Tumansky R-13
# Tumansky R-13

The Tumansky R-13 is a Soviet turbojet engine designed by Sergei Alekseevich Gavrilov [ru].

## 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originally, both were licensed to be built in China, but after the Sino-Soviet split all Soviet technical support was withdrawn and Chinese proceeded on their own.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.

## 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
