# US 2020/0400031 A1 · Turbine vane, and turbine and gas turbine including the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2020/0400031 A1 - Document ID: US20200400031A1 - Status: Published application - Kind: A1 - Application number: 16/889,368 - Filed: 2020-06-01 - Published: 2020-12-24 - Earliest claimed: 2019-06-21 - Assignees: Doosan Heavy Industries Construction Co., Ltd - Applicants: Doosan Heavy Industries & Construction Co., Ltd. - Inventors: Hyun Woo JOO - Web page: https://patentgrep.com/patent/US20200400031A1 ## CPC - F01D 9/06: Fluid supply conduits to nozzles or the like - F01D 5/187: {Convection cooling} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - 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 - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2250/185: serpentine-like - F05D 2260/202: by film cooling - F05D 2260/2214: by increasing the heat transfer surface - 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 A turbine vane, a turbine, and a gas turbine capable of reducing thermal stress are provided. The turbine vane may include an airfoil including a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud, a first cooling passage and a second cooling passage configured to extend in a height direction thereof, and a first passage bending part configured to connect the first cooling passage and the second cooling passage, and the first passage bending part is positioned inside the inner shroud or the outer shroud. ## Claims ### Claim 1 A turbine vane comprising: an airfoil including a leading edge and a trailing edge; an inner shroud disposed at one end of the airfoil to support the airfoil; an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud; a first cooling passage and a second cooling passage configured to extend in a height direction thereof; and a first passage bending part configured to connect the first cooling passage and the second cooling passage, wherein the first passage bending part is positioned inside the inner shroud or the outer shroud. ### Claim 2 (depends on 1) The turbine vane of claim 1, wherein the first passage bending part comprises a first curved surface which is curved in an arc shape around a first point which is positioned inside the inner shroud or the outer shroud. ### Claim 3 (depends on 2) The turbine vane of claim 2, further comprising a first partition wall configured to split the first cooling passage and the second cooling passage, and extend in a height direction of the airfoil, wherein a longitudinal end of the first partition wall is positioned further outward than an end of the airfoil. ### Claim 4 (depends on 3) The turbine vane of claim 3, wherein the inner shroud comprises an inner platform connected to an inner end of the airfoil and an inner hook protruding from the inner platform, and wherein the inner platform comprises an inner protrusion which protrudes to form a space therein, and the first passage bending part is positioned inside the inner protrusion. ### Claim 5 (depends on 3) The turbine vane of claim 3, wherein the first partition wall comprises a plurality of inducing holes which penetrate the first partition wall in a thickness direction thereof, and some inducing holes are disposed further outward than the end of the airfoil with respect to a center of the turbine vane. ### Claim 6 (depends on 5) The turbine vane of claim 5, wherein some inducing holes are positioned on a boundary surface in which the airfoil and the inner platform are connected. ### Claim 7 (depends on 3) The turbine vane of claim 3, wherein the first partition wall comprises a first passage extending in a thickness direction of the first partition wall and a second passage which is connected to the first passage and extends to an end of the first partition wall, and wherein the first passage is positioned inside the airfoil, and the second passage extends from an interior of the airfoil to an interior of the inner shroud. ### Claim 8 (depends on 3) The turbine vane of claim 3, wherein a plurality of porous plates are formed to protrude from the first partition wall, the porous plates being positioned on the first passage bending part. ### Claim 9 (depends on 2) The turbine vane of claim 2, further comprising a third cooling passage configured to extend in a height direction thereof and a second passage bending part configured to connect the second cooling passage and the third cooling passage, wherein the second passage bending part comprises a second curved surface which is curved in an arc shape around a second point which is positioned inside the outer shroud. ### Claim 10 (depends on 9) The turbine vane of claim 9, wherein the outer shroud comprises an outer platform connected to an outer end of the airfoil and an outer hook protruding from the outer platform, and wherein the outer platform comprises an outer protrusion which protrudes outward and forms a space therein, and the second passage bending part is positioned inside the outer protrusion. ### Claim 11 (depends on 9) The turbine vane of claim 9, wherein the outer protrusion comprises a transverse cross section shaped like the airfoil. ### Claim 12 (depends on 1) The turbine vane of claim 1, further comprising a third cooling passage configured to extend in a height direction thereof and a second partition wall configured to split the second cooling passage and the third cooling passage, and extend in a height direction of the airfoil, wherein a longitudinal end of the second partition wall is positioned inside the outer shroud. ### Claim 13 A turbine comprising: a rotor disk configured to be rotatable; and a plurality of turbine blades and turbine vanes which are installed on the rotor disk, wherein the turbine vane comprises an airfoil including a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud, a first cooling passage and a second cooling passage configured to extend in a height direction thereof, and a first passage bending part configured to connect the first cooling passage and the second cooling passage and to include a first curved surface curved in an arc shape around a first point which is positioned inside the inner shroud or the outer shroud, and wherein the first passage bending part is positioned inside the inner shroud or the outer shroud. ### Claim 14 (depends on 13) The turbine of claim 13, further comprising a first partition wall configured to split the first cooling passage and the second cooling passage, and extend in a height direction of the airfoil, wherein a longitudinal end of the first partition wall is positioned further outward than an end of the airfoil. ### Claim 15 (depends on 14) The turbine of claim 14, wherein the inner shroud comprises an inner platform connected to an inner end of the airfoil and an inner hook protruding from the inner platform, and wherein the inner platform comprises an inner protrusion which protrudes to form a space therein, and the first passage bending part is positioned inside the inner protrusion. ### Claim 16 (depends on 14) The turbine of claim 14, wherein the first partition wall comprises a plurality of inducing holes which penetrate the first partition wall in a thickness direction thereof, and some inducing holes are formed outside the airfoil. ### Claim 17 (depends on 16) The turbine of claim 16, wherein some inducing holes are positioned on a boundary surface in which the airfoil and the inner platform are connected. ### Claim 18 (depends on 14) The turbine of claim 14, wherein the first partition wall comprises a first passage extending in a thickness direction of the first partition wall and a second passage which is connected to the first passage and extends to an end of the first partition wall, and wherein the first passage is positioned inside the airfoil, and the second passage extends from an interior of the airfoil to an interior of the inner shroud. ### Claim 19 (depends on 14) The turbine of claim 14, wherein a plurality of porous plates are formed to protrude from the first partition wall, the porous plates being positioned on the first passage bending part. ### Claim 20 A gas turbine comprising: a compressor configured to compress air drawn thereinto from an outside; a combustor configured to mix fuel with air compressed by the compressor and combust a mixture of the fuel and the compressed air; and a turbine comprising a plurality of turbine blades configured to be rotated by combustion gas discharged from the combustor, wherein the turbine comprises a rotor disk configured to be rotatable, and a plurality of turbine blades and turbine vanes which are installed on the rotor disk, wherein the turbine vane comprises an airfoil including a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud, a first cooling passage and a second cooling passage configured to extend in a height direction thereof, and a first passage bending part configured to connect the first cooling passage and the second cooling passage, and wherein the first passage bending part is positioned inside the inner shroud or the outer shroud.