fez n tabulation of j-2s thrust cha-yber component … · tjle 2 tjbulalt sui.1i. ry of j.2s ta....

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TABLE 1

TABULATION OF J-2S THRUST CHA-YBER COMPONENT TESTS, VTS- 1

Thrust Chamber Assy

No . Non- Tapoff

Test of Test Period Injector tap- Tap- Port

`Series Test Numbers Tests From To U/N U/N off off Geometry Objective

027 - 031 1 5-18-67 5-26-67 021 001 X NA Stand checkout

032 - 038 7 6-1-67 6-8-67 114 001 X NA Injector stability

1 039 - 012 4 6-12-67 6-14-67 109 002 X Curved Tapoff evaluatio n

0L3 - 0U 2 6-15-67 6-16-67 114 001-1 X NA Injector stability

0145 - 0148 4 6-16-67 6-20-67 109 002 X Curved Tapoff evaluation

- 162 5 8-9-67 8-15-67 109 002 X Curved Injector stabilityIn~ y

II 063 - U72 10 8-16-67 .,. 8-23-67 109 002 X Curved Tapoff evaluation

073 1 •---- 8-23-67 109 002 Curved Injector stability

080 - 083 4 9-21-67 9-25-67 017 001-2 X NA Inj . stability & delt a

0814 - 089 6 9-28-67 10-6-67 022B 001-3 X NA Inj . baffle H .T . study

III 090 - 09 7 8 10-12-67 10-30-67 106 003 X Curved Tapoff evaluation

098 - 099 2 1.0.31-67 10-31-67 106 003 X Curved Injector stability

100 - 103 4 11-6-67 11-8-67 017 001-4 K NA Injector stability

101x. - 1.10 7 y 11-111-67 11-117-67 109 004 X Radial Tapoff evaluation

001 - 005 5 2-14-68 2-20-68 106 0014-1 x Radial Stand checkout

IV 006 - 011 6 2-28-68 3-1-68 109 00,5 X Radial Tube wall thrus tchamber evaluation

012 - 019 8 3-8-68 3-13-68 601 005-1 X Radial Effect of F/C reduction& checkout of 601 inj .

00= Imo ; . Lrt6~- (7

TJLE 2

TJBULALt SUI.1i. RY OF j .2S TA. POFF Tr1RIj3`T' G i~lr'isrti C

VTS-l Iaainstage

Date Test Duration Thrust Cnaffibe r

1967 No . (seconds ) Thrust Chamber Injector Yerfom+arice

6/12 039 Prestage Solid Wall U/N 109 36 psia Fc, Inj . End

1;/N 002 .0311 Row 13 "O" Dim . 9`~R Fuel inj . Term .

Uncoated TOB O O Row 13 i1D" Dim , ° 1.61 lb/sec Wt((( 2 .0)3 Row 13 D/C Ratio 2 .15 U .rt .

17 .515 T /O Ring ID.316 "Gil Ga p

Coated 3137 T/0 Ring

t

ditt Inj Endsia Pc)256/13 01 0 5 . 3 ditto o ., ,p98°R Fuel Inj . Temp .1117 lb/sec Engine W.45 lb/sec Engine Wf

192 lb/sec Engine W.

! 3 .25 Engine M .R .

1

3 .45 Throat N .R .

6/13 0111 5 .3 ditto ditto 702 psia Pc, Inj . End102OR Fuel Inj . Temp .252 lb/sec Engine 9.68 lb/sec Engine Wf

320 lb/sec Engine Wt3 .71 Engine : .P .

{ 3 .99 Throat M .R .

6 1 042 0 .6 ditto ditto 890 psia Fe 9 Inj . End210OR Fuel In j . Temp .

;

°

I

3 °

8

CONFIDENTIAL LEVEL II -- UNDER PROTECTIVE ORDERUnited States District Court for th eCentral District of California , No . CV 971554

I I II IBNA08128644

H D M St00000789

Cvn 8123-200920 September 1966

TALE 2

LPOFF TF, dWST CH iii h COPN ONE" T VTS-1

. .._ . .._._..._..~ .

T apoff Duct

...,.__ ..._ -- ~,..~~.,.. .~,.. .-.~. .. . ..v, ..._.~..~. .. . .. .~.,R,,,.. ...,.._.-.a._

Thrust Chamber Gas F lowPerformance Performance Tast Objectives, Results, & Hardware Conditio n

°F T/0 T66 s Intended 5 sec test at 430 Pc andtOOb 'psia Pc, Inj . End em .4.b W '

ivesecheckout the hardware at simulated05 3 H to3b. Fuel inj . Tempo /sec5 .1 l t . . c..

i>1 lb/sec Wt .64 I°i .H tengine dome prime conditions .

,15 2 .51" Orifice Results : Test terminated by observer in presta-ewhen "Fuel Temp . OK" device failed to signalmair_stage because of a low fuel injection

temperature . Fuel leak 3600 around, noted atforward (upper) fuel manifold seal .

Hardware : Posttest torque check of the fuelmanifold bolts indicated the torque on 1/3 of thebolts had relaxed from, 125 to 80 ft-lbs . Random

~

mild discoloration marks on top of J-tubes and }II lower braze band in line with LOX posts . Heatstains in line with LOX posts at entrances to

8 tapoff ports .

25 psia Pc, Inj . End 912°F T/O Temp . i Objectives : Repeat test 039 .

3°R. Fuel Inj . Temp . 5 .3 lb/sec Wt Results : Programmed cutoff . Satisfactory test .

47 lb/sec Ent ine Wo .614 m .?, . Hardware : No change .

45 lb/sec Engine Wf 2 .51" Orifice

?2 lb/sec Engine Wt

.25 Engine M .R.

.45 Throat M.R .

)2 psia Pc, Inj . End 984°F T/O Temp . Objectives : Intended 5 sec hardware checkout test

)20R Fuel Inj . Temp . 8.7 lb/sec Wt ( at simulated engine transition point (697 psia P e

2 lb/sec Engine W .68 K.R . and 4.02 X.R .) ..

58 lb/sec Engine Wf 2 .51" Orifice Results : Programmed cutoff . Satisfactory test .

20 lb/sec Engine Wt Hardwares Mild erosion on left side of entrance ,

.714 Engine H .R . ~f port (previously heat stained) .to one + ~apo`~

.99 Throat M.R . ! +

90 psia Pc, Inj . End 1807°F T/O Tempi Objectives : Intended 5 sec tapoff evaluation tes t

10°R Fuel Inj . Temp . 11 lb/sec Wt at 180K (907 psia Pc and 5 .50 M .R .) .

2 .51" Orifice Results : Tapoff overtemp cutoff 4 msec after LCVreached full open position . Max temp at end of

start transient was 1910°aF . Max temp duringcutoff transient was 1960°F .Hardware : Mild to moderate erosion of 8 tapoffports. ue severe overheat streaks in chamber,Copper segment eroded moderately due to mismatc h

t with adjacent segment .$


I I II IBNA0812864 5

H D M St00000790

TABLE 2 (Continued)

VTS-1 NainstageDate Test Duration Thrust Chamber

1967 No . (seconds) Thrust Chamber Injector Performance

6/16 045 5 .2 ditto except ditto except tapoff psia Pe, Inj . End9021nine 0 .020 holes ring enlarged to ;

o205 OR Fuel Inj . Temp .

added into fuel 17 .747 ID 3118 lb/sec Engine Wo

passage below h22 "G" Gap 70 lb/sec Engine WfJ -tubes to 1118 lb/sec Engine Wtcompensate for 4.98 Engine N .R .the 9 J-tubes 5 .31 Throat M .H .apparentlyplugged

6/19 046 2 .1 ditto ditto except row 13 1150 psia Pc, Inj . Enc

LOX post "C" dim. 2111°R Fuel Inj . Temp .decreased to : 0®028" 155 lb/sec Engine W.Resultant dimensions 63 lb/sec Engine Wf

area 536 lb/sec Engine Wt

.028 Row 13 "C" Dim, 5 .50 Engine M .R .

I 1 .056 Row 13 "D" Dims 5 .91 Throat N .R .12 .0 Row 13 D/C Ratio

6/19 0217 5 .2 ditto ditto 1297 Asia Pc, Inj J . Enc218°R Fuel Inj . Temp .

517 lb/sec Engine Wo

91 lb/sec Engine Wf608 lb/sec Engine Wt5 .69 Engine M .H .

6 .15 Throat M .R .

6/20 0481

5 .3 ditto ditto 1283 psia Pc, Inj . En220OR Fuel. Inj . Temp .

510 lb/sec Engine W.90 lb/sec Engine Wf

600 lb/sec Engine Wt5 .611 Engine N .R .6 .12 Throat M .tt .


I I IIBNA08128646

IH D M St00000791

CDR 8123..200920 September 1968

TABLE 2 (Continued)

Tapoff DuctThrust Chamber Gas Flow

Performance Performance Test Objectives, Results,, & Hardware Condition

902 psia Pc, Inj . End 1096°F •T/O Temp . Objectives .* Repeat test 042 .205°R Fuel Inj . Temp . 9 .7 lb/sec Wt Results : Programmed cutoff . Satisfactory test .

-14 8 lb/sec Engine W° .7t M .R . Hardware : Mild to moderate erosion in line wit h

70 lb/sec Engine Wf 2 .51" Orifice I LOK posts at entrance to 5 additional tapoff ports .

118 lb/sec Engine Wt Tapoff ring surfaces discontinuous due to bendin g

1L .98 Engine N.R. and/or machining of tapoff ring . Leading edge of5 .31 Throat N .H . lower chamber copper segment eroded and washe d

over . Wall pressure tap GG3B eroded .

1150 psia Pc, Inj . End 882°F T/O Temp . Objectives : Intended 5 sec tapoff evaluation tes t

2lL°R Fuel Inj . Temp . 10 .5 lb/sec Wt at 230K (1133 psia Pc and 5 . 5455 lb/see Engine W. .62 M .R . Results : Premature cutoff after 2 .1 seconds

83 lb/sec Engine Wf 1 .95" Orifice mainstage due to fuel depletion . Satisfactory

538 lb/sec Engine Wt test .

5 .50 Engine M .R . Hardware : No change except for slight increase in

5 .91 Throat N .H . erosion of lower copper segment and CG3B tap .

1297 Asia Pc, Inj . End 8i.;2°F T/0 Temp . Objectives .- Intended 5 sec tapoff evaluation tes t---- -218°R Fuel Inj . Temp . 12 .1 lb/sec Wt ~',5K 1326 psia Pc ) and 5 .50 I .R .at 26

517 lb/sec Engine W° .60 N .R . Results : Prograrm.ed cutoff . Satisfactory test .

91 lb/sec Engine Wf 1 .95" Orifice Small fuel leak around the forward side of th e

608 lb/sec Engine Wt fuel inlet manifold was evident during the test .

5 .69 Engine N .R .6 .15 Throat M .R .

1263 psis Pc, Inj . End 8760F T O Temp . Obje c tives : Stability rate injector with 50-grain

220°R Fuel Inj . Temp . 12 .6 lb/sec Wt S thermally detonated bomb at 265K (1275 ps-Ja Pc )510 lb/sec Engine W° .62 M .P . and 5 .5 M .R .

I90 lb/sec Engine Wf 1 .95" Orifice Results : Programmed cutoff . Satisfactory test600 lb/sec Engine Wt except that the bomb caused only an insignifican t

5 .64 Engine M .N . disturbance In the accelerometer traces and cannot

6 .12 Throat M .R . be considered a satisfactory stability rating test . £1

Ye_~ - - -- - - -

,Hardware : No change in hardware condition .

59


I I II ftBNA08128647

H D M St00000792

TABLE 2 (Continued)

Date1967

VTS-;.TestNo .

HainstageDuration(seconds) Thrust Chamber Injector

Thrust ChamberPerformance

..~

8/9 058 Ignition Solid Wall U/N 109

---

U/N 002 .029 Row 13 '°C" Dim .Uncoated TOB .052 Row 13 "D" Dim.

1 .8 Row 13 D/C Ratio

17 .633 T/0 Ring ID

.368 "G O' GapCoated 718 T/0 Ring

8/10 059 Ignition ditto ditto - - -

8/10 060 11.9 ditto ditto 430 psia Pc, Inj . Enc64oR Fuel Inj . Temp .138 lb/sec Inj . W.

46 -Lb/sec Inj . :W1186 lb/sec Inj . Wt

2 .89 Injector M .R .

2 .66 Engine M.R .2 .87 Throat M .R .

i

1

t

E

««{


I I IIBNA08128648

H D M St00000793

CDR 8123-200920 September 1968

TABLE 2 (Continued)


Performance Performance Test Objectives, Results, .Hardware Condition

Objectives .- Intended 5 sec test tostabiliE-y rateinjector at simulated engine dome prime conditio n(1430 psia Pc), first with a 50-grain thermallydetonated bomb and then by decreasing fuelinjection ter.mp .Results : Premature cutoff . Test terminated byVSC 736-msec after ignition .Hardware : Not inspected (due to LOX flo=ametercalibrations) .

- - - - Objectives : Repeat test 058 except stand duration .

Results : Chart observer cutoff . Fuel flowmetertemp exceeded redline value (erroneous) .

Problem was traced to a faulty fuel temp . bulb .

Hardware : No change .

30 Asia Pc, Inj . End 202°F T/0 Temp . Objectives : Repeat test 059 .o4°R Fuel Inj . Temp . 5 .2 lb/sec Wt Results : VSC cutoff . No evidence of bomb

.38 lb/sec Inj . W° .24 M.R . detonation on oscillosgraphs or high speed

)8 lb/sec Inj . Wf 1 .95" Orifice recorders . Self-induced combustion instability

.86 lb/see Inj . Wt occurred at 61.7°R fuel injection temp . The test

! .89 Injector M.R. records "indicate that at beginning of mainstage ,.66 Engine M.R. fuel injection temp cycled twice at about 1 cp s

, .87 Throat M .R . and then began a steady decay until self-induced 11instability was triggered at 61 .7oR. The tapoffgas temperature in the manifold and duct reflecte dthis behavior and after a couple of cycles, th etapoff gas temperature decayed steadily from avalue of about 675°F until at the onset ofinstability it was 200°F (a change of 15° intapoff temperature resulted from each 1 0 charge infuel injection temp) . Chamber pressure prior tothe instability was fairly constant (120 to 43 0psia) . At the onset of instability, the gastemperature in the tapoff manifold went from 200° Fto 1675°F, the gas temperature in the duct severa lfeet downstream went from 200°F to 1525°' and themetal surface temperatures at the tapoff por tentrances exceeded 2200°F .Hardware : Injector face burned and mildly erode dfrom center to row 2 similar to U/N 024, test 031 .ASI weld and row 2 fuel cups eroded . Face slightlybuckled. 18 tapoff ports overheated on left sideof entrance and 5 on right side .


I I IIBNA08128649

HDMSt00000794

TABLE 2 (Continued)

VT 35-1 haInstageDate Test Duration Thrust Chamber

1967 No . (seconds) Thrust Chamber Injector Performance

8/10 061 5 .li ditto ditto 1120 psia Pc, Inj . End

8/15 062 15 .3 ditto ditto 300 psia Pc, Inj . End87°R Fuel Inj . Term .92 lb/sec Inj . W.36 lb/sec Inj . Wf128 lb/sec Inj . Wt2.52 Injector M .R.2 .32 Engine M .R .2 .87 Throat M .R .

8/16 063 5.0 ditto ditto 913 psia Pc, Inj . End203°R Fuel Inj . Temp .340 lb sec Inj . Wp65 lb/sec Inj . Wf

405 lb/sec Inj . Wtf s 5.21 Injector M.R.

4.81 Engine N .R .1 i 5.16 Throat M .R .

8/16 064 Prestage ditto ditto 482 psia Pc, Inj . End

4fff


I I I IIBNA08128650

H D M St00000795


TABLE 2 (Continued)

Tapoff Duc tThrust Chamber Gas Flow

Performance Performance Test Objectives, Results, & Hardware Condition

420 psia Pc, Inj . End - - - Objectives : Intended 5 sec test to stability rateinjector at simulated engine done prime condition(L30 psia Pc and 3 .05 M .R.) with a 50-grainthermally detonated bomb .

; Results : Programmed cutoff . Cork bomb in cente rdid not go off although ROFI stud at row 6 burne daway. Hydrogen fuel system cycled during the testcausing fluctuations in chamber pressure andmixture ratio .Hardware : No change .

300 psia Pc, Inj . End 160°F T/O Temp . Objectives : Intended stand duration at 300 psia P c37°R Fuel Inj . Temp . 1 .95" Orifice and 2 .3 mixture ratio to stability rate injector?2 1b/sec Inj . Wo with a 50-grain thermally detonated bomb mounte d36 lb/sec Inj . Wf in the center position ..28 lb/sec Inj . Wt Results : Programmed cutoff . Bomb detonated after?.52 Injector M.R. 1 .97 seconds of mainstage (10 .56 seconds Beckman?.32 Engine N .R. time) .? .87 Throat M.R . Hardware : J-tubes in three small areas of film

coolant ring and several areas of chamber weredented by nylon bomb fragments . Also removedfiberglass which was found to be plugging som eJ -tubes .

~l3 psia Pc, Inj . End 872°x' T O Temp . 1/s

..~.,...,. .~.... .,- .r ..-~. ...~.~ .. ...~. ._.~., ..Ob jectives : Intended 5 sec tapoff evaluation test

?03°R Fuel Inj . Temp . ec Wt8.9 lb at 160K 5-0 psia Pc) .4110 lb/sec Inj . W° .6l M .R . Results : Programmed cutoff . Satisfactory test .65 lb/sec Inj . Wf 1.95" Orifice l Hardware : No damage except for two mild tapoff port105 lb/sec Inj . Wt entrance erosions (one between injector elements p;.21 Injector M.R. 31-32 and one at injector element t7 .a .81 Engine I .R .ss" .16 Throat M .R .

182 psia Pc, Inj . End 210°F T/O Temp . Objectives : Intended 5 see tapoff evaluation test- - - - - - at 230K (1070 psia Pc) .

Results : Premature cutoff. Chart observer cutoffat beginning of pre stage ; fuel flowmeter tempexceeded redline value .Hardware : No change .

61


I I II ABNA0812865 1

H D M St00000796

TABLE 2 (Continued)

Date1967

VTS-1TestNo .

MainstageDuration(seconds) Thrust Chamber Injector

Thrust ChamberPerformance

8/17 065 5 .1 ditto ditto 11514 psia Pc, Inj . Er218°R Fuel Inj . Temp ,

j j 150 lb /sec Inj . Wo76 lb/sec Inj . Wf

526 lb/sec Inj . Wt5.92 Injector M .R .

5 .47 Err-: ne M .R .5 .90 Throat

8/21 066 5 .3 ditto ditto 1298 psia Pc, Inj . Er220°R Fuel Inj . Temp .1490 lb/sec Inj, Wo86 lb/sec Inj . Wf

576 lb/sec Inj . Wt5.73 Injector M .R.5 .29 Engine M .R .

5 .71 Throat M.R .

@ 8/21 067 8 .1 ditto ditto 1161 psia Pc, Inj . Er218°R Fuel Inj . Temp ,410 lb/sec Inj . Wo90 lb/sec Inj . Wf

500 lb/sec Inj . Wt14 .56 Injector M .R .14 .21 Engine M .R .14.50 Throat M .R.

8/22 068 10 .1 ditto ditto 11414 Asia Pc, Inj . Er218°R Fuel Inj . Temp .116 lb/sec Inj . W.82 lb/sec Inj . Wf

1498 lb/sec Inj . Wt5 .07 Injector M .R.4.68 Engine M.R .5.03 Throat M.R .

62


I I IIBNA08128652

H D M St00000797

TABLE 2 (Continued)

Tapoff DuctGas Flow

Perforr,ance

1154 psia Pc, Inj . End 923°r T/0 Temp .218°R Fuel Inj . Temp. 11.1 lb/sec Wt150 lb/see Inj . Wo .64 N .H .76 lb/sec Inj . Wf 1.95" Orifice

526 lb/sec Inj . Wt5 .92 Injector M .R .

5 .147 Engine N .H .5 .90 Throat M .R .

1298 psia Pc, Inj . End 898°F T/O Temp .220°R Fuel Inj . Temp . 12 .5 lb/sec Wt1490 lb/sec Inj . W° .62 M.R .86 lb/sec Inj . Wf 1.95" Orifice

576 lb/sec Inj . Wt5.73 Injector M .R.5 .29 Engine M .R .

5 .71 Throat M.R .

1161 psia Pc, Inj . End l 830°F T/0 Temp .218°R Fuel Inj . Tern . 11.2 lb /sec Wt1410 lb/sec Inj . Wo .59 M .R .90 lb/sec Inj . W f 11.95" Orifice

500 lb/sec Inj . Wt14 .56 Injector M .R .4 .21 Engine M .R .4.50 Throat M.R.

11414 psia Pc, Inj . End 867°F T/O Temp .218°R Fuel Inj . Temp . 11.2 lb/sec W.416 lb/sec Inj . Wo .61 M .R .82 lb/sec Inj . Wf 1.95" Orifice

498 lb/sec Inj . Wt

5.07 Injector M .R .4.68 Engine M .R.5 .03 Throat M.R .

CDR 8123-200920 September 196 8

Objectives : Repeat test 064 .Results : Programmed cutoff . Satisfactory test .Hardware : No change except for minor erosion andoverheating at entrance to several additionaltapoff ports (16) in line with injector element s

1, 84, 82-83, 88, 67, 60, 58, 52, 51-50, 49, 146-147,145, 32-31, 28, 15-114 , and 13-14.

Objectives : Intended 5 sec tapoff evaluation testat 26 1290 psia Pc and 5 .5 N .R .) .Results : Programmed cutoff . Satisfactory test .Hardware : No change in hardware condition .

Objectives : Intended 6 sec tapoff evaluation testat 2308 1130 psia Pc and 14 .140 M .R .) .Results : Programmed cutoff . Satisfactory test .Hardware : No change in hardware condition ,

Objectives : Intended 10 sec tapoff evaluation testat 230x , 5 .0 N, R . and 220°R fuel inj . temp .Results : Progra m ed cutoff . Satisfactory test .Har dware : No change in hardware condition ,


I I I IBNA08128653

IH D M St00000798

TABLE 2 (Continued)

V TS-1 MainstageDate Test Duration Thrust Charnber1967 No . (seconds ) Thrust Chamber Injector Performance

3/22 069 10 .2 ditto ditto 1148 psia Pc, Inj . En191°R Fuel Inj . Temp.4436 lb/sec Inj . We75 lb/sec Inj . Wf

511 lb/sec Inj . Wt5 .78 Injector M .R .5 .34 Engine M.R .5 .80 Throat M.R .

6/22 070 8 .1 ditto ditto 1160 psia Pc, Inj . En255°R Fuel Inj . Temp .

1.110 lb/sec Inj . We77 lb/sec Inj . 14f

517 lb/sec Inj . Wt

5.70 Injector M .R .5 .26 Engine M .R.5 .66 Throat N.R .

8/22 071 12.2 ditto ditto 91.1 psia Pc, Inj . End222°R Fuel Inj . Temp .3118 lb/sec Inj . Wo60 lb/sec Inj . Wf

408 lb/sec Inj . Wt5 .84 Injector N .R .5 .39 Engine M.R .5.81 Throat M .R .

8/23 072 7 .9 ditto ditto except "C" dim . 1288 psia Pc, Inj . Enof 45 of the 85 row 13 219°R Fuel Inj . Temp .elements increased 486 lb/sec Inj . W°.005" resulting in an 85 lb/sec Inj . Wfaverage "C" for the 45 571 lb/sec Inj . Wtelements of 0 .033" . 5 .73 Injector M.R .The average increase 5 .29 Engine N .R .in "C" for all 85 1 5 .69 Throat M.R .posts was 0 .0025" .


I I II IBNA08128654

H D M St00000799


TABLE 2 (Continued)


Performance Performance Test Objectives' Results, & Hardware Condition

1148 psis Pc, Inj . End 803°F T/O Tem . Objectives : Intended 10 sec tapoff evaluation at191°R Fuel Inj . Temp . 11 .3 lb/sec Wt 230K, . M .R. and 180°R fuel inj . temp .436 lb/sec Inj . Wo .57 M .R . Results : Programmed cutoff . Satisfactory although75 lb/sec Inj . W f 1 .95" Orifice a one second burst of fire occurred just below

511 lb/sec Inj . Wt fuel inlet manifold at start of mainstage .5 .78 Injector M .H. Hardware : No change in hardware condition .5.34 Engine K .R .5 .80 Throat M.R .

1160 psia Pc , Inj . End 965°F T/0 Temp . Objectives : Intended 8 see tapoff evaluation test255°R Fuel Inj . Temp . 11 .1 lb/sec Wt at 230K_, .5 M.R. and 260°R fuel inj . temp .440 lb/sec Inj . Wo .66 M . R. Results : Programmed cutoff . Satisfactory test .77 lb/sec Inj . W f 1 .95" Orifice Hardware : No change in hardware condition .

517 lb/sec Inj . Wt5 .70 Injector M.R.5 .26 Engine M .R .5.66 Throat M.R .

911 psia Pc, Inj . End 928°F T/O Terip . Objectives : Intended 12 sec tapoff evaluation tes t222°R Fuel Inj . Temp . 8 .8 lb/sec Wt at 180K, .5 I.A .A. and 220°R fuel inj . temp .3I8 lb/sec Inj . Wo .67 M.R . Results : Prog_ramrr d cutoff . Satisfactory test ,60 lb/sec Inj . Wf 1.95" Orifice Hardware : No change in hardware condition excep t408 lb/sec Inj . Wt for one mild and one deep ( 1/6") erosion in throat ,5.81 Injector N .H .

.respectively, in line with injector elements

5.39 Engine M.R . 8L and 81 .5.81 Throat N.R .

L288 psia Pc, Inj . End 969°F T/O Temp . Objectives : Intended 8 sec tapoff evaluation a t219°R Fuel Inj . Temp . 12 .4 lb/sec Wt 265K, 5 .5 M.R. and 220°R fuel inj . temp .486 lb/sec Inj . Wo .67 M.R . Results : Programmed cutoff . Satisfactory test .85 lb/sec Inj . Wf 1 .95" Orifice Hardware : No change in hardware condition excep t571 lb/sec Inj . Wt the 17611 deep throat erosion is now 0 .163" deep .5 .73 Injector M.R .

5 .29 Engine N.R .5 .69 Throat M.R .

63


I I IIBNA08128655

IH D M St00000800

fez n tabulation of j-2s thrust cha-yber component … · tjle 2 tjbulalt sui.1i. ry of j.2s ta....

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