# US 2019/0316485 A1 · Blade outer air seal cooling fin > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0316485 A1 - Document ID: US20190316485A1 - Status: Published application - Kind: A1 - Application number: 15/950,549 - Filed: 2018-04-11 - Published: 2019-10-17 - Earliest claimed: 2018-04-11 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Adam Lee Hart; Brian Levy; Luis Miguel Ayalde; Jose R. Paulino; Patrick Scheelk; Nicolas Bueno - Web page: https://patentgrep.com/patent/US20190316485A1 ## CPC - F01D 11/12: using a rubstrip, e.g. erodible. deformable or resiliently-biased part - F01D 25/12: Cooling - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 11/127: {with a deformable or crushable structure, e.g. honeycomb} - F01D 11/18: using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion - F01D 11/24: by selectively cooling-heating stator or rotor components - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F05D 2220/32: in gas turbines - F05D 2230/237: Brazing - F05D 2240/11: Shroud seal segments - F05D 2240/14: Casings or housings protecting or supporting assemblies within - F05D 2250/11: triangular - F05D 2250/283: honeycomb - F05D 2260/22141: using fins or ribs - F05D 2300/17: Alloys - 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 (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture. ## Claims ### Claim 1 A blade outer air seal (BOAS) for a gas turbine engine, comprising: a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture. ### Claim 2 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, wherein each of the multitude of cooling fins have at least one aperture. ### Claim 3 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, wherein a first set of the multitude of cooling fins have at least one aperture which defines a first area, and a second set of the multitude of cooling fins have at least one aperture which defines a second area different than the first area. ### Claim 4 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, wherein a first set of the multitude of cooling fins have at least one aperture which defines a first area, and a second set of the multitude of cooling fins do not have an aperture. ### Claim 5 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, further comprising a seal secured to the radially inner face of the seal body. ### Claim 6 (depends on 5) The blade outer air seal (BOAS) as recited in claim 5, wherein the seal is a honeycomb seal. ### Claim 7 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, wherein the at least one cooling fin extends outboard of a radially outermost surface of at least one of the leading edge portion and the trailing edge portion. ### Claim 8 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, wherein the seal body forms a full ring hoop. ### Claim 9 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, wherein the multitude of cooling fins forms a triangular shape in cross-section. ### Claim 10 (depends on 1) The blade outer air seal (BOAS) as recited in claim 1, wherein the multitude of cooling fins is manufactured of a nickel-chromium-iron-molybdenum alloy brazed to the radially outer face. ### Claim 11 (depends on 10) The blade outer air seal (BOAS) as recited in claim 10, wherein the multitude of cooling fins is manufactured as a single component that is wrapped around the seal body. ### Claim 12 A gas turbine engine, comprising: an engine casing; a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion, the radially outer face adjacent to the engine casing; a seal secured to the radially inner face of the seal body; and a multitude of cooling fins disposed around the radially outer face between the leading edge portion and the trailing edge portion, at least one of the a multitude of cooling fins having at least one aperture. ### Claim 13 (depends on 12) The gas turbine engine as recited in claim 12, wherein a first set of the multitude of cooling fins have at least one aperture which defines a first area, and a second set of the multitude of cooling fins have at least one aperture which defines a second area different than the first area. ### Claim 14 (depends on 13) The gas turbine engine as recited in claim 13, wherein the second set of the multitude of cooling fins are circumferentially located to be adjacent to a port. ### Claim 15 (depends on 14) The gas turbine engine as recited in claim 14, wherein a BOAS is positioned radially outward from a blade tip of a blade of at least one of a compressor section and a turbine section. ### Claim 16 (depends on 12) The gas turbine engine as recited in claim 12, wherein a first set of the multitude of cooling fins have at least one aperture which defines a first area, the first area associated to with a quantity of airflow to an annular cavity formed by the casing and a BOAS. ### Claim 17 (depends on 12) The gas turbine engine as recited in claim 12, wherein a first set of the multitude of cooling fins have at least one aperture which defines a first area, and a second set of the multitude of cooling fins do not have an aperture. ### Claim 18 (depends on 17) The gas turbine engine as recited in claim 17, wherein the second set of the multitude of cooling fins are circumferentially located to be adjacent to a port. ### Claim 19 A method of controlling a specific rate of thermal expansion that will match a corresponding blade design by using a cooling fin arrangement attached to a blade outer air seal (BOAS) for a gas turbine engine, comprising: controlling an area of at least one aperture in each of a multitude of cooling fins disposed around a radially outer face of the seal body. ### Claim 20 (depends on 19) The gas turbine engine as recited in claim 19, wherein a first set of the multitude of cooling fins have at least one aperture which defines a first area, and a second set of the multitude of cooling fins have at least one aperture which defines a second area different than the first area, wherein the second set of the multitude of cooling fins are circumferentially located to be adjacent to a port.