Military Gas Turbine Engines Data
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Data for some military gas turbine engines Model No.
Type
J57-P-23
TJ
J57-P-43WB
TJ
J58-P
TJ
J60-P-3
TJ
J69-T-25
TJ
J75-P-17
TJ
J79-GE-17
TJ
J85-GE-5H
TJ
J85-GE-17
TJ
J85-GE-21
TJ
PT6A-42
TP
PT6A-45R
TP
T400-CP-400
TS
T406-AD-400
TS
T53-L-13
TS
T55-L-11
TS
T56-A-7
TP
T56-A-15
TP
T58-GE-100
TS
T64-GE-100
TS
T700-GE-700
TS
Max thrust or power @ SLS
16,000 lb
11,200 lb
*32,500 lb
3,000 lb
1,025 lb
24,500 lb
17,820 lb
3,850 lb
2,850 lb
5,000 lb
850 eshp
1,197 eshp
1,800 shp
6,150 shp
1,400 shp
3,750 shp
3,775 eshp
4,591 eshp
1,500 shp
4,330 shp
1,622 shp
SFC at max
Airflow
OPR (stages)
(lb/sec) 2.10
165
0.775
180
—
*450
0.96
50
1.14
20.5
2.15
252
1.965
170
2.20
44
0.99
44
2.13
51.9
0.601
8.0
0.553
8.6
0.606
6.51
0.424
—
0.58
12.2
0.52
—
0.528
32.5
0.54
32.5
0.606
14
0.487
29.3
0.46
—
D
L (in)
Weight (lb)
TIT (F)
Remarks
(in)
11.5 (16)
12 (16)
*6 (9)
7 (9)
3.9 (0,1)
12.0 (15)
13.5 (17)
7 (8)
7 (8)
8 (8)
8 (3,1)
8.7 (3,1)
7 (3, 1)
(14)
7 (5,1)
8 (6,1)
9.45 (14)
9.55 (14)
8.4 (10)
14 (14)
15 (5,1)
40
246
5,169
1,600
AB, F-102A, F-100D
39
167.3
3,870
1,600
Water-injected, KC-135
—
—
—
—
AB, YF-12A, SR-71
23.4
79.5
460
1,600
T-39A, C-140A
22.3
43.3
364
1,525
T-37B
43
237.6
5,875
1,610
AB, F-106A/B
39.1
208.7
3,855
1,210
AB, F-4E/G
20.4
109.1
584
1,640
AB, T-38A/B
17.7
40.4
395
1,640
A-37B
20
116
667
1,790
AB, F-5E/F
19
67
391
—
C-12E
19
72
434
—
C-23A
43.5
66.3
716
1,920
Bell UH-1N
24.5
77.9
975
1,422
CV-22
23
47.6
549
1,720
Bell UH-1H, AH-IG
24.3
44
670
—
40.9
146
1,833
1,780
C-130B/E/F
44.6
146.3
1,848
1,970
C-130H/N/P
21.5
58.6
335
1,372
Sikorsky CH-3E, HH-3E, F
20.2
77.1
720
1,520
MH-53T
25
47
423
1,563
UH-60A
Boeing CH-47C
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.
Type
J57-P-23
TJ
J57-P-43WB
TJ
J58-P
TJ
J60-P-3
TJ
J69-T-25
TJ
J75-P-17
TJ
J79-GE-17
TJ
J85-GE-5H
TJ
J85-GE-17
TJ
J85-GE-21
TJ
PT6A-42
TP
PT6A-45R
TP
T400-CP-400
TS
T406-AD-400
TS
T53-L-13
TS
T55-L-11
TS
T56-A-7
TP
T56-A-15
TP
T58-GE-100
TS
T64-GE-100
TS
T700-GE-700
TS
Max thrust or power @ SLS
16,000 lb
11,200 lb
*32,500 lb
3,000 lb
1,025 lb
24,500 lb
17,820 lb
3,850 lb
2,850 lb
5,000 lb
850 eshp
1,197 eshp
1,800 shp
6,150 shp
1,400 shp
3,750 shp
3,775 eshp
4,591 eshp
1,500 shp
4,330 shp
1,622 shp
SFC at max
Airflow
OPR (stages)
(lb/sec) 2.10
165
0.775
180
—
*450
0.96
50
1.14
20.5
2.15
252
1.965
170
2.20
44
0.99
44
2.13
51.9
0.601
8.0
0.553
8.6
0.606
6.51
0.424
—
0.58
12.2
0.52
—
0.528
32.5
0.54
32.5
0.606
14
0.487
29.3
0.46
—
D
L (in)
Weight (lb)
TIT (F)
Remarks
(in)
11.5 (16)
12 (16)
*6 (9)
7 (9)
3.9 (0,1)
12.0 (15)
13.5 (17)
7 (8)
7 (8)
8 (8)
8 (3,1)
8.7 (3,1)
7 (3, 1)
(14)
7 (5,1)
8 (6,1)
9.45 (14)
9.55 (14)
8.4 (10)
14 (14)
15 (5,1)
40
246
5,169
1,600
AB, F-102A, F-100D
39
167.3
3,870
1,600
Water-injected, KC-135
—
—
—
—
AB, YF-12A, SR-71
23.4
79.5
460
1,600
T-39A, C-140A
22.3
43.3
364
1,525
T-37B
43
237.6
5,875
1,610
AB, F-106A/B
39.1
208.7
3,855
1,210
AB, F-4E/G
20.4
109.1
584
1,640
AB, T-38A/B
17.7
40.4
395
1,640
A-37B
20
116
667
1,790
AB, F-5E/F
19
67
391
—
C-12E
19
72
434
—
C-23A
43.5
66.3
716
1,920
Bell UH-1N
24.5
77.9
975
1,422
CV-22
23
47.6
549
1,720
Bell UH-1H, AH-IG
24.3
44
670
—
40.9
146
1,833
1,780
C-130B/E/F
44.6
146.3
1,848
1,970
C-130H/N/P
21.5
58.6
335
1,372
Sikorsky CH-3E, HH-3E, F
20.2
77.1
720
1,520
MH-53T
25
47
423
1,563
UH-60A
Boeing CH-47C
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.
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