# US 9,752,780 B2 · Abradable liner for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,752,780 B2 - Document ID: US9752780B2 - Status: Granted - Kind: B2 - Application number: 14/309,698 - Filed: 2014-06-19 - Published: 2015-01-01 - Granted: 2017-09-05 - Earliest claimed: 2013-06-27 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce PLC - Inventors: Simon Lloyd Jones; Kevin Paul Self; Mark John Simms - Web page: https://patentgrep.com/patent/US9752780B2 ## CPC - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - F01D 11/125: {with a reinforcing structure} - F01D 11/127: {with a deformable or crushable structure, e.g. honeycomb} - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 1) 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. ### Claim 4 (depends on 1) 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. ### Claim 5 (depends on 1) 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. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 6) 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. ### Claim 8 (depends on 1) 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. ### Claim 9 (depends on 1) 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. ### Claim 10 (depends on 9) 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. ### Claim 11 (depends on 1) An abradable component for a gas turbine engine according to claim 1, wherein the boss is cylindrical. ### Claim 12 (depends on 1) 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. ### Claim 13 (depends on 1) 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. ### Claim 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. ### Claim 15 (depends on 14) 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. ### Claim 16 (depends on 14) 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. ### Claim 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. ### Claim 18 (depends on 17) An abradable component for a gas turbine engine according to claim 17, wherein the abradable material is a sintered powder material. ### Claim 19 (depends on 17) 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. ### Claim 20 (depends on 17) 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.