# US 10,309,253 B2 · Gas turbine engine blade outer air seal profile > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,253 B2 - Document ID: US10309253B2 - Status: Granted - Kind: B2 - Application number: 14/994,186 - Filed: 2016-01-13 - Published: 2017-07-13 - Granted: 2019-06-04 - Earliest claimed: 2016-01-13 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Kevin J. Ryan; Terence P. Tyler, Jr.; Ken F. Blaney - Web page: https://patentgrep.com/patent/US10309253B2 ## CPC - F01D 25/12: Cooling - F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) - F01D 5/12: Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) - 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} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F05D 2220/32: in gas turbines - F05D 2240/11: Shroud seal segments - F05D 2240/35: Combustors or associated equipment - F05D 2250/232: conical - F05D 2260/202: by film cooling - 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) - 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 for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed. ## Claims ### Claim 1 A blade outer air seal for a gas turbine engine comprising: a gas path surface exposed to exhaust gas flow; a first side extending radially outward from the gas path surface; a second side extending radially outward from the gas path surface; an axially forward side and an axially aft side, wherein the gas path surface and the axially forward side define an arc and a point of origin is defined at the center of curvature of the arc on the axially forward side; and a plurality of film cooling holes disposed on at least one of the gas path surface, the first side and the second side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to the defined point of origin. ### Claim 2 (depends on 1) The blade outer air seal as recited in claim 1, wherein the forward side and the aft side include features for securement to a support structure within the turbine section of the gas turbine engine. ### Claim 3 (depends on 1) The blade outer air seal as recited in claim 1, the blade outer air seal is one of a plurality of outer air seals disposed circumferentially about a longitudinal axis of the gas turbine engine. ### Claim 4 (depends on 1) The blade outer air seal as recited in claim 1, wherein each of the film cooling air holes are located within a true position of 0.023 inches (0.58 mm). ### Claim 5 (depends on 1) The blade outer air seal as recited in claim 1, wherein at least some of the film cooling air holes comprise one of a conical and cylindrical shape. ### Claim 6 (depends on 1) The blade outer air seal as recited in claim 1, wherein each of the film cooling air holes correspond with a passage through the corresponding surface and at least some of the passages are disposed at an angle different than normal relative to the surface. ### Claim 7 (depends on 1) The blade outer air seal as recited in claim 1, wherein a plurality of film cooling holes have a diameter within a range of 0.010-0.035 inch (0.25-0.89 mm). ### Claim 8 A gas turbine engine comprising: a compressor section disposed about an axis; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor, the turbine section includes at least one rotor having a plurality of rotating blades; and a plurality of blade outer air seals circumferentially surrounding the rotating blades, wherein each of the blade outer air seals includes: a gas path surface exposed to exhaust gas flow; a first side extending radially outward from the gas path surface; a second side extending radially outward from the gas path surface; an axially forward side and an axially aft side, wherein the gas path surface and the axially forward side define an arc and a zero-coordinate is defined at the center of curvature of the arc on the axially forward side; and a plurality of film cooling holes disposed on at least one of the gas path surface, the first side and the second side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to the zero-coordinate. ### Claim 9 (depends on 8) The gas turbine engine as recited in claim 8, wherein the forward side and the aft side include features for securement to a support structure within the turbine section of the gas turbine engine. ### Claim 10 (depends on 8) The gas turbine engine as recited in claim 8, wherein each of the plurality of film cooling air holes are located within a true position of 0.023 inches (0.58 mm). ### Claim 11 (depends on 8) The gas turbine engine as recited in claim 8, wherein at least some of the plurality of film cooling air holes comprise one of a conical and cylindrical shape. ### Claim 12 (depends on 8) The gas turbine engine as recited in claim 8, wherein each of the plurality of film cooling air holes are in communication with a corresponding plurality of passages and at least some of the passages are disposed at an angle different than normal relative to the surface. ### Claim 13 (depends on 8) The gas turbine engine as recited in claim 8, wherein a plurality of film cooling holes have a diameter within a range of 0.010-0.035 inch (0.25-0.89 mm).