Gas turbine engine cooling system

Details Gas turbine engine cooling system Gas turbine engine cooling system

1992-03-23

1994-04-26

Capossela, Ronald C.

Refrigeration

Air compressor, cooler and expander type

Motor-type expander

62 87, F25D 900

Patent

active

053056167

ABSTRACT:
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 ducted from the engine compressor to the engine turbine.

REFERENCES:
patent: 4461154 (1984-07-01), Allam
patent: 4539816 (1985-09-01), Fox
patent: 5036678 (1991-08-01), Renninger et al.
patent: 5056335 (1991-10-01), Renninger et al.

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