GB456385A - Improvements in evaporative cooling systems for engines and other machines, especially for aircraft engines - Google Patents

Abstract

456,385. Cooling systems for engines &c. HEINKEL, E., 15, Seestrasse, Warnemunde, Germany. July 29, 1935, No. 21558. Convention date, July 28, 1934. [Class 29] In an evaporative cooling system for aircraft or vehicle internal combustion engines, turbines or other power units, having a throttling device b located between the cooling jacket &c. a and an evaporator or reducedpressure vessel c where vapour forms, an auxiliary evaporator t is provided which comes into use when the engine is inverted, as for example in flying, so that the jacket &c. is at all times flooded. The throttling device may be a valve or nozzle, and may maintain the liquid space at above atmospheric pressure and the vapour space at atmospheric or below. The liquid from vessel c returns by gravity to the jacket inlet e and the vapour passes through a non-return valve f to a small capacity condenser g which is connected by a pipe h to a vessel i provided with condensate and air pumps k, s, the condensate being returned to the jacket inlet. In the case of large engines the capacity of the condenser can be kept small by employing a vapour compressor l, driven by a motor m, to super-heat the vapour and promote rapid condensation, the compressor being arranged in a valved byepass pipe. The flow of cooling air over the condenser may be controlled by a flap r adjusted by a device q, o, in accordance with the pressure on the discharge side of the condenser. Alternatively the condenser may be movable into and out of the air stream. The evaporator t is located at the end of a pipe u connected between vessel c and the jacket inlet, and a pipe u<1> connects the upper part of the condenser with the receiver i, which, with its associated pumps, may be cardan suspended.