Cooling system for a gas turbine

Power plants – Combustion products used as motive fluid

Patent

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Details

60 3975, F02C 604

Patent

active

051632853

ABSTRACT:
A cooling system is disclosed including a drive shaft interconnecting a turbine rotor wheel with a compressor rotor wheel, a heat exchanger, and an auxiliary air compressor formed as part of the drive shaft which draws air from a portion of the compressor, through the heat exchanger and directs it onto portion of a gas turbine. The auxiliary air compressor may be a mixed-flow air compressor having a plurality of axial flow stages located upstream of a rotor portion with an impeller wheel to direct the cooling air onto portions of the gas turbine rotor and the stationary vanes. The heat exchanger may also be located externally of the gas turbine engine to improve the cooling of the cooling air before it is directed onto the gas turbine. It is envisioned that the system will be utilized with a gas turbine engine having a generally annular combustion chamber and that the auxiliary air compressor will be formed as part of the driving shaft interconnecting the gas turbine rotor wheel with the compressor rotor and be located within the space between the drive shaft and the interior of the combustion chamber. Thus, the rotation of the gas turbine rotor which drives the compressor rotor will also drive the rotating portion of the auxiliary, cooling air compressor.

REFERENCES:
patent: 2603453 (1952-07-01), Sollinger
patent: 2618120 (1952-11-01), Papini
patent: 2672013 (1954-03-01), Lundquist
patent: 2783965 (1957-03-01), Birmann
patent: 4187675 (1980-02-01), Wakeman
patent: 4236869 (1980-12-01), Laurello
patent: 4254618 (1981-03-01), Elovic
patent: 4574584 (1986-03-01), Hovan
patent: 4901520 (1990-02-01), Kozak et al.

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