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Turbine blade for gas turbine engine and method of cooling same

  • US 6,402,471 B1
  • Filed: 11/03/2000
  • Issued: 06/11/2002
  • Est. Priority Date: 11/03/2000
  • Status: Active Grant
First Claim
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1. A turbine blade comprising:

  • a platform having an internal cavity formed therein;

    an airfoil extending radially from said platform;

    an internal cooling circuit formed in said airfoil for circulating a coolant therethrough, said internal cooling circuit including a plurality of radially extending cavities fluidly connected in series in a serpentine arrangement with two of said radially extending cavities being connected at a turn; and

    at least one supply passage extending between said turn and said internal cavity.

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