Tumansky R-13
{{Short description|Soviet turbojet aircraft engine}}
| {{Infobox Aircraft Begin
| name = R-13 | image = Р-195 для Су-25 - МАКС-2009 01.jpg | caption = The R-195 derivative used on the Su-25 }}{{Infobox Aircraft Engine |type= Turbojet |manufacturer= Tumansky |first run= |major applications= Sukhoi Su-15 |number built = |program cost = |unit cost = |developed from = Tumansky R-11 |developed into = |variants with their own articles = }} |
The Tumansky R-13 is a Soviet turbojet engine designed by {{ill|Sergei Alekseevich Gavrilov|ru|Гаврилов, Сергей Алексеевич}}.Gunston 1989, p. 168.
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 similar to Tumansky R-11 — originally both were licensed to be built in China, but after the Sino-Soviet split all Soviet technical support was withdrawn, Chinese proceeded on their own. Under the leadership of the principal engineer 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.Braybrook 1991, p.147.
Specifications (R-13-300)
{{Jetspecs
|
|type=Afterburning turbojet
|length=4,605 mm (181.3 in)
|diameter=1,095 mm (43.1 in)
|weight=1,205 kg (2,656 lb)
|compressor=Two-spool axial compressor, 3-stage LP, 5-stage HP
|combustion=can-annular
|turbine=one stage LP, one stage HP
|fueltype=
|oilsystem=
|power=
|thrust=
- 39.9 kN (8,970 lbf) military thrust
- 63.7 kN (14,320 lbf) with afterburner
|compression=8.9:1
|aircon=
|turbinetemp=1,005 °C (1,840 °F)
|fuelcon=
|specfuelcon=
- 95 kg/(h·kN) (0.93 lb/(h·lbf)) at idle
- 213 kg/(h·kN) (2.09 lb/(h·lbf)) with afterburner
|power/weight=
|thrust/weight=5.4
}}
See also
{{aircontent
|see also=
|related=
|similar aircraft=
|lists=
|similar engines=
}}
References
= Citations =
{{Reflist}}
= Sources =
{{refbegin}}
- Gunston, Bill. World Encyclopaedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. {{ISBN|1-85260-163-9}}.
- Braybrook, Roy. Soviet Combat Aircraft. London, England. Osprey Publishing Limited, 1991. {{ISBN|1-85532-120-3}}.
{{refend}}
External links
- [http://www.leteckemotory.cz/motory/r-13 R-13 on LeteckeMotory.cz] (cs,sk)
{{Tumansky aeroengines}}