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Chordally bifurcated turbine blade

  • US 5,356,265 A
  • Filed: 08/25/1992
  • Issued: 10/18/1994
  • Est. Priority Date: 08/25/1992
  • Status: Expired due to Term
First Claim
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1. A gas engine turbine blade comprising:

  • a dovetail for joining said blade to a rotor disk;

    an airfoil including;

    a pressure side and a suction side joined together at a leading edge and a trailing edge, and extending longitudinally from a root to a tip, said root being integrally joined with said dovetail;

    a chordal line extending between said pressure and suction sides from said leading edge to said trailing edge; and

    a longitudinally extending flow channel including a chordally extending, imperforate septum diving said flow channel into a first chamber disposed adjacent to said pressure side and a second flow chamber spaced laterally from said first chamber and disposed adjacent to said suction said; and

    a supply manifold for receiving compressed air at a single pressure, and disposed in flow communication with both said first and second chambers for channeling thereto first and second portions of said compressed air, respectively.

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