Tumansky R-13
The Tumansky R-13 is a Soviet turbojet engine designed by Sergei Alekseevich Gavrilov.[1]
| R-13 | |
|---|---|
| Type | Turbojet |
| Manufacturer | Tumansky |
| Major applications | Sukhoi Su-15 Mikoyan-Gurevich MiG-21 |
| Developed from | Tumansky R-11 |
Design and development
The Tumansky R-13 is a development of the successful Tumansky R-11 engine. It is a two-spool axial-flow turbojet featuring a new five-stage high-pressure compressor, new combustion chamber design to facilitate restarting the engine at high altitudes, new afterburner, and greater use of titanium components. It is used by MiG-21M, MF, SM, and SMT, and Sukhoi Su-15M and TM. R-13 is also built in China as LM WP13, and experienced similar fate like Tumansky R-11: originally, both were licensed to be built in China, but after the Sino-Soviet split all Soviet technical support was withdrawn and Chinese proceeded on their own. Under the leadership of the general designer Jiang Hepu (江和甫), both R-11 and R-13 were successfully built in China.
The R-95 is a non-afterburning development of this engine used by initial versions of the Sukhoi Su-25 attack aircraft. It was subsequently replaced in production by the improved R-195, which produces 12 percent more thrust.[2]
Specifications (R-13-300)
General characteristics
- Type: Afterburning turbojet
- Length: 4,605 mm (181.3 in)
- Diameter: 1,095 mm (43.1 in)
- Dry weight: 1,205 kg (2,656 lb)
Components
- Compressor: Two-spool axial compressor, 3-stage LP, 5-stage HP
- Combustors: can-annular
- Turbine: one stage LP, one stage HP
Performance
- Maximum thrust:
- 39.9 kN (8,970 lbf) military thrust
- 63.7 kN (14,320 lbf) with afterburner
- Overall pressure ratio: 8.9:1
- Turbine inlet temperature: 1,005 °C (1,840 °F)
- Specific fuel consumption:
- 95 kg/(h·kN) (0.93 lb/(h·lbf)) at idle
- 213 kg/(h·kN) (2.09 lb/(h·lbf)) with afterburner
- Thrust-to-weight ratio: 5.4
References
Citations
- Gunston 1989, p. 168.
- Braybrook 1991, p.147.
External links
- R-13 on LeteckeMotory.cz (cs,sk)