Kuznetsov NK-8
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| NK-8 | |
|---|---|
 | |
| Type | Turbofan |
| National origin | Soviet Union |
| Manufacturer | Kuznetsov Design Bureau |
| First run | 1961 |
| Major applications | |
| Developed into | |
The NK-8 was a low-bypass turbofan engine built by the Kuznetsov Design Bureau, in the 90 kN (20,000 lbf) thrust class. It powered production models of the Ilyushin Il-62 and the Tupolev Tu-154A and B models.
Variants
[edit]- NK-8-2
- 93.2 kN (20,950 lbf) (Tupolev Tu-154)
- NK-8-2U
- 103.00 kN (23,155 lbf) (Tupolev Tu-154)
- NK-8-4
- 103.0 kN (23,150 lbf) (Ilyushin Il-62)
Applications
[edit]Specifications (NK-8-2)
[edit]
Data from Jane's all the World's Aircraft 1982–83.[1]
General characteristics
- Type: Two-shaft turbofan
- Length: 4,762 mm (187.5 in)
- Diameter: 1,442 mm (56.8 in)
- Dry weight: 2,100 kg (4,600 lb)
Components
- Compressor: Two stage axial fan, two-stage IP compressor, six-stage HP compressor
- Combustors: Annular (139 burners)
- Turbine: Single-stage HP turbine, two-stage LP turbine
- Fuel type: Avtur
- Oil system: Pressure feed
Performance
- Maximum thrust: 93.2 kN (21,000 lbf) for take-off
- Overall pressure ratio: 10.8
- Bypass ratio: 1
- Turbine inlet temperature: 1,140 K (870 °C)
- Specific fuel consumption: 0.76 lb/lbf/h (77 kg/kN/h) at 11,000 m (36,000 ft) at cruise power
- Thrust-to-weight ratio: 4.53
See also
[edit]Related development
Comparable engines
Related lists
References
[edit]- ^ Taylor, John W.R., ed. (1983). Jane's all the World's Aircraft 1982–83. London: Jane's Publishing Company. p. 752. ISBN 978-0-7106-0748-5.
External links
[edit]
Wikimedia Commons has media related to Kuznetsov NK-8.
- NK-8 on LeteckeMotory.cz - NK-8 (cs)
| NK-8 | |
|---|---|
| |
| Type | Turbofan |
| National origin | Soviet Union |
| Manufacturer | Kuznetsov Design Bureau |
| First run | 1961 |
| Major applications | |
| Developed into | |
The NK-8 was a low-bypass turbofan engine built by the Kuznetsov Design Bureau, in the 90 kN (20,000 lbf) thrust class. It powered production models of the Ilyushin Il-62 and the Tupolev Tu-154A and B models.
Variants
- NK-8-2
- 93.2 kN (20,950 lbf) (Tupolev Tu-154)
- NK-8-2U
- 103.00 kN (23,155 lbf) (Tupolev Tu-154)
- NK-8-4
- 103.0 kN (23,150 lbf) (Ilyushin Il-62)
Applications
Specifications (NK-8-2)
Data from Jane's all the World's Aircraft 1982–83.[1]
General characteristics
- Type: Two-shaft turbofan
- Length: 4,762 mm (187.5 in)
- Diameter: 1,442 mm (56.8 in)
- Dry weight: 2,100 kg (4,600 lb)
Components
- Compressor: Two stage axial fan, two-stage IP compressor, six-stage HP compressor
- Combustors: Annular (139 burners)
- Turbine: Single-stage HP turbine, two-stage LP turbine
- Fuel type: Avtur
- Oil system: Pressure feed
Performance
- Maximum thrust: 93.2 kN (21,000 lbf) for take-off
- Overall pressure ratio: 10.8
- Bypass ratio: 1
- Turbine inlet temperature: 1,140 K (870 °C)
- Specific fuel consumption: 0.76 lb/lbf/h (77 kg/kN/h) at 11,000 m (36,000 ft) at cruise power
- Thrust-to-weight ratio: 4.53
See also
Related development
Comparable engines
Related lists
References
- ^ Taylor, John W.R., ed. (1983). Jane's all the World's Aircraft 1982–83. London: Jane's Publishing Company. p. 752. ISBN 978-0-7106-0748-5.
External links
- NK-8 on LeteckeMotory.cz - NK-8 (cs)