Gas turbine engine cooling system

Details Gas turbine engine cooling system Gas turbine engine cooling system

1993-01-21

1995-02-28

Capossela, Ronald C.

Refrigeration

Air compressor, cooler and expander type

Motor-type expander

62 87, F25D 900

Patent

active

053926145

ABSTRACT:
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 uncooled discharge air from the engine high pressure compressor) is used to drive the turbine section of the turbocompressor. The spent air exiting the turbine section of the turbocompressor is used to help cool the engine low pressure turbine.

REFERENCES:
patent: 2970437 (1961-02-01), Anderson
patent: 4254618 (1981-03-01), Elovic
patent: 4461154 (1984-07-01), Allan
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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