GB1411123A - Integral turbo-compressor shock wave engine - Google Patents

Abstract

1411123 Gas turbine plant; pressure exchanges GENERAL POWER CORP 18 Oct 1972 [21 Oct 1971] 48075/72 Headings F1G and F1N The invention relates to a gas turbine engine comprising a rotor provided with rotor chambers in which both compression and expansion occur, the compression being effected by shock waves. The engine comprises a rotor 17 provided at its periphery with blades 27 which define rotor chambers 18 having divergent discharge nozzles 38. The rotor rotates within stator structure 29 which is formed to provide a series of inlet and outlet ports, viz. an air inlet port 12, a combustion gas inlet port 31, a gas exhaust port 19 and a compressed air discharge port 32; the stator is also formed with a series of hot gas discharge ports 34E, 35E, 36E, 37E and with hot gas re-entry ports 34R, 35R, 36R, 37R. The air inlet port 12 is provided with a series of guide vanes 13 which may be angularly adjustable. Air is supplied to the inlet port by means of a blower 15 and inlet passage 11, the air being compressed in the rotor chambers 18 by a series of shock waves as indicated in Fig.2 at 44, 50 and a reflected shock wave 51. The air so compressed is discharged through outlet port 32 and passes through chamber 33 and passage 55 to a combustion chamber 22 which comprises a fuel injector 24 and an igniter 25. The combustion gases so generated pass to gas inlet port 31 and so into the rotor chambers 18, the air and gas interface being as indicated at 48, Fig.2. The gases discharge from the rotor chambers 18 through the nozzles 38 thereby driving the rotor. The gases discharge through the ports 34E.... and are re-directed into the rotor chambers through re-entry ports 34R.... The gases finally discharge from the rotor chambers through nozzles 38 into the outlet 19 and to exhaust passage 20. The manner in which the shock compression is achieved is explained in detail. The engine may be controlled by means of members 78, 79, 80, Fig.4 which are disposed adjacent the trailing edge of the combustion gas inlet port 31, adjacent the trailing edge of the compressed air outlet port 32, and adjacent the leading edge of the compressed air outlet port 32, respectively, the members being movable so as to vary the areas of the ports. Other arrangements of control members associated with the ports are described. The compressed air passing through the passage 55 may be pre-heated in a heat exchanger 56 through which the exhaust gases are discharged as indicated in Fig.4. The engine may be started by utilizing air under pressure in container 59, the air passing to combustion chamber 22; the air container is refilled by tapping air from the passage 55 through line 58. The engine may be designed to provide shaft power or so as to provide jet thrust. Also any form of heating may be utilized and the cycle may be open or closed.