# US 10,370,994 B2 · Pressure activated seals 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 10,370,994 B2 - Document ID: US10370994B2 - Status: Granted - Kind: B2 - Application number: 15/159,163 - Filed: 2016-05-19 - Published: 2016-12-01 - Granted: 2019-08-06 - Earliest claimed: 2015-05-28 - Assignees: Rolls-Royce North American Technologies Inc.; ROLLS-ROYCE plc - Applicants: Rolls-Royce Corporation; Rolls-Royce North American Technologies, Inc. - Inventors: David J. Thomas; Joseph P. Lamusga; Ted J. Freeman; Aaron D. Sippel - Web page: https://patentgrep.com/patent/US10370994B2 ## CPC - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F05D 2240/11: Shroud seal segments - F05D 2270/65: Pneumatic actuators - 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 for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap. ## Claims ### Claim 1 A gas turbine engine assembly adapted to be arranged between a high pressure zone and a low pressure zone within a gas turbine engine, the assembly comprising a first component comprising metallic materials formed to include an axially extending seal-support slot, a second component comprising ceramic-matrix composite materials arranged adjacent to the first component to form a radially extending gap therebetween, and a pressure-activated seal comprising a sheet of material having a generally uniform thickness shaped to form a support portion that extends into the seal-support slot of the first component and a sealing portion arranged in the gap between the first component and the second component, wherein the sealing portion is shaped to be pushed by high pressure gas on one side of the gap into contact with the second component to resist flow through the gap, wherein the sealing portion of the pressure-activated seal forms a radially-outwardly opening channel that receives high pressure gas from the high pressure zone and wherein the support portion of the pressure-activated seal forms an axially opening channel facing the gap that receives high pressure gas from the high pressure zone. ### Claim 2 (depends on 1) The assembly of claim 1, wherein the sealing portion of the pressure-activated seal has a generally U-shaped cross sectional profile. ### Claim 3 (depends on 1) The assembly of claim 1, wherein the support portion of the pressure-activated seal has a U-shaped cross sectional profile. ### Claim 4 (depends on 1) The assembly of claim 1, wherein the support portion of the pressure-activated seal is shaped to be pushed by the high pressure gas in the high pressure zone into contact with the seal-support slot of the first component to couple the pressure-activated seal to the first component and to resist flow through the gap. ### Claim 5 (depends on 1) The assembly of claim 1, wherein the first component is formed to include a body and an attachment feature extending radially inward from the body and wherein the second component is formed to include a panel that separates the high pressure zone from the low pressure zone shielding the first component from the low pressure zone and an attachment feature engaging the attachment feature of the first component to couple the second component and the first component. ### Claim 6 (depends on 5) The assembly of claim 5, wherein the gas turbine engine assembly further includes a compliant load pad arranged between the attachment feature of the second component and the attachment feature of the first component. ### Claim 7 (depends on 6) The assembly of claim 6, wherein the compliant load pad is more compliant than one of the first component and the second component. ### Claim 8 (depends on 7) The assembly of claim 7, wherein the compliant load pad is configured to block chemical interaction of the first component and the second component during operation of the gas turbine engine when temperatures are elevated. ### Claim 9 A gas turbine engine assembly comprising a first component formed to include a seal-support slot, a second component arranged adjacent to the first component to form a gap therebetween, and a pressure-activated seal including a support portion that extends into the seal-support slot of the first component and a sealing portion arranged in the gap between the first component and the second component, wherein the sealing portion of the pressure-activated seal forms a primarily radially-outwardly opening channel to open toward a high pressure zone when assembled in an engine, and wherein the support portion of the pressure-activated seal forms a primarily axially opening channel facing the gap that receives high pressure gas from the high pressure zone. ### Claim 10 (depends on 9) The assembly of claim 9, wherein the sealing portion of the pressure-activated seal has a generally U-shaped cross sectional profile that forms the radially-outwardly opening channel. ### Claim 11 (depends on 9) The assembly of claim 9, wherein the sealing portion of the pressure-activated seal cooperates with a portion of the first component to define the radially-outwardly opening channel. ### Claim 12 (depends on 9) The assembly of claim 9, wherein the support portion of the pressure-activated seal has a U-shaped cross sectional profile. ### Claim 13 (depends on 9) The assembly of claim 9, wherein the support portion of the pressure-activated seal is shaped to be pushed by the high pressure gas in the high pressure zone into contact with the seal-support slot of the first component to couple the pressure-activated seal to the first component and to resist a flow of gas through the gap. ### Claim 14 (depends on 9) The assembly of claim 9, wherein the first component is formed to include a body and an attachment feature extending radially inward from the body and wherein the second component is formed to include a panel that separates the high pressure zone from the low pressure zone shielding the first component from the low pressure zone and an attachment feature engaging the attachment feature of the first component to couple the second component and the first component. ### Claim 15 (depends on 14) The assembly of claim 14, wherein the gas turbine engine assembly further includes a compliant load pad arranged between the attachment feature of the second component and the attachment feature of the first component. ### Claim 16 (depends on 15) The assembly of claim 15, wherein the compliant load pad is more compliant than one of the first component and the second component. ### Claim 17 (depends on 15) The assembly of claim 15, wherein the seal-support slot is formed in the attachment feature included in the first component that engages the attachment feature of the second component to couple the first component to the second component.