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Turbine engine bearing support

  • US 6,428,269 B1
  • Filed: 04/18/2001
  • Issued: 08/06/2002
  • Est. Priority Date: 04/18/2001
  • Status: Expired due to Term
First Claim
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1. In an aircraft turbine engine comprising a rotor having a shaft which rotates about an axis of rotation R during balanced engine operation, a fan stage having at least two fan blades attached to the shaft, a bearing support structure for supporting the shaft for rotation, said bearing support structure comprising a front bearing and a rear bearing, and a first bearing support and a second bearing support for securely attaching the front bearing and the rear bearing to the aircraft turbine engines support structure, respectively, the improvement comprising the first bearing support includes a joint located at an axial distance “

  • a”

    from the front bearing, the joint includes a frangible linkage wherein the joint is designed so as to substantially eliminate shear forces on the frangible linkage so that the frangible linkage is subjected to tensile force.

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