GB472820A - Improvements in the cooling of engines particularly for aircraft - Google Patents

Abstract

472,820. Cooling aero-engines. ELLOR, J. E., and PARAVICINI, T. P. DE. March 26, 1936, No. 9064. [Class 4] The cooling means of an aero-engine are placed in a duct which has one or more entrances and one or more exits open to the air through which the vehicle is travelling in positions in which such air is at higher pressure than the' static pressure of the surrounding air either by reason of the passage of the aircraft or by reason of such passage in combination with the airscrew slipstream, and the positions being such that the external pressures at entrance and exit of the duct are substantially the same whatever the speed of the vehicle, the air being caused to flow through the duct by mechanical means and discharged therefrom at low velocity. In one form, Figs. 1 and 2, an engine nacelle A is mounted on a wing A<2> in which is formed a duct B<1> having an intake at B and an exit of larger area at E, both formed in the leading edge. A radiator D<1> is arranged in the duct and air is circulated therethrough by a fan D driven by the engine or by separate power means. The engine exhaust manifold may discharge into the duct or finned exhaust pipes be led therethrough, and the engine may aspirate air for combustion from the duct. In a modification, Fig. 3, openings in the leading edge of a wing F<2> open into ducts G, G<1> leading into the interior of cowling J<1>. The air is circulated by fans G<2>, G<3> and escapes at an annular opening J after passing over crankcase H, cylinders H<1> and exhaust collector ring H<2>. The area of opening J is greater than the combined areas of openings F, F<1>. Ring H<2> may be finned or the exhaust gases may be discharged directly into the cowling.