Compressor rotor cooling system for a gas turbine

Power plants – Combustion products used as motive fluid – Combustion products generator

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60 3902, 416 95, F02C 100

Patent

active

056851588

ABSTRACT:
In a gas turbine including a compressor having a bore and a rotor comprised of multiple stages extending between a first stage at a forward end of the compressor and a last stage at an aft end of the compressor, each stage including a rotor disk having a peripheral rim and multiple blades secured to the peripheral rim, a combustion system comprising a plurality of combustors utilizing discharge air from the compressor for combustion, and multiple turbine stages driven by combustion gases from the combustion system, the improvement comprising means for supplying cooling air at least to a peripheral rim of the last stage of the compressor.

REFERENCES:
patent: 3546882 (1970-12-01), Berkey
patent: 4291531 (1981-09-01), Campbell
patent: 4719747 (1988-01-01), Willkop et al.
patent: 4793772 (1988-12-01), Zaehring et al.
patent: 5310319 (1994-05-01), Grant et al.
patent: 5360318 (1994-11-01), Siga et al.
"GE Gas Turbine Design Philosophy"--GE Turbine Reference Library, Brandt et al., GE Power Generation. Date Unavailable.

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