|Rolls-Royce licensed-built Palouste|
|Manufacturer||Turbomeca, Blackburn Aircraft, Rolls-Royce Limited, Lucas Aerospace|
|Major applications||Sud-Ouest Djinn|
The Turbomeca Palouste is a French gas turbine engine, first run in 1952. Designed purely as a compressed air generator, the Palouste was mainly used as a ground-based aircraft engine starter unit. Other uses included rotor tip propulsion for helicopters.
Design and development
Designed and built by Turbomeca, the Palouste was also built under license in Britain by Blackburn and Rolls-Royce. Originally conceived as an aircraft ground support equipment starter gas generator, it was used also as propulsion for the Sud-Ouest Djinn and other tip-jet powered helicopters.
The Palouste was a very simple unit, its primary purpose being to supply a high flow rate of compressed air to start larger jet engines such as the Rolls-Royce Spey as installed in the Blackburn Buccaneer (this aircraft having no onboard starting system). Air from the centrifugal compressor was divided between external supply (known as bleed air) and its own combustion chamber.
Several British naval aircraft were adapted to carry a Palouste in a wing-mounted pod installation to facilitate engine starting when away from base.
A novel use of a surplus Palouste engine was its installation in a custom-built motorcycle known as the Boost Palouste. In 1986 this motorcycle broke an official ACU 1/4 mile speed record at 296 km/h (184 mph)). The builder modified the engine to include a primitive afterburner device and noted that pitch changes which occurred during braking and acceleration caused gyroscopic precession handling effects due to the rotating mass of the engine.
- Palouste IV
- The gas generator used to power the Sud-Ouest S.O.1221 Djinn and other tip-jet helicopters.
- A development of the Palouste delivering a higher mass flow of compressed air.
Specifications (Blackburn Palouste)
- Type: Gas generator
- Length: 850 mm (33.42 in)
- Diameter: 450 mm (17.72 in)
- Dry weight: 85 kg (187.5 lb)
- Compressor: Single stage centrifugal
- Combustors: Annular combustion chamber
- Turbine: Two-stage axial flow
- Fuel type: Kerosene
- Oil system: Dry sump
- Maximum power output:
- Overall pressure ratio: 3.6:1
- Thrust-to-weight ratio:
- Air output: 0.75 kg/s at 255 kPa (1.65 lb/sec at 37 psi)
- Related development
- Comparable engines
- Related lists
- Gunston 1989, p.170.
- Flightglobal archive - Flight, February 1962 Retrieved: 24 July 2009
- Flightglobal archive - Flight, March 1965 Retrieved: 24 July 2009
- The Boost Palouste - jet-pack.co.uk Retrieved: 24 July 2009
- Bridgman, Leonard (1955). Jane's all the World's Aircraft 1955-56. London: Jane's all the World's Aircraft Publishing Co. Ltd.
- Palouste/Artouste - Hobby Gas Turbines Retrieved: 24 July 2009
- Flightglobal archive - Flight, September 1953 Retrieved: 24 July 2009
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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