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Gas turbine and gas turbine cooling method

  • US 20060034685A1
  • Filed: 07/06/2005
  • Published: 02/16/2006
  • Est. Priority Date: 07/07/2004
  • Status: Active Grant
First Claim
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1. A gas turbine including a nozzle vane and sealing means engaging with said nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel, said nozzle vane and said sealing means being disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path, wherein a plurality of engagement portions between said sealing means and said nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and downstream one of said plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft.

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