GB792910A - Reaction turbines - Google Patents

Abstract

792,910. Turbines. DE HAVILLAND ENGINE CO., Ltd. May 19, 1954 [June 19, 1953], No. 17119/53. Class 110 (3). A reaction turbine comprises a hollow rotor, means for supplying to the rotor at or near its axis of rotation a liquid which can be decomposed catalytically to produce gaseous decomposition products, pervious catalytic material within the hollow interior of the rotor for decomposing the liquid, and discharge nozzles at or near the periphery of the rotor directed substantially tangentially and through which the gaseous decomposition products are discharged to impart a driving torque to the rotor. In Fig. 1 the rotor comprises a flange 14 formed on one end of a shaft 11 and a disc 15 bolted to this flange and provided with perforated annular projections 16, 17. The space between projections 16, 17 is filled with catalyst material 18, e.g. silver gauze, capable of decomposing concentrated hydrogen peroxide. A rod 22, axially movable within a supply pipe 20, is provided with a metering land 23 which co-operates with a port 24 to control the supply of hydrogen peroxide to the interior of the rotor. In operation hydrogen peroxide is supplied to end chamber 21 and passes through pipe 20 and port 24 to the interior of the rotor where it is decomposed by the catalyst 18 into steam and oxygen which produces a reaction on the nozzles 28 tending to rotate the rotor. Control of the turbine speed is exercised by adjusting the metering rod 22 and thus controlling the supply of hydrogen peroxide; this may be effected by a governor driven by the turbine controlling the pressure of a fluid contained in a bellows 29. The exhaust from the turbine may be allowed to escape, or when the turbine forms part of a rocket motor the exhaust may be collected in a discharge duct and fed into the combustion chamber of the rocket motor where its oxygen content can be used for the combustion of some of the fuel.