Method of producing a protective coating, protective coating, and component with a protective coating

Abstract

A method for producing a wear-resistant, temperature-resistant, and corrosion-resistant protective coating for a component, in particular for components of a gas turbine, using thermal spraying, wherein during the application onto the component of the protective coating, which consists of a hard material-metal combination, in order to produce an abrasive surface a structuring of that surface of the protective coating that faces away from the component takes place, the hard material or materials consisting of boron nitride particles, titanium carbide particles, tungsten carbide particles, chromium carbide particles, and zirconium oxide particles, or a mixture thereof, and the hard materials having a particle size of 0.1 μm-200 μm, and the protective coating having a thickness of 10 μm-6.0 mm.

1 - 13 . (canceled) 
   
   
       14 . A method for producing a wear-resistant, temperature-resistant, and corrosion-resistant protective coating for a component, in particular for components of a gas turbine, using thermal spraying, characterized in that during the application onto the component of the protective coating, which consists of a hard material-metal combination, in order to produce an abrasive surface a structuring of that surface of the protective coating that faces away from the component takes place, the hard material or materials consisting of boron nitride particles, titanium carbide particles, tungsten carbide particles, chromium carbide particles, and zirconium oxide particles, or a mixture thereof, and the hard materials having a particle size of 0.1 μm-200 μm, and the protective coating having a thickness of 10 μm-6.0 mm. 
   
   
       15 . The method as recited in  claim 14 , wherein the structuring is produced by a covering masking during the application of the protective coating. 
   
   
       16 . The method as recited in  claim 14 , wherein the structuring is produced by a segmented application of the protective coating. 
   
   
       17 . The method as recited in  claim 14 , wherein the structuring is produced by applying the protective coating onto the component with different thicknesses. 
   
   
       18 . A protective coating, namely a wear-resistant, temperature-resistant, and corrosion-resistant protective coating for a component, in particular for components of a gas turbine, having an abrasive surface, wherein the protective coating has a one-layer construction and is produced using a method according to  claim 14 , and that the protective coating is made of a hard material-metal combination, and that the hard material or materials consist of boron nitride particles, titanium carbide particles, tungsten carbide particles, chromium carbide particles, and zirconium oxide particles, or a mixture thereof, and that the hard materials have a particle size of 0.1 μm-200 μm, and that the protective coating has a thickness of 10 μm-6.0 mm. 
   
   
       19 . The protective coating as recited in  claim 18 , wherein the protective coating has a thickness of 30 μm-300 μm, in particular 30-150 μm. 
   
   
       20 . The protective coating as recited in  claim 18 , wherein the hard materials are situated in a matrix made of metal or a metal alloy. 
   
   
       21 . The protective coating as recited in  claim 14 , wherein the protective coating is fashioned as a continuous or segmented layer. 
   
   
       22 . The protective coating as recited in  claim 14 , wherein the protective coating has different thicknesses. 
   
   
       23 . The protective coating as recited in  claim 14 , wherein the protective coating has a blade-like construction. 
   
   
       24 . The protective coating as recited in  claim 14 , wherein the protective coating has a multiplicity of projections on the surface of the layer that faces away from the component. 
   
   
       25 . A component, in particular a component of a gas turbine, having a protective coating as recited in  claim 18 . 
   
   
       26 . The use of a wear-resistant, temperature-resistant, oxidation-resistant, and corrosion-resistant protective coating as recited in  claim 18 , for the coating and/or repair of turbine parts and engine parts, in particular of gas turbines in an aircraft engine.