GB898368A - Improved combustion chamber - Google Patents

Abstract

898,368. Generating combustion products under pressure. ROLLS-ROYCE Ltd. June 15, 1960. [June 23, 1959], No. 21576/59. Class 51 (1). [Also in Group XXVI] An annular combustion equipment such as for a gas turbine engine comprises an air inlet and a combustion gas outlet which are disposed of the inner periphery of the annular equipment, the equipment comprising also an annular flame tube to which combustion air is supplied through an annular duct which extends along one side only of the flame tube. The combustion equipment shown is disposed between an air compressor 13 and a turbine 15, the air inlet to the combustion equipment being shown at 11 and the combustion gas outlet at 12. The combustion equipment comprises an annular flame tube 24, 28 disposed within a casing 17, a series of channel-section members 20 being disposed circumferentially so as to form the outlet from the annular flame tube. The channel members 20 have holes 21 in their side walls through which dilution air flows to mix with the combustion gases. The channel members have " keel " portions 20<SP>1</SP> by which they are supported from the inner tubular wall 22 and which in turn support three concentric annular vanes 23. The inner flame tube wall 24 is curved and projects into the air inlet and divides the air stream into two parts, viz. combustion air and dilution air. The combustion air flows through the annular passage 25 between the flame tube wall 24 and the outer casing 17 and a portion thereof enters into the combustion space 16 through a series of apertures 33 provided in the portion of the flame tube wall indicated at 3. Fuel is supplied through injectors 34 and the resulting combustion gases discharge through the channel members 20 to the inlet nozzle guide vanes 14 of the turbine 15. The dilution air stream is guided by the vanes 23 and enters the channel members 20 through the apertures 21, there mixing with the combustion gases and cooling them. The remaining portion of air from the passage 25 passes around the flame tube and flows along the other wall 28 thereof so as to cool it, the air finally discharging into the combustion gases within the channel members 20. The object of the invention is to provide a vertical lift engine of reduced axial length which may be mounted vertically within an aircraft wing.