Combustor for a gas turbomachine

Abstract

A combustor for a gas turbomachine includes a combustor body, and a combustor liner arranged in the combustor body and defining a combustion chamber extending from a head end to a combustor discharge. The combustor liner is spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage. At least one nozzle is arranged at the head end of the combustor liner. The at least one nozzle includes an outlet configured and disposed to establish a flame zone. At least one recirculation member is arranged at the head end of the combustor liner. The at least one recirculation member is configured and disposed to guide oxygen-depleted combustion products from the flame zone back to the outlet of the at least one nozzle.

What is claimed is: 
     
         1 . A combustor for a gas turbomachine comprising:
 a combustor body;   a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge, the combustor liner being spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage;   at least one nozzle arranged at the head end of the combustor liner, the at least one nozzle including an outlet configured and disposed to establish a flame zone; and   at least one recirculation member arranged at the head end of the combustor liner, the at least one recirculation member being configured and disposed to guide oxygen-depleted combustion products from the flame zone back to the outlet of the at least one nozzle.   
     
     
         2 . The combustor according to  claim 1 , wherein the at least one recirculation member includes an outer surface and an inner surface that defines an interior cavity. 
     
     
         3 . The combustor according to  claim 2 , wherein the interior cavity is fluidically connected to the CDC airflow passage. 
     
     
         4 . The combustor according to  claim 2 , wherein the at least one recirculation member includes a plurality of openings extending through the inner and outer surfaces fluidically connecting the interior cavity and the combustion chamber. 
     
     
         5 . The combustor according to  claim 4 , wherein the at least one recirculation member includes a plurality of guide elements arranged at respective ones of the plurality of openings on the outer surface. 
     
     
         6 . The combustor according to  claim 2 , further comprising: a recirculation passage arranged radially outwardly of the at least one recirculation member. 
     
     
         7 . The combustor according to  claim 6 , wherein the recirculation passage is defined between the at least one recirculation member and the combustor liner. 
     
     
         8 . The combustor according to  claim 6 , further comprising: an aerodynamically shaped vane arranged in the recirculation passage. 
     
     
         9 . The combustor according to  claim 6 , further comprising: at least one conduit extending from the combustor liner to the at least one recirculation member, the at least one conduit fluidically connecting the CDC air flow passage and the interior cavity. 
     
     
         10 . The combustor according to  claim 1 , wherein the at least one recirculation member extends radially outwardly of, and about, the at least one nozzle. 
     
     
         11 . A gas turbomachine comprising:
 a compressor portion;   a turbine portion operatively connected to the compressor portion; and   a combustor assembly including at least one combustor fluidically connecting the compressor portion and the turbine portion, the at least one combustor comprising:
 a combustor body; 
 a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge, the combustor liner being spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage; 
 at least one nozzle arranged at the head end of the combustor liner, the at least one nozzle including an outlet configured and disposed to establish a flame zone; and 
 at least one recirculation member arranged at the head end of the combustor liner, the at least one recirculation member being configured and disposed to guide oxygen-depleted combustion products from the flame zone back to the outlet of the at least one nozzle. 
   
     
     
         12 . The turbomachine according to  claim 11 , wherein the at least one recirculation member includes an outer surface and an inner surface that defines an interior cavity. 
     
     
         13 . The turbomachine according to  claim 12 , wherein the interior cavity is fluidically connected to the CDC airflow passage. 
     
     
         14 . The turbomachine according to  claim 12 , wherein the at least one recirculation member includes a plurality of openings extending through the inner and outer surfaces fluidically connecting the interior cavity and the combustion chamber. 
     
     
         15 . The turbomachine according to  claim 14 , wherein the at least one recirculation member includes a plurality of guide elements arranged at respective ones of the plurality of openings on the outer surface. 
     
     
         16 . The turbomachine according to  claim 11 , further comprising: a recirculation passage arranged radially outwardly of the at least one recirculation member. 
     
     
         17 . The turbomachine according to  claim 16 , wherein the recirculation passage is defined between the at least one recirculation member and the combustor liner. 
     
     
         18 . A gas turbomachine system comprising:
 a compressor portion;   a turbine portion operatively connected to the compressor portion;   an air inlet system fluidically connected to the compressor portion;   a load operatively connected to one of the compressor portion and the turbine portion; and   a combustor assembly including at least one combustor fluidically connecting the compressor portion and the turbine portion, the at least one combustor comprising:
 a combustor body; 
 a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge, the combustor liner being spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage; 
 at least one nozzle arranged at the head end of the combustor liner, the at least one nozzle including an outlet configured and disposed to establish a flame zone; and 
 at least one recirculation member arranged at the head end of the combustor liner, the at least one recirculation member being configured and disposed to guide oxygen-depleted combustion products from the flame zone back to the outlet of the at least one nozzle. 
   
     
     
         19 . The gas turbomachine system according to  claim 18 , wherein the at least one recirculation member includes an outer surface and an inner surface that defines an interior cavity fluidically connected to the CDC airflow passage. 
     
     
         20 . The gas turbomachine system according to  claim 19 , wherein the at least one recirculation member includes a plurality of openings extending through the inner and outer surfaces fluidically connecting the interior cavity and the combustion chamber, and a plurality of guide elements arranged at respective ones of the plurality of openings on the outer surface, and wherein a recirculation passage being arranged radially outwardly of the at least one recirculation member.