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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

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. Two major versions of the Artouste were produced. The Artouste II family, mainly used in the Aérospatiale Alouette II helicopter, had a one-stage centrifugal compressor and a two-stage turbine, with gearbox-limited power of 300 kW (400 hp). The Artouste III family, mainly used in Aérospatiale's Alouette III and Lama helicopters, had a two-stage axial-centrifugal compressor and a three-stage turbine, with gearbox-limited power of 420–440 kW (560–590 hp).

Variants

Artouste I
Artouste II
Artouste IIB, IIB1: 300 kW (400 hp) for takeoff, 245 kW (330 hp) continuous^[1]
Artouste IIC, IIC1, IIC2, IIC5, IIC6: 300 kW (400 hp) for takeoff, 245 kW (330 hp) continuous^[1]^[2]^[3] (limited by engine gearbox); (Without gearbox limit, ratings are 390 kW (523 hp) for takeoff and 353 kW (473 hp) continuous)^[4]
Artouste IIIB: 420 kW (563 hp) for takeoff, 405 kW (543 hp) continuous (limited by engine gearbox)^[5]^[6]^[3]; (Without gearbox limit, sea level ratings are 640 kW (858 hp) for takeoff and 515 kW (690 hp) continuous)^[5]
Artouste IIIB1, IIID: 440 kW (590 hp) for takeoff, 405 kW (543 hp) continuous (limited by engine gearbox)^[5]^[6]; (Without gearbox limit, sea level ratings are 640 kW (858 hp) for takeoff and 515 kW (690 hp) continuous)^[5]
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

Morane-Saulnier Epervier

Engines on display

A Turbomeca Artouste is on public display at:

The Helicopter Museum (Weston)
Aviodrome - Lelystad Airport - The Netherlands

Specifications (Artouste IIIB)

Data from Aircraft engines of the World 1970^[7]

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)

Overall pressure ratio: 5.2:1
Air mass flow: 4.3 kg/s (9.5 lb/s)
Turbine inlet temperature: JPT 773 K (500 °C) at 33,500 rpm
Specific fuel consumption: 0.46 kg/kWh (0.76 lb/(hp⋅h)) (equivalent)
Power-to-weight ratio: 2.84 kW/kg (1.73 hp/lb) (equivalent)

References

Notes

^ ^a ^b Federal Aviation Administration (FAA) (20 March 2007). "Type Certificate Data Sheet No. E-300".
^ European Aviation Safety Agency (EASA) (1 August 2016). "Type-Certificate Data Sheet No. E.137" (PDF).
^ ^a ^b "Our products: Artouste". TURBOMECA - Safran Group. Archived from the original on 18 December 2008. Retrieved 1 September 2021.
^ Taylor, John W. R., F.R.Hist.S., A.R.Ae.S. (1965). Jane's All the World's Aircraft 1965-66. New York: McGraw-Hill Book Company. p. 460. ISBN 9780531039151.{{cite book}}: CS1 maint: multiple names: authors list (link)
^ ^a ^b ^c ^d Federal Aviation Administration (FAA) (20 March 2007). "Type Certificate Data Sheet E1IN".
^ ^a ^b European Aviation Safety Agency (EASA) (1 August 2016). "Type-Certificate Data Sheet No. E.091" (PDF).
^ Wilkinson, Paul H. (1970). Aircraft engines of the World 1970 (21st ed.). Washington D.C.: Paul H. Wilkinson. p. 178.

Bibliography

Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 163.

[FAA_E-300-1] Federal Aviation Administration (FAA) (20 March 2007). "Type Certificate Data Sheet No. E-300".

[EASA_E.137-2] European Aviation Safety Agency (EASA) (1 August 2016). "Type-Certificate Data Sheet No. E.137" (PDF).

[Turbomeca-3] "Our products: Artouste". TURBOMECA - Safran Group. Archived from the original on 18 December 2008. Retrieved 1 September 2021.

[JAWA65-66p460-4] Taylor, John W. R., F.R.Hist.S., A.R.Ae.S. (1965). Jane's All the World's Aircraft 1965-66. New York: McGraw-Hill Book Company. p. 460. ISBN 9780531039151.{{cite book}}: CS1 maint: multiple names: authors list (link)

[FAA_E1IN-5] Federal Aviation Administration (FAA) (20 March 2007). "Type Certificate Data Sheet E1IN".

[EASA_E.091-6] European Aviation Safety Agency (EASA) (1 August 2016). "Type-Certificate Data Sheet No. E.091" (PDF).

[Wilkinson70-7] Wilkinson, Paul H. (1970). Aircraft engines of the World 1970 (21st ed.). Washington D.C.: Paul H. Wilkinson. p. 178.

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Turbomeca Artouste