Tumansky R-11

The Tumansky R-11 (initially AM-11) is a Soviet Cold War-era turbojet engine.

R-11
Preserved Tumansky R-11 turbojet engine at the Polish Aviation Museum
Type	Turbojet
National origin	Soviet Union
Manufacturer	Tumansky
First run	1956
Major applications	Sukhoi Su-15 Mikoyan-Gurevich MiG-21 Yakovlev Yak-28
Number built	20,900

Design and development

The Tumansky R-11 was developed by A.A. Mikulin, Sergei Tumansky, and B.S. Stechkin as a twin-spool axial-flow high-altitude non-afterburning turbojet for Yakovlev Yak-25RV reconnaissance aircraft. This engine was the first Soviet twin-spool turbojet. It was first run in early 1956 and was later employed in some variants of the Yakovlev Yak-26 and Yakovlev Yak-27, as well as the Yak-28. The R-11's basic design was very successful and it was later developed into the Tumansky R-13 and Tumansky R-25 along with the experimental Tumansky R-21. A total of 20,900 R-11 engines were built.

Variants

• R-11V-300 - first production version, high-altitude, non-afterburning
• R-11F-300 (R-37F) - afterburning version, entered production in 1956, used on MiG-21F, P and U.
• R-11AF-300 - improved version for Yakovlev Yak-28B, L and U.
• R-11F2-300 - new compressor, afterburner and nozzle, used on MiG-21P, PF and FL.
• R-11AF2-300 - R-11F2-300 adapted for Yakovlev Yak-28I, R and P.
• R-11F2S-300 - upgraded version for MiG-21PFM, PFS, S, U and UM, and for Sukhoi Su-15, UT and UM.
• Shenyang WP-7, Chinese license built copies of the R-11

Applications

• Sukhoi Su-15
• Mikoyan-Gurevich MiG-21
• Yakovlev Yak-25
• Yakovlev Yak-26
• Yakovlev Yak-27
• Yakovlev Yak-28

Specifications (R-11F2S-300)

General characteristics

• Type: Afterburning turbojet
• Length: 4,600 mm (181.1 in)
• Diameter: 906 mm (35.7 in)
• Dry weight: 1,124 kg (2,477 lb)

Components

• Compressor: Axial compressor, 3-stage LP, 3-stage HP
• Turbine: one stage LP, one stage HP

Performance

• Maximum thrust:
  
• 38.7 kN (8,708 lbf) military power
• 60.6 kN (13,635 lbf) with afterburner
• Overall pressure ratio: 8.9:1
• Turbine inlet temperature: 955 °C (1,750 °F)
• Specific fuel consumption:
  
• 97 kg/(h·kN) (0.95 lb/(h·lbf)) at idle
• 242 kg/(h·kN) (2.37 lb/(h·lbf)) with afterburner
• Thrust-to-weight ratio: 3.51; 5.50 with afterburner.

See also

• List of aircraft engines

References

Sources

• Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9.

External links

• LeteckeMotory.cz - R-11 (in Czech) - (in Slovak)