Turbomeca Artouste

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 US as the Continental T51. Power is typically in the 300 kW (400 hp) range.

Artouste
Turbomeca Artouste IIIB
Type Turboshaft
National origin France
Manufacturer Turbomeca
First run 1947
Major applications Aérospatiale Alouette II
Aérospatiale Alouette III
Developed into Continental T51

Variants

Artouste I
Artouste II
Artouste IIB
Artouste IIC
373 kW (500 hp)[1]
Artouste IIC-5
Artouste IIC-6
Artouste IIIB
410 kW (550 hp)[1]
Artouste IIID
Continental T51
Licence production and development of the Artouste in the United States
Turbomeca Marcadau
A turboprop variant, the Marcadau was a development of the Artouste II, producing 300 kW (402 hp) through a 2.3:1 reduction gearbox.

Applications

Artouste
Marcadau

Engines on display

A Turbomeca Artouste is on public display at:

Specifications (Artouste IIIB)

Data from Aircraft engines of the World 1970[2]

General characteristics

  • Type: Turboshaft
  • Length: 1,815 mm (71.5 in)
  • Diameter: ~450 mm (18 in) (casing)
  • Width: 507 mm (20.0 in)
  • Height: 627 mm (24.7 in)
  • Dry weight: 154 kg (340 lb)

Components

  • Compressor: 1-stage axial + 1-stage centrifugal
  • Combustors: Annular combustion chamber
  • Turbine: 3-stage turbine
  • Fuel type: Aviation Kerosene, such as Jet A, Jet A-1 or JP-4
  • Oil system: Pressure spray at 4.6 bar (66 psi) with return

Performance

  • Maximum power output:
  • Take-off power: 437 kW (586 shp) (equivalent) (410 kW (550 shp) + 0.39 kN (88 lbf)) at 33,500 rpm, de-rated
  • Maximum continuous power: 437 kW (586 shp) (equivalent) (410 kW (550 shp) + 0.39 kN (88 lbf)) at 33,500 rpm, to 5,000 m (16,000 ft)

See also

Related development

Related lists

References

Notes
  1. Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
  2. Wilkinson, Paul H. (1970). Aircraft engines of the World 1970 (21st ed.). Washington D.C.: Paul H. Wilkinson. p. 178.
Bibliography
  • Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
  • Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 163.
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