Aerodynamic Fuel Nozzle
AssigneeGeneral Electric Company
InventorJoel Meier Haynes
Life of this patent
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Abstract
The present application and the resultant patent provide a combustor for a turbine engine. The combustor may include a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly. The swirler assembly may include a number of stages with a number of fueled structures and a number of unfueled structures.
Claims20
A combustor for a turbine engine, comprising:
- a plurality of fuel nozzles;
- and
- one or more of the plurality of fuel nozzles comprising a swirler assembly;
- wherein the swirler assembly comprises a plurality of stages;
- and
- wherein the plurality of stages comprises a plurality of fueled structures and a plurality of unfueled structures.
The combustor of claim her comprising a primary recirculation zone about the plurality of fuel nozzles and a secondary recirculation zone downstream of the plurality of fuel nozzles.
A method of operating a combustor for late lean injection, comprising:
- providing a flow of air to a fuel nozzle;
- providing a flow of fuel through one or more fueled structures of a swirler assembly;
- swirling the flow of air and the flow of fuel through multiple stages of the swirler assembly;
- establishing a primary recirculation zone about the fuel nozzle for low emissions;
- and
- establishing a secondary recirculation zone downstream of the fuel nozzle for high temperatures.
A swirler assembly for use with a combustor, comprising:
- a plurality of stages;
- a plurality of vanes;
- and
- a plurality of blocks;
- wherein each of the plurality of stages comprises one or more of the plurality of vanes and/or one more of the plurality of blocks.
Dependencies are inferred from the claim text.