GB471368A - Improvements relating to the propulsion of aircraft - Google Patents

Abstract

471,368. Propelling aircraft by fluid reaction. WHITTLE, F. March 4, 1936, No. 6505. [Class 4] In a fluid reaction propulsion system for aircraft, the output from an air compressor is divided into two streams, a first stream which is passed out through a propulsion nozzle and a second stream which supplies an internal combustion engine, the compressor being driven by a gas turbine supplied wholly or partly by the effluent gas from the engine. In one form, Fig. 1, twin nacelles 52 are provided each having at its mouth a compressor 50 and a jet 52a at its trailing end. Intermediate the two nacelles is arranged a multi-stage compressor of the kind described in Specification 456,976, [Group XXVI], the outlet of which is led to the delivery chamber 60 of a turbine driving the compressor shaft 61, a combustion chamber being disposed in the passage indicated by arrow 59. The combustion effluent expands through the vanes of turbine rotor 62 and passes to the intake of a turbine 55 driving compressor 50. In another form, Fig. 2, a compression ignition engine 34 drives a centrifugal compressor 35 supplying part of its air output to the engine and the remainder to a turbine 33 driving a compressor 31. The exhaust products of engine 34 discharge into the intake of turbine 33 and the effluent gases from the latter discharge into the atmosphere through a rearwardly facing outlet 39. The apparatus described mav derive some or all of the intake air from the boundary layer at any part of the aircraft structure. Specification 456,980 also is referred to.