A method for repairing a gas turbine component

Details A method for repairing a gas turbine component A method for repairing a gas turbine component

B - Operations, Transporting

23

P

B23P 6/04 (2006.01)

Patent

CA 2717717

A method for repairing a gas turbine component (10) comprises the steps of: = identifying on said gas turbine component (10) a worn out location, where said gas turbine component (10) is damaged; = removing said damaged location, thereby creating a missing zone (18); = manufacturing an insert, which fits into said missing zone (18); = putting said insert into said missing zone (18); = adjusting said insert in said gas turbine component (10); and = joining said adjusted insert to said gas turbine component (10). A higher degree of precision and automation is achieved, because = the worn out location is measured/scanned by means of a 3-D scanning/measuring system (20) to get the actual geometry of the missing zone (18), especially as a CAD data; = the nominal geometry for the insert is defined by said actual geometry of the worn out location, with respect to certain defined gap tolerances; = the actual geometry of the insert is measured during the manufacture of the insert; = the nominal geometry and the actual geometry of the insert are compared; and = an adaptive machining operation of the insert is carried out based on the results from the comparison between the actual and nominal geometries of the insert.

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