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.
Artouste I
Artouste II
Artouste IIB
Artouste IIC
373 kW (500 hp)
Artouste IIC6
Artouste IIIB
410 kW (550 hp)
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.
Artouste
Aérospatiale Alouette II
Aérospatiale Alouette III
Aerospatiale Lama
Aerotécnica AC-14
Atlas XH-1 Alpha
Handley Page Victor - as APU
Hawker Siddeley Trident - as APU
IAR 316
IAR 317
Nord Norelfe
Piasecki VZ-8 Airgeep
SNCASO Farfadet
Vickers VC10 - as APU
Marcadau
Morane-Saulnier Epervier
A Turbomeca Artouste is on public display at:
The Helicopter Museum (Weston)
Aviodrome - Lelystad Airport - The Netherlands
Data from Jane's All the World's Aircraft 1962-63.
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)
Compressor: Single-stage centrifugal
Combustors: Annular combustion chamber
Turbine: Three-stage axial
Fuel type: Aviation kerosene to AIR 3405
Oil system: Oil grade AIR 3512, pressure lubrication
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)
