Primary fuel nozzle having dual fuel capability

A gas turbine combustor capable of operating on multiple fuels with reduced carbon buildup, said combustor comprising:

• a generally cylindrical combustion liner having a center liner axis, a first end, and a second end;
• a cap assembly fixed to said combustion liner proximate said first end and located generally within said combustion liner, said cap assembly having a plurality of openings located about said center liner axis, each of said openings having a mixing tube and a collar, with said mixing tube having a forward tube end and an aft tube end with said aft tube end proximate said opening, and said collar positioned adjacent said forward tube end of said mixing tube;
• a plurality of fuel nozzles arranged about said center liner axis, each of said fuel nozzles corresponding to one of said openings, and having a fuel nozzle axis, a nozzle tip, and comprising:
• a liquid fuel assembly comprising:
• a first tube extending substantially along said fuel nozzle axis;
• a second tube surrounding said first tube;
• a third tube surrounding said second tube,
• a gas fuel assembly comprising:
• a nozzle body surrounding said third tube of said liquid fuel assembly, said nozzle body having a first wall, a second wall, and a plurality of swirler vanes extending therebetween;
• and,
• wherein each of said first, second, and third tubes extend to proximate said nozzle tip, said nozzle body extends to proximate said nozzle tip, and said nozzle tip is located approximately halfway between said forward tube end and said aft tube end of said mixing tube.