Fan containment system

Patent metadata

Field	Value
Publication number	US-9816510-B2
Application number	US-201414160985-A
Country	US
Kind code	B2
Filing date	Jan 22, 2014
Priority date	Feb 13, 2013
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

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 has a respective tip. The system includes: a cylindrical fan case including a hook projecting in a radially inward direction and positioned axially forward of the radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a damaging tool which projects radially inwards from the fan case towards the tips. The damaging tool has a tip radially outward of the fan blade tips. The damaging tool is configured that in the event that one of the fan blades is released from the hub, the tip of the damaging tool damages the fan blade tip of the released fan blade to promote penetration of the fan blade into the fan track liner.

First claim

The invention claimed is:

1. A fan assembly comprising:
a radial array of fan blades mounted to a hub in an axial gas turbine engine, each fan blade having a respective fan blade tip; and
a fan containment system arranged to be fitted around the fan blades, 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 assembly 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 damaging tool which projects radially inwards from the fan case towards the fan blade tips when the fan assembly is fitted around the array of radially extending fan blades, the damaging tool having a tip which is radially outward of the fan blade tips during normal operation of the gas turbine engine,

wherein the damaging tool is configured such that in the event that, during operation of the gas turbine engine, one of the fan blades is released from the hub, the tip of the damaging tool damages the fan blade tip of the released fan blade so as to promote penetration of the fan blade into the fan track liner and ensure the fan blade collides with the hook,
wherein the damaging tool follows a path disposed against the radially inner surface of the fan case, and
wherein the fan blade tip defines a chord line, and the path disposed against the radially inner surface of the fan case is generally parallel to the chord line when fitted around the array of radially extending fan blades.

2. A fan assembly as claimed in claim 1 wherein the tip of the damaging tool has a sharp edge.

3. A fan assembly as claimed in claim 1 wherein the damaging tool comprises a wedge shaped cylindrical rib disposed against the radially inner surface of the fan case.

4. A fan assembly as claimed in claim 3 wherein the wedge has a symmetrical cross-sectional profile.

5. A fan assembly as claimed in claim 3 wherein the wedge has an asymmetrical cross-sectional profile such that it is inclined aft or forwards towards the respective back or front of the gas turbine engine.

6. A fan assembly as claimed in claim 1 wherein the damaging tool is castellated so as to form a plurality of teeth.

7. A fan assembly as claimed in claim 6 wherein the damaging tool comprises an array of radially extending individually formed teeth.

8. A fan assembly as claimed in claim 1 wherein the damaging tool is disposed around the entire circumference of the radially inner surface of the fan case.

9. A fan assembly as claimed in claim 1 wherein the damaging tool is one of a plurality of damaging tools spaced apart in the axial direction of the fan case.

10. A fan assembly as claimed in claim 1 wherein the path is a helical path such that the damaging tool has a helical shape by way of following the helical path disposed against the radially inner surface of the fan case.

11. A fan assembly as claimed in claim 1 wherein the damaging tool is one of an array of damaging tools disposed around the radially inner surface of the fan case in a circumferential direction of the radially inner surface.

12. A fan assembly as claimed in claim 1 wherein the damaging tool projects partially through the thickness of the fan track liner.

13. A fan assembly as claimed in claim 12 wherein the fan track liner comprises a radially outer honeycomb layer and a radially inner attrition layer.

14. A fan assembly as claimed in claim 13 wherein the honeycomb layer and the radially inner attrition layer are separated by a septum.

15. A fan assembly as claimed in claim 13 wherein the damaging tool projects through the thickness of the fan track liner up to the radially outer surface of the attrition liner.

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

Assignees

• Rolls Royce Plc

Inventors

• Harper Cedric Brett

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2250/183

  zigzag · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic