GB884646A - Improvements relating to gas turbine power plants - Google Patents

Abstract

884,646. Gas turbine plants; axial-flow compressors. DAIMLER-BENZ A.G. Nov. 24, 1959 [Nov. 26, 1958], No. 39837/59. Classes 110 (1) and 110 (3). In a gas turbine power plant of the type in which a number of coaxial rotors each comprise radially inner compressor blading, radially outer turbine blading, and radially therebetween a rotor ring separating the compressor flow from the turbine flow, which flows are in opposite directions, one of the rotors being secured to a power output shaft which may carry an airscrew, the other rotors being individually rotatable, consecutive rotors being contra-rotational, the compressor is constructed as a supersonic compressor. In Fig. 1, air enters the inner passage and is compressed in the compressor which comprises rotor blades 12<SP>2</SP> and 12, the air then entering combustion chamber 16 where fuel is burned, the combustion gases then flowing through the turbines which comprise rotor blades 11, 11<SP>1</SP>. The blades 11 constitute the compressor-driving turbine and they are mounted radially outwardly of the compressor blades 12, the blades 12 being secured to rotor discs L 1 which are independently rotatably mounted on a stationary shaft 14. The blades 12 and the blades 11 associated therewith are separated by a ring member 13. The blades 11<SP>1</SP> constitute a separate power turbine and they are mounted radially outwardly of compressor blades 12<SP>1</SP>, the blades 12<SP>1</SP> being mounted on a rotor disc L 1 <SP>1</SP> secured to a shaft 15 which may drive an airscrew through reduction gearing. The blades 12<SP>1</SP> may act as a rotating inlet guide vane assembly. The blades 11<SP>1</SP> of the separate power turbine are low-pressure blades. In a second embodiment similar to Fig. 1, and shown in Fig. 4, the power turbine L 4 1 is disposed adjacent the combustion chamber so that it is a high-pressure turbine, the compressor blades associated therewith constituting a rotating outlet guide vane assembly. The air inlet is indicated at E 4 and the combustion gas outlet at A 4 . The airscrew driven by the power turbine is in this case of the pusher type. In a further embodiment the engine is similar to that shown in Fig. 4 but the engine is mounted with combustion chamber forward so that the airserew is of the tractor type. The air intake to the compressor is through lateral openings and the gas discharge through an annular duct which merges into a central cylindrical outlet, the air inlet ducts crossing the annular gas outlet duct. Leakage of combustion gases from the turbine passage to the compressor passage is prevented by causing air from a higher-pressure compressor stage to flow through the ring members 13 to a chamber between a ring member 13 and a corresponding ring member of the stator guide blades. The plant may alternatively be of the hot-air type having either an open or closed circuit, in which the air from the compressor is heated indirectly in a heat exchanger.