A multi-functional fuel nozzle for a combustion turbine engine, comprising: an annular fuel-injecting lance comprising a first fluid circuit and a second fluid circuit, wherein the first fluid circuit is centrally disposed within the lance, wherein the first fluid circuit extends along a longitudinal axis of the lance to convey a first fluid to a downstream end of the lance, wherein the second fluid circuit is annularly disposed about the first fluid circuit to convey a second fluid to the downstream end of the lance, wherein one of the first and second fluids comprises a liquid fuel conveyed by one of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine, wherein the other of the first and second fluids conveyed by the other of the first and second fluid circuits comprises a selectable non-fuel fluid; an atomizer disposed at the downstream end of the lance, the atomizer having a first ejection orifice responsive to the first fluid circuit to form a first atomized ejection cone, the atomizer further having a second ejection orifice responsive to the second fluid circuit to form a second atomized ejection cone, wherein the first and second ejection orifices of the atomizer are respectively configured so that the first and second ejection cones formed with the atomizer comprise concentric cones that intersect with one another over a predefined angular range; wherein, during a gas fuel operating mode of the engine, the selectable non-fuel fluid comprises water, which is conveyed by at least one of the first and second fluid circuits, and wherein at least one of the first and second ejection cones (34, 36) comprises a respective cone formed of atomized water, characterised in that a plurality of gas fuel channels are circumferentially disposed about the longitudinal axis of the lance, the plurality of gas fuel channels being positioned circumferentially outwardly relative to the annular lance, and that an angular range of the first atomized ejection cone extends from approximately 80 degrees to approximately 120 degrees and and that an angular range of the second atomized ejection cone extends from approximately 40 degrees to approximately 90 degrees. an annular fuel-injecting lance comprising a first fluid circuit and a second fluid circuit, wherein the first fluid circuit is centrally disposed within the lance, wherein the first fluid circuit extends along a longitudinal axis of the lance to convey a first fluid to a downstream end of the lance, wherein the second fluid circuit is annularly disposed about the first fluid circuit to convey a second fluid to the downstream end of the lance, wherein one of the first and second fluids comprises a liquid fuel conveyed by one of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine, wherein the other of the first and second fluids conveyed by the other of the first and second fluid circuits comprises a selectable non-fuel fluid; an atomizer disposed at the downstream end of the lance, the atomizer having a first ejection orifice responsive to the first fluid circuit to form a first atomized ejection cone, the atomizer further having a second ejection orifice responsive to the second fluid circuit to form a second atomized ejection cone, wherein the first and second ejection orifices of the atomizer are respectively configured so that the first and second ejection cones formed with the atomizer comprise concentric cones that intersect with one another over a predefined angular range; wherein, during a gas fuel operating mode of the engine, the selectable non-fuel fluid comprises water, which is conveyed by at least one of the first and second fluid circuits, and wherein at least one of the first and second ejection cones (34, 36) comprises a respective cone formed of atomized water, characterised in that a plurality of gas fuel channels are circumferentially disposed about the longitudinal axis of the lance, the plurality of gas fuel channels being positioned circumferentially outwardly relative to the annular lance, and that an angular range of the first atomized ejection cone extends from approximately 80 degrees to approximately 120 degrees and and that an angular range of the second atomized ejection cone extends from approximately 40 degrees to approximately 90 degrees.