r l c a f advanced oxygen-hydrocarbon rocket engine study · foreword...
TRANSCRIPT
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(llA_ A-CR'-'161760) ADVitltCED It81-231_4
OXYGEH-_¥D_OCARBON ROCKET ENGINE _TUD¥Bimonthly PEogEe_ RepoRt, I Feb. - 31 MaR.
,, 1980 (AeEojet Li,_uid Rocket Co.} 53 p Unclas,{ _C A04/_F A01 C$CL 21t-1 G3/20 24073
Advanced Oxygen-HydrocarbonRocket Engine Study
Contract NAS 8-33452Bi-Monthly Progress Report 33452M-3April 1980
Prepared For:National Aeronautics And Space AdministrationGeorge C. Marshall Space Flight CenterMarshall Space Flight Center, Alabama 35812
By:C. J. O'Brien
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1981014651
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ADVANCEDOXYGEN- HYDROCARBONROCKEI
ENGINESTUDYi,
CONTRACTNAS 8-33452
r Bi-MonthlyTechnicalProgressNarrative33452 M3
lO April 1980
PreparedFor
NationalAeronauticsand SpaceAdministrationGeorgeC. MarshallSpace FlightCenter
MarshallSpace FlightCenter,Alabama35812
Preparedby: Approvedby:
en / J. IV.Salmo(k(kProjectEngineer ProgramMan_ge#ALRC Engineering ALRC Programs
AEROJETLIQUIDROCKETCOMPANYP.O. Box 13222
Sacramento,California 95813
,_._.,.................................................................-"'"_:_:':" ':-:-.....:::::::::::::::::::::........:_......::"=::'::.....:"'::-': ..................................i98i014651-TSA0:
FOREWORD
This is the third bi-monthlyprogressreportsubmittedfor the Advanced
Oxygen- HydrocarbonRocketEngineStudy per the requirementsof Contract
NAS 8-33452. The work is being performedby the AerojetLiquidRocketCom-
pany for the NASA-Marshal]Space FlightCenter. The contractwas issuedon
15 October1979. The programinclusivedates for periodof performanceare
15 October1979through15 February1981. This reportcoversthe periodfrom
l February1980to 31 March 1980.
The programconsistsof parametricanalysisand designto providea
consistentenginesystemdata base for definingadvantagesand disadvantages,
systemperformanceand operatinglimits,engineparametricdata, and tech-
nologyrequirementsfor candidatehigh pressureLO2/Hydrocarbonenginesystems.
The NA_A-MSFCProjectManageris Mr. R. J. Richmond. The ALRC Program
Manageris Mr. J. W. Salmonand the ProjectEngineeris Mr. C. J. O'Brien.
Contributorsto this bi-monthlyreportare:
R. L. Ewen - HeatTransferAnalysis
S. Kent - EngineWeightand EnvelopeAnalysis
G. M. Meagher- PerformanceAnalysis
."_ECEDING PAGE BL.ANKNOT F_,Lk_D
iii
1981014651-TSA04
L.NTS.
.!",".', I Introduc ti{ill ]
_,:,,;.*I A. Ta';k| L l,(}illP(:ycI{_C{111fi¢IIlriitJOIl[}eflnltlon 2
;L_I';;'_", [_. T,14k I] -' i Jib,lille P_r_lillo.tri¢ All_l],ysis _'_
C. '[,_skIll .-IJIuine/VehicleTrajectoryPo.rfoMilallCe 2Assessment(En{.!ine Screenitlg)
I). Task IV - LIaselineEngineSystemsbefinition 2
IL. Task V - Reporting 2
II. TechnicalProgress5u,l,ary 2
A. Task I - LngineCycle ConfigurationDefinition 4
B. Task II - EngineParametricAnalysis 12
C. Task Ill - Engine/VehicleTrajectoryPerformance 32AssesSlllellt
D. Task IV - BaselilleEngine SysLeIi!Definition 32
E. Task V - Reporting 32
III. CurrentProblei1_s 46
IV. Work Planned 46
A. Task I 46
B. Task II 46
C. Task Ill 46
D. Task IV 46
E. TaskV 47
iv
- * 1981014651-TSA05
TABLE LIST
':'!i No. P.a,j.o:.:'_ I Purlfled RP-'ICooling Sunlnary 5
i...i_ !I Methane Coolin.qSummary 6;ii'!:"_. III Oxygen Coolin,qSmmlary 7
IV Hydrogen Cooling Smmtary (LOX/RP-I Enqine) 8
V Hydrogen Cooling Summary (LOX/CH4 Engine) 9 ,i
Vl Nozzle Cooling Sunmary lO I
Vll LOX/IIDFBaseline Engine Weight Breakdown 43 1
VIII LOX/RP-I En_lineEnvelope 44 i
IX LOX/CH4 Engine Envelope 45
FIGURE LIST
.F.i_]ure No. p_a_ge
1 Major Milestone Schedule 3
2 Delivered LOXIRP-I Engine Performance Versus Chamber Pressure 13
3 Delivered LOX/RP-I Engine Performance Versus Mixture Ratio 14
4 Delivered LOX/RP-I En.qinePerformance Versus Thrust 15
5 Delivered LOX/RP-I Engine Performance Versus Area Ratio 16
6 Delivered LOX/CH4 Engine Perfmlllance Versus Chamber Pressure 17
7 Delivered LOX/CH4 Engine Performance Versus Mixture Ratio 18
B Delivered LOX/CH4 Engine Performance Versus Thrust 19
9 Delivered LOX/CH4 Engine Performance Versus Area Ratio 20
I0 Typical AOIICWTWeight and Envelope Computer Program Printout 21
II LOX/RP-I End.lineWeight Versus Chamber Pressure (, _ 20) 22
1'2 L.IIX/RP-IEngine Weight Versus Chamber Pressure (, = 50) 23
13 LOX/RP-I Engine Weight Versus Chamber Pressure (, = 80) Z4
14 LOXIRP-I En_lim, Weight Versus Chamber Pressure (, : lOO) 25
15 LOX/RP-I Fn!lineWeight.Versus Area Ratio (Pc _ 5000) 26
16 LOX/RP-I En!lineWeight Versus Area Ratio (Pc = 4000) 27
1981014651-TSA06
FI_G!I LJs.X. t..,.)
F.i_._Lre_No. .Pa_!_;
17 LOX/RP-I Engine Weiqht Vor_a_ Area Ratio (Pc _.3000) 2B
I_ LOX/RP-I Engine Weiqht Versus Area Ratio (Pc _ 2000) 29 :
19 t.OX/RP-I[ngine Wei_lhtVersus Area Ratio (Pc :"I000) 30 I
20 LOX/RP-I En_.lineEnvelope Parameter_ Versus Chamber Pressure 31
21 LOX/CH4 Engine Weight Versus Chan_er Pressure (, = 20) 33
22 LOX/CH4 Engine Weight Versus Chambe.rPressure (, = 50) 34
23 LOX/CH4 Engine Weight Versus Chamber Pressure (, : 80) 35
24 LOX/CH4 En_jineWeight Versus Chamber Pressure (, = I00) 36 i
25 LOX/CH4 Engine Weight Versus Area Ratio (Pc = 5000) 37
26 LOX/CH4 Engine Weight Versus Area Ratio (Pc : 4000) 38
27 LOX/CH4 Engine Weight Versus Area Ratio (Pc --3000) 39
28 LOX/CH4 Engine Weight Versus Area Ratio (Pc = 2000) 40
29 LOX/CH4 Engine Weight Versus Area Ratio (Pc : I000) 41
30 LOXICH4 Engine Envelope Parameters Versus Chamber Pressure 42 "
_" vi
1981014651-TSA07
I. INTRODUCTION
In the dr_cadeof tho lBBO'sand beyor1(I,tho nation'.sexpanding,space
operationsmay r_.quir__n improwd ,;urfacf,-to_orbittran._partationsystem
using advanc_.dboostervehicleswhich havo in_.roa_edp_rformanc_and capa-
bllitycompared'tothe currentspaceshuttloc(}ncept.The mlxc,d-modepro-.
pulsionprincipleclearlyindicatesthe potentialporformanc_advantagesof
usinghighdensity-impulserocketpropellantsin such large^V applications.
For thisreason,hydrocarbonfuelsexhibitingincreasedden.sityrelative
to liquidhydrogen(L.H2),at the penaltyof lower specificimpulse,are beingconsideredfor the boosterpropulsionsystemof space shuttleimprovement_
and derivativesas well as for single-stage-to-orbitand two-stage-to-orbit
heavy-payloadvehicles..I
Preliminaryidentificationand evaluationof promisingliquidoxygen/ 'i
hydrocarbon(LO2/HC)rocketenqinecyclesis desirableto producea consistent .'and reliabledata base for vehicleoptimizationand designstudies,to demon- _
stratethe significanceof propulsionsystemimprovements,and to selectthe
criticaltechnologyareasnecessaryto realizesuch advances.
It is the purposeof this study to generatea consistentenginesystem
data base for definingadvantagesand disadvantages,systemperformanceand
operatingli-'_ts,engineparametricdata, and technologyrequirementsfor
candidatehigh pressureLO2/HCenginesystems. The studywill alsosynthesize
optimumLO2/HCenginepower cyclesand generaterepresentativeconceptual'enginedesignsfor a specifiedadvancedsurface-to-orbittransportationsystem.
To accomplishthe programobjectives,the study is composedof four
major technicaltasksand a reportingtask. These tasksand summarizedob-
jectivesare:
A. TASK I ENGINECYCLE CONFIGURATIONDEFINITION
Formulateand assessfamiliesof high chamberpressureL02/IICenginecycles.
l j.!
1981014651-TSA08
1_. TASK II ENGINE PARAMETRICANALYSIS
it Gl,ll_w,| t¢_ pot FOl'lll_llc(_., wt_'l¢,]ht,, _lnd _nv(_,lope ptit'dlllO,t.ri_: data forvlabl(, cmlCel)t,,; l_a_,d upml historical data and c(mCel)t, ual (_valuat'ions.
t C. TASK III INGINII/Vi]IICL_ TRAJICTORYP[RFORMANCI"ASSESSMENT(IiNGINF _CRL[:NING)
Li a preliminary comparison engine cycles utilizing
Conduct of selected
a simplified vehicle trajectory performance model.
ii.D. TASK IV - BASELINE ENGINE SYSTEMS DEFINITION
Prepare preliminary designs of two baseline engine configurations.
Conduct heat transfer, turbomachinery, combustion stability, structural, and
controls analysis of the baseline engines and components. Conduct a parametric
sensitivity analysis including the effects of turbine temperature and number
of usable life cycles. Provide the appropriate data in a format suitable for
use in vehicle application analyses.
E. TASK V - REPORTING
Provide infomnal bi-monthly technical and fiscal progress reports,
f hold program reviews at NASA/MSFCand prepare a final report./II. TECHNICAL PROGRESS SUMMARY
., - ......................................
The overall progress on the program is indicated in Figure I.
......................"- # '_......"...........:'._" '_;.':C_L"'L:"_"_."'0:'• '....' "''_"':"_ ....."'-''"'"''._.'_""_''!,'_
1981014651-TSA09
3
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]98]01465]-TSA]0
A. TASKI - ENGINECYCLECONFIGURATIONDEFINITION
1, T_h.ru._.tC.hamh_r._!'ImLt.T_rjTnsf'Or
The paraB_trlcchamberand nozzle,(, _ H to 40) cooling
analy._isis completefor the fourpotentialcoolants' RP-I, LCH4, LO2 and
LII2. Docune.ntationof the resultsis underway. A summaryof the coolingcapabilityof each propellantis (.livenin Tables I throughVI.
RP-Iwas found to be an unsatisfactorycoolantwhen a
coolant-sldewall temperatureof 550°F {theacceptedcokingtemperature
for this fuel)is imposed. If a purifiedversionof RP-I (e.g.,JP-7) with i
a coolant-sidewall temperaturecokinglimitof 800_F is used, the purified _
fuel is seen in Table I to be capableof coolingenginesoperatingat cham-
ber pressuresup to 2500 psia.L
All of the heat transferanalysesare based upon a clean
zirconium-copperhot gas-sidewall. Early LO2/RP-Iengines,such as theTitan I, the H-I and the F-l enginesbenefitedfroma carbonlayerbuildup
on the thrustchamberhot gas-sidewall. These enginesoperatedat chamber
pressuresfrom600 to I000 psia and at fuel-richmixtureratiosfrom 2.23to
2.27 (equivalenceratiosfrom 1.53to 1.51),and were RP-I cooledto area
ratiosfrom 8:1 to lO:l. Since the carbonlayerbuildupon such engineshas
been knownto flakeoff, advancedengineparametricstudies(suchas on
ContractNAS 3-19727)were directedby NASA/LeRCto be based on uncoatedwalls.
This assumptionis seen to ruleout conventionalRP-I as a coolantat chamber
pressuresof lO00psia or greater.
An investigationof the sensitivityof a carboncoatingis
beingconductedon anotherproqram (NAS9-15958). The data and approachfor
thateffortwill be reviewedon thisprogram,and the coatingsensitivity
_ .. ..
1981014651-TSA11
, ')'
. .].
i TA_BJ:.F-_!_._, PURIFIED RP-1 COOLINGSIIMMARY
COKINB WALL TI:MPERATI.IRI;LIMII _._HOO'_F
-i'Thrust I) AIb
Jlm
' ¢ Coolant AP L'
) ).p6].bf, P.s_!_ Fr_a._.tlon p,_1 "_,l
:] 0.2 I000 0.9 192 191 14.14;l) 1500 641 203 12,.88 i
2000 1.0 1210 195 12.05
2500 2322 200 1I. 45 1
0.6 I000 O.9 237 165 22.38 ]
1500 614 165 18.27 i
1" _ 2000 1210 168 15.83-_FJ
i! 2500 2063 169 14.74 i2.0 lO00 332 147 40.86
1500 794 148 33.36
2000 1466 150 28.89
2500 1.0 2517 135 25.84
5
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i98iOi465i-TSAi2
1Off]bf pst a p'_1 "F
/it0,2 I000 45 147
2000 258 '176
3000 840 193
4000 219_ 197
O,6 ]000 6}2 IP.9
2000 295 138
3000 833 147
4000 2088 ] 53
5000 4885 156
2,0 1000 84 117
2000 388 123
3000 1220 124
4000 2818 124
,_.1'::', ..-.- , . '_" • ,%,, , .:_: _' ....-,. " t . ,
1981014651-TSAq3
....
T!_!_U:_._UI
OXY(41_NC(.I(.II.INGLIIIMMARY
l'hru,;t Pc Co_'lant Ap ATb I,'1061hf pc,i,_ Fraction fmi "F Ill,
O,2 1UO0 I,0 78 82. 14,14
2000 376 % 1_,05
3000 1122 103 10.98
400U 2889 107 1U,28
0.6 1000 108 72 22,3b
2000 450 73 _[ :
3000 11?_" ,:. 14.14i
4000 28,. 79 13.23 1
2.0 1000 0.87 125 73 40.86
2000 553 74 28.89
3000 1672 73 23.59
4000 4424 73 20.43
1981014651-TSA14
TABLE IV _.i
HYDROGENCOOLINGSUMMARY
LOX/RP-IENGINE
Thrust Pc Coolant ap ATb1061bf psia Flow,Ib/sec psi _F
0.2 lO00 7.5 53 655
4000 15 440 445
5000 20 799 355
0.6 lO00 15 137 787
4000 25 405 491 I'
5000 30 680 429
l.O lO00 20 256 946
4000 30 429 559
5000 35 770 498
2,0 lO00 40 607 879
4000 50 715 594
5000 60 850 478
8
1981014651-TSB01
!_'I-'.F_
.,,_i TABLEYHYDROGEN COOLING SUMMARY
LOX/Ctt4 ENGINE
Thrust Pc Coolar AP ATb
!.06!bf psia F_l_gw_,_.J__Z_e__P_.i. ._.._
0.2 I000 7.5 72 740
4000 14.6 611 495
5000 19.4 II05 395
0.6 lOOO 15.0 199 900
4000 24.7 563 558 _!
5000 29.5 1041 484
l.o 1000 25.0 334 852 I;
4000 29.7 767 642 iJ]5000 34.6 1369 568
2.0 1000 40.0 893 1004 :!I
4000 49.6 983 684 ;:
5000 59.4 l]22 551
ii
:!
"198"10"14651-TSB02
TAB!-EVI
NOZZLECOOLINGSUMMARY(t__ B to 40)
I. BaselinoD(_siqns(LOX/RP-I)
F _ 600,000Ib Pc _ 4000psia ]
Coolant ^P ^Tb
psi °F
_"_ Purlfied RP-1 440 106O_ 77 56C
2. Scaling
^p pc3"5 F0.25
ATb -.PcO.O5/FO.075
?
4'
lO
1981014651-TSB03
II,TechnicalProgre._sSummary(cont.)
determinedfor selectcasesat a thrustl(_velof 6(10KIbf. Caremust be
taken,however,in applyingdata from lowerpressure(Pc _,1000psia)
chambers. The higherpressuresof this programrequirea mixttlreshift
towardstoichiometric(e.g.,Pc _ 4000 psia,MR _,2.9, ER _ l.IB),and the
lessfuel-richenvironmentmay not resultin as greata carbondeposit.
Methaneis capableof coolingan LO2/LCH4 thrustchamber
to chamberpressuresof 4000 psia. Above thispressurelevelthe coolant
channelpressuredrop becomesexcessiveas shown in Table II for the 600K
Ibf engineat a chamberpressureof 5000 psia (^P = 4885 psia).
Table Ill showsthat liquidoxygencan coolan LO2/RP-Ior
LCH4 engineto chamberpressuresof 4000psia. The high pressuredrop shown d
for the largethrust(2M Ibf)enginecan probablybe reducedthroughchamber
geometryoptimization.Scalingo_ the baseline600Kengineresultsin a !relativelylongchamberat the high thrustlevel,which resultsin a high I
coolantchannel^P. .i
Liquidhydrogencoolingsunmlariesare given in Tables IV
and V, for LO2/RP-Iand LO2/LCH4 engines,respectively.It is seen thatsmallamountsof hydrogenare required,theseamountsbeing co_nensurate
with the powerbalancerequirementsfor theseengines.q
The nozzlecoolingsunmlaryis given in Table VI for bothi
purifiedRP-I and LO2 coolants. The pressuredrop and bulk temperaturerisein both casesappearto be satisfactoryfor the baselinecase given in the
table. Scalingequationsfor differentchamberpressuresand thrustlevels
are also given in the table.
II
] 98] O]465]-TSB04
II, A, task I - En_In_)Cycle Conflquration Definition (cont.)
No additional work was cond,cted on this subtask pending
completion of the heat transfer effort.
B. TASK II - ENGINE PARAMETRIC ANALYSIS
I. .EnginePerfomnance
Parametric engine performance data are summarized in Figures
2 through 9 for the LO2/RP-I and LO2/LCH4 engines. The simplified JANNAFmethodology was used to derive the delivered performance for each point design
engine. A more detailed description of the n_thodology and results will be
given when this effort is con@leted.
2. En._ne Wei_lhtand Envelope
These subtasks have been completed. An existing ALRC
parametric weight/envelope computer program was modified to provide the
weight and envelope data for the advanced oxygen-hyarocarbonengine cycles
considered in this _tudy. A sample output for the baseline case (LO2/RP-I,fuel-rich gas generator, RP-I cooled) is illustrated in Figure lO. Parametric
engine weight and envelope data are presented for LO2/RP-I engines in Figures
II through 20. Table VII gives the baseline weic_ts used throughout the
analysis. (This table is an updated version of Table V of Bimonthly Progress
Report 33452 M-2, February 1980.)
Because most of the cycles studied are very similar, parametric
information is presented only for a typical baseline cycle. Differences in
these cycles leading to weight differences will be reported separately when a
con@arisen is nBde between the cycles.
12
il 14
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1981014651-TSB07
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1981014651-TSBO8
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1981014651-TSC04
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I I I i• dc; ,..Z u-,
30
?*''...... 2 ...o'c,2_2 _'TT?T _ . ............. , ..._ _. ..... :'_'--_ ...... _"_-; ............."_"_....... _ _-'," .,_ _--"_';__ ' -_-'_ - ' "_'_:_
1981014651-T8009
If, B, Ta._k II - Enflln_ ParametricAnal.w;is (c_mt.)
Bas_l'InP m,_lino,w_i!.lht and onvel_pe data i'nr th_ I-,O?/LCH4
_,la.,;flenorator, fu_q-r'ich ,qas !_,,,oratm', LCH4 cooled cycle ar(_ pr_smlted in' Fiqures 21 throuqh 31_.
!! ParamL,tri(:envelope'Infnrmal,i{_n,as gt,neratt)dby the AOHCWT
coml_ut:eri_rL_gram,is (t_:l_en(h,ni_ only on thrust, area ratio,and propellant
" combination.Thesedata are presentedgraphicallyin Flqures20 and 30 for
-!_ U_ebaselinearea ratioof 50:I,but otherarea ratioenvelopedata are in-_'_i cludedin TablesVIII and IX.
C, TASK Ill - ENGINE/VEIIICLETRAJECTORYPERFORMANCEASSESSMENT
I. MissionCharacteristics
The characteristicsdata presentedin BimonthlyProgress
Report33452M-2were approvedby the NASA ProjectManager.
Z. Traje_cto_orgy_PerformanceModels
This taskwas delayeduntildefinitiveenginedatawere
generatedin Task I.
D. TASK IV - BASELINEENGINESYSTEMDEFINITION
No scheduledactivity.
E. TASK V - RFPORTING
An inform,i!prm}ramreviewwas held 7 March wlth the NASA Project
Mana_ler.It was concludedfrom the discussionthat ._uchitemsas turbine
32
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"198"10"1485"I-TSC'I3
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1981014651-TSD03
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"198"101465"l-TSD04
I
i
TABLEVl!
LOXIHDFBASELINEENGINEWEIGHTBREAKDOWN
_ LOX/RP.'I L0._X/_C,_H4"
I STAGED GAS STAGEDGAS. CO_MB_USTIONGENERATO_R.C.__!BLI_§T_IONGEN_ERAT_OR
FB (Thrust,Ib) 600,000 600,000 600,000 600,000
PCB (ChamberPressure,psia) 4000 4000 4000 4000
'B (AreaRatio) 50:1 50:1 50:I 50:I
'ATTB (AttachedArea Ratio) 8:1 8:I 8:1 8:1
ATB (ThroatArea, in.2) 85.66 85.66 86.14 86.14(AllWeightsin Ibs)
WGB (Gimbal 207 207 207 207
WMISCB (Miscellaneous) 296 296 296 296
WINJB (Injector) 656 656 656 656
WTCNB (Nozzle) 420 420 422 422
WCCB (ThrustChamber) 226 226 22.7 227
WPBOB (Ox RichPreburner) 224 - 224 -
WPBFB (FuelRich Preburner) 181 50 181 51
WVOB (OxidizerValves& Actuators) 325 325 331 331
WVFB (FuelValves& Actuators) 82 82 131 131
WBPOB (OxidizerBoost Pump) 307 307 313 313
WBPFB (FuelBoost Pump) 52 52 83 83
WMPOB (MainOxidizerPump) 862 623 878 638
WMPFB (MainFuel Pump) 327 366 521 567
WLPLB (LowPressureLines) 201 201 243 243
WHPLB (HighPressureLines) 268 268 324 324
WPSSB (PressurizationSystem) 133 133 133 133
WHGMB (HotGas Manifold) 207 207 207 207
i!I WIGNB (Igniters) 60 60 60 60WCNTRB (Contro11er) ]30 !3_0 ]_30 130
/ii TOTAL 5164 4609 5567 5019
1981014651-TSD08
v_
_5
....:_,,,+_.__17T;_T_-T-'__ .. .+,.._._
........'....".... °-. '..+".' '.......'..... '".."_ :_.,° ".....'":.__ _. ,, __._,_:+'_-_,'_'+:'+-._:-._::?C,-__....... , ,+., . , , • ..,,. . ,,., , ,: ,_.... , . . . _=.._ . -,v ";' 'T "--- +_" _. ...................................
.+,-,,.,+,̂ _, ; _ ± .:_'....... +.....
iIii! inl(,tt,_mlmraturefro'nxidizer rich turbin,,Gbt_ro-t_xamin,_din an effort
I in e_;tabli_htim tochntllo_lyrequlr_ment,s t_)make some of the marginal cycle_.;.- cm)ipetitive.
i:!i Completion of the heat transfer effnrt six weeks behind schedule is-f
not anticipated to cause a slip in the overall schedule for completion of
Task I and the interim program review scheduled for mid-June.V. !'mH..KPfANN[?
A. TASK I
Complete the engine cycle power balance, define the component
design requirements, establish optimum engine operating conditions, and
establish an engine cycle rating system. Document the heat transfer results.
B. TASK II
Complete documentation of the work accomplished in this task.
C. TASK Ill
Set up trajectory perfon_lance models for the most promising
engine cycle_, determine vehicle performance for tilevarious engine cycles,
and establish an engine cycle ranking based upon the mission payload results.
D. TASK IV
No scheduled activity.
1981014651-TSD11