Gas turbine engine cooling system

Details Gas turbine engine cooling system Gas turbine engine cooling system

F - Mech Eng,Light,Heat,Weapons

01

P

F01P 11/10 (2006.01) F02C 7/12 (2006.01) F02C 7/18 (2006.01)

Patent

CA 2089278

A gas turbine engine cooling system. A first turbocompressor and a heat exchanger are fluidly interconnected and are each in fluid communication to receive air of differing pressures and temperatures. Typically, such air is received from various regions of the engine low pressure compressor and the engine high pressure compressor. The system delivers air through a duct to a portion of the engine for cooling, such as the engine high pressure turbine region, at lower temperatures and higher pressures than if cooling air were directly dusted from the engine compressor to the engine turbine.

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