Methods and apparatus for decreasing combustor emissions with swirl stabilized mixer
AssigneeGeneral Electric Company
InventorsArthur Wesley Johnson, Robert Andrew Wade, Hukam Chand Mongia, David Louis Burrus
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Abstract
A combustor for a gas turbine engine operates with high combustion efficiency, and low carbon monoxide and nitrous oxide emissions during low, intermediate, and high engine power operations. The combustor includes a fuel delivery system that includes at least two fuel stages, at least one trapped vortex cavity, and at least one mixer assembly radially inward from the trapped vortex cavity. The two fuel stages include a pilot fuel circuit that supplies fuel to the trapped vortex cavity through a fuel injector assembly and a main fuel circuit that also supplies fuel to the mixer assembly with the fuel injector assembly.
Claims14
A combustor for a gas turbine comprising:
- a fuel system comprising at least two fuel stages;
- at least one trapped vortex cavity, a first of said two fuel stages configured to supply fuel to said trapped vortex cavity;
- at least two mixer assemblies radially inward from said trapped vortex cavity, a second of said two fuel stages configured to supply fuel to said at least two mixer assemblies;
- a diffuser upstream from said at least two mixer assemblies.
A gas turbine engine comprising a combustor comprising a fuel system, a diffuser, at least one trapped vortex cavity, and a plurality of mixer assemblies downstream from said diffuser, said fuel system comprising at least a first stage and a second stage, said first stage configured to supply fuel to said trapped vortex cavity, said second stage configured to supply fuel to said plurality of mixer assemblies.
Dependencies are inferred from the claim text.