System for Protecting an Inner Wall of a Combustor

Abstract

In a first embodiment a system, including a gas turbine combustor, including an inner wall disposed about a combustion chamber, and an outer wall disposed about the inner wall, wherein a coolant flow path extends between the inner and outer walls, wherein the inner wall comprises a material blocking a plurality of openings, and the plurality of openings are configured to open after the material is consumed or depleted to define a plurality of coolant passages through the inner wall.

1 . A system, comprising:
 a gas turbine combustor, comprising:
 an inner wall disposed about a combustion chamber; and 
 an outer wall disposed about the inner wall, wherein a coolant flow path extends between the inner and outer walls; 
 wherein the inner wall comprises a material blocking a plurality of openings, and the plurality of openings are configured to open after the material is consumed or depleted to define a plurality of coolant passages through the inner wall. 
   
     
     
         2 . The system of  claim 1 , wherein the material is part of the inner wall. 
     
     
         3 . The system of  claim 1 , wherein the material is part of a protective coating disposed over an inner surface of the inner wall. 
     
     
         4 . The system of  claim 3 , wherein the protective coating comprises a thermal barrier coating, a chemical resistant coating, an oxidation resistant coating, or a combination thereof. 
     
     
         5 . The system of  claim 3 , wherein the protective coating comprises a ceramic-based coating. 
     
     
         6 . The system of  claim 1 , wherein the plurality of openings have a uniform width, a uniform spacing, a uniform depth, or any combination thereof. 
     
     
         7 . The system of  claim 1 , wherein the plurality of openings have a variable width, a variable spacing, a variable depth, or any combination thereof. 
     
     
         8 . The system of  claim 1 , wherein the plurality of coolant passages are configured to provide effusion cooling of the inner wall. 
     
     
         9 . The system of  claim 1 , wherein the plurality of coolant passages are configured to provide film cooling of the inner wall. 
     
     
         10 . The system of  claim 1 , wherein the plurality of coolant passages are configured to block exposure of the inner wall to hot combustion gases. 
     
     
         11 . The system of  claim 1 , wherein the inner wall comprises a combustor liner, a transition piece, or any combination thereof. 
     
     
         12 . The system of  claim 1 , comprising a gas turbine engine having the gas turbine combustor. 
     
     
         13 . A system, comprising:
 a gas turbine engine, comprising:
 a coolant flow path; 
 a combustion gas path; and 
 a wall between the coolant flow path and the combustion gas path, wherein a first side of the wall faces the coolant flow path, and a second side of the wall faces the combustion gas path; 
 wherein the wall comprises a material blocking a plurality of openings, and the plurality of openings are configured to open after oxidation of the material to define a plurality of coolant passages through the wall. 
   
     
     
         14 . The system of  claim 13 , wherein the material is part of the wall. 
     
     
         15 . The system of  claim 13 , wherein the material is part of a protective coating disposed over second side of the wall. 
     
     
         16 . The system of  claim 15 , wherein the protective coating comprises a thermal barrier coating, a chemical resistant coating, an oxidation resistant coating, or a combination thereof. 
     
     
         17 . The system of  claim 13 , wherein the plurality of coolant passages are configured to block exposure of the wall to hot combustion gases along the combustion gas path. 
     
     
         18 . The system of  claim 13 , wherein the gas turbine engine comprises a gas turbine combustor having the wall. 
     
     
         19 . A system, comprising:
 a combustion system, comprising:
 a coolant flow path; 
 a combustion gas path; and 
 a wall between the coolant flow path and the combustion gas path, wherein a first side of the wall faces the coolant flow path, and a second side of the wall faces the combustion gas path; 
 wherein the wall comprises a material blocking a plurality of openings, and the plurality of openings are configured to open after oxidation of the material to define a plurality of coolant passages through the wall. 
   
     
     
         20 . The system of  claim 19 , wherein the combustion system comprises a gas turbine engine, a gas turbine combustor, or a combination thereof, having the wall.