Cooler in nacelle with radial coolant

Details Cooler in nacelle with radial coolant Cooler in nacelle with radial coolant

B - Operations, Transporting

64

D

B64D 33/08 (2006.01) F02C 7/14 (2006.01)

Patent

CA 2743279

A cooling system in an aircraft gas turbine engine includes a heat exchanger positioned within an annular nacelle space surrounding a bypass duct of the engine. The heat exchanger has a radial coolant passage extending between the bypass duct and ambient air surrounding the nacelle, and a flow passage extending substantially normal to the radial passage for direction of a fluid to be cooled therethrough. A configuration of this nature may assist in defining a no-flow length of the heat exchanger in a third direction normal to the other two mentioned directions, which may allow for improved performance within a given radial envelope.

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