Table 1.2
Main specifications for some serial TFEs used in civil aviation
Engine |
Country |
Takeoff rating thrust R, kN |
Specific fuel con-sumption
|
Маss of engine
|
Compres. pres- sure ratio *c |
Fan pres-sure ratio *fan |
By-pass ratio m |
Massair flow rate Ga, kg/s |
Turbine inlet tempe-rature T*ti, К |
Aircraft |
НК-8-2У |
USSR |
103,0 |
0,0591 |
2350 |
10,7 |
2,06 |
1,05 |
228 |
1250 |
Ту-154Б |
Д-30 series II |
USSR |
66,5 |
0,0600 |
1150 |
18,4 |
2,10 |
1,00 |
128 |
1340 |
Ту-134 |
Д-30КУ |
USSR |
112,0 |
0,0510 |
2600 |
19,6 |
2,08 |
2,40 |
200 |
1400 |
Ил-62М |
АИ-25 |
USSR |
14,7 |
0,0580 |
348 |
8,0 |
1,76 |
2,00 |
42 |
1270 |
Як-40 |
Д-36 |
USSR |
64,0 |
0,0390 |
1100 |
20,0 |
1,47 |
5,30 |
275 |
1500 |
Як-42, Ан-72 |
Д-18Т |
USSR |
235,0 |
0,0370 |
3700 |
27,5 |
1,65 |
5,50 |
740 |
1550 |
Ан-124, Ан-225 |
ПС-90А |
USSR |
157,0 |
0,0350 |
3500 |
32,5 |
1,65 |
4,80 |
500 |
1620 |
Ту-204, Ил-96 |
RB-211-535 |
England |
169,0 |
0,0380 |
3215 |
23,0 |
1,60 |
4,50 |
435 |
1473 |
В-757-200 |
RB-211-524D |
England |
244,0 |
0,0360 |
3678 |
26,2 |
1,70 |
5,50 |
750 |
1590 |
В-747-200 |
JT8D-15 |
USA |
69,0 |
0,0650 |
1500 |
18,0 |
1,80 |
1,00 |
147 |
1340 |
В-737 |
JT9D-70A |
USA |
236,0 |
0,0380 |
4146 |
24,5 |
1,70 |
4,90 |
734 |
1623 |
В-747G |
JT9D-7R4D |
USA |
214,0 |
0,0347 |
3913 |
23,2 |
1,70 |
5,00 |
721 |
1468 |
В-747 |
CF6-50C |
USA |
224,0 |
0,0400 |
3960 |
29,4 |
1,70 |
4,40 |
664 |
1595 |
DC-10, A‑300 |
CF6-50C2 |
USA |
234,0 |
0,0379 |
3955 |
30,4 |
1,70 |
4,31 |
670 |
1620 |
DC-10 |
CFM56-С5 |
France+ USA |
112,5 |
0,0360 |
2183 |
26,6 |
1,65 |
5,90 |
380 |
1540 |
B‑737-300 |
PW-4056 |
USA |
250,0 |
0,0366 |
4267 |
30,5 |
1,70 |
4,85 |
700 |
1626 |
A‑320 |
,
kg/(Nh)
,
kg
The high expenses on GTE production stipulate considerable operating costs of aeroengines maintenance and repair. These expenses are to a large extent connected with salary costs of highly qualified pilots, engineers and technicians. The preparation of a personnel structure for civil aviation enterprises provides studying fundamental, engineering and special disciplines. First module of the course “Design and strength of aeroengines” gives analysis of the loads, that affects the details and units of GTEs, and considers strength calculation techniques as well as calculation techniques of vibrations of blades, discs, shafts and shell-type constructions.