| NK-87 | |
|---|---|
| Type | Turbofan |
| National origin | Soviet Union |
| Manufacturer | Kuznetsov Design Bureau |
| First run | January 1983 [1] |
| Major applications |
Lun-class ekranoplan Spasatel |
| Developed from | NK-86 |
The Kuznetsov NK-87 is a low-bypass turbofan engine rated at 127.5 kN [1] (28,700 lbf) thrust. It powers the Lun-class ekranoplan. It is made by the soviet Kuznetsov Design Bureau (now JSC Kuznetsov).
Applications
- Lun-class ekranoplan
- Spasatel (proposed)
Specifications (NK-87)
Data from Otechestvennaya aviatsionno-kosmicheskaya tekhnika - SAMARSKIY NTK [1]
General characteristics
- Type: Two-spool low-bypass afterburning turbofan
- Length: 20.5 ft
- Diameter: 1,455 mm (57.3 in) [1] in compressor
- Dry weight: 2,200 kg (4,900 lb) [1]
Components
- Compressor:
Performance
- Maximum thrust: 127.5 kN (28,700 lbf) [1] at takeoff
- Overall pressure ratio: 13 [1]
- Bypass ratio: 1.17 [1]
- Turbine inlet temperature: 1,280 K (1,010 °C; 1,840 °F) [1]
- Specific fuel consumption: 54 kg/(kN⋅h) [1] at takeoff
See also
Comparable engines
Related lists
References
 |
This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |
| NK-87 | |
|---|---|
| Type | Turbofan |
| National origin | Soviet Union |
| Manufacturer | Kuznetsov Design Bureau |
| First run | January 1983 [1] |
| Major applications |
Lun-class ekranoplan Spasatel |
| Developed from | NK-86 |
The Kuznetsov NK-87 is a low-bypass turbofan engine rated at 127.5 kN [1] (28,700 lbf) thrust. It powers the Lun-class ekranoplan. It is made by the soviet Kuznetsov Design Bureau (now JSC Kuznetsov).
Applications
- Lun-class ekranoplan
- Spasatel (proposed)
Specifications (NK-87)
Data from Otechestvennaya aviatsionno-kosmicheskaya tekhnika - SAMARSKIY NTK [1]
General characteristics
- Type: Two-spool low-bypass afterburning turbofan
- Length: 20.5 ft
- Diameter: 1,455 mm (57.3 in) [1] in compressor
- Dry weight: 2,200 kg (4,900 lb) [1]
Components
- Compressor:
Performance
- Maximum thrust: 127.5 kN (28,700 lbf) [1] at takeoff
- Overall pressure ratio: 13 [1]
- Bypass ratio: 1.17 [1]
- Turbine inlet temperature: 1,280 K (1,010 °C; 1,840 °F) [1]
- Specific fuel consumption: 54 kg/(kN⋅h) [1] at takeoff
See also
Comparable engines
Related lists
References
|
|
This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |