GB1077955A - Gas turbine jet propulsion units for aircraft - Google Patents

Abstract

1,077,955. Deflecting propulsive jets. BRISTOL SIDDELEY ENGINES Ltd. June 5, 1964 [May 16, 1963], No. 19576/63. Heading B7G. [Also in Division F1] A gas turbine jet propulsion unit comprises low and high pressure compressors, 5 and 2, combustion equipment 8 and high and low pressure turbines 4 and 7, the high pressure turbine 4 driving the high pressure compressor 2 through shaft 3, the low pressure turbine 7 driving the low pressure compressor 5 through shaft 6 and the gases from the low pressure turbine discharging through a rearwardly directed nozzle 10. Only a portion of the air from the low pressure compressor 5 passes to the high pressure compressor 2, the remaining portion passing to two or more rearwardlydirected air passages, part of this air passing to at least one " cold " propulsion nozzle and the remaining part being delivered to the inlet or inlets of one or more auxiliary engines of the gas turbine type arranged to discharge their exhaust gases through one or more rearwardly directed auxiliary " hot " propulsion nozzles. In Figs. 1 and 2, four rearwardly-directed air passages 13, 14, 15 and 16 are provided, two of these passages 13 and 15 terminating in " cold " propulsion nozzles 17, while the other two passages 14 and 16 have auxiliary gas turbine jet engines 18 disposed therein, each engine comprising compressor 19, combustion equipment 21, turbine 20 and discharge nozzle 22. Adjustable vanes 23 may be provided in the inlet to the high pressure compressor 2 so as to control the air flow to the compressor and to the passages 13, 14, 15 and 16. The " cold " nozzles 17 may have adjustable flaps to vary the flow area thereof. Also the auxiliary engines 18 may have adjustable inlet guide vanes. In the embodiment of Figs. 3, 4 and 5 (not shown), only two rearwardlyextending passages are provided, the passages comprising laterally extending ducts 26, 27, right-angle bends 30 and rearwardly extending ducts 31. Disposed within the duct portions 31 are auxiliary gas turbine jet engines winch discharge through " hot " propulsion nozzles 36, annular air ducts 37 being disposed around the engines whereby a portion of the air in the ducts 31 may pass to " cold " propulsion nozzles 38. The nozzle 36 may be axially movable, Fig. 5 (not shown), whereby air flow through the duct 37 may be controlled. The duct portions 31 may be swung pivotally, Fig. 3 (not shown), so that air discharges rearwardly directly from the bends 30. The bends 30 may be mounted for angular movement whereby the air and gases may be discharged downwardly instead of rearwardly.