PRODUCTION OF A TURBINE BLISK HAVING AN OXIDATION AND/OR CORROSION PROTECTION LAYER

摘要

The present invention relates to a method for producing an integral turbine blade and disk unit (20) for a gas turbine, comprising the following steps: a) providing an integral turbine blade and disk unit (20), comprising a disk (21) made of an Ni-based super alloy and at least one turbine blade (22) bonded to the disk; and b) coating at least one part of the surface of the blade of the turbine blade and disk unit with an oxidation and/or corrosion protection layer using a low-temperature coating method, and to a corresponding method comprising the following steps: a) providing a disk (21) made of an Ni-based super alloy; b) providing at least one turbine blade (22) for connecting the disk so as to form an integral turbine blade and disk unit; c) coating at least one part of the surface of the turbine blade with an oxidation and/or corrosion protection layer; and d) joining the coated turbine blade to the disk by bonding so as to form the integral turbine blade and disk unit.