| Aircraft Engine Manufacturer |
Lyulka-Saturn |
IHI Corporation |
| Aircraft Engine Type |
Turbojet |
Turbojet |
| Dry Weight (kg) |
885 |
430 |
| Diameter (mm) |
|
627 |
| Length (mm) |
|
1661 |
| Wikipedia Article (URL) |
en.wikipedia.org/wiki/Lyulka_TR-1 |
en.wikipedia.org/wiki/Ishikawajima-Harima_J3 |
| Fuel |
|
JP-4 jet fuel |
| Geared Fan |
No |
No |
| Combustion Chamber |
|
annular combustion chamber with 30 fuel supply pipes and vapouriser tubes |
| Afterburner |
No |
No |
| Streams |
1 |
1 |
| Maximum Takeoff Thrust (kN) |
12.8 |
13.7 |
| Thrust To Weight |
1.47 |
3.2 |
| Specific Fuel Consumption (g/(kN·s)) |
3653.925 |
3027.942 |
| Compressor Description |
eight-stage axial-flow |
eight-stage axial compressor |
| Turbine Description |
single stage |
single-stage axial-flow |