초록 ▼

A nozzle for a combustor is disclosed. The nozzle includes a center body, a burner tube provided around the center body and defining a fuel-air mixing passage therebetween, and an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween. The nozzle further

A nozzle for a combustor is disclosed. The nozzle includes a center body, a burner tube provided around the center body and defining a fuel-air mixing passage therebetween, and an outer peripheral wall provided around the burner tube and defining an air flow passage therebetween. The nozzle further includes a nozzle tip connected to the center body. The nozzle tip includes a pilot fuel passage configured to deliver a flow of pilot fuel to a combustion zone, and a plurality of transfer passages. The plurality of transfer passages are 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.

대표청구항 ▼

1. A nozzle for a combustor, 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 cen

1. A nozzle for a combustor, 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; anda 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; andat 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, andwherein the fuel flows from the premix fuel passage through a reverse flow passage into the cooling chamber. 2. The nozzle of claim 1, the tip defining a plurality of pilot holes connecting the pilot fuel passage to the plurality of transfer passages. 3. The nozzle of claim 1, the tip defining a diffuser configured such that the flow of pilot fuel flows from the pilot fuel passage through the diffuser into the combustion zone. 4. The nozzle of claim 1, wherein the flow of pilot fuel and the flow of air are at least partially mixed prior to combustion. 5. The nozzle of claim 4, wherein the flow of pilot fuel and flow of air are at least partially mixed in the plurality of transfer passages. 6. The nozzle of claim 1, wherein the burner tube is film-cooled by air in the air flow passage. 7. The nozzle of claim 1, wherein the at least one swirl vane further defines an outlet chamber configured to expel the fuel through at least one fuel injection port into the fuel-air mixing passage, and wherein the at least one swirl vane further comprises a divider provided between the cooling chamber and the outlet chamber. 8. The nozzle of claim 7, wherein the divider defines a by-pass hole configured to permit fuel flow from the cooling chamber to the outlet chamber. 9. 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; anda 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; andat 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, andwherein the fuel flows from the premix fuel passage through a reverse flow passage into the cooling chamber. 10. The combustor of claim 9, the tip defining a plurality of pilot holes connecting the pilot fuel passage to the plurality of transfer passages. 11. The combustor of claim 9, the tip defining a diffuser configured such that the flow of pilot fuel flows from the pilot fuel passage through the diffuser into the combustion zone. 12. The combustor of claim 9, wherein the flow of pilot fuel and the flow of air are at least partially mixed prior to combustion. 13. The combustor of claim 12, wherein the flow of pilot fuel and flow of air are at least partially mixed in the plurality of transfer passages. 14. The combustor of claim 9, wherein the at least one swirl vane further defines an outlet chamber configured to expel the fuel through at least one fuel injection port into the fuel-air mixing passage, and wherein the at least one swirl vane further comprises a divider provided between the cooling chamber and the outlet chamber. 15. The combustor of claim 14, wherein the divider defines a by-pass hole configured to permit fuel flow from the cooling chamber to the outlet chamber.