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Gas-turbine brush seals with permanent radial gap

  • US 6,488,471 B1
  • Filed: 04/27/2001
  • Issued: 12/03/2002
  • Est. Priority Date: 10/04/2000
  • Status: Expired due to Fees
First Claim
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1. A method of enabling a gas turbine engine compressor to withstand transient rub events, said compressor including an axially disposed, rotatable rotor having a series of rotor blades arranged axially in rows received within a stator including a series of stator blades arranged axially in rows corresponding with said rows of rotor blades, said method comprising the steps of:

  • providing rub tolerant, deformable surfaces in between each of said rows of stator blades and located radially outward from the tips of the corresponding row of rotor blades;

    providing rub tolerant, deformable surfaces upon the surface of said rotor in between each of said rows of rotor blades spaced a distance radially from the tips of the corresponding row of stator blades;

    said rub tolerant, deformable surfaces in said first providing step above having an axial length substantially equal to the axial length of said corresponding row of rotor blades;

    said rub tolerant, deformable surfaces in said second providing step above having an axial length substantially equal to the axial length of said corresponding row of stator blades; and

    , said rub tolerant, deformable surfaces from said providing steps above being annular brush seals;

    wherein the tips of the stator blades and the tips of the respective opposing annular brush seals, and the tips of the rotor blades and the tips of the respective opposing annular brush seals define substantial radial clearances that provide gaps that remain open under all regular and normal operating conditions of the gas engine.

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