GB735570A - Improvements relating to combustion equipment of gas-turbine engines - Google Patents

Abstract

735,570. Generating combustion products under pressure. ROLLS-ROYCE, Ltd. Sept. 11, 1953 [June 16, 1952], No. 15165/52. Class 51 (1). In a gas turbine engine comprising reheat combustion equipment downstream of a turbine stage, the equipment includes a flame stabilizer so arranged that in operation a surface area thereof acquires a temperature which is substantially higher than that of another part of the stabilizer and substantially higher than that of the exhaust gas leaving the turbine. The reheat equipment may be used in the jet pipe of a jet propulsion engine or between turbine stages in the case of an engine with a multi-stage turbine. Pilot fuel injectors 16, 17, Fig. 2, are fed with fuel from a supporting pipe 18, and main fuel injectors spraying fuel upstream are in the form of a ring manifold 19 fed with fuel from a further pipe 20. Pilot injector 16 is housed in a conical baffle 21 disposed with its concavity facing downstream. A flame stabilizing ring 22, Figs. 2 and 3, of V-section comprises an insert or inserts 23 of ceramic material overlapping the edges of the ring and' conveniently free for expansion relative to the ring. The ceramic inserts, being poor thermal conductors, become heated to elevated temperature by the combustion of fuel. Alternatively or additionally, the edges of the ring 22 may be provided with elongated fingers in a manner ensuring poor thermal conduction from the fingers to the ring itself. Electrical heating may be provided. In a modification, the flame stabilizer comprises a number of conical or dished baffles 24, Fig. 5, each having an annular ceramic insert or, as shown, a number of inserts 25 forming an annulus which preferably overlaps the free edge of the bafHe. As in the previous construction, projecting fingers or heating elements may be provided. Fuel is injected at a location upstream of the baffles, or in an upstream direction from a downstream location.