Additive-based electroforming manufacturing methods and metallic articles produced thereby

Abstract

Additive-based electroforming manufacturing methods for producing turbomachine components and other metallic articles are provided, as are metallic articles manufactured utilizing such manufacturing methods. In various embodiments, the method includes providing a sacrificial tooling structure having a component-defining surface region. A metallic body layer or shell is deposited over the component-defining surface region utilizing an electroforming process. The tooling structure is removed, while the metallic body layer is left substantially intact. After tooling structure removal, the metallic body layer is further processed to complete fabrication of the metallic component.

What is claimed is: 
     
         1 . A method for manufacturing a metallic component, comprising:
 providing a sacrificial tooling structure having a component-defining surface region;   forming an electrically-conductive coating layer from an alloy predominately composed of aluminum by weight percentage over the component-defining surface region;   depositing a metallic body layer over the electrically-conductive coating layer utilizing an electroforming process;   removing the sacrificial tooling structure to form an internal void within the metallic body layer, and the electrically-conductive coating layer lines the internal void; and   further processing the metallic body layer to complete fabrication of the metallic component, the further processing including heat treating the electrically-conductive coating layer substantially concurrently with the removing of the sacrificial tool structure to form an aluminide coating on the metallic body layer.   
     
     
         2 . The method of  claim 1 , wherein the method further comprises:
 energizing the electrically-conductive coating layer during the electroforming process to deposit the metallic body layer over the electrically-conductive coating layer.   
     
     
         3 . The method of  claim 2 , further comprising, during the electroforming process, depositing the metallic body layer to have a global average thickness exceeding that of the electrically-conductive coating layer. 
     
     
         4 . The method of  claim 1 , wherein the providing the sacrificial tooling structure further comprises additively manufacturing the sacrificial tooling structure. 
     
     
         5 . The method of  claim 1 , wherein removing the sacrificial tooling structure comprises removing the sacrificial tooling structure, while leaving electrically-conductive coating layer substantially intact. 
     
     
         6 . The method of  claim 1 , further comprising applying a dielectric masking material to the sacrificial tooling structure, the dielectric masking material creating an opening in the metallic body layer during the electroforming process, and the removing comprises removing the sacrificial tooling structure through the opening created in the metallic body layer. 
     
     
         7 . The method of  claim 1 , wherein the removing comprises removing the sacrificial tooling structure to form an internal void within the metallic component, the metallic body layer forming a shell substantially enclosing the internal void. 
     
     
         8 . The method of  claim 7 , wherein the shell has a substantially uniform wall thickness. 
     
     
         9 . The method of  claim 1 , wherein the sacrificial tooling structure further has a non-component-defining surface region; and
 wherein the method further comprises producing the component-defining surface region from an electrically-conductive material, while producing the non-component-defining surface region from a dielectric material by additive manufacturing.   
     
     
         10 . The method of  claim 1 , wherein the metallic component comprises an airfoil, and wherein the method further comprises shaping and sizing the sacrificial tooling structure to create a void space within the airfoil when the sacrificial tooling structure is removed through an opening provided in the metallic body layer. 
     
     
         11 . The method of  claim 10 , further comprising forming the opening at a location radially inboard or radially outboard of the airfoil. 
     
     
         12 . The method of  claim 1 , wherein the metallic component comprises a gas turbine engine component having a flow passage therethrough, and wherein the method further comprises forming the flow passage, at least in substantial part, by removal of the sacrificial tooling structure. 
     
     
         13 . A method for manufacturing a metallic article, comprising:
 applying an electrically-conductive coating layer from an alloy predominately composed of aluminum by weight percentage over a portion of a sacrificial tooling structure;   utilizing an electroforming process to deposit a metallic shell encasing the sacrificial tooling structure;   removing the sacrificial tooling structure to form an internal void within the metallic shell, and the electrically-conductive coating layer lines the internal void; and   further processing the metallic shell to yield the metallic article, the further processing including heat treating the electrically-conductive coating layer substantially concurrently with the removing of the sacrificial tool structure to form an aluminide coating on the metallic body layer.   
     
     
         14 . The method of  claim 13 , further comprising:
 applying a dielectric masking material to the sacrificial tooling structure; and   in conjunction with the electroforming process, creating at least one opening in the metallic shell with the dielectric masking material through which the sacrificial tooling structure is exposed.   
     
     
         15 . The method of  claim 14 , wherein the removing the sacrificial tooling structure further comprises removing the sacrificial tooling structure through the at least one opening in the metallic shell to form the internal void within the metallic shell. 
     
     
         16 . The method of  claim 13  wherein the metallic article comprises a Gas Turbine Engine (GTE) component, and wherein the method further comprises:
 selecting the sacrificial tooling structure to have an airfoil-defining region; 
 forming the metallic shell to extend over the airfoil-defining region and define at least one airfoil contained within the GTE component. 
 
     
     
         17 . The method of  claim 13  wherein the metallic article comprises a GTE component, and wherein the method further comprises:
 selecting the sacrificial tooling structure to have a flow passage-defining region; and 
 forming the metallic shell to extend over the flow passage-defining region and impart the metallic shell with a flow passage section through which gas flow is conducted when the GTE component is utilized within a GTE.