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Turbine blades with tip portions having converging cooling holes

  • US 9,856,739 B2
  • Filed: 09/18/2013
  • Issued: 01/02/2018
  • Est. Priority Date: 09/18/2013
  • Status: Active Grant
First Claim
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1. A turbine rotor blade for a turbine section of an engine, the turbine section including a shroud surrounding the turbine rotor blade, comprising:

  • a platform; and

    an airfoil extending from the platform into a mainstream gas path of the turbine section, the airfoil comprisinga pressure side wall;

    a suction side wall joined to the pressure side wall at a leading edge and a trailing edge;

    a tip cap extending between the suction side wall and the pressure side wall;

    a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges from an inlet to an outlet, wherein the first squealer tip extension terminates at a radial wall, and wherein the outlet of the first cooling hole is formed on the radial wall,wherein the first squealer tip extension includes a forward surface that is continuous with a forward surface of the pressure side wall and is completely forward of the forward surface of the pressure side wall relative to a radial axis of the pressure side wall, and wherein the first squealer tip extension further includes a trailing surface that extends in a forward direction at a second angle, non-parallel to the radial axis of the pressure side wall, anda second squealer tip extension extending from the suction side wall at a third angle relative to the suction side wall, wherein the second squealer tip extension includes a trailing surface that is continuous with a trailing surface of the suction side wall and is completely forward of the trailing surface of the suction side wall relative to a radial axis of the suction side wall; and

    an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.

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