TheKlimov GTD-350(initiallyIsotov GTD-350) is a Soviet gas-turbineturboshaftengine intended for helicopter use. Designed in the early 1960s by theIsotov Design Bureauthe engine was later produced byKlimovandPZL,production ending in the late 1990s.[1]
| GTD-350 | |
|---|---|
| |
| Type | Turboshaft |
| Manufacturer | Klimov |
| First run | 1963 |
| Major applications | Mil Mi-2 |
| Number built | > 11,000 |
The GTD-350 powers theMil Mi-2,the first Soviet gas-turbine powered helicopter, and has accumulated over 20 million hours in service.[1]
Applications
editSpecifications (GTD-350)
editData fromKlimov,[1]World Encyclopaedia of Aero Engines,[2]Aircraft engines of the World 1970[3]
General characteristics
- Type:Turboshaft
- Length:1,350 mm (53 in)
- Diameter:~450 mm (18 in) inlet casing
- Width:522 mm (20.6 in)
- Height:680 mm (27 in)
- Dry weight:135 kg (298 lb)
Components
- Compressor:Seven-stage axial flow plus single-stage centrifugal
- Combustors:Single-chamber reverse flow
- Turbine:Single-stage compressor turbine, two-stage power turbine
- Fuel type:Aviation Kerosene, such asJP-4
- Oil system:Pressure spray at 3.1 bar (45 psi)
Performance
- Maximum power output:
- Take-off:300 kW (400 shp) at 45,000 rpm (gas generator)
- Normal:240 kW (320 shp) at 40,000 rpm (gas generator)
- Overall pressure ratio:6.05:1 at 45,000 rpm
- Air mass flow:2.19 kg/s (290 lb/min)
- Turbine inlet temperature:1,210 K (940 °C)
- Specific fuel consumption:0.49 kg/kWh (0.8 lb/(hp⋅h))
- Power-to-weight ratio:2.20 kW/kg (1.34 hp/lb)
See also
editComparable engines
Related lists
References
edit
Wikimedia Commons has media related toKlimov GTD-350.
- ^abc"GTD-350".klimov.ru.moscow. 2013. Archived fromthe originalon 7 March 2013.Retrieved23 March2019.
- ^Gunston, Bill (1989).World Encyclopaedia of Aero Engines(2nd ed.). Cambridge, England: Patrick Stephens Limited. p. 81.ISBN978-1-85260-163-8.
- ^Wilkinson, Paul H. (1970).Aircraft engines of the World 1970(21st ed.). Washington D.C.: Paul H. Wilkinson. p. 215.