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| TURBOMECA PALAS | ||
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SOCI�T� TURBOMECA. The Soci�t� Turbomeca was formed in 1938 by MM. Szydlowski and Planiol to develop blowers, compressors and turbines for aeronautical use. In 1947 the Company began the development of gas-turbines of low power for driving aircraft auxiliaries and for aircraft propulsion. Licences for Turbomeca gas-turbines have been negotiated with the Blackburn and General Aircraft, Ltd. in England, and the Continental Aviation & Engineering Corporation in the United States. |
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Type Turbojet with single-stage compressor, annular combustion chamber with rotating fuel delivery ring and single-stage turbine. Two version have been product. the first with 150 Kg. (330 lb.) and the second with 160 kg. (353 lb.) Compressor Single-stage centrifugal compressor. Compression ratio 3.95 : 1. Air mass flow 3.2 kg. /sec. (7.05 lb./sec.). Combustion chamber Annular, with rotary fuel injection. The fuel ring, around the periphery of which are a number of vents, is attached to the shaft connecting compressor and turbine dises and revolver with it. Fuel is fed into the inside of the ring and is vented by centrifugal force, being vaporised in the process. Fuel delivery at low thrust settings regulated by by-pass valve. Turbine Single-stage single-piece turbine with 24 or 25 blades preceded by stator with twenty air-cooled valve. Turbine r.p.m. 33,800. Gas temperature before turbine 700°C., after turbine 600°C. Fuel Pump Turbomeca. Maximum pressure 4 kg./cm.2 (57 lb./sq. in.). Fuel Kerosene (Jet A1). Oil Grade Air 3512 Starter Air Equipement 24 volt electric or compressed-air starter. Two igniter plugs. Mounting Three mounting pans, two on compressor casing and one on underside of combustion chamber. Dimensions Length 1,200 mm. (47.25 in.). Diameter 405 mm. (16 in.) Weight dry 72 kg. (159 lb.). Performances ratings Max. T.O. (static) 160 kg. (353 lb.) at 33,8000 r.p.m. Normal thrust 130 kg. (287 lb.). Fuel consomptions At max. T.O. 1.17 kg./kg. s.t./hr. (1.17 lb./ lb. s.t./hr.). At normal thrust 1.13 kg./kg. s.t./hr. (1.13 lb./lb. s.t./hr.). |
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Histoire Les premiers essais du Palas eurent lieu en septembre 1950. Il a été homologué en 1951. Parmi les avions qu'il a propulsé on peut citer : Les SIPA 200 et 300, Les FOUGA Cyclope II et Midget, le Caproni F.5, le Payen PA 49 Katy, Le Miles M-77 SparrowJet, le Short Sherpa SB-4, Les IKARUS 451M, 452M et S451M, le Somers-Kendall SK-1, le CCV6 Canguro Palas et l'AM12 Palas soit 14 appareils. A ceux-ci, il faut ajouter ceux où il fut employé comme réacteurs d'appoints, comme le Curtiss commando C46 (2 sous le fuselage, 1er vol octobre 1952), le Douglas DC-3 (1 sous le fuselage, 1er vol Juillet 1951), le Curtiss commando C46F (2 sous les ailes) et le SO30P Bretagne (2 sous les ailes). S'arrêter là serait oublier l'hydoglisseur Couzinet. |
Compresseur / Compressor |
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Turbine |
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