# US 8,770,919 B2 · Turbine disk and gas turbine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,770,919 B2 - Document ID: US8770919B2 - Status: Granted - Kind: B2 - Application number: 12/864,006 - Filed: 2009-01-16 - Published: 2010-11-18 - Granted: 2014-07-08 - Earliest claimed: 2008-02-27 - Assignees: Mitsubishi Heavy Industries, Ltd. - Applicants: Shinya Hashimoto; Kenichi Arase - Inventors: Shinya Hashimoto; Kenichi Arase - Web page: https://patentgrep.com/patent/US8770919B2 ## CPC - F01D 5/087: {in the radial passages of the rotor disc} - F01D 5/081: {Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence)} - F01D 5/323: {Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor} - F05D 2260/941: particularly aimed at mechanical or thermal stress reduction - 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 ## Abstract In a turbine disk and a gas turbine, the turbine disk is firmly connected to a rotor (24) to be rotatably supported; a plurality of rotor blades (22a) is arranged on an outer circumference thereof in a circumferential direction; first cooling holes (42) penetrating the turbine disk from inside toward outside thereof and being communicatively connected to a cooling passage (41) arranged inside of the rotor blades (22a) are arranged in the circumferential direction; second cooling holes (43) arranged between each of the first cooling holes (42) and penetrating the turbine disk from the inside toward the outside thereof are provided; and the first cooling holes (42) and the second cooling holes (43) are communicatively connected by way of a radial direction communicating channel (47), to alleviate concentration of stress and to improve durability. ## Claims ### Claim 1 A turbine disk that is supported rotatably and in which a plurality of rotor blades is arranged on a circumference thereof in a circumferential direction, the turbine disk comprising: a plurality of first cooling holes that penetrates the turbine disk from inside toward outside thereof in a radial direction of the turbine disk, that is communicatively connected to a cooling passage provided inside of each of the rotor blades, and that is arranged in the circumferential direction; and a plurality of second cooling holes that are positioned between each of the first cooling holes, and penetrates the turbine disk from the inside toward the outside thereof in a radial direction of the turbine disk, wherein base ends of the first cooling holes and the second cooling holes are configured to receive cooling gas, leading ends of the first cooling holes and the second cooling holes are communicatively connected to a radial direction communicating channel arranged in the circumferential direction, a plurality of fitting grooves arranged on an outer circumference in the circumferential direction are fitted with respective fitting protrusions on the rotor blades to form axial direction communicating channels in spaces between the fitting grooves and the rotor blades along an axial direction, the first cooling holes are arranged correspondingly to the axial direction communicating channels in the circumferential direction, and the leading ends thereof are communicatively connected to the radial direction communicating channel and the axial direction communicating channels, and the second cooling holes are arranged between the first cooling holes in the circumferential direction, and have the leading ends sealed, and are communicatively connected to the radial direction communicating channel. ### Claim 2 (depends on 1) The turbine disk according to claim 1, wherein both ends of the axial direction communicating channel are sealed with seal pieces. ### Claim 3 (depends on 1) The turbine disk according to claim 1, wherein the radial direction communicating channel is formed in an annular shape by sealing a ring-shaped communicating groove with a seal ring. ### Claim 4 A gas turbine in which compressed air compressed in a compressor is combusted by supplying fuel thereto in a combustor, and a combustion gas thus generated is supplied to a turbine to obtain rotation drive power, wherein the turbine comprises a turbine disk that is rotatably supported; and a plurality of rotor blades arranged on an outer circumference of the turbine disk in a circumferential direction, and having a cooling passage inside, the turbine disk includes: a plurality of first cooling holes that penetrates the turbine disk from inside toward outside thereof in a radial direction of the turbine disk, is communicatively connected to the cooling passage, and is arranged in the circumferential direction; and a plurality of second cooling holes that are arranged between each of the first cooling holes, and penetrates the turbine disk from the inside toward the outside thereof in a radial direction of the turbine disk, wherein base ends of the first cooling holes and the second cooling holes are configured to receive cooling gas, leading ends of the first cooling holes and the second cooling holes are communicatively connected to a radial direction communicating channel arranged in the circumferential direction, a plurality of fitting grooves arranged on an outer circumference in the circumferential direction are fitted with respective fitting protrusions on the rotor blades to form axial direction communicating channels in spaces between the fitting grooves and the rotor blades along an axial direction, the first cooling holes are arranged correspondingly to the axial direction communicating channels in the circumferential direction, and the leading ends thereof are communicatively connected to the radial direction communicating channel and the axial direction communicating channels, and the second cooling holes are arranged between the first cooling holes in the circumferential direction, and have the leading ends sealed, and are communicatively connected to the radial direction communicating channel.