A cooling system for aircraft engines is provided with a water‐cooling radiator, 14 of such size as to effect adequate cooling under normal conditions and a steam‐condenser 17 which becomes operative under abnormal conditions, the condenser being located behind the radiator or incorporared in the wing or fuselage structure in known manner so that only the water‐cooling radiator offers head resistance. Liquid and steam from the engine jackets 10 pass by a pipe 11 to a steam separator 12 whence the liquid descends to the radiator and steam passes through a dome 15 to the condenser, which is preferably formed of two similar triangular parts 18, 19, Fig. 3. The water from the radiator is returned by a pump 24 to the jackets and the condensate is delivered by a pump 21 back to the separator. In a modification, Fig. 4, a centrifugal steam separator 26, as described in Specification 315007, is employed, and the condenser is constituted by headers 31 and conduits 32 in the wing surface.
(1935), "Month in the Patent Office: A Selection of the More Important Aircraft and Engine Specifications Published Recently", Aircraft Engineering and Aerospace Technology, Vol. 7 No. 2, pp. 52-52. https://doi.org/10.1108/eb029910
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