Abstract: A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a premixing chamber formed between an outer annular shroud and an inner annular hub, a number of swirler vanes disposed about the premixing chamber between the outer annular shroud and the inner annular hub, one or more liquid fuel injectors positioned about the swirler vanes, and a flow of liquid fuel in communication with the one or more liquid fuel injectors.

Abstract: A pre-film liquid fuel cartridge includes a main body having a water passage, a liquid fuel passage, a compressed air passage and a pre-film tip disposed at a downstream portion of the pre-film liquid fuel cartridge. The pre-film tip includes a forward end portion that is axially separated from an aft end portion and an inner side that extends therebetween. The inner side at least partially defines a pre-filming surface which terminates at an emulsion atomizing shear edge. The pre-film tip includes a plurality of water injection ports oriented tangentially through the pre-filming surface, a plurality of liquid fuel injection ports oriented tangentially through the pre-filming surface and a plurality of atomizing air injection ports axially oriented around the emulsion atomizing shear edge. An atomizing air shear edge is defined downstream from the emulsion atomizing shear edge and the atomizing air injection ports.

Abstract: A pre-film liquid fuel cartridge (20) includes a primary liquid fuel passage (106), a plurality of inner fuel ports (116) and a plurality of outer fuel ports (124) that are in fluid communication with the primary liquid fuel passage. An inner pre-filming surface (142) is defined downstream from the plurality of inner fuel ports. The inner pre-filming surface (142) terminates at a first shear edge (140). An outer pre-filming surface (152) is defined downstream from the plurality of outer fuel ports. The outer pre-filming surface (152) terminates at a second shear edge (154). The first and second shear edges are relatively oriented so that a first pre-filmed liquid fuel sheet exiting the first shear edge intersects with a second pre-filmed liquid fuel sheet exiting the second shear edge, thereby atomizing the first and second pre-filmed liquid fuel sheets.

Abstract: A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a premixing chamber formed between an outer annular shroud and an inner annular hub, a number of swirler vanes disposed about the premixing chamber between the outer annular shroud and the inner annular hub, one or more liquid fuel injectors positioned about the swirler vanes, and a flow of liquid fuel in communication with the one or more liquid fuel injectors.

Abstract: A pre-film liquid fuel cartridge includes a main body having a water passage, a liquid fuel passage, a compressed air passage and a pre-film tip disposed at a downstream portion of the pre-film liquid fuel cartridge. The pre-film tip includes a forward end portion that is axially separated from an aft end portion and an inner side that extends therebetween. The inner side at least partially defines a pre-filming surface which terminates at an emulsion atomizing shear edge. The pre-film tip includes a plurality of water injection ports oriented tangentially through the pre-filming surface, a plurality of liquid fuel injection ports oriented tangentially through the pre-filming surface and a plurality of atomizing air injection ports axially oriented around the emulsion atomizing shear edge. An atomizing air shear edge is defined downstream from the emulsion atomizing shear edge and the atomizing air injection ports.

Abstract: A combustor (10) includes a combustion chamber (18), a liner (12) surrounding the combustion chamber, and a flow sleeve (52) surrounding the liner. An annular passage is between the liner and the flow sleeve, and a fuel injector (50) is located partially in the annular passage and extending through the liner into the combustion chamber. The fuel injector includes an outer tube, an inner tube, and a flow passage. A method of supplying a fuel to a combustor includes flowing a diluent inside an outer tube extending along a liner and flowing a liquid or gaseous fuel inside an inner tube extending inside a portion of the outer tube. The method further includes flowing the diluent and the liquid or gaseous fuel through the liner and into a combustion chamber surrounded by the liner.

Abstract: A pre-film liquid fuel cartridge (20) includes a primary liquid fuel passage (106), a plurality of inner fuel ports (116) and a plurality of outer fuel ports (124) that are in fluid communication with the primary liquid fuel passage. An inner pre-filming surface (142) is defined downstream from the plurality of inner fuel ports. The inner pre-filming surface (142) terminates at a first shear edge (140). An outer pre-filming surface (152) is defined downstream from the plurality of outer fuel ports. The outer pre-filming surface (152) terminates at a second shear edge (154). The first and second shear edges are relatively oriented so that a first pre-filmed liquid fuel sheet exiting the first shear edge intersects with a second pre-filmed liquid fuel sheet exiting the second shear edge, thereby atomizing the first and second pre-filmed liquid fuel sheets.

Abstract: A gas turbine system is provided. The gas turbine system includes a combustor assembly. At least one liquid fuel cartridge in the combustor assembly includes at least one flexible tube section coupled within a housing. An elongated inner tube section is coupled in fluid communication with the at least one flexible tube section and oriented within an elongated outer tube extending from the housing. At least one support member oriented within and coupled to an inner surface of the elongated outer tube substantially precludes transverse movement of the elongated inner tube section within the elongated outer tube.

Abstract: A combustor (10) includes a liner (12) that defines a combustion chamber (18) first pre-mix chamber (14) is upstream of the combustion chamber, and a fuel plenum (40) in fluid communication with the first pre-mix chamber surrounds a least a portion of the first pre-mix chamber. A method of supplying a fuel to combustor includes flowing the fuel over an outer surface of a first pre-mix chamber and into the first pre-mix chamber.

Abstract: A fuel nozzle for a combustor includes a burner tube and a center nozzle assembly disposed within the burner tube. The center nozzle assembly includes a center body that at least partially defines a cooling air flow passage through the center nozzle assembly. A premix flow passage is defined between the burner tube and the center nozzle assembly. A tip assembly is disposed at a downstream end of the center body. The tip assembly includes an impingement plate, and a cap that is disposed downstream from the impingement plate. The impingement plate and the cap at least partially define a cooling plenum therebetween. An insert passage extends through the impingement plate and a cooling flow outlet extends through the cap. A plurality of cooling ports extends through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum.

Abstract: A fuel nozzle for a combustor includes a burner tube and a center nozzle assembly disposed within the burner tube. The center nozzle assembly includes a center body that at least partially defines a cooling air flow passage through the center nozzle assembly. A premix flow passage is defined between the burner tube and the center nozzle assembly. A tip assembly is disposed at a downstream end of the center body. The tip assembly includes an impingement plate, and a cap that is disposed downstream from the impingement plate. The impingement plate and the cap at least partially define a cooling plenum therebetween. An insert passage extends through the impingement plate and a cooling flow outlet extends through the cap. A plurality of cooling ports extends through the impingement plate to provide for fluid communication between the cooling air flow passage and the cooling plenum.

Abstract: A combustor (10) includes a combustion chamber (18), a liner (12) surrounding the combustion chamber, and a flow sleeve (52) surrounding the liner. An annular passage is between the liner and the flow sleeve, and a fuel injector (50) is located partially in the annular passage and extending through the liner into the combustion chamber. The fuel injector includes an outer tube, an inner tube, and a flow passage. A method of supplying a fuel to a combustor includes flowing a diluent inside an outer tube extending along a liner and flowing a liquid or gaseous fuel inside an inner tube extending inside a portion of the outer tube. The method further includes flowing the diluent and the liquid or gaseous fuel through the liner and into a combustion chamber surrounded by the liner.