Aerodynamic Fuel Nozzle

Abstract

The present application and the resultant patent provide a combustor for a turbine engine. The combustor may include a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly. The swirler assembly may include a number of stages with a number of fueled structures and a number of unfueled structures.

1 . A combustor for a turbine engine, comprising:
 a plurality of fuel nozzles; and   one or more of the plurality of fuel nozzles comprising a swirler assembly;   wherein the swirler assembly comprises a plurality of stages; and   wherein the plurality of stages comprises a plurality of fueled structures and a plurality of unfueled structures.   
     
     
         2 . The combustor of  claim 1 , wherein the plurality of fuel nozzles comprises a central fuel nozzle. 
     
     
         3 . The combustor of  claim 1 , wherein the plurality of stages comprises a first stage, a second stage, and a third stage. 
     
     
         4 . The combustor of  claim 1 , wherein the plurality of stages extend in an axial direction. 
     
     
         5 . The combustor of  claim 1 , wherein the plurality of stages extend in a circumferential direction. 
     
     
         6 . The combustor of  claim 1 , wherein the plurality of stages comprises a plurality of radial vanes. 
     
     
         7 . The combustor of  claim 1 , wherein the plurality of stages comprises a plurality of blocks. 
     
     
         8 . The combustor of  claim 7 , wherein the plurality of blocks comprises a plurality of fixed blocks and a plurality of movable blocks. 
     
     
         9 . The combustor of  claim 1 , wherein the plurality of fueled structures comprises a plurality of radial vanes and a plurality of blocks. 
     
     
         10 . The combustor of  claim 1 , wherein the plurality of fueled structures comprises a plurality of injection ports. 
     
     
         11 . The combustor of  claim 10 , wherein the plurality of injection ports comprises an axial direction and/or a circumferential direction. 
     
     
         12 . The combustor of claim her comprising a primary recirculation zone about the plurality of fuel nozzles and a secondary recirculation zone downstream of the plurality of fuel nozzles. 
     
     
         13 . The combustor of  claim 1 , wherein the plurality of fueled structures comprises a plurality of vanes. 
     
     
         14 . The combustor of  claim 1 , wherein the plurality of fueled structures comprises a plurality of movable blocks. 
     
     
         15 . A method of operating a combustor for late lean injection, comprising:
 providing a flow of air to a fuel nozzle;   providing a flow of fuel through one or more fueled structures of a swirler assembly;   swirling the flow of air and the flow of fuel through multiple stages of the swirler assembly;   establishing a primary recirculation zone about the fuel nozzle for low emissions; and   establishing a secondary recirculation zone downstream of the fuel nozzle for high temperatures.   
     
     
         16 . The method of  claim 15 , wherein the step of establishing a primary recirculation zone comprises combusting the flow of fuel and the flow of air near a flammability limit. 
     
     
         17 . The method of  claim 15 , wherein the step of establishing a primary recirculation zone comprises combusting the flow of fuel and the flow of air without forming nitrogen oxides. 
     
     
         18 . The method of  claim 15 , wherein the step of establishing a secondary recirculation zone comprises lean mixing of the flow of fuel and the flow of air. 
     
     
         19 . The method of  claim 15 , wherein the step of establishing a secondary recirculation zone downstream of the fuel nozzle for high temperatures comprises combusting the flow of fuel and the flow of air at higher combustion temperatures as compared to the primary recirculation zone. 
     
     
         20 . A swirler assembly for use with a combustor, comprising:
 a plurality of stages;   a plurality of vanes; and   a plurality of blocks;   wherein each of the plurality of stages comprises one or more of the plurality of vanes and/or one more of the plurality of blocks.