Surface Condensers; construction of wings.—In a cooling system for aircraft internal combustion engines, steam evolved from the cylinder jackets is admitted to the whole of the interior of a hollow water‐tight aerofoil, wherein it is condensed. A separate collecting‐chamber for the condensate and non‐return valves in the condensate outlet may be provided. In a biplane, drains may be provided at the wing tips, passing down the interplane struts. The cooling jacket of an engine 2 is connected by a pipe 4 to a steam separator 3, from which a pipe 5 leads to a hollow aerofoil 1. A pipe 6 leads to a water inlet pump (not shown). A drain pipe 7 connects the aerofoil with a condensate collector 8, from which the condensate is returned by pipes 9 and 10 by means of a pump (not shown) to the separator 3. An air‐vent 11 is provided and non‐return valves 12, 13 are fitted to the collector 8.
(1930), "Month in the Patent Office: A Selection of the More Important Aircraft and Engine Specifications Published Recently", Aircraft Engineering and Aerospace Technology, Vol. 2 No. 9, pp. 244-244. https://doi.org/10.1108/eb029319
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