High-pressure turbine blade and procedure for repair of 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; and—generating 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.

主权项

1. A method for repairing high pressure turbine blades, comprising the following steps:
separating a damaged section of a high pressure turbine blade from a remaining blade section to define a section plane on the remaining blade section; determining a contour of the remaining blade section at the section plane; covering the remaining blade section to a predetermined height over the section plane with unfused powder to form a powder bed of unfused powder, the powder bed of unfused powder simultaneously covering the remaining blade section to the predetermined height over the section plane with unfused powder and surrounding the remaining blade section around a perimeter of the remaining blade section below the section plane with unfused powder; and generating a replacement layer for the damaged section on the remaining blade section from the powder bed using a laser beam to illuminate a first portion of the unfused powder covering the remaining blade section to selectively build up a fused powder layer on the remaining blade section; covering the remaining blade section to the predetermined height over the replacement layer with the unfused powder to form a subsequent powder bed of unfused powder at least one further time; and generating one or more subsequent replacement layers for the damaged section on the remaining blade section from each subsequent powder bed using the laser beam to illuminate a second portion of the unfused powder covering the remaining blade section to selectively build up one or more additional fused powder layers on the remaining blade section until the damaged section is replaced by the replacement layer and the one or more subsequent replacement layers.