|Tumansky R-29-300 on display at the Deutsches Museum Flugwerft Schleissheim|
|Developed from||Tumansky R-27|
|Developed into||Tumansky R-35|
The Tumansky R-29 is a Soviet aircraft turbojet engine that was developed in the early 1970s. It is generally described as being in the "third generation" of Soviet gas turbine engines which are characterized by high thrust-to-weight ratios and the use of turbine air cooling.
R-29-300 Original variant. Used in the MiG-23MF and related variants.
R-29B-200 Simplified variant of the engine intended for the MiG-27.
R-29PN Advanced variant that replaced the -300 model on non-export aircraft.
Data from Gunston
- Type: Turbojet
- Length: 4,991 mm (196.5 in)
- Diameter: 968 mm (38.1 in)
- Dry weight: 1,760 kg (3,880 lb)
- Compressor: Two-spool Five-stage low pressure, six-stage high pressure (axial)
- Combustors: Annular
- Turbine: Two-stage high pressure, single-stage low pressure
- Maximum thrust:
- 78,48 kN dry
- 112,81 kN with afterburner
- Overall pressure ratio: 12.9:1
- Air mass flow: 105 kg/s
- Turbine inlet temperature: 1,083 °C
- Specific fuel consumption: =
- 95,8 kg/(h·kN) (0.94 lb/(h·lbf)) at maximum military power
- 183.5 kg/(h·kN) (1.81 lb/(h·lbf)) with afterburner
- Power-to-weight ratio:
- Comparable engines
- Related lists
|Wikimedia Commons has media related to Tumansky R-29.|
- Gunston 1989, p. 168.
- Sosounov, V.A. (1990). The Development of Aircraft Power Plant Construction in the USSR and the 60th Anniversary of CIAM. AlAA/ASME/SAE/ASEE 26th Joint Propulsion Conference, July 16–18, 1990. Orlando, Florida. AIAA-90-2761.
- TMKB Soyuz R29-300 (subscription required). Janes Aero Engines. Edited: 1 April 2010. Retrieved: 8 September 2010.
- Gunston, Bill. World Encyclopaedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9