Cooling air cooler for a gas turbine engine

Power plants – Combustion products used as motive fluid – With lubricators

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Details

60 3966, 60 3967, 60 3971, F02C 718

Patent

active

041377052

ABSTRACT:
A gas turbine engine having a compressor and an air-cooled turbine is provided with a cooling system for decreasing the temperature of the turbine cooling air. A compact heat exchanger, rotatable with the compressor, receives a portion of the pressurized air which is bled from the compressor. Relatively cool engine lubrication oil is pumped through the heat exchanger into heat exchange relationship with the pressurized air, thereby cooling the air and heating the lubrication oil. The cooled air is then routed to and circulated through the turbine blades to provide improved internal cooling thereof. The heated lubrication oil is collected from the heat exchanger and routed to a second heat exchanger wherein it is placed in heat exchange relationship with engine fuel to recover the heat extracted from the compressor bleed air and to return the heat to the engine operating cycle. The cooling system is designed to contain the lubricant in the unlikely event of a leak developing in the heat exchanger. Incorporation of the heat exchanger of the present invention into a gas turbine engine permits a reduction in the quantity of compressor air required for turbine rotor blade cooling and, thus, provides an improvement in engine performance.

REFERENCES:
patent: 2676458 (1954-04-01), Hill
patent: 2907527 (1959-10-01), Cummings
patent: 3078667 (1963-02-01), Deinhardt
patent: 3191707 (1965-06-01), Peterson
patent: 3528250 (1970-09-01), Johnson
patent: 3742706 (1973-07-01), Klompas

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