Fan casing arrangement for a gas turbine engine and related method

Patent metadata

Field	Value
Publication number	US-9777599-B2
Application number	US-201414505956-A
Country	US
Kind code	B2
Filing date	Oct 3, 2014
Priority date	Oct 15, 2013
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.

First claim

The invention claimed is:

1. A fan casing arrangement for a gas turbine engine of a type having a propulsive fan, the fan casing arrangement comprising a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of the fan case so as to adopt a radial position between the fan and the fan case, the fan track liner including an elongate member which is helically wound against the inside of the fan case in a plurality of turns, wherein the helically-wound member of the fan track liner is self-supporting such that it is not radially fixed to the fan case.

2. The fan casing arrangement according to claim 1 , wherein successive turns of the helically-wound member are laterally engaged with one another.

3. The fan casing arrangement according to claim 2 , wherein said helically-wound member has a uniform cross sectional profile along its wound length, with a projection extending outwardly from one side of the member along its length, and a recess or opening provided on the other side of the member along its length, wherein said successive turns are laterally engaged via receipt of the projection in an adjacent length of the recess or opening.

4. The fan casing arrangement according to claim 1 , wherein the elongate member has a hollow cross-sectional configuration defining an internal chamber.

5. The fan casing arrangement according to claim 4 , wherein said internal chamber is filled with filler material.

6. The fan casing arrangement according to claim 4 , wherein said hollow cross-sectional configuration of the elongate member defines a plurality of discrete internal chambers.

7. The fan casing arrangement according to claim 6 , wherein at least some of said internal chambers are filled with filler material.

8. The fan casing arrangement according to claim 7 , wherein the filled chambers are filled with filler materials of different densities.

9. The fan casing arrangement according to claim 1 , wherein said elongate member has a plurality of integrally formed longitudinally extending spaced apart fins which project radially inwardly towards the axis around which the member is wound.

10. The fan casing arrangement according to claim 9 , wherein the spaces between said fins are filled with an abradable filler material.

11. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine of a type having a propulsive fan, the method comprising: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner, wherein the helically-wound member of the fan track liner is self-supporting such that it is not radially fixed to the fan case.

12. The method according to claim 11 , wherein said step of helically winding the liner member against the inside of the fan case comprises laterally abutting and/or laterally engaging successive turns of the liner member.

13. The method according to claim 11 , wherein the elongate member has a hollow cross-sectional configuration defining a plurality of discrete internal chambers, the method further comprising filling at least some of said chambers with respective filler materials of different densities.

14. The method according to claim 13 , wherein the densities of said filler materials are selected in dependence on characteristics of the fan to tune the impact characteristics of the fan track liner to the fan.

Assignees

• Rolls Royce Plc

Inventors

• Radomski Steven Aleksy
• Read Simon

Classifications

• F01D21/045

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

• F05D2300/615

  Filler · CPC title

• F04D19/002

  Axial flow fans · CPC title

• F04D29/023

  especially adapted for elastic fluid pumps · CPC title

• Y10T29/49245

  Vane type or other rotary, e.g., fan · CPC title