A fuel nozzle for a combustor, comprising: an inner tube defining a first flow passage for flowing one of a fuel or an oxidizer therethrough, the inner tube comprising a first swirler device configured to impart a swirl on the one of the fuel or the oxidizer; an intermediate tube at least partially surrounding the inner tube and defining a second flow passage for flowing one of a fuel or an oxidizer therethrough, the intermediate tube comprising a second swirler device configured to impart a swirl on the one of the fuel or the oxidizer; and an outer tube at least partially surrounding the intermediate tube and defining a third flow passage for flowing one of a fuel or an oxidizer therethrough, the outer tube comprising a third swirler device configured to impart a swirl on the one of the fuel or the oxidizer, wherein at least one of the first swirler device, the second swirler device, or the third swirler device comprises a plurality of swirler vanes, at least a portion of the swirler vanes configured to impart a swirl on the one of the fuel or the oxidizer and wherein each of the first flow passage, the second flow passage, and the third flow passage defines a generally axial axis, wherein one of the first flow passage, the second flow passage or the third flow passage is configured to flow fuel therethrough, another of the first flow passage, the second flow passage or the third fuel passage is configured to flow fuel therethrough, any of a third of the first flow passage, the second is configured to flow passage or the third flow passage flows oxidizer therethrough; characterized in that the fuel nozzle further comprises: a plurality of igniter devices (112, 114) extending through a plurality of the flow passages; wherein the inner tube includes a tip and wherein the first swirler device comprises a passage defined in the tip and configured to impart a swirl on the fuel flowing through the passage defined in the tip; and wherein the vanes of each of the first swirler device, the second swirler device, and the third swirler device are positioned at an angle with respect to the axial axis in the range between approximately 40° and approximately 60°. an inner tube defining a first flow passage for flowing one of a fuel or an oxidizer therethrough, the inner tube comprising a first swirler device configured to impart a swirl on the one of the fuel or the oxidizer; an intermediate tube at least partially surrounding the inner tube and defining a second flow passage for flowing one of a fuel or an oxidizer therethrough, the intermediate tube comprising a second swirler device configured to impart a swirl on the one of the fuel or the oxidizer; and an outer tube at least partially surrounding the intermediate tube and defining a third flow passage for flowing one of a fuel or an oxidizer therethrough, the outer tube comprising a third swirler device configured to impart a swirl on the one of the fuel or the oxidizer, wherein at least one of the first swirler device, the second swirler device, or the third swirler device comprises a plurality of swirler vanes, at least a portion of the swirler vanes configured to impart a swirl on the one of the fuel or the oxidizer and wherein each of the first flow passage, the second flow passage, and the third flow passage defines a generally axial axis, wherein one of the first flow passage, the second flow passage or the third flow passage is configured to flow fuel therethrough, another of the first flow passage, the second flow passage or the third fuel passage is configured to flow fuel therethrough, any of a third of the first flow passage, the second is configured to flow passage or the third flow passage flows oxidizer therethrough; characterized in that the fuel nozzle further comprises: a plurality of igniter devices (112, 114) extending through a plurality of the flow passages; wherein the inner tube includes a tip and wherein the first swirler device comprises a passage defined in the tip and configured to impart a swirl on the fuel flowing through the passage defined in the tip; and wherein the vanes of each of the first swirler device, the second swirler device, and the third swirler device are positioned at an angle with respect to the axial axis in the range between approximately 40° and approximately 60°. a plurality of igniter devices (112, 114) extending through a plurality of the flow passages; wherein the inner tube includes a tip and wherein the first swirler device comprises a passage defined in the tip and configured to impart a swirl on the fuel flowing through the passage defined in the tip; and wherein the vanes of each of the first swirler device, the second swirler device, and the third swirler device are positioned at an angle with respect to the axial axis in the range between approximately 40° and approximately 60°.