Non-uniform mixer for combustion dynamics attenuation
AssigneeGeneral Electric Company
InventorsHejie Li, David Louis Burrus, Arvind Kumar Rao, Sreejith Keloth
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Abstract
The present disclosure is directed to a combustor assembly for a gas turbine engine comprising a fuel nozzle and an annular shroud. The fuel nozzle comprises a centerbody extended along a lengthwise direction. The fuel nozzle defines a nozzle centerline extended through the centerbody of the fuel nozzle along the lengthwise direction. The fuel nozzle defines a plurality of exit openings in circumferential arrangement on the centerbody relative to the nozzle centerline. The annular shroud surrounds the centerbody of the fuel nozzle. At least a portion of the shroud defines a contoured structure defining a waveform.
Claims20
A combustor assembly for a gas turbine engine, the combustor assembly comprising:
- a fuel nozzle comprising a centerbody extended along a lengthwise direction, wherein the fuel nozzle defines a nozzle centerline extended through the centerbody of the fuel nozzle along the lengthwise direction, the fuel nozzle defining a plurality of exit openings in circumferential arrangement on the centerbody relative to the nozzle centerline;
- an annular shroud surrounding the centerbody of the fuel nozzle, wherein at least a portion of the shroud defines a contoured structure defining a waveform.
A gas turbine engine defining an axial centerline, a radial direction extended therefrom, and a circumferential direction around the axial centerline, the gas turbine engine comprising:
- a combustor assembly disposed generally concentric to the axial centerline of the gas turbine engine, the combustor assembly comprising a plurality of fuel nozzles disposed in circumferential arrangement around the axial centerline, wherein each fuel nozzle comprises a centerbody extended along a lengthwise direction and defining a nozzle centerline therethrough, and wherein an annular shroud is defined around the centerbody, and wherein at least a portion of the shroud defines a contoured structure defining a waveform, and wherein each fuel nozzle defines a plurality of exit openings in circumferential arrangement on the centerbody relative to the nozzle centerline.
Dependencies are inferred from the claim text.