US2013323430A1PendingUtilityA1

Method of coating corner interface of turbine system

48
Assignee: TAXACHER GLENN CURTISPriority: May 31, 2012Filed: May 31, 2012Published: Dec 5, 2013
Est. expiryMay 31, 2032(~5.8 yrs left)· nominal 20-yr term from priority
Inventors:Glenn Curtis Taxacher
C23C 4/01C23C 4/12
48
PatentIndex Score
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Claims

Abstract

A method of coating a corner interface of a turbine system includes placing a mesh assembly proximate the corner interface. The method also includes depositing a coating onto and through the mesh assembly and into the corner interface, wherein the mesh assembly dampens a kinetic energy of the coating and secures the coating proximate the corner interface.

Claims

exact text as granted — not AI-modified
1 . A method of coating a corner interface of a turbine system comprising:
 placing a mesh assembly proximate the corner interface; and   depositing a coating onto and through the mesh assembly and into the corner interface, wherein the mesh assembly dampens a kinetic energy of the coating and secures the coating proximate the corner interface.   
     
     
         2 . The method of coating a corner interface of a turbine system of  claim 1 , wherein the corner interface comprises an intersection between a first surface and a second surface, the first surface and the second surface defining an angle of open area of approximately 90 degrees. 
     
     
         3 . The method of coating a corner interface of a turbine system of  claim 1 , wherein the corner interface comprises an intersection between a first surface and a second surface, the first surface and the second surface defining an angle of open area of approximately 270 degrees. 
     
     
         4 . The method of coating a corner interface of a turbine system of  claim 1 , wherein placing the mesh assembly proximate the corner interface comprises bonding the mesh assembly to a surface. 
     
     
         5 . The method of coating a corner interface of a turbine system of  claim 1 , wherein placing the mesh assembly proximate the corner interface comprises tacking the mesh assembly to a surface. 
     
     
         6 . The method of coating a corner interface of a turbine system of  claim 1 , wherein the mesh assembly comprises a ceramic material. 
     
     
         7 . The method of coating a corner interface of a turbine system of  claim 1 , wherein the mesh assembly comprises a carbon based material. 
     
     
         8 . The method of coating a corner interface of a turbine system of  claim 1 , wherein the mesh assembly comprises a polymer material. 
     
     
         9 . The method of coating a corner interface of a turbine system of  claim 1 , wherein the mesh assembly comprises a metallic alloy. 
     
     
         10 . The method of coating a corner interface of a turbine system of  claim 1 , further comprising placing a plurality of mesh assemblies proximate the corner interface. 
     
     
         11 . The method of coating a corner interface of a turbine system of  claim 1 , wherein the coating comprises a plasma. 
     
     
         12 . A method of coating a corner interface of a turbine component comprising:
 placing a mesh assembly proximate the corner interface, wherein the mesh assembly is removable;   depositing a coating onto and through the mesh assembly and into the corner interface, wherein the mesh assembly dampens a kinetic energy of the coating and secures the coating proximate the corner interface; and   removing the mesh assembly from proximate the corner interface.   
     
     
         13 . The method of coating a corner interface of a turbine component of  claim 12 , wherein placing the mesh assembly proximate the corner interface comprises bonding the mesh assembly to the corner interface. 
     
     
         14 . The method of coating a corner interface of a turbine component of  claim 12 , wherein placing the mesh assembly proximate the corner interface comprises tacking the mesh assembly to the corner interface. 
     
     
         15 . The method of coating a corner interface of a turbine component of  claim 12 , further comprising placing a plurality of mesh assemblies proximate the corner interface. 
     
     
         16 . The method of coating a corner interface of a turbine component of  claim 12 , wherein the coating comprises a plasma. 
     
     
         17 . A method of coating a corner interface of a turbine component comprising:
 placing a mesh assembly proximate the corner interface; and   depositing a coating onto and through the mesh assembly and into the corner interface, wherein the mesh assembly dampens a kinetic energy of the coating and secures the coating proximate the corner interface, wherein the mesh assembly comprises a material that is consumable within the coating.   
     
     
         18 . The method of coating a corner interface of a turbine component of  claim 17 , wherein placing the mesh assembly proximate the corner interface comprises bonding the mesh assembly to the corner interface. 
     
     
         19 . The method of coating a corner interface of a turbine component of  claim 17 , wherein placing the mesh assembly proximate the corner interface comprises tacking the mesh assembly to the corner interface. 
     
     
         20 . The method of coating a corner interface of a turbine component of  claim 17 , further comprising placing a plurality of mesh assemblies proximate the corner interface.

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