A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10). A higher degree of precision and automation can be achieved, because the worn out location is measured/scanned with 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 the 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.