System for cooling a gas turbine by bleeding air from the compre

Details System for cooling a gas turbine by bleeding air from the compre System for cooling a gas turbine by bleeding air from the compre

1981-10-06

1983-11-15

Coe, Philip R.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

416 90R, 415115, 415144, 60726, F01D 508

Patent

active

044153104

ABSTRACT:
A system for cooling a gas turbine by bleeding air from the compressor and channeling the air at the center of the engine towards the turbine in order to cool it. The air is bled from the plane of the disc bearing the blades of the compressor, said disc having radial ducts for the flow of the air. The invention is utilized in gas turbine engines to cool the turbine.

REFERENCES:
patent: 1574859 (1926-03-01), Baumann
patent: 2618433 (1982-11-01), Loos et al.
patent: 2641440 (1953-06-01), Williams
patent: 2833514 (1958-05-01), Rainbow et al.
patent: 3281116 (1966-10-01), Keenan
patent: 3609059 (1971-09-01), Wagle
patent: 3897168 (1975-07-01), Amos
patent: 4102603 (1978-07-01), Smith et al.
patent: 4127988 (1978-12-01), Becker
patent: 4231704 (1980-11-01), Ayache et al.

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