# US 2021/0277784 A1 · Turbomachine component for a gas turbine, turbomachine assembly and gas turbine having the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2021/0277784 A1 - Document ID: US20210277784A1 - Status: Published application - Kind: A1 - Application number: 17/149,079 - Filed: 2021-01-14 - Published: 2021-09-09 - Earliest claimed: 2020-03-06 - Assignees: Doosan Heavy Industries Construction Co., Ltd - Applicants: Doosan Heavy Industries & Construction Co., Ltd. - Inventors: Vincent GALOUL; Simon HAUSWIRTH; Richard JONES - Web page: https://patentgrep.com/patent/US20210277784A1 ## CPC - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - 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)} - F05D 2240/126: Baffles or ribs - F05D 2240/304: related to the trailing edge of a rotor blade - F05D 2240/81: Cooled platforms - F05D 2250/75: given by its similarity to a letter, e.g. T-shaped - F05D 2260/201: by impingement of a fluid - F05D 2260/232: characterized by the cooling medium - 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 The present technique presents a turbomachine component having an airfoil e.g. a vane of a gas turbine. The airfoil wall defines an internal space which includes a first and a second cooling channels having a first and a second impingement inserts, that define a first main and a first peripheral flow channels in the first cooling channel and a second main and a second peripheral flow channels in the second cooling channel, respectively. Impingement jets ejected from the main flow channels via impingement holes of the corresponding impingement inserts are received in the corresponding peripheral flow channels. A channel connecting conduit conducts a flow of the cooling air from the first cooling channel to the second cooling channel. The channel connecting conduit includes an inlet connected to an outlet of the first cooling channel, and an outlet connected to an inlet of the second cooling channel. ## Claims ### Claim 1 A turbomachine component for a gas turbine, the turbomachine component comprising: an airfoil comprising an airfoil wall defining an internal space of the airfoil, and a first and a second cooling channel in the internal space of the airfoil; a first impingement insert inserted in the first cooling channel and defining a first main flow channel for conducting flow of cooling air along a longitudinal direction of the airfoil and at least one first peripheral flow channel for receiving impingement jets ejected from the first main flow channel via impingement holes of the first impingement insert; a second impingement insert inserted in the second cooling channel and defining a second main flow channel for conducting flow of cooling air along the longitudinal direction of the airfoil and at least one second peripheral flow channel for receiving impingement jets ejected from the second main flow channel via impingement holes of the second impingement insert; and a channel connecting conduit configured to conduct a flow of the cooling air from the first cooling channel to the second cooling channel and comprising: an inlet of the channel connecting conduit connected to an outlet of the first cooling channel, and an outlet of the channel connecting conduit connected to an inlet of the second cooling channel. ### Claim 2 (depends on 1) The turbomachine component according to claim 1, wherein the inlet of the channel connecting conduit encompasses an outlet of the first peripheral flow channel without encompassing an outlet of the first main flow channel; or wherein the inlet of the channel connecting conduit encompasses each of an outlet of the first main flow channel and an outlet of the first peripheral flow channel. ### Claim 3 (depends on 1) The turbomachine component according to claim 1, wherein an outlet of the first main flow channel comprises a sealing cap for completely stopping flow of cooling air out of the outlet of the first main flow channel into the channel connecting conduit; or wherein an outlet of the first main flow channel comprises a sealing cap and wherein the sealing cap comprises one or more through-holes for conducting flow of cooling air of the first main flow channel into the channel connecting conduit. ### Claim 4 (depends on 1) The turbomachine component according to claim 1, wherein the outlet of the channel connecting conduit encompasses an inlet of the second main flow channel without encompassing an inlet of the second peripheral flow channel. ### Claim 5 (depends on 1) The turbomachine component according to claim 1, wherein an inlet of the second peripheral flow channel is sealed. ### Claim 6 (depends on 1) The turbomachine component according to claim 1, wherein the airfoil wall comprises a pressure side and a suction side meeting at a leading edge and a trailing edge and defining an internal space of the airfoil; and wherein the airfoil comprises at least one web disposed within the internal space of the airfoil and extending between the pressure side and the suction side; and wherein the first cooling channel and/or the second cooling channel is defined by the at least one web and the pressure side and/or the suction side. ### Claim 7 (depends on 1) The turbomachine component according to claim 1, further comprising a platform from which the airfoil extends, and wherein the inlet and the outlet of the channel connecting conduit, the outlet of the first cooling channel, and the inlet of the second cooling channel are arranged at the platform. ### Claim 8 (depends on 1) The turbomachine component according to claim 1, further comprising a seal ring configured to be positioned between the inlet of the channel connecting conduit and the outlet of the first cooling channel. ### Claim 9 (depends on 1) The turbomachine component according to claim 1, wherein the channel connecting conduit comprises a bent portion having a U-shape between the inlet and the outlet of the channel connecting conduit. ### Claim 10 (depends on 1) The turbomachine component according to claim 1, wherein the channel connecting conduit comprises an extension portion extending horizontally from the outlet of the channel connecting conduit in a direction opposite to the inlet of the channel connecting conduit; and wherein the second impingement insert comprises a receiving portion having a shape corresponding to the extension portion, and wherein the receiving portion and the extension portion are configured to be coupled to each other. ### Claim 11 (depends on 1) The turbomachine component according to claim 1, wherein the second cooling channel is located at the trailing edge of the airfoil. ### Claim 12 (depends on 1) The turbomachine component according to claim 1, wherein the turbomachine component is a vane of a gas turbine. ### Claim 13 (depends on 1) A turbomachine assembly comprising a plurality of turbomachine components, wherein the plurality of turbomachine components comprises a turbomachine component according to claim 1. ### Claim 14 (depends on 13) A turbomachine assembly according to claim 13, wherein the inlet of the channel connecting conduit encompasses an outlet of the first peripheral flow channel without encompassing an outlet of the first main flow channel; or wherein the inlet of the channel connecting conduit encompasses each of an outlet of the first main flow channel and an outlet of the first peripheral flow channel. ### Claim 15 (depends on 13) A turbomachine assembly according to claim 13, wherein an outlet of the first main flow channel comprises a sealing cap for completely stopping flow of cooling air out of the outlet of the first main flow channel into the channel connecting conduit; or wherein an outlet of the first main flow channel comprises a sealing cap and wherein the sealing cap comprises one or more through-holes for conducting flow of cooling air of the first main flow channel into the channel connecting conduit. ### Claim 16 (depends on 13) A turbomachine assembly according to claim 13, wherein the airfoil wall comprises a pressure side and a suction side meeting at a leading edge and a trailing edge and defining an internal space of the airfoil; and wherein the airfoil comprises at least one web disposed within the internal space of the airfoil and extending between the pressure side and the suction side; and wherein the first cooling channel and/or the second cooling channel is defined by the at least one web and the pressure side and/or the suction side. ### Claim 17 (depends on 13) A turbomachine assembly according to claim 13, further comprising a platform from which the airfoil extends, and wherein the inlet and the outlet of the channel connecting conduit, the outlet of the first cooling channel, and the inlet of the second cooling channel are arranged at the platform. ### Claim 18 (depends on 13) A turbomachine assembly according to claim 13, wherein the channel connecting conduit comprises an extension portion extending horizontally from the outlet of the channel connecting conduit in a direction opposite to the inlet of the channel connecting conduit; and wherein the second impingement insert comprises a receiving portion having a shape corresponding to the extension portion, and wherein the receiving portion and the extension portion are configured to be coupled to each other. ### Claim 19 (depends on 13) A gas turbine comprising a turbomachine assembly, wherein the turbomachine assembly is according to claim 13. ### Claim 20 (depends on 19) The gas turbine according to claim 19, wherein a turbine section of the gas turbine comprises an inner casing and an outer casing defining thereinbetween at least a section of a hot gas path, the inner casing disposed radially inwards of the outer casing; wherein the turbomachine component is a vane and connected to the inner and the outer casings and disposed in the section of the hot gas path; and wherein the outlet of the first cooling channel, the inlet of the second cooling channel and the channel connecting conduit are positioned radially inwards of the airfoil at the inner casing or the outlet of the first cooling channel, the inlet of the second cooling channel and the channel connecting conduit are positioned radially outwards of the airfoil at the outer casing.