Patent GB-829132-A (GB)
Title: Improved fuel burning means for a gaseous-fluid propulsion jet
Inventor: STOKES MORRIS AMOS
IPC: F23R3/00
Filed: 1957-03-20
Abstract: 829,132. Generating combustion products under pressure. ARMSTRONG SIDDELEY MOTORS Ltd. March 7, 1958 [March 20, 1957], No. 9085/57. Class 51 (1). In combustion equipment for a gaseousfluid propulsion jet comprising an axiallydisposed flame stabilizer casing having at its upstream end an annular arrangement of swirlinducing vanes, an additional annular casing is arranged to provide an annular chamber which is axially directed, the downstream end thereof being arranged to lead into the swirl vanes. The upstream end of the annular casing is open to receive during operation a small proportion of the oxygen-containing gases flowing through the jet pipe, at least one fuel supply nozzle for the flame stabilizer being provided adjacent the upstream end of the chamber, so that in operation, fuel and oxygen-containing gases are mixed in the chamber, the whole of the mixture then passing between the swirl vanes into the stabilizer casing. In Fig. 1 the exhaust cone 12 is supported within the jet pipe 11 by means of radial struts 13, and the downstream end of the exhaust cone is formed as an integral structure comprising an inner convergent wall 14, an outer convergent wall 16 and axiallydirected radial vanes 17 therebetween, the two walls 14, 16 forming an annular mixing chamber of diminishing cross-sectional area in the downstream direction. A flame stabilizer casing 22 is annularly spaced and supported from a cylindrical wall 15 by a plurality of swirlinducing vanes 28, the casing 22 forming a continuation of the outer wall 16. Radiallyextending trough members 23, open at their downstream ends, are disposed around the stabilizer casing 22 to act as flame stabilizers for the main combustible mixture flowing past the outside of the casing 22. Fuel is supplied through a pipe 34 to a fuel manifold 32 which is supported by means of pivoted links 31 from a ring member 29 which is clamped between wall 16 and mounting ring 24. The fuel manifold 32 supplies nozzles 35 disposed in line with the trough members 23, also a number of circumferentially-spaced pipes 36 from which fuel is injected as shown by the arrows 37 towards the open upstream end of the annular mixing chamber 14, 16. Combustion may be initiated by a streak ignition system. In Fig. 2, the annular mixing chamber is formed between an inner bullet-shaped member 44 and an outer cylindrical casing 45 swirl-inducing vanes 46 being formed integrally with the bullet member 44 and an outer ring portion 43. The stabilizer casing 39 is supported by means of radial webs 40 from the jet pipe 41, three trough-shaped members 42 being carried on the outside of the casing. The bullet member 44 and casing 45 are supported at the upstream end of the stabilizer casing 39. An annular trough member 51 is supported around the downstream end of the casing 39 by means of pivoted links 51a from the jet pipe 41. A fuel manifold 52 is also supported around the casing 39 by means of links 53 connected to the radial webs 40, fuel being injected through nozzles 58 in a downstream direction. Fuel is also supplied through pipe 48 to the duct 49 in the bullet member 44, fuel being injected into the annular mixing chamber 44, 45 through outlet 50. Combustion is initiated by means of an igniter 59 disposed within the casing 39. The invention is applicable to after-burner or reheat equipment of gas-turbine engines, also to ramjet engines.