| Aircraft Engine Manufacturer |
Rolls-Royce |
Klimov |
| Aircraft Engine Type |
Turbofan |
Turbojet |
| Dry Weight (kg) |
446.7885 |
872 |
| Diameter (mm) |
822.96 |
1300 |
| Length (mm) |
1544.32 |
2600 |
| Wikipedia Article (URL) |
en.wikipedia.org/wiki/Rolls-Royce_RB401 |
en.wikipedia.org/wiki/Klimov_VK-1 |
| Fuel |
Hydromechanical with provision for electronic monitoring |
|
| Geared Fan |
No |
No |
| Combustion Chamber |
Annular |
Nine can combustion chambers |
| Afterburner |
No |
No |
| Streams |
2 |
1 |
| Bypass Ratio |
4.2 |
|
| Maximum Takeoff Thrust (kN) |
24.7 |
26.5 |
| Thrust To Weight |
5.6 |
3.1 |
| Specific Fuel Consumption (g/(kN·s)) |
|
3090.257 |
| Compressor Description |
Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes |
Centrifugal compressor |
| Turbine Description |
Two-stage LP, single-stage HP with air-cooled blades |
single stage axial |