GB1002177A - Jet engine for propelling and lifting aircraft - Google Patents

Abstract

1,002,177. Gas turbine jet propulsion plant. SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. July 27, 1962 [Aug. 4, 1961], No. 28863/62. Heading F1J. [Also in Division B7] A jet engine for use in aircraft capable of vertical take-off and landing comprises a rearwardly-directed propulsion nozzle and a downwardly-directed lifting nozzle, the two nozzles branching from a common duct from which by means of a suitable distributing device, gas flow is distributed between the nozzles in any desired proportions, the engine comprising a low pressure compressor or fan disposed within the common duct, the compressor discharging air into a combustion chamber disposed upstream of the point from which the two nozzles branch off. At least part of the power required to drive the compressor is supplied by means external to the duct. The engine shown in Fig. 1 comprises a low pressure compressor or fan 3 mounted within a duct 1, the compressor being driven by a gas turbine 4 which receives gases from a combustion chamber 5, the combustion chamber being supplied with air under pressure from a compressor 12 which is disposed within a separate duct 13. Air passes from the compressor 12 to the combustion chamber 5 through a duct 10 and manifold 9. The compressor 12 is driven by a device 14. The air delivered by the compressor 3 is heated by combustion equipment 6, the resulting combustion gases mixing with gases discharging from the turbine 4, the mixed gases then being further heated in reheat chamber 8 by combustion equipment 7. The flow of gases to the propulsion nozzle 2 and vertical lift nozzle 15 is controlled by a shutter device 16 which is pivotally mounted at 17, three positions of the shutter being indicated at a, b and c. Additional combustion equipment is provided at 18 in the duct leading to the propulsion nozzle 2. The stator blading 3a of the compressor is adjustable. In a second embodiment, the gas flow from the reheat chamber 8 to the vertical lift nozzle is through a series of nozzles 23 from which gas is discharged into a pair of transverse ducts 20 which are open at both ends, the gas discharging from the nozzles producing an ejector effect whereby ambient air is drawn into the ducts 20 at the upper ends and discharged with the combustion gases at the lower ends. The upper ends of the ducts are controlled by pivoted flaps 21 which are pivoted on axes transverse to the aircraft, while the lower ends of the ducts are controlled by pivoted flaps 22 and 25, the pivotal axes of these flaps extending longitudinally of the aircraft. The outlets of the nozzles 23 are controlled by pivotally-mounted shutters 24. Specification 955,013 is referred to.