Continental Model 320
In 1947, commissioned by the Air Ministry, Turbomeca begins the design of a small gas turbine. This gas turbine, TT 782, became the TR 01. The first test application, under the name Piméné, was in a modified Sylph glider on 14 July 1949. The Palas, then Marbore I and II followed in 1950.
The Turbomeca Palas is a diminutive centrifugal flow turbojet engine used to power light aircraft. An enlargement of the Turbomeca Piméné the Palas has a turbofan with a centrifugal compressor stage, combustion chamber with an annular fuel distribution by injection of a wheel, and having a turbine stage. Two versions have been put on the market, the first (I) delivering 150 kgf and the second (II) delivering 160 kpg.
With an annular fuel distribution by the injection of a wheel, this wheel is driven by the turbine shaft which is itself fixed to the compressor. At its periphery is formed a number of leads through which the fuel flows. When fuel is introduced into the interior of the wheel, it is vaporized and discharged in the combustion chamber by the centrifugal force. The fuel flow is regulated by a bypass valve.
The compressor is a single-stage centrifugal, with a compression ratio of 3.95 / 1 and a irflow of 3.2 kg / sec. The turbine stage has 24 (or 25) blades. It is preceded by a stator equipped with a twenty entrys. Kerosene (Jet A1) is provided by a Turbomeca pump of 4 kg. / Cm ² maximum pressure.
It can be equipped with an electric starter Air Equipment (24 volt) or ramp start compressed air. Ignition is via two ignitors and the later versions were equipped with an injection to start directly on Kerosene.
Three anchor points, two above the compressor, behind the combustion chamber, are provided for mounting.
The Palas was 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.
BlackBurn Palas 600
Length: 1.2 m (47.25 in)
Diameter: 405 mm (16 in)
Dry weight: 72 kg (159 lb)
Compressor: Single-stage centrifugal
Combustors: Annular with rotary fuel injection
Turbine: Single-stage with 24 or 25 blades
Fuel type: Jet A1
Maximum thrust: 1.6 kN (353 lbf) static to 33 800 rpm
Rated normal util: 130 kgp
Overall pressure ratio: 3.95:1
Turbine inlet temperature: 700°C
Fuel consumption: 0.117 kg N-1 h-1 (1.15 lb lbf-1 h-1 )
Fuel burn A Rated normal: 1.13 kg / kgp / hr
Thrust-to-weight ratio: 22.2 N kg-1 (2.26 lbf lb-1)
Turbine rated speed: 33 800 rpm
Temperature before turbine: 700 ° C.
Temperature after turbine: 600 ° C.