# US 2019/0169994 A1 · Double wall turbine gas turbine engine blade cooling configuration > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0169994 A1 - Document ID: US20190169994A1 - Status: Published application - Kind: A1 - Application number: 15/832,430 - Filed: 2017-12-05 - Published: 2019-06-06 - Earliest claimed: 2017-12-05 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Christopher Whitfield; Carey Clum; Dominic J. Mongillo, JR. - Web page: https://patentgrep.com/patent/US20190169994A1 ## CPC - F01D 5/187: {Convection cooling} - F05D 2220/32: in gas turbines - F05D 2240/24: for turbines - F05D 2240/301: Cross-sectional characteristics - F05D 2250/185: serpentine-like - F05D 2260/201: by impingement of a fluid - F05D 2260/202: by film cooling - F05D 2260/204: by the use of microcircuits - 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 pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A slot extends longitudinally in the skin passage. A resupply hole fluidly interconnects the core passage and the slot. ## Claims ### Claim 1 An airfoil comprising: pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, a skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core passage, the core passage and the skin passage are configured to have a same direction of fluid flow, a slot extends longitudinally in the skin passage, and a resupply hole fluidly interconnects the core passage and the slot. ### Claim 2 (depends on 1) The airfoil of claim 1, a centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulent flow region in the skin passage. ### Claim 3 (depends on 2) The airfoil of claim 2, wherein the angle is in a range of 5°-45°. ### Claim 4 (depends on 1) The airfoil of claim 1, wherein the skin passage has an aspect ratio that may vary between 3:1≥H/W≥1:5, wherein H corresponds to a passage height and W corresponds to a passage width. ### Claim 5 (depends on 4) The airfoil of claim 4, wherein the passage height (H) is in a range of 0.010-0.200 inches (0.25-5.08 mm). ### Claim 6 (depends on 1) The airfoil of claim 1, comprising serpentine cooling passage having first, second and third cooling passages, the first and third cooling passages having a direction of fluid flow toward the tip, and the second cooling passage having a direction of fluid flow away from the tip, the core passage provided by one of the first, second and third cooling passages. ### Claim 7 (depends on 1) The airfoil of claim 1, wherein a film cooling hole extends from the skin passage to the exterior airfoil surface. ### Claim 8 (depends on 1) The airfoil of claim 1, wherein the airfoil is a turbine blade. ### Claim 9 (depends on 1) The airfoil of claim 1, wherein the slot extends longitudinally in a direction that is different than the direction of fluid flow. ### Claim 10 (depends on 9) The airfoil of claim 9, wherein the slot extends longitudinally in a direction that is normal to the direction of fluid flow. ### Claim 11 (depends on 9) The airfoil of claim 9, wherein the direction of fluid flow is the radial direction. ### Claim 12 (depends on 1) The airfoil of claim 1, wherein multiple resupply holes feed the slots from the core passage. ### Claim 13 (depends on 1) The airfoil of claim 1, wherein the resupply hole terminates in an exit at the slot, the exit is provided by a diffuser. ### Claim 14 A gas turbine engine comprising: a combustor section arranged fluidly between compressor and turbine sections; and an airfoil arranged in the turbine section, the airfoil including pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, a skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core passage, the core passage and the skin passage are configured to receive a cooling fluid from the compressor section and have a same direction of fluid flow, a slot extends longitudinally in the skin passage, and a resupply hole fluidly interconnects the core passage and the slot. ### Claim 15 (depends on 14) The gas turbine engine of claim 14, a centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulent flow region in the skin passage, wherein the angle is in a range of 5°-45°. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the skin passage has an aspect ratio that may vary between 3:1≥H/W≥1:5, wherein H corresponds to a passage height and W corresponds to a passage width, wherein the passage height (H) is in a range of 0.010-0.200 inches (0.25-5.08 mm). ### Claim 17 (depends on 14) The gas turbine engine of claim 14, wherein the slot extends longitudinally in a direction that is different than the direction of fluid flow. ### Claim 18 (depends on 17) The gas turbine engine of claim 17, wherein the slot extends longitudinally in a direction that is normal to the direction of fluid flow. ### Claim 19 (depends on 17) The gas turbine engine of claim 17, wherein the direction of fluid flow is the radial direction. ### Claim 20 (depends on 14) The gas turbine engine of claim 14, wherein multiple resupply holes feed the slots from the core passage.