Abradable liner for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9752780-B2
Application number	US-201414309698-A
Country	US
Kind code	B2
Filing date	Jun 19, 2014
Priority date	Jun 27, 2013
Publication date	Sep 5, 2017
Grant date	Sep 5, 2017

Abstract

Described is an abradable component for a gas turbine engine that includes a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon. The walls intersect one another to define an abradable network of open faced cells on a gas washed surface thereof, and at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use.

First claim

The invention claimed is:

1. An abradable component for a gas turbine engine, comprising:
a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon, the walls intersecting one another to define an abradable network of open faced cells on a gas washed surface thereof,
wherein at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use, and
wherein one of the walls or an intersection at which two or more of the walls intersect one another includes a boss through which one of the one or more through-holes passes.

2. An abradable component for a gas turbine engine as claimed in claim 1 , wherein the one or more through-holes are positioned at an intersection of two or more of the walls.

3. An abradable component for a gas turbine engine according to claim 1 , wherein at least one of the one or more through-holes outlet into one of the open faced cells.

4. An abradable component for a gas turbine engine according to claim 1 , wherein the one or more through-holes are provided at an outer edge of the network of open faced cells.

5. An abradable component for a gas turbine engine according to claim 1 , wherein the one or more through-holes have a uniform cross section along their lengths.

6. An abradable component for a gas turbine engine according to claim 1 , wherein the cross-section of one of the one or more through-holes changes along the length of the one through-hole.

7. An abradable component for a gas turbine engine according to claim 6 , wherein cross-sectional diameter of the one through-hole reduces continuously along the length of the one through-hole.

8. An abradable component for a gas turbine engine according to claim 1 , wherein one of the one or more through-holes has a plurality of sections along its length, each section having uniform cross-sectional areas along the length of the section.

9. An abradable component for a gas turbine engine according to claim 1 , wherein the walls intersect one another to provide a lattice work of walls.

10. An abradable component for a gas turbine engine according to claim 9 , wherein the lattice work comprises a first and a second linear array of elongated walls.

11. An abradable component for a gas turbine engine according to claim 1 , wherein the boss is cylindrical.

12. An abradable component for a gas turbine engine according to claim 1 , wherein the one or more through-holes have central axes normal to a tangent of the inboard surface.

13. An abradable component for a gas turbine engine according to claim 1 , wherein the gas washed surface is arcuate and the walls are provided on the arcuate, gas washed surface.

14. An abradable component for a gas turbine engine, comprising:
a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon, the walls intersecting one another to define an abradable network of open faced cells on a gas washed surface thereof,
wherein at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use, and
wherein the abradable component further comprises at least one hole which extends from the base partially through one of the walls towards the open face of one of the open faced cells so as to provide a blind hole which is arranged to be exposed after a predetermined amount of wear.

15. An abradable component for a gas turbine engine according to claim 14 , wherein a closed end of the blind hole is provided by an abradable material which is a different material to that constituting the plurality of walls.

16. An abradable component for a gas turbine engine according to claim 14 , comprising two or more blind holes having end walls of different thicknesses so as to be exposed after different amounts of wear.

17. An abradable component for a gas turbine engine, comprising:
a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon, the walls intersecting one another to define an abradable network of open faced cells on a gas washed surface thereof,
wherein at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use, and
wherein the open faced cells are filled with an abradable material.

18. An abradable component for a gas turbine engine according to claim 17 , wherein the abradable material is a sintered powder material.

19. An abradable component for a gas turbine engine according to claim 17 , wherein one of the walls or an intersection at which two or more of the walls intersect one another includes a boss through which one of the one or more through-holes passes.

20. An abradable component for a gas turbine engine according to claim 17 , further comprising at least one hole which extends from the base partially through one of the walls towards the open face of one of the open faced cells so as to provide a blind hole which is arranged to be exposed after a predetermined amount of wear.

Assignees

• Rolls Royce Plc

Inventors

• Jones Simon Lloyd
• Self Kevin Paul
• Simms Mark John

Classifications

• F01D11/125

  with a reinforcing structure · CPC title

• F01D11/122 Primary

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

• F01D11/127

  with a deformable or crushable structure, e.g. honeycomb · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title