Patent GB-987564-A (GB)
Title: Aircraft jet propulsion power plant fuel burning equipment
Inventor: ORCHARD PETER FREDERIC
IPC: B64C29/00
Filed: 1961-03-06
Abstract: 987,564. Gas turbine jet propulsion engines; combustion equipment. BRISTOL SIDDELEY ENGINES Ltd. Feb. 27, 1962 [March 6, 1961], No. 8094/61. Headings F1J and F1L. [Also in Division B7] The invention relates to combustion equipment for burning fuel in air discharged from the low pressure compressor of a gas turbine jet engine of the by-pass type, such air (or combustion gases when fuel is burned in the air) being discharged through nozzles which may be directed either rearwardly to give forward thrust or downwardly to give upward thrust. Such an engine, is shown mounted in an aircraft in Fig. 7 and comprises a low pressure compressor 81, a high pressure compressor 83, main combustion equipment 84, a high pressure turbine 85 and a low pressure turbine 86, the exhaust gases from the turbine 86 discharging through a bifurcated jet pipe 87 at the outlets of which are swivelling nozzles 91 which may be directed rearwardly or downwardly. Air discharged from the low pressure compressor 81 is divided into two streams, one stream passing into the high pressure compressor 83 and the other stream passing through outlet ducts 89 at either side of the engine, the ducts terminating in swivelling outlet nozzles 90 whereby the air may be caused to discharge either rearwardly or downwardly. Arrangements are provided to burn fuel in the air passing through the ducts 89 when the nozzles 90 are directed downwardly, such arrangements comprising a perforated flame tube 88 disposed within each duct. A duct and flame tube is shown in detail in Fig. 1, the duct being of arcuate form at its inlet end 7 and of cylindrical form at its outlet end. The inner wall 18 of the flame tube has a U-shaped member 25 secured -thereto at the radially outer surface at its upstream end, and the upstream end 26 of the outer wall of the flame tube is bent rearwardly and enters the space formed between the walls 18 and 25 so as to form a reversal passage 27. Fuel is discharged from a manifold 22 into a gutter 23 and the resulting fuel and air mixture enters the passage 27 to form a pilot mixture which is ignited in the space 24. Further fuel and air mixture enters the flame tube through the perforations 29 and burns in the combustion space 15. The mixture is guided along the outer surface of the outer wall of the flame tube by a baffle member 31 which also guides a stream of air between the baffle and the outer wall 10 to enter the flame tube as secondary air. Further cooling air also flows in through spaces between the ring members 32. The outlet nozzle 14 is mounted for swivelling in a bearing 13. In a second embodiment, Fig. 3, the inner wall of the flame tube is recessed so that the upstream walls of the flame tube are more nearly parallel. In this embodiment fuel is supplied from manifolds 67, 68, 69, Fig. 5, the fuel from manifold 67 discharging through nozzles 66 as pilot fuel and fuel from manifolds 68, 69 discharging through nozzles 71 and being swept by jets of air under pressure discharging through nozzles 72 from a manifold 70.