Thrust compensation and cooling system for gas turbines

Details Thrust compensation and cooling system for gas turbines Thrust compensation and cooling system for gas turbines

1978-06-22

1980-07-29

Croyle, Carlton R.

Power plants

Combustion products used as motive fluid

With safety device

60 3917, 60 3975, 415107, F02C 702, F02C 718

Patent

active

042144361

ABSTRACT:
A gas turbine is disclosed having at least one turbine stage with hot gas flowing axially through the one stage. At least one balance piston is provided on the shaft to equalize an axial thrust and is located adjacent to at least a first pressurized fluid chamber. The first pressurized fluid chamber is adjacent to a hot gas intake of the turbine stage and is separated from at least a second pressurized fluid chamber by a first transfer gasket co-acting with the balance piston. Pressurized fluid within the first fluid chamber has a pressure greater than the pressure of the hot gas in the vicinity of a hot gas intake. A cooling system is connected to the second fluid chamber for supplying a cooling fluid. A slot of the first transfer gasket is selected so that a pressure difference between the first and second fluid chambers at least partially brings the axial thrust into equalization through the balance piston.

REFERENCES:
patent: 1988456 (1935-01-01), Lysholm
patent: 2614799 (1952-10-01), Judson et al.
patent: 2647684 (1953-08-01), Lombard
patent: 2779531 (1957-01-01), Wheatley
patent: 3034298 (1962-05-01), White
patent: 3044744 (1962-07-01), Berlyn
patent: 3452542 (1969-07-01), Saferstein et al.
patent: 3903691 (1975-09-01), Szydlowski

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