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

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Amin, Samy, Wojtyczka, Czeslaw
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US10/200,460
• Time in Patent Office: 448 Days
• Field of Search: 415/9, 415/173.4, 415/197, 415/200
• US Class Current: 415/9
• CPC Class Codes: B32B 3/12 characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
• CPC Class Codes: B32B 5/18 characterised by features of a layer of foamed material
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F05D 2220/326 to drive shrouded, low solidity propeller
• CPC Class Codes: F05D 2220/327 to drive shrouded, high solidity propeller
• CPC Class Codes: F05D 2300/433 Polyamides, e.g. NYLON
• CPC Class Codes: F05D 2300/601 Fabrics
• CPC Class Codes: F05D 2300/612 Foam
• CPC Class Codes: F05D 2300/614 Fibres or filaments

Abstract

A fan blade fragment containment assembly for a gas turbine engine having a fan case surrounding the fan and having a circumferential axially extending blade fragment impact zone. An inner relatively slack or low tension deformable layer of Kevlar™ or Zylon™ fabric is mounted to the fan case outer surface and envelopes the impact zone. A compressible (ex. metal foam or honeycomb) layer is mounted on an outer surface of the deformable layer. A friction reduction layer of Teflon™ is mounted on an outer surface of the compressible layer and an outer relatively taut higher tension containment layer of Kevlar™ or Zylon™ fabric is mounted on an outer surface of the friction reduction layer. The friction reduction layer enhances the distribution of impact forces about the circumference of the compressible layer by reducing local shear stresses between the compressible layer and the containment layer.

Claims

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.

2. A fan blade fragment containment assembly according to claim 1 wherein,the deformable layer is a fabric of fibres selected from the group consisting of:

an aromatic polyamide fibre; and

a phenylene-2, 6-benzobisoxazole fibre.

4. A fan blade fragment containment assembly according to claim 1 wherein the friction reduction layer is selected from the group consisting of:

a plastic sheet; and

a composite graphite based fabric.

5. A fan blade fragment containment assembly according to claim 1 wherein the containment layer is a fabric of fibres selected from the group consisting of:

an aromatic polyamide fibre; and

a phenylene-2, 6-benzobisoxazole fibre.

3. A fan blade fragment containment assembly according to crushable layer selected from the group consisting of:

a metal foam;

a honeycomb structure;

an expanded metal sheet;

sintered metal particles; and

spray applied metal particles.