a dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed . the dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture . the premix fuel nozzle includes a plurality of coaxial passages , which provide gaseous fuel and compressed air to the fin assembly . when in liquid fuel operation , the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle , where they inject liquid fuel and water into the secondary combustion chamber . an alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle , downstream of the fin assembly . a second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly and simplify fuel nozzle manufacturing .