초록 ▼

Accordingly, the present invention provides a method for joining metallic members, which can be used to join component sub-assemblies. Further, the present invention provides a method for repairing a component by replacing a damaged portion and re-inserting a replacement section. In general, the pre

Accordingly, the present invention provides a method for joining metallic members, which can be used to join component sub-assemblies. Further, the present invention provides a method for repairing a component by replacing a damaged portion and re-inserting a replacement section. In general, the present invention provides in one embodiment a method for joining metallic members comprising: preparing a surface of a first metallic member, thereby providing an oxide-free surface; preparing a surface of a second metallic member, thereby providing an oxide-free surface; applying pressure to the first and second metallic members, thereby forcing the surface of the first metallic member and the surface of the second metallic member together and forming a joint area; sealing an outer edge of the joint area; and subjecting the members to a hot isostatic process operation.

대표청구항 ▼

What is claimed is: 1. A method for joining superalloy metallic members for repairing a superalloy turbine blade comprising: preparing a surface of a first superalloy metallic member, thereby providing a clean and an oxide-free surface, wherein said surface of said first superalloy metallic member

What is claimed is: 1. A method for joining superalloy metallic members for repairing a superalloy turbine blade comprising: preparing a surface of a first superalloy metallic member, thereby providing a clean and an oxide-free surface, wherein said surface of said first superalloy metallic member comprises a first interlocking section; preparing a surface of a second superalloy metallic member, thereby providing a clean and an oxide-free surface, wherein said surface of the second superalloy metallic member comprises a second interlocking section wherein said second interlocking section corresponds to said first interlocking section; interlocking said first interlocking section with said second interlocking section such that said first interlocking section directly contacts said second interlocking section; applying pressure to said first and second superalloy metallic members, thereby forcing said clean and oxide-free surface of said first superalloy metallic member directly against said clean and oxide-free surface of said second superalloy metallic member thereby forming a joint area; sealing an outer edge of said joint area to form a sealed joint area, with the proviso that said sealing is not performed by brazing; and subjecting said members and said sealed joint area to a hot isostatic process operation. 2. The method of claim 1, wherein said preparing is selected from the group consisting of, grit blasting, grinding, polishing, and chemical cleaning. 3. The method of claim 1, wherein said sealing comprises applying a seal weld. 4. The method of claim 1, wherein said sealing step comprises applying a sealing media. 5. The method of claim 4, wherein said sealing media comprises a high temperature wax. 6. The method of claim 1, wherein said interlocking further comprises shrink-fitting said first interlocking section with said second interlocking section wherein said shrink-fitting comprises: cooling said first interlocking section to a temperature below room temperature; fitting said cooled first interlocking section into said second interlocking section; and warming said interlocking sections to room temperature. 7. A method for joining superalloy metallic members for repairing a superalloy turbine blade comprising: preparing a surface on a first superalloy metallic member, thereby providing a clean surface on said first superalloy metallic member; preparing a surface on a second superalloy metallic member, thereby providing a clean surface on said second superalloy metallic member; positioning said clean surface on said first superalloy metallic member physically against said clean surface on said second superalloy metallic member tightly together, thereby causing direct contact between said clean surface on said first superalloy metallic member and said clean surface on said second superalloy metallic member and forming a joint area; applying pressure on said first superalloy metallic member and said second superalloy metallic member to force said clean surface on said first superalloy metallic member and said clean surface on said second superalloy metallic member closer together; sealing an outer edge of said joint area with a seal weld to form a sealed joint area, with the proviso that said sealing is not performed by brazing; and subjecting said first superalloy metallic member and said second superalloy metallic member and said sealed joint area to a hot isostatic processing operation. 8. The method of claim 7, wherein said surface on said first superalloy metallic member and said surface on said second superalloy metallic member each comprises an interlocking section and wherein said positioning further comprises interlocking said interlocking section of said first superalloy metallic member with said interlocking section of said second superalloy metallic member, thereby forming said joint area. 9. A method for repairing a damaged superalloy turbine blade, comprising: removing a damaged portion from a damaged location of a superalloy turbine blade; preparing a surface of said superalloy turbine blade; preparing a surface of a superalloy metallic member configured to replace said damaged portion of said superalloy turbine blade; positioning said superalloy metallic member adjacent to said damaged location of said superalloy turbine blade such that the prepared surface of said superalloy metallic member directly contacts the prepared surface of said superalloy turbine blade; applying pressure to said superalloy turbine blade and said superalloy metallic member, thereby forcing said surface of said superalloy turbine blade directly against said surface of said superalloy metallic member together and forming a joint area; sealing an outer edge of said joint area to form a sealed joint area; and subjecting said superalloy turbine blade and said superalloy metallic member and said sealed joint area to a hot isostatic process operation. 10. The method of claim 9, wherein said preparing is selected from the group consisting of grit blasting, grinding, polishing, and fluoride ion cleaning. 11. The method of claim 9, wherein said sealing comprises applying a seal weld. 12. The method of claim 9, wherein said sealing step comprises applying a sealing media. 13. The method of claim 12, wherein said sealing media comprises a high temperature wax. 14. The method of claim 9, wherein said surface of said superalloy turbine blade and said surface of said superalloy metallic member each has an interlocking section. 15. The method of claim 14, wherein said interlocking section of said superalloy turbine blade fits into said interlocking section of said superalloy metallic member, thereby forming said joint area during said positioning. 16. The method of claim 15, wherein said positioning further comprises shrink-fitting said superalloy metallic member to form said joint area. 17. The method of claim 16, wherein said shrink-fitting comprises lowering the temperature of said superalloy metallic member to below room temperature. 18. The method of claim 17, wherein said positioning further comprises warming said superalloy metallic member to room temperature after positioning said superalloy metallic member adjacent to said damaged location of said superalloy turbine blade. 19. The method of claim 15, wherein said positioning further comprises shrink-fitting said superalloy turbine blade to form said joint area. 20. A method for joining superalloy metallic parts, comprising: providing a first superalloy metallic member with a first interlocking section and a second superalloy metallic member with a second interlocking section, wherein said first interlocking section can be fitted into a corresponding area in said second interlocking section; preparing said first interlocking section of said first superalloy metallic member, thereby providing a clean surface on said first interlocking section; preparing said second interlocking section of said second superalloy metallic member, thereby providing a clean surface on said second interlocking section; positioning said first interlocking section of said first superalloy metallic member into said corresponding area in said second interlocking section of said second superalloy metallic member, thereby causing direct contact between said clean surface of said first interlocking section and said clean surface of said second interlocking section and forming a joint area; applying pressure on said first superalloy metallic member and said second superalloy metallic member to force said clean surface of said first interlocking section of said first superalloy metallic member directly against said clean surface of said second interlocking section of said second superalloy metallic member; sealing an outer edge of said joint area to form a sealed joint area, with the proviso that said sealing is not performed by brazing; and subjecting said first superalloy metallic member and said second superalloy metallic member and said sealed joint area to a hot isostatic processing operation. 21. The method of claim 20, wherein said sealing comprises applying a seal weld. 22. The method of claim 20, wherein said sealing step comprises applying a sealing media. 23. The method of claim 22, wherein said sealing media comprises a high temperature wax. 24. The method of claim 20, further comprising a preliminary step of creating the first interlocking section and the second interlocking section. 25. The method of claim 20, wherein said positioning further comprises shrink-fitting said superalloy metallic members to form said joint area. 26. A method for repairing a superalloy turbine blade, comprising: removing a damaged portion from a damaged location of a superalloy turbine blade; creating a first interlocking section of said superalloy turbine blade; creating a second interlocking section of a superalloy repair member, wherein said superalloy repair member is configured to replace said damaged portion of said superalloy turbine blade and wherein said first interlocking section can be fitted into a corresponding area in said second interlocking section; preparing said first interlocking section of said superalloy turbine blade, thereby providing a clean surface on said first interlocking section; preparing said second interlocking section of said superalloy repair member, thereby providing a clean surface on said second interlocking section; positioning said first interlocking section of said superalloy turbine blade into said corresponding area in said second interlocking section of said superalloy repair member, thereby causing direct contact between said clean surface of said first interlocking section and said clean surface of said second interlocking section and forming a joint area; applying pressure on said superalloy turbine blade and said superalloy repair member to force said clean surface of said first interlocking section of said superalloy turbine blade directly against said clean surface of said second interlocking section of said superalloy repair member; sealing an outer edge of said joint area to form a sealed joint area; and subjecting said superalloy turbine blade, said superalloy repair member, and said sealed joint area to a hot isostatic processing operation. 27. The method of claim 26, wherein said positioning further comprises shrink-fitting the superalloy turbine blade and the superalloy repair member, wherein said shrink-fitting comprises reducing the temperature of said superalloy repair member to a temperature less than room temperature. 28. A method for repairing a superalloy turbine blade, comprising: removing a damaged portion of said sup eralloy turbine blade; creating a first interlocking section comprising a clean surface of said superalloy turbine blade; creating a second interlocking section comprising a clean surface of a superalloy repair member, wherein said superalloy repair member is configured to replace said damaged portion of said superalloy turbine blade and wherein said second interlocking section can be fitted into a corresponding area in said first interlocking section; positioning said second interlocking section of said superalloy repair member into said corresponding area in said first interlocking section causing direct contact of said second interlocking section and said first interlocking section while the superalloy repair member is at a first temperature lesser than room temperature, thereby forming a joint area; applying pressure on said superalloy turbine blade and said superalloy repair member to force said clean surface of said superalloy repair member directly against said clean surface of said superalloy turbine blade; waiting for said superalloy repair member to reach a second temperature greater than said first temperature; sealing an outer edge of said joint area to form a sealed joint area; and subjecting said superalloy turbine blade, said superalloy repair member, and said sealed joint area to a hot isostatic processing operation.