Patent ID: 7360363

Claim:
A premixing nozzle for a gas turbine combustor, comprising: a swirler blade positioned inside a nozzle body; a tube-shaped hub that is connected to the swirler blade, wherein a combustion gas is passed through a hollow portion of the hub; a fuel nozzle shaft that is located inside the nozzle body and that is coaxial with the hub, wherein the fuel nozzle shaft is configured to have a tip portion which is tapered toward a tip of the fuel nozzle shaft and arranged inside the hub having a gap larger than 3 mm between the fuel nozzle shaft and the hub; and hollow gas fuel supply blades fitted in the upstream of the fuel nozzle shaft, wherein gas fuel is configured to be injected from a plurality of gas fuel supply holes provided on the sides of the gas fuel supply blades, to thereby form a combustion gas as a mixed gas of the gas fuel and combustion air.