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ASME- PTC10

ADOPTI ON NOTI CE

ASME- PTC10, Compr essor s and Exhaust er s, ' ' was adopt ed on

Oct ober 3 , 1994 f or use by t he Depar t ment of Def enseDoD) .

Pr oposed changes by DoD act i vi t i es muste subm t t ed t o t he

DoD Adopt i ng Act i vi t y: Di r ect or , US Ar my Mobi l i t y

Technol ogy Cent er / Bel voi r , ATTN: AMSTA- RBES, For t Bel voi r ,

VA

22060-5606. DoD act i v i t i es may obt ai n copi es o f t hi s

st andar d f r om t he St andar di zat i on Document Or deresk, 700

Robbi ns Avenue, Bui l di ng 4D, Phi l adel phi a, PA 19111- 5094.

The pr i vat e sect or and ot her Gover nment agenci esay

pur chase copi es f r om t hemer i can Soci et y of Mechani cal

Engi neer s , 345 East 47t h St r eet , New Yor k, NY 10017.

Cust odi ans:

Ar my - ME

Navy - YD- 1

Ai r For ce

-

99

Adopt i ng Act i v i t y

Ar my - ME

FSC 4310

DI STRI BUTI ON STATEMENT

A.

Appr oved f or publ i c r el ease;

di s t r i but i on

is

unl i m t ed.

merican Society of Mechanical Engineers

Services

YRIGHT American Society of Mechanical Engineersensed by Information Handling Services

http://www.bzxzw.com/

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merican Society of Mechanical EngineersYRIGHT American Society of Mechanical Engineers

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ASME

PTC

10-1

997

Performance

Test

Code

on

Lompressors

and Exhausters

merican Society of Mechanical EngineersYRIGHT American Society of Mechanical Engineersensed by Information Handling Services

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S T D . A S M E

P T C L O - E N G L 1977 m 0757b70 Oh05923

158

m

Date o f Issuance: September 30,

1998

T h i s d o c u m e n t

will

b e r e v i s e d w h e n h e S o c i e t y a p p r o v e s h e s s u a n c e of a n e w

edition.

There

wi l l be no

a d d e n d a issued

to ASME

PTC 10-1997.

P lease Note : A S M E i s s u e s w r i t t e n r e p l i e s

to

i n q u i r i e s c o n c e r n i n g n t e r p r e t a t i o n of

t e c h n i c a l a s p e c t s

of

t h i s d o c u m e n t . T h e i n t e r p r e t a t i o n s a r e n o t

art

o f t h e d o c u m e n t .

PTC 10-1997 is being issued with an automatic subscription service to the interpreta-

t i o n s t h a t will b e i s s u e d to

it

u p to t h e p u b l i c a t i o n of t h e n e x t e d i t i o n .

ASME is the registered trademark of The American Society

of

Mechanical Engineers.

This code or standard was developed under procedures accrediteds meeting the cri teria for

American National Standards. The Standards Committee that approved the code or standard

was balanced to assure that indiv iduals f rom competent and concernednterests have had an

opp ortun ity to art icipate. The proposed code ortandard was made availableor public review

and comment which provides an opportuni ty for addi t ional publ ic input f romndustry, academia,

regulatory agencies, an d the public-at- large.

ASME doe s not approve, rate, or end orse an y item, constru ction, proprieta ry device,

or activi ty.

ASME does no t take any pos it ion with respect to the val idityo f any patent r ights asserted in

connect ion wi th any i tems ment ioned in th is document, and does notndertake to insure anyone

uti l izing a standard against l iabi l i ty for infr ingem ent of anypplicable LettersPatent, nor assum e

any such l iabi li ty. Users of a code or standard are expressly advised that dete rmination of the

val idity of any such patent r ights, and the r isk of infr inge men t of such rights, is entirely their

own responsibi l i ty .

Participation by federal age ncy repres entative(s)or personb) af f i l ia ted wi th industry is not to

be interpreted as governm ent o r indus try end orseme nt of this cod e r standard.

ASME accepts espo nsibi l i tyfor onlyhose interpretat ions ssued in accordancew i th governing

ASM E procedure s and pol icies which preclude the issuance

of

in terpretat ions by ndiv idual

volunteers.

No par t of th is document may be reproduced in anyorm,

in an electronic retr ieval system or otherwise,

withou t the p rior writ ten perm ission of the ubl isher.

The A merican Society of Mechanical E ngineers

Three Park Avenue, New York, NY

10016-5990

Copyr ight (B 1998 b y

THE AME RICAN SOCIETY OF MECH ANICAL ENGINEERS

All Rights Reserved

Printed in U.S.A.


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FOREWORD

(This Foreword is not a part o f

ASME

PTC 10-1997.)

PTC

10

was

last

revised in 1965 and t has been reaffirmed many timesn the intervening

period. The PTC

1

O Committee has been in various states of activity for approximately

the past20 years. During that time the Code

as

been completely rewritteno be

far

more

explanatory in nature.

The performance testing of compressors

is

complicated by the need in virtually every

case to consider and make correction for the differences between the test and specified

conditions. The echniques used to do

so

arebased upon he rules of fluid-dynamic

similarity. Some familiarity with this fundamental technique wi ll be

a

significant aid to

the users of PTC IO.

Compressors and exhausters come in

all

sorts of configurations. A very simple case i s

a single section compressor with one impeller, and single inlet and outlet flanges. Many

more complex arrangementsexist with multiple inlets,outlets, mpellers,sections, in-

tercoolers and side seams. Typical gases handled areair,

its

constituents, and various

hydrocarbons. Tests are commonly run in the shop or in the field, at speeds equal to or

different from the specified speed, and with the specified or a substitute

gas.

In order to

handle

this

vast array of possibilities PTC 10 reduces the problem o the simplest element,

the section, and provides the instructionsor combining multiple sections to compute the

overall results.

Uncertainty analysis can play a very mportant role in compressor esting, from he

design of the test to interpretation of the test results. In all but the very simplest of cases

the development of an analytic ormulation, ¡.e., in simple equation orm, for overall

uncertainty computation

is

formidable. The test uncertainty wi ll always be ncreasingly

more complex to evaluate with the complexity of the compressor configuration, and by

the very nature of the test wi ll be a function of the performance curves.

The modern personal computer

is

readily capable of completing the calculations re-

quired. The Committee developed software and used it to perform both the basic code

calculations and uncertainty analysis computationsfor aide range of possible compressor

configurations.

This Code was approved byhe PTC 1O Committee on January 18,1991.twas approved

and adopted by the Council

as a

standard practice of the Society by action of the Board

on Performance Test Codes on October 14,

1996.

It was also approved as an American

National Standard by the ANSI Board of Standards Review on April

22,

1997.

iii


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~

S T D - A S M E PTC L O-EN GL L997 D 0759b70

Ob05925 T 2 0

NOTICE

All PerformanceTestCodesMUST adhere to the equirements ofPTC 1, GENERAL

INSTRU CTION S. The following nformation is based on hat document and is included

here for emphasis and for the convenience of the user

of this

Code.

It is

expected that

the

Code user is

fully

cognizant

of

Parts

I

and III of

PTC

I and has read them prior to applying

this Code.

ASME Performance Test Codes provide test procedures which yield results of the highest

level

of

accuracy consistent with the best engineering know ledge and practice currently

available. They were developed y balanced committees represen ting all concerned interests.

Theyspecifyprocedures, nstrumentation,equipmentoperatingrequirements,calculation

methods, and uncertainty analysis.

When tests are run in accordance with thisCode, the test results themselves, without adjust-

ment for uncertainty, yield the

best

available indication of the actual performan ce

of

the

tested equipment.

ASME

Performance Test Codes do

not

specify means

to

compare those

results to contractual guarantees. Therefore,

t

is recommended that the parties tocommercial

test agree

before starting the test and preferably before signing the contract

on the

method to be used fo r comparing the test results to the con tractual guarantees.

It is

beyond

the

scope of any code

to

determine or interpret how such comparisons shall be made.

Approved

by

Letter Ballot

#95-1

and B E C Adm inistrative Meeting of March

13-14, 1995

IV


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PERSONNELOFPERFORMANCE

TEST

CODE COMMITTEE

NO.

10

ON COMPRESSORS

AND

EXHAUSTERS

(The following

is

the roster of he Com mittee at he time of approva l of this Code.)

OFFICERS

Gordon J. Gerber, Chair

Richard J. Gross,

ViceChair

jack H. Karian,

Secretary

COMMITTEEPERSONNEL

Helmut B. Baranek, Public Service Electric & GasCompany

John J. Dwyer,

Consultant

Gordon

J.

Gerber,

Praxair

Richard J. Gross,

The University

of

Akron

Jack

H.

Karian,

ASME

Robert E. Lawrence,

Consultant

Jack

A.

Lock,

Lock E ngineering

Vincent

J.

Polignano,

IMO Delaval

Frank H. Rassmann,

Elliott Comp any

Norman

A.

Samurin,

DresserRandCompany

Joseph A. Silvaggio,Jr., Alternate to Polignano, IMO Delaval

V


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STD-ASME

P T C

L O - E N G L L777 m

0757b70 O b 0 5 4 2 7

A T 3

m

B O A R D

ON

PERFORMANCE TEST COD ES

OFFICERS

D.R. Keyser, Chair

P. M. Cerhart, Vice Chair

W.

O. Hays, Secretary

C O M M l l T E E P ER SO NN EL

R.

P.

Allen

R.

L.

Bannister

B. Bornstein

J .

M.

Burns

J. R.

Friedman

G. J. Gerber

P.

M.

Gerhart

R. S. Hecklinger

R.

W.

Henry

D.

R. Keyser

S. J.Korellis

J .

W.

Milton

G. H.

Mittendorf, ]r.

S. P.

Nuspl

R.

P. Perkins

A. L. Plumley

S.

B. Scharp

J.

Siegmund

J.

A. Silvaggio, Jr.

R.

E.

Sommerlad

W. G.

Steele, Jr.

J. C.

Westcott

J.

G.

Yost

v i


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STD-ASME P T C LO-ENGL

CONTENTS

Foreword . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CommitteeRoster . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BoardRoster . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Sect ion

1 Objectandscope

. . . . . . . . . . . . .. . . . . . . . . . . . .. . . . . . . . . . . . ..

2 Definitionsndescription of Terms

. . . . . . . . . . . . . . . . . . . . . . . . . .

3

Guiding Principles

. . . . . . . . . . . . .. . . . . . . . . . . . .. . . . . . . . . . . . ..

4 InstrumentsndMethods of Measurement

. . . . . . . . . . . . . . . . . . . . . .

5 Computationf Results . . . . . . . . . . . . .. . . . . . . . . . . . .. . . . . . . . . .

6

ReportofTest . . . . . . . . . . . . . .. . . . . . . . . . . . . . .. . . . . . . . . . . . . .

Figures

3.1

3.2

3 . 3

3 . 4

3 .5

3 . 6

3 . 7

4.1

4 . 2

4.3

4 . 4

4.5

4 . 6

4.7

4.8

4 . 9

4.1

O

4.1

1

4.1

2

5.1

Section Control Volumes

. . . . . . . . . . . . .. . . . . . . . . . . . .. . . . . . . . .

Typical Sideload Sectional Compressors

. . . . . . . . . . . . . . . . . . . . . . . .

Allowable Machine Mach Number Departures. Centrifugal

Compressors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Allowable Machine Mach Number Departures. Axial Compressors. . . .

Allowable Machine Reynolds Number Departures. Centrifugal

Compressors

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Schultz Compressibility Factor- unction Y versus Reduced Pressure

Schultz Compressibility Factor- unction

X

versus Reduced Pressure

OpenInlet . . . . . . . . . . . . . .. . . . . . . . . . . . . . .. . . . . . . . . . . . . .. . .

OpenDischarge

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Diffusing Volute Discharge With Nonsymmetric Flow . . . . . . . . . . . . .

TypicalClosedLoop . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Typical Closed Loop With Sidestream . . . . . . . . . . . . . . . . . . . . . . . . .

Straighteners and Equalizers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Inlet Nozzle on an Open Loop . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Discharge Nozzle on an Open Loop, Subcritical

Flow

. . . . . . . . . . . . .

Typical Sidestream Inlet Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Specified Condition Capacity Coefficient for SpecifiedCondition

Capacity of Interest

. . . . . . . . . . . .. . . . . . . . . . . . .. . . . . . . . . . . .

Inlet and Discharge Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Vortex Producing Axial Inlet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Discharge Nozzle on an Open Loop, Critical Flow

. . . . . . . . . . . . . . . .

Tables

3.1 PermissibleDeviationFromSpecifiedOperatingConditions for

Type1 Tests

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

iii

vi

V

1

3

11

23

39

55

1 4

16

18

19

2 0

21

22

24

24

25

25

26

26

27

29

32

33

33

35

49

12


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S T D * A S M E P T C LO-ENGL

L997

D

D759b70

0b05429 b7b

W

3.2 Permissible Deviation FromSpecifiedOperatingParametersor

Type1nd2Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

3.3 Limits of DepartureFromdeal GasLaws of Specifiedand

TestGases

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

3.4 Permissibleluctuations of Testeadings

.......................

14

5.1 Ideal Gasimensionlessarameters

..........................

40

5.2

Realasimensionlessarameters

...........................

41

5.3 Total Work Input Coefficient. All Gases

. . . . . . . . . . . . . . . . . . . . . . . .

48

5.4 Typical Conversionfimensionlessarameters

. . . . . . . . . . . . . . . . .

50

Nonmandatory Appendices

AUse of Total Pressureand TotalTemperature to Define Compressor

Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

B

Properties of Gas Mixtures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

Cample Calculations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63

C.l Type

1

Test for a Centrifugal Compressor Using an deal Gas

. . . . . . . .

65

C.2Type2Test for

a

CentrifugalCompressorUsingan dealGas

. . . . . . . .

85

C.3 Ideal Gas Application to Selection of TestSpeed and TestGas and

Methods of PowerEvaluation .............................. 109

C.4 Treatment of Bracketed TestPoints

............................

119

C.5 Selection of a Test Gas for a Type 2 Test

Using

Ideal and Real Gas

Equations.............................................

123

C.6 Type 2Test Using RealGasEquations forDataReduction . . . . . . . . . . 139

Intercoolers,CondensateRemoval .......................... 151

C.8 Application of UncertaintyAnalysis

. . . . . . . . . . . . . . . . . . . . . . . . . . .

159

D References

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

165

E Rationaleor Calculation Methods ............................ 167

F

Reynolds Number Correction

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

183

G

RefinedMethodsoralculatingotalonditions

. . . . . . . . . . . . . . . .

185

H

SIUnits

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

187

C.7 Treatment of a Two SectionCompressor

With

ExternallyPiped

viii


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~~

~ ~ ~~ ~

S T D - A S M E P T C 1 0 - E N G L 1777 W

0759b70

Ob05431 378

COMPRESSORS A N D EXHAUSTERSSMETC 10-1 997

SECTION 1

-

OBJECTANDSCOPE

1.1 OBJECT

Theobjectof this Code i s to providea test

procedure to determine the thermodynamic perform-

ance of an axial or centrifugal compressororex-

hauster doing work on a gas of known or measurable

propertiesunderspecifiedconditions.

This Code is written to provide explicit test proce-

dures which wi ll yield the highest level of accuracy

consistent with the best engineering knowledge and

practice currently available. Nonetheless, no single

universal value of he uncertainty is, or should be,

expected to apply to everyest.The uncertainty

associated with any individual PTC 10 test

will

dependupon practical choicesmade in terms of

instrumentationandmethodology. Rulesare pro-

vided to estimate the uncertainty for individual tests.

1.2

SCOPE

1.2.1 General.

The cope of

this

Codencludes

instructions on test arrangement and instrumentation,

test rocedure, ndmethods for evaluationand

reporting of final results.

Rules are provided for establishing he following

quantities,corrected as necessary to representex-

pected performance under specified operating ondi-

tions with the specified gas:

al quantity of gas delivered

(b) pressure rise produced

(c) head

(d) shaft power required

(e) efficiency

(0 surge point

(g)

choke point

Other than providing methods for calculating me-

chanicalpower losses, this Code does notcover

rotor dynamicsorothermechanicalperformance

parameters.

1.2.2

CompressorArrangements. This Code

i s

de-

signed to allow he testing of single orultiple casing

axial or centrifugal compressors or ombinations

thereof, with oneormore stages ofcompression

per casing. Procedures are also included for exter-

1

nally piped ntercoolersand for compressors with

interstage side load nlets or outlets.

Internally cooled compressorsare includedpro-

vided hat test conditions are held nearly identical

to specified conditions.

Compressors, as thenamemplies,areusually

intended to produceconsiderabledensitychange

as a esultof the compressionprocess.Fansare

normally considered to be air or gas moving devices

and are characterized by minimal densitychange.

A

distinction betweenhe

two

a t

timesmaybe

unclear. As

a

very oughguide,either PTC 10 or

PTC 11 maybeused for machines fall ing nto the

approximatepressure ratio rangeof 1.05 to 1.2.

Themethodsof PTC 10, which provide for the

pronounced effects of density change during com-

pression, have no theoretical lower limit. However,

practical considerations regarding achievable accu-

racy become mportant in attempting to apply PTC

10 to devices ommonly lassified as fans.For

example, he low temperature iseassociated with

fans may lead to large uncertainty in power require-

ment if theheatbalancemethod

i s

chosen.Fans

also may require traversing techniques for flow and

gas state measurements due to the inlet and discharge

ducting systems employed. Refer to PTC 11 on Fans

for urther nformation.

1.3 EQUIPMENTNOTCOVERED

BY

THIS

CODE

The calculation procedures provided in this Code

are based on thecompressionof

a

singlephase

gas.They should not be used for

a

gas containing

suspendedsolids or any liquid, when l iquid could

be

formed in thecompression process, or when a

chemical eaction takes place in

the

compression

process.

Thisdoes not preclude he use of this Code on

a

gas where condensation occurs in a cooler provid-

ing the droplets are removed prior to he gas entering

the next stage of compression.


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ASME

PTC

10-1

997

1.4

TYPES OF TESTS

ThisCodecontainsprovisions for two different

types of tests. A Type

1

test must

be

conducted on

the specified gas with a limited deviation between

test and specifiedoperatingconditions. A Type 2

test permits he use ofasubstitute est gas and

extends the permissible deviations between test and

specified operating conditions.

1.5 PERFORMANCERELATIONTO

G U A R A N T E E

This Code provides

a

means for determining the

performance of a compressor at specified operating

conditions.

It

also provides a method for estimating

the uncertainty of the results. The interpretation of

the

results relative to any contractual guarantees is

beyond the scope of

this

Code and should

be

agreed

upon in writing prior to the test by the participating

parties.

1.6 ALTERNATE

PROCEDURES

Definitive procedures for testing compressors are

describedherein. If anyotherprocedureorest

COMPRESSORS AND EXHAUSTERS

configuration is used, this shall

be

agreed upon

in

writing prior to the test by the participating parties.

However, no deviationsmaybemadehat will

violate anymandatory equirementsof this Code

when the tests are designated

as

tests conducted in

accordance with ASMEPTC

10.

The mandatory rules ofhis Code are characterized

by

the use of the word "shall." If a statement

i s of

an advisory nature it

i s

indicated by the use of the

word "should" or i s stated as a recommendation.

1.7 INSTRUCTIONS

TheCode on General nstructions, PTC

1,

shall

be tudiedand followed whereapplicable.The

instructions n PTC

10

shall prevail over other ASME

Performance Test Codes where there

is any

conflict.

1.8 REFERENCES

Unlessotherwisespecified, eferences to other

Codes refer to ASME Performance Test Codes. Litera-

ture eferencesareshown in Appendix

D.

2


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~~

STD-ASME

P T C 1 0 - E N G L L777 m 0759670 Ob05q32 Lb0

m

COMPRESSORS

AND EXHAUSTERS ASME PTC 10-1997

SECTION

2 -

DEFINITIONSANDDESCRIPTION

OF

TERMS

2.1 BASIC SYMBOLS AND UNITS

Symbol

A

a

b

C

C

C

CP

CV

D

d

e

f

gc

H

HR

h

h,

j

K

k

In

MW

Mm

M

m

log

m

N

n

n

ns

P

P

P v

Qext

O m

Descript ion

Flow channel cross sectional area

Acoustic velocity

Tip width

Coefficient of discharge

Molal specific heat (Appendix B only)

Specificeat

.

Specific heat at constant pressure

Specific heat at constant volume

Diameter

Diameter of fluid meter

Relative error

Polytropic work factor

Dimensional constant, 32.1

74

Molal enthalpy

Humidity ratio

Enthalpy

Coefficient of heat transfer or casing and

adjoining pipe

Mechanical equivalent of heat,

778.1 7

Flow coefficient

Ratio of specific heats, cp/cy

Common ogarithm (Base 10)

Naperian (natural) ogarithm

Molecular weight

Machine Mach number

Fluid Mach number

Polytropic exponent for a path on the P-T

Mass (Appendix B only)

Rotative speed

Polytropic exponent for a path on the P-v

Number of moles (Appendix

B

only)

Isentropic exponent for a path on the p-v

Power

Pressure

Velocity pressure

Other external heat losses

Total mechanical losses (equivalent)

diagram

diagram

diagram

3

Units

f t 2

ftlsec

ft

dimensionless

Btu/lbm mole R

Btu/lbm

R

Btu/lbm " R

Btu/lbm R

in.

In.

dimensionless

dimensionless

Ibm

ft/lbf e

sec2

Btu/lbm-mole

Ibm H20/lbm dry air

Btu/lbm

Btu/hr

f t 2

R

ft

Ibf/Btu

dimensionless

dimensionless

dimensionless

dimensionless

Ibmllbmole

dimensionless

dimensionless

dimensionless

Ibm

rPm

dimensionless

lb

mole

dimensionless

hP

PSi

psia

Btu/min

Btu/min


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~~~

STDDASME P T C L O-EN GL L997

m 0759b70

Ob05433

UT7

W

ASME PTC

10-1997

0,

QSl

9

R

RA,

RB, RC

Re

Rem

RH

RP

Rt

r

'r

P

'

rt

r

S

Sc

S

T

t

U

U

V

V

W

W

X

Y

Y

Z

ß

Y

X

a

rl

P

L in

PP

PS

Y

P

c

T

E

R

d

Heat transfer from the section boundaries

External seal

loss

equivalent

Rate of flow

Gas constant

Machine Reynolds number correction

constants

Fluid Reynolds number

Machine Reynolds number

Relative humidity

Reduced pressure

Reduced temperature

Pressure ratio across fluid meter

Recovery factor

Pressure ratio

Flow rate ratio

Temperature ratio

Ratio

of

specific volumes

Molar entropy

Heat transfer surface area of exposed

Entropy

Absolute temperature

Temperature

Internal energy

Blade tip speed

Velocity

Specific volume

Work per unit mass

Mass rate of flow

Compressibility function

Mole fraction

Compressibility function

Elevation head

or

potential energy

Compressibility factor as used in gas law,

144

pv = ZRT

Diameter ratio of fluid meter,

d/D1

Isentropic exponent

Partial derivative

Efficiency

Absolute viscosity

Work input coefficient

Polytropic work coefficient

Isentropic work coefficient

Kinematic viscosity

Density

Summation

Torque

Surface roughness

Total work input coefficient

Flow coefficient

compressor casing and adjoining pipe

COMPRESSORS A ND EXHAUSTERS

Btu/min

Btulmin

ft3/min

ft IbWlbm . R

dimensionless

dimensionless

dimensionless

percentage

dimensionless

dimensionless

dimensionless

dimensionless

dimensionless

dimensionless

dimensionless

dimensionless

Btullbmmole

-

R

f i 2

Btu/lbm R

R

"F

Btu/lbm

filsec

ftlsec

ft3/lbm

ft - Ibf/lbm

Ibm/m n

dimensionless

dimensionless

dimensionless

ft

Ibfllbm

dimensionless

dimensionless

dimensionless

dimensionless

dimensionless

Ibm/ft sec

dimensionless

dimensionless

dimensionless

ft2/sec

Ibm/ft3

dimensionless

in.

dimensionless

dimensionless

I

bf-ft

4


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S T D - A S M E P T C L O - E N G L L997

D

0759b70 Ob05434T33 m

COMPRESSORS A N D EXHAUSTERS

Subscripts

a Ambient

a,b,c,j Component of

gas

mixture (Appendix

B

av

corr

crit.

d

da

db

des

dg

C

g

hb

i

lu

Id

m

P

rotor

sh

SP

sd

S

su

SV

t

Wb

1, l n

2, 2n

(Y

Y

static

meas.

only)

Average

Casing

Correction

Fluid’s critical point value

Compressor discharge conditions

Dry air

Design

Dry gas

Gas

Heat balance

Compressor inlet conditions

Leakage upstream

Leakage downstream

Gas mixture

Polytropic

Flow ocation reference

Isentropic

Shaft

Specified conditions

sidestream upstream

sidestream downstream

Saturated vapor

Test conditions

Wet-bulb

Upstream of fluid meter

Downstream or

at

throat

of

fluid meter

Compressor inlet conditions (static,

Compressor discharge conditions (static,

Static

Measured

Dry-bulb

Appendix A only)

Appendix A only)

Superscripts

(

’

Condition at dischargepressure with

entropy equal to inlet entropy

( )

Determined

at

staticonditions

2.2 PRESSURES

2.2.1AbsolutePressure. Theabsolutepressure i s

the pressuremeasuredaboveaperfectvacuum.

ASME

PTC

10-1997

2.2.2Gage ressure.

The age ressure i s that

pressure which i s measured directly with the existing

barometric pressure as the zero base eference.

2.2.3 Di ff eren ti al Pressure.

The differential pres-

sure is thedifferencebetweenany

two

pressures

measured with respect to

a

common reference (e.g.,

the difference between two absolute pressures).

2.2.4Static Pressure.

The tatic ressure i s the

pressure measured in such

a

manner that no effect

i s produced by the velocity of the flowing fluid.

2.2.5 Total (Stagnation) Pressu re. The total (stagna-

tion) pressure is an absoluteor gagepressure that

would exist when

a

moving fluid i s brought to rest

and ts kinetic energy is converted to an enthalpy

rise by an isentropic process from the flow condition

to the stagnation condition. In a stationary body of

fluid the static and total pressuresareequal.

2.2.6Velocity Kinetic)Pressure. Thevelocity (ki-

netic) pressure i s thedifferencebetween he total

pressureand hestaticpressure a t the same point

in a fluid.

2.2.7 InletTotal Pressure.

The inlet total pressure

is the absolute total pressure that exists at the inlet

measuringstation (seepara.

4.6.8).

Unless specifi-

cally statedotherwise, this i s thecompressor inlet

pressure

as

used in

this

Code.

2.2.8 Inl et Static Pressure.

The inlet static pressure

is the absolute static pressure that exists at the inlet

measuringstation seepara.4.6.7).

2.2.9 Disc harg e To tal Pressure.

The discharge total

pressure

i s

the absolute total pressure that exists at

thedischargemeasuringstation (see para. 4.6.9).

Unless specifically stated otherwise, this

is

the com-

pressordischargepressure as used in this Code.

2.2.1

O

DischargeStaticPressure.

Thedischarge

staticpressure

is

theabsolutestaticpressure that

exists a t the discharge measuring station (see para.

4.6.7).

2.3 TEMPERATURES

2.3.1AbsoluteTemperature.

The absolute emper-

ature i s the emperaturemeasuredaboveabsolute

zero. It

is

stated in degrees Rankine or Kelvin. The

Rankine emperature i s the Fahrenheit emperature

plus 459.67 and the Kelvin temperature s the Celsius

temperature plus 273.1

5.

5


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STD-ASME

P T C

LO-ENGL 1977 9

ASME

PTC 10-1997

2.3.2StaticTemperature. The staticemperature

is the temperature determined in such

a

way that no

effect

i s

producedby the velocity of the flowing fluid.

2.3.3

Total (Stagnation)emperature. The total

(stagnation)emperature i s theemperaturehat

would exist when

a

moving fluid i s brought to rest

and i ts kinetic energy i s converted to an enthalpy

rise by an isentropic process from the flow condition

to the stagnation condition. In

a

stationary body of

fluid the static and the total temperatures are equal.

2.3.4 Veloc ity (Kin etic) Temperatu re.

The velocity

(kinetic) temperature i s the difference between the

total temperature and he static emperature at the

measuring station.

2.3.5 Inlet Tot al Temperature.

The inlet total tem-

perature

is

the absolute total temperature

that

exists

at the nlet measuring station see para. 4.7.7). Unless

specifically stated otherwise, this

i s

the compressor

inlet temperature used in this Code.

2.3.6 Inl et Static Temperature.

The inlet static tem-

perature

i s

the absolute static temperature that exists

at the inlet

measuring station.

2.3.7DischargeTotalTemperature. The discharge

total temperature

i s

the absolute total temperature

that

exists

at

the dischargemeasuringstation

(see

para.

4.7.8).

Unless specifically statedotherwise,

this i s the compressor discharge temperature

s

used

in this Code.

2.3.8 Discharge Static Temp erature.

The discharge

static temperature

i s

the absolute static temperature

that exists at he discharge measuring station.

2.4 OTHER GAS (FL UID ) PROPERTIES

2.4.1 Density. Density is the mass of he gas per

unit volume. It i s a thermodynamic property and i s

determined

a t a

point once he total pressure and

temperature are known at he point.

2.4.2 Specific Volum e. Specific volume is the vol-

ume occupied

by

a unit mass of gas. It i s a thermody-

namic property and is determined

at

a point once

the total pressure and temperature are known a t the

point.

2.4.3 Mol ecu lar Weigh t.

Molecular weight

is the

weight of a molecule of

a

substance referred to that

of an atom of carbon-1

2

a t 12.000.


2.4.4AbsoluteViscosity.

Absolute viscosity

i s

that

property of any fluid which tends to resist

a

shearing

force.

2.4.5KinematicViscosity. The kinematic viscosity

of a fluid is the absolute viscosity divided by the

fluid

density.

2.4.6 Specific He at at Constant Pressure.

The

spe-

cific heat at constant pressure, (c) =

(dh/aT), i s the

change in enthalpy with respect to temperature at

a constant pressure.

2.4.7 Specific Heat at Constant Volum e.

The spe-

cific heat at constant volume,

(c,,)

=

(au/aT),

i s

the

change in internal energy with respect to temperature

at a

constant specific volume.

2.4.8 Ratio of Specific Heats.

The ratio of specific

heats,

k,

is

equal to

cpIc,,.

2.4.9

Acoust icVelocity SonicVelocity). A pres-

sure wave or acoustic wave of infinitesimal ampli-

tude

is

described by an adiabaticand eversible

(isentropic) process. The corresponding acoustic ve-

locity for suchwaves in any medium

is

given

by:

a2 = ($)

5

2.4.10 Fluid Mach Num ber.

The Fluid Mach num-

ber is the ratio of fluid velocity to acoustic velocity.

2.5 MA CH INE CHARACTERISTICS

2.5.1Capacity.

Thecapacity

of a

compressor is

the rate of flow which i s determined by delivered

mass flow rate divided by nlet total density. For

an exhauster

it

is determined by the inlet mass flow

rate dividedby nlet total density. Forsidestream

machines, this definition must be applied to individ-

ualsections.

2.5.2

Flow

Coefficient.

The flow coefficient

is a

dimensionless parameter defined

as

the compressed

mass flow rate divided

by

the product of inlet

density, rotational speed, and the cube of

the blade

tip diameter. Compressed mass flow rate i s the

net

mass flow rate hrough he rotor.

2.5.3Pressure Ratio.

Pressure ratio

i s

the ratio of

the absolute discharge total pressure to the absolute

inlet total pressure.

6


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STD-ASME

P T C

10-ENGL 1997

m 0759b70

Ob05V3b

AOb m

COMPRESSORS

AND EXHAUSTERS

2.5.4 PressureRise. Pressure ise i s thedifference

between hedischarge total pressureand he inlet

total pressure.

2.5.5 emp eratur e Rise.

Temperatureise i s the

difference between he discharge total temperature

and he inlet total temperature.

2.5.6 Vol um e FlowRate. The volume flow rate as

used in this Code

is

the local mass flow rate divided

by local total density. It i s used to determine volume

flow ratio.

2.5.7VolumeFlowRatio.

Thevolume flow ratio

i s

the ratio ofvolume flow rates

at two

points in

the flow path.

2.5.8Specific Volum e Ratio.

Thespecificvolume

ratio is the ratio of inlet specific volume to discharge

specific volume.

2.5.9 Mach ine Reynolds Num ber .

The Machine

Reynolds number

is

defined by the equation Rem =

Ub/v,

where

U

is thevelocity at heouterblade

tip

diameter of the first impeller or of the first stage

rotor tip diameter of the eading edge, Y

is

the total

kinematicviscosityof he gas at thecompressor

inlet, and b i s a characteristic ength. For centrifugal

compressors, b shall be aken as the exit width at

the outer blade diameter of the first stage impeller.

For axial compressors,

b

shall be taken as the chord

length at the tip of the first stage rotor blade. These

variablesmustbeexpressed in consistent units to

yield a dimensionless ratio.

2.5.10 Machin e Mach Num ber. The Machine

Mach number

is

defined as the ratio of heblade

velocity

a t

the largest blade tip diameterof the

first mpeller for centrifugal machines or at he tip

diameter of the eading edge of the first stage rotor

blade foraxial flow machines to the acoustic velocity

of he gas

at

the total inlet conditions.

NOTE:

This i s not to

be confused with local Fluid Mach

number.

2.5.11 Stage. A stage for a centrifugal compressor

i s comprised of

a

single mpeller and its associated

stationary flow passages. A stage for an axial com-

pressor i s comprisedofasingle row

of

rotating

blades

and ts associated stationary blades and flow

passages.

2.5.12Section. Section

i s

defined as one or more

stages having

the

samemass flow without external

heat transfer other than natural casing heat transfer.

2.5.13 Con tro l Volu me. The controlvolume

is

a

region of space selected for analysis where the flow

7

ASME PTC 10-1 997

streams enteringand eavingcanbequantitatively

defined as well as the power nput and heat exchange

by conduction and radiation. Such

a

region can

be

considered to be in equilibrium for both

a

mass

and energy balance.

2.5.14 CompressorSurge Point.

Thecompressor

surge point

i s

the capacity below which he compres-

sor operation becomes unstable. This occurs when

flow i s reduced

and

the compressor back pressure

exceeds the pressure developed by

the

compressor

and a breakdown in flow results. This immediately

causes a reversal in

the

flow direction and reduces

the ompressorbackpressure.The moment this

happens egularcompression

i s

resumedand he

cycle

is

repeated.

2.5.15ChokePoint.

Thechoke point

is

the point

where the machine

i s

run at a given speed and the

flow

is

increased until maximum capacity s attained.

2.6 WORK, POWER, AND EFFICIENCY

These definitions apply to

a

section.

2.6.1 sentropicCompression.

Isentropiccompres-

sion as used in thisCode efers to a reversible,

adiabaticcompressionprocess.

2.6.2sentropic Wor k (Head). Isentropic work

(head) s the work required o isentropically compress

a

unit mass of gas from the inlet total pressure and

total temperature to thedischarge total pressure.

The total pressure ndemperature re sed to

account for thecompressionof he gas and he

change in the kinetic energy of the gas. The change

in the gravitational potentialenergyof he gas i s

assumed negligible.

2.6.3PolytropicCompression.

Polytropic compres-

sion

is

a reversiblecompressionprocessbetween

the inlet total pressure andemperatureandhe

discharge total pressure and emperature. The total

pressures and emperatures are used to account for

the ompressionofhe

gas

and

the hange in

the kinetic energy of the gas.Thechange in the

gravitational potential energy is assumed negligible.

The polytropic process follows a path such that the

polytropic exponent

i s

constant during he process.

2.6.4 olytro pic Wor k (Head).

Polytropic work

(head) i s the eversible work required to compress

a unit mass of gas by a polytropic process from the

inlet total pressure and temperature to the discharge

total pressureand emperature.


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ASME PTC 10-1997

2.6.5 Gas Work.

Gas

work i s the enthalpy rise of

a

unit mass of the

gas

compressedanddelivered

by the ompressorromhe inlet total pressure

and temperature to the discharge total pressure and

temperature.

2.6.6 Cas Pow er.

Gas power

is

the power transmit-

ted to the gas. It i s equal to the product of the

mass flow rate compressed and the gas work plus

the heat loss from he compressed gas.

2.6.7sentropicfficiency.

The

isentropic

effi-

ciency i s the ratio of the isentropic work to the gas

work.

2.6.8olytropicfficiency. The polytropic effi-

ciency i s the ratio of the polytropic work to the gas

work.

2.6.9 Shaft Power (Brake Pow er).

The

shaft

power

(brake power)

s

the power delivered o the compres-

sor shaft. It i s the

gas

power plus hemechanical

losses in thecompressor.

2.6.10 sentropic Wo rk Coefficient.

The isentropic

work coefficient i s thedimensionless ratio of the

isentropic work o

the

sum of the squares of he

blade tip speeds of

all

stages in a given section.

2.6.1 1 Polytropic Wo rk Coefficient. The polytropic

work coefficient i s thedimensionless ratio of the

polytropic work to the sum of he

squares

of the

blade tip speeds of

al l

stages in

a

given section.

2.6.1 2Mechanical losses.

Mechanical lossesare

the total powerconsumedby frictional losses in

integral gearing,bearings,andseals.

2.6.13 Worknput Coefficient.

The work input

coefficient i s the dimensionless ratio of the enthalpy

rise to the sum of the squares of the tip speeds of

al l

stages in

a

givensection.

2.6.14 otal Wo rknput Coefficient. The total

work nput coefficient

is

the dimensionless ratio of

the total work nput to the

gas

to the sum of the

squares of heblade tip speeds of al l stages in a

givensection.

2.7 MISCELLANEOUS

2.7.1FluidReynolds Number. The Fluid Reynolds

number is the Reynolds number for the

gas

flow in

a pipe. It is defined by theequation Re = V D / v ,

where he velocity, characteristic ength, and static

kinematic viscosity are to be used as follows: velocity

V

is the average velocity at the pressure measuring


station, the characteristic length D s the inside

pipe

diameter at the pressure measuring station and he

kinematicviscosity,

Y

i s that which exists or he

staticemperatureandpressureat the measuring

station.Thepressureandemperaturemeasuring

stations for flow metering calculations shall

be

speci-

fied

as in Section 4 and the accompanying illustra-

tions.Thevariables in theReynoldsnumbermust

beexpressed in consistent units to yield

a

dimen-

sionless ratio.

2.7.2 Dimens ional Co nstant.

The dimensional con-

stant,

gc,

is required to account or heunitsof

length, time, and force. It i s equal to 32.174 ft-lbm/

Ibf sec2.

The

numerical value is unaffected by the

local gravitationalacceleration.

2.7.3Specified Oper ating Conditions. Thespeci-

fied operating conditions are hose conditions for

which the compressor performance

is

to

be

deter-

mined. Refer

to

paras.6.2.3 and 6.2.4.

2.7.4 Test Op erat in g Condi tions .

The test operating

conditions are theoperating conditions prevailing

during the est.Refer to paras.6.2.7 and 6.2.8.

2.7.5Equivalence.

The specifiedoperating condi-

tions and the test operating conditions, for the pur-

pose of

this

Code, are said to demonstrate equiva-

lence when, for the samelow coefficient the ratiosof

the three dimensionless

parameters

(specific volume

ratio, Machine Mach umber, and Machine Reynolds

number)

fall

within the limits prescribed in Table 3.2.

2.7.6 Raw Da ta .

Raw data is the recorded observa-

tion of an instrument aken during the test un.

2.7.7Reading.

A reading i s theaverageofhe

corrected individual observations (raw data) at any

given measurement station.

2.7.8TestPoint. The est point consists of three

or more readings hat have been averaged and fall

within the permissible specified fluctuation.

2.7.9luctuation.

The fluctuation of a specific

measurement

is

defined

as

the highest reading minus

the owest eading divided

by

the average

of

all

readings expressed

as

a percent.

2.8NTERPRETATION OF SUBSCRIPTS

2.8.1 Certainvalues or hermodynamicstateand

mass flow rate are used in the computation of the

dimensionless performance parameters

M,

Re,

r,, 4,

P,,, pi, T,, and s1. Unlessotherwise specifically

a


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S T D - A S M E

P T C L O - E N G L

L997 0759b70 O b 0 5 4 3 B b A 9 m

CO MP RE SS O RS A N D E X HA US TE RS

stated, the thermodynamic total conditions are used.

The subscripts used n these equations are interpreted

as follows.

2.8.1.1

The subscript

i

on thermodynamic state

variablesdenotes inlet conditions. For singleentry

streams it refers to conditions at

the

section inlet

measurementstation.For multiple inlet streams

it

refers to

a

calculated mixed state.Seepara.

E.5

of

Appendix E.

2.8.1.2

Theubscript d on thermodynamic

state variables denotes discharge conditions. It refers

to conditions a t the mainstream discharge measure-

ment station.

2.8.1.3 The ubscript "rotor" i s used on mass

flow rate to denote the netmass flow rate compressed

by the

rotor. Its determination requires that al l mea-

sured

flows

and calculated leakages are considered.

A S M E

PTC 10-1997

9


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S T D * A S M E P T C LO-ENGL L797 W 0 7 5 7 b 7 0 UbO5439

515

H

COMPRESSORSANDEXHAUSTERS

SECTION 3 - GUIDING PRINCIPLES

3.1 PLANNING THE TEST

3.1.1

Before undertaking a test in accordance with

the rules of

this

Code, the Code on General Instruc-

tions,PTC 1, shallbeconsulted.

It

explainshe

intended use of the Performance Test Codes and

i s

particularly helpful

in

the initial planning of the test.

3.1.2

When a test i s to be conducted in accordance

with this Code, thescopeandprocedures to be

used shall be determined in advance. Selections of

pipe arrangements, test driver, instruments, and test

gas,

if

applicable,shallbe made.Estimates of he

probable uncertainty in the planned measurements

shouldbe

made.

3.1.3 The scope of the test shall be agreed to

by

the

interested parties. This may be dictatedn advance by

contractual commitments or may be mutuallygreed

upon prior to the start of the test. This Code contains

procedures for a single point performance est and

gives guidance on determining a complete perform-

ance curve.

3.1.4 Specifiedconditions, that is, mass flow rate,

inlet conditions of pressure, emperature, humidity,

discharge pressure, cooling water temperature if ap-

plicable, speed, as properties,andnputpower

expectedshallbedefined.

3.1.5 A detailed written statement of the

test

objec-

tives shall be developed prior to conducting the test.

3.1.6

A test facility shall be selected. Typically

this

i s

themanufacturer’s est

stand

or he user’s

installation site.

3.1.7 The umber fest ersonnel hould e

sufficient to assure a careful and orderly observation

ofall instruments with timebetweenobservations

to check for indications of error

in

instrumentsor

observations.

3.1.8

An individual

shall

be designated

as

responsi-

ble for conducting the test.

ASME PTC 10-1997

3.2

TYPES OF TESTS

ThisCodedefines two typesof test which are

based on the deviations between test and specified

operating conditions.

3.2.1

Type 1 tests are conducted with the specified

gas at or very near the specified operating conditions.

Deviations in the specified gas and operating condi-

tions are subject to the limitations imposed by Table

3.1. These limitations are subject to theurther

restriction that their individual and combined effects

shall

not exceed he limits of Table

3.2.

3.2.2

Type 2 testsare conductedsubject to the

limits ofTable

3.2

only. Thespecified gas ora

substitute gas may be used. The test speed equired i s

often different from the specified operating ondition

speed.

3.2.3

Theselection of test type shall bemade in

advanceof the test. In the nterestof maximizing

accuracy of

test

results it

is

desirable that test condi-

tions duplicate pecifiedoperating onditions as

closely

as

possible. The limits in Table

3.1

provide

maximum allowable deviations of individual param-

etersorType 1 tests.The limitations of Table

3.2 providemaximumallowabledeviationsof he

fundamental dimensionless parameter groupings for

both types.Theemphasis in conducting either a

Type

1

or Type

2

test should be toward minimizing

these deviations. The most eliable test results would

be expected when the deviations in both tables are

minimized.

3.2.4

Calculationprocedures are given in Section

5

for gases conforming to Ideal GasLaws and for

Real Gases. Where the compressibility values depart

from the limits prescribed in Table 3.3 the alternate

calculation procedures provided for Real Gases shall

be used. These alternate procedures apply o calcula-

tions foreitherType 1 orType

2

tests.

3.3 LIMITATIONS

3.3.1

Compressorsconstructed with iquid cooled

diaphragms,or built-in heatexchangers,shallbe

11


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S T D D A S M E P T C L O - E N G L

L777 m

0 7 5 7 b 7 0

ObOSqqO

237

M

ASME 10 -19 97 COMPRESSORS AND EXHAUSTERS

TABLE

3.1

PERMISSIBLEDEVIATION FROM SPECIFIEDOPERATINGCONDITIONS FOR

TYPE

1

TESTS

Permissible

Variableymbol

Inlet pressure

Pi

psia

5 6

Inlet temperature

Ji

O R 8%

S P d

N rPm 2%

Molecular weight MW Ibm/lbmole 2%

Coo ling temperature O R 5

Coolant flow rate

gal/min 3 o

Capacity

4i

ft3/m n%

GENERAL NOTES:

(a) Type 1 tests are to be condu cted w ith the specified gas. D eviations are based on he specified values

whe re pressures and temperatures are expressed n absolute values.

(b) The com bine d effect of inlet pressure, emperature and molecular weight shall not prod uce more

than an

8%

deviation in the inlet gas density.

(c) The comb ined effect

of

the deviations

shall

not exceed the imited

of

Table 3.2.Coo ling temperature

difference is defined as inlet gas temperature minus nlet cooling water temperature.

difference

TABLE

3.2

PERMISSIBLE D EV IA TIO N FR OM SPECIFIED OPERA TING PARAMETERSFOR

TYPE 1 A N D 2 TESTS

l im i t of Test Values as Percent of

Design Values

Parameter Symbol M in Milx

Specific volume ratio vh’d 9505

Flow coefficient

4 96 104

Machine Mach number

Centrifugal compressors

Ax ial compressors

Mach ine Reynolds number

Centrifugalompressors [Note (111em

Axial compressors where the Machine

Reynolds numberat specified con di-

tions is below 100,000

Axial compressors where the Machine

Reynolds number at specified ondi-

tions

is

above 100,000

S e e Fig. 3.3

See

Fig. 3.4

See Fig. 3.5

9005

[Note (1

1

10

200

NOTE:

(1) Min imu m allowable test Ma chine Reynolds number

is

90,000.

12


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COMPRESSORS AND EXHAUSTERSSME 10-1997

TABLE

3.3

L I M I T S

OF

DEPARTURE FROM I D E A LC A S L A W S

OF

SPECIFIED A N D TEST

GASES

~~ ~~ ~~ ~

Maxim um Allowed Range

for

Allowed Range

for

Ratio

Function

X

Function Y

Pressure

Ratio

k

rnaxlk

min

Min Max Min Max

1.4.12 -0.344

0.279

0.925

1 O71

2

1.10

-0.1 75

0.1 67 0.964

1 .O34

4

1 o9

-0.073 0.071 0.982

1

.o17

8

.O8

-0.041

0.050 0.988

1 o1

1

16 1 O7

-0.031 0.033

0.991 1 .O08

32

1

.O6

-0.025 0.028

0.993 1.006

GENERAL NOTES:

(a)Where:

X

= - - 1 and

Y

= 72) See Figs. 3.6 and3.7)

av

v a-r V ap T

(b)

Maximu m and minimum values of k shall apply to both the specified andest gas over the complete

range of conditions.

(c) When these

l im i ts

are exceeded by either the specified gas or he est gas at any point along the

compre ssion path real gas calculation metho ds shall be use d

or

that gas. Ideal or

real gas

method may

be used if these limits are not exceeded.

tested on thespecified

gas

and at theoperating

conditions specified for the inlet pressure, inlet tem-

peratureand speed, and with the flow rateand

the temperature specified for the cooling fluid. The

fluctuations of the test readings shall be controlled

within the limits of Table

3.4.

The esultsshallbe

computed by themethodsprovided or

a

Type 1

test, and eported “as run.”

3.3.2 Themethodsof this Codemay

be

applied

for conversion of test results to specified operating

condition results for compressors which maybe

treated as oneormoresections.

A

section

i s

that

portion of

a

compressorwhere ontermediate

stream eavesorentersbetweenone impeller inlet

andhe sameoranother following impeller dis-

charge. See Table 3.2. Heat exchangers are excluded

from the interior of the section boundaries. Section

boundaries are indicateddiagrammatically in Fig.

3.1. The

gas

state and flow rate shall be established

for each stream where

it

crosses the section bound-

ary. The power absorbed and heat oss or gain

by

naturalambientheat ransfermustalso be deter-

m ned.

3.3.3

Compressors with externally piped intercool-

ersmaybegiven

a

Type

1 test

or heymaybe

tested

by

individual sectionsusing

a

Type

2

test.

3.3.4

Compressors with nlet or outlet sidestreams

may be testedusing heprocedures or a Type 1

test providing

all

conditions, including those at the

sidestream,meetheequirementsofTable

3.1.

Compressors with sidestreamsmayalsobe ested

by individual sections utilizing the criteria for a

Type 2 test.

3.3.5

Where condensation can ake place between

compression sections; for example, intercooled com-

pressors handlingmoist air; thecapacityshall be

measured a t thecompressordischarge. Foratmo-

sphericexhausters

the

flow shall bemeasuredat

the nlet.) Care

shall be

taken to assure that there

is

no liquid carry-over rom he intercoolers.

3.3.6

Volume flow ratiosmay in practice differ

between test and specified operating conditions due

to leakagedifferences.Forexample,

it

is common

to test

at

reduced inlet pressure and he educed

differential pressure cross a seal to atmosphere

could result in zero or negative eakage.

As a

result,

volume flow ratio equalitycannot be achieved

between est and specified conditions.

Therefore,

it

shall be necessary to estimate he

leakage ratio; that is, the eakage mass flow divided

by he inlet mass flow for both test and specified

conditions. If the eakage ratio differencebetween

test

andspecified is significant, heseeffectsshall

be applied o the calculations of capacity and power.

13


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ASME 1

O- 1997


TABLE 3.4

PERMISSIBLE FLUCTUATIONSOF TEST READINGS'

Measurementymbol

~~~ ~ ~

Inlet pressure

Inlet temperature

Discharge pressure

Nozz le differential

Nozz le temperature

Speed

Torque

Electric motor input

Molecular weight

Coo ling water inlet

temperature

Cooling water flow

rate

Line voltage

pressure

MW

T

psia

R

psia

PSi

R

rPm

Ibf ft

kW

l bd lbmole

R

gal/min

volts

2%

2%

0.5%

2%

0.5%

1

Yo

1Yo

0.25%

0.5%

0.5% [Note (2)1

2%

2%

GENERAL NOTES:

(a) A fluctuation is the percent difference between theminimum and maximum test reading divided b y

the average of a ll readings.

(b) Permissible fluctuations apply to Type 1 and Type 2 tests.

NOTES

( 1 ) Seepara.5.4.2.3.

(2)

See

para. 4.1 6 for further restrictions.

Power

in

r-- -------

I

c

lest

ection /1

4

-7

Mult ip le

boundary

I

-

I

I

I

""- -

exit

Multiple

entry

t reams

I

Heat transfer

FIG. 3.1

SECTIONCONTROLVOLUMES

14


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S T D - A S M E P T C

1 0 - E N G L

L997 0 7 5 9 b 7 0 Ob05YY3 T q b m


In many cases it is not practical to measure he

leakage flow and it is permissible to use calculated

values of leakage for test and specified conditions.

3.3.7 Where he efficiency i s to be determined by

shaft input power measurements hebearingand

sealosses shouldnotexceed

10

percent of the

total

test

power.

This

will minimize theeffectof

uncertainties in the bearing and seal loss determina-

tion of gas power.

3.3.8

Evaluation of performance f omponents

between sections,

if

any,such

as

heatexchangers,

piping, valves,etc.,

is

generallybeyond hescope

of this Codeandshallbeagreeduponbyparties

to the test.The specifiedoperating condition per-

formance of suchcomponentsorheechnique

for correction of test esults to specified operating

conditions

shall

be agreed upon by parties to the test.

3.3.9 When power

i s

to be determined by the heat

balancemethod, the heatossesdue to radiation

andconvection,expressed in percentof the total

shaftpower,shall not exceed 5 percent.

3.3.10

ForType 2 tests, the inlet gas condition

shall have

a

minimum of 5°F of superheat.

3.4

TEST CAS

AND SPEED

3.4.1

The physicaland hermodynamicproperties

of the specified and test gas shall beknown.The

option of using tabulated data, an equation of state

correlation,rxperimentaletermination

as

a

source for theseproperties shall be agreed upon

prior to the est.

3.4.2 The following physical properties of the est

gas throughout the expected pressure and tempera-

ture range

shall

be known or accurately determined:

(a) molecular weight

b) specific heat at constant pressure (cf)

(c)

ratio of specific heats

(c&)

d) compressibility factor

Z)

(e) dew point

(g)

isentropic exponent

(h )

enthalpy

i)

acoustic velocity

(fl viscosity

3.4.3 Theest peed hallbe elected so

as

to

conform to the limits of Table 3.2.The estspeed

shall not exceed he safe operating speed of the

compressor. Consideration should e given to critical

ASMEPTC

10-1997

speeds of rotating equipment in selecting he est

speed.

Test pressures and emperatures

shall

not exceed

the maximum allowable pressures and temperatures

for the compressor.

3.5 INTERMEDIATE FLOW STREAMS

3.5.1

Section Treatment.

Compressors having

flowsaddedor emoved at intermediate ocations

between he inlet and final dischargearehandled

by treating the compressor by sections. The gas state

and flow rate shall be established for eachstream

where it crosses the section boundary.

3.5.2 It i s necessary to maintain

a

consistency

betweenspecifiedvolume flow rate ratio and

test

volume flow rate ratio for each section. Permissible

deviations rom hese atiosare listed in Fig.3.2.

As an example, in the first section of multisection

compressor, he ratio of inlet volume flow rate to

dischargevolume flow rate for thespecifiedand

test conditions must be held o within + S percent

which

is

the same as that required for conventional

compressors in Table 3.2. In addition, it is required

that he ratio of first stage sectiondischarge flow

rate to secondsection inlet volume flow rate for

the specified and est conditions be held to within

2 1

O

percent.This

is

required

so

that the total

pressure determined at thesidestream lange wi ll

havehe ame relationship to the total pressure

actually existing at

he

exit of the

first

section bound-

ary for specified and est conditions.

For thesecondandsucceedingsections he e-

quirements are similar. The ratio of inlet volume

flow rate to discharge volume flow rate for specified

andest conditionsmustbeheld to within +5

percent.

Also, the preceding section discharge volumelow

rate to sidestream inlet volume flow rate ratio for

specified and est conditions must be

held

to

21

O

percent. Finally, he ratio of he discharge volume

flow rateof hesectionbeing ested to thenext

sidestream volume flow ratemustalsobeheld to

2 1O percent.

This requirement is most mportant in the second

section of a three section machine where both inlet

and discharge total pressuresare being determined

at the sidestream langes andvelocity similarities

are necessary for test accuracy. Code requirements

arealsodescribed in equation orm in Fig. 3.2.

15


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S

o

1

-

S

o

2

s

o

3

M

i

n

M

a

M

i

n

M

a

M

i

n

M

a

‘

q

2

q

=

9

-

q

2

(

q

2

M

.

J

9

1

(

1

r

q

2

=

-

9

(

q

2

9

1

(

q

2

s

4

Q

L

%

5

=

4

h

w

&

5

w

1

9

‘

q

2

=

4

h

2

g

,

o

(

~

2

s

4

w

5

=

4

(

p

5

9

(

+

1

r

q

=

4

Q

8

9

1

w

e

s

p

1

-

S

o

1

n

e

f

o

m

f

a

m

e

e

m

e

s

2

=

S

o

1

d

h

g

c

m

p

e

f

o

m

m

e

e

m

e

a

b

o

e

s

d

n

3

=

S

o

2

n

e

f

o

m

f

a

m

e

e

m

e

r

e

q

5

(

&

g

1

s

p

4

=

S

o

2

m

i

x

i

n

e

c

m

p

e

5

-

S

o

2

d

s

g

c

m

p

e

f

o

m

i

n

e

n

m

e

e

m

e

s

b

o

e

r

d

e

m

6

-

S

o

3

n

e

f

o

m

f

a

m

e

e

m

e

s

F

G

.

3

2

T

C

A

S

D

E

O

A

S

T

O

N

A

C

O

M

P

E

O

R

S

p

7

=

S

o

3

m

i

x

i

n

e

c

m

p

e

8

=

S

o

3

d

s

g

f

o

m

f

a

m

e

e

m

e

s

merican Society of Mechanical EngineersRIGHT American Society of Mechanical Engineers

nsed by Information Handling Services

8/17/2019 209274836-ASME-PTC-10.pdf

26/191

STD-ASME P T C

LO-ENGL

L997 m 0759b70 0b05445 8 1 9 m


3.5.3

Inward Sidestreams. Whenhe sidestream

flow is inward, hedischarge emperatureof he

precedingsectionshallbe measured prior to the

mixing ofhe two streams. This temperature measure-

ment

shall

bemade

in

a portion of hedischarge

flow stream where the sidestream cannot affect the

raw data. Raw data may be affected by heat transfer

froma cold sidestream to a hotmainstream flow

or from ecirculation which mayoccur within the

flow passage. The discharge emperature

is

needed

to compute the performance f the preceding section

and to compute he eferencemixed emperature

for the next section inlet.

It is possible for internal total pressures to exceed

flange total pressure due o the higher internal veloci-

ties. The higher internal velocities are accompanied

by a lower static pressure which provides

a

pressure

difference for inward flow.

3.5.4

Temperature Stratification. It i s common for

sideload sectional compressors to have temperature

differences between the mainstream and sidestream.

When testing all sections of a multisection compres-

sor (threeormoresections)simultaneously, arge

differences between the sidestream and mainstream

temperatures may occur. It i s possible, due to these

differences, for thermal flow stratification to exist

within thecompressorsections. This stratification

may esult in inaccurate measurements of internal

temperatures in downstream ections.Underest

conditions,hetreamemperatureifferences

should be maintained as close to specified as prac-

tical.

3.5.5 Performance Definition. Thesectionalhead,

efficiencies,and pressures re definedlange to

flange. The only internal measurements needed are

the

sectional discharge emperatures for computing

the mixed temperature conditions and sectional per-

formance.Thepressureusedor alculatinghe

sectionalperformance

i s

assumed to be equal to

the sidestream lange total pressure.

The internal mixed emperatureshould

be

com-

puted on a mass enthalpy basis (real gas evaluation)

for obtaining the inlet temperature for succeeding

sections. Simplified mixing based on mass empera-

turemaybedone for ideal gases with constant

specific heat.For urther information see para.

E.5

of Appendix

E.

3.5.6

Extraction Sidestreams. When he ntermedi-

ate flows are removed (¡.e., bleed-off) fromhe

compressor, hey will cross asectionboundary.

ASMEPTC 10-1997

The internal temperatureandpressure anbe

assumed to be equal to the external flange tempera-

tureand pressure of heprimary internal stream.

The ratio of flow rate estrictions in Fig.

3.2

shall

also apply to outward flowing sidestreams.

3.5.7

It

is

recommended that eachsection

of

a

multisectionmachine avets own performance

curvedefinedby

a

number of testpoints.This

enables synthesis of the combined overall perform-

ance curve and provides data on the interrelations

of the individual sections. The ratios of Fig. 3.5 will

apply at all points unless other specified operating

ratiosare identified.

3.6 SAFETY

3.6.1

Theest

gas

used hallbe in compliance

with local regulationsandprudentpractice with

regard to flammability and/or toxicity.

3.6.2

Testgasesused in a closed loop shall be

continuously monitored for composition and avoid-

ance of combustible mixtures. Air or other oxidizing

gases shallnotbeused in aclosed oop.

3.6.3

The party providing theestite wi ll be

responsible for establishing the requirements of sys-

temprotection.Considerationshouldbegiven to

the need or relief valves for accidental overpressure.

The equirement of alarmsand/orautomaticshut-

down devices orsuch tems

as

high

temperature,

loss

of cooling water, low oi l pressure, compressor

overspeed, or other possible malfunctions should be

reviewed,

3.7 PIPING

3.7.1

Piping arrangements required to conducta

test under the Code are detailed n Section 4. Permis-

sible alternatesaredescribed for convenience and

suitability. A selection suitable for the prevailing test

conditions shall be made and described in the est

report. When he choke point is to be determined,

care should be taken to assure that the compressor

pressure ise shall exceedsystem esistance.

3.7.2 Minimum straightengths ofpiping a t the

inlet, discharge, and on both sides of the flow device

arespecified in Section 4.

When compressorsare reated

as

anumber of

individual sections, these piping requirements apply

to each section. Such piping between sections may

not occurnaturally in thedesign. When it does

1 7


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ASME

PTC

10-1997

COMPRESSORSNDXHAUSTERS

O

.3

0.2

0.1

8

I

0.0

Ë

B

S

-0.1

-0.2

I I

I

I

I I I 1 I

I

I

I

I

I

I

I

I

I I I

I

I

I

I

I

I

I

I

I

I

-0.3 I

I

1 I I

I I

I

I

O

0.2

0.4

0.6

0.8 1

o 1.2 1.4 1.6

Mach No.

Specified-

msp

FIG. 3.3 A L L O W A B L EM A C H I N EM A C HNUM BER DEPART URES,

CENT RI F UG AL CO M PRESSO RS

not, he parties to the test should elect by mutual

agreement to:

(a) install additional piping between the sections

(6)

take measurements n the availablespace. Con-

sideration

shall be

given to any compromise in mea-

surement accuracy and i ts effect upon the final test

objective.

(c) remove components such as external heat ex-

changers and replace them with the required piping.

When

this

alternate

is

selected it

is

important that the

removal of the component have a negligible effect

upon the section entry or exit flowfield so

as

not to

affect the section performance parameters.

3.7.3 Where external ntercoolerperformanceand

pressure drop are known for the specified operating

conditions,ordeterminedon

a

separateest, the

compressor may be ested as separate sections and

the combined performance computed by the method

described in Section 5.

shall be designed for the maximum pressure plus a

suitable

safety

factor and he cooler

shall

be sized

to dissipatehe maximum heatoad. Additional

lengths of piping beyond he minimum prescribed

may be required o provide additional system capaci-

tance.Provisionsmay be necessary toallow for

expansion of the piping and the piping design shall

beofsufficientstrength to withstand he stresses

imposed during compressorsurge.

3.8

I N S T R U M E N T A T I O N

Test instruments shall be selected, calibrated, and

installed in accordance with the equirements of

Section 4.

3.7.4

If a closed loop test i s to beperformed, the

3.9

PRETEST

maximum messure to be obtained and themaximum

heat load shallbeestimated.The piping and ooler Pretest inspection may be of interest to either

from thecompressordischarge to the throttle valveparty.Refer to PTC

1

forguidance.

18


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STD-ASME P T C

LO-ENGL

L997 D 0757b70 O h 0 5 4 4 7 bqL

COMPRESSORS AND EXHAUSTERSSME

PTC 10-1

997

Mach No.

Specified- msp

FIG.

3.4 A L L O W A B L EM A C H I N EM A C HN U M B E R D E PA R TUR ES , A X I A L

COMPRESSORS

3.10

P RE TE ST R U N

3.10.1

Thecompressorshallbeoperated for suffi-

cient time at the required conditions to demonstrate

acceptable mechanical operation and stable values

of a l l measurements to b e takenduring he test,

Preliminarydatashallbe aken to familiarize test

personnel, to determine if

all

instruments are func-

tioning properly,and to ascertain if theeading

fluctuations fall within the limits prescribed in Ta-

ble

3.4.

3.10.2 All

instrument observations pertinent to the

test hall be taken during

the

pretest run. They

commonly include the following:

(a) inlet pressure

(b)

inlet temperature

(c) relative humidity or wet bulb temperature, if

(d) discharge pressure

(e) discharge temperature and/or

haft

power input

(0 flow device pressures and temperatures

(gl

speed

(h)

cooler inlet and outlet temperatures,gas and

atmospheric air i s

the

test gas

coolant sides, if applicable

( i)

lubricant temperatures, inlet and outlet of bear-

ings, seals, and speed changing gear,

if

applicable

(j)

coolant and lubricant flows,

if

applicable

fk/

barometric pressure

I) gas analysis, if atmospheric air is not the test gas

(m) time

3.10.3 A set ofcalculationsshall

be

madeusing

the preliminary test data to assure that he correct

test speed

has

been selected, that the test parameters

required in Tables 3.1 or 3.2, as applicable,were

obtainedand that theoverallperformancevalues

are easonable.

3.10.4 Thepretest unmaybeconsidered

as

part

of the test if

it

meets all requirements of he est.

3.11

TE S T O P E R A TI O N

3.11.1

Thecompressor shall be operated at the

required conditions for a sufficient period

of

time

to demonstrate

that all

variables have stabilized.

3.11.2 When all variables have stabilized, he test

personnel shall take the irst set of eadings of all

19


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~~

S T D - A S M E

P T C 10-ENGL L797 m

0 7 5 7 b 7 0 .

O b 0 5 4 4 8 528

m

ASME PTC 10-1997

GENERAL NOTE:

90,000 is cutoff

FIG.

3.5 A L L O W A B L E

MACHINE

R E Y N O L D SNUMBER DEPARTURES,

C E N TR I FU G A L C O M P R E S S O R S

EXHAUSTERS

essential nstruments.Three

sets

of readingsshall

be taken during each est point.

3.1 1.3 The minimum duration of a test point, after

stabilization, shall be

15

minutes rom he

start

of

the first set

of

readings to the end of

the

third set

of readings.

3.11.4

When

a

test is only to verify

a

single speci-

fied condition, the test

shall

consist of

two

test points

which bracket the specified capacity within a range

of

96

percent to 104 percent.

3.1

1.5

When performancecurves are required to

verify

the

complete compressor range of operation,

a multipoint test

shall

beperformed. Each point

selected along he curve shall be assumed to be a

specified point andchecked orequivalency.This

may require

a

different equivalent speed foreach

test point. Usually five pointsshouldbe used to

complete a curve. A point shall be taken at approxi-

mately the specified capacity. The additional points

should consist of one point near surge, two points

between specified capacity and urge, and one point

in

the

overload range (preferably

105

percentor

greater of specified capacity). When the compressor

is

used with

a

variable

speed

driver additional points

may be run onselectedspeed ines, provided that

an equivalent speed is generated for each operating

point selected.

3.11.6

The flow at which surgeoccurs an be

determined by slowly reducing the flow rate at the

test speed until indications of unstable or pulsating

flow appear. The severity of surge wil l vary widely

as a

function of pressure ratio, type of compressor,

andcapacitanceof he piping system.Surgemay

be identified

by

noise, fluctuations in the differential

pressure of the low nozzle, or

a

drop and/or fluctua-

tion of he pressure and/or emperatu

209274836-asme-ptc-10.pdf

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