Gas turbine engine cooling systems

Details Gas turbine engine cooling systems Gas turbine engine cooling systems

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/12 (2006.01) F02C 7/18 (2006.01)

Patent

CA 2107429

A gas turbine engine cooling system. Hotter engine compressor air is cooled by a heat exchanger using a colder engine fluid such as fuel or lower pressure (colder) engine compressor air. The cooled air passes through the compressor section of an auxiliary turbocompressor and is used to cool the engine high pressure turbine. Some of the cooled air (or un- cooled discharge air from the engine high pressure compressor) is used to drive the turbine reaction of the turbocompressor. The spent air exiting the turbine section of the turbocompressor is used to help cool the engine low pressure turbine.

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