# US 11,028,700 B2 · Airfoil with cooling passage circuit through platforms and airfoil section > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,700 B2 - Document ID: US11028700B2 - Status: Granted - Kind: B2 - Application number: 16/594,125 - Filed: 2019-10-07 - Published: 2020-10-22 - Granted: 2021-06-08 - Earliest claimed: 2018-11-09 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Allan N. Arisi; Tracy A. Propheter-Hinckley - Web page: https://patentgrep.com/patent/US11028700B2 ## CPC - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 5/187: {Convection cooling} - 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 25/12: Cooling - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2240/124: related to the suction side of a stator vane - F05D 2240/126: Baffles or ribs - F05D 2240/127: Vortex generators, turbulators, or the like, for mixing - F05D 2240/81: Cooled platforms - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/202: by film cooling - F05D 2260/204: by the use of microcircuits - F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes - 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 An airfoil includes a cooling passage circuit that has a first plenum, a skincore passage, a first connector passage, a second plenum, and a second connector passage. The first plenum is in a first platform and extends adjacent a first side, a trailing end, and a second side of and airfoil section. The skincore passage is embedded in the first side of the airfoil section and extends longitudinally. The first connector passage is longitudinally spaced from an internal core cavity in the airfoil section so as to extend around the cavity. The first connector passage connects the first plenum with the skincore passage. The second plenum is in the second platform and extends adjacent the first side, the trailing end, and the second side of the airfoil section. The second connector passage connects the skincore passage with the second plenum. ## Claims ### Claim 1 An airfoil comprising: an airfoil section having an airfoil wall defining a leading end, a trailing end, and first and second sides joining the leading end and the trailing end, the first and second sides spanning in a longitudinal direction between first and second ends, the airfoil wall circumscribing an internal core cavity; first and second platforms attached, respectively, with the first and second ends; a cooling passage circuit extending in the first platform, the airfoil section, and the second platform, the cooling passage circuit including a first plenum in the first platform, the first plenum extending adjacent the first side of the airfoil wall, adjacent the trailing end, and adjacent the second side of the airfoil wall, a skincore passage embedded in the first side of the airfoil wall and extending longitudinally, a first connector passage longitudinally spaced from the internal core cavity so as to extend around the internal core cavity, the first connector passage connecting the first plenum with the skincore passage, a second plenum in the second platform, the second plenum extending adjacent the first side of the airfoil wall, adjacent the trailing end, and adjacent the second side of the airfoil wall, and a second connector passage connecting the skincore passage with the second plenum. ### Claim 2 (depends on 1) The airfoil as recited in claim 1, wherein the first plenum has an inlet adjacent the first side. ### Claim 3 (depends on 1) The airfoil as recited in claim 1, wherein the first plenum wraps around the internal core cavity. ### Claim 4 (depends on 1) The airfoil as recited in claim 1, wherein the skincore passage includes a plurality of longitudinally-elongated ribs that define longitudinally-elongated passages there between. ### Claim 5 (depends on 4) The airfoil as recited in claim 4, wherein the skincore passage includes a plurality of trip strips in the longitudinally-elongated passages. ### Claim 6 (depends on 1) The airfoil as recited in claim 1, wherein the second connector passage defines a central connector passage axis that forms an oblique angle with the longitudinal direction. ### Claim 7 (depends on 1) The airfoil as recited in claim 1, wherein the second plenum includes a plurality of trip strips. ### Claim 8 (depends on 1) The airfoil as recited in claim 1, wherein the second platform includes a plurality of orifices, each said orifice having an inlet end that opens to the second plenum and an outlet end that opens to an exterior of the second platform. ### Claim 9 (depends on 1) The airfoil as recited in claim 1, wherein the first side is a suction side and the second side is a pressure side. ### Claim 10 (depends on 9) The airfoil as recited in claim 9, wherein the skincore passage includes a plurality of longitudinally-elongated ribs that define longitudinally-elongated passages there between. ### Claim 11 (depends on 10) The airfoil as recited in claim 10, wherein the second platform includes a plurality of orifices, each said orifice having an inlet end that opens to the second plenum and an outlet end that opens to an exterior of the second platform. ### Claim 12 (depends on 11) The airfoil as recited in claim 11, wherein the first plenum wraps around the internal core cavity. ### Claim 13 (depends on 12) The airfoil as recited in claim 12, wherein the second connector passage defines a central connector passage axis that forms an oblique angle with the longitudinal direction. ### 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, the turbine section having a turbine airfoil that includes an airfoil section having an airfoil wall defining a leading end, a trailing end, and first and second sides joining the leading end and the trailing end, the first and second sides spanning in a longitudinal direction between first and second ends, the airfoil wall circumscribing an internal core cavity, first and second platforms attached, respectively, with the first and second ends, and a cooling passage circuit extending in the first platform, the airfoil section, and the second platform, the cooling passage circuit including a first plenum in the first platform, the first plenum extending adjacent the first side of the airfoil wall, adjacent the trailing end, and adjacent the second side of the airfoil wall, a skincore passage embedded in the first side of the airfoil wall and extending longitudinally, a first connector passage longitudinally spaced from the internal core cavity so as to extend around the internal core cavity, the first connector passage connecting the first plenum with the skincore passage, a second plenum in the second platform, the second plenum extending adjacent the first side of the airfoil wall, adjacent the trailing end, and adjacent the second side of the airfoil wall, and a second connector passage connecting the skincore passage with the second plenum. ### Claim 15 (depends on 14) The gas turbine engine as recited in claim 14, wherein the first plenum wraps around the internal core cavity. ### Claim 16 (depends on 14) The gas turbine engine as recited in claim 14, wherein the skincore passage includes a plurality of longitudinally-elongated ribs that define longitudinally-elongated passages there between. ### Claim 17 (depends on 14) The gas turbine engine as recited in claim 14, wherein the second connector passage defines a central connector passage axis that forms an oblique angle with the longitudinal direction. ### Claim 18 (depends on 14) The gas turbine engine as recited in claim 14, wherein the second platform includes a plurality of orifices, each said orifice having an inlet end that opens to the second plenum and an outlet end that opens to an exterior of the second platform. ### Claim 19 (depends on 14) The gas turbine engine as recited in claim 14, wherein the first side is a suction side and the second side is a pressure side.