Method for producing a protective layer for a rotor blade

Abstract

A method for producing a protective layer for a rotor blade of a turbomachine is proposed. The rotor blade has a wear cap wall that in relation to the axis of the turbomachine protrudes radially towards the exterior of the turbomachine beyond a body of the rotor blade. The method enables the entire rotor blade to have a comparatively long service life and at the same time allows the wear cap wall to be thermally insulated in an especially simple manner. For the purpose, a profile producing a positive fit effective in the radial direction is inserted in a radially located region of the wear cap wall, a slip containing metal powder and/or a ceramic slip is applied to the region and the slip in sintered.

1 .- 10 . (canceled) 
     
     
         11 . A method for producing a protective layer for a rotor blade of a turbomachine having a wear tip wall projecting toward an outside of the turbomachine beyond a body of the rotor blade in a radial direction with respect to an axis of the turbomachine, comprising:
 introducing a profile producing a radial form fit into a radial region of the wear tip wall; and   applying a metal powder-containing slurry and/or a ceramic slurry to the region,   wherein the slurry is sintered.   
     
     
         12 . The method as claimed in  claim 11 , wherein the profile is cast and/or introduced by electric discharge machining. 
     
     
         13 . The method as claimed in  claim 11 , wherein the slurry is dried before sintering, and wherein shape of the dried slurry is machined. 
     
     
         14 . The method as claimed in  claim 11 , wherein the slurry is water based and/or an organic binder is added to the slurry. 
     
     
         15 . The method as claimed in  claim 11 , wherein a metal powder-containing slurry and a ceramic slurry are applied in sequence. 
     
     
         16 . The method as claimed in  claim 11 , wherein the slurry comprises ceramic fibers or gauzes. 
     
     
         17 . The method as claimed in  claim 11 , wherein the wear tip wall is arranged around a circumference of the rotor blade and forms a recess arranged radially toward the outside of the turbomachine with respect to the axis of the turbomachine, and wherein the region encloses an inside of the recess. 
     
     
         18 . A rotor blade for a turbomachine, comprising:
 a wear tip wall projecting toward an outside of the turbomachine beyond a body of the rotor blade in a radial direction with respect to an axis of the turbomachine;   a profile being introduced in a region of the wear tip wall; and   a sintered metal powder-containing slurry and/or a ceramic slurry being applied to the region.   
     
     
         19 . A power plant, comprising:
 a turbomachine comprising a rotor blade as claimed in  claim 18 .