GB406713A - Improvements in or relating to a method and means for the propulsion of aircraft - Google Patents

Abstract

406,713. Propelling aircraft. CAMPINI, S., 3, Viale Cossica, Milan, Italy. July 30, 1932, No. 22000/33. Divided on 405,634. [Class 4.] In reaction propulsion of aircraft an air intake is of such form and position that the kinetic energy of air which flows into it without substantial change of direction is transformed substantially into pressure energy which is further increased by mechanical compression, the compressed air being subsequently heated and allowed to discharge into the atmosphere so that its total energy is transformed substantially into kinetic energy. In one form, a conical nacelle 28 is detachably connected to an aeroplane body which includes divergent inlets 3, compressors 4, 4<1>, a combustion chamber 5 provided with burners 20 adapted to consume pulverized or liquid fuel by ejector action, and a discharge nozzle 7 controlled by a valve 22. A radiator 25, through which passes cooling water for the engines, is placed between the compressor 4<1> and the chamber 5. The combustion chamber 5 may be lined with sheet metal or refractory material and surrounded by an air space through which air is circulated from its cooler end ; alternatively an internally or externally arranged radiator may be provided for a circulating cooling medium. Combustion may be started by an electric spark or incandescent wire. The nacelle 28 may be hermetically sealed and is released in case of emergency by a handwheel 29 when a parachute descent may be effected. Air is supplied to the nacelle 28 from a liquid air supply or from the compressors. In a modification, the cabin projects into the fuselage the nose of which forms the intake and the size of the discharge nozzle may be controlled by adjustable vanes. The inlets may be provided with an adjustable portion 13, Fig. 2, and with manually or automatically controlled auxiliary inlets 2<1> to facilitate starting.