Combustor liner for a can-annular gas turbine engine and a method for constructing such a liner

Abstract

A combustor liner ( 30 ) for a can-annular gas turbine engine ( 10 ) and a method for constructing such a liner are provided. The combustor liner includes an annular wall member ( 32 ) A cooling channel ( 34, 42, 50, 54, 56, 58 ) is formed through the wall member and extends from an inlet end of the liner to an outlet end of the liner A property of the cooling channel may be varied along a length of the cooling channel. The cooling channel may be formed through the combustor liner using an electro-chemical machining (ECM) process or a three dimensional printing process (3DP).

The invention claimed is: 
     
         1 . A combustor liner for a can-annular gas turbine engine comprising.
 an annular wall member; and   a cooling channel formed through the wall member and extending from an inlet end of the liner to an outlet end of the liner,   wherein a property of the cooling channel varies along a length of the cooling channel.   
     
     
         2 . The combustor liner of  claim 1 , wherein a circumferential position of the cooling channel varies along a longitudinal axis of the liner 
     
     
         3 . The combustor liner of  claim 2 , wherein the cooling channel defines a curved shape 
     
     
         4 . The combustor liner of  claim 2 , wherein the cooling channel defines a helix shape. 
     
     
         5 . The combustor liner of  claim 1 , wherein a diameter of the cooling channel is not constant along its length. 
     
     
         6 . The combustor liner of  claim 1 , wherein a surface finish of the cooling channel is not constant along its length 
     
     
         7 . The combustor liner of  claim 1 , wherein a cross-sectional shape of the cooling channel is not constant along its length. 
     
     
         8 . The combustor liner of  claim 1 , wherein a cross-sectional shape of the cooling channel comprises a multi-lobe shape. 
     
     
         9 . A combustor comprising the combustor liner of  claim 1 . 
     
     
         10 . A method for constructing a combustor liner for a can-annular gas turbine engine, the method comprising:
 establishing expected thermal transfer demands along the combustor liner;   forming a cooling channel through the combustor liner using a process for forming a structure; and   controlling the forming process to vary a cooling channel property along a length of the cooling channel based on the expected thermal transfer demands.   
     
     
         11 . The method of  claim 10 , wherein the forming process comprises an electro-chemical machining process. 
     
     
         12 . The method of  claim 10 , wherein the forming process comprises a three-dimensional printing process 
     
     
         13 . The method of  claim 10 , further comprising varying a circumferential position of the cooling channel along a longitudinal axis of the liner. 
     
     
         14 . The method of  claim 13 , wherein the cooling channel defines a helix shape 
     
     
         15 . The method of  claim 10 , further comprising controlling the forming process such that a diameter of the cooling channel is not constant along its length. 
     
     
         16 . The method of  claim 10 , further comprising controlling the forming process such that a surface finish of the cooling channel is not constant along its length. 
     
     
         17 . The method of  claim 10 , further comprising controlling the forming process such that a cross-sectional shape of the cooling channel is not constant along its length 
     
     
         18 . The method of  claim 10 , further comprising controlling the forming process such that a cross-sectional shape of the cooling channel comprises a multi-lobe shape 
     
     
         19 . A combustor liner for a can-annular gas turbine engine comprising.
 an annular wall member, and   a cooling channel formed through the wall member and extending from an inlet end of the liner to an outlet end of the liner,   wherein a property of the cooling channel varies along a length of the cooling channel, and wherein the cooling channel is formed by a process selected from the group consisting of an electro-chemical machining process and a three-dimensional printing process.