Lyulka TR-3
| TR-3 | |
|---|---|
| Type | turbojet |
| National origin | Soviet Union |
| Manufacturer | Lyulka |
| First run | 9 September 1947 |
| Major applications | Ilyushin Il-30 |
| Developed into | Lyulka AL-5 |
The Lyulka TR-3 was a Soviet axial turbojet designed after World War II by Arkhip Mikhailovich Lyulka.
Development
The Lyulka TR-3 was a single-shaft turbojet with a seven-stage axial compressor. It had an annular combustion chamber with 24 nozzles and a single-stage turbine. It had a fixed exhaust nozzle and had a pneumatic SV-3 starting unit, although this was later replaced by a turbine unit. It had a thrust of 46 kN (10,000 lbf). It was used in the Ilyushin Il-30 during 1949, but was superseded by later versions. The improved TR-3A version was redesignated as the AL-5 to honor Lyulka in 1950.[1]
Applications
Specifications (TR-3)
Data from Kay, Turbojet
General characteristics
- Type: turbojet
- Length:
- Diameter:
- Dry weight: 1,900 kg (4,200 lb)
Components
- Compressor: seven-stage axial-flow
- Combustors: annular combustion chamber
- Turbine: single-stage
Performance
- Maximum thrust: 46 kN (10,000 lbf)
- Specific fuel consumption: approximately 1.1
- Thrust-to-weight ratio: 2.38
See also
- Related development
- Related lists
References
- Notes
- ↑ Kay, pp. 27–28
- Bibliography
- Kay, Anthony L. Turbojet: History and Development 1930–1960: Volume 2: USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy, Czechoslovakia and Hungary. Marlborough, Wiltshire: Crowood Press, 2007 ISBN 978-1-86126-939-3
- Gunston, Bill. The Osprey Encyclopaedia of Russian Aircraft 1875–1995. London, Osprey, 1995 ISBN 1-85532-405-9
External links
 |
Wikimedia Commons has media related to Ljulka aircraft engines. |
This article is issued from Wikipedia - version of the 4/16/2016. The text is available under the Creative Commons Attribution/Share Alike but additional terms may apply for the media files.