GB800512A - Liquid fuel combustion chambers - Google Patents

Abstract

800,512. Generating combustion products under pressure. LUCAS (INDUSTRIES), Ltd., J. Jan. 2, 1956 [Jan. 3, 1955], No. 50/55. Class 51 (1). Combustion equipment for a gas turbine engine, a jet propulsion engine, an air heater or industrial furnace comprises an outer easing o to which air is supplied from a blower, and a flame tube disposed therein, the flame tube comprising a pair of concentric cylindrical sheetmetal parts a and c, the inner one a which is shorter than the outer one c, having at its upstream end a plate b and forming the primary combustion zone which is open to the secondary combustion zone formed by the outer part c. The parts a and c are formed at their upstream ends with extensions d and e of substantially conical form, the two extensions forming a narrow annular air passage leading to the secondary combustion zone. A coaxial air duct g, g<SP>1</SP> is also provided extending through the plate b and having at its discharge end a plurality of radial outlets h through which air is supplied to the primary combustion zone. A plurality of liquid fuel injectors k is disposed on the plate b forming the upstream end wall of the primary combustion zone. An annular baffle f is disposed within the secondary combustion zone to promote toroidal swirling of the air admitted thereto. The part g of the coaxial duct g, g<SP>1</SP> is of smaller diameter than the part g<SP>1</SP> so as to provide a narrow annular air passage i leading to the central region of the primary combustion zone. Air entering through the openings p in the inner nose-piece d flows between the part a and the plate b to form a thin film of cooling air over the inner surface of the part a.