Kuznetsov NK-6
1950s Soviet/Russian turbofan aircraft engine From Wikipedia, the free encyclopedia
The Kuznetsov NK-6 was a low-bypass afterburning turbofan engine, designed by the Kuznetsov Design Bureau.
| NK-6 | |
|---|---|
| Type | Turbofan |
| National origin | Soviet Union |
| Manufacturer | Kuznetsov Design Bureau |
| First run | May 1958[1] |
Development
Development of the NK-6 started in 1955 at the Kuznetsov Design Bureau.[2] It was the first afterburning by-pass engine made in the Soviet Union.[1] With a maximum thrust of 216 kN (49,000 lbf), it was the most powerful jet engine in the world in the early 1960s.[2] Despite this fact, development of the NK-6 was halted in July 1963.[2] The accumulated experience of the NK-6 project was subsequently used in the development of the NK-144.[2]
A modified version of this engine, the NK-7, was intended for the Soviet Navy[1] and had a takeoff thrust of 216 kN (49,000 lbf).
Applications
- Project "106"[3] (proposed)
- Tupolev Tu-95LL (testbed)
- Tupolev Tu-123[4] (proposed)
- Tupolev Tu-125[1] (proposed)
- Tupolev Tu-135[3] (proposed)
Specifications (NK-6)
Data from Otechestvennaya aviatsionno-kosmicheskaya tekhnika - SAMARSKIY NTK[1]
General characteristics
- Type: Two-spool low-bypass afterburning turbofan
- Length: 4,810 mm (189 in)
- Diameter: 1,750 mm (69 in)
- Dry weight: 3,200 kg (7,100 lb)
Components
- Compressor: 4-stage LP,[1] 6-stage HP[1]
- Combustors: Annular multi-nozzle combustion chamber[1]
- Turbine: 1-stage HP,[1] 2-stage LP[1]
Performance
- Maximum thrust:
- Overall pressure ratio: 13.4[1] at takeoff
- Bypass ratio: 1.79[1]
- Air mass flow: 343 kg/s (760 lb/s)[1]
- Turbine inlet temperature: 1,400 K (1,130 °C; 2,060 °F)[1]
- Specific fuel consumption:
See also
Comparable engines
Related lists
References
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