.jpg "D-25V Turboshaft engine © Konstantinos Panitsidis")
In numbers Through the lens Video
More than 3.000 units of all modifications were produced.
Production Period: 1960 to 1981.
The D-25V turboshaft engine was developed based on the gas generator of the D-20 bypass turbofan engine and was the first aircraft engine to feature a “free turbine.”
This 7.375 h.p, single-shaft turboshaft engine includes a 9-stage axial compressor, a tubular-annular combustion chamber, and a single-stage turbine “free turbine” that consists of two stages with a rear transfer shaft.
The engine is designed to operate under the following conditions:
Altitude: up to 3.000 meters
Temperature: up to 40°C at sea level
Technical specifications
| DESIGNER | Soloviev Design Bureau |
| COUNTRY | Russia |
| TYPE |
Turboshaft engine
|
| Installed On (aerial means) |
Mi-6
|
| Fuel | TS-1, T-1 and mixtures thereof |
| Oil | MK-8 (from gas generator), МК-22, МК-8 and МС-20 (from turbine and gear box) |
| Propeller shaft power, take-off power rating | 5.550 h.p. |
| Specific fuel consumption, take-off power rating | 0,287 kg/h.p.*h |
| Propeller shaft power, cruise power (H=1.000 m, V=250 km/h) | 3.100 h.p. |
| Specific fuel consumption, cruise power | 0,343 kg/h.p.*h |
| Pressure ratio, take-take-off power rating | 5,6 |
| Temperature of the gas at the turbine intake, take-off power rating | 1.160 K |
| Air flow rate, take-off power rating | 26 kg/h |
| Compressor rotation frequency low-pressure, take-off power rating | 10.530 rpm. |
| OVERALL DIMENSIONS | |
| Diameter | 572 mm |
| Height | 1158 mm |
| Width | 1086 mm |
| Length | 2737 mm |
| WEIGHT | |
| Engine weight | 1.243 kg |
| Specified service life | 6.000 h |
Photos D-25V Turboshaft engine.
Video
D-25V Turboshaft engine © Redstar.gr