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Turbomeca Palas

From Wikipedia, the free encyclopedia

Palas
Sectioned Turbomeca Palas
Type Turbojet
National origin France
Manufacturer Turbomeca
Major applications Miles Sparrowjet
Short SB.4 Sherpa
Developed from Turbomeca Piméné

The Turbomeca Palas is a diminutive centrifugal flow turbojet engine used to power light aircraft. An enlargement of the Turbomeca Piméné, the Palas was designed in 1950 by the French manufacturer Société Turbomeca,[1] and was also produced under licence by Blackburn and General Aircraft in the United Kingdom and Teledyne Continental Motors in the United States as the Continental Model 320.

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  • Turbomeca Marbore II turbojet engine from 1952

Transcription

Applications

Douglas DC-3 of Aigle Azur (France) arriving at Manchester Airport on 3 April 1953. It is equipped with a ventral Turbomeca Palas booster jet engine for "hot and high operations".

Specifications

Data from Aircraft engines of the World 1953 [2]

General characteristics

  • Type: Turbojet
  • Length: 1,200 mm (47 in)
  • Diameter: 408 mm (16.1 in)
  • Dry weight: 72 kg (159 lb)

Components

  • Compressor: single-stage centrifugal
  • Combustors: annular with rotary fuel injection
  • Turbine: single-stage with 24 or 25 blades
  • Fuel type: Jet A1
  • Oil system: dry sump with Turbomeca gear pump at 3.0 bar (43 psi)

Performance

Take-off: 1.6 kN (350 lbf)
Max Continuous: 1.27 kN (285 lbf)
Cruising: 0.98 kN (220 lbf)
TIT: 1,123.15 K (850 °C)
JPT: 973.15 K (700 °C)

See also

Related lists

References

Notes
  1. ^ Gunston 1989, p. 169.
  2. ^ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 162–163.
Bibliography
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9

External links

Wikimedia Commons has media related to Turbomeca Palas.
This page was last edited on 1 December 2022, at 00:15
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