GB489076A - Improvements in or relating to the air-cooling of the cylinders of internal combustion engines on aircraft - Google Patents

Abstract

489,076. Aircraft engines. MERCIER, P. E. Sept. 21, 1937, Nos. 25631, 25632, 25633, and 25634. Convention dates, March 10, April 16, July 29, and Aug. 9. [Class 4] [Also in Groups XXVII and XIII] In an aircraft engine, a hollow fairing 31 in front of each cylinder divides the cooling air into two streams and acts as an exhaust conduit for the streams when reunited after having passed over the front cylinder ribs. Normal inter-cylinder baffles 16 are placed between the cylinders, but in the case of a tworow engine, these may also be formed as exhaust conduits for the cooling air. In a radialcylinder engine, these conduits lead to an annular conduit 25 having a controlled outlet from the engine cowling at a point where a depression exists, either in front of, or behind, the engine. Annular guide blades 36, 37, at the nose, may be adjustable, preferably in conjunction with an adjustable outlet; separate conduits 32 may deliver air directly to the cylinder heads or other overheated parts. The fairings 31 may be arranged unsymmetrically to allow for distortion of the air flow caused by the airscrew, and an annular, or semi-annular, lubricant cooler 28 may be located round the reducing gear in a conduit having an entrance for the cooling air which is adjusted by inflating an annular expansible air chamber. The cooler 28 may, however, be located in a chamber forming a branch from the main cooling air conduit. In an in-line engine, a fairing 31 divides the cooling air into two streams flowing along the two sides of the line, and additional inter-cylinder fairings act as further exhaust conduits for the cooling air, which is led to a conduit extending over the line of cylinder heads and having an exit adjustable simultaneously with flaps on the two sides of the fairing 31.