To securely restrict production of NOx by providing a fuel nozzle part for injecting a fuel as a turning flow and a fuel atomization nozzle part for providing a turning flow toward the injected fuel and atomizing it on at least one of a pilot fuel nozzle and a main fuel nozzle.
A gas turbine combustor includes a pilot fuel nozzle provided upstream a combustor liner, and a plurality of main fuel nozzles 8 provided on the outer peripheral side of the former for injecting a main fuel to form a premixing combustion part. The main fuel nozzle 8 comprises a fuel nozzle part 24 and a fuel atomization nozzle part 25. The fuel nozzle part 24 pressure- injects a fuel supplied from a fuel header through a fuel piping 22 as a turning flow. The fuel atomization nozzle part 25 is coaxially disposed on the outer peripheral side of the fuel nozzle part 24 for injecting a fluid such as air a gas fuel to an outlet of the fuel nozzle part 24 as a turning flow whereby the fuel is atomized and is sprayed into a premixing duct.
OKAMOTO YASUO
MAEDA FUKUO
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