Method and apparatus for cooling combustor liner in combustor

Abstract

A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner.

1 . A combustor comprising:
 a transition piece;   an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween; and,   an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path.   
     
     
         2 . The combustor of  claim 1 , wherein the injection sleeve is mounted to the impingement sleeve. 
     
     
         3 . The combustor of  claim 1 , wherein the impingement sleeve comprises a forward sleeve portion, and wherein the injection sleeve is mounted to the forward sleeve portion. 
     
     
         4 . The combustor of  claim 1 , wherein the flow path defines an axial flow direction, and wherein the flow channel is configured such that working fluid flowing through the flow channel is exhausted from the flow channel at an angle in the range between approximately 0° and approximately 45° from the axial flow direction. 
     
     
         5 . The combustor of  claim 1 , wherein the flow channel is a generally annular flow channel. 
     
     
         6 . The combustor of  claim 1 , wherein the injection sleeve further defines a plurality of flow channels, the plurality of flow channels disposed in a generally annular array. 
     
     
         7 . The combustor of  claim 1 , wherein the combustor further comprises a combustor liner and a flow sleeve at least partially surrounding the combustor liner, the combustor liner and flow sleeve further defining the flow path. 
     
     
         8 . The combustor of  claim 7 , wherein the flow channel is configured to flow working fluid to the flow path adjacent the combustor liner, cooling the combustor liner. 
     
     
         9 . The combustor of  claim 7 , wherein the injection sleeve is further mounted to the flow sleeve. 
     
     
         10 . A sleeve assembly for a combustor, the combustor comprising a transition piece and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween, the sleeve assembly comprising:
 an inner sleeve configured for mounting to the transition piece;   an intermediate sleeve at least partially surrounding the inner sleeve and configured to partially define the flow path therebetween, the intermediate sleeve configured for mounting to the impingement sleeve; and,   an injection sleeve mounted to one of the inner sleeve or the intermediate sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid therethrough.   
     
     
         11 . The sleeve assembly of  claim 10 , wherein the injection sleeve is mounted to the intermediate sleeve. 
     
     
         12 . The sleeve assembly of  claim 10 , wherein the intermediate sleeve is configured for mounting to a forward sleeve portion of the impingement sleeve. 
     
     
         13 . The sleeve assembly of  claim 10 , wherein the flow path defines an axial flow direction, and wherein the flow channel is configured such that working fluid flowing through the flow channel is exhausted from the flow channel at an angle in the range between approximately 0° and approximately 45° from the axial flow direction. 
     
     
         14 . The sleeve assembly of  claim 10 , wherein the flow channel is a generally annular flow channel. 
     
     
         15 . The sleeve assembly of  claim 10 , wherein the injection sleeve further defines a plurality of flow channels, the plurality of flow channels disposed in a generally annular array. 
     
     
         16 . A method for cooling a combustor liner in a combustor, the method comprising:
 flowing a working fluid through a flow channel at least partially defined by an injection sleeve, the injection sleeve mounted to one of a transition piece or an impingement sleeve and positioned radially outward of the impingement sleeve, the impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween;   exhausting the working fluid from the flow channel into the flow path adjacent the combustor liner.   
     
     
         17 . The method of  claim 16 , wherein the flow path defines an axial flow direction, and wherein the working fluid is exhausted from the flow channel at an angle in the range between 0° and 45° from the axial flow direction. 
     
     
         18 . The method of  claim 16 , wherein the injection sleeve is mounted to the impingement sleeve. 
     
     
         19 . The method of  claim 16 , wherein the flow channel is a generally annular flow channel. 
     
     
         20 . The method of  claim 16 , wherein the injection sleeve further defines a plurality of flow channels, the plurality of flow channels disposed in a generally annular array.