Mixer assembly for gas turbine engine combustor
AssigneeGeneral Electric Company
InventorsSteven Clayton Vise, Clayton Stuart Cooper, Michael Anthony Benjamin, Hiranya Kumar Nath, Rameshkumar Muthuvel Chandrasekaran
Life of this patent
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Abstract
A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.
Claims19
A mixer assembly, comprising:
- a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist;
- wherein each of the plurality of mixer vanes has a three-dimensional shape defined by the length, the width, the thickness, the cross-sectional area, the curvature, and the twist of the body portion;
- and
- wherein at least one of the plurality of mixer vanes has a non-uniform three-dimensional shape from the first end to the second end such that at least one of the width, the thickness, the cross-sectional area, the curvature, or the twist of the body portion varies between the first and the second end, and
- wherein the plurality of mixer vanes are joined at their respective first ends to a first annular ring and are joined at their respective second ends to a second annular ring.
A fuel nozzle assembly comprising:
- an annular pilot fuel injector defining a nozzle axis and an axial direction, a radial direction normal to the axial direction, and a circumferential direction normal to both the axial direction and the radial direction and extending around a circumference of the annular pilot fuel injector, the annular pilot fuel injector further having a plurality of primary mixer vanes circumferentially distributed about the nozzle axis and a plurality of secondary mixer vanes located radially outwardly of the primary mixer vanes;
- and
- an annular main fuel injector surrounding and concentric with the annular pilot fuel injector and having a plurality of main mixer vanes circumferentially distributed about the nozzle axis;
- and
- each of the plurality of primary mixer vanes, the plurality of secondary mixer vanes, and the plurality of main mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist;
- wherein each of the plurality of primary mixer vanes, the plurality of secondary mixer vanes, and the plurality of main mixer vanes has a three-dimensional shape defined by the length, the width, the thickness, the cross-sectional area, the curvature, and the twist of the body portion;
- and
- wherein at least one of the plurality of primary mixer vanes, the plurality of secondary mixer vanes, or the plurality of main mixer vanes has a non-uniform three-dimensional shape from the first end to the second end such that at least one of the width, the thickness, the cross-sectional area, the curvature, or the twist of the body portion varies between the first and the second end.
Dependencies are inferred from the claim text.