Turbomachine combustor assembly and method of operating a turbomachine

Abstract

A turbomachine combustor assembly includes a combustor body having a combustor outlet, and a combustion liner arranged within the combustor body. The combustion liner defines a combustion chamber. An injection nozzle is arranged within the combustor body upstream from the combustion chamber. The injection nozzle is configured and disposed to deliver a first fluid toward the combustion chamber. A fluid module is mounted to the combustor body downstream from the combustion chamber. The fluid module includes a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.

1 . A turbomachine combustor assembly comprising:
 a combustor body having a combustor outlet;   a combustion liner arranged within the combustor body, the combustion liner defining a combustion chamber;   an injection nozzle arranged within the combustor body upstream from the combustion chamber, the injection nozzle being configured and disposed to deliver a first fluid toward the combustion chamber; and   a fluid module mounted to the combustor body downstream from the combustion chamber, the fluid module including a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.   
     
     
         2 . The turbomachine combustor assembly according to  claim 1 , wherein the injection nozzle is configured and disposed to deliver an axial stream of the first fluid toward the combustion chamber 
     
     
         3 . The turbomachine combustor assembly according to  claim 2 , wherein the first injector member is configured to deliver a first radial stream of the second fluid into the fluid zone at the first orientation, and the second injector member is configured to deliver a second radial stream of the third fluid into the fluid zone at the second orientation. 
     
     
         4 . The turbomachine combustor assembly according to  claim 3 , wherein the first orientation is substantially perpendicular to the fluid module body and the second orientation is angled downstream of the first orientation. 
     
     
         5 . The turbomachine combustor assembly according to  claim 1 , wherein the first injector member includes a first plurality of injector members arranged in an annular array about the fluid module body and the second injector member includes a second plurality of injector members arranged in an annular array about the fluid module body. 
     
     
         6 . The turbomachine combustor assembly according to  claim 5 , wherein the second plurality of injector members is arranged downstream relative to the first plurality of injector members. 
     
     
         7 . The turbomachine combustor assembly according to  claim 1 , wherein the injection nozzle is configured and disposed to establish a first fluid zone, the first injector member is configured and disposed to establish a second fluid zone downstream from the first fluid zone, and the second injector member is configured to establish a third fluid zone downstream from the second fluid zone. 
     
     
         8 . A method of operating a turbomachine comprising:
 introducing a first fluid into a combustor assembly to establish a first fluid zone;   introducing a second fluid into the combustor assembly to establish a second fluid zone down stream of the first fluid zone;   introducing a third fluid into the combustor assembly to establish a third fluid zone downstream of the second fluid zone; and   combusting one or more of the first, second and third fluids to produce a hot gas stream to establish a first operating mode of the turbomachine.   
     
     
         9 . The method of  claim 8 , wherein introducing the first fluid includes guiding a stream of the first fluid along a longitudinal axis of the combustor assembly. 
     
     
         10 . The method of  claim 9 , wherein introducing the second fluid includes injecting a stream of the second fluid along a first radial axis of the combustor assembly. 
     
     
         11 . The method of  claim 10 , wherein introducing the third fluid includes injecting a stream of the third fluid along a second radial axis of the combustor assembly, the second radial axis being angled relative to the first radial axis. 
     
     
         12 . The method of  claim 8 , further comprising: ceasing introduction of the third fluid establishing a second operating mode of the turbomachine. 
     
     
         13 . The method of  claim 12 , wherein establishing the second operating mode includes operating the turbomachine at about 40% to about 70% of the first operating mode. 
     
     
         14 . The method of  claim 12 , further comprising: ceasing introduction of the second fluid establishing a third operating mode of the turbomachine. 
     
     
         15 . The method of  claim 14 , wherein establishing the third operating mode includes operating the turbomachine at about 20% to about 40% of the first operating mode. 
     
     
         16 . A turbomachine comprising:
 a compressor portion;   a turbine portion operatively connected to the turbine portion; and   a combustor assembly fluidly connected to the compressor portion and the turbine portion, the combustor assembly comprising:
 a combustor body; 
 a combustion liner arranged within the combustor body, the combustion liner defining a combustion chamber; 
 an injection nozzle arranged within the combustor body upstream from the combustion chamber, the injection nozzle being configured and disposed to introduce a first fluid toward the combustion chamber; and 
 a fluid module mounted to the combustor body downstream from the combustion chamber, the fluid module including a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation. 
   
     
     
         17 . The turbomachine according to  claim 16 , wherein the injection nozzle is configured and disposed to deliver an axial stream of the first fluid toward the combustion chamber. 
     
     
         18 . The turbomachine according to  claim 16 , wherein the first injector member is configured to deliver a radial stream of the second fluid into the fluid zone, and the second injector member is configured to deliver a radial stream of the third fluid into the fluid zone. 
     
     
         19 . The turbomachine according to  claim 16 , wherein the injection nozzle is configured and disposed to establish a first fluid zone, the first injector member is configured and disposed to establish a second fluid zone down stream from the first fluid zone, and the second injector member is configured to establish a third fluid zone downstream from the second fluid zone. 
     
     
         20 . The turbomachine according to  claim 18 , further comprising: a transition piece fluidly connecting the combustor assembly and the turbine portion, at least a portion of one the third fluid zone residing in the transition piece.