Method for reprocessing a turbine blade having at least one platform

Abstract

A method for reprocessing a turbine blade having at least one platform which due to the action of corrosion is undersized on at least one lateral platform face is provided. According to the method, the target dimension of the platform is restored by applying material to the at least one lateral platform face such that, after the material application, the platform is oversized and then the platform is given the target dimension by machining the at least one lateral platform face. The material application is carried out with the material of an adhesion promoter layer.

1 - 12 . (canceled) 
     
     
         13 . A process for refurbishing a turbine blade or vane having at least one platform which, on account of corrosive attack, is undersized on a platform side face, comprising:
 restoring the desired dimension of the platform, the restoring comprising:
 applying material to the platform side face in such a manner that, after the material application, the platform is oversized, and 
 machining the platform side face in order the to give the desired dimension to the platform, 
   wherein the material application is effected with the material of an adhesion promoter layer,   wherein the adhesion promoter material is applied within the scope of renewing a thermal barrier coating system of the turbine blade or vane which comprises an adhesion promoter layer and a thermal barrier coating, and   wherein the material of the adhesion promoter layer is an MCrAlX material.   
     
     
         14 . The process as claimed in  claim 13 , wherein the material application is effected by means of the repeated application of the adhesion promoter material. 
     
     
         15 . The process as claimed in  claim 13 , wherein the material application of at least  10  um is used each time the application of adhesion promoter material is repeated. 
     
     
         16 . The process as claimed in  claim 13 , further comprising using a bonding heat treatment after the application of adhesion promoter material. 
     
     
         17 . The process as claimed in  claim 13 , wherein the material application and the machining are effected on two opposite platform side faces. 
     
     
         18 . The process as claimed in  claim 17 , wherein the turbine blade or vane includes a central axis and the machining of the platform side face to give the platform the desired dimension is effected with respect to the central axis. 
     
     
         19 . The process as claimed in  claim 18 , wherein the current dimension of the platform is gathered by scanning at least five measurement points on the opposite platform side faces and the required material removal for the machining is determined from the current dimension. 
     
     
         20 . The process as claimed in  claim 17 , wherein the turbine blade or vane includes a main blade or vane part with a pressure side and a suction side and the opposite platform side faces are the platform side faces located on the pressure side and suction side in relation to the main blade or vane part. 
     
     
         21 . The process as claimed in  claim 13 , the machining is realized by face grinding. 
     
     
         22 . The process as claimed in  claim 21 , wherein a plurality of layers are removed from the turbine blade or vane before the thermal barrier coating system is renewed. 
     
     
         23 . The process as claimed in  claim 22 , wherein activation blasting is effected after the plurality of layers have been removed and before the thermal barrier coating system is renewed. 
     
     
         24 . The process as claimed in  claim 13 , wherein the adhesion promoter material is applied by means of a thermal spraying process.