|Type||National origin||Manufacturer||Designed by|| Major applications
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Design and development
The development of the high performance single-shaft engine began in 1948. The engine was used in different versions for the Tupolev Tu-16 and Tu-104, as well as the Myasishchev M-4. It had a single-stage blower and an eight-stage high pressure compressor, that were propelled by a two-stage high pressure turbine.
- first series version
- Version for M-4 with 85,6 kN thrust
- AM-3M-500, AM-3M-500A: developed further versions with 93,1 kN
- Chinese copy of the AM-3 with 91,3 kN thrust for the Xian H-6 (reproduction of the Tu-16)
- Type: Turbojet engine
- Length: 5,380 mm
- Diameter: 1,400 mm
- Dry weight: 3,200 kg
- Compressor: 8-stage axial-flow
- Maximum thrust: 85,3 kN
- Turbine inlet temperature: 860°C
- Specific fuel consumption: 0.932 kg (kN•h)
- Power-to-weight ratio:
- Related lists
- Gunston 1989, p. 104.
- Gunston, Bill. World Encyclopaedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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