GB603112A - Improvements in or relating to systems of heat exchange - Google Patents

Abstract

603,112. Heat exchange apparatus. GIRODIN, M. G. H. Sept. 18, 1945, No. 24149. Convention date, March 10, 1943. [Class 64(iii)] In a heat exchanger for use with aircraft engines. &c., comprising a series of adjacent parallel similar flow passages, through which the two heat-exchanging fluids flow in alternate passages as shown by two arrows and having inlet and outlet manifolds for one fluid, each manifold has branches 5 which individually connect with the respective flow passages and are constructed to have a section no greater than that of the flow passages in the exchanger so that flow through adjacent passages is not impeded. Each manifold comprises a chamber 4 which is connected to the main fluid supply pipes 3 and the branches 5. In the modification shown in Figs. 11-13, the exchanger 10 is connected to the two parts of the pipe 11 by manifold branches 12 the flow paths of which are practically normal to the open face of the exchanger and to the chambers 13 of the manifolds. The external walls of the chambers 13 and branches 12 serve as transverse inlet and outlet conduits for the other fluid, e.g. in case of an engine, air which is drawn into the conduits by casings 14. Examples are also given of (1) an exchanger mounted directly on an engine between a compressor and the induction manifold in order to cool the compressor gases, (2) an exchanger for cooling compressor gases for a radial engine, and (3) an exchanger for intermediate cooling as applied to an axial compressor suitable for a combustion group supplying the combustion chamber of a re-superheated gas turbine or a compression unit for a stratospheric aircraft.