Axial-flow gas turbine cooling arrangement

Details Axial-flow gas turbine cooling arrangement Axial-flow gas turbine cooling arrangement

1991-04-02

1993-03-02

Vrablik, John J.

Power plants

Combustion products used as motive fluid

Combustion products generator

415115, 415175, 415176, F02C 300, F01D 514

Patent

active

051898748

ABSTRACT:
In a single-shaft axial-flow gas turbine, the shaft part lying between turbine and compressor is a drum (12) which is surrounded by a drum cover (13). The annular passage (18) formed between drum and drum cover assumes the function of conducting all the rotor cooling air, tapped on the hub side behind the last moving row of the compressor, to the front end (16) of the turbine and after this to its rotor-side cooling passages. The cooling air is deflected inside the annular passage in a spin cascade (25) and accelerated to the highest possible tangential velocity. With this measure, the axial thrust of the gas turbine can be reduced on the one hand and the hitherto conventional recooler for the cooling air can be dispensed with on the other hand.

REFERENCES:
patent: 2647684 (1953-08-01), Lombard
patent: 2951337 (1960-09-01), Atkinson et al.
patent: 3826084 (1974-07-01), Branstrom et al.
patent: 3989410 (1976-11-01), Ferrari
patent: 4236869 (1980-12-01), Laurello
patent: 4332133 (1982-06-01), Schwarz et al.
patent: 4462204 (1984-07-01), Hull
patent: 4650395 (1987-03-01), Weidner
patent: 4657482 (1987-04-01), Neal

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