Tumansky R-29
(Redirected from Khatchaturov R-35)
| R-29 | |
|---|---|
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| |
| Tumansky R-29-300 on display at the Deutsches Museum Flugwerft Schleissheim | |
| Type | Turbojet |
| Manufacturer | Tumansky, UMPO, MMP Chernyshev, AMNTK Sojuz |
| First run | 1972 |
| Major applications | MiG-23 |
| Developed from | Tumansky R-27 |
| Developed into | Tumansky R-35 |
The Tumansky R-29 is a Soviet turbojet aircraft engine that was developed in the early 1970s.[1] 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.[2]
Variants
[edit]- R-29-300
Original variant. Used in the MiG-23MF and related variants.[3]
- R-29B-300
Simplified variant of the engine intended for the MiG-27.[3]
- R-29PN
Advanced variant that replaced the -300 model on non-export aircraft.[3]
- R-29BS-300
Variant with modified gearbox. Used in several export variants of the Sukhoi Su-17.[3]
- Khatchaturov R-35-300
Developed version used in late variants of the MiG-23.
- Shenyang WP-15
Chinese reverse-engineered copy of the R-29-300.[4]
Applications
[edit]- IAR 95 (Intended application)
- Mikoyan-Gurevich MiG-23
- Mikoyan MiG-27
- Chengdu J-10 (Prototype)
- Shenyang J-13 (Intended application)
- Sukhoi Su-22
Specifications (R-29-300)
[edit]Data from [5]
General characteristics
- Type: Turbojet
- Length: 4,953 mm (195.0 in)
- Diameter: 912 mm (35.9 in)
- Dry weight: 1,880 kg (4,140 lb)
Components
- Compressor: Two-spool Five-stage low pressure, six-stage high pressure (axial)
- Combustors: Annular
- Turbine: Two-stage high pressure, single-stage low pressure
Performance
- Maximum thrust:
- 78.48 kilonewtons (17,640 lbf) full military (dry)
- 112.81 kilonewtons (25,360 lbf) with boosted afterburner (CSR mode, altitude < 4,000 metres (13,000 ft))
- Overall pressure ratio: 12.9:1
- Air mass flow: 105 kg/s
- Turbine inlet temperature: 1,083 °C
- Specific fuel consumption: =
- 96,8 kg/(h·kN) (0.95 lb/(h·lbf)) at maximum military power
- 202,76 kg/(h·kN) (2 lb/(h·lbf)) with afterburner
- Thrust-to-weight ratio: 4.446; 6.119 with afterburner.
See also
[edit]Comparable engines
Related lists
References
[edit]Citations
[edit]- ^ 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.
- ^ a b c d TMKB Soyuz R29-300 (subscription required)[permanent dead link]. Janes Aero Engines. Edited: 1 April 2010. Retrieved: 8 September 2010.
- ^ [1] 中国涡喷15A算不算国产航发 曾用于歼10原型机试飞. Sina Military. Edited: 21 March 2018. Retrieved: 12 July 2021.
- ^ "Turbofan and Turbojet Engines" (PDF). Retrieved 2024-02-10.
Sources
[edit]- Gunston, Bill. World Encyclopaedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9.
External links
[edit]
Wikimedia Commons has media related to Tumansky R-29.
- R-29 on leteckemotory.cz (in Czech and Slovak)