# US 11,028,712 B2 · Seal support feature for brush seals > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,712 B2 - Document ID: US11028712B2 - Status: Granted - Kind: B2 - Application number: 16/366,860 - Filed: 2019-03-27 - Published: 2020-10-01 - Granted: 2021-06-08 - Earliest claimed: 2019-03-27 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Terence P. Tyler; Brian C. McLaughlin - Web page: https://patentgrep.com/patent/US11028712B2 ## CPC - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/246: {Fastening of diaphragms or stator-rings} - F05D 2220/32: in gas turbines - F05D 2240/11: Shroud seal segments - F05D 2240/55: Seals - F05D 2240/56: Brush seals - 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 A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal. The second seal may include a seal support extending radially therefrom which mechanically supports the first seal during engine operation. ## Claims ### Claim 1 A seal assembly of a gas turbine engine, comprising: a first engine component including a flange, the first engine component disposed between a first airflow path and a second airflow path; a first seal disposed between the first airflow path and the flange; and a second seal disposed between the first airflow path and the second airflow path, wherein the second seal is disposed in a series arrangement with the first seal, and the second seal mechanically supports the first seal, wherein the first engine component comprises a seal support; the first seal is disposed on the seal support; and the second seal comprises a second seal support extending radially from the second seal, a radially outer surface of the second seal support is substantially flush with a radially outer surface of the seal support. ### Claim 2 (depends on 1) The seal assembly of claim 1, wherein the first airflow path is at a pressure greater than a pressure of the second airflow path. ### Claim 3 (depends on 2) The seal assembly of claim 2, wherein the first seal and the second seal are disposed in a third airflow path between the first airflow path and the second airflow path. ### Claim 4 (depends on 3) The seal assembly of claim 3, wherein the first seal comprises a “W” seal. ### Claim 5 (depends on 4) The seal assembly of claim 4, wherein the second seal comprises a brush seal. ### Claim 6 (depends on 3) The seal assembly of claim 3, further comprising a second engine component disposed between the first airflow path and the second airflow path, wherein the third airflow path is disposed between the first engine component and the second engine component. ### Claim 7 (depends on 6) The seal assembly of claim 6, wherein the first engine component comprises a blade outer air seal and the second engine component comprises a stator vane. ### Claim 8 (depends on 5) The seal assembly of claim 5, wherein the first seal is mechanically supported by the radially outer surface of the second seal support. ### Claim 9 A turbine section of a gas turbine engine, comprising: a stator vane; a blade outer air seal adjacent to the stator vane; a first seal disposed between the stator vane and the blade outer air seal; and a second seal disposed between the stator vane and the blade outer air seal, wherein the second seal is disposed in a series arrangement with the first seal, and the second seal mechanically supports the first seal during engine operation, wherein the blade outer air seal comprises a seal support extending toward the stator vane; the first seal is disposed on the seal support; and the second seal comprises a second seal support extending radially from the second seal, a radially outer surface of the second seal support is substantially flush with a radially outer surface of the seal support. ### Claim 10 (depends on 9) The turbine section of claim 9, wherein the blade outer air seal comprises a flange extending toward the stator vane. ### Claim 11 (depends on 10) The turbine section of claim 10, wherein the second seal is disposed on the flange. ### Claim 12 (depends on 9) The turbine section of claim 9, wherein the first seal comprises a “W” seal. ### Claim 13 (depends on 12) The turbine section of claim 12, wherein the second seal includes a brush seal. ### Claim 14 A gas turbine engine, comprising: a turbine section or a compressor section including a stator vane; a blade outer air seal adjacent to the stator vane; a first seal disposed between the stator vane and the blade outer air seal; and a second seal disposed between the stator vane and the blade outer air seal, wherein the second seal is disposed in a series arrangement with the first seal, and the second seal mechanically supports the first seal during engine operation, wherein the blade outer air seal comprises a seal support extending toward the stator vane, the first seal disposed on the seal support, and the second seal comprises a second seal support extending radially from the second seal, a radially outer surface of the second seal support is substantially flush with a radially outer surface of the seal support. ### Claim 15 (depends on 14) The gas turbine engine of claim 14, wherein the first seal and the second seal are disposed between a first airflow path and a second airflow path and wherein the first airflow path is at a pressure greater than a pressure of the second airflow path. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the first seal comprises a “W” seal and the second seal includes a brush seal.