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Method and apparatus for convective cooling of side-walls of turbine nozzle segments

  • US 20050123388A1
  • Filed: 12/04/2003
  • Published: 06/09/2005
  • Est. Priority Date: 12/04/2003
  • Status: Active Grant
First Claim
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1. 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, each said cooling channel comprising at least one inlet, each said inlet isolated from the flowing hot gases of combustion.

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