Patent ID: 8661825

Claim:
A secondary fuel nozzle for a combustor of a gas turbine wherein the combustor provides a downstream combustion air flow within a fuel-air premixing space around the secondary fuel nozzle, the secondary fuel nozzle comprising: an elongated tube body with a fuel source end and a tip end; a unitary fuel injection manifold for premixing fuel with downstream combustion air flow, the fuel injection manifold being of a generally annual shape body shape within the elongated tube body and disposed between the fuel source end and the tip end, wherein the fuel injection manifold extends radially from internal to the elongated tube body to radially above and circumferentially fully around in a fuel-air premixing space external to the elongated tube body; a fuel passage from a fuel source end of the elongated tube body to a proximity of the fuel injection manifold supplying premixing fuel to the unitary fuel injection manifold; and a plurality of fuel channels for fluid communication of the premixing fuel providing fluid communication between the premixing fuel passage within the elongated tube body and a plurality of fuel discharge outlets on the outer surface of the unitary fuel injection manifold, wherein the plurality of fuel channels are circumferentially organized around the body of the fuel injection manifold.