Fuel nozzle for combustor

A combustor for a gas turbine system, the combustor comprising:

• a nozzle, the nozzle comprising:
• a center body;
• a burner tube provided around the center body and defining a fuel-air mixing passage therebetween;
• an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween;
• a nozzle tip connected to the center body, the nozzle tip comprising:
• a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone;
• and
• a plurality of transfer passages radially outboard of the pilot fuel passage, the plurality of transfer passages configured to deliver a flow of air for combustion with the flow of pilot fuel in the combustion zone and further configured to deliver a flow of transfer fuel to the combustion zone;
• and
• at least one swirl vane disposed in the fuel-air mixing passage, the swirl vane defining a cooling chamber configured to receive fuel from a premix fuel passage, and
• wherein the fuel flows from the premix fuel passage through a reverse flow passage into the cooling chamber.