# US 2021/0340876 A1 · Turbine blade cooling hole combination > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2021/0340876 A1 - Document ID: US20210340876A1 - Status: Published application - Kind: A1 - Application number: 16/866,130 - Filed: 2020-05-04 - Published: 2021-11-04 - Earliest claimed: 2020-05-04 - Assignees: Raytheon Technologies Corporation - Applicants: Raytheon Technologies Corporation - Inventors: Pedro David Laureano; John A. Lucena - Web page: https://patentgrep.com/patent/US20210340876A1 ## CPC - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/303: related to the leading edge of a rotor blade - F05D 2240/304: related to the trailing edge of a rotor blade - F05D 2240/305: related to the pressure side of a rotor blade - F05D 2240/81: Cooled platforms - F05D 2260/202: by film cooling - 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 turbine blade includes an airfoil, a platform and a suction pocket positioned under the platform on a suction side. The suction pocket includes a platform underside, and a fillet connecting the platform underside into a neck. The neck extends into a fir tree. A first cooling hole extends from a first end in the platform underside to a second end in a top surface of the platform. A second cooling hole extends from a first end in the platform underside, but closer to the fillet than is the first end of the first cooling hole, to a second end in the top surface. There is a third cooling hole having a first end in the fillet and extending to a second end at the top surface. A gas turbine engine is also disclosed. ## Claims ### Claim 1 A turbine blade comprising: an airfoil including a pressure side and a suction side; a platform including a pressure side wall and a suction side wall and having a leading edge end wall and a trailing edge end wall; a suction pocket positioned under the platform on the suction side; the suction pocket including a platform underside, and a fillet connecting said platform underside into a neck, said neck extending into a fir tree; and there being at least three cooling holes, with a first cooling hole extending from a first end in said platform underside to a second end in a top surface of said platform along a direction having a component toward said suction side wall, and having a component towards said trailing edge end wall, there being a second cooling hole extending from a first end in said platform underside, but closer to said fillet than is said first end of said first cooling hole, to a second end in said top surface along a direction having a component toward said pressure side end wall and a component toward said trailing edge, there being a third cooling hole having a first end in said fillet and extending to a second end at said top surface along a direction and having a component toward said pressure side end wall and another component towards said trailing edge end wall. ### Claim 2 (depends on 1) The turbine blade as set forth in claim 1, wherein there is a fourth cooling hole having a first end in said fillet and extending to a second end in said upper surface along a direction having a component towards said pressure side end wall and another component towards the trailing edge end wall. ### Claim 3 (depends on 2) The turbine blade as set forth in claim 2, wherein said first end of said second cooling hole is within 1-3 diameters of said second cooling hole from an edge of said fillet at said platform underside. ### Claim 4 (depends on 2) The turbine blade as set forth in claim 2, wherein said second end of said first cooling hole at said upper surface of said platform is within 4 diameters of said first cooling hole measured from said suction side end wall. ### Claim 5 (depends on 2) The turbine blade as set forth in claim 2, wherein there are at least three other cooling hole ends in said upper surface of said platform within a distance of 4 diameters of said first cooling hole measured from said suction side end wall. ### Claim 6 (depends on 5) The turbine blade as set forth in claim 5, wherein the component through which the direction of said second cooling hole extends towards said trailing edge is greater than the component of the direction towards said trailing edge side wall for said third and said fourth cooling holes. ### Claim 7 (depends on 6) The turbine blade as set forth in claim 6, wherein said second end of said second cooling hole is closer to said trailing edge side wall than is said second end of said third cooling hole, but further from said trailing edge side wall than said second end of said fourth cooling hole. ### Claim 8 (depends on 7) The turbine blade as set forth in claim 7, wherein the directions through which the first, second, third and fourth cooling holes extend form an angle with said top surface of said platform, and said angle associated with said first cooling hole is greater than said angles associated with said second, third and fourth cooling hole. ### Claim 9 (depends on 2) The turbine blade as set forth in claim 2, wherein the component through which the direction of said second cooling hole extends towards said trailing edge is greater than the component of the direction towards said trailing edge side wall for said third and said fourth cooling holes. ### Claim 10 (depends on 2) The turbine blade as set forth in claim 2, wherein said second end of said second cooling hole is closer to said trailing edge side wall than is said second end of said third cooling hole, but further from said trailing edge side wall than said second end of said fourth cooling hole. ### Claim 11 (depends on 2) The turbine blade as set forth in claim 2, wherein the directions through which the first, second, third and fourth cooling holes extend form an angle with said top surface of said platform, and said angle associated with said first cooling hole is greater than said angles associated with said second, third and fourth cooling holes. ### Claim 12 A gas turbine engine comprising: a compressor section; a combustor; a turbine section having at least one turbine blade; and the at least one turbine blade including: an airfoil including a pressure side and a suction side; a platform including a pressure side wall and a suction side wall and having a leading edge end wall and a trailing edge end wall; a suction pocket positioned under the platform on the suction side; the suction pocket including a platform underside, and a fillet connecting said platform underside into a neck, said neck extending into a fir tree; and there being at least three cooling holes, with a first cooling hole extending from a first end in said platform underside to a second end in a top surface of said platform along a direction having a component toward said suction side wall, and having a component towards said trailing edge end wall, there being a second cooling hole extending from a first end in said platform underside, but closer to said fillet than is said first end of said first cooling hole, to a second end in said top surface along a direction having a component toward said pressure side end wall and a component toward said trailing edge, there being a third cooling hole having a first end in said fillet and extending to a second end at said top surface along a direction and having a component toward said pressure side end wall and another component towards said trailing edge end wall. ### Claim 13 (depends on 12) The gas turbine engine as set forth in claim 12, wherein there is a fourth cooling hole having a first end in said fillet and extending to a second end in said top surface, along a direction having a component towards said pressure side end wall and another component towards the trailing edge end wall. ### Claim 14 (depends on 12) The gas turbine engine as set forth in claim 12, wherein said first end of said second cooling hole is within 1-3 diameters of said second cooling hole from an edge of said fillet at said platform underside. ### Claim 15 (depends on 13) The gas turbine engine as set forth in claim 13, wherein said second end of said first cooling hole at said upper surface of said platform is within 4 diameters of said first cooling hole measured from said suction side end wall, and there are at least three other cooling hole ends in said upper surface of said platform within a distance of 4 diameters of said first cooling hole measured from said suction side end wall. ### Claim 16 (depends on 15) The gas turbine engine as set forth in claim 15, wherein said second end of said second cooling hole is closer to said trailing edge side wall than is said second end of said third cooling hole, but further from said trailing edge side wall than said second end of said fourth cooling hole. ### Claim 17 (depends on 16) The gas turbine engine as set forth in claim 16, wherein the directions through which the first, second, third and fourth cooling holes extend form an angle with said top surface of said platform, and said angle associated with said first cooling hole is greater than said angles associated with said second, third and fourth cooling holes. ### Claim 18 (depends on 13) The gas turbine engine as set forth in claim 13, wherein the component through which the direction of said second cooling hole extends towards said trailing edge is greater than the component of the direction towards said trailing edge side wall for said third and said fourth cooling holes. ### Claim 19 (depends on 13) The gas turbine engine as set forth in claim 13, wherein said second end of said second cooling hole is closer to said trailing edge side wall than is said second end of said third cooling hole, but further from said trailing edge side wall than said second end of said fourth cooling hole. ### Claim 20 (depends on 13) The gas turbine engine as set forth in claim 13, wherein the directions through which the first, second, third and fourth cooling holes extend form an angle with said top surface of said platform, and said angle associated with said first cooling hole is greater than said angles associated with said second, third and fourth cooling holes.