# US 10,370,300 B2 · Additively manufactured turbine shroud segment > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,370,300 B2 - Document ID: US10370300B2 - Status: Granted - Kind: B2 - Application number: 15/799,709 - Filed: 2017-10-31 - Published: 2019-05-02 - Granted: 2019-08-06 - Earliest claimed: 2017-10-31 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Carlos Bonilla Gonzalez; Eric John Ruggiero; Jason Randolph Allen - Web page: https://patentgrep.com/patent/US10370300B2 ## CPC - C04B 35/638: Removal thereof - B22C 3/00: Selection of compositions for coating the surfaces of moulds, cores, or patterns - F01D 5/187: {Convection cooling} - F01D 5/225: {by shrouding} - F01D 5/34: Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} - F01D 9/04: forming ring or sector - B33Y 10/00: Processes of additive manufacturing - B33Y 80/00: Products made by additive manufacturing - C04B 2235/6026: Computer aided shaping, e.g. rapid prototyping - F05D 2220/32: in gas turbines - F05D 2230/21: by casting - F05D 2230/30: with deposition of material - F05D 2240/11: Shroud seal segments - F05D 2260/204: by the use of microcircuits - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - C04B: LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE {(roofing granules E04D7/005)}; CERAMICS (devitrified glass-ceramics C03C10/00); REFRACTORIES; TREATMENT OF NATURAL STONE - B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B33Y: ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - 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 system includes a turbine shroud segment. The turbine shroud segment includes a backside, a flow path surface opposite to the back side and configured to be disposed adjacent a hot gas path of the turbine system, and side walls extending between the backside of the turbine shroud segment and the flow path surface of the turbine shroud segment. The turbine shroud segment also includes cooling channels disposed in a thickness of the turbine shroud segment between the backside and the flow path surface, where each cooling channel includes an outlet at one of the side walls of the turbine shroud segment. ## Claims ### Claim 1 A turbine system having a turbine shroud segment, wherein the turbine shroud segment comprises: a backside; a flow path surface opposite to the back side and configured to be disposed adjacent a hot gas path of the turbine system; side walls extending between the backside of the turbine shroud segment and the flow path surface of the turbine shroud segment; and a plurality of cooling channels disposed in a thickness of the turbine shroud segment between the backside and the flow path surface, wherein each cooling channel of the plurality of cooling channels comprises an outlet at one of the side walls of the turbine shroud segment. ### Claim 2 (depends on 1) The turbine system of claim 1, wherein each cooling channel of the plurality of cooling channels extends parallel to the flow path surface a distance comprising at least fifty percent a total length of the flow path surface of the shroud segment. ### Claim 3 (depends on 1) The turbine system of claim 1, wherein a first subset of the plurality of cooling channels is configured to route coolant in a first direction, and wherein a second subset of the plurality of cooling channels is configured to route the coolant in a second direction transverse to the first direction. ### Claim 4 (depends on 1) The turbine system of claim 1, wherein a cross-section of each cooling channel of the plurality of cooling channels comprises a non-circular shape. ### Claim 5 (depends on 4) The turbine system of claim 4, wherein the cross-section comprises a triangular shape, a square shape, a rectangular shape, an oval shape, or a star shape. ### Claim 6 (depends on 1) The turbine system of claim 1, wherein a first sub-set of the plurality of cooling channels comprises a first cooling channel shape, and wherein a second sub-set of the plurality of cooling channels comprises a second cooling channel shape different than the first cooling channel shape. ### Claim 7 (depends on 1) The turbine system of claim 1, wherein each cooling channel of the plurality of cooling channels comprises at least one bend. ### Claim 8 (depends on 7) The turbine system of claim 7, wherein each cooling channel of the plurality of cooling channels comprises at least two bends. ### Claim 9 (depends on 1) The turbine system of claim 1, wherein an additive core die is disposed within the plurality of cooling channels, wherein the additive core die is configured to be broken and removed from the plurality of cooling channels. ### Claim 10 (depends on 1) The turbine system of claim 1, wherein at least one cooling channel of the plurality of cooling channels comprises a non-uniform cross-sectional shape or area along a length of the cooling channel. ### Claim 11 (depends on 1) The turbine system of claim 1, wherein at least one cooling channel of the plurality of cooling channels comprises raised bumps or dimples along a surface of the at least one cooling channel. ### Claim 12 (depends on 1) The turbine system of claim 1, wherein each cooling channel of the plurality of cooling channels comprises a diameter, wherein each cooling channel of the plurality of cooling channels comprises a portion extending parallel to the flow path surface and at an offset distance from the flow path surface, and wherein the turbine shroud segment comprises at least one of the following: a ratio of the diameter to the thickness within a range of 0.1 and 0.5; or a ratio of the offset distance to the thickness within a range of 0.1 and 0.5. ### Claim 13 (depends on 1) The turbine system of claim 1, wherein the backside of the turbine shroud segment comprises raised bumps configured to enhance impingement cooling of the backside of the turbine shroud segment. ### Claim 14 A method of manufacturing a turbine shroud segment, comprising: selecting a thermal management architecture for the turbine shroud segment; and additively manufacturing the turbine shroud segment, via a casting process, such that the turbine shroud segment includes the selected thermal management architecture. ### Claim 15 (depends on 14) The method of claim 14, wherein additively manufacturing the turbine shroud segment, via a casting process, such that the turbine shroud segment includes the selected thermal management architecture comprises: forming a die corresponding with the selected thermal management architecture; disposing the die in a liquid form of a material of the turbine shroud segment; and breaking and removing the die after the material of the turbine shroud segment solidifies from the liquid form to a solid form. ### Claim 16 (depends on 15) The method of claim 15, comprising forming the die via a 3-D printing technique. ### Claim 17 A method of manufacturing a turbine shroud segment for a turbine shroud, comprising: thermally modeling, based on an expected thermal loading on the turbine shroud segment corresponding with an expected position of the turbine shroud segment within the turbine shroud, a first digital version of the turbine shroud segment to determine a first thermal model result of the first digital version, wherein the first digital version comprises a first parameter of a thermal management characteristic; thermally modeling, based on the expected thermal loading on the turbine shroud segment corresponding with the expected position of the turbine shroud segment within the turbine shroud, a second digital version of the turbine shroud segment to determine a second thermal model result of the second digital version, wherein the second digital version comprises a second parameter of the thermal management characteristic, and wherein the second parameter of the thermal management characteristic is different than the first parameter of the thermal management characteristic; selecting to manufacture the first digital version based on a comparison between the first thermal model result and the second thermal model result; and additively manufacturing the turbine shroud segment based on the first digital version. ### Claim 18 (depends on 17) The method of claim 17, comprising: thermally modeling a baseline digital version of a baseline turbine shroud segment to determine a baseline thermal model result of the baseline digital version, wherein the baseline turbine shroud segment corresponds with a part to be replaced in the turbine shroud; and ensuring that the first thermal model result is an improvement over the baseline thermal model result. ### Claim 19 (depends on 17) The method of claim 17, wherein the thermal management characteristic comprises a cross-sectional shape of a cooling channel, a cross-sectional size of the cooling channel, a direction of flow of the cooling channel, or a pitch between adjacent cooling channels. ### Claim 20 (depends on 17) The method of claim 17, wherein additively manufacturing the turbine shroud segment based on the first digital version comprises: generating a die corresponding with a thermal management architecture of the first digital version; and disposing the die in a liquid form of a material of the turbine shroud segment; and breaking and removing the die from the material of the turbine shroud segment after the material changes from the liquid form to a solid form.