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Gas turbine engine systems involving turbine blade platforms with cooling holes

  • US 8,206,114 B2
  • Filed: 04/29/2008
  • Issued: 06/26/2012
  • Est. Priority Date: 04/29/2008
  • Status: Active Grant
First Claim
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1. A turbine blade for a gas turbine engine comprising:

  • an airfoil having a leading edge, a trailing edge, a pressure side and a suction side, an interior cooling passage extends at least partially into the airfoil; and

    a blade platform on which the airfoil is disposed, the blade platform having a pressure side mateface located adjacent to the pressure side of the airfoil and a suction side mateface located adjacent to the suction side of the airfoil, the blade platform having a cooling hole that pneumatically communicates with the interior cooling passage, the cooling hole having a cooling hole exit in the suction side mateface to direct a flow of cooling air through the suction side mateface toward a trailing edge of an airfoil disposed on an adjacent blade platform, the cooling hole raked aftward.

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