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In a method of repairing a structural component, especially a stator-side structural component such as a housing or a guide vane ring of a gas turbine, a damaged section is separated-out along a separating line and removed from the structural component, and a new section that replaces the removed da

In a method of repairing a structural component, especially a stator-side structural component such as a housing or a guide vane ring of a gas turbine, a damaged section is separated-out along a separating line and removed from the structural component, and a new section that replaces the removed damaged section is connected with the structural component by welding along the separating line to produce a weld seam. The damaged section is separated-out from the structural component so as to minimize the length of the separating line and thus the weld seam. Depending on the material thickness distribution of the component along the separating line, material is removed from the structural component to provide the most uniform possible material thickness along the weld seam. After connecting the new section with the structural component by welding, at least the removed material is renewed by laser powder deposit welding.

대표청구항 ▼

1. A method of repairing a structural component, comprising the steps: a) providing a structural component that has a damaged section including damage, and that has a varying component thickness adjoining said damaged section;b) determining a desired welding thickness range of said structural compon

1. A method of repairing a structural component, comprising the steps: a) providing a structural component that has a damaged section including damage, and that has a varying component thickness adjoining said damaged section;b) determining a desired welding thickness range of said structural component for a welding operation on said structural component;c) determining a separation line around said damaged section in said structural component such that said damaged section can be separated along said separation line and removed from a remainder of said structural component, wherein said separation line extends to a bounding surface of said structural component so that said separation line cannot form a first continuous closed loop within said structural component;d) adding supplemental material onto said bounding surface and extending said separation line into said supplemental material so that said separation line forms a second continuous closed loop within said structural component and said supplemental material;e) forming a separation seam along said separation line and thereby separating said damaged section from said remainder of said structural component along said separation line, and then removing said damaged section from said remainder of said structural component;f) removing material from said structural component in a first area along said separation line in which said varying component thickness comprises a first area thickness greater than said desired welding thickness range so as to reduce said first area thickness of said structural component in said first area along said separation line to fall within said desired welding thickness range, and/or adding material to said structural component in a second area along said separation line in which said varying component thickness comprises a second area thickness less than said desired welding thickness range so as to increase said second area thickness of said structural component in said second area along said separation line to fall within said desired welding thickness range;g) after said step e), arranging a replacement section fitting into said remainder of said structural component along said separation line to replace said damaged section that has been separated and removed, wherein said replacement section has, along said separation line, a thickness within said desired welding thickness range;h) after said steps f) and g), welding said replacement section to said remainder of said structural component along said separation line to form along said separation line a weld seam that joins said replacement section to said remainder of said structural component; andi) after said step h), adding material to said replacement section and to said structural component in said first area so as to form a first component surface contour in said first area wherein said thickness of said replacement section and said first area thickness of said structural component in said first area along said separation line are increased to greater than said desired welding thickness range, and/or removing material from said replacement section and said structural component in said second area so as to form a second component surface contour in said second area wherein said thickness of said replacement section and said second area thickness of said structural component in said second area along said separation line are reduced to less than said desired welding thickness range. 2. The method according to claim 1, wherein said structural component is a component of a stator arrangement of a gas turbine apparatus. 3. The method according to claim 1, wherein said step c) comprises determining a location and path of said separation line to have a minimum necessary length around said damaged section in said structural component such that said damaged section can be separated along said separation line and removed from said remainder of said structural component. 4. The method according to claim 1, wherein said determining of said location and said path of said separation line is carried out without regard to and independent of said varying component thickness. 5. The method according to claim 1, wherein said determining of said separation line is carried out without regard to and independent of said varying component thickness. 6. The method according to claim 1, wherein said adding of said material in said step f) and/or said adding of said material in said step i) is carried out by laser deposit welding. 7. The method according to claim 1, wherein said removing of said material in said step f) and/or said removing of said material in said step i) is carried out by surface machining. 8. The method according to claim 1, wherein said adding of said material and/or said removing of said material in said step f) is carried out so as to make said first area thickness and/or said second area thickness as uniform as possible within said desired welding thickness range along said separation line. 9. The method according to claim 1, wherein said step f) comprises said removing of said material, said step i) comprises said adding of said material, and said adding of said material in said step i) adds an amount and thickness of said material corresponding to an amount and thickness of said material removed in said step f). 10. The method according to claim 1, wherein said step f) comprises said adding of said material, step i) comprises said removing of said material, and said removing of said material in said step i) removes said material that was added in said step f). 11. The method according to claim 1, wherein said step b) comprises determining said desired welding thickness range as an optimal weld seam material thickness along said weld seam, said step f) comprises both said removing of said material in said first area and said adding of said material in said second area, and said step i) comprises both said adding of said material in said first area and said removing of said material in said second area. 12. The method according to claim 1, wherein said step f) is carried out before said step e). 13. The method according to claim 1, wherein said step f) is carried out after said step e). 14. The method according to claim 1, further comprising, after said step h), applying additional material onto said replacement section by laser powder deposit welding so as to form on said replacement section a desired component surface contour. 15. The method according to claim 14, further comprising carrying out a surface machining of said additional material on said replacement section so as to machine said desired component surface contour to a finished component surface contour. 16. The method according to claim 1, further comprising carrying out a surface machining of said material that was added in said first area in said step i) so as to machine said first component surface contour to a finished component surface contour. 17. The method according to claim 1, further comprising removing said supplemental material after said step h). 18. The method according to claim 1, further comprising, before said step g), a step of providing as said replacement section a solid member having a configuration corresponding to said damaged section but without said damage. 19. The method according to claim 1, wherein said structural component is a guide vane ring of a gas turbine, wherein said damaged section is a damaged guide vane of said guide vane ring, and wherein said method further comprises, before said step g), a step of providing as said replacement section a replacement guide vane to replace said damaged guide vane.