GB821286A - Improvements in or relating to reheat combustion equipment of jet-propulsion engines - Google Patents

Abstract

821,286. Generating combustion products under pressure. ROLLS-ROYCE Ltd. June 3, 1957 [June 5, 1956], No. 17403/56. Class 51 (1). In a gas-turbine jet-propulsion engine having an exhaust assembly comprising outer and inner walls 15, 16, defining an annular exhaust gas passage, one or more annular walls 18 is or are provided in the exhaust passage each extending downstream from adjacent the turbine outlet so as to divide the exhaust passage into a number of coaxial annular exhaust gas paths 19a, 19b of substantially similar diffusing characteristics, reheat fuel injection means being disposed in the annular exhaust gas passage adjacent the downstream ends of the paths. The intermediate annular wall 18 does not extend axially downstream as far as the inner wall 16 and the reheat fuel injectors are disposed axially between the downstream ends of these two walls. The reheat fuel injectors comprise perforated annular tubes 20a, 20b, 20c, the tubes 20a being disposed in the path of the gases issuing through the annular path 19a, the tubes 20b in the path of the gases issuing from the annular path 19b, and the tubes 20c being disposed radially between the tubes 20a, 20b. Each set of tubes is associated with an annular trough-section flame stabilizer baffle 21a, 21b, 21c, the tubes and baffles being supported from the outer and inner walls 15, 16 by means of struts 22. A baffle 24 is disposed at the downstream end of the inner wall 16 and an igniter or a pilot fuel injector and igniter are disposed within the baffle to effect ignition. The wall 18 is formed in two parts which are notched at their adjoining edges so as to accommodate the supporting struts 17.