초록 ▼

A method for fabricating a fuel nozzle assembly includes providing a nozzle portion including a fuel passageway defined about a center axis of the fuel nozzle assembly. A longitudinal axis of a first peg is oriented to intersect the fuel nozzle assembly center axis such that a first plane is defined

A method for fabricating a fuel nozzle assembly includes providing a nozzle portion including a fuel passageway defined about a center axis of the fuel nozzle assembly. A longitudinal axis of a first peg is oriented to intersect the fuel nozzle assembly center axis such that a first plane is defined. The first peg defines a first opening having a centerline intersecting the first peg longitudinal axis and obliquely oriented with respect to the first plane. The first peg is coupled in flow communication with the fuel passageway such that the first peg extends radially outward from the nozzle portion and such that the first opening is configured to direct a flow of fuel in an oblique direction with respect to the fuel nozzle assembly center axis to facilitate fuel mixing.

대표청구항 ▼

What is claimed is: 1. A secondary fuel nozzle assembly comprising: a nozzle portion comprising a fuel passageway defined about a center axis of the secondary fuel nozzle assembly; and at least one peg extending radially outward from said nozzle portion, a longitudinal axis of a first peg of said a

What is claimed is: 1. A secondary fuel nozzle assembly comprising: a nozzle portion comprising a fuel passageway defined about a center axis of the secondary fuel nozzle assembly; and at least one peg extending radially outward from said nozzle portion, a longitudinal axis of a first peg of said at least one peg intersecting the secondary fuel nozzle assembly center axis to define a first plane, said first peg defining a first opening having a centerline intersecting the first peg longitudinal axis, the centerline of said first opening obliquely oriented with respect to the first plane at a first angle and configured to discharge fuel therefrom in a direction that is oblique with respect to the secondary fuel nozzle assembly center axis to facilitate fuel mixing, said first peg further defines a second opening having a centerline oriented with respect to the first plane at a second angle that is different than the first angle. 2. A secondary fuel nozzle assembly in accordance with claim 1 wherein the longitudinal axis of said first peg is oriented orthogonal to the secondary fuel nozzle assembly center axis. 3. A secondary fuel nozzle assembly in accordance with claim 1 wherein the first opening centerline is oriented orthogonal to the first peg longitudinal axis. 4. A secondary fuel nozzle assembly in accordance with claim 1 wherein said first opening is oriented such that the centerline is at the first angle of about 5° to about 135° with respect to the secondary fuel nozzle assembly center axis. 5. A secondary fuel nozzle assembly in accordance with claim 1 wherein said first opening is oriented such that the centerline is at the first angle of about 5° to about 90° with respect to the secondary fuel nozzle assembly center axis. 6. A secondary fuel nozzle assembly in accordance with claim 1 wherein said first opening is oriented such that the centerline is at the first angle of about 30° to about 60° with respect to the secondary fuel nozzle assembly center axis. 7. A secondary fuel nozzle assembly in accordance with claim 1 further comprising a second peg of said at least one peg, a longitudinal axis of said second peg intersecting the secondary fuel nozzle assembly center axis to define a second plane, said second peg defining a first opening having a centerline intersecting the second peg longitudinal axis, the centerline of said second peg first opening obliquely oriented with respect to the second plane at a second angle. 8. A secondary fuel nozzle assembly in accordance with claim 7 wherein the second angle is less than the first angle. 9. A combustor assembly for use with a gas turbine engine, said combustor assembly comprising: a combustor liner defining a primary combustion zone and a secondary combustion zone, said combustor liner configured to direct a flow of combustion gases substantially in a downstream direction; a primary fuel nozzle assembly extending into said primary combustion zone; and a secondary fuel nozzle assembly extending through said primary combustion zone and into said secondary combustion zone, said secondary fuel nozzle assembly comprising: a nozzle portion comprising a fuel passageway defined about a center axis of the secondary fuel nozzle assembly; and at least one peg extending radially outward from said nozzle portion, a longitudinal axis of a first peg of said at least one peg intersecting the secondary fuel nozzle assembly center axis to define a first plane, said first peg defining a first opening having a centerline intersecting the first peg longitudinal axis, the centerline of said first opening obliquely oriented with respect to the first plane at a first angle, said first opening configured to discharge fuel in a direction that is oblique with respect to the secondary fuel nozzle assembly center axis to facilitate fuel mixing, said first peg further defines a second opening having a centerline oriented with respect to the first plane at a second angle that is different than the first angle.