# US 10,480,337 B2 · Turbine shroud assembly with multi-piece seals > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,337 B2 - Document ID: US10480337B2 - Status: Granted - Kind: B2 - Application number: 15/490,478 - Filed: 2017-04-18 - Published: 2018-10-18 - Granted: 2019-11-19 - Earliest claimed: 2017-04-18 - Assignees: Rolls-Royce North American Technologies Inc. - Applicants: Rolls-Royce North American Technologies, Inc. - Inventors: Daniel K. Vetters - Web page: https://patentgrep.com/patent/US10480337B2 ## CPC - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 25/246: {Fastening of diaphragms or stator-rings} - F05D 2230/642: using maintaining alignment while permitting differential dilatation - F05D 2240/11: Shroud seal segments - F05D 2300/6033: Ceramic matrix composites [CMC] - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An assembly adapted for use in a gas turbine engine has a carrier component, a supported component, and a seal adapted to resist the flow of gasses between the supported component and the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for resisting gasses from passing over turbine blades included in the gas turbine engine. ## Claims ### Claim 1 A turbine shroud assembly adapted for use in a gas turbine engine, the assembly comprising a carrier comprising metallic materials, a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner that mounts to the carrier to couple the blade track segment to the carrier, and a multi-piece seal including components received in a first radially-inwardly opening channel formed in the carrier, the multi-piece seal engages the runner of the blade track segment to resist the flow of gasses through an interface between the carrier and the runner of the blade track segment, wherein the multi-piece seal includes a forward wire arranged along a forward side of the first radially-inwardly opening channel, an aft wire arranged along an aft side of the first radially-inwardly opening channel, and a rope seal arranged in the first radially-inwardly opening channel between the forward wire seal and the aft wire seal, and wherein the rope seal is sized to engage the forward wire seal and the aft wire seal such that the forward wire seal and the aft wire seal are pushed away from one another and radially inward into engagement with the carrier and the runner of the blade track segment, wherein the first radially-inwardly opening channel is arranged along a forward side of the blade track segment axially forward of the attachment portion of the blade track segment, and wherein the carrier is formed to include a second radially-inwardly opening channel that opens to face the runner of the blade track segment, wherein the multi-piece seal includes (i) a second forward wire arranged along a forward side of the second radially-inwardly opening channel, (ii) a second aft wire arranged along an aft side of the second radially-inwardly opening channel, and (iii) a second rope seal arranged in the second radially-inwardly opening channel between the second forward wire seal and the second aft wire seal, and wherein the second rope seal sized to engage the second forward wire seal and the second aft wire seal such that the second forward wire seal and the second aft wire seal are pushed away from one another and radially inward into engagement with the carrier along a side of the second radially-inwardly opening channel and the runner of the blade track segment. ### Claim 2 (depends on 1) The assembly of claim 1, wherein the carrier is formed to include a plurality of buffer air passages spaced circumferentially around the radially-inwardly opening channel from one another and shaped to conduct buffer air into the radially-inwardly opening channel. ### Claim 3 (depends on 2) The assembly of claim 2, wherein the rope seal is a hollow braided or woven rope configured to permeably conduct buffer air from the buffer air passages into an internal hollow of the rope seal. ### Claim 4 (depends on 3) The assembly of claim 3, wherein the rope seal includes ceramic core portions sized and arranged to be spaced apart from discharge openings formed by each of the plurality of buffer air passages. ### Claim 5 (depends on 1) The assembly of claim 1, wherein the second radially-inwardly opening channel is arranged along an aft side of the blade track segment axially aft of the attachment portion of the blade track segment. ### Claim 6 (depends on 5) The assembly of claim 5, wherein the carrier is formed to include axially-extending radially-inwardly opening channels that open to face the runner of the blade track segment, the axially-extending radially-inwardly opening channels interconnect the first radially-inwardly opening channel and the second radially-inwardly opening channel, and the multi-piece seal includes components received in the axially-extending radially-inwardly opening channels such that the multi-piece seal surrounds the attachment portion of the blade track segment on forward, aft, and circumferential sides. ### Claim 7 (depends on 1) The assembly of claim 1, wherein the attachment portion of the blade track segment forms a T shape when viewed in the circumferential direction such that the entire blade track segment forms an I-beam shape when viewed in the circumferential direction. ### Claim 8 (depends on 7) The assembly of claim 7, wherein a gap is formed between the carrier and the runner of the blade track segment along an aft side of the blade track segment axially aft of the attachment portion of the blade track segment without an intervening seal that engages the runner of the blade track segment such that a mechanical moment is not induced onto the runner of the blade track segment by engagement of the runner aft of the attachment portion. ### Claim 9 An assembly adapted for use in a gas turbine engine, the assembly comprising a carrier component, a supported component, the supported component formed to include a heat shield shaped to extend partway around a central axis and an attachment portion that extends radially outward from the heat shield to couple the supported component to the carrier component, and a multi-piece seal including components received in a radially-inwardly opening channel formed in the carrier component, the multi-piece seal engages the heat shield of the supported component to resist the flow of gasses through an interface between the carrier component and the heat shield of the supported component, wherein the multi-piece seal includes a first wire arranged along a first side of the radially-inwardly opening channel, a second wire arranged along a second side of the first radially-inwardly opening channel, and a rope seal arranged in the radially-inwardly opening channel between the first wire seal and the second wire seal, and wherein the rope seal is sized to engage the first wire seal and the second wire seal such that the first wire seal and the second wire seal are pushed away from one another and radially inward into engagement with the carrier component and the heat shield of the supported component. ### Claim 10 (depends on 9) The assembly of claim 9, wherein the carrier component is formed to include a plurality of buffer air passages spaced from one another and shaped to conduct buffer air into the radially-inwardly opening channel. ### Claim 11 (depends on 10) The assembly of claim 10, wherein the rope seal is a hollow braided or woven rope configured to permeably conduct buffer air from the buffer air passages into an internal hollow of the rope seal. ### Claim 12 (depends on 10) The assembly of claim 10, wherein the rope seal is sized and arranged to be spaced apart from discharge openings formed by each of the plurality of buffer air passages. ### Claim 13 (depends on 9) The assembly of claim 9, wherein the carrier component comprises metallic materials and the supported component comprises ceramic materials. ### Claim 14 (depends on 13) The assembly of claim 13, wherein the supported component comprises ceramic matrix composite materials. ### Claim 15 (depends on 9) The assembly of claim 9, wherein the multi-piece seal surrounds the attachment portion of the supported component on forward, aft, and circumferential sides. ### Claim 16 A turbine shroud assembly adapted for use in a gas turbine engine, the assembly comprising a carrier comprising metallic materials, the carrier formed to include a radially-inwardly opening channel and a plurality of buffer air passages spaced from one another and shaped to conduct buffer air into the radially-inwardly opening channel, a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner that engages the carrier to couple the blade track segment to the carrier, and a multi-piece seal received in a radially-inwardly opening channel formed in the carrier and engaged with the runner of the blade track segment to resist gasses from moving through an interface between the carrier and the blade track segment, the multi-piece seal including a forward seal element arranged along a forward side of the radially-inwardly opening channel and an aft seal element arranged along an aft side of the radially-inwardly opening channel, wherein the forward seal element includes a plurality of lobes arranged to receive buffer air from the buffer air passages formed in the carrier and shaped to cause the forward seal to expand in the radial direction upon receipt of buffer air from the buffer air passages formed in the carrier, and the aft seal element includes a plurality of lobes arranged to receive buffer air from the buffer air passages formed in the carrier and shaped to cause the aft seal to expand in the radial direction in response to receipt of buffer air from the buffer air passages formed in the carrier. ### Claim 17 (depends on 16) The assembly of claim 16, wherein each of the forward seal element and the aft seal element are formed to include two lobes such that each of the forward seal element and the aft seal element have an E-shape when viewed in the circumferential direction. ### Claim 18 (depends on 16) The assembly of claim 16, wherein the carrier is formed to include a locator that extends into the radially-inwardly opening channel between the first seal element and the second seal element, and at least one of the buffer air passages is formed through the locator.