Turbomachine rotor with improved cooling

Details Turbomachine rotor with improved cooling Turbomachine rotor with improved cooling

1996-05-17

1998-05-26

Kwon, John T.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

60 3975, F04D 2958

Patent

active

057555567

ABSTRACT:
A gas turbine rotor has an essentially closed loop cooling air scheme in which cooling air drawn from the compressor discharge air that is supplied to the combustion chamber is further compressed, cooled, and then directed to the aft end of the turbine rotor. Downstream seal rings attached to the downstream face of each rotor disc direct the cooling air over the downstream disc face, thereby cooling it, and then to cooling air passages formed in the rotating blades. Upstream seal rings attached to the upstream face of each disc direct the heated cooling air away from the blade root while keeping the disc thermally isolated from the heated cooling air. From each upstream seal ring, the heated cooling air flows through passages in the upstream discs and is then combined and returned to the combustion chamber from which it was drawn.

REFERENCES:
patent: 3945758 (1976-03-01), Lee
patent: 4021138 (1977-05-01), Scaizo et al.
patent: 4113406 (1978-09-01), Lee et al.
patent: 4820116 (1989-04-01), Hovan et al.
patent: 5318404 (1994-06-01), Carreno et al.

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