HIGH-PRESSURE TURBINE BLADE AND METHOD OF REPAIRING HIGH-PRESSURE TURBINE BLADES

摘要

The invention relates to a procedure for repair of high pressure turbine blades of an aircraft engine, with the steps:separating a damaged section of the high pressure turbine blade; andgenerating a section to replace the separated section on or upon the high pressure turbine blade by means of laser beam generation from the powder bed, as well as a high pressure turbine blade.