Patent ID: 7634854

Claim:
A method for joining blades to blade roots or rotor disks when manufacturing and/or repairing gas turbine blades or integrally bladed gas turbine rotors, comprising: a) prefabricating a blade and a blade support to be joined to the blade, the blade support being one of a blade root and a rotor disk, the blade having a thickened region at a portion of the blade to be joined to the blade support, the blade support having a thickened region at a portion of the blade support to be joined to the blade; b) machining said portion of the blade and said portion of the blade support to form recesses; c) subsequently mutually aligning the blade and the blade support to be joined to the blade such that said recesses form mutually opposing recesses delimiting at least one groove-shaped weld preparation; d) joining the blade and the blade support in an area of the at least one groove-shaped weld preparation by employing laser powder build-up welding; e) machining the joined blade and blade support to form a gas turbine blade or an integrally bladed gas turbine rotor having a predefined geometric profile.