87.8 274.1 55.N 513.7 27|E+06 8' 18 . 7 3 f. . %-
l-21 lh.44 96.3 9'J . 4 87.9 275.5 55.7 513.9 . e 721.M 105.99 u.311-?2 Is.44 %.3 99.4 37,7 274.m 55.9 514.2 .b72E 06 129.b8 10.17e
1-23 13.46 %.3 99.4 s7.6 274.s 56.1 515.3 .874F*o6 149.R6 l l . f.41-24 10.45 ' 96.3 99.4 37.9 274.3 55.9 514.3 . m 721: * M 379.55 14.051-?S 10.4's %.4 99.4 88.7 262.4 54.8 Si6.0 7751 06 224.14 17.421 - 25. 1u.44 96.4 99.4 e7.s 27J.6 55.7 584.3 e 72F ati6 lu4.92 14.471-27 10.46 %.3 %4 u?.s 274.2 55.3 515.0 .a73t.06 In4.it 14.37l '4 10.44 %. 3 YJ 4 h8.0 2 76.0 55.5 514.0 . u?21 *t6 IN3.ko 14.40l * 2'8 lis. 4 3 %.3 93.4 47.M 274.3 55.A 513.t 871F*06 181.56 14.39|- %f 1H.46 9e. 4 99.4 iss . 4 275.7 55.2 514.9 . s73 F.M l ie 3. M 14.29| .16 lu.46 %.3 99.4 us.o 274.5 55.4 515.0 8 74 I: + 06 lul.09 14.2n1-32 lu.46 9r. 3 99.4 87.7 275.3 55.5 514.9 .b 731. t6 la2.94 14.2%l-13 10.44 96.4 99.4 u?.6 274.6 55.9 514.0 . u ? 21. ni6 Iw2.93 14.338-34 in.47 96.3 99.4 97.9 274.6 55.9 515.6 . u ?41' . M 1R2.47 14.211-3% 10.43 %.3 99.4 64.3 274.6 55.3 513.5 . tr7 t E H4 191.96 14.141 - 'If. 10.45 %.3 99.4 isu . D 276.0 55.4 514.8 . k 73E *M 181.25 14.151-37 14e. 3=s %.3 99.4 87.7 277.3 55.4 518.9 . bf.f E *06 125.91 14.741 - 18e Id. M %.3 99.4 e7.6 277.5 $5.5 511.8 .b6MF oG ik6.23 14.711 - J 'J la.h %. 3 99.4 97.9 278.1 55.8 Sil.7 . WhE*06 465.50 14.f6l - de t 141. 4 4 96.3 99.4 84.4 272.9 55.n 514.0 . e 7 21. * o6 ' wil,97 14.121-41 los . 4') %.4 99.4 37.5 274.1 55.2 513.5
. N 7 t E.*o6D6 IMO.3d 14.16
l-42 lu.42 96.3 99.4 sk o 273.9 55.1 513.2 . s 7ut. lho.as 14. l es1-43 Id.45 %.3 99.4 kW.9 274.1 54.5 514.6 .u?3F*M lha.10 84.07|-44 10.42 90.4 99.4 S al . 0 274.0 55.2 51.1.2 8 70> .M 179. 5sl 14.116-45 15' 42 %.3 99.4 87.6 273.6 55.2 5.J.3 .870t.06 179.25 14.09l-46 16.44 96.3 99.4 s7.8 274.s 55.1 514.2 .5721+06 179.95 14 . m1-47 in.3e M.3 99.4 87.6 279.8 54.9 511.3 . p671: * 06 183.04 14.49l-as 10.44 %3 99.4 24.G 274.9 55.1 514.2
. 8 721' .* n617N.67 13.YJ
1-41 10.43 %.3 99.3 N7.5 274.6 54.7 513.7 37|E <E 18?.13 14.2850-0 10.37 96.3 99.4 87.7 277.3 54.s Ste.7 .666E 06 17.94 1.42
m .f1 Q U ~.
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.
;t -..g *-,
FLOW , "d W
FLDJ 4giiii vg i i vg i i 1 ji,e
.i1 i i1 1 ir i ,i, iy i 1 ,i 1 . . . i1 1 i , i1 ii
. .9 =.. ,*E E E*
, ,. =
i.:gaI*
*3,ya,
P- -". ?-U ". E I s ,8n O s
o . o s
- :- -E- k "-,
,'*
76 T mgE Ln 2um .
11,_ e
3
mk PW i k 3
$ca-
. ,,,.................... ,g g;,,,...................,
p -= s-,
MfM NL W I 73 ^ R'JN pefMR 73, 4 -I le 4 LP5 To le. 4 LPS *99.4 Of C C 93.4 CEC C
~ 274.0 pe 75 Isti = ~ 274.e are 75 lutEt-'' ~ * '%.5 aPq Con fra F %. 5 IL A CON f *WP
3.
ss.e sa.e 6a.e e.s ie.e 2e.e 3e. e as.e se.e 62.eI 2
e. e ie.e 2e.e 3s. s. .
AXIAL O! STANCE (CM) AX1AL DISTANCE (CM)
-158-
, i} Pb(| j \ U. .-
BEL Ft.Astilwa Flows ITPta luDffFRtMI RE LkCP Def a 71:04
TLNT 51 L.T ION 8 2
RL'4 NI'llBf R 738
LDur FIDW Yt WPE Rail RYS 801X) Cl PRFE'RE t1P A) WP10 CITY R a%OIDS D i >1TR FY! I A L F RIMT PFTAFS Li k/51I F1hw un t A TS14MT COND Ta>E TS Inu.T Cu=U TAME CN S t.C mi n atet etASthlb Di nL% ION LL2$
l-2 18.31 96.2 99.4 ts.1 ?hil . 7 52.3 Se8.5 . b6?F + t 4 43 .n3l*3 1o.J3 96.2 Yd . 4 N7.7 279.7 52.6 Sm.7 .k6 u .f 6 00 . nt il-4 10.35 96.2 9') . 4 67.6 2ki) . 5 52.5 su9.h .h65t.o6 1. 2'3 .in1-5 10.33 %.3 TA . 4 N9.4 279.8 51.5 SON.9 . M3 t' + 06 2.NI .22
*l-7 10.33 'Je2. 3 99.4 an.3 281.3 $2.1 5. u . 9 .hr3reo6 6. tw 4 ')
l-9 10.34 46.3 9J,4 kg.2 241.1 52.2 So9.1 .h63t H6 10 t 6 .hs
1-11 10.32 96.2 93.4 kN.0 2a0.H 52.4 50N.3 .h62!*D6 IN,16 1.45|-13 10.Ju %.3 9' A . 4 67.8 2ha.8 52.4 507.2 4Mii+06 26.43 2.13l*l5 10.33 %. 3 99.4 6 9. ft 2M't . 2 52.2 Vit . H 903f*OS 35.76 2.h61-17 1o.32 %.3 9') . 4 87.8 241.0 52.3 Sod.3 462F otA 55.N2 J.47|-19 10.31 %. 3 99.4 87.; 279.t 42.4 Sm.5 . h6 21 + 0ei 72.49 5.hul-20 10,36 96.3 9') . 4 8 7. N 281.3 52.4 S09.9 .M5! +44 M.61 6.v)1-21 to.32 %. 3 99.4 u?.7 2ka.7 52.5 5+m.3 . h 0 21. * * 6 101.05 N.251-?? In.31 %3 9'* . 4 87.9 240.7 52.6 5o7,9 . h b i l' 4 6 I ?6. f. 2 in.161-21 10 3) %.3 9'A . 4 87.9 241.5 52.5 NN.8 . b6 J1. 4 6 145.M2 l i . f.S1-24 la 3s %. 3 99.4 87.s ZW1.4 52.6 509.6 .M46*D6 174. 4 d 13.961-2% Id.3d 96.3 99.4 N7.8 2 *) . 2 52.6 507.0 .kwlH6 225.19 1%.111-?6 1i4.15 %. 3 99.4 km.0 27W,9 $2.7 9 "d . 6 .M al H% l '3 2 . P'J 15.311-27 to.31 % 1 9-) . 4 M7.M 2ha.1 52.7 Ni7.6 . Wit *** lh6.it I4.95|- Jis 16.32 %.3 93.4 67.m 240.3 52.W N$u . i .M?t a t6 thm.0M 15.121*29 10.33 %.3 9J.4 s7.6 279.5 52.7 Nm.9 .h6 M ai C !=7.47 14.9wl-34 10.32 %.3 99.4 >4.7 279.3 52.2 N*.o . kG i r H C in 7. h4 15 . t i6l-ll l e) . 3 2 96.3 99.4 h4.8 2ho.4 52.3 Sow.! . ht 2 I: + 4 6 147.37 1 % . t'26-15 10.35 96.3 99.4 W7.9 2kl.2 $2.4 Nr) . R . he .a t + 4 0 th7.52 14.911-37 10.3) 96.3 9'A . 4 k7.9 2he.4 52.6 N:d . 9 . h6.11 o m Ib6.51 I4.91l- TJ 10.32 %. 3 9'J . 4 h7.7 24o.8 52.7 Nm.2 .M2F un th6.M2 14.s71-41 i n . 3.) 96.3 99.4 87.N 291.4 52.6 Nm.6 . ML J L u wi th6.29 14.901-43 10.34 %.3 9') . 4 h9.5 2 hit.1 51.9 5o9.1 .w 3t.06 tu5.hs 14.h4t-45 to 32 %.3 9A.4 hM.5 2 7's . N 52,3 Soug . 3 .h62f 44 lh5.92 j d M't
1-47 10.34 %.3 9'J . 4 an.2 2ho 2 $2.4 Se r) . e . h 0 3 t. *i n 145.14 14.731-49 10. ~1o 96.3 99.4 hN.2 2hd.9 52.6 50 7.3 .h601+o6 tha.A0 14,h650-1 15). 3 2 96.3 Y) . 4 27.3 281.5 52.7 508.2 862 E + t6 17.71 1.42
% eD. ,' . .-
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hr rrg r re ,- rrrr,, ny rr.;2- w
my . ,.,7,. ,,,. m1 18 15 .d 3d , , ,15 42 45 43 T A*5 1 $ y.77, , , 77 .,,,m,m n. , . . y, , , , ,23 25 32 35 42 a5 43. ta 152
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~ ,I Pa v-Ma 73 .N P.*; st. -m 73:# 12.3 t% 2 | 2' is,3 tes
93 4 DC C'
i 99.4 :n c'
% 2*2.5 ("a is INLET 2*2.5 me r. '5 N !f.-
.
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N| 52.4 z*2 CN f red ~P 'I 52.4 da CCw m w|$ 2 2 'v--
s.t to a ze.e 3e.e ae.e sa. e sa.e o e.s t s. t 2a.t 22 a n?.a 12.a s2.2AXIAL DISTANCE (CM) 07'. L 0:57FNCE !CM)-
-159-1
t , ,, } ,'i__
l {. .
.
BNL R.ASillhG PLOlr5 EXPF1 tin 2stTFWI WkE I4fW DAT A F Moll
TLST Sl(1104 s2
2UN hUstilli '732
LEWV P'lDW Ti et R ATi llt$ 4 Cf.U Cl PRIMTRE (LPA) W*1DrlTV REih0f.DS DI FTi k t:NTIAl. PRF.W RPTAPS I f R/ht C M4h NL7 LR TS I NI.J.T 0040 TANE TS int.ET CuwD TAME CII Sir NtNRLM litAn aLD D i al.ss losti:ss
t-5 10.44 H6 # 99.4 89.9 244.0 52.5 514.2 672f' t2 2.65 21
t-9 10.4I 96.4 99.4 RII . I 2w4.7 52.1 512.4 . Nr.'il .14 10.79 .35I-13 IR 42 %.3 93.3 N7.7 2N3.7 $2.2 553.3 .llM ei4 26.R4 2 111-17 in.42 %3 99.3 e7.k 2k).9 52.3 513.1 . 87M ate 56/J4 4 . -184
l-21 10.43 96 3 99.3 87.6 2nd.3 52.2 513.6 .N70L 06 104.94 8. 2.1*
l-?2 10.40 96.3 M.3 67.9 ;w3.5 52.4 512.3 .66Ht.06 124.94 in.I7
t-23 10.42 96.3 99.3 s?.6 245.2 52.4 513.2 . h >L a t4 142.43 I I . r.r,
4-24 10.4% %3 9') . 3 b7.7 2M4.4 52.6 514.4 .u??t 06 177.34 13.57|-2% lu.41 %.3 99.4 NR.2 2h3 h 52.3 512.0 .Nf 41 *o6 2r+4. 39 16,14
6-26 10.43 %.3 (yl . 4 k7.7 2x3.6 52.4 5'1.4 .W 71 t i% 194.83 1%. hs
1-27 10.43 %.3 99.4 m7.9 244.u 52.6 SlJ.4 870t+o6 194.14 15.241-?u 1o.44 %.4 99.4 a7.m 245.3 52.6 514.0 . #7 21~ .(E 193.27 15.14
l - ?'J l e* 4 3 %.3 9'J . 4 bh.o 2w4.7 52.2 513.5 . N 71 f *f6 193.66 1%. 99
t-31 1u.43 9r. 4 99.4 kW.2 2k5.0 52.3 513.8 . N 71 ). * t 6 191.77 15. I'J1-3; 30.43 %. 4 99.4 64.1 2x4.3 52.5 513.4 .W701 * tE 192.67 t%.131-3 # li' . 44 %. 4 9J.4 97.8 2wS.9 52.6 513.9 . p71 t + t * 191.51 15 Hi
3-41 IH.42 %4 99.4 47.5 294.4 52.6 513.3 . H ?ol *+ E 189.91 14.921 - d's 10.43 %.3 (#J . 4 88.3 285.0 52.2 513.5 8711 06 185t . 91 14.A3
W- 1 10.44 %.3 99.4 is8. 5 2s5.0 52.4 514.2 .k72L 06 17.83 1.4a
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h- . > I i 6. - rT LJ 6 ; 5d
l' L (/.. .j webb b EM
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n,l 1Y ' ' '2e' ' '25' ' ' Y 15" "ad' ' ' '25" 49Fr~ ~,r, -m,-r -
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g RhNPNR 732 g g Run sc.".R 732
LS e. e, le.4 tr$Po- le.s
99.a Df C C 99.4 o(C C= ~' 284.5 <*A 15 INLETu "a.5 8 *E f 5 IKET '* ** 52.4 K*E CON 1 ANit.# 52.4 *PA C2% i Aw -L m _ r_ _ ,..__ _ J.2 2 _ .
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e.e le e 2e.e n.e ar.e St.e ee.e e.e le.e 2e.e n.e aa.e te.e te e, .v
AXIAL DIS!9NCE (CM) AXIRL O! STANCE (CM)
-160-
.n.he r
's /bh_ f '.
BWl. ftE3flWG F1.0VS DPf'A l dDffPRl"2a kt' DRor DAT A FRDA
TtST S11'f l04 e2
R131 kr u sfJi 7J3
LDnr F1(Mr 7t nPIRATt Ris eMX2 Cl PtimTRE IKP Al WF1 N ITY RFYWOfDS CltH 8fhTIAL Pk o v RPTAPS LY R>"AC F1.D9 ut.Tf]l TS [hLET CUWD T AWK TS |=LET COND TANE LN SIE hlMhlR Nt A*A N:D D I R} % 10% LINS
|-5 10.37 96.4 99.4 87.9 2ne.9 53.3 510.9 . HFJ.E . 06 2.62 .211 'J 16.37 %.3 99.4 67.7 287.7 53.4 510.7 . hts. F . (4 11.03 .h9
i-13 1u.34 %.4 99.4 hs.0 2ks.2 53.5 511.1 .h6 7L m 26.71 2.12
1-17 80.39 96.4 99.4 68.4 2N7.5 53.1 511.6 .b67tt4 56. f,0 4.44
1-21 10.37 %.4 9 J.4 sw.I 287.4 53.3 510.5 . h6r.E . tm 164.29 h 24
1-22 10.4u %.4 9'J . 4 87.7 2s7.8 53.5 512.2 .h69t t6 12'i.41 10.131-23 10.41 96.4 99.4 h8.3 2ha.1 53.5 512.1 . b6s t . t 6 147.48 l a .f.4l-24 18.33 96.4 99.4 h4.2 247.4 53.3 511.6 66hE t4 176. f,4 13. 'J 7
l-2% |u.34 %.4 99.4 ##.3 2k6.2 53.4 511.4 .hf.hr t6 201.29 15 93| - N. 10. 3') %.4 99.4 eM.e 287.5 53.5 511.6 . host =06 197.03 15.58l-27 1a.36 96.4 99.4 64.4 289.1 53.5 510.3 . hr.v o6 l % .06 1% + s
B - ?'8 10.4.1 %.4 99.4 h 7. 9 2N7.2 5 3. f. $12.2 . kr.9 t .i s 197.02 1%.54l- ?' t to.37 *an . 4 99.4 64.0 ?w7.4 $3.7 Sio.7 . ni .f. r . 06 195.72 I%.53
.
6-3 ) 10.34 %.4 9's . 4 87.8 287.3 53.6 511.1 . ht61.s % IM.47 15.49l-37 lu.37 %4 74.4 87.7 2s 7. 4 53.7 S IO . f, . kn6 t .it 194.00 15. -IS1-41 149. 4 0 %4 99 4 er) . 2 2M 7.0 $1.1 512.0 . h( h r o * 19 3 . <3 2 15.111-45 la. 6d %4 99.4 b4.7 2Nu.I 53.4 512.2 . ht.h r . t6 193.10 l% 2J1 - 4'A 16.37 %.4 99.4 he.6 2h5.9 53.6 510.9 . ht6P = 66 192.J7 15 26*48 1 10.34 %.4 SPA 4 Hs.3 2W6.8 53.7 541.4 . 86 7E.64 17. h6 I 44
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9'). A CM C93.4 010 C I 287.5 KM f 5 !w ETw i87.5 **A T5 tw ET . ~~. ~ * * **F $ 3. t va tcs Tow ! 53. A BPA C ON II W
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AxlAL DISTANCE ICM) AXIAL DIS 1ANCE (CM)
-161-
n| .)g-c ',
I l
Sht FL A91ING F1hws f3Pt'Rimf~lfffal/At w rif0P DATA F Ma se
TLST Si t fl0m e 2
RLN DUnillR 734
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l-5 in % %.3 99.4 as.e 2s 7. 5 54.1 519.8 . 665 E.(6 2 56 .201-il in.39 %.3 99.4 64.0 2N7.0 54.1 5[I.4 . bf.7F t 6 19.67 1,44
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| 14 4 92 116.2 I T) .1 14 % . 7 344,0 143.6 242.3 ,9.41 66 7'.>4 2f. . %l-M 4 9% l i f, 2 i 3 s.1 1643. 3 344.2 141. f. 2 41. f. . 9,71 u d. 7J %7 M. 9 'l - 1f. 4.95 116.1 11).1 IfE.s 342. es 142.7 241 f, ,9 41 n e, 71,. 0 7 21. .i %l-17 4.9% 8888088088 134.9 l ev. 9 342.2 142.3 2 J 3. is . % 71 ei n $s . 41 3 's111 4.91 I l f, u I Pf.0 10 7.2 342.6s 141 o 241.7 42 n d, la d 15 1. i *.Jf-Ie 4.91 11%.9 |M.E 10F. 4 3 40 , 4 142.4 24I.9 . Si 'l u * M 1 94 8 'l- ) 't i
g1-40 4 9t, 11% 9 1 746.06 168 7. 1 344.5 542.6 244.1 .*6,leiA b6.131 11.1'4t-41 4 95 IIS.9 11al . 7 le+,4 341.0 142.3 241.5 . %,9 u W. h) Ji 3'.'/l 4? 4.41 ||%.9 114.7 18 6 . f, 334.w 141.9 242.6 . %616 *i w 94 11 li I
l-41 4.31 la e 11's 7 I ne, . 3 34o.1 ial.9 242.9 . % )l . * % f.3 '. i- 7
1-44 4 47 1 15.1e lh 6 16 W. . ' 311.2 141.5 244.7 . % ''l a e v4.11 .I N . a s1% 4.97 11% 7 | * ben . 5 le 6.11 1 he . S 140 11 2J4 6 . Sf. 71 o i8, 1OI.20 3f. . I %|-40 4.9% lli 6 IN 4 It%.3 J ail U 1 449. 9 2 4 3. *f *f.9H6 102.180 ,1f. 9%.
l-4' 4.96 ||% 6 lb.4 140 4 317.1 140.6 244.4 . % 51 i t I n4. ii4 3 7. bel=4% 4.4% ||%.3 lh.4 isti . 9 137.1 140.3 243,N ,9.al e s 4. I t 'h . e di J un 951 -4'1 4.92 115 6 1 38s. 4 lit ,0 337.2 1 461. 3 242.2 . 9. I t n o I I 1. f.mi =i 7iSet- l 4 . 's 2 115.5 1 388. 4 106.2 336.7 140.3 242.3 . 56 t l. u 6 2 65 .97
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Ax!AL OlSihNCE ICM) Pxl AL D!STPCE I CM1
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VOID FRACTION DISTRIBUTION DATA
FIASilING EXPERIMENTS
. -
in(kPa) T.in( C) G(Mg/m s) pct (kPa) Tct( C)RUN p
730 285 99.4 4.91 54 88.0
740 285 99.4 4.91 54 88.0
762 394 99.3 6.05 61 88.3
770 157 99.3 3.05 67 88.5
771 157 99.3 3.05 67 88.5
780 138 99.3 2.61 71 88.1
781 138 99.3 2.61 71 88.1
792 125 99.4 2.26 76 88.1
793 125 99.4 2.26 76 88.1
801 582 148.3 4.34 434 143.5
802 582 148.3 4.34 434 143.5
812 493 148.3 2.91 431 144.4
813 493 148.3 2.91 431 144.4
821 376 142.3 2.34 175 111.3822 376 142.3 2.34 175 111.3831 350 140.0 2.30 147 107.5
832 350 140.0 2,30 147 107.5
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RCN h t' a M L3 73*TAPS '1 ' ' ' $ ' ' ' ' 12 ' ' ' ' 15 ' ' ' ' 2'2 ' ' ' ' 2 5 '32 ' ' 35 '42 '45' '45
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f'4.Se 1237 .3v . as37.lt 1242.9.65 LN7
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12. hr 12. e. . 2e .u4 Q f34.73 12:93 ..25 . a*4 424 .05 * w17.h 1243.
.id two W19.s2 1232
.13 . L'622.36 1238
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27.45 !?57 .0J 0427. N 1328 .U2 . t42s.44 1315. .02 05 0h . 'J 2 1374. .L *> 0'3M . 44 1303. .o? 0*J - [*yN . 9= 12w .
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35.865 1227.
31.53 1234.02 9%
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IO l:4.44 [397 , li : . t ,4
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T AP 49 14 54 St; A 'J'8 4 STD I D p]RUN 762- i3.,, ,m .n .e:
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7.tI ti74..34 c329 ."d 2G("g/m s) 6.059.fd il%i 2* 85
i..m i i n. .-i2 # .es ca 1.n u r. _ .ro .oS
-41' p (kPa) 39417,7% l i . *, . 21 .05
T[n(C) 99.3is. 2 . : v, . .ia .c5 mi: .v a m. .o . ' ' ' . in... a.. .m .< kPa 61z 7. < s a.s . c.t.
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v . s. _ .. .oi .m |:n 4< s ys ' . .en t<
.O I;tt . *f,? 13A4 ..K .P%7<> 13o.. .f** .07 3 tra l:.. 4.3, 20 .ia 09 p c;3e.d4 i wr. . 50 .09 t3 ,fwi t ;s 1, .ei .Di T j +31.51 tws. 00 .M -
I32.es 2mi. .e5 .05 -
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33.53 12''# . 02 .P1 N37.57 is?4 .04 03 W , ,
40.i$ f i 10 .03 .f 4,
I 4 2, f. 7 i%). .tus .P5 +~ as.:: , i n, . .~ .u +c47.7,s lii41. .60 .e5 *ss.3 a. ..n .esw , ,
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+ RUN NUFSE9 762 !,
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a,n n >
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nsT sterium e 2 FLOW +iiiiiiir 1 i
iiii'S,ii.;i 35 42,ii5 . 49TAPS 1 iii$iiiiiiii,415. i 4 22inii m nn 7,e
2 32 4.
laW AT inig tp AVFil LGr. kTW:WR -
cu |gcq U1 tim =TS AVFN4CE *
TAP 49 14 sd SEC ALII!A ST O DI Y OG
3 : ',', 'E: :: :s RUN 7707.11 11i.9. .d'*
"4
9.cs o.. u. .at2
|2:M |$d, :$$ :$ P_ G(Mg/m s) 3.05.os e
. n.iv.2 i2si.
in(kPa) 157.i . cc. tn pim.,i 9. u z2 n ar,' .in .o9
L:.y4 in(C) 99.3i i n.. .ni .n7 T27.4s i2ii. .in .o627.yo im. . o<. .cs pc.t.(kPa) 672 i249. .ni .e4 .o2,.7. 94i9 nio. . . . + .ra
i34s. .oi .as I en +2. 44 + + +2 7i 2344 .00 .c2 p a +
0 24 .oo .os24.92,22i on. .ni .i<. O .
.49 i276. .Os . Of. T*29.3 7.12 l ati . .02 0s *
29.9M 1232. . 41 2 .os M Q +30.24 1211. .H2 .P9
g 3d.4% 1161. .fU .10 N.g 3a.74 i t 'ia . .+44 09 (J1 ,g "t I . se 1216 .03 .Il
31,2s 1224 .D9 8Wyg 31.si 12*? . 4 %) .D4
34.76 1272 .Ps 06.09 Q042?.OI 12f.U ..t 6 .D6 +72 2F. 1264
,#+ ,32.52 i2s2. .64 .o* n, +, + + ,
32.77 1249. .n4 . t'7 G + + + + # ** %, ,33.02 122s. .nd 03 + ++33.27 1239, .06 .U7n . s, nm. ..+ .nn
-n n.n i 2 2r. . .ns .*as.os usi. .e9 .u7
. os. + RUN NUMBER 772~ v . s1 uu. .een.is u 2,. . <o
.n,t- 2. r,7 -.i. .c ..
.n.s.22 n< s. - in47.7s 1D22. .1% 04 i i i i . 1
0:n 3M: : 11 :"2 c.e t e. e 22.0 33.2 40.2 Ee.e 62.2
w..? ?.7.::"; :"s AXIAL DISTANCE (CM)U:s :r'
s s .e, ..sm.. _ .
n o- s u.s.< :o mw 49h
O. '. y . . ;. . 1 , . i\i.|| Dh,;W , j~ , ) V' - ~ ~
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841. | I AS'!! bG fl.OkT f ~k'1R illChi_-GA444 Ill.NN ilosi..Tra DAT4 f[QQ 4 ~
1LST SICTIGN s2
' ' ' " """" * I I
TAPS 1 I$I le 15 20 25 30 3'5 42 45 49i1 | I I I iiI iI i1 1 I I I i iiI I i iiiI i 3 I iiiI I I I I
IACATION ||I AVh,n 4Gl; Wl'OLR "
fil Fkr4 Of O,UhTS AbER4GR -
TAP 49 l ad 54 Sir All'fI A 5'TD DEY N
3.31 1254 .d2 34 RUN 7714.5N 12s6 42 .e57.11 1294. 43 . or.
2i?:'s |R': :3 : c(Mg/m s) 3.05oU.'s |20: 's :G V kPa) 157
1U(C)p
19.m2 1194 .12 .05 #
in( 99.32 2. 3c. u45. .o . w. T. n.224. w ir47 . ~ ,
c.t.(,Pa) 6.i27.4s i 2~ . .oi .% p x27. n i nn . .n7 .0727.94 12F O. 00 .D4 02M.19 1310 .03 .10 *
2*l.d4 1317 .05 08 d-24.71 1333 .el 07 I U29.92 13 3 - 01 .0% + , +g * +/ *> . /n 127H. 03 .f%29 ,481 1277 03 .D6 129.73 125n. .06 .06 +gQ2) . 9's 1232 . (50 .06 *V.24 1872 .M .0630. ad 8k 1142. * t% . (% N.i 30.74 11hu. .e5 .HS W
H ** ! . m1 1:M7 .07 . i'9@ 31.25 1233 . ef, . f nep 31. *. ] 12f 2. . 68 3 .ON +g :n t . 7b 1215 .03 .n932.04 1259, .HH 05 G12.26 1241 .09 .07 ,
,
32.52 1249 .05 .99 G-, + + + , + , ++ + + + + +32.77 1236 .05 .16 G * ,4 g+
+ *# p++ + +31.02 1242_ .Al .e4 + + +33.27 12 6 .04 063,3 . ,5,3, 1227 .H7 .073. a 3. .2 . o.,
!?:"' ||3: ::3 :E + RUN NUMBER 77140.55 1129 02 0242.67 I H'l l . 01 .0045.22 18 4.0
. . n,l . t iel2. 7 s Ims. .1 . <% , i i i i i ii;:0 :': ::n : e.0 10.0 20.0 30.e de.e 52.0 E0.0!?:'i 0: ::n :: AXIAL DISTANCE (CM).0. n m. . n._, .
_n%,
9
%
v
b
e e 88
. .
%
Rht FT AS1?l%C FLOkS P KPFD illrnifGA444 1 + .% N I T o m.T i ll DATA
TFST 50'fl0* 8 2 Ft.0W >>RUN M'ulu.A 790 3 g i ii; r i i ; ; i i i ,22 25,,,,32 35' ; '
y j y , 7 ; ;;,#31 - 10 42,;,''45 '49'
15toc T m in m ncr n nra .
CM FRr11 0F ON%TS A VT11 Mi' .
TAT 49 |N $4 Sff AUTA STD LT'V Q"3.31 931. .02 04
1:M M: :S :[? RUN 7809.fS '733. 06 05
12.1H [052. .10 0$ g g14.73 il27. .16 04 . 6G(Mg/m s) 2.59-17.29 I?o). .23 .H7 y69.n2 i 2.ia . .i; .o4 on
n * .i . ..o .o p Pa2 2. 3.r. in24.in il49. .oi ..,6
27.4s i va. .e4 .i<, T C) 99.327.7o i2s9. . .u ..# in
2R.44 1355. 02 . 6 '6 2 (fl~c.t.(kPa) 7127.94 1292, 02 .u7 Q p
?=.is i327 on .c7 .'
2M.71 1349. .A2 .o6 p Gr' 24.92 illi. .03 6M 32'i . 2t1 1327 .D5 .05(
2'). 73 1277..01 08 Z2*> . 44 13t '<*.nl .os gQ29.99 123%. .tus .e4
30.24 I t hi). , 97 . si 7g 30.d4 I I f.6 . . nti .e5 PQ,,
+381. 7 4 1191. . 03 .n4 U1g +31.00 1256 .s13 06g31.25 1247 .03 .o7 +g31.51 1250. . ass .oG31.76 1266 ..e4 .e7 + +32.01 12%7 . 02
,n7 g + +
++ U+32.26 1266 +94 05 , + +
k* * / +.+ +32.52 125%. .04 .ps a" + +, ,
+ + + +32.77 1273. .P2 .07 Q + +33.02 1241. .no .es , +33.2' 1273. .02 .e433.53 12??. itu 06
'q 33.74 1260 .ni 073%.0" 1172. .03 .ag
~. ' 3 7. s , n ao. .e2 .o7 + RUN NUMBER 782=0.15 1119. .04 .05', 42 G7 18 E6 04 ,p6JS.22 006 . ins .0547.75 1023. .i>5 .tu i i r i r rso.29 w%. - no
:oc 0.0 10.0 22.0 32.2 40.0 50.0 62.032.n 9 v, . ..es n3N 107 '': -::S :: AX1AL DISTANCC (CM)[N-. 60.45 h48 .02 .e5 "
.
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GAnwa li n11cp TER DAT* FLOW + !TIST SLCT!DM f2 '
TAPS '1'''$''''1'0''''1'S''''2'0''''2'5''''3'2''''?S ' ' 40 ' 45' ' ' 49'R!N h2MDTR 791
thCAT10v 1M AvivACE NFnRTR ~
Cu Fdr4 Or CochTS AVDIAGE w*
TAP 49 14 54 SEC ALT!! A STD DFV
h}4.5N 934 .03 03 'RUN 7813.si a94 .o3 .es
7.I1 941. ,f7 .049.05 9%. 01 .D4
q|
| .14 .M -G(Mg/m/- ') 138, 59s 2u . n+ noc. .0* .ns
14.7,3 i ,a l l . j piv.2 os. .24 .a6
in(kPa)19.N2123N.i.
2 69 05n . x, 99 3ii524.Na iisa..
.es .esin(C)T02
. o'727.ws >2in. .o: 71c.t.(kPa)
.o27.'O 12r o. .Di .10 027.94 .2... .e4 .n624.19 1332. 02 .07 *a
. # w{2 st . 4 4 6332. *0L .to2M.71 1342. .e2 04 I C24.92 43.17 05 . t* 5 g29.2n 130i. 02 .u62') . 4 4 1103 03 .e9 12'>i. 73
1243 01 . 44 9 Y]2 .9. n23n. .o\ .os a30.24 1190 .03 07 *
3').48l ilF 5 .01 ,07 N- +
30.74 1201 .0L 07 O +31. f h) 12t6, .a4 09
1 31.25 1242. .02 .P2 +H 31.51 1252. .04 09C 3i.76 12*33. .*2 .07
++& 32.01 i24t. 02 05 G +.,++++ . + , 4,./h4, + ++ +, +
1 32.26 1 21* 4 010,5
H, ++ +32.52 , 2rA . po ++ , , +N +.p , ,++32.77 12r.2 ., n t .% N33.02 1251 .04 .H733.27 42st. .UI .n733.51 125 A. .D! .0%
|33.7# 12s3 .nl .m!?:0 ||3: M :M + RUN NUMBER 781:40.t5 1143 .D2 0742.67 p 'N I . On .10
|45.22 1070 Al .e447.7%1047: :o2 :07
- 90 I I I ' isa.29 977 04 0'0 12.0 22.2 32.0 42,0 52.e 62.0N!E @! '!!3 iT; AXIAL DISTANCE [CM'60.45 es. .c2 .02 -
J1NJ'
f '! ''~I . P
fqy %. C~ ~:u m!1,-
~ u u wuuNiG-
. ,.
- - 4
B'41 Ft A51if *G nDW I FFR lWENTld *N I Tour'TE DATAGA#44um su;neu R FLOW +2
iiii iiii iiir it i int* newaEn 792iii$iiiiiiii.iiiii'e.iiiii..i 32 35 de 45 49le 15 2 25TR?S 1
LACAffoM IN AVER 4T wt WREll -CM FNott m WrNTS A% f R.47 .
TAP 49 IN $4 SEC Al.I'11 A STD CEV Gu
9is. .es3.3i . m.4.5 93s. .e .ns7.it 944 .et .P1 RUN 7929.6s 9s3. .no .e512 iD 1325. '97 . +' 5 C314.7' 007 ."3 .M - . G(Mg/m9s) 2.261072. 03 06 ~s
-
17. 2.hi9. 2 u d6 . ee, .ov m
in(kPa)125
7 22. 3.r.u so. .e4 .o7 p
2 4. . u xo. .o7 .ns27.45 i227 .o* .e6
Tin (C)99.4
t v.vo i ;<. 4 .o2 .*
c t-(kPa) 76v 94 nos . . w. .e* o0 29. .o2 . c<.
p2, . m
-
2 .u on. 2 . nc, 23 us-24.71 1354 ud 05 p G24.92 L31s. 05 .e$
r.29.20 1321. .oS .06 329.44 i364 .t% 09 *T
r2%7.1 s 2*r9. .u3 .64*
125% .P5 .e4 2' $''194 O..a,24 un. .o3 .ori34.44 l ir 6 0: .P9 Ng30.74 1231 .v7 6:9 Wg31.40 1250 4'3 .09q31.25 1267 .e3 05I 31.51 I?77 ol .e738.76 1240 . t w1 07 + + ,
+ 8 , *+*%+ +++32.01 1299. . 31 .e4 G + + , , +
32.26 1273. 02 .e4 ., + +
*+
37.52 1.**. 05 6% 0., + + + , 4 y+ ,+ ,
+ + *.' 2. 7 7 1273. .e4 09 G33.02 1263. 1% .0733.27 1241. 04 0733.51 62%9. .el .e433.74 1262. .e3 .DH I
35.05 8191 02 .07.<i .os + RUN NUtdBER 79237.59 iii 7 <>
40.15 1820 .03 .e74 2. f.7 10H7 .01 0745.22 1a47 .Hi 054 7.15 1041 .Di 06 I I i i i I
;":0 0 = :0 e.e 10.e 20.e 32.e 42.e 5e.e 52.e!?:0 0;: -:0 :0 AXIAL DISTANCE (CM)60.45 95 mi . .ul .e4
.-
\-
~7(m
\ - p
,1,:,.g, tgfs- n s, m ;. . ., .
'
s e, n < . a, .
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I,* *d bt %, gj .p
, j j,., f -{ jbP
A'tLN* .1
swt. n enc: n. css mentum __
(; A m il A M 5 SIT 04EtER DATArisT sicTica e 2 FLOW +RUM NUw$rt 793
IA S l''' '''0'' ' I'5 ' ' ' 2'0 ' ' ' ' 2 S ' ' ' ' W' ' ' ' ~*3 ' 4'0 ' '' ' ' '2''''493
LOCATIO'd lif AVEP Acr. preta --
c=vma = we~rs Avrnce*
TAP 49 14 54 SEC ALrita STD DEV q
3.31 914 . tm .e4 G
4.SH 'J J41 01 .06
7.11 952 ,01 .e59.ss 9.i 2 . .ci .o' RUN 793i2.in sus. . . .o .es
Oi 7. 2,3 l o ?.A . . 0.. 3
0114.7 2i o. s . .o. .
*
B:;! ||0: :0 :'' Dj- G(Mg/m s) 2.26
in(kPa) 125N:U OSI: :fd :N P
1n @) 99.427.7H 1272. 03 .)7 T27.9.i i3na. .nc .e4
.a .ns a. _ PC*b'(kPa) 76.32s.i9 iii9.
i .nc28.44 5342. O ( 1124.71 1354!. 03 .o72*4.92 1342. 06 .07 p G2'J . 20 1319. 05 .e3 32'J . 4 4 i309. 04 .ti
24.73 1298 .04 .rm T^2'J . 9M 1247 04 . f*6 230.24 L205 .on ,07 O31.49 i l *8 3. .e5 05
g Ja.74 1207 02 07 TOH 31.00 1249. .u3 .ua C1* 31.25 12r. i . .o3 .n?@ 31.51 1 28*9 . 34 05I 31.7G 1292. 02 1*A
32.Di 1.W7 03 . im,/4t *M ++#+Q j'32.26 1299. 03 .e4 + + + + +p+ ,
32.42 laut. .M .e5 , + , + % + + ++ 4 , + + ,
32;77 1279. 05 . t fi O +
33.n2 1273. .uR , tis G
33.27 1254 .01 . o'J33,53 125%. .00 97
33.74 124N. 6* * 04
35.05 1212. .n3 0n
37.59 i144 .00 Its
mi. i s n eu. .ni :ox + RUN NUMBER 79342.07 1047 .01 .M45.22 1043. 33 04
47.75 1953. 6t l .e450.29 992. 03 06 | ; I I I i
52.N3 9w6 .o3 .e5 00 10.0 20.0 30.0 40*0 52 0' b2.0.mss.w v in . ..o. AXIAL DISTANCE (CM)57.91 WI. .e: .e5+ 4s >". .e2 .3
u,~Jt n
e - y,
-} "f Ev_ t g h]nnQ F }. [.T'
33P*
V'MddYddsd$8#1L:+'
. . .
. . . .
nu. n Asnie n rws nrrainnerDt. W I Ti m DATA IGAmet
nsi sieriei7.t il FLOW +2|Rm ,,nna sai
TAPS l'' $ ' ' ' ' I'c ' ' ' ' 15 ' ' ' ' 2d ' ' ' 2'5 ' ' ' ' 3'e ' ' ' ' 3 5 ' ' ' ' le ' ' ' ' I5 ' ' ' i9I. DRAT [m tig AVER gcr 4f 4 tritC4 Thon f4 COINTS AVFRAN
,T A !' 4') 14 54 $[C AU h4 STD DEV=
N3.31 is97 75 .o44.54 1575. 73 .os7.11 1553. 7 .on9f5 1%l2. 6') .os32.10 14N7 . (. s ,04 g14.71 14ss. .60 04
~
*17.29 1407 .50 .05 Q.
t '). N 2 139w. 42 34 m * +22. 3f. 1319. .33 .m *24.84 12H7 ; .1 .cs +27.45 ,3a$, _;; ,g7
2,7. 7" , 7,32 13n3. ,oy +
.94 ,es. .2 . cr. o29.19 1434 .iw s. .a a w-9(~.y |@ .52 :n,,, .c. +. .i9
:n r- ozua ,454 .25 . c ..>.4- ,42,. 22 .v4 12'J . 7 3 |412. 23 ,072'f . 9 9 13s5. .29 ,pq ] +
,,.a.24 i2,7 .i6 .o1
g3d.49 69772 .
g30.74 1249 :71 :o|q h*
*+g
+[ + #6 w +ai.no i .v. 7 . . ,9e 3>.2s ,m. .a . r,u *e .c ~
'|:U. |s'.',: .'|? :r.,;,i *
s 7.*+ RUN 801+3 2. n,i . , o,
w ., .. + - . -3u. os . o . .+ + .. . ,
Si:F7 |L'J: :"7 :: g- * .2c(Mg/m s) 4.32+
31.02134 t9 [ |id ;n,7
gs g31.27 12 a)
in(kPa) 582733.51 oia. p:o, :os
osn 33.P nia. in
in(C) 148.3T. s. s an. .e, .a7'N U:Il |%2; ;g ;"; + RUN NUMBER 801 p c.t. M a) G, - 42. o n 30
i nn= .:e,s ',- es.22 n, nso.7s in
.M . 21 1.ie r 7.'n, ns
. -:g4 :(. 4I I I i 1 I$n:;;
;;"i :i:i !U AXIAL DISTANCE (CM).:3 0.0 10.e 20.0 39.: 42.c 52.e 62.0[' N:n ;;:
m.w
f. f* -p . f. t
,p -
t . S*% , i, 4
,Y f. ,u.{ c , -
._-{{{''' is
. . j r.1 - ta u - ,. .. u v.U u, ..
, gya s.u
BNL TLA917 4G ITF=S F'1tPP I RENT 1GAW4A l'E W I TO 8 LT ER DATA I
TIST SCCTION e2 NY|
Rt'N kt'n3ER 802 I I
TAPS I i$I le 15 2'e 25 S'e 35 40 45 49i I I I I I I I I I I I I iii1 7 I I I i I I I I a i 1 1 I I i ' I 3 L 3
UICAfl04 IN AVERACE NrmiEltCM FRf A Ol' COIwrs AVERACE _,
=
TAP 49 Iri 54 Sir Ati lla STD DEY Go
3.3i isos. .ra .e34.5= i467. 64 03 RUN 802
1 48,0. .7.18 .03 .039.ss o. .56 .o32.io o*2 .54 .n. ca 214.71 1341. 46 05 * - G(Mg/m s) 4.3217.24 1275 .33 .07 %4
in(kPa) 58219.N2 1252 .21 00 U1 p.2 06?? . x. wn ..1.s
*
Tin (C) 148.3.0724..< im. ++27.4s uw. 08 .e527.70 12*7 .04 .D627.94 1337 .30 .04 Q Pg g-(kPa) 434 +
+2s.is oss. .re .e5 .
29.44 I T)M . . t i9 .H4 2 m.29.71 1367 .od 09 p C +2N.92 1143. .05 052's.20 1352. . s"b 94 T2'> . 4 N 6130 07 . D'J *T
^29.73 1305. 04 07 +29.99 1203. 05 .06 E G31.24 1243. 07 .H5l 36.48 1200 .n7 .o5 NN 30.74 1226. 04 .t 3 LTI +
O 31.00 1250. 02 . it'JO 31.25 12N7 .05 06 ,I 31.51 12'so . 02 .0G31.76 1320 07 56 + , , + ++ u +
g ,'*+e 4 * I32.ts l 1314 03 .pG G + + + + t
32.52 1291. .01 .05 C9.+ + + *32.26 1103. .03 06 + + <*
+32.77 1206 .Di .07 O33.02 1244 .OR 0733.27 12w7 .e4 0733.53 127R. .03 0531.74 1271 03 . 0'335 nt il97 ni sy)
+ RUN NUM8ER 80237.59 I?ON 03 61N
40.15 6157 02 0742.67 ii17 04 .ON45.22 18 .HI , 64 3
t o'9 447.75
11 0 ;a"k. : ,' :: e.e 10.0 2e.e 30.0 40.0 Se.e se.e. .01 .DG I i I i I i
:!;:!? su: :M :'4 AXIAL DISTANCE (CM)60.45 945. .05 .05
7~ . ' %
/
a %.m7.-
; ,n . ,n,;' u s J:-{ s.
+w' . dl 5.
N' b d 'e -
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j O' LJ ,Q: I /t,'
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6 * .
BNL TI AS'll%G f1Pht iltPERluDITCA st * 4
nm sieria .R DATA FLOW +LIMiToMITF
2
RL'N NIMBER 812 1 1
TAPS,. 1 I$I le i i '5i i i i '2.I
25 'e 'S 42 ii,5 toI I i ( i I i 1 iI i i i .s iii iiiiiis ii;l 2 * * 4U)f' AT I ON IN AVER 47 hir'RPR *
Cu FRon UI W NTS AVFNACR .
TAP 49 IN 54 SIT All'li A STD DEV Q"G
3.31 1027 .14 054.54 IOSH. 12 04 R,u,N oi9ot7.II 1947 .t7 .049 . F.5 1102. .20 0,5 912. til I147 . 2.1 63 g 6
G(Mg/tri s) 9. 88i4.73 ii7s. .23 .r5 .
17.29 1174 .in .<4 q'i n. 6.
.i7 .o m p111(kPa) 493i9. 22 2. 3r, 12 . . .\2 .o7
in(C) 148.324 i2in. .o .os T2 7. .n 9si z 7n,, . .in e7
C,t,(kPa) 43127.vo i2= . .oS .e7 p27.94 1315 06 .''6 g24.19 1319 . s* * .0%29.44 1376. 6is .U7 B m-2H.71 13A3. 34 06 o24.92 1369. . sv3 .In2'd . 20 54d4 .t6 . (% T29. 4 fil 1312. . ti? .07 y29.73 1219. 01 .0429.94 1270 .tn .H9 )
12 .nl , ent .g30.24l l HN.2 5.30.48 M. ,HS .05 N~ . .30.74 i20s. . r io .12 my ,3 t . (H 12(4 .n5 .H5g ++ , +
31.25 1244. .03 05O 31.51 12s9 . o.: .e7 + +H 31.76 1346. 04 . e47
+ , ,I 32.01 1320 .o4 ,07 o #
# ++++h4+
* #32.26 1302. 03 09 . ~+
++ + + * , * +32.52 IloH. 1% .s% G + +32.77 12' H . 05 .in G + 4
+33.01 12r,'3. .n5 .o933.27 12r.6 6. ' 64 4
'l_ 1 127 03 0712r.'J .32 . 79 g. .P2 .u7
35.95 1172 .e4 .PN. f' 7 + RUN NUMBER 81237.51 I l'W .
01,n.is n .o. . .$. o.42.67 IDW5. A2 .0745.22 1889 5 .D3 .0547,75 [4 26, ,64 ,07 , , ,
3 M:n E: :s % e.0 10.0 2e.c 30.e 4e.e se.e s'e. cN IU? .N?: ::"2 :: AXIAL DISTANCE (CM), 08.45 9 13. .02 .e5
(s
V4
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851. VI A911%G FILh5 FxPEn t WEwTDt.h S I Tns L DATAGAN44u sT sirfio.1,[R2 FLOW +
IlN NUMBER 813 iI I
TA S 1 I$I 10 15 2'eiI I I 1 , I I I I I 1
I I I .2'5 32 35 4e 45 49I i l I i1 I I .1 i i i1 1 I i I i
LOCATinN tu avEMAtz Na nER -
Cat Frail of (.Y)t'47S AVtRAGE .
TAP 49 IN 54 SEC Ati ll A STD DEV r9 1C !
3.31 1039. .12 .nd
1:i" |2,1 :|| :|j i RUN 8139. r.5 1 s* # 7 21 .04 I12.to i127 2i . t r. G j <)
|;:'l ||'s: 32 ::; y G(Mg/m's) 2.88' *
0 :52 If?2: .|? :% p
in((kPa)493
24.n i2nx. .e 7. i r,..i C) 148.3.a3 T27.ds i240.
in27.7- u.r .ni. <$. aj pC.t.(kPa) 431zu. i .wi . . . < . .o
2a.is r3%. .o3 .os29.44 1377 . vi 7 .on Dm,
,2=.7i 3. .o9 .o7 r- 0 1o,s3.2=.92 i .o9 . tm
T,- !23.2u i326 . i d, .os.w . * im. .os .ns -
21.73 i329 .De .e5 *
29.99 1276 . fa9 . tE M Q30.24 12$3. .in .p7
g3".49 1t95. 07 .32 N, + +N 30.74 122l. 05 .im W + +O 31 lit 1291. 01 .10
N 31.25 s h *4 .lo .12 ++ *+1 3i.5i 1242. . a i2 .s* + +,
4,9+
+,\ "%Ji.70 1305. .n5 .oM + * /32.nl i32%. .is .09 g , + +* +' +,32.26 1317 .it 47_ + + + ,
+ +32.52 !?w3. .bJ 08 rg+32.77 42%2. 06 .06 Q
33.02 i 2M . .se .s433.27 1252 .ol .on31.53 1264 02 .0733.72 6263 .o3 .0735.0,5 :Hi + RUN NUMBER 813
li90 .nN37.s i22i. w. .in40.]3 | | $, r . ,c2 ,g742.07
i,l 1,3. . 04, . 0,64s.22 , . .c .,4>.7s io. . ,2 .no , , , , ,
0:0 :ff: _:;a1 :"s e.e 1e.e 2e.e 3e.e 4e.e Se.e ee.c'
B:?! |in: ~ ::1 :f,2 AXIAL DISTANCE (CM):60.45 925. .03 .0J
S~. .
' 7
. f , p.j .. ~} ' _f}p-;||, $ j.
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TIM NICILON 8 2 C)"QW 4* "
nrw wrunca s2t i
1993 1 ii;8iii1 le 15 29 2'S'aq q 5 ' ' ' ' lo ' ' '45'''A9
I I ( 1 I i1 6 1 5 1 * 1 1 I I iI I Io - - ~gjy,a y tog | ti
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-
++ .3.31 197'-
*4j,, :;;3':i" !" :*
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1,7:gaa 14f7 33 ,pq gn is":
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??:i' ISTi: :N :S4:0 |E}: a!! i;2 /p"(kPa) 376;
(C) 142.3f + RUN NU''BER 82137.5,9 123 .p "D.(kPa)
'
175.n.% i2ni. .o .es
2. m, u r.~ . ~ C.;i.s:,! !".0,i :'?, :'1
no .i. .
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e e.e te.e 2a.e 32.0 42 e Se.e s2.c.
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+ *IAF 49 IN 54 SEC Atru4 TfD DET 97
03.31 1923. 1.na .e34.59 1924 1.na .o3 +7.I1 ! '.b ' t . | . tic .049.05 th25. I.e2 . ** 2 +
12.1d 1917. 1.02 .03 g14.73 17se. 97 04 ,
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DISTRIBUTION LIST
G. Bagchi, NRCD. Basdekas, NRCV. Benaroya, NRCC. Burger, NRCR. T. Curtis, NRCS. Fabic, h1CD. Fischer, NRC,
Y. Y. Lau, NRCW. Y. Kato, BNLC. N. Kelber, NRC,
H. J. Kouts, BNLR. Mattson, NRCA. W. Serkiz, NRCL. Shao, NRCM. Silberberg, NRCL. Thompson, NRCH. Todosow, BNLL. S. Tong, NRCR. W. Wright, NRCN. Zuber, NRC
BNL RSP Division HeadsBNL RSP Group LeadersBNL RSE Modeling Group
U.S. NRC Division ofTechnical Informationand Control
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