Patent ID: 8771786

Claim:
A method for the repair of a rotor of an aircraft gas turbine, with blades ( 8 ) taken up in at least one groove ( 6 ) and with at least one support region ( 26 ) for blades ( 8 ) for limiting a blade tilt angle α, comprising the steps of: providing a rotor having at least one annular groove, the at least one annular groove having side walls, removing at least one segment ( 28 ), which has been subjected to wear, of a first support region ( 26 ) adjacent to the annular groove, and forming a coating ( 38 ) that can be introduced in the unit on at least one supporting surface ( 36 ) of a second support region for engaging at least one blade ( 8 ) for limiting the blade tilt angle α, the coating forming a bearing surface on the at least one supporting surface, wherein the bearing surface limits the blade tilt angle α more than the supporting surface would without the coating applied thereon.