Fan containment system

Patent metadata

Field	Value
Publication number	US-9598978-B2
Application number	US-201414154671-A
Country	US
Kind code	B2
Filing date	Jan 14, 2014
Priority date	Feb 13, 2013
Publication date	Mar 21, 2017
Grant date	Mar 21, 2017

Abstract

A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub.

First claim

We claim:

1. A fan containment system arranged to be fitted around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine, each fan blade having a respective fan blade tip, the fan containment system comprising:
a generally cylindrical fan case including a hook, the hook projecting in a generally radially inward direction and positioned axially forward of the radial array of fan blades when the fan containment system is fitted around the radial array of fan blades;
a fan track liner disposed on the radially inner surface of the fan case; and
a panel which is fitted into a recess in the fan track liner is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades when the fan containment system is fitted around the radial array of fan blades such that the panel forms a substantially continuous air washed surface with the fan track liner
wherein the panel is configured to be temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine in use and strike the panel, without compromising the structural integrity of the panel while being weak enough so that in the event that, during operation of the gas turbine engine, one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub by the panel and so increases the likelihood that the fan blade collides with the hook and is retained in the gas turbine engine.

2. A fan containment system as claimed in claim 1 , wherein the panel comprises an elastomeric structure.

3. A fan containment system as claimed in claim 2 , wherein the elastomeric structure comprises an elastomer material.

4. A fan containment system as claimed in claim 1 , wherein the panel comprises ribs.

5. A fan containment system as claimed in claim 4 , wherein the ribs are stiffened by inserts.

6. A fan containment system as claimed in claim 4 , wherein the ribs are inclined in an axially forward direction.

7. A fan containment system as claimed in claim 1 , wherein the panel includes a face sheet.

8. A fan containment system as claimed in claim 7 , wherein the face sheet comprises a plurality of strips.

9. A fan containment system as claimed in claim 8 , wherein the strips are inclined at an angle relative to a plane perpendicular to the axial direction of the gas turbine engine.

10. A fan containment system as claimed in claim 9 , wherein the angle matches the angle of a trajectory of the fan blade tip of the released fan blade.

11. A fan containment system as claimed in claim 7 , wherein the face sheet defines a plurality of holes.

12. A fan containment system as claimed in claim 1 , wherein the panel defines pressure relief holes.

13. A fan containment system as claimed in claim 1 , wherein the panel is one segment of a circumferential array of like panel segments.

14. A fan containment system as claimed in claim 1 , wherein the panel extends around the entire circumference of the fan case.

15. A fan assembly comprising a fan containment system as claimed in claim 1 and a radial array of fan blades mounted to a hub.

16. A gas turbine engine comprising a fan containment system as claimed in claim 1 .

Assignees

• Rolls Royce Plc

Inventors

• Hoyland Matthew Ashley Charles
• Evans Dale Edward

Classifications

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2250/25

  helical · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic