Restriction/Classification Cancelled

Restriction/Classification Cancelled

https://ntrs.nasa.gov/search.jsp?R=20090021720 2018-05-07T12:21:39+00:00Z

NACA RM SE54H18

!Jate/- -

NATIONAL ADVISORY COMMITTEE FOR A'ROANUTICS

RESEARCH MEMORANDUM

f o r the

A i r Research and Development Command, U.S. A i r Force

PRELIMINARY ALTITUDE PERFORMANCE DATA FOR THE J65-B3 TURBOJET

ENGINE AT REYNOLDS llUiYf3E.R INDICES FROM 0.2 TO 0.8

By W. M. Braithwaite and W. K. Greathouse

SUMMARY

Altitude performance character is t ics of the J65-B3 turbojet engine and i t s components were obtained a t engine-inlet conditions correspond- ing t o Reynolds number indices from 0.2 t o 0.8 over a range of corrected engine speeds from 70 t o 110 percent of rated speed. Engine operation- a l l imi ts up t o an a l t i t ude of 75,000 f e e t together with ignition and windmilling character is t ics were a l so obtained. The engine and component data are presented both i n graphical and i n tabulated form. The opera- t iona l character is t ics are presented i n graphical form.

A t the request of the A i r Research and Development Command, U.S. A i r Force, an experimental investigation of performance of the J65-B3 turbojet engine was made i n an NACA Lewis a l t i tude chamber. Preliminary r e su l t s of t h i s investigation are presented herein fo r a range of engine- i n l e t conditions corresponding t o Reynolds number indices from 0.2 t o 0.8 and corrected engine speeds from 5800 (70 percent rated) t o 9200 (110 percent rated) rpm. Engine operational l imi ts and igni t ion and windmilling character is t ics are also presented. Over-all engine and component perfor- mance are shown, i n terms of conventional parameters for the various Reynolds number indices, as plot ted curves and also in tabulated form. Engine operational l i m i t s between 60,000 and 75,000 fee t a l t i t ude were obtained by u t i l i z ing a no-flow ejector at the exhaust-nozzle ex i t . A fixed engine exhaust-nozzle area of 1.969 square f e e t was used throughout the investigation.

NACA RM SE54H18

APPARATUS

Engine

The J65-B3 axial-flow turbojet engine (fig. 1) has a rated thrust of 7220 pounds at standard sea-level static operation at an engine speAed of 8300 rpm and a limiting turbine-discharge temperature of ~ 1 6 6 ~ F (1626' R). For this investigation, the fixed exhaust nozzle was sized to an area of 1.969 square feet which gave limiting turbine-discharge temperature (1166' F) at 8300 rpm for 100' F inlet-air temperature at sea-level static operation.

Instrumentation

Location of instrumentation stations throughout the engine and the amount of instrumentation at each station are shown in the diagram and table in figure 2. Engine fuel was measured by rotome'cers and engine thrust was measured with a null-type thrust cell.

PROCEDURE

Performance data were obtained at Reynolds number indices from 0.2 to 0.8 and corrected engine speeds from 5808 to 9200 rpm. At each Rey- nolds index, the maximum engine-inlet ram-pressure ratio available from the test facility was maintained while engine speed was varied from rated engine speed down to the engine speed at which the exhaust nozzle "unchoked," Engine operational limits were determined over a range of altitudes at a Mach number of 0.8. Determination of operational charac- teristics between altitudes of 60,000 and 75,000 feet was made possible by utilizing a no-flow ejector to reduce the static pressure surrounding the exhaust nozzle. Fuel flows less than that corresponding to the J65- B3 throttle setting of "idle" were obtained by use of a separate "modi- fied" fuel control. MIL-5-5624A, grade JP-4 fuel was used throughout the investigation.

PRESENTATION OF RESULTS

The experimental data are grouped according to the index presented in table I. Over-all engine performance is shown in figure 3 and com- ponent performance is shown in figures 4 to 7.

The performance of the engine was measured.and presented in a man- ner similar to that reported in'reference 1. Therefore, within the range of Reynolds number indices covered, engine performance may be de- termined from the curves presented for any flight condition at which the

CONFIDENTIAL

RACA RM SE54H18 . CONFIDENTIAL 3

engine exhaust nozzle 1s choked. In order to calculate the Jet thrust for the engine at a particular flight condition from figure 3(e), the exhaust-nozzle pressure-drop parameter must be determined by usingfig- ures 3(c) and (d). Subtracting the inlet momentum term from this jet thrust will give the net thrust. The corrected net thrust and specific fuel consumption at a flight Mach number of 0-8 are presented in figures 3ff) and 3(g) for a range of altitude corresponding to the range of Reynolds number indices investigated.

The data of figure 8 are presented to show the difference between the exhaust-gas temperature as measured by the 4 thermocouples on the manufacturer's thermocouple harness at the turbine outlet and the aver- age temperature as measured by 30 thermocouples installed at the exhaust- nozzle inlet. The oil-mist-overboard air flow and turbine-flange cooling air flow are shown in figure 9.

The operational range of the engine is presented in figure 10 for a flight Mach number of 0.80 and superimposed on the range is the wind- milling speed and the manufacturer's throttle idle position setting. Windmilling and ignition characteristics are presented in figures 11 and 12. The procedure followed in determining the ignition characteristics was prescribed by the manufacturer. All ignitions presented on the fig- ure were therefore obtained in the 20-second time interval which is in- corporated into the ignition system.

The corrected engine speed at which the exhaust-nozzle chokes is presented in figure 13 and the data reported herein represent the per- formance of the engine only in the region where the exhaust nozzle is choked. The relation between Reynolds number index and flight conditions is shown in figure 14. A complete tabulation of the performance data is presented in table I1 and the symbols used in the various parameters are defined in the appendix.

Lewis Flight Propulsion Laboratory National Advisory Committee for Aeronautics

Cleveland, Ohio, August 23, 1954

CONFIDENTIAL NACA RM SE54H18

APPENDIX A

SYMBOLS

The following symbols are used in this report:

jet thrust, lb

net thrust, lb

Mach number

engine speed, rpm

total pressure, lb/sq ft

static pressure, lb/sq ft

total temperature, %

static temperature, OR

velocity, f t/sec

air flow, lb/sec

fuel flow, lb/sec

W63 gas flow, lb/sec

oil mist overboard air flow, lb/sec

Wtf turbine flange cooling air flow, lb/sec

Y ratio of specific heats of gas

S ratio of absolute total pressure to absolute static pressure of NACA standard atmosphere at sea level

q efficiency

8 ratio of absolute total temperature to absolute static tem- perature of NACA standard atmosphere at sea level

cP ratio of absolute viscosity of air to absolute viscosity of air of standard NACA atmosphere at sea level

6

9 3 Reynolds number index

CONFIDENTIAL

NACA RM SE54H18 + CONFIDENTIAL

Subscripts:

b combustor

c compressor

e engine

t turbine

0 altitude test condition

1 compressor inlet

3 compressor discharge

4 turbine inlet

5 turbine discharge

6 manufacturer's temperature measuring station

9 exhaust-nozzle inlet

REFERENCE

1. Walker, Curtis L., Braithwaite, Willis Ma, and Fenn, Daniel B.: Com- ponent and Over-All Performance Evaluation of a J47-GE-25 Turbojet Engine over a Range of Engine-Inlet Reynolds Number Indicies. NACA RM E52L16, 1953.

CONFIDENTIAL

* CONFIDENTIAL NACA RM SE54H18

TABLE I, - FIGURE INDEX Figure

1 2

Dependent variable Independent variable

Over-all Engine Performance

Engine installation Sectional view of J65-B3 turbojet engine

Corrected engine speed Corrected engine speed Corrected engine speed

Engine total-temperature ratio

Exhaust-nozzle pressure- drop parameter

Corrected eogine speed Corrected engine speed

3(a) 3(b) 3(c)

3(d)

3(e)

3(f) 3(g)

Corrected engine air flow Corrected fuel flow Corrected exhaust-gas total temperature

Engine total-pressure ratio

Jet thrust

Corrected net thrust Corrected specific fuel consumption

Component Performance

Corrected engine speed Combustion parameter and corrected engine speed

Corrected engine speed Corrected engine speed

4 5

6 7

Compressor performance Combustor performance

Turbine performance Tail-pipe total- pressure loss

Operational Characteristics

Nozzle-inlet total temperature

Engine-inlet air flow

Acutal engine speed Corrected flight velocity

Mach number

8

9

10 ll

12

Manufacturer's 4 thermo- couple temperature average

Oil mist and turbine cooling air flow

Altitude ( operational) Ratio of windmilling engine speed to rated speed

Altitude (ignition)

13

14

Exhaust-nozzle choked-flow range

Relation between Reynolds number index and flight condition.

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Table 11. - Concluded. Cal ibrat ion of J65-B3 Turbojet Engine.

Turbine

Total preaeure,

lb/s?ft abs

1517 1813 2106 2294 2530

2883 3119 3486 3949 3954

1164 1405 1643 1868 2116

2336 2518 2734 2913 2934

1401 1679 1946 2196 2171

2167 2339 2499 2616 2754

2789 1141 1200 1298 1394

1530 1532 1607 1770 1839

1890 926 1028 1032 1112

1199 1313 1500 1475 1606

1795 756 899 984 1010

1095 1279 1274 580 585

636 700 789 829 865

Turbine

Total pressure,

lb/s2ft abs

4204 5078 5928 6473 7119

8119 8793 9839 11093 11055

3237 3940 4620 5259 5960

6610 7110 7666 8144 8227

3919 4727 5477 6102 6118

6169 6544 1072 7390 7724

7800 3131 3359 3655 3941

4365 4309 4557 4966 5147

5278 2540 2894 2944 3191

3422 3695 4290 4201 4542

5004 2037 2592 2772 2913

3104 3591 3592 1655 1662

1818 1987 2222 2347 2457

Inlet total

temperature,

534 534 534 534 535

535 534 534 533 531

531 532 531 532 532

532 533 533 530 533

463 466 461 461 461

464 460 461 463 463

459 461 465 464 467

466 459 463 464 464

464 406 404 402 403

404 406 429 412 428

416 419 412 416 420

423 421 416 416 419

413 413 413 413 414

outlet

Static pressure, P 3

lb/aq5ft gbs

1364 1621 1885 2091 2291

2623 2830 3174 3606 3616

1045 1258 1470 1688 1918

2120 2290 2496 2664 2680

1263 1522 1767 1966 1966

2005 2135 2283 2393 2523

2553 1041 1093 1183 1265

1396 1401 1471 1623 1686

1733 838 933 937 1013

1093 1205 1369 1343 1466

1645 664 813 896 920

1001 1166 1165 527 529

579 642 722 759 791

Compressor

pressure,

lb/s?it abs

4426 5301 6198 6763 7441

8469 9155 10234 11521 11507

3397 4111 4828 5494 6221

6879 7399 7974 8458 8541

4107 4950 5721 6349 6373

6451 6813 7347 7661 7999

8071 3265 3504 3806 4104

4535 4483 4736 5169 5328

5462 2647 3010 3066 3322

3566 3843 4461 4354 4708

5170 2121 2694 2880 3039

3217 3720 3718 1720 1729

1890 2068 2304 2431 2540

inlet

Total temperature,

:it

970 1111 1229 1321 1414

1567 1665 1826 2001 2000

1005 1145 1289 1414 1565

1680 1774 1903 1997 2019

1143 1315 1469 1591 1596

1619 1692 1795 1875 1953

---- 1321 1412 1491 1569

1693 1679 1759 1667 1964

2019 1150 1242 1260 1345

1424 1516 1708 1660 1809

2016 1214 1419 1491 1574

1652 1889 1917 1444 1452

1534 1635 1798 1937 2007

Altitude static pressure,

lb/sFft sba

803 800 795 805 800

805 793 804 790 789

596 603 595 590 597

606 602 598 600 597

491 502 497 507 496

494 489 500 500 498

490 626 604 609 615

607 594 606 623 616

598 515 509 501 498

500 495 541 630 542

523 372 377 380 385

377 378 371 176 147

154 150 145 151 144

Run

2 3 4 5

6 7 8 9 10

11 12 13 14 15

16 17 18 19 2C

21 22 23 24 25

26 27 28 29 30

31 32 33 34 35

36 37 38 39 40

41 42 43 44 45

46 47 48 49 5C

51 52 53 54 55

56 57 58 59 60

61 62 63 64 65

Nozzle

Total temperature,

760 869 961 1039 1114

1241 1323 1457 1605 1604

786 898 1012 1115 1239

1334 1415 1522 1607 1624

895 1035 1163 1259 1264

1286 1346 1430 1498 1564

1593 1048 1120 1188 1246

1350 1338 1404 1514 1578

1626 905 979 990 1059

1132 1200 1364 1319 1444

1619 954 1122 1181 1251

1316 1512 1539 1144 1155

1218 1309 1446 1561 1622

outlet

Total temperature,

zz' 745 779 808 827 849

883 906 943 976 976

751 784 817 846 881

906 929 956 972 979

715 757 767 819 820

826 840 866 885 902

905 745 772 791 815

842 833 655 885 901

913 656 680 682 703

725 746 808 785 835

873 687 728 748 771

790 844 843 735 736

752 775 809 839 857

inlet

Total pressure

lb/s2it abe

1461 1744 2021 2210 2440

2805 3042 3399 3835 3849

1120 1351 1583 1809 2059

2276 2457 2667 2829 2851

1349 1630 1898 2110 2110

2144 2282 2434 2548 2681

2713 1111 1170 1269 1356

1494 1496 1569 1726 1793

1842 894 998 1003 1082

1169 1282 1463 1433 1563

1746 711 874 959 9a4

1069 1243 1240 563 567

619 683 770 809 841

Fuel

v. Ib,s

584 991 1421 1725 2102

2770 3253 4138 5230 5259

504 824 1208 1591 2115

2495 2904 3425 3920 3960

959 1420 1926 2335 2341

2411 2686 3100 3410 3746

3872 98C 1132 1310 1488

1802 1784 1959 2335 2511

2670 725 907 938 1093

1285 1454 1862 1766 2064

2686 588 934 1050 1191

1310 1755 1790 607 612

720

Inlet ~eynolds number index,

6 - *-@

1 0 . 7 9 8 .I97 .800 ,797 .795

0.800 ,799 .796 ,802 ,798

C.599 .594 .598 .595 .595

0.596 ,592 ,591 .597 .595

C.596 .597 ,598 .592 .598

C.597 .597 .598 .591 .594

0.593 .400 '.397 .399 .397

0.399 .402 ,400 .400 .407

C.412 .400 .4C2 .401 .395

C.397 .395 ,396 .401 .390

C.395 .3GO .304 301 .299

C.293 .301 .298 .I954 ,1935

0.1974 ,2013 ,1987 .I943 .I985

Manufact- Engine Oil w b l n a Inlet total pressure,

4, lb/aq it abs

1751 1748 1755 1749 1747

1759 1753 1746 1755 1738

1304 1298 1303 1300 1299

1301 1296 1293 1298 1302

1066 1098 1084 1C73 1084

1091 1079 1C84 1C77 1083

1066 734 727 730 732

734 724 729 731 730

730 612 612 606 599

604 604 637 626 641

624 475

' 475 476 479

474 483 472 309 309

309 315 311 304 312

lb%C

0.76 .89

1.01 1.09 1.19

1.33 1.42 1.56 1.71 1.65

0.59 .69 .78 .89 .97

1.06 1.13 1.20 1.26 1.27

0.72 .84 .95

1.03 1.04

1.05 1.10 1.16 1.20 1.24

1.24 0.55 .58 .63 .67

0.72 .72 .75 .81 .82

0.84 .49 .54 .55 .58

C.62 .66 .73 .72 .76

0.81 .38 .46 .49 .51

0.53 .60 .59 .30 .30

0.32

::::;:- o$&d couple

3, 762 865 967 1034 1066

1186 1283 1428 1558 1590

783 893 1007 1103 1180

1288 1383 1490 1590 1599

889 1011 1140 1233 1241

1258 1328 1420 1479 1543

1568 1034 1094 1159 1211

132C 1309 1379 1490 1529

1573 895 963 975 1-5

1117 1183 1335 1288 1404

1623 933 1095 1152 1220

1283 1470 1511 1111 1119

1190

1599

flow, 'a 1 1b)s;c

53.54 60.35 66.18 69.64 73.99

80.71 84.69 89.62 97.28 96.45

40.28 46.82 50.71 55.49 59.25

63.32 66.04 68.67 71.31 71.72

46.53 51.71 57.04 60.34 60.95

61.02 63.41 65.51 67.44 68.83

68.82 33.95 35.44 37.60 39.41

4155 41.59 42.90 44.97 45.66

46.15 30.16 32.54 32.80 34.61

36.01 37.42 40.27 40.95 41.49

42.91 22.97 26.80 27.65 29.11

29.12 32.40 31.44 16.65 16.93

17.39

21.14

ilopr, 'om

lb/eec

0.84 0.92 1.00 1.04 1.09

1.16 1.16 1.26 1.33 1.32

0.63 .69 .75 .79 .84

0.86 0.91 0.64 1.04 1.01

0.68 .75 .80 .80 .81

0.83 .84 .86 .86 .86

0.84 .50 .49 .51 .51

0.55 .54 .54 .57 .56

0.54 .40 .44 .43 .45

0.46 .47 .55 .48 .48

0.53 .29 .35 .36 .36

0.37 .36 .40 .21 .21

0.23

3.0

2.8

2.6

2.4

2.2

2 .o

1.8

1.6

1.4

1.2

1;o

2 Engine total-temperature ratio, T 9 /T 1 (d) Engine pumping characteristics.

Figure 3, - Over-all engine performance for several values of Reynolds number indices.

C m I m u L

Exhaust-nozzle pressure-drop parameter, 1.26 P9 - po (e) Jet thrust.

Figure 3. - Over-all engine performance for several values of Reynolds number indices.

1.6

1.5

1.4

1.3

1.2

I I ' * '$400 6800 7200 7600 I I 8000 I I 8400 I I 8800 I I 9200 I I 9600 I Corrected exigine speed, ~/a, rprn

(g) Specific f u e l consumption f o r f l i g h t Mach number of 0.8.

Figure 3. - Over-all engine performance f o r several values of Reynolds number indices.

., 0

.rl +,

k

E ra (I) a,

! 4

+-'

+-'

k

10 (I) Q

& B U

Figure 4. - Variation of compressor performance with corrected engine speed f o r several values of Reynolds number indices.

3u5600 6000 6400 6800 7200 7600 8000 8400 8800 9200 Corrected engine speed, N/*, .rmp

Figure 6. - Variation of turbine performance with corrected engine speed f o r severa l values of Reynolds number indices.

Figure 7. - Variation of tail-pipe total-pressure loss with corrected engine speed for several values of Reynolds number indices. 1

Figure 8. - Variation of manufacturer's four thermocouple temperature average at station 6 with NACA 30 thermocouple temperature average at station 9.

CONFIDENTIAL

Figure 10. - Effect of altitude on engine operational characteristics at flight Mach number of 0.80.

CONFIDENTIAL

0 400 800 1200 1600 Corrected f l i g h t velocity, vO/f i , f t / sec

Figure 11. - Effect of f l i g h t velocity on windmilling speed fo r several values of Reynolds number indices,

0 .2 .4 .6 .8 Flight Mach number, Mg

Figure 12. - Effect of altitude and Mach number on engine ignition characteristics.

Flight Mach number, % %! Figure 13. - Minimum corrected engine speeds at which critical flow existed in exhaust e

nozzle.

Reynolds number tndex,

0 0.2

8000 a PI k

Exhaust nozzle choked

0 .3 q 0 .4 A .6

\ 7000 A .8

3

3 - 0 .87 a 8 5 3 E Exhaust nozzle

d .rl

7' 6000 Q)

a Q) -P U 0, k k 0 U

5000 .2 .4 .6 .8 1 .O 1.2 1.4

unchoked -pp---p--A----

Figure 14. - Reynolds number index as a function of a l t i tude and Mach number aasuming 100 percent ram-pressure recovery.

NACA RM SE54H18 CONFIDENTIAL

PRELIMINARY ALTITUDE PERFQRM.QTCE DATA FOR THE J65-B3 TURBOJET

ENGINE AT REYNOLDS lWMB;E;R INDICES FROM 0.2 TO 0.8

W. M. Braithwaite Aeronautical 3esearch Scientist

Propulsion Systems

W. K. Greathouse Aeronautical Research Scientist

Propulsion Systems

Approved :

H. Dean Wilsted Aeronautical Research Scientist

Propulsion Systems

Bruce T. Lundin Chief

Engine Research Division

CONFIDENTIAL

\

NACA RM SE54H18

Engines, Turbo jet 3.1.3

Braithwaite, W. M, and Greathouse, W. K.

PRELIkUNARY ALTITUDE PERFORMANCE DATA FOR TRE 365-B3 TURBOJET

ENGINE AT REYNOLDS NUMBE3? INDICES FROM 0.2 TO 0.8

Abstract

Altitude performance characteristics of the J65-I33 turbojet engine and its components were obtained at engine-inlet conditions correspond- ing to Reynolds number indices from 0.2 to 0.8 over a range of corrected engine speeds from 70 to 110 percent of rated speed. Engine operational limits up to an altitude of 75,000 feet along with ignition and wind- milling characteristics were also obtained. The engine and component data are presented both in graphical and in tabulated form. The opera- tional characteristics are presented in graphical form.

Restriction/Classification Cancelled

Restriction/Classification Cancelled

NACA RM SE54H18 L

FORWARD

To permit expeditious transmittal of performance data to those concerned, figures and a tabulation of "preliminary data" are presented herein. Preliminary Data are test data that have not received the complete analysis and extensive cross-checking nor- mally given a set of NACA data before release.

AL

Restriction/Classification Cancelled

Restriction/Classification Cancelled