Combustor Wall Channel Cooling System

Abstract

The present application provides a combustor liner for use with a gas turbine engine. The combustor liner may include a liner wall extending from a head end to an aft end in whole or in part, a number of liner wall cooling channels positioned within the liner wall and extending from an inlet to an outlet, and a number of liner return ducts. The outlets of the liner wall cooling channels may be positioned about the liner return ducts.

We claim: 
     
         1 . A combustor liner for use with a gas turbine engine, comprising:
 a liner wall extending from a head end to an aft end in whole or in part;   a plurality of liner wall cooling channels positioned within the liner wall;   wherein the plurality of liner wall cooling channels extends from an inlet to an outlet; and   a plurality of liner return ducts;   wherein the outlets of the plurality of liner wall cooling channels are positioned about the plurality of liner return ducts.   
     
     
         2 . The combustor liner of  claim 1 , wherein the plurality of liner return ducts is in communication with a head end duct positioned about the head end of the liner wall. 
     
     
         3 . The combustor liner of  claim 2 , wherein the liner wall comprises a plurality of purge holes in communication with the head end duct. 
     
     
         4 . The combustor liner of  claim 1 , wherein the inlets of the plurality of liner wall cooling channels are positioned in communication with a flow of air in a flow path within a flow sleeve. 
     
     
         5 . The combustor liner of  claim 1 , wherein the plurality of liner wall cooling channels comprises a substantially square shape or a substantially round shape. 
     
     
         6 . The combustor liner of  claim 1 , wherein the plurality of liner wall cooling channels comprises a length of about 2 to 5 inches (about 5.1 to 20.3 centimeters). 
     
     
         7 . The combustor liner of  claim 1 , wherein the plurality of liner wall cooling channels comprises a diameter of about 0.060 inches (about 1.524 millimeters) to about 0.080 inches (about 2.0 millimeters). 
     
     
         8 . The combustor liner of  claim 1 , wherein the plurality of liner wall cooling channels comprise a inlet diameter of about 0.065 inches (about 1.65 millimeters) and an exit diameter of about 0.075 inches (about 1.91 millimeters). 
     
     
         9 . The combustor liner of  claim 1 , wherein the plurality of liner wall cooling channels may be positioned in a plurality of columns on the liner wall. 
     
     
         10 . The combustor liner of  claim 9 , wherein eight to fifteen of the plurality of liner wall cooling channels may be positioned in each of the plurality of columns on the liner wall. 
     
     
         11 . The combustor liner of  claim 1 , wherein the plurality of liner wall cooling channels is cast into the liner wall. 
     
     
         12 . The combustor liner of  claim 1 , wherein the plurality of liner wall cooling channels is formed in an additive manufacturing process. 
     
     
         13 . The combustor liner of  claim 1 , wherein the liner wall surrounds a combustion chamber. 
     
     
         14 . A method of cooling a component in a gas turbine engine, comprising:
 providing a flow of air to a wall of the component;   flowing the air through a plurality of cooling channels in the wall of the component;   flowing the air from the plurality of cooling channels in the wall of the component into a return duct; and   flowing the air in the return duct to a further component.   
     
     
         15 . The method of cooling of  claim 14 , wherein the step of flowing the air in the return duct to a further component comprises flowing the air in the return duct to a head end duct. 
     
     
         16 . A component for use with a gas turbine engine, comprising:
 a component wall extending from a head end to an aft end in whole or in part;   a plurality of component wall cooling channels positioned within the component wall;   wherein the plurality of component wall cooling channels extends from an inlet to an outlet; and   a plurality of component return ducts;   wherein the outlets of the plurality of component wall cooling channels are positioned about the plurality of component return ducts.   
     
     
         17 . The component of  claim 16 , wherein the component comprises a combustor liner. 
     
     
         18 . The component of  claim 16 , wherein the plurality of component wall cooling channels comprises an inlet and an outlet and wherein the outlets of the plurality of component wall cooling channels are positioned about the plurality of component return ducts. 
     
     
         19 . The component of  claim 16 , wherein the plurality of component return ducts is in communication with a duct positioned about the component wall. 
     
     
         20 . The component of  claim 16 , wherein the plurality of component wall cooling channels comprises a length of about 2 to 5 inches (about 5.1 to 20.3 centimeters).