GB473341A - Improvements in aircraft - Google Patents

Abstract

473,341. Cooling aircraft engines. ELLOR, J. E., and PARAVICINI. T. P. DE. April 8, 1936, No. 10381. [Class 4] One or more radiators for a liquid-cooled aero-engine are housed inside the leading edge of a wing in one or more ducts to which air is admitted through one or more openings in the leading edge, the air being caused to flow through the radiator or radiators in a direction parallel to the front or main spar, mechanical means being provided to increase the air pressure on the upstream side of the radiator or radiators ; the duct being so shaped as to convert the pressure energy of the airstream leaving the radiator or radiators into kinetic energy and having the discharge outlet into the external air stream at a point of low pressure. In one form, Fig. 2, an engine is mounted within a cowling A<1> which is continuous with the surface of a wing A<2> having spars B, B'. Tubular radiators C, C<1> are mounted in tunnels in front of spar B. Air is led to the radiators through leading edge openings D, D' and circulated by fans E, E<1>. The airstreams passing through the radiators unite at F and discharge through conduits passing respectively above and below spar B<1> and which unite at the trailing side of the spar. The discharge aperture at the trailing edge is variable in area by flaps F<3>. Fig. 3 shows a modification in which a downwardly and rearwardly directed discharge conduit G is provided on the underside of cowling A<1>. In a further modification, Fig. 4, the airstreams leaving the radiators are passed forwards over the engine and discharge through an annular orifice H variable in area by axial movement of a nose piece H<1> in the manner described in Specification 473,340.