GB1299454A - Combustion chamber for a gas turbine engine - Google Patents

Abstract

1299454 Gas turbine engine combustion equipment CURTISS-WRIGHT CORP 23 Dec 1969 62575/69 Heading F1L [Also in Division F4] The invention relates to combustion equipment for gas turbine engines comprising a fuel vapourizing tube extending into the chamber, the tube being open at its upstream end for inflow of air and having at its downstream end a single opening for discharge of air and vaporized fuel in an upstream direction, fuel being admitted into the tube through a duplex type atomizing spray nozzle which discharges atomized liquid fuel on to the inner wall surface of the tube at two different portions. In Fig. 2, the combustion chamber comprises inner and outer walls 16, 17 and an upstream end wall 18 formed with air inlet openings 19. A vaporizing tube 21 projects through the end wall into the chamber, the downstream end of the tube having a hemispherical cap 22 disposed adjacent thereto whereby air and vaporized fuel are discharged in an upstream direction as indicated. A fuel atomizing nozzle 24 projects into the upstream end of the tube, the nozzle comprising an inner duct 26 and an outer duct 27, the spray cones being indicated at 28, 29. In a second embodiment the vaporizing tube is of J-form. The atomizing nozzle shown in Fig. 4 comprises an inner tube 26 and an outer tube 27, the inner tube having a conical end and a plug member 34 which define passages 36, 37, an annular manifold 38 and discharge ducts 39. The end of the outer duct is also conical so as to form a conical fuel spray from the outer passage 41. In a second arrangement fuel is discharged from the outer passage 41 through radial outlets.