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Fan case design with metal foam between Kevlar

  • US 6,652,222 B1
  • Filed: 09/03/2002
  • Issued: 11/25/2003
  • Est. Priority Date: 09/03/2002
  • Status: Expired due to Term
First Claim
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1. A fan blade fragment containment assembly for a gas turbine engine, comprising:

  • a fan case having an inner surface, surrounding a fan mounted for rotation about an engine axis, and an outer surface, the fan case having a circumferential axially extending blade fragment impact zone;

    a deformable layer mounted to the fan case outer surface and enveloping the impact zone;

    a compressible layer mounted on an outer surface of the deformable layer;

    a friction reduction layer mounted on an outer surface of the compressible layer; and

    a containment layer mounted on an outer surface of the friction reduction layer.

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