~- ,-.

-- “-----”i=F-

..-

RESEARCH MEMORANDUM-

COMBUSTOR PERFORMANCE WITH VARIOUS HYDROGEN -OXYGEN

INJECTION METHODS IN A 200 -POUND -THRUST ROCKET ENGINE

By M. F. Heidmann and Louis Baker, Jr.

Lewis Flight Propulsion LaboratoryCleveland, Ohio

COMMITTEENATIONAL ADVISORYFOR AERONAUTICS

WASHINGTONSeptember 30, 1958

TECH LIBRARY KAFB, NM

w

NACA RM E58E21

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

RESIIW3CHMEMORANDUM

I!lll[llll[llllllfllnllllllllll01J4387D

CQMBUS!IORPERFOIWW!7CE

METHOIE IN A

WITH VARIOUS IUDRCKU21-OXYGENIXJECTION

200-POUIID-THRUSTROCKET ENGD1’11

By M. F. Heidmamn and Louis Bakerj h.

!5uMMlmY

Characteristic velocity of liquid oxygen and gaseous hydrogen wasdetermined as a function of mixture ratio in a nominal 200-pound-thrustvariable-length rocket engine. Fourteen different injectors, whichvaried mixing and oxygen atmizationj were evaluated. The heat-transferrates were determined for seven of these injectors. Injector designsincluded (1) triplets of two hydrogen jets impinging on me oxygen Jetwith variatims in impingement angle and orifice size, (2) concentricinjection with hydrogen surrounding a Jet of oxygen, (3) radial injec- .tion of oxygen with variations in hydrogen injection, and (4) oxygenatomization by two @inging jets with variations in hydxogen inJection.The triplet and concentric arrangements were studied h both single andmultiple units.

The degree of oqygen atomization appeared to be the primary factoraffecting efficiency in agreement with a vaporization model of cmbus-tion. Increasing the oxygen-jet size generally produced a reduction incharacteristic exhaust-velocity efficiency regardless of the atomizationmethod.

A decrease in efYlciency with an increase in mixture ratio was en-countered with several injectors. This implies incomplete mixing for acombustion process limited by physical processes. The effect was mostpronounced with large spacing between oxygen-injection orifices or poordispersion frcm a single orifice. I&tiogen-injection changes also con-tributed to performance variations with mixture ratio. The method ofhydrogen injection appearedto affect both qgen atomization andUspersion.

Heat rejection showed no significant variation with injectionmethod. Maximum heat-rejection rates of 3.5 to 4 Btu per second persquare inch occurred near the stoichhnetric mixture ratio.

2 IWCA RM lZ58E21

INTRODUCTION

High combustion efficiency with a minimun of complexity is contin-ually sought in the design of injectors for rocket engines. Realizationof this goal depends on a better understanding of the effects of designon performance. In order to gain a greater insight into the effect ofinjector configuration on the combustion characteristics of thehydrogen-oxygen systmj 14 injectors were studied in a 200-pound-thrust

—

rocket engine. The configurations included triplet, concentric-tube, 1+radial-jet,and self-impinging jet injectors. Some M these configura-tions were studied because-they pertained to the design of a hy&rogen-

E

cooled inJector for a larger thrust engine. ——

A previous study using similar apparatus (ref. 1) showed quali-tatively that combustor efficiency depends more on oxygen atomizationthan on hydrogen dispersion or propellant mixing. The present study maybe considered an extension of this work in that a more quantitativeevaluation was made of the effect of these parameters on combustorperformance.

The characteristic exhaust velocity (C*) was measured for all theinjectors over a range of mixture ratios. In some instances chember-length variations were used to evaluate performance more accurately.

?“

Heat-transfer measuraents were also made f“orseven of the injectors.Stability characteristics were studied separately and are reported inreference 2. Gaseous hydrogen at roan temperature rather than liwi_

● .——

hydrogen was used for all testsconditions for a regenera.tively

Six triplet injectors with

because It more nearly simulated entrancecooled rocket engine.

IMII?lc!m

Triplet

two hydrogen jets impinging on one oxygenjet, as shown in figure l(a), were stu~ed. These included four in- ‘-jectors with a single element, one with four elements, and one with nineelements. Orifice diameters of the single- and four-element injectorswere equal. The die.metersof the orifices in the nine-element injectorwere about one-half as large. II@rogen-injectionvelocity} tabulated infigure 1, is the calculated velocity for isentropic flow assuming a totalflow of 0.12 pound per second and a chamber yressure of 300 pounds persquare inch.

NACA RME58E21 3

.

Concentric Tube

Two concentric-tube injectors (fig. l(b)) with an oxygen jet sur-rounded by a hydrogen annulus were used. These were a stigle- and anine-element injector. The oxygen orifice diameter of the nine-elementinjector was about one-third that of the single-element injector.

Radial Jet

Two injectors tith radial injection of eight oxygen jets (fig. l(c))were used. Eytiogen was injected fran 10 centmlly located orifices inone injector and frcnn45 distributed holes in the other.

bpingingJet

Four injectors with oxygen i~ected as two impinging jets were usedas shown in figure l(d). Hydrogen-orifice arrangements varied asfollows: (1) 45 distributed holes, (2) 16 peripheral holes, (3] 10center holes, and (4) one center hole. Hydrogen injection velocitydiffered for these arranganents by a factor of about 3.

.--

APPARATUS ANDPRocErmE

Test Facilities

Small-scale test facilities similar to those described in refer-ences 1 and 3 were used. Hydrogen, at approximtel.y ambient tanpera-ture, was delivered to the rocket engine from high-pressure storagecylinders after one stage of pressure regulation. The flow rate, whichwas limited to a total flow of about 0.12 pound per second, was measuredwith a Venturi meter. Liquid oxygen at 140° R was supplied from apressurized tank immersed in liquid nitrogen. Two rotary-vane-type flowmeters were used to inticate ~gen flow rate. Chamber Iressure wasdetermined from the average indication of two strain-gage pressuretransducers.

The combustor consisted of an in~ector, uncooled cylindrical cham-ber, and water-cooled convergent nozzle in separable units. A chambertiameter of 2 inches and a nozzle throat diameter of 0.750 inch (con-traction ratio of 7.0) were used in all.of the tests.

Heat-transfer rates were measured in a 2-inch long, water-cooledchamber segment adjacent to the exhaust nozzle, shown in figure 2..

.W

4 NACA RM E58E21

Water-air spray photographs were obtained for all the injectors toshow qua~tatively their atomization and dispersion characteristics.

.

The mean operating mass flow rates were simulated. ~s approximatedJet velocity and momentum for both oxygen And hydrogen except in the re-gion where airflow was greater than critical.

Performeuce Eval@tion

Engine firings from 3- to 5-seconds duration, sufficient to estab- ~lish steady-state operation, were used. A series of oxidam.t-fuelmix-ture ratios was run ~or each of several hydrogen flow rates. In thismanner a mixture-ratio range of about 2 to 10 and total flow rates ofabout 0.4 to 0.8 pound per second were covered. Chamber lengths (cylind-rical sections) fram 3 to 24 inches were used. The range of oyeratingconditions and chamber lengths differed sanewhat for the variousinjectors. ,L

The characteristic exhaust velocity C* and mixture ratio o/fwere evaluated for each test condition. Experimental values, expressedas & efficiency, are percentages of the theoretical values shown infigure 3. .

Total heat transfer during a finite time intem’al was reduced toheat-transfer rate per unit area. The reported values were normalized -.to 300 pounb per square inch absolute chamber pressure by assuming directproportionality between the heat-transfer rate md the pressure.

REWLTSAND DISCUSSION

The experimental performance values obtained with the 14 injectorsare presented in tzibleI. Performance curves, water-air spray photo-graphs, and injector designs are shown for each injector in figures 4to 7.

General Observations

The C* (characteristicexhaust velocity) efficiency was generalJy~eater than 70 percent for all injectors. As observed in reference 1the efficiency is higher than that obtained with heptane-mygen combina-tion for similar injection methods (ref. 3). The result agrees with thehypothesis that propellant vaporization is.a controlling process inliquid-propellantcombustors. Analytical studies based on this hypothe-sis (ref. 4) have shown that for a given chsmber length the heptanevaporization rate is about one-third that for liquid oxygen for the sameinitial drop size distributims.

llACARM E58E21 5

Injectors with 0.04- to 0.047-inch-diameter oxygen orifices gavethe best pezfornmnce. These included the nine-element triplet, nine-element concentric-tube, and radial-jet injectors. Of these, the tripletgave the highest performance. The C* efficiency exceeded 95 percent ina 12-inch chartiberlength and remained above 90 percent in a 3-inch cham-ber length. The performance with inJectors having larger oxygen orificeswas generally lower. The result attests to the importance of oxygenatomization.

The perfo~ce with several injectirs depended on hydrogen distri-bution and injection velocity. This effect was shown in the impingingoxygen-jet injector where changes in the size and orientation of the hy-drogen jet caused 15-percent changes in & efficiency.

Several of the injectors showed a pronounced decrease in C* effi-ciency with an increase in mixture ratio off. This characteristic willbe subsequently discussed in the performance analysis of individualinjectors.

High-frequency ccunbustioninstabi~ty was observed during some testconditions. This condition primarily occurred with high-efficiencyperformance. These stability characteristics were studied separatelyand are reported in reference 2.

Combustion Model

A combustion model proved useful in pretious experimental studies(refs. 4 to 8) assumed propellant vaporization as the rate-controllingstep in the combustion process. Reference 8 is particularly applicableto this study. It shows that the shape of the curve of characteristicexhaust velocity against oxitit-fuel ratio indicates whether theoxidant or fuel is completely vaporized. If sme constant fraction ofthe oxidant is not vaporized, the & efficiency is relatively constantwith chsmges in o~f. A constant fraction of unvaporized fuel gives apronounced decrease in efficiency with an increase in ,Ojf.

This analysis was extended to the case of gaseous.hyhogen andliquid oxygen. The assumptions used differed from those of reference 8in the following manner: H@rogen was assumed incompletely mixed ratherthan incompletely vaporize% and this unused hydrogen was assumed to havea finite volume rather than a negligible volume. The & variations witho/f obtained with these assumptions (fig. 8) are similar to those ofreference 8, that is, a constant fraction of unmixed hydrogen in the ex-haust causes a decrease in & efficiency with o/fj whereas a constantfraction of oxygen escaping unvaporized causes a constant or graduallyincreasing efficiency with o/f. These performance trends will aid ininterpreting the experh.ental data.

6

Performance Analysis...

Triplet injector. - !l%e

IM2A RM E58E21 .

of Characteristic Exhaust Velocity .

C* performance obtained in a 12-inch. .chsmber with the triplet injectors is summarized in figure 9(a). withsingle elements the performance level was nearly identical for 20° and40° impingtient angles. This represents about a 20-percent increaseover nombmpinging streams. The spray photographs (fig. 4) show a cau-

.-

parable change in that the improvement in atomization and dispersion ismore pronounced for an Ur@ngement-angle change of 0° to 20° t~n for achange of 20° to 40°. The higher C* efficiency observed with the nine- -element injector than for the four-element injector may also be attributed E

to better spray properties.Cn

Increasing the number of orifices and de-creasing the diameter of the orifices should improve atomization anddispersion of oxygen.

All the single-element injectors show a decrease in & efficiencywith an increase in aidmt-fuel ratio. This implies incomplete pro-pellant mixing. With single elements the Mq.uid oxygen is concentratedalong the chamber axis snd hydrogen is dispersed over a l-inch radial

.-

distance from this axis. Mixing processes therefore, must take placeover a lateral distance of 1 inch for ccxnple~emixing. Therefore, im-proved mixing wouldbe expected froma decrease in this lateral mixingM.stmce. The four-element injector is an example of such a change.

●

In this case, four elements identical to the single element were usedin the 2-inch-dismeter chamber. The lateral mixing distance was reduced .considerably; the gradual rise in C!* efficiency with o/f obtainedexperimentally is evidence of a marked increase in mixing.

The performance obtained with the offcenter single-element injectoris another example of a change in lateral mixing distance. The effectivemixing distance is larger than that of an equivalent central element.The decrease in efficiency obtained may be attributed to poor mixing.

h example of a change in mixing with.cl=mber len M iS show by thefnine-element-injectorperformance in figures 4(d) and e). As chamber

length is reduced, injector performance develops a trend of decreasingC* efficiency with o/f which indicates less complete mixing h short .

chambers.

A decrease in C* efficiency with o/f was also observed in ref-erence 1. This primarily occurred when one instead of two oxygenorifices were used. The larger lateral mixing distance with singleorifice would account for this performance trend.

Analyzing the data in this manner shows that lateral mixing in someinstances is a rate-limiting process in combustion. Generalizing theresults for triplets shows that the chamber length at which mixing iscomplete varies with spacing between oxygen orifices. Interpolation of

NACA RM E58E21 7

the experimental data shows that complete mixing is obtained in a lengthof 8 inches tith 3/8-inch spacing, 13 inches with 0.7-inch spacing, andconsiderablymore than 12 inches for a single element representing a2-inch spacing. As a rough rule-of-thumb, therefore, chber lengthmust be about 20 times larger than the spacing between oxygen orificesin order to assure cmplete mixing.

Concentric-tube injector. - me performance of the concentric-tube injectors is sumnarizedin figure 9(b). Qualitatively the per-formance is similar to that obtained with triplet injectors for equiva-lent size oxygen orifices. Single-element performance again decreasesrapidly with an increase in o/f indicating incomplete mixing. Thepoorer dispersion with the single-element injector than with the nine-element injector is shown by the spray photographs in figure 5 andsuggests inefficiency caused by incomplete lateral mixing. Therefore,for concentric-tube injectors dispersion of the oxygen as well as atomi-zation is required for high performance.

Radial-jet injector. - The performance obtained with redialoxygen jets is summarized in figure 9(c). Eytiogenwas concentratednear the chamber axis with one injector and uniformly distributed withthe other. By adjusting for the differences in chamber lengths usedthe C* efficiency was about the same for both injectors in the higho/f region, but centrally injected hydrogen was definitely better inthe low o/f region. Apparently, oxygen atomization differed in thisregion. With central injection the hydrogen jets were of higher veloc-ity and orimtated for a ~eater exchamge of momentum with the oxygenthan with distributed injection. As a result, oxygen atomization wasimproved as shown by the photographs h figure 6. This differenceapparently affected performance only when a high proportion of hydxogento oxygen existed (low o/f region).

Ii?lp“mging oxygen-jet injector. - The performance of the imping-ing oxygen-jet injectors in which hydrogen was in~ected in various ori-entations is summarized in figure 9(d].

bjecting hydrogen through a 45-hole plate gave a C* efficiencyof 88 percent with no significant change with o/f. On the basis ofthe combustion model, incomplete oxygen vaporization is implied withfull utilization of the hydrogen. This injector introduced the hydro-gen uniformly and at a low velocity. The spray photographs (figs. 7(a)and (b)) show no effect of hydrogen flow on the atomization process.‘J?bisC* performance, therefore, will be used as a reference conditionin evaluating the effect of changes in hydrogen injection.

8 NACA RM E58E21.

The & efficiency level was less than 85 percent with hydrogen in-jected fiot.u16 peripheral holes. *Such a hole errangemmt suggests poorly -mixed propellants. The rising C efficiency with o/f, however, impliesincomplete oxygen vaporization rather than incomplete mixing. The effi-ciency level is also lower than with the 45-hole plate indicating less

—

complete oxygen vaporization. Corresponding changes in oxgyen atomizationsre not evident in the spray photographs of figures 7(a) to (d); however,conditions may differ considerably within the combustor.

$ incomplete mixing is impliedby the performance curve obtiined withhydrogen injected centrally from 10 holes. The high performance level,however, also irddcates improved oxygen atomization. The spray _photo-graphs (figs. 7(e) and (f)) show that oxygem atomization is affectedlyhydxogen flow and that oxygen is directed away from the axis of thechamber which may contribute to poor mixing.

Hydrogen injected frcm a single center hole gave an increase in &efficiency with an increase in o/f. The spray photographs (figs. 7(g)and (h)) again show that oxygen atcmdzation is effected by hydrogenflow ● This effect presumably varies with o/f. The over-all effect onCY efficiency is not clear, however, because c~ues in ~ol? size)drop acceleration, and oxygen dispersion would occur stiultaneouslywithchsmges in o/f. At low o/f values, such interaction apparentlycauses performance losses.

Heat Transfer

The heat-transfer data are sumarized in figure 10. The rates re-ported are the average values for a 2-inch chamber segnent installednear the exhaust nozzle. Heat-transfer rates were usually of the orderof 3 to 4 Btu per second per square inch. The maximum rate was obtainednear the stoichiometric oxidant-fuel ratio of 8. The higher performanceinjectors generally gave the highest heat-injection rates. The resultsdeviate from this trend in the low mixture ratio region, smd the dis-tinction between injectors is less evident. A heat-transfer rate of3.08 Btu per second per square inch at an o~f of 3.2 was ccmputedtheoretically for this engine configuration. A gas-side wall tempera-ture of 450° F and gas-film properties at 2300° F were assumed for thesecalculations. Experimental rates at this o/f are within 10 percentof this value.

.

—

.

—

A greater differentiation between injectors wouldbe expected foraverage values for the entire chamber length. Measurements for tiffer-ent chsmber lengths were obtained for several injectors. The & effi-ciency changes with length, however, were small and did not significantlyaffect heat transfer at the measuring station. .

NACA RM E58E21 9

A heat-transfer rate fran 3 to 4 Btu per second per square inch re-sults in a loss in performance of about 1 percent per 6 inches of chsmberlength. The C* efficiencies have not been corrected for these losses.The corrections become si@ficant when perfornwnce changes with chamberlength are analyzed.

SUMMAIH OF RESULTS

A study of propellant atomization and “distributionwith 14 cliffer-ent injectors using liquid o~gen and gaseous hydrogen has shown thatC* performance primarily depends on the effectiveness of oxygen atomi-zation. Injecting o~gen by a 0.040-inch-diameter jet gave a & effi-ciency of about 90 percent in a 3-inch chsmber len@h. Increasing theoxygen-jet size generally gave a reduction in efficiency regardless ofthe injection method.

Variations in design of specific injection methods gave the follow-ing results.

y (1) Triplet: Single-element perf~ce increased wtth impingementg. angle up to em included angle cd?20°. Multiple elements showed less

variations in & efficiency with o/f than single elements. Elementspacing or c&ygen dispersion appeared important in these variations im-

. P1.@IW that lateral mix5ng 13mits the ccmibustion-rateprocess.

(2) Concentric tube: Performnc e level was comparable with thatobtained with triplet injectors.

(3) Radial jet: An orientation of hydrogen and oxygen jets to give~um interchange of manentum gave the highest C* efficiency.

(4) Impinging jet: Variations in hydrogen distribution and injec-tim velocity affected both C* efficiency level and variations inefficiency with o/f. Compared with the conditim of uniformly dis-tributed hydrogen at low injection velocity, the interaction betweenhydrogen jets and oxygen sprays in some instances caused performancelosses.

Lewis Flight Propulsion LaboratoryNational Advisory Committee for Aeronautics

Cleveland, Ohio, July 14, 1958

.

10 NACA RM E58E21

REFERENCES

1. Auble, CarmOn M.: A Study of Injection FYocesses for Idquid Oxygenand Gaseous Hydrogen in a 200-Pound-ThrustRocket Engine. Nh2ARM E56125a, 1957.

2. Baker, Louis, Jr., and Steffen, Iked W.: Screaming Tendency of theGaseous Hydrogen - Uquid Oxygen propellant Canbination. NACA EME58E09, 1958.

3. Hei&mnn, M. F., and Auble, C. M.: bjection Principles from Com-bustion Studies ina 200-Pound-ThrustRocket Eugine Using LiquidOxygen and Heptane. NACARME55C22, 1955.

4. Priem, RichardJ.: Propellant Vaporization as a Criterion for Rocket@3ine Desi@; Calculations of ChaaiberLength to Vaporize VariousPropellants. NACA TN 3883> 1958.

5. Priem, Richard J.: PropeMt Vaporization as a Criterion forRocket-Engine Desi@; Calculations of Chamber Length to Vaporize aSingle ~-Heptane Drop. NACA ‘IN3985, 1957.

6. Priem, Richard J.: Propellant Vaporization as a Criterion forRocket-Engine Iksign; Calculations Using Various Log-ProbabilityDistributions of Heptane Drops. NACA ~ 4098, 1957.

7. Heidmann, M. F.: Propellant Vaporization as a Criterion for Rocket-Engine Design; Expertiental lM’feetof Fuel Temperature on Idquid-Oxygen - Heptane Performance. NACA RM E57E03, 1957.

8. Hetdmann, Marcus F., and Priem, Richard J.: Propellant Vaporizationas a Criterion for Rocket-Engine Design; Relation Between Percentageof Propellant Vaporized and Engine Performance. NACA TN4219, 1958.

.

NACA RME58E21 11

TABIS 1. - SUMMARY C@ 2XPERI?4ENTA.LIX7SC’KR PEF!3CFMANCE

(a) ‘IMplet Injeotor

Cka tial llmld-o~ jet, two iw~ hydrogen jets par element.1

Iun Chamber Impinge- Fuel Fuel- Oxidant Total Chamber Oxldent- charaa- Percent Heat-len&th, ment weight injection weight W&@lt preOsure, fuel teri6tic of thec- twmfer

. angle, flow, Velmitg, flow , lb/eq In. weight aaua t retical ratedeg lb/see ft/8ec lb/see lb/n&c abs ratio vel~*ity, c+ Btu//seo)

(aq in.)t-t/s&J

sing]

t42 12 %L43L44L45L20

147146119117118

129 al130L28

L26 40L24L22L25

225 b=2s32842s3296294297

eleme

1.023.021.020.090.074

.065

.064

.060

.043

.036 ~

.051

.050

.056

.056

.049

.042

.041

.126

.097

.084

.009

.062

.064

.053

t; oxygen

31202838273533702672

26402820278023372216

237023502052

230921.SO224021327

sonic32052525330031e526Ca2657

flow area. 0.&J75: hydrc en flow erea, 0.0433. .249274283219219

213194le4162144

le9le7157

214199Ieslel

233

324223215200154

e73eem9562178426230

543264733960495043eo

630763924e63

e37056105430!5060

71907455656670477ooe6223Seoo

es.sel.777.49e.oe2.3

76.765.360.574.571.5

20.289.379.2

62.6e4.5el.8el.s

3.431.542.624.30e.426

.491

.361

.379

.422

.430

.362

.366

.423

.422

.455

.3e3

.46s

.342

.3e6

.en

.36e

.3el

.404

.274

.524

.63s

.n4

.39e

.5U0

.566

.425

.439

.465

.46s

.413

.416

.459

.47e

.504

.435

.509

.46e

.463

.705

.457

.443

.464

.327

4.655.936.ea3.405.73

7.5’95.e46.3e9.e2~.ee

7.107.3011.92

R

l::E

2.713.9e6.4e4.144.426.735.21

90.193.7eel66.9ea.e

2.7e3.753.373.402.622.701.73

n flow I

]

4.714.447.627.oe9.15

3.64

W3.053.66

6.s37.105.164.767.53

6.928.KL9.581.06 ~9.45

3.613.114.093.662.’e2

3.154.325.s36.92e.028.le

Lea, O.0$

J73567436641e66666oe7

759775s375637e4e7425

6879663375447494657e

67el622eeon58066067

774276S6754776~7376

7513760272137ole66886414

1elm a

).533.39e.572.437.461

.46e

.52s

.3ee

.3e7

.454

.579

.5e4

.419

.3e4

.470

.421

.525

.571

.639

.4e3

.446

.3s3

.504

.451

.322

.3s3

.51.O

.563

.577

.520

.596

a, O.0113; hydr(

T

.64e 330

.4ee 252

.646 2ee

.499 231

.5U 216

Rlne element5; oxyset1

-14:514ea10s01130979

16201530122uI.elo1710

XL551090K@J13901075

11301CM33960e7095s

1640leso163316552155

le7514s31.210107097010ZQ

94.0 -—-94.4 -—eo.9 —-22.4 ——2a.e —-

241242243244245

257256238226227

239231240229224

3

6

12

.113

.090

.074

.oe2

.050

.129

.12e

.127

.127

.124

.oes

.oe2

.oel

.oel

.062

.Oel

.060

.060

.ose

.051

.123

.123

.123

.123

.123

.122

.ne

.027

.0s3

.074

.073

.597 315

.657 346

.516 2n

.514 273

.578 29e

95.1 4.oe95.5 5.36e4.4 3.n95.5 3.0592.9 3.00

91.7s4.e95.295.992.6

93.4st.e91.992.2el.4

4.5e

=82.693.23

.6e4 3oe

.666 316

.SCa 255

.465 242

.532 243

.4e2 227

.5e5

.631 266

.e97 281

.534 225

.569 310

.306

.627 ;3?

.574 307

.445 231

96.9 3.4e95.7 2.7695.1 3.e995.2 3.ee62.5 2.2s

__L-.505 2e7.62e 336.660 355.660 32e.664 ?J3.669 1

93.e 2.069e.2 4.4495.7 4.2696.7 4.049e.o 4.1092.4 3.09

12 NACA RM E58E21

TABLE 1. - Continued. SONMARY @ EXPERIMENTAL INJECTOR PERFORK#JCE

(b) Concentric-tube injector

iun Chamber Fuel Fuel- Oxldant Total Chamber oxl&ant- Charac- Percent 13eat-length, weight ln~ectlon weight weight prea8ure, fuel terlstic

In. flow,of theo- tranafer

veloelty, flow, flow, lb/::ein. We;pot exhaust retioal ratelb/seo ft/8ec lb/see lb/see velocity, C* Btu~(seo)

C*, (SCIin.)ft/seo

Single element j oxygen flow area, O.010S; hydtiouenflow area. 0.0490—

:

li158

N2123

E2425

3031333s363738—

8

14

22

).1238.122s.1228.1200.1200.1114

.1210

.1210

.1160

.1160

.0969

.0844

.0s31

.0629

.1260

.1230

.1210

.0843

.0631

.0821

.Oeol

Nine el(

L46 3 0.12347 .123

.123% .06249 .0s1

04 12 .12203 .12102 .121

.121:: .115

06 .076.073

:; .06412 .05613 .049

3465 0.456Sonla .3123360 .6073555 .415“3065 .6603140 .757

36353200264525802475245023202360

.324

.368

.444

.602

.563

.529

.672

.611

L2970 .4392605 .5172455 .5722$60 .4052190 .4942050 .5821965 .661

Ienta; 02

1890160014W11001300

15351780211014701345

12701105910935790

;en fla

0.375.47a.581.665.459

.512

.379

.323

.570

.575

.409

.515

.626

.541

.633

256

:E

%265

235277307344302266279273

3213573s0264

3.682.544.843.46S.506.60

2.883.043.635.196.026.278.097.37

3.434.204.734.80

297 \ 5.94314 7.09322 8.25

area, O.0113; hyh

).498 270.601 320.704 356.747 316.540 263

.634 333

.500 284

.444 236

.691 345

.690 360

1-.485 253.588 282.690 303.597 256.682 266

rogen fl

3.04“3.874.728.165.68

4.213.132.684.734.99

5.407.029.819.6412.64

66837379 %::5496 70.76780 84.85630 73.84622 63.6

7339 92.07873 98.37619 95.66660 86.461T4 82.46026 81.15135 “ 73.85466 76.5

7870 98.47754 97.87622 97.57W2 96.27152 95.26570 91.16039 87.3

------------------------

--------------------------------

--------------—-:-.--------

r area, 0.0939m7463 94.2 3.558071 100.6 3.047552 94.6 2.307095 90.7 2.117413 95.6 3.9a

!ii-M-E(c) Radial-jet lnjeotor

[Oxygen flow area, 0.0136 aq in. 1

Hydrogen Injeation plate 2 (nine center holes); area, 0.1668 sq in.

272 3 0.122 0.465 0.607273

312 4.CO.121

93.0 ----:3? .622 .743

274358

.0625.14 K% 89.9 ----

663 .494 .576 266 6.03 6650 88.8 ----

263 12 .127 710 .632 .759262

3e0 4.98.126 770

7209.545

92.9.671

3.84

266353 4.33

.123 7207576 95.6

.629 .7524.26

267367 5.10

.123 8207027 90.9

.531 .6544.50

215325 4.32

.122 7687155

.52290.5

.6443.61

334 4.29 7369 93.2 3.35

261 .098 7S8 .423 .521269

269.081

4.33609 .521

7435.602

94.1287

3.23

2646.41 6864 92.8 3.85

.081 620 .324 .605270

283 6.47 6736 91.3.060. 530 .662 .742

3.65328 8.24 6365 92.1 4.S?4

Hydrogen inJectlon plate 4 (45 holee); area, 0.6286 S% In.

258 16 0.125 210 0.631 0.756168

377.121

5.03295

7181.438 .559

92.7 4.08

169265

.1213.62

2406775

.53184.8

.6523.53

171323 4.39

.0717079

16089.7

.5253.88

.596 277172

7.44.069 145

6642 93.3.608

3.42.677 302

170 .063 1756375

.40594.3

.4683.09

231 % 7054 95.6 2.97

.—

—

.

.—

d

NACA RME58E21 13

TA2LE I. - Concluded. SUMMARY 08 EXP2RDlENTAL JITJEC9XRPERFORMANCE

(d) Impinging-jet, series I injector

[TWO impinging liquid-oxygen jets; oxygen flow area, 0.0124 w In.]

IRun hamber Fuel Fuel-

1

Oxldan Total Chamberength, weight injeation weight weight pressure,in. flow, velooity, flow, flow, lb/~~~ln.

lb/seo ft/see lb/see lb/8eo

Heat -

tramfer

%fi sec

(sq In. )

I I 1 I I I

Eydrogen injection plate 1 (one center hole); area, 0.0356 sq in.

82 14 0.1083 SOnio 0.422 0.528 255 3.97 8830 85.S.0982 3230 .518 .816 30s 5.27

::7025 81.4

.0977 2935 .804 .702 34578

8.18 6950.0968

93.32915 .610 .707 344 6.30 6881 92.0

.0705 3190 .353 .424 224 5.01::

7470 96.4.0888 2435 .567 .634 281 8.51 6490 94.6

plate 2 (nin zenter holes); area, 0.1868 aq In.Hydrogen injecti

2912902S62832872862922.S8

686970

E424841

;:5354

58588061836465—

3

s

14

22

.128

.126

.125

.125

.116

.083

.082

.077

.125

.126

.125

.126

.125

.125

.124

.123

.123

.067

.086

.086

.127

.125

.118

.119

.Oeo

.079

.070

80512401150U5Q870680SW855

880705730

8961060

1120785

940540645580

985835n5875

W490

3.807.285.367.383.519.391.851.519

.521

.616

.696

.446

.348

.828

.323

.555

.421

.718

.=9

.623

.427

.W9

.800

.678

.635

.637

.668

).733.411.492.4S8.635.474.753.596

.646

.741

.821

.572

.473

.753

.447

.658

.544

.@35

.625

.708

.554

.634

.719

.798

.815

.716

.736

337217233

289207

?s5

315344371

303253373237340

2s1348288316

2833243583&Y289325306

4.822.272.932.804.484.727.916.78

4.174.835.57

3.542.785.022.614.35

3.428.256.277.25

3.364.075.045.706.688.069.54

86107601878768578525626457806096

734470006810

76287698713676257442

7436623466316427

7494746172886980686166506087

84.766.184.865.782.880.382.683.5

92.690.189.5

95.486.498.495.794.2

92.9W.189.289.6

93.694.294.192.284.095.592.0

.

late 3 (16 Pe >heral holes); arerogen injection 0.1963 sq In.

.122

.la

.081

.070

.061

.122

.122

.122

.120

835705555430415

680795

1::

0.543.677.643.757.770

.570

.490

.387

.321

0.665.798.724.827.831

.692

.612

.509

.441

300352298315303

383315273242

2:Z7.69

10.603.2.54

4.684.033.182.67

64156272585354165179

7460731976267804

61.4

.%;85.485.8

85.292.195.297.8

9182979899

104103LolLCKJ

14

22

E@

.123

.121

.101

.080

.080

.123

.122

.121

.079

.079

.119

.119

.118

.078

..078

aen in.iectlonDlate 4 (45 holes}; area. 0.8286 ❑a in.—251253252255254

151150!.48153L54

158157159165166—

3

12

24

-330375235188250

-0.471 72.7

73.176.176.32U.9

8s.868.892.587.268.4

91.961.793.594.092.6

——).594.509.700.709.554

.641

.554

.458

.469

.576

.827

.542

.709

.707

.581

239 3.82207 3.21278 5.95264 7.83205 5.95

318278 ::E239 2.&1224 4.92287 6.34

5795585857185363=28

7035no37399677265541

72n7329

:E6903

.388

.598

.629:i74

245 .518280 .432320 .337Z?o .380180 .499

3.473.082.532.492.82

4.483.044.563.343.37-i

240 .508275 .423210 .590265 .629185 .483 --L

319 4.26278 3.55

4.97:2? 6.04271 6.18

@

0.M5”

J-i

4-

56

+’*. ., ,.

.91ng19fikmnt crAnt9r

4/-- 4oQ-

,,

v....mm elelint mlla dE9m’t

Total rlml area,

w in.

m 0.C075 0.0075 O.a?m O.oll?l

.inzz .0Lx5 .1731 .raa

a-m Ma, in.

- O.Can 0.0s73 O.Can O.obo

J-m .16s .168 ,092g

~-~nz.ceit~,rt~mo SZ9Z 3293 m M4.5

(oou lb/M.J)i

(a)miJllDtirMta. M

Ti&lm91. -r@.84tacaedm9. #

P

1 .1

i, . .. ... ,, !:;.,: .,

, S98’P ~ ‘1, ,, ,,

.

I ) h 4865

I

02 Oz

t

%+A

%!. p2

<:.:::::<“’:3.:rlalhllq ..,, ,.jfi<,.,i.i.;,;,:>, i~,~ .,./.,,..:? runeekmlent ‘“‘“-._.

Total flow area, eq h.

0.0108 O.om

=~en ;0490 .0939

tiY~ OrSiOO au., b.Hydrcgen eanwlar width, in.

o.117 0.C40.0625 .044

E@kW1l-%iection velocity,

29EL5(o.ufi&/L)

1675

(b) Conoentrio-tube Injeotor.

Figure 1. - Cont@ed. mjeotor d.ealgm.

. /$’)0.45”

02 %.

“z-r- ..3-02

Injection plate 4 Inj&tiOn plate Z

(4s Holes) (10 Canter imles)

mtal KLQU area,

%%0.co.36 “.6=6

0,0136

.lma

mifica aim., in.

- 0.0466 0.0496

F@r-0.1.2s 44 wlas

1

0.2.25 Him hal.ee )

.SM5 @ 1231e.2125 “m hole)

~cgan-lnjeotim

velmiq, fi/wZi5

(0.12 lb/13Y0)

840

(0) Radial-jet In.iOo’tm.

m 1. - o~. IDJ.sata &ml@w.

, ,$%X37”

‘,

Q~ooo

o0° 0

0 00 00000

% %

o

4865 ,

m’tcklnow mea,

9a in.

w o.Ola o.m?.4 0,0U4 0.0M4

.dmd .19&s .lm?a .0ss4

OrW1.ce dim., in.

Q .@30 0,039 0.039 0,0.99

~ O.uo 44 E0100) 0.126J1l.fs ma bolo)

0.xxi HIM lam) o.n.z

mwwm-iaildim

.Slm cam IlOLa)

I-OlOaitr,ftfti(0.M lb/,cc) m 880 Em mm

[

Ni-

llACARM E58E21

.

Water * ‘T7ml

-’”Figure 2. - Water-cooled chamber segment used

section view of coolant passages.

4for heat-re~ection measurements showing

.

.

.

* I CjT-3 back. 4865 , ,

8400

60002 4 6 8 10 12 14

Oxidant-fuel weight ratio, o/f

Figure 3. - TheoreticeJ_ variatton of characteristic exhanat velocity with

mixture ratio for hydrogen and omwen.

Fm

@ @

0.35”

!-i0.35”

+

Eangla AYrant OfYcenkr;

impinganalteagle, a, w

Hz‘%

Hz

#

. . 1..,

T i

0.Z5”

a

,,

v

,,:

6

L+

4A

A AA

A

:Z‘

. ‘z

1,”, II

2 4 6 e 10 12

Oxlam’c-futi weight ratio, 0/f~

(a) Siugle-elemmt cO&uratiOn; chmber length, 12 inches.k’

Ffme 4. - Pea%— e of triplet i~eckma. &l

!?

.S9w ,“ ‘

9 \ , t 4865 * .

Ho airflow In@n8emnt angle, 0° Impingement angle, ZX3° Impingement angle, 40°

(b) Single-element c~iguration. Flow rates: water, 0.211 pound per second; air, 0.036 ~und persecond.

l?Qure 4. - Continued. Performance of triplet injectors.

.

.

.

.

.

1 I 4865 , 0

Oz

292 “

-q /’-’400

100

n

-o 9— 3c)

80

1.2-lach Ohamber length

60 ,

“2 4 6 8 10 i2Oxidaut-fuel weight ratio, o/f

(c) Four-element cofiiguratlon.

Figure 4. - Continued. Performance of triplet injectors. ccl0!

.—

3“ 3“

,,,

100

80

Cbfmber Urn@,in.

6

J❑ ❑

4 ‘ I1 u—c~

J~

[

P “~

o?-2 4 6 8 10 12

Oxkiarib-fuel weight ratio, o/f

(d) Nine-element cotiignrati.on.

F@ure 4. - Continued. Performance of triplet injectors.

*

.

.

.

NACA RM E58E21 25

--- . ,_ .._ ._. .,. :~::~. . . .. . ~~.$

-.

(e) Nine-element configuration.water, 0.370 pound per second;pound per second.

Flow rates:air, 0.058

Figure 4. - Concluded. Performancetriplet injectors.

of

—

Chmiw length,

k.

2 4 6 8

Oxidant-fuel weight ratio, o/_f

10

(a) Single-element configuration.

Figure 5. - Perfonnauce of concentric-tube injector.

h!

,,,

.

.

.

NMA FM E58E21 2’7

,

(b) Single-element configuration. Flow rates:water, 0.330 pound per second; air, 0.040pound per second.

Figure 5. - Continued. Performance ofconcentric-tube injector.

,,

-2 4 6 8 10 12 U

tiidant-fiel weight ratio, o/f

(c) mine-dent ConfigWBticnl.

Fiwe 5. - Continued. Perfom9nce of concentric-tuba in.jertor.

. W&P ‘ ‘

HACA RM E58E21.

.

K..!n=-.,,-

;..

c-:.--.,., .*—— .%:-

>—- --—-- -– ---=+—- ‘:’F,—

-.——— j

%-j<:$ ---.““u%?:.%!

.

(d) Nine-element configuration. Flowrates: water, 0.370 pound per second;air, 0.032 pound per second.

29

Figure 5. - Concluded. Performance ofconcentric-tube injector.

010

H2,

02 02

& .,,

6

4. .

n o n() n

22 4 6 8 10

Oxidant-fiel weight ratio, o/f

(a) 45-Distributed-hola plate.

Figure 6. - Perkumxmoe of radial-jet injectom.

,S987

●

NACA RM E58E21 31

-. . ..- .,‘ A

g:.-’.-

.“. :i -.,,

----- . .. .-. ~, “ ..

,.,.$. .. .. . ..—

(b) 45-Distributed-holeplate. Flow rates:water, 0.320 pound per second; air, 0.107pound per second.

Figure 6. - Continued. Performance ofradial-jet injectors.

-. _—. .

4 6 8

oxidant-fuel weight ratio, o/f 5

(c) IHne-center-hole plate.R

H

F@ure 6. - Conthm?d . Perfcummce of redid-jet injectors. B

&

.,, i,

a . S9EW $ *1

.

.

NACA RM E56E21

m&

s

(d) Nine-center-hole plate. Flow rates:water, 0.320 pound per second; air, 0.105pound per second.

33

Figure 6. - Concluded. Performance ofradial-jet injectors.

,1

, .

I&x% -f. -

t ,Chamber ligth,

h.

A so 12h 24

100

0 t.u -1A•ÿÿÿÿÿÿ u

u uc

*

80

A A. &

/,

60

6

h4

E,

6u

L

2z.4 6 8 10

oxidant-fuel weight ratio, oif

(a) 45-Distributed-hole pkt..

Perfmmncf3 of h@ng* -n-jet ~eatcnm.

● ✎

‘398? ‘ “

NAC!ARM E58E21 35.

.

.

----4

L. . . . . ,.. ..a+

k -- ~ :.. .y-J ...:.+

— .“. - “A,-

. . ,... .:r~,.=

..-.->..

k.,.’.: . -.:.

,.. -A., .;.”-=

.’ .

3s!.. .=.‘X’”vv’+?o”~.. —................

(b) 45-Distributed-holeplate. Flow rates:water, 0.305 pound per second; air, 0.110pound per second.

“iiii...------._--=...!

.’, ,-

..<..

. .

. .

*n-t n*.

Figure 7. - Continued. Performance of im-pinging oxygen-jet injectors.

.

—.

.

.,

—

,-

Q~o 00

0 0

0#

o

0 0

0 0

‘o o0

Ohexacterld 10 exhaust

veloo ity, @,

proemt’ of theoretical

-CZEBSE HH Vmm

I’iACARM,E58E21 37

1 ,.-... . . .--. .-,.

..:.

ElEL ..””-’.. .

.... . I

c-48195-.——..——. .— .—.—.— .—.—

(d) 16-Peripheral-holeplate. Flow rates:water, 0.305 pound per second; air, 0.107pound per second.

Figure 7. - Continued. perfor~nce of im-pinging oxygen-jet injectors.

.

HZ

Figure 7. - Cautinued .

# .

80

1 1 IChmnber length,

in.

A 3

❑ 8

0 14

() h 22

1m

n

AA

-A A

4 6 8 10 12

Oxidant-fuel weight ratio, o/f

(e) Kim-center-hole plate.

Perf ormano e ~ ~q~ oqgen-jet iqjectora.

I .

S9W●

I$ *

4865 ,

.,

(T) Nine-center-hole plate. Flow rates: water, O .XIO pcund per second; air, 0.103 pound par second.

Figure 7. - Continued. Pert%rmam e M @@@ o-n-jet Insectors.

wto

.

Hz

-.2 8 10

Q&ant-fuel w~lght ratio, o/f

(g) One-oenter-hole plate.

FQyre 7. - continued . Perfczmmce of 5mpMM qen-det frklectms.

t .‘3-87’

.

,4863 “ ‘

(h) One-center-hole plate. Flow rates:

Figure 7. - Conoluded.

,.-. C-4819:

water, 0.305 pound Per second; ah. O.OZO pound per second.

Perforuwoe of impinging oxygen-jet inJectorao

42

100

90

80

70

60

100

90

80

70

60,

NACA RM E58E21

Oxygen vaporized and availablefor reaction, 100 percent

Hydrogen not mixed)—percent of tot&1

\

\

.

.

,.Gaseous hydrogen available @gen not vaporized,for reaction, 100 percent percent of totti

— — — 10

- 20

— ~- 30

-

\ ~ ~~ /

40

2 4 6 8 10 12Oxidant-fuel weight ratio, o/f

Figure 8. - The effect of incomplete o~gen vaporization andincomplete hydrogen mixing on characteristic exhaust velocity.

4

.

NACA RM E58E21

I I 1 I 1 I iInjector Impingement

engle, deg—.— Single element o----- Si@Le element 2oena40—-- — Single demerit 20 (offcentcr]— — Four &iement 40

Nine .dement 30

lm

_ —- -\ ~

-- q :90 — N%

. -- -\

\\

x x-. \\

so -.\

1.%

702 k 6 8 10 12

(a) Triplet injector in 12-inch chember length.

100 \

\

\

\

90 \

80

\

70

m2 4 6 s 10 12

Oxidant-fud weight ratio, o/f

(b) Concentric-tube i~ector.

Ftgure 9. - Sumnary of inJectir performance.

44 NACA RM E58E21

1 1 I 1 1 L

Hydrogen plate Chamberlength, in.

45 Hole 16.— Nine hole 12

100

90

Ou2 4 6 8 10

(c) Radial oxygen-set injector.

1 1 I 1Plate Chamber

length, in.

45 Hole 12‘—— 16 Hole 14—.— Nine ~ole

10014

,———— One hole 14

+. --- .— -./&

y

./‘ -/

90- 6 \ .//

/8 /

- - - —,

— — . -

80 \2 4 6 8 10 12

Oxident-fuel weight ratio, o/f

(d) Impinging oxygen-jet injector.

Figure 9. - Concluded. Summary of injector performance.

NAC!ARM E58E21 45

1 1 1 1 1 i

Injector

Four-element triplet— — Nine-element triplet———— Nine-element concentric tube

5 —-— Radial jet, 45-hole plate—--— Radial jet, nine-hole plate—---— Impinging jet, 45-hole plate

f

3 -

.‘2 4 6 8 10 12

Oxidant-fuel weight ratio, o/f

Figure 10. - Summary of heat rejection for various injectors.

NACA - LangleyField.Va.