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Turbine airfoil with near-wall impingement and vortex cooling

  • US 7,497,655 B1
  • Filed: 08/21/2006
  • Issued: 03/03/2009
  • Est. Priority Date: 08/21/2006
  • Status: Expired due to Fees
First Claim
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1. An insert for use in a turbine airfoil, comprising:

  • a first rib extending from a pressure side to a suction side of the insert and forming a first impingement cavity;

    a second rib extending from the pressure side to the suction side of the insert and forming a second impingement cavity adjacent to the first impingement cavity;

    a plurality of impingement cooling holes spaced along the insert in the first impingement cavity;

    a first insert support member extending from an insert wall of the second impingement cavity;

    at least one inlet cooling hole in the second impingement cavity wall of the insert and located between the first impingement cavity and the first insert support member; and

    ,a plurality of impingement cooling holes in the second impingement cavity wall of the insert and located between the first insert support member and the second rib.

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