Method and apparatus for convective cooling of side-walls of turbine nozzle segments
AssigneeGeneral Electric Company
InventorsSze Bun Brian Chan, John Ellington Greene, Linda Jean Farral
Life of this patent
Estimating the term…
Abstract
A turbine nozzle includes, in an exemplary embodiment, an outer band portion, an inner band portion at least one nozzle vane extending between the inner band portion and the outer band portion, and at least one cooling channel extending axially at least partially through at least one of the outer band portion and the inner band portion. The at least one nozzle vane, the inner band portion, and the outer band portion define a flowpath for flowing hot gases of combustion. Each cooling channel includes at least one inlet with each inlet isolated from the flowing hot gases of combustion.
Claims21
A turbine nozzle segment comprising:
- an outer band portion;
- an inner band portion;
- at least one nozzle vane extending between said inner band portion and said outer band portion, said at least one nozzle vane, said inner band portion, and said outer band portion defining a flowpath for flowing hot gases of combustion;
- and
- at least one cooling channel extending axially at least partially through at least one of said outer band portion and said inner band portion, such that said at least one cooling channel is defined by an undercut region in said band portion and a coverplate covering at least a portion of said undercut region of said band portion, each said cooling channel comprising at least one inlet, each said inlet isolated from the flowing hot gases of combustion.
A turbine nozzle segment comprising:
- an outer band portion having an outer surface, an inner surface, and first and second mating side surfaces;
- an inner band portion having an outer surface, an inner surface, and first and second mating side surfaces;
- at least one nozzle vane extending between said outer surface of said inner band portion and said inner surface of said outer band portion, said at least one nozzle vane, said outer surface of said inner band portion, and said inner surface of said outer band portion defining a flowpath for flowing hot gases of combustion;
- and
- at least one cooling channel extending axially at least partially through at least one of said outer band portion and said inner band portion, such that said at least one cooling channel is defined by an undercut region in said band portion and a cover plate covering at least a portion of said undercut region of said band portion, each said cooling channel comprising at least one inlet, each said inlet isolated from the flowing hot gases of combustion.
A method of cooling mating side faces of inner and outer band portions of turbine nozzle segments, the nozzle segment comprising an outer band portion, an inner band portion, and at least one nozzle vane extending between the inner band portion and the outer band portion, the at least one nozzle vane, the inner band portion, and the outer band portion defining a flowpath for flowing hot gases of combustion, wherein the inner and outer band portions each comprise first and second mating side surfaces, each mating side surface comprises a seal slot extending circumferentially into the mating surface, and wherein the at least one cooling channel is located between the seal slot and said hot gas flowpath, said method comprising:
- flowing a cooling medium through at least one cooling channel extending axially at least partially through at least one of the outer band portion and the inner band portion, each cooling channel comprising at least one inlet, each inlet isolated from the flowing hot gases of combustion.
A gas turbine comprising a plurality of nozzle stages, each said nozzle stage comprising a plurality of nozzle segments, each said nozzle segment comprising:
- an outer band portion;
- an inner band portion;
- at least one nozzle vane extending between said inner band portion and said outer band portion, said at least one nozzle vane, said inner band portion, and said outer band portion defining a flowpath for flowing hot gases of combustion;
- and
- at least one cooling channel extending axially at least partially through at least one of said outer band portion and said inner band portion, such that said at least one cooling channel is defined by an undercut region in said band portion and a cover plate covering at least a portion of said undercut region of said band portion, each said cooling channel comprising at least one inlet, each said inlet isolated from the flowing hot gases of combustion.
Dependencies are inferred from the claim text.