Multi-premixer fuel nozzle

Abstract

The present application provides a fuel nozzle for use in a gas turbine. The fuel nozzle may include a mounting flange, a number of premixers attached to each other, and a number of gas pathways extending from the mounting flange to the number of premixers.

1 . A fuel nozzle for use in a gas turbine, comprising:
 a mounting flange;   a plurality of premixers attached to each other; and   a plurality of gas pathways extending from the mounting flange to the plurality of premixers.   
     
     
         2 . The fuel nozzle of  claim 1 , further comprising a center body in communication with the mounting flange. 
     
     
         3 . The fuel nozzle of  claim 1 , wherein the plurality of premixers each comprise a swirler therein. 
     
     
         4 . The fuel nozzle of  claim 3 , wherein the plurality of premixers each comprise a burner tube downstream of the swirler. 
     
     
         5 . The fuel nozzle of  claim 3 , wherein the swirler comprises a plurality of vanes. 
     
     
         6 . The fuel nozzle of  claim 5 , wherein the plurality of gas pathways extend from the mounting flange to the plurality of vanes of the swirlers in the plurality of premixers. 
     
     
         7 . The fuel nozzle of  claim 1 , wherein the plurality of premixers each comprise an air inlet section. 
     
     
         8 . The fuel nozzle of  claim 2 , wherein the center body comprises a plurality of pathways therethrough. 
     
     
         9 . The fuel nozzle of  claim 1 , wherein the plurality of gas pathways comprises a plurality of fuel tubes. 
     
     
         10 . The fuel nozzle of  claim 1 , further comprising an outer shell surrounding the plurality of fuel tubes. 
     
     
         11 . A combustion chamber, comprising:
 a center nozzle;   wherein the center nozzle comprises a fuel passage and a premixer; and   a plurality of outer nozzles;   wherein the plurality of outer nozzles comprises a plurality of fuel passages and a plurality of premixers.   
     
     
         12 . The combustion chamber of  claim 11 , wherein the plurality fuel passages extend from a mounting flange to the plurality of premixers. 
     
     
         13 . The combustion chamber of  claim 11 , wherein the plurality of premixers each comprise a swirler therein. 
     
     
         14 . The combustion chamber of  claim 13 , wherein the plurality of premixers each comprise a burner tube downstream of the swirler. 
     
     
         15 . The combustion chamber of  claim 13 , wherein the swirler comprises a plurality of vanes. 
     
     
         16 . The combustion chamber of  claim 15 , wherein the plurality of fuel passages extend from a center body to the plurality of vanes of the swirlers in the plurality of premixers. 
     
     
         17 . The combustion chamber of  claim 11 , wherein the plurality of premixers each comprise an air inlet section. 
     
     
         18 . A fuel nozzle for use in a gas turbine, comprising:
 a mounting flange;   a plurality of premixers attached to each other;   a plurality of fuel tubes extending from the mounting flange to the plurality of premixers; and   an outer shell surrounding the plurality of fuel tubes.   
     
     
         19 . The fuel nozzle of  claim 18 , wherein the plurality of premixers each comprise a swirler therein. 
     
     
         20 . The fuel nozzle of  claim 18 , wherein the swirler comprises a plurality of vanes on communication with the plurality of fuel tubes.