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Cooling apparatus for a bearing in a gas turbine

  • US 4,156,342 A
  • Filed: 11/07/1977
  • Issued: 05/29/1979
  • Est. Priority Date: 06/11/1976
  • Status: Expired due to Term
First Claim
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1. A method of cooling a bearing in a location adjacent the combustor section in a gas turbine engine comprising, bleeding compressed air from an intermediate stage of the compressor section of said engine, feeding said compressed air into the inner pipe of a coaxial pair of pipes which passes from a point outside the casing of said turbine through said casing and through said combustor section to the housing of said bearing, said housing having a pair of separated channels therein, a first channel being in communication with said inner pipe of said coaxial pair, said first channel delivering cooling air to a pair of annular shaped recesses therein, where the cooling air is heated, bleeding said heated cooling air from said annular recesses to a central gathering passage, which passage is in communication with the outer pipe of said coaxial pair, passing substantially all said heated cooling air through said outer pipe to atmosphere.

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