Patent ID: 8091363

Claim:
A fuel nozzle for a gas turbine combustor comprising: a centerbody extending along a nozzle axis having a first end, a second end located opposite the first end, and a first opening extending from the first end through the centerbody to a plenum; a plurality of swirlers positioned adjacent the second end and extending radially outward from the centerbody, the swirlers oriented at an angle relative to the nozzle axis; an outer shroud extending from the centerbody to the second end and radially encompassing the plurality of swirlers, and wherein the outer shroud has a plurality of slots located therein that are in fluid communication with a passageway formed between the outer shroud and the centerbody; and a plurality of second openings located in the centerbody adjacent to the plurality of swirlers; wherein fuel passes through the first opening to the plenum and air passes through the passageway such that the air is separate from the fuel until the fuel and air are mixed upon exiting the fuel nozzle at the second end of the fuel nozzle.