# US 10,767,501 B2 · Article, component, and method of making a component > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,767,501 B2 - Document ID: US10767501B2 - Status: Granted - Kind: B2 - Application number: 15/134,758 - Filed: 2016-04-21 - Published: 2017-10-26 - Granted: 2020-09-08 - Earliest claimed: 2016-04-21 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Joseph Anthony Weber; Srikanth Chandrudu Kottilingam; Brian Lee Tollison - Web page: https://patentgrep.com/patent/US10767501B2 ## CPC - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 5/041: {of the Ljungström type} - F01D 25/005: {Selecting particular materials} - F05D 2220/32: in gas turbines - F05D 2230/22: by sintering - F05D 2230/237: Brazing - F05D 2230/80: Repairing, retrofitting or upgrading methods - F05D 2230/90: Coating; Surface treatment - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/128: Nozzles - F05D 2240/15: Heat shield - F05D 2240/80: Platforms for stationary or moving blades - 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 An article, a component, and a method of making a component are provided. The article includes a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component. The component includes a first end wall, a second end wall, and an article including a contoured proximal face secured to at least one of the first end wall and the second end wall. The method of making a component includes forming an article having a proximal face and a distal face, contouring the proximal face of the article to form a contoured proximal face that substantially mirrors a contour of a first end wall or a second end wall of the component, and securing the contoured proximal face of the article to one of the first end wall and the second end wall. ## Claims ### Claim 1 An article comprising: a pre-sintered preform having: a contoured proximal face; and a contoured distal face; wherein the contoured proximal face is arranged and disposed to mirror a contour of at least one of an end wall and an airfoil outer surface of a component, such that installation of the pre-sintered preform on the at least one of the end wall and the airfoil outer surface results in continuous, direct contact between the contoured proximal face and the contour of the component; wherein the pre-sintered preform is formed of a mixture of a first powder material and a second powder material, the second powder material being a braze alloy; and wherein the first powder material is the same material as the component. ### Claim 2 (depends on 1) The article of claim 1, wherein a contour of the contoured distal face differs from a contour of the contoured proximal face. ### Claim 3 (depends on 1) The article of claim 1, wherein the contoured distal face is arranged and disposed to provide an exterior surface over the end wall of the component. ### Claim 4 (depends on 3) The article of claim 3, wherein the exterior surface provides a modified surface characteristic, the modified surface characteristic being selected from the group consisting of hardness, corrosion resistance, temperature resistance, machinability, or a combination thereof. ### Claim 5 (depends on 1) The article of claim 1, wherein the component is a hot gas path component of a gas turbine. ### Claim 6 An assembly comprising: a hot gas path component comprising: a first end wall having a first contoured surface; a second end wall having a second contoured surface facing the first contoured surface; and an airfoil positioned between the first end wall and the second end wall, the airfoil having an airfoil outer surface; and a pre-sintered preform having a proximal face secured to at least one of the first contoured surface, the second contoured surface, and the airfoil outer surface, the pre-sintered preform further having a contoured distal face opposite the contoured proximal face; wherein a contour of the proximal face mirrors the at least one of the first contoured surface, the second contoured surface, and the airfoil outer surface such that the proximal face is in continuous, direct contact with the at least one of the first contoured surface, the second contoured surface, and the airfoil outer surface; wherein the pre-sintered preform is formed of a mixture of a first powder material and a second powder material, the second powder material being a braze alloy; and wherein the first powder material is the same material as the hot gas path component. ### Claim 7 (depends on 6) The assembly of claim 6, wherein the hot gas path component is a nozzle of a gas turbine. ### Claim 8 (depends on 6) The assembly of claim 6, wherein a material of the hot gas path component is selected from the group consisting of a metal, a ceramic, an alloy, a superalloy, steel, a stainless steel, a tool steel, nickel, cobalt, chrome, titanium, aluminum, and combinations thereof. ### Claim 9 (depends on 6) The assembly of claim 6, wherein a contour of the contoured distal face differs from the contour of the proximal face. ### Claim 10 (depends on 6) The assembly of claim 6, wherein the contoured distal face is arranged and disposed to provide an exterior surface providing a modified surface characteristic over the first end wall of the hot gas path component, the modified surface characteristic being selected from the group consisting of hardness, corrosion resistance, temperature resistance, machinability, or a combination thereof. ### Claim 11 (depends on 6) The assembly of claim 6, wherein a tolerance between the contour of the proximal face and the at least one of the first contoured surface, the second contoured surface, and the airfoil outer surface eliminates a formation of gaps between the pre-sintered preform and the at least one of the first contoured surface, the second contoured surface, and the airfoil outer surface. ### Claim 12 A method comprising: forming an article comprising a pre-sintered preform having a proximal face and a distal face; contouring the proximal face of the pre-sintered preform to form a contoured proximal face; and securing the contoured proximal face of the pre-sintered preform to one of a first end wall, a second end wall, and an airfoil portion of a component; wherein, prior to the step of securing, the contoured proximal face mirrors a contour of the one of the first end wall, the second end wall, and the airfoil portion of the component; wherein the step of securing the contoured proximal face to the contour of the component results in continuous, direct contact between the contoured proximal face and the contour of the component; wherein the pre-sintered preform is formed of a mixture of a first powder material and a second powder material, the second powder material being a braze alloy; and wherein the first powder material is the same material as the component. ### Claim 13 (depends on 12) The method of claim 12, further comprising contouring the distal face of the pre-sintered preform to form a contoured distal face, the contoured distal face differing from the contoured proximal face. ### Claim 14 (depends on 12) The method of claim 12, wherein the step of contouring the proximal face occurs prior to the step of securing and decreases a tolerance between the contoured proximal face and the contour of the one of the first end wall, the second end wall, and the airfoil portion. ### Claim 15 (depends on 12) The method of claim 12, wherein the step of securing comprises brazing. ### Claim 16 (depends on 15) The method of claim 15 further comprising applying a bond coat and a thermal barrier coating to the component after brazing.