# US 10,309,239 B2 · Cooling hole for a gas turbine engine component > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,239 B2 - Document ID: US10309239B2 - Status: Granted - Kind: B2 - Application number: 14/766,496 - Filed: 2014-02-07 - Published: 2016-01-14 - Granted: 2019-06-04 - Earliest claimed: 2013-02-15 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Brandon W. Spangler; Dominic Mongillo - Web page: https://patentgrep.com/patent/US10309239B2 ## CPC - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F01D 11/20: Actively adjusting tip-clearance - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F01D 5/288: {Protective coatings for blades} - F05D 2240/11: Shroud seal segments - F05D 2240/81: Cooled platforms - F05D 2250/12: rectangular - F05D 2260/202: by film cooling - F23R 2900/03042: Film cooled combustion chamber walls or domes - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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 ## Abstract A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle. ## Claims ### Claim 1 A component for a gas turbine engine, comprising: a wall having an internal surface and an outer skin; a cooling hole having an inlet extending from said internal surface and merging into a metering section, and a diffusion section downstream of said metering section that extends to an outlet located at said outer skin; and wherein said diffusion section of said cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of said diffusion section, said downstream diffusion angle being less than said first side diffusion angle and said second side diffusion angle, said first side diffusion angle is a different angle from said second side diffusion angle, said downstream surface of said diffusion section is coaxial with a downstream surface of said metering section, and an upstream surface of said diffusion section opposite said diffusion section from said downstream surface is coaxial with said metering section. ### Claim 2 (depends on 1) The component as recited in claim 1, wherein said wall is part of a vane. ### Claim 3 (depends on 1) The component as recited in claim 1, wherein said wall is part of a blade. ### Claim 4 (depends on 1) The component as recited in claim 1, wherein said wall is part of a blade outer air seal (BOAS). ### Claim 5 (depends on 1) The component as recited in claim 1, wherein said diffusion section includes a first side surface that diverges in a first axial direction from an axis of said metering section and a second side surface that diverges in a second axial direction from said axis. ### Claim 6 (depends on 5) The component as recited in claim 5, wherein said first side surface and said second side surface diverge at said first and second side diffusion angles relative to said axis. ### Claim 7 (depends on 6) The component as recited in claim 6, wherein said side diffusion angles are between 1° and 15° relative to said axis. ### Claim 8 (depends on 1) The component as recited in claim 1, wherein said downstream diffusion angle is between 0° and 10°. ### Claim 9 (depends on 1) The component as recited in claim 1, wherein said diffusion section does not diffuse toward a downstream edge of said wall. ### Claim 10 A component for a gas turbine engine, comprising: a wall having an internal surface and an outer skin; a cooling hole having an inlet extending from said internal surface and merging into a metering section, and a diffusion section downstream of said metering section that extends to an outlet located at said outer skin; and wherein each of said metering section and said diffusion section includes a downstream surface, said downstream surface of said diffusion section is coaxial with said downstream surface of said metering section, and said diffusion section includes a diffusion section inlet and a diffusion section outlet downstream of said diffusion section inlet, said diffusion section outlet includes a leading edge and a trailing edge, and said trailing edge is generally linear and defines the downstream most end across an entire width of said cooling hole, and said trailing edge is defined where said downstream surface meets said outer skin. ### Claim 11 (depends on 10) The component as recited in claim 10, wherein said downstream surface excludes a downstream diffusion angle. ### Claim 12 (depends on 10) The component as recited in claim 10, wherein said diffusion section includes a first side surface that diverges in a first axial direction from an axis of said metering section and a second side surface that diverges in a second axial direction from said axis. ### Claim 13 (depends on 12) The component as recited in claim 12, wherein said first side surface and said second side surface diverge at a side diffusion angle of between 1° and 15° from said axis. ### Claim 14 (depends on 12) The component as recited in claim 12, wherein said first side surface and said second side surface each diverge at a side diffusion angle of about 10° from said axis, said downstream surface of said diffusion section diffuses at a 0° angle relative to an axis of said metering section. ### Claim 15 (depends on 9) The component as recited in claim 9, wherein the diffusion section includes a diffusion section inlet and a diffusion section outlet downstream of the diffusion section inlet, the diffusion section outlet includes a leading edge and a trailing edge, and the trailing edge is generally linear and defines the downstream most end across an entire width of the cooling hole. ### Claim 16 A component for a gas turbine engine, comprising: a wall having an internal surface and an outer skin; a cavity, wherein the internal surface faces into the cavity; a cooling hole having an inlet extending from said internal surface and merging into a metering section, and a diffusion section downstream of said metering section that extends to an outlet located at said outer skin; and wherein said diffusion section of said cooling hole includes a first side diffusion angle, a second side diffusion angle, and a downstream diffusion angle at a downstream surface of said diffusion section, said first side diffusion angle is a different angle from said second side diffusion angle, said downstream diffusion angle is 0° from an axis of said metering section, said downstream surface of said diffusion section is coaxial with a downstream surface of said metering section, said diffusion section does not diffuse toward a downstream edge of said wall, and said diffusion section includes a diffusion section inlet and a diffusion section outlet downstream of said diffusion section inlet, said diffusion section outlet includes a leading edge and a trailing edge, and said trailing edge is generally linear and defines the downstream most end across an entire width of said cooling hole, and said trailing edge is defined where said downstream surface meets said outer skin. ### Claim 17 (depends on 16) The component as recited in claim 16, wherein an upstream surface of the diffusion section opposite said diffusion section from said downstream surface is coaxial with the metering section. ### Claim 18 (depends on 10) The component as recited in claim 10, wherein an upstream surface of said diffusion section opposite said diffusion section from said downstream surface is coaxial with said metering section. ### Claim 19 (depends on 1) The component as recited in claim 1, wherein said diffusion section includes a diffusion section inlet and a diffusion section outlet downstream of said diffusion section inlet, said diffusion section outlet includes a leading edge and a trailing edge, and said trailing edge is generally linear and defines the downstream most end across an entire width of said cooling hole, and said trailing edge is defined where said downstream surface meets said outer skin. ### Claim 20 (depends on 19) The component as recited in claim 19, wherein said leading edge is generally linear.