GB928996A - Gas turbine engine - Google Patents

Abstract

928,996. Generating combustion products under pressure. ROLLS-ROYCE Ltd. Dec. 27, 1961, No. 46352/61. Class 51 (1). [Also in Group XXVI] A gas turbine engine 1 has an exhaust duct within which is mounted a plurality of segmental members each having a channel portion and being movable by power means between an inoperative position in which they merge into a flow defining wall of the exhaust duct and an operative position in which they collectively constitute a substantially annular combustion stabilizing member in the path of the turbine exhaust gases, reheat fuel injector means being disposed upstream of the segmental members. The segmental gutter members 17, having a downstream facing channel portion 18, are mounted within the jet pipe inner wall 16 by arms 21 secured to a pivot 22 mounted in a pair of roller bearings. Each pivot 22 has a flange 25 connected by rod 26 to a piston-rod 27 of a double-acting ram 28. In the inoperative position the members 17 and arms 21 are received in angularly spaced apart recesses in the jet pipe inner wall 16. Cooling air from the low pressure compressor is supplied to a manifold 42 and thence through conduits 43 to the pivots 22. Alternatively, each arm 21 may be loosely mounted on its pivot. An exhaust cone 44 is supported from the jet pipe by struts 45 each of which is aligned with a reheat fuel injector pipe 46. Means may be provided for moving the injector pipe 46 in and out of the path of the exhaust gases. The reheat fuel may be ignited by the ignition of a small quantity of fuel injected into the combustion equipment 12. A catalytic igniter is provided to maintain reheat combustion. Means may be provided for preventing pivotal movement of the gutter members beyond the operative and inoperative positions and for slowing down movement of the members by the use of stops or dashpots.