Hot gas path component for turbine system

Abstract

A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell having an exterior surface and an interior surface. The hot gas path component further includes a porous medium having an exterior surface and an interior surface, the exterior surface positioned adjacent to the interior surface of the shell. The porous medium is configured for flowing a cooling medium therethrough.

What is claimed is: 
     
         1 . A hot gas path component for a turbine system, comprising:
 a shell having an exterior surface and an interior surface; and   a porous medium having an exterior surface and an interior surface, the exterior surface positioned adjacent to the interior surface of the shell, the porous medium configured for flowing a cooling medium therethrough.   
     
     
         2 . The hot gas path component of  claim 1 , further comprising an impingement sleeve positioned adjacent the interior surface of the porous medium. 
     
     
         3 . The hot gas path component of  claim 1 , wherein the interior surface of the porous medium is treated. 
     
     
         4 . The hot gas path component of  claim 1 , wherein the porous medium defines an impingement passage extending between the interior surface and the exterior surface. 
     
     
         5 . The hot gas path component of  claim 1 , wherein the exterior surface of the porous medium is in contact with the interior surface of the shell. 
     
     
         6 . The hot gas path component of  claim 1 , wherein the shell defines a cooling passage extending between the interior surface and the exterior surface. 
     
     
         7 . The hot gas path component of  claim 6 , wherein the cooling passage further extends at least partially into the porous medium. 
     
     
         8 . The hot gas path component of  claim 1 , wherein the porous medium is formed from one of a metal foam, a ceramic foam, or a carbon fiber foam. 
     
     
         9 . The hot gas path component of  claim 1 , further comprising a plurality of porous mediums, and wherein an exterior surface of each of the plurality of porous mediums is positioned adjacent to the interior surface of the shell. 
     
     
         10 . The hot gas path component of  claim 1 , wherein the hot gas path component is a nozzle. 
     
     
         11 . A turbine system, comprising:
 a compressor;   a turbine coupled to the compressor; and   a plurality of hot gas path components disposed in at least one of the compressor or the turbine, at least one of the hot gas path components comprising:
 a shell having an exterior surface and an interior surface; and 
 a porous medium having an exterior surface and an interior surface, the exterior surface positioned adjacent to the interior surface of the shell, the porous medium configured for flowing a cooling medium therethrough. 
   
     
     
         12 . The turbine system of  claim 11 , further comprising an impingement sleeve positioned adjacent the interior surface of the porous medium. 
     
     
         13 . The turbine system of  claim 11 , wherein the interior surface of the porous medium is treated. 
     
     
         14 . The turbine system of  claim 11 , wherein the porous medium defines an impingement passage extending between the interior surface and the exterior surface. 
     
     
         15 . The turbine system of  claim 11 , wherein the exterior surface of the porous medium is in contact with the interior surface of the shell. 
     
     
         16 . The turbine system of  claim 11 , wherein the shell defines a cooling passage extending between the interior surface and the exterior surface. 
     
     
         17 . The turbine system of  claim 16 , wherein the cooling passage further extends at least partially into the porous medium. 
     
     
         18 . The turbine system of  claim 11 , wherein the porous medium is formed from one of a metal foam, a ceramic foam, or a carbon fiber foam. 
     
     
         19 . The turbine system of  claim 11 , further comprising a plurality of porous mediums, and wherein an exterior surface of each of the plurality of porous mediums is positioned adjacent to the interior surface of the shell. 
     
     
         20 . The turbine system of  claim 11 , wherein the hot gas path component is a nozzle.