GB802477A - Improvements in hot air turbines - Google Patents

Abstract

802,477. Gas turbine plant. JOHNSTON, J. Oct. 2, 1956 [Oct. 3, 1955], No. 28046/55. Class 110 (3). [Also in Groups XII and XXIX] In a gas turbine plant of the type in which jets of fuel are injected into a mechanically produced stream of air, and in which the fuel ignition is such as to cause successive explosions in the stream, the flow passage ahead of the turbine divides into two branches, one of which passes through a device for preventing back flow and then through a combustion chamber and ends in a nozzle which discharges centrally into the other branch, the passage then continuing as a single straight passage. In the intermittentcombustion gas turbine engine shown, centrifugal compressor blading 6 supplies air through a tangential passage 13 to a combustion chamber 14. Fuel is supplied through an injector 16 and ignited by a plug 17. An aerodynamic valve 15 at the inlet to the flame tube 21 of the combustion chamber opposes back flow during combustion. After leaving the flame tube, the combustion gases are joined, at an injector-like portion 20 of the flow passage, by air which has by-passed the flame tube, and flow tangentially into an annular passage 18. In rotating around the passage 18, the gases acquire a uniform condition free from pulsation before entering inward-flow turbine blading 7. The blading 6, 7 are arranged on opposite sides of a common rotor.