# US 10,480,334 B2 · Airfoil with geometrically segmented coating section > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,334 B2 - Document ID: US10480334B2 - Status: Granted - Kind: B2 - Application number: 15/354,118 - Filed: 2016-11-17 - Published: 2018-05-17 - Granted: 2019-11-19 - Earliest claimed: 2016-11-17 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Eric A. Hudson - Web page: https://patentgrep.com/patent/US10480334B2 ## CPC - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 5/14: Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) - F01D 5/288: {Protective coatings for blades} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F04D 29/023: {especially adapted for elastic fluid pumps} - F04D 29/324: {Blades} - F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)} - F05D 2220/32: in gas turbines - F05D 2230/90: Coating; Surface treatment - F05D 2240/124: related to the suction side of a stator vane - F05D 2240/306: related to the suction side of a rotor blade - F05D 2240/35: Combustors or associated equipment - F05D 2250/20: Three-dimensional - F05D 2250/28: patterned - F05D 2300/17: Alloys - F05D 2300/20: Oxide or non-oxide ceramics - F05D 2300/608: Microstructure - 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) - 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 airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells. ## Claims ### Claim 1 An airfoil comprising: an airfoil body having a geometrically segmented coating section, the geometrically segmented coating section including a wall having an outer side, the outer side including an array of cells that are closed-sided, and a coating disposed in the array of cells, wherein the geometrically segmented coating section is on a portion of the airfoil section, and an adjacent portion of the airfoil section includes the coating but excludes the cells. ### Claim 2 (depends on 1) The airfoil as recited in claim 1, wherein the cells are polygonal. ### Claim 3 (depends on 1) The airfoil as recited in claim 1, wherein the coating substantially fills the cells. ### Claim 4 (depends on 1) The airfoil as recited in claim 1, wherein the coating fully embeds the cells. ### Claim 5 (depends on 1) The airfoil as recited in claim 1, wherein the airfoil body is an airfoil section. ### Claim 6 (depends on 5) The airfoil as recited in claim 5, wherein the geometrically segmented coating section is on a suction side of the airfoil section. ### Claim 7 (depends on 5) The airfoil as recited in claim 5, wherein the geometrically segmented coating section is on a pressure side of the airfoil section. ### Claim 8 (depends on 1) The airfoil as recited in claim 1, wherein the airfoil body is a platform. ### Claim 9 (depends on 1) The airfoil as recited in claim 1, wherein the coating is substantially formed of ceramic. ### Claim 10 (depends on 9) The airfoil as recited in claim 9, wherein the coating has a laminar microstructure. ### Claim 11 (depends on 10) The airfoil as recited in claim 10, wherein the ceramic includes yttria and the wall is formed of an alloy. ### Claim 12 (depends on 1) The airfoil as recited in claim 1, wherein adjacent cells of the array of cells share a common uniform thickness wall. ### Claim 13 (depends on 1) The airfoil as recited in claim 1, wherein the coating is flat such that it excludes contours from the cells. ### Claim 14 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 an airfoil having an airfoil body, the airfoil body including a geometrically segmented coating section, the geometrically segmented coating section including a wall having an outer side, the outer side including an array of cells that are closed-sided, and a coating disposed in the array of cells, wherein the geometrically segmented coating section is on a portion of the airfoil section, and an adjacent portion of the airfoil section includes the coating but excludes the cells. ### Claim 15 (depends on 14) The gas turbine engine as recited in claim 14, wherein the cells are polygonal and the coating substantially fills the cells. ### Claim 16 (depends on 14) The gas turbine engine as recited in claim 14, wherein the airfoil body is an airfoil section. ### Claim 17 (depends on 16) The gas turbine engine as recited in claim 16, wherein the geometrically segmented coating section is on a suction side of the airfoil section. ### Claim 18 (depends on 14) The gas turbine engine as recited in claim 14, wherein the coating is substantially formed of ceramic and has a laminar microstructure. ### Claim 19 (depends on 18) The gas turbine engine component as recited in claim 18, wherein the ceramic includes yttria and the wall is formed of an alloy. ### Claim 20 (depends on 19) The gas turbine engine component as recited in claim 19, wherein the geometrically segmented coating section is on a suction side of the airfoil section.