Turbine components and methods of manufacturing
At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a mounting location of the turbine component in a turbine. Methods of manufacturing articles and turbine components are also disclosed.
1. A method of manufacturing comprising:
additive manufacturing an article having a proximal face sized and shaped to cover at least a portion of an upper surface of a platform of a base component and a contoured distal face opposite the proximal face, the base component and the article together forming a turbine component, the contoured distal face of the article having a contour surface serving as at least a portion of a hot gas path surface of the turbine component, the contour surface being arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface, the contour surface being customized based on a clock mounting location of the turbine component in a turbine and a hot gas flow determined empirically or by modelling at the clock mounting location, the base component being formed by casting; wherein the article includes at least a portion of at least one wall cooling feature customized based on the clock mounting location of the turbine component in the turbine.
2. The method of claim 1 further comprising brazing the article to the platform of the base component.
3. The method of claim 1 , wherein the additive manufacturing of the article occurs directly on the platform of the base component.
4. The method of claim 1 further comprising casting the base component.
5. The method of claim 1 , wherein the turbine is a gas turbine.
6. The method of claim 1 , wherein the turbine component is a nozzle comprising the platform and an airfoil portion extending from the platform.
7. The method of claim 1 further comprising inserting the article into a recess on the upper surface of the platform of the base component.
8. The method of claim 1 further comprising covering the upper surface of the base component with the article.
9. The method of claim 1 , wherein the portion of the at least one wall cooling feature comprises at least one film cooling hole.
10. The method of claim 9 , wherein the method comprises forming the at least one film cooling hole in the contoured distal face.
11. A method of manufacturing comprising:
additive manufacturing a set of articles for a set of base components, each article of the set of articles having a proximal face sized and shaped to cover at least a portion of an upper surface of a platform of one of the set of base components and a contoured distal face opposite the proximal face, each one of the set of base components and each article together forming a turbine component, each contoured distal face having a contour surface serving as at least a portion of a hot gas path surface of the turbine component, each contour surface being arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface, each contour surface being customized based on a clock mounting location of the turbine component in a turbine and a hot gas flow determined empirically or by modelling at the clock mounting location, the set of base components being formed by casting; wherein each article includes at least a portion of at least one wall cooling feature customized based on the clock mounting location of the turbine component in the turbine.
12. The method of claim 11 further comprising casting the set of base components from a single casting.
13. The method of claim 11 , wherein the turbine components are nozzles, each nozzle comprising the platform and an airfoil portion extending from the platform, and the turbine is a gas turbine.
14. The method of claim 11 , wherein the portion of the at least one wall cooling feature comprises at least one film cooling hole.
15. The method of claim 14 , wherein the method comprises forming the at least one film cooling hole in the contoured distal face.