Main fuel nozzle for combustion dynamics attenuation
AssigneeGeneral Electric Company
InventorsHejie Li, Duane Douglas Thomsen
Life of this patent
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Abstract
The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a fuel nozzle comprising a centerbody extended along a lengthwise direction, wherein the fuel nozzle defines a nozzle centerline extended through the centerbody along the lengthwise direction. The centerbody defines a plurality of exit openings in circumferential arrangement relative to the nozzle centerline. The plurality of exit openings defines two or more locations different from one another on the centerbody along the lengthwise direction.
Claims20
A combustor assembly for a gas turbine engine, the combustor assembly defining a combustor centerline and a radial direction extended from the combustor centerline, the radial direction and combustor centerline together defining a reference plane, 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 along the lengthwise direction, the centerbody defining a plurality of exit openings in circumferential arrangement relative to the nozzle centerline, the plurality of exit openings defining two or more locations different from one another on the centerbody along the lengthwise direction.
A gas turbine engine defining an axial centerline and a radial direction extended from the axial centerline, the radial direction and axial centerline together defining a reference plane, the gas turbine engine comprising:
- a combustor assembly comprising a plurality of fuel nozzles disposed in circumferential arrangement around the axial centerline of the gas turbine engine, wherein each fuel nozzle comprises a centerbody extended along a lengthwise direction, and wherein the fuel nozzle defines a nozzle centerline extended through the centerbody along the lengthwise direction, the centerbody defining a plurality of exit openings in circumferential arrangement relative to the nozzle centerline, the plurality of exit openings defining two or more cross sectional areas different from one another on the centerbody.
Dependencies are inferred from the claim text.