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Cooling circuit for gas turbine fixed ring

  • US 7,517,189 B2
  • Filed: 07/08/2004
  • Issued: 04/14/2009
  • Est. Priority Date: 07/10/2003
  • Status: Active Grant
First Claim
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1. A stationary ring surrounding a hot gas passage of a gas turbine, the ring being surrounded by a stationary annular housing so as to co-operate therewith to define an annular cooling chamber into which there opens out at least one cooling air feed orifice, the ring comprising:

  • a plurality of ring segments, wherein each ring segment includes a top internal cooling circuit and a bottom internal cooling circuit, the bottom cooling circuit being independent of the top cooling circuit, and being radially offset relative to the top cooling circuit, and the bottom cooling circuit including at least one cooling air feed orifice leading from the cooling chamber,wherein said top cooling circuit includes at least one cooling air feed orifice leading from said cooling chamber.

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