Turbomeca Artouste
From Infogalactic: the planetary knowledge core
| Artouste | |
|---|---|
| 300px | |
| 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 |
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.
Contents
Variants
- Artouste I
- Artouste II
- Artouste IIB
- Artouste IIC
- 373 kW (500 hp)[1]
- Artouste IIC6
- 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
- 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
Engines on display
A Turbomeca Artouste is on public display at:
- The Helicopter Museum (Weston)
- Aviodrome - Lelystad Airport - The Netherlands
Specifications (Artouste IIC)
Data from Jane's All the World's Aircraft 1962-63[1]
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
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
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)
See also
- Related development
- Related lists
References
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- Notes
- Bibliography
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