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Turbomeca Artouste / Marcadau


Turbo-Artouste-IIIB
Turbomeca Artouste IIIB

 

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 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.

 

Variants:
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 1300 kW (402 hp) through a 2.3:1 reduction gearbox.

 

Applications:
Artouste -
Aérospatiale Alouette II
Aérospatiale Alouette III
Aerospatiale Lama
Aerotécnica AC-14
Atlas XH-1 Alpha
IAR 316
IAR 317
Handley Page Victor - as APU
Hawker Siddeley Trident - as APU
Piasecki VZ-8 Airgeep
Vickers VC10 - as APU
SNCASO Farfadet

 

Marcadau -
Morane-Saulnier Epervier

 

Specifications:
Artouste IIC
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
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
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)

 

 

 

 

 


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