| 摘要 |
The invention relates to a method of repair for gas turbine components, in particular for integrally bladed gas turbine rotors, comprising the following steps: a) providing a gas turbine component that is to be repaired, in particular an integrally bladed gas turbine rotor; b) removing a damaged portion, in particular a damaged blade aerofoil portion, from the gas turbine component that is to be repaired, involving forming a connecting portion, in particular a blade stump; c) providing a surround for the connecting portion; d) attaching the surround to the connecting portion in such a way that the surround encloses the connecting portion with virtually no gap, and in such a way that a connecting surface of the connecting portion lies together with a surface of the surround in one plane; e) renewing the removed portion by building up the same on the connecting portion by laser beam generation; f) working the renewed portion by milling, involving removing the surround. |
