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Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same

  • US 20110110772A1
  • Filed: 11/11/2009
  • Published: 05/12/2011
  • Est. Priority Date: 11/11/2009
  • Status: Abandoned Application
First Claim
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1. A turbine vane comprising:

  • a core having an outer peripheral surface, the core having an airfoil shape, a plurality of channels formed in the core such that each channel opens to the outer peripheral surface of the core, the channels extending substantially radially so as to be elongated in the radial direction;

    a first platform attached to the core;

    a non-permeable skin having a hollow interior, the skin being airfoil-shaped and having an inner peripheral surface and an outer peripheral surface, the skin being sized so that the core can be received in the hollow interior of the skin; and

    a second platform attached to the skin,the core being received in the hollow interior of the skin such that the outer peripheral surface of the core engages the inner peripheral surface of the skin such that a plurality of generally radial cooling channels are formed between the channels in the core and the inner peripheral surface of the skin, the skin being attached to the core over at least a portion of the engaging surfaces of the outer peripheral surface of the core and the inner peripheral surface of the skin.

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