# US 2020/0400032 A1 · Boas thermal baffle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2020/0400032 A1 - Document ID: US20200400032A1 - Status: Published application - Kind: A1 - Application number: 16/893,595 - Filed: 2020-06-05 - Published: 2020-12-24 - Earliest claimed: 2019-06-19 - Assignees: RaytheonTechnologies Corporation - Applicants: RaytheonTechnologies Corporation - Inventors: Ken F. Blaney; Thomas E. Clark - Web page: https://patentgrep.com/patent/US20200400032A1 ## CPC - F01D 11/001: {for sealing space between stator blade and rotor} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 11/16: by self-adjusting means (F01D11/12 takes precedence) - F01D 25/246: {Fastening of diaphragms or stator-rings} - 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 A blade outer air seal assembly includes a support structure. A blade outer air seal has a plurality of segments that extend circumferentially about an axis and mounted in the support structure. At least two of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. A recess is arranged in at least one of the first wall and the second wall. An intersegment seal is arranged between the at least two segments. The intersegment seal has a circumferentially extending portion and a radially extending tab. The radially extending tab extends into the recess to define at least two cavities within the recess. ## Claims ### Claim 1 A blade outer air seal assembly, comprising: a support structure; a blade outer air seal having a plurality of segments extending circumferentially about an axis and mounted in the support structure, at least two of the segments having a first wall circumferentially spaced from a second wall, a base portion extending from the first wall to the second wall, and a recess arranged in at least one of the first wall and the second wall; and an intersegment seal arranged between the at least two segments, the intersegment seal having a circumferentially extending portion and a radially extending tab, the radially extending tab extending into the recess to define at least two cavities within the recess. ### Claim 2 (depends on 1) The blade outer air seal assembly of claim 1, wherein the intersegment seal has a plurality of radially extending tabs that extend into the recess. ### Claim 3 (depends on 1) The blade outer air seal assembly of claim 1, wherein the circumferentially extending portion and the radially extending tab form a T shaped cross-section. ### Claim 4 (depends on 1) The blade outer air seal assembly of claim 1, wherein the intersegment seal has a thickness of greater than about 0.02 inches (0.508 mm). ### Claim 5 (depends on 1) The blade outer air seal assembly of claim 1, wherein the circumferentially extending portion abuts a radially outermost portion of the first and second walls. ### Claim 6 (depends on 1) The blade outer air seal assembly of claim 1, wherein the circumferentially extending portion extends in an axial direction for at least 85% of an axial length of the first wall. ### Claim 7 (depends on 1) The blade outer air seal assembly of claim 1, wherein the recess forms a gap between the at least two segments, the gap having a width of at between about 0.007 and 0.10 inches (0.178-2.54 mm). ### Claim 8 (depends on 1) The blade outer air seal assembly of claim 1, wherein a clip secures the intersegment seal to the at least two segments. ### Claim 9 (depends on 8) The blade outer air seal assembly of claim 8, wherein the clip is a metallic material. ### Claim 10 (depends on 1) The blade outer air seal assembly of claim 1, wherein the intersegment seal is a ceramic material. ### Claim 11 (depends on 1) The blade outer air seal assembly of claim 1, wherein the intersegment seal is a metallic material. ### Claim 12 (depends on 1) The blade outer air seal assembly of claim 1, wherein the blade outer air seal is a ceramic matrix composite material. ### Claim 13 A gas turbine engine, comprising: a compressor section, a combustor section, and a turbine section arranged about an axis of rotation; a blade outer air seal assembly having a plurality of segments extending circumferentially about the axis of rotation axis and mounted in a support structure, at least two of the segments having a first wall circumferentially spaced from a second wall, a base portion extending from the first wall to the second wall, and a recess arranged in at least one of the first wall and the second wall; and an intersegment seal arranged between the at least two segments, the intersegment seal having a circumferentially extending portion and a radially extending tab, the radially extending tab extending into the recess to define at least two cavities within the recess. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the turbine section has a plurality of blades arranged radially inward of the blade outer air seal assembly, the plurality of blades is configured to push air into the cavities as each blade passes the cavities. ### Claim 15 (depends on 13) The gas turbine engine of claim 13, wherein the intersegment seal has a plurality of radially extending tabs that extend into the recess. ### Claim 16 (depends on 13) The gas turbine engine of claim 13, wherein the circumferentially extending portion and the radially extending tab form a T shaped cross-section. ### Claim 17 (depends on 13) The gas turbine engine of claim 13, wherein the recess forms a gap between the at least two segments, the gap having a width of at between about 0.007 and 0.10 inches (0.178-2.54 mm). ### Claim 18 (depends on 13) The gas turbine engine of claim 13, wherein the at least two segments are a ceramic material. ### Claim 19 (depends on 13) The gas turbine engine of claim 13, wherein the intersegment seal is ceramic material. ### Claim 20 (depends on 13) The gas turbine engine of claim 13, wherein the intersegment seal is a metallic material.