Turbomachine component marking

Abstract

A system for indicating wear of a turbomachine is provided herein. An embodiment of the system includes a turbomachine component, an indicating layer which is formed on the surface of the turbomachine component, and a top layer which covers the indicating layer, such that the indicating layer becomes optically detectable if the top layer is worn out by wear due to exposure of a working fluid or is fretted by fretting due to a contact of the turbomachine component with a further turbomachine component.

1 . A system for indicating wear of a turbomachine, the system comprising:
 a turbomachine component,   a further turbomachine component which contacts the turbomachine component,   wherein a groove is formed to the turbomachine component in a contact area with the further turbomachine component,   an indicating layer which is formed within the groove of the turbomachine component, and   a top layer which is formed within the groove and which covers the indicating layer, such that the indicating layer becomes optically detectable if the top layer is fretted by fretting due to the contact of the turbomachine component with a further turbomachine component.   
     
     
         2 . The system according to  claim 1 , wherein the top layer comprises a top layer colour, and wherein the indicating layer comprises an indicating colour which differs from the top layer colour. 
     
     
         3 . The system according to  claim 1 , wherein the top layer comprises a top layer structure, and wherein the indicating layer comprises an indicating structure which differs from the top layer structure. 
     
     
         4 . The system according to  claim 1 , wherein the indicating colour differs from a component colour of the turbomachine component. 
     
     
         5 . The system according to  claim 1 , further comprising a further indicating layer with a further indicating colour, wherein the further indicating layer is interposed between the top layer and the indicating layer, and wherein the further indicating colour differs from the indicating colour, from the top layer colour and from a component colour of the turbomachine component. 
     
     
         6 . The system according to  claim 1 , wherein the top layer and/or the indicating layer is a hard coating layer, wherein the hard coating layer has a lower coefficient of friction and a higher resistance to wear or fretting in comparison to the material of the turbomachine component. 
     
     
         7 . The system according to  claim 1 , wherein the top layer and/or the indicating layer is an oxidation protection coating layer, and wherein the oxidation protection coating layer has a higher resistance to oxidation in comparison to the material of the turbomachine component. 
     
     
         8 . The system according to  claim 1 , wherein the top layer and/or the indicating layer is a smooth surface coating layer, and wherein the smooth surface coating layer has a lower surface roughness or coefficient of friction in comparison to the material of the turbomachine component. 
     
     
         9 . The system according to  claim 1 , wherein the turbomachine component is a combustion chamber, a blade, a vane, a seal, a tile, a transition duct or a wall section of the turbomachine. 
     
     
         10 . The system according to  claim 1 , wherein the turbomachine component has a curved shape with a circumferential direction, wherein the indicating layer comprises a plurality of indicating layer sections which is interposed between the top layer and the surface of the turbomachine component, and wherein the indicating layer sections are spaced apart from each other along the circumferential direction. 
     
     
         11 . A method for indicating wear of a turbomachine, the method comprising:
 indicating wear of a turbomachine component by an indicating layer if a top layer is fretted by fretting due to a contact of the turbomachine component with a further turbomachine component, wherein the further turbomachine component contacts the turbomachine component,   wherein a groove is formed to the turbomachine component in a contact area with the further turbomachine component,   wherein the indicating layer is formed within the groove of the turbomachine component, and wherein the top layer is formed on within the surface groove and covers the indicating layer, such that the indicating layer becomes optically detectable if the top layer is fretted by fretting.