Soloviev D-25
From Infogalactic: the planetary knowledge core
| D-25 | |
|---|---|
| 300px | |
| Type | Turboshaft |
| Manufacturer | Soloviev Design Bureau |
| First run | 1954 |
| Major applications | Mil Mi-6. |
The Soloviev D-25V is a Soviet gas-turbine turboshaft engine for use in large helicopters. Designed and originally manufactured by the Soloviev Design Bureau the engine has been in production since May 1960.
The V in the designation means vertoletny (Russian: Вертолетный), for helicopters.
Contents
Variants
- D-25V
- Standard helicopter use production engines
- D-25VF
- Additional compressor zero-stage, power output 6,500 hp (4,847 kW)
- D-25VK
- A combined propeller and shaft output engine for the Kamov Ka-22 developing 5,500 hp (4,101 kW)
Applications
- Mi-6 helicopter
- Mi-10 helicopter
- Mi-10K "flying crane" helicopter
- Mi-12 helicopter
- Kamov Ka-22 Compound helicopter
Specifications (D-25V)
Data from Gunston.[1]
General characteristics
- Type: Turboshaft engine
- Length:
- Diameter:
- Dry weight: 1,325 kg (plus 3,200 kg for helicopter gearbox)
Components
- Compressor: Nine-stage axial flow
- Combustors: 12-chamber cannular
- Turbine: Single-stage compressor turbine, two-stage power turbine
Performance
- Maximum power output: 5,500 hp
- Power-to-weight ratio:
See also
- Comparable engines
- Related lists
References
Notes
- ↑ Gunston 1989, p. 164.
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
 |
This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |
