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 power unit consists of two engines coupled to a gearbox weighing 3,200 kg (7,050 lb).
The V in the designation means vertoletny (Russian: Вертолетный), for helicopters.
Specifications (D-25V)
Data from Aircraft engines of the World 1970.[1]
General characteristics
- Type: Free-turbine single-shaft turboshaft engine
- Length: 2,737 mm (107.8 in)
- Diameter: 508 mm (20.0 in) (casing)
- Width: 1,086 mm (42.8 in)
- Height: 1,158 mm (45.6 in)
- Frontal area: 0.2 m2 (2.2 sq ft)
- Dry weight: 1,200 kg (2,600 lb)
Components
- Compressor: Nine-stage axial flow
- Combustors: 12-chamber cannular
- Turbine: Single-stage compressor turbine, two-stage free power turbine
- Fuel type: Aviation kerosene based fuels, such as Jet A, Jet A-1, JP-4
- Oil system: Pressure spray at 4.7 bar (68 psi) with return
Performance
- Take-off power: 5,500 shp (4,100 kW) (equivalent) sea level to 3,000 m (9,800 ft) at 8,300 free power turbine rpm
- Cruising power: 4,700 shp (3,500 kW) (equivalent) at 3,000 m (9,800 ft) at 8,300 free power turbine rpm
Aviadvigatel, Soloviev and Shvetsov aero engines