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AssigneeGeneral Electric Company
InventorsAlfred A. Mancini, Michael L. Vermeersch, Duane D. Thomsen, Allen M. Danis, James N. Cooper, Steven J. Lohmueller, Hukam C. Mongia
Estimating the term…
A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.
A combustor for a gas turbine comprising:
A mixer assembly for a gas turbine engine combustor, said mixer assembly configured to control emissions from the combustor and comprising a pilot mixer, a main mixer, and an annular centerbody, said pilot mixer comprising a pilot fuel nozzle, and a plurality of axial swirlers upstream and radially outward from said pilot fuel nozzle, said main mixer radially outward from and concentric with respect to said pilot mixer, said main mixer comprising a plurality of fuel injection ports and a swirler upstream from said fuel injection ports, said centerbody extending between said main mixer and said pilot mixer and configured to direct flow exiting said pilot mixer into a pilot flame zone downstream from said pilot mixer.
Dependencies are inferred from the claim text.