Annular flow conditioning member for gas turbomachine combustor assembly

Abstract

A turbomachine combustor assembly includes a combustor body, a combustor liner arranged within the combustor body and defining a combustion chamber, a fluid passage defined between the combustor body and the combustor liner, and an annular flow conditioning member arranged in the fluid passage and extending about the combustor liner.

1 . A turbomachine combustor assembly comprising:
 a combustor body;   a combustor liner arranged within the combustor body and defining a combustion chamber;   a fluid passage defined between the combustor body and the combustor liner; and   an annular flow conditioning member arranged in the fluid passage and extending about the combustor liner.   
     
     
         2 . The turbomachine combustor assembly according to  claim 1 , wherein the annular flow conditioning member includes an external surface and an internal surface that defines an annular fuel plenum. 
     
     
         3 . The turbomachine combustor assembly according to  claim 2 , wherein the external surface of the annular flow conditioning member includes an aerodynamic profile. 
     
     
         4 . The turbomachine combustor assembly according to  claim 3 , wherein the aerodynamic profile defines an airfoil. 
     
     
         5 . The turbomachine combustor assembly according to  claim 2 , wherein the annular flow conditioning member includes a plurality of openings extending through the external and internals surfaces, the plurality of openings fluidly connecting the annular fuel plenum and the fluid passage. 
     
     
         6 . The turbomachine combustor assembly according to  claim 2 , further comprising: a fuel delivery passage fluidly connected to the annular fuel plenum. 
     
     
         7 . The turbomachine combustor assembly according to  claim 1 , further comprising: a support member extending between the combustor body and the annular flow conditioning member. 
     
     
         8 . The turbomachine combustor assembly according to  claim 7 , further comprising: another between the combustor liner and the annular flow conditioning member. 
     
     
         9 . The turbomachine combustor assembly according to  claim 1 , further comprising: another annular flow conditioning member arranged in the fluid passage and extending about the combustor liner. 
     
     
         10 . The turbomachine combustor assembly according to  claim 9 , wherein the another annular flow conditioning member extends about the annular flow conditioning member. 
     
     
         11 . The turbomachine combustor assembly according to  claim 9 , wherein the another annular flow conditioning member is arranged downstream relative to the annular flow conditioning member. 
     
     
         12 . The turbomachine combustor assembly according to  claim 11 , wherein the another annular flow conditioning member is arranged substantially co-planar relative to the annular flow conditioning member. 
     
     
         13 . The turbomachine combustor assembly according to  claim 11 , wherein the another annular flow conditioning member is axially off-set relative to the annular flow conditioning member. 
     
     
         14 . A gas turbomachine system comprising:
 a compressor portion;   a turbine portion operatively coupled to the compressor portion; and   a combustor assembly fluidly connecting the compressor portion and the turbine portion, the combustor assembly comprising:
 a combustor body; 
 a combustor liner arranged within the combustor body and defining a combustion chamber; 
 a fluid passage defined between the combustor body and the combustor liner; and 
 an annular flow conditioning member arranged in the fluid passage and extending about the combustor liner. 
   
     
     
         15 . The gas turbomachine system according to  claim 14 , wherein the annular flow conditioning member includes an external surface that defines an aerodynamic profile and an internal surface that defines an annular fuel plenum. 
     
     
         16 . The gas turbomachine system according to  claim 14 , further comprising: another annular flow conditioning member arranged in the fluid passage and extending about the combustor liner. 
     
     
         17 . The gas turbomachine system according to  claim 16 , wherein the another annular flow conditioning member extends about the annular flow conditioning member. 
     
     
         18 . The gas turbomachine system according to  claim 16 , wherein the another annular flow conditioning member is arranged downstream relative to the annular flow conditioning member. 
     
     
         19 . The gas turbomachine system according to  claim 18 , wherein the another annular flow conditioning member is arranged substantially co-planar relative to the annular flow conditioning member. 
     
     
         20 . The gas turbomachine system according to  claim 18 , wherein the another annular flow conditioning member is axially off-set relative to the annular flow conditioning member.