Gas turbine engine

Patent metadata

Field	Value
Publication number	US-10337350-B2
Application number	US-201514630771-A
Country	US
Kind code	B2
Filing date	Feb 25, 2015
Priority date	Mar 21, 2014
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element, and one or more pockets are provided in a radially outer side of the fan track liner. One or more dampers for damping vibration of the fan track liner are positioned in each of the one or more pockets and are arranged so as to contact the annular casing element.

First claim

The invention claimed is:

1. A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine, the fan containment system comprising:
a fan case having an annular casing element that encircles the array of fan blades;
an annular fan track liner positioned substantially coaxial to the annular casing element and extending around the array of fan blades in the fan case, the annular fan track liner including: (i) a tray connecting the fan track liner to the fan case, (ii) a first intermediate layer fixed to a radially inner surface of the tray and positioned radially inward of the annular casing element, and (iii) a second intermediate layer fixed to a radially outer surface of the tray and positioned radially outward of the first intermediate layer and abutting the first intermediate layer via the tray, the second intermediate layer including one or more pockets recessed into the second intermediate layer; and
one or more resilient members configured to snub or damp vibration of the fan track liner, one of the one or more resilient members being positioned in each of the one or more pockets, the one or more resilient members being arranged to contact a radially inner side of the annular casing element.

2. The fan containment system according to claim 1 , wherein the one or more resilient members are made from a viscoelastic material.

3. The fan containment system according to claim 1 , wherein an area of the one or more resilient members in contact with the annular casing element is smaller than an area of the one or more resilient members in contact with the fan track liner.

4. The fan containment system according to claim 3 , wherein the one or more resilient members are conical or frusto-conical in shape.

5. The fan containment system according to claim 3 , wherein an end of the one or more resilient members adjacent to the annular casing element is castellated.

6. The fan containment system according to claim 1 , wherein the one or more resilient members are positioned at locations corresponding to anti-node points of expected operational modes of vibration.

7. The fan containment system according to claim 1 , wherein the one or more resilient members are constructed so as to compress into the one or more pockets so that there is substantially no protrusion of the one or more resilient members from the fan track liner at a pre-determined load.

8. The fan containment system according to claim 1 , wherein the fan track liner includes the first intermediate layer provided on a radially inner side of the tray, and an abradable layer provided on a radially inner side of the first intermediate layer.

9. The fan containment system according to claim 8 , wherein the fan track liner includes the second intermediate layer connected to a radially outer side of the separation layer.

10. The fan containment system according to claim 9 , wherein the second intermediate layer includes the one or more pockets.

11. The fan containment system according to claim 9 , wherein the second intermediate layer includes a honeycomb structure.

12. The fan containment system according to claim 1 , wherein the fan track liner includes a plurality of arcuate fan track liner panels positioned coaxially so as to define the fan track liner.

13. A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine, the fan containment system comprising:
a fan case having an annular casing element that encircles the array of fan blades;
an annular fan track liner positioned substantially coaxial to the annular casing element and extending around the array of fan blades in the fan case, the annular fan track liner including: (i) a tray connecting the fan track liner to the fan case, (ii) a first intermediate layer fixed to a radially inner surface of the tray and positioned radially inward of the annular casing element, and (iii) a second intermediate layer fixed to a radially outer surface of the tray and positioned radially outward of the first intermediate layer and abutting the first intermediate layer via the tray, the second intermediate layer including one or more pockets recessed into the second intermediate layer; and
one or more viscoelastic dampers configured to damp vibration of the fan track liner, one of the one or more dampers being positioned in each of the one or more pockets.

14. A gas turbine engine comprising the fan containment system according to claim 1 .

15. A gas turbine engine comprising:
a casing;
a component positioned radially outward of the casing;
a bracket connecting the component to the casing;
an intermediate layer positioned between the component and the casing, the intermediate layer being positioned radially outward of the casing, the intermediate layer including one or more pockets recessed into the intermediate layer; and
one or more dampers formed of a viscoelastic material, one of the one or more dampers being positioned in each of the one or more pockets.

16. The gas turbine engine according to claim 15 , wherein the component is a raft assembly.

Assignees

• Rolls Royce Plc

Inventors

• Thomas Keith Jeremy Paul

Classifications

• F05D2250/283

  honeycomb · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2250/232

  conical · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D21/045 Primary

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