# US 10,309,238 B2 · Turbine engine component with geometrically segmented coating section and cooling passage > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,238 B2 - Document ID: US10309238B2 - Status: Granted - Kind: B2 - Application number: 15/354,153 - Filed: 2016-11-17 - Published: 2018-05-17 - Granted: 2019-06-04 - Earliest claimed: 2016-11-17 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Tracy A. Propheter-Hinckley - Web page: https://patentgrep.com/patent/US10309238B2 ## CPC - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 5/288: {Protective coatings for blades} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 11/125: {with a reinforcing structure} - F01D 25/12: Cooling - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F04D 29/083: {especially adapted for elastic fluid pumps} - F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)} - F04D 29/582: {specially adapted for elastic fluid pumps} - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F05D 2220/32: in gas turbines - F05D 2230/10: by removing material - F05D 2230/30: with deposition of material - F05D 2250/28: patterned - F05D 2250/60: Structure; Surface texture - F05D 2260/202: by film cooling - F05D 2300/20: Oxide or non-oxide ceramics - F23M 2900/05004: Special materials for walls or lining - F23R 2900/03042: Film cooled combustion chamber walls or domes - 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) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - F23M: CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine component includes a passage and a geometrically segmented coating section adjacent the passage. The geometrically segmented coating section includes a wall that has a first side bordering the passage and a second side opposite the first side. The second side includes an array of cells, and there is a coating disposed over the array of cells. The coating defines an exterior side. A cooling passage extends through the wall and the coating. The cooling passage fluidly connects the passage and the exterior side. ## Claims ### Claim 1 A gas turbine engine component comprising: a passage; and a geometrically segmented coating section adjacent the passage, the geometrically segmented coating section including a wall having a first side bordering the passage and a second side opposite the first side, the second side including an array of closed-sided cells defined by cell sidewalls, a coating disposed in the array of closed-sided cells, the coating defining an exterior side, and a cooling passage that extends through the wall and the coating, the cooling passage fluidly connecting the passage and the exterior side. ### Claim 2 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the cooling passage is sloped relative to the coating. ### Claim 3 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the cooling passage includes at least one flow guide. ### Claim 4 (depends on 3) The gas turbine engine component as recited in claim 3, wherein the flow guide tapers. ### Claim 5 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the wall defines a portion of the cooling passage and the coating defines another portion of the cooling passage. ### Claim 6 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the cooling passage has an aspect ratio of greater than one. ### Claim 7 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the cooling passage tapers. ### Claim 8 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the coating is ceramic. ### Claim 9 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the cooling passage is sloped relative to the coating, the cooling passage includes at least one flow guide, and the wall defines a portion of the cooling passage and the coating defines another portion of the passage. ### Claim 10 (depends on 1) The gas turbine engine component as recited in claim 1, wherein the passage is in a blade or vane. ### Claim 11 (depends on 10) The gas turbine engine component as recited in claim 10, wherein the cell sidewalls have a uniform thickness. ### Claim 12 (depends on 10) The gas turbine engine component as recited in claim 10, wherein the wall defines a portion of the cooling passage and the coating defines another portion of the cooling passage. ### Claim 13 (depends on 12) The gas turbine engine component as recited in claim 12, wherein the wall defines 60% to 90% of the surface area of the cooling passage. ### Claim 14 (depends on 1) The gas turbine engine as recited in claim 1, wherein the closed-sided cells are polygonal cells. ### Claim 15 A gas turbine engine comprising: a compressor section; a combustor in fluid communication with the compressor section; and a turbine section in fluid communication with the combustor, at least one of the turbine section or the compressor section including a gas turbine engine component having a passage, and a geometrically segmented coating section adjacent the passage, the geometrically segmented coating section including a wall having a first side bordering the passage and a second side opposite the first side, the second side including an array of polygonal cells defined by cell sidewalls, a coating disposed in the array of polygonal cells, the coating defining an exterior side, and a cooling passage that extends through the wall and the coating, the cooling passage fluidly connecting the passage and the exterior side. ### Claim 16 (depends on 15) The gas turbine engine as recited in claim 15, wherein the cooling passage is sloped relative to the coating. ### Claim 17 (depends on 15) The gas turbine engine as recited in claim 15, wherein the cooling passage includes at least one flow guide. ### Claim 18 (depends on 15) The gas turbine engine as recited in claim 15, wherein the wall defines a portion of the cooling passage and the coating defines another portion of the passage. ### Claim 19 A method for fabricating a geometrically segmented coating section, the method comprising: depositing a coating on a wall, wherein the wall includes a first side and a second side opposite the first side, the second side includes an array of closed-sided cells defined by cell sidewalls, and a cooling passage that extends from the first side and through the array of cells to an encapsulation, and the coating is deposited in the array of cells; removing a portion of the coating along the array of cells; and removing the encapsulation to open the cooling passage. ### Claim 20 (depends on 19) The method as recited in claim 19, wherein the removing of the encapsulation is conducted after the removing of the portion of the coating. ### Claim 21 (depends on 19) The method as recited in claim 19, wherein the removing of the portion of the coating includes exposing the array of cells. ### Claim 22 (depends on 19) The method as recited in claim 19, further comprising depositing additional coating with a thickness that does not bridge over the open cooling passage. ### Claim 23 (depends on 19) The method as recited in claim 19, wherein the coating is formed of ceramic material. ### Claim 24 (depends on 19) The method as recited in claim 19, wherein the encapsulation projects beyond the array of closed-sided cells.