# US 11,028,702 B2 · Airfoil with cooling passage network having flow guides > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,702 B2 - Document ID: US11028702B2 - Status: Granted - Kind: B2 - Application number: 16/218,691 - Filed: 2018-12-13 - Published: 2020-06-18 - Granted: 2021-06-08 - Earliest claimed: 2018-12-13 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Tracy A. Propheter-Hinckley; Allan N. Arisi - Web page: https://patentgrep.com/patent/US11028702B2 ## CPC - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - F01D 5/187: {Convection cooling} - F01D 25/12: Cooling - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/126: Baffles or ribs - F05D 2260/201: by impingement of a fluid - F05D 2260/204: by the use of microcircuits - F05D 2260/2214: by increasing the heat transfer surface - F05D 2260/22141: using fins or ribs - 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 An airfoil includes a cooling passage network is embedded in an airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an entrance region adjacent the first end of the airfoil section, a plenum region between the entrance region and the second end of the airfoil section, and an exit region adjacent the plenum region. The entrance region includes a plurality of flow guides that divide the entrance region into a plurality of channels that open into the plenum region. The plenum region includes a plurality of pedestals that have a shape that is different from the flow guides. ## 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; and a cooling passage network embedded in the airfoil wall between inner and outer portions of the airfoil wall, the cooling passage network having an entrance region adjacent the first end of the airfoil section, a plenum region between the entrance region and the second end of the airfoil section, and an exit region adjacent the plenum region, the entrance region including a plurality of flow guides dividing the entrance region into a plurality of channels opening into the plenum region, each of the flow guides having a distinct shape among the plurality of flow guides, the flow guides defining flow guide lengths in the longitudinal direction and the flow guide lengths differ from each other, and the plenum region including a plurality of pedestals having a shape different from the flow guides. ### Claim 2 (depends on 1) The airfoil as recited in claim 1, wherein the flow guides define flow guide thicknesses in a direction perpendicular to the longitudinal direction, and the flow guide thicknesses differ from each other. ### Claim 3 (depends on 1) The airfoil as recited in claim 1, wherein at least one of the flow guides is arced. ### Claim 4 (depends on 1) The airfoil as recited in claim 1, wherein the plurality of flow guides consists of three flow guides dividing the entrance region into four of the channels. ### Claim 5 (depends on 1) The airfoil as recited in claim 1, wherein at least two of the flow guides overlap in a direction perpendicular to the longitudinal direction. ### Claim 6 (depends on 1) The airfoil as recited in claim 1, wherein the pedestals define pedestal lengths in the longitudinal direction, the flow guides define flow guide lengths in the longitudinal direction, and the pedestal lengths are less than at least one of the flow guide lengths. ### Claim 7 (depends on 6) The airfoil as recited in claim 6, wherein the exit region includes a rib that is elongated in the longitudinal direction. ### Claim 8 (depends on 7) The airfoil as recited in claim 7, wherein the rib defines a rib length in the longitudinal direction, and the rib length is greater than each of the pedestal lengths. ### Claim 9 (depends on 1) The airfoil as recited in claim 1, including first and second platforms attached, respectively, with the first and second ends, the second platform including a platform plenum, and the cooling passage network including an outlet orifice opening to the platform plenum. ### Claim 10 (depends on 1) The airfoil as recited in claim 1, wherein the cooling passage network defines a longitudinal axis, and the entrance region has an inlet that is biased to one side of the longitudinal axis. ### Claim 11 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, and a cooling passage network embedded in the airfoil wall between inner and outer portions of the airfoil wall, the cooling passage network having an entrance region adjacent the first end of the airfoil section, a plenum region between the entrance region and the second end of the airfoil section, and an exit region adjacent the plenum region, the entrance region including a plurality of flow guides dividing the entrance region into a plurality of channels opening into the plenum region, each of the flow guides having a distinct shape among the plurality of flow guides, the flow guides defining flow guide lengths in the longitudinal direction and the flow guide lengths differ from each other, and the plenum region including a plurality of pedestals having a shape different from the flow guides. ### Claim 12 (depends on 11) The gas turbine engine as recited in claim 11, wherein the flow guides define flow guide thicknesses in a direction perpendicular to the longitudinal direction, and the flow guide thicknesses differ from each other. ### Claim 13 (depends on 11) The gas turbine engine as recited in claim 11, wherein at least one of the flow guides is arced. ### Claim 14 (depends on 13) The gas turbine engine as recited in claim 13, wherein at least one of the flow guides is straight. ### Claim 15 (depends on 11) The gas turbine engine as recited in claim 11, wherein the plurality of flow guides consists of three flow guides dividing the entrance region into four of the channels. ### Claim 16 (depends on 11) The gas turbine engine as recited in claim 11, wherein at least two of the flow guide overlap in a direction perpendicular to the longitudinal direction. ### Claim 17 (depends on 11) The gas turbine engine as recited in claim 11, wherein the pedestals defines pedestal lengths in the longitudinal direction, the glow guides define flow guide lengths in the longitudinal direction, and the pedestal lengths are less than at least one of the flow guide lengths. ### Claim 18 (depends on 17) The gas turbine engine as recited in claim 17, wherein the exit region includes a rib that is elongated in the longitudinal direction, the rib defines a rib length in the longitudinal direction, and the rib length is greater than each of the pedestal lengths. ### Claim 19 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 having, respectively, first and second platform plenums; and a cooling passage network embedded in the airfoil wall between inner and outer portions of the airfoil wall, the cooling passage network having an entrance region including an inlet that opens to the first platform plenum and receives cooling air there from, a plenum region between the entrance region and the second end of the airfoil section, and an exit region including an outlet that opens to the second platform plenum to discharge the cooling air thereto, the entrance region including a plurality of flow guides dividing the entrance region into a plurality of channels opening into the plenum region, and the plenum region including a plurality of pedestals having a shape different from the flow guides. ### Claim 20 (depends on 19) The airfoil as recited in claim 19, wherein the cooling passage network defines a longitudinal axis, and the inlet is biased to one side of the longitudinal axis.