Patent GB-882072-A (GB)
Title: Improvements in equipment for burning fuel
Inventor: JAMISON ROBIN RALPH
IPC: F23R3/00
Filed: 1957-01-29
Abstract: 882,072. Generating combustion products under pressure. BRISTOL SIDDELEY ENGINES Ltd. Jan. 29, 1958 [Jan. 29, 1957], No. 3184/57. Class 51 (1). [Also in Group XXVI] Combustion equipment for example of a ramjet or of a reheat chamber of a gas-turbine jet-engine comprises a duct 1, a core member 5 in the duct having a hollow rear end portion 8 constituting a pilot combustion zone open at its downstream end, a plurality of hollow vanes 10 open at each end extending longitudinally along the rear part of the core member in the annular passage between the core and the duet, each vane having two internal partitions dividing the hollow interior into front and rear chambers and a middle chamber, openings being provided in the wall of the core member connecting the front and rear chambers with the pilot combustion zone. An igniter is supported in the middle chamber of each vane, openings being provided in the wall of the core member whereby flame from the igniter may be projected into the pilot combustion zone, and means are provided for injecting fuel into the pilot combustion zone and into the passages between each adjacent pair of hollow vanes. The invention is shown applied to a ram-jet engine, the core member 5 being disposed within the outer duct 1 to form an annular gas flow passage 7 therebetween. Three hollow vanes 10 are radially disposed at the downstream end of the core member, the vanes being open at the upstream and downstream ends 11, 12. Partition members 13, 14 are disposed within the hollow vanes forming chambers 15, 16, 17. Air enters the upstream chamber 16 through the span inlet edge 11 and passes through openings 18 in the wall of the core member into the manifold chamber 19, the air then passing through swirl vanes 23 into the pilot combustion zone 9. Fuel is supplied to this zone through duct 21 and nozzle 22, and ignition is effected by means of cartridges 27, two of which are disposed in each middle chamber 15, the ignition flames being projected through openings 29 in the core member. The pilot combustion gases discharge into the rearward chambers 17 and issue therefrom through the open downstream ends 12. A V-section flame stabilizing ring 25 interconnects the open downstream ends 12 of the vanes. An outer wall 35 covers the open tips of the vanes 10 being supported from the duct 1 by means of bolts 37. Fuel is supplied to the main air flow passages between adjacent pairs of vanes 10 through injectors 52, 53 which direct fuel upstream and downstream respectively. The injectors 52, 53 are mounted on brackets 50 supported one on either side of radial projections 39 which are formed integrally with the centre-piece 20 and the partitions 13, one projection 39 being disposed between each adjacent pair of vanes 10. Each projection 39 forms part of a fin 40 which is tapered at both the leading and trailing edges and extends between the core member 5 and the duet 1. The duct 1 is secured to the fins 40 by means of bolts 43 some of which screw into holes tapped in the projections 39 and others of which screw into holes 44 tapped into the forward part 45 of the fin, the parts 45 being made as a unitary light alloy casting with the leading part 46. Specification 794,010 is referred to.