Turbomeca Artouste
Description

The Turbomeca Artouste is an early French turboshaft engine, first run in 1947. Originally conceived as an auxiliary power unit (APU), it was soon adapted to aircraft propulsion, and found a niche as a powerplant for turboshaft-driven helicopters in the 1950s. Artoustes were licence-built by Bristol Siddeley (formerly Blackburn) in the UK, Hindustan Aeronautics Limited in India, and developed by Continental CAE in the USA as the Continental T51. Power is typically in the 300 kW (400 hp) range.

General characteristics

  • Type: Turboshaft
  • Length: 1,440 mm (56.7 in)
  • Diameter: 545 mm (21.5 in) - height, 390 mm (15.4 in) - width
  • Dry weight: 115 kg (253.5 lb) - dry

Performance

  • Maximum power output: 500 hp (372.85 kW) at 34,000 rpm for take-off
  • Fuel consumption: 153 kg (337.3 lb)/hour at maximum continuous power
  • Power-to-weight ratio: 3.24 kW/kg (1.972 hp/lb)

Components

  • Compressor: Single stage centrifugal
  • Combustors: Annular combustion chamber
  • Turbine: Three stage turbine
  • Fuel type: Aviation kerosene to AIR 3405
  • Oil system: Oil grade AIR 3512, pressure lubrication