Method for forming a coating matrix on a shaft and disk assembly for a turbine

Abstract

A method for forming a coating matrix on a bore surface of a turbine disk wherein the coating matrix is applied at an interface between the disk and a turbine shaft. The coating matrix enhances thermal conductivity to increase heat transfer from the disk. The method includes providing a receiving surface on the bore surface. The receiving surface is then heated to melt the receiving surface. Next, at least one coating matrix layer is deposited on the receiving surface. The coating matrix layer includes a graphene layer. A pulsed laser system or a robot welding system may be used to melt the receiving section.

What is claimed is: 
     
         1 . A method for forming a coating matrix on a component used in a shrink fit arrangement wherein the coating matrix has a higher thermal conductivity than the component, comprising:
 providing a receiving section on the component;   heating the receiving section to melt the receiving section; and   depositing at least one coating matrix layer on the receiving section.   
     
     
         2 . The method according to  claim 1 , wherein the receiving section is melted to a depth approximately equivalent to a thickness of the coating matrix layer. 
     
     
         3 . The method according to  claim 2 , wherein the depth is approximately 10-1000 micrometers. 
     
     
         4 . The method according to  claim 1 , wherein the coating matrix includes graphene. 
     
     
         5 . The method according to  claim 1 , wherein the coating matrix includes graphene and copper. 
     
     
         6 . The method according to  claim 1 , wherein the coating matrix includes a graphene layer located between copper layers. 
     
     
         7 . The method according to  claim 6 , wherein the coating matrix includes graphene layers which are adjacent each other. 
     
     
         8 . The method according to  claim 1 , wherein the coating matrix is applied to a shrink fit interface between shrink fit components. 
     
     
         9 . The method according to  claim 1 , wherein the receiving section is located on a bore surface of a turbine disk. 
     
     
         10 . The method according to  claim 1 , wherein the receiving section is located on a surface of a turbine shaft. 
     
     
         11 . A method for forming a coating matrix on a component used in a shrink fit arrangement wherein the coating matrix has a higher thermal conductivity than the component, comprising:
 providing a receiving section on the component;   thermal spraying a graphene layer on the receiving section; and
 thermal spraying a copper layer on the graphene layer thereby forming the coating matrix. 
   
     
     
         12 . The method according to  claim 11  further including thermal spraying an anti-corrosion coating on the receiving section. 
     
     
         13 . The method according to  claim 11 , wherein a graphene layer is formed between copper layers. 
     
     
         14 . The method according to  claim 13 , wherein at least two graphene layers are formed adjacent each other. 
     
     
         15 . The method according to  claim 11 , wherein the coating matrix is applied to a shrink fit interface between shrink fit components. 
     
     
         16 . The method according to  claim 11 , wherein the receiving section is located on a bore surface of a turbine disk. 
     
     
         17 . The method according to  claim 11 , wherein the receiving section is located on a surface of a turbine shaft. 
     
     
         18 . A shaft and disk assembly for use in a turbine, comprising:
 a disk having a central bore;   a shaft received by the central bore, wherein the shaft and central bore are fastened by a shrink fit arrangement; and   a coating matrix located between the central bore and the shaft, wherein the coating matrix has a higher thermal conductivity than the disk.   
     
     
         19 . The shaft and disk assembly according to  claim 18 , wherein the coating matrix includes graphene. 
     
     
         20 . The shaft and disk assembly according to  claim 18 , wherein the coating matrix is formed on a receiving section of a surface of the central bore. 
     
     
         21 . A shaft and disk assembly for use in a turbine, comprising:
 a disk having a central bore and an outer diameter which includes a plurality of grooves, wherein each groove is adapted to receive an associated blade;   a shaft affixed to the central bore; and   a coating matrix applied to first and second sides of the disk, the outer diameter, the grooves and between the central bore and the shaft, wherein the coating matrix has a higher thermal conductivity than the disk.   
     
     
         22 . The shaft and disk assembly according to  claim 21 , wherein the coating matrix includes graphene.