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Side seal for combustor transitions

  • US 6,345,494 B1
  • Filed: 09/20/2000
  • Issued: 02/12/2002
  • Est. Priority Date: 09/20/2000
  • Status: Active Grant
First Claim
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1. A sealing device for resisting the flow of gas through a labyrinth seal between a pair of adjacent combustor transitions of a gas turbine engine, the labyrinth seal including a first ridge disposed on a side wall of each combustor transition, the first ridges being offset along a gas flow leakage path between the side walls of the combustor transitions and adjacent one another, the sealing device comprising:

  • a seal member having a plurality of metal fibers;

    an elongated frame having a longitudinal axis, the frame being formed with a seat extending longitudinally along the frame and including a first connection tab protruding from the seat, the first connection tab being structured to be mounted on one of the first ridges of one of the combustor transitions; and

    the seal member being disposed in the seat and being structured to be positioned at least partially opposite the other of the first ridges on the other of the combustor transitions.

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