Turbomeca Palouste

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Rolls Royce-Turbomeca Palouste-001.jpg
Rolls-Royce licensed-built Palouste
Type Gas turbine
National origin France
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.[1] 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[edit]

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).[2] 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.[3]

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.[4]


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.[5]


Specifications (Blackburn Palouste)[edit]

Palouste engine fitted to a Sud-Ouest Djinn helicopter

Data from Hobby Gas Turbines[6]and Flight[7]

General characteristics

  • 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


See also[edit]

Related development
Comparable engines
Related lists



  1. ^ Gunston 1989, p.170.
  2. ^ Flightglobal archive - Flight, February 1962 Retrieved: 24 July 2009
  3. ^ Flightglobal archive - Flight, March 1965 Retrieved: 24 July 2009
  4. ^ The Boost Palouste - jet-pack.co.uk Retrieved: 24 July 2009
  5. ^ Bridgman, Leonard (1955). Jane's all the World's Aircraft 1955-56. London: Jane's all the World's Aircraft Publishing Co. Ltd. 
  6. ^ Palouste/Artouste - Hobby Gas Turbines Retrieved: 24 July 2009
  7. ^ 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

External links[edit]