Klimov GTD-350

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GTD-350
Klimow GTD-350.jpg
Type Turboshaft
Manufacturer Klimov
First run 1963
Major applications Mil Mi-2
Number built > 11,000

The Klimov GTD-350 (initially Isotov GTD-350) is a Soviet gas-turbine turboshaft engine intended for helicopter use. Designed in the early 1960s by the the engine was later produced by Klimov and PZL, production ending in the late 1990s.[1]

The GTD-350 powers the Mil Mi-2, the first Soviet gas-turbine powered helicopter, and has accumulated over 20 million hours in service.[1]

Applications[]

Specifications (GTD-350)[]

Data from Klimov,[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 as JP-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[]

Comparable engines

Related lists

References[]

  1. ^ a b c "GTD-350". klimov.ru. moscow. 2013. Archived from the original on 7 March 2007. Retrieved 23 March 2019.
  2. ^ Gunston, Bill (1989). World Encyclopaedia of Aero Engines (2nd ed.). Cambridge, England: Patrick Stephens Limited. p. 81. ISBN 978-1-85260-163-8.
  3. ^ Wilkinson, Paul H. (1970). Aircraft engines of the World 1970 (21st ed.). Washington D.C.: Paul H. Wilkinson. p. 215.
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