Turbomeca Palas
From Wikipedia, the free encyclopedia
The Turbomeca Palas is a diminutive centrifugal flow turbojet engine used to power light aircraft. It was designed in 1950 by the French manufacturer Société Turbomeca, and was also produced under licence by Blackburn and General Aircraft in the UK and Continental Motors in the US.
[edit] Applications
The Palas was used on many small jet-powered aircraft, including the Short Sherpa, Fouga CM130, Miles Sparrowjet, SIPA S-200 and Caproni-Vizzola F.5. Many of these aircaft were little more than powered gliders.
[edit] Specifications
General characteristics
- Type: turbojet
- Length: 1.2 m (47.25 in)
- Diameter: 405 mm (16 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
Performance
- Thrust: 1.6 kN (353 lbf)
- Overall pressure ratio: 3.95:1
- Turbine inlet temperature: 700°C
- Fuel consumption: 0.117 kg N-1 h-1 (1.17 lb lbf-1 h-1 )
- Thrust-to-weight ratio: 22.2 N kg-1 (2.22 lbf lb-1)
