Data for some military gas turbine engines

Model No. Type Max thrust or power @ SLS SFC at max

Airflow

(lb/sec)

OPR

(stages)

D

(in)

L

(in)

Weight

(lb)

TIT

(F)
Remarks
J57-P-23 TJ

16,000 lb

2.10

165

11.5 (16)

40 246 5,169 1,600 AB, F-102A, F-100D
J57-P-43WB TJ

11,200 lb

0.775

180

12 (16)

39 167.3 3,870 1,600 Water-injected, KC-135
J58-P TJ

*32,500 lb

*450

*6 (9)

AB, YF-12A, SR-71
J60-P-3 TJ

3,000 lb

0.96

50

7 (9)

23.4 79.5 460 1,600 T-39A, C-140A
J69-T-25 TJ

1,025 lb

1.14

20.5

3.9 (0,1)

22.3 43.3 364 1,525 T-37B
J75-P-17 TJ

24,500 lb

2.15

252

12.0 (15)

43 237.6 5,875 1,610 AB, F-106A/B
J79-GE-17 TJ

17,820 lb

1.965

170

13.5 (17)

39.1 208.7 3,855 1,210 AB, F-4E/G
J85-GE-5H TJ

3,850 lb

2.20

44

7 (8)

20.4 109.1 584 1,640 AB, T-38A/B
J85-GE-17 TJ

2,850 lb

0.99

44

7 (8)

17.7 40.4 395 1,640 A-37B
J85-GE-21 TJ

5,000 lb

2.13

51.9

8 (8)

20 116 667 1,790 AB, F-5E/F
PT6A-42 TP

850 eshp

0.601

8.0

8 (3,1)

19 67 391

C-12E
PT6A-45R TP

1,197 eshp

0.553

8.6

8.7 (3,1)

19 72 434

C-23A
T400-CP-400 TS

1,800 shp

0.606

6.51

7 (3, 1)

43.5 66.3 716 1,920 Bell UH-1N
T406-AD-400 TS

6,150 shp

0.424

(14)

24.5 77.9 975 1,422 CV-22
T53-L-13 TS

1,400 shp

0.58

12.2

7 (5,1)

23 47.6 549 1,720 Bell UH-1H, AH-IG
T55-L-11 TS

3,750 shp

0.52

8 (6,1)

24.3 44 670

Boeing CH-47C
T56-A-7 TP

3,775 eshp

0.528

32.5

9.45 (14)

40.9 146 1,833 1,780 C-130B/E/F
T56-A-15 TP

4,591 eshp

0.54

32.5

9.55 (14)

44.6 146.3 1,848 1,970 C-130H/N/P
T58-GE-100 TS

1,500 shp

0.606

14

8.4 (10)

21.5 58.6 335 1,372 Sikorsky CH-3E, HH-3E, F
T64-GE-100 TS

4,330 shp

0.487

29.3

14 (14)

20.2 77.1 720 1,520 MH-53T
T700-GE-700 TS

1,622 shp

0.46

15 (5,1)

25 47 423 1,563 UH-60A
T76-G-10 TS

715 shp

0.60

6.16

8.6 (2)

27.1 44.5 348 1,818 OV-IOA

TJ = turbojet, TP = turboprop, OPR = overall pressure ratio, TIT = turbine inlet temperature, TS = turboshaft,

(Stages) = (axial, centrifugal) compressor stages, SFC = specific fuel consumption.

*J-58 Reference: Lockheed SR-71 by Jay Miller, Aerofax Minigraph 1, Aerofax, Inc., Arlington, TX, 1985.

Sources: The Engine Handbook, Directorate of Propulsion, Headquarters Air Force Logistics Command, Wright-Patterson AFB, Ohio, 1991 and manufacturers’ literature.