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An end cap for a fuel injector of a turbine engine is disclosed. The end cap includes an annular first surface including a plurality of perforations. The annular first surface is exposed to a combustion chamber of the turbine engine. The end cap is coupled to an end face of the fuel injector to defi

An end cap for a fuel injector of a turbine engine is disclosed. The end cap includes an annular first surface including a plurality of perforations. The annular first surface is exposed to a combustion chamber of the turbine engine. The end cap is coupled to an end face of the fuel injector to define an enclosed cavity. The enclosed cavity and the plurality of perforations form an array of Helmholtz resonators.

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1. A fuel injector for a turbine engine comprising: a body member, including a pilot injector, extending along a longitudinal axis, the pilot injector being configured to direct a stream of fuel into a combustion chamber of the turbine engine;a barrel member located radially outwards from the body m

1. A fuel injector for a turbine engine comprising: a body member, including a pilot injector, extending along a longitudinal axis, the pilot injector being configured to direct a stream of fuel into a combustion chamber of the turbine engine;a barrel member located radially outwards from the body member, to define an annular duct therebetween, the fuel injector being adapted to direct a stream of fuel air mixture, separate from the stream of fuel from the pilot injector, into the combustion chamber through the annular duct, the barrel member including an end face facing the combustion chamber; andan end cap coupled to the barrel member, wherein the end cap and the end face form an array of Helmholtz resonators. 2. The fuel injector of claim 1, wherein each resonator in the array of Helmholtz resonators includes a perforation exposed to the combustion chamber and an angular spacing between any two adjacent perforations is substantially the same. 3. The fuel injector of claim 2, wherein the angular spacing is between about 2 degrees and about 45 degrees. 4. The fuel injector of claim 2, wherein the longitudinal axis is substantially parallel to a central axis of each perforation. 5. The fuel injector of claim 2, wherein a diameter of each perforation is substantially the same and is between about 0.005 inches and about 0.5 inches. 6. The fuel injector of claim 2, wherein the array of Helmholtz resonators include an enclosed cavity fluidly communicating with the combustion chamber through the perforations. 7. The fuel injector of claim 6, wherein a cross sectional width of the cavity is between about 0.05 inches and about 0.5 inches and a cross sectional height of the cavity is between about 0.05 inches and about 1 inch. 8. The fuel injector of claim 6, wherein the end face includes one or more vent holes configured to admit air into the enclosed cavity. 9. The fuel injector of claim 1, wherein the end cap forms an annular ring around the longitudinal axis. 10. The fuel injector of claim 9, wherein an outer diameter of the end-cap is between about 1 inch and about 6 inches and an inner diameter of the end cap is between about 0.5 inches and about 5 inches. 11. A component for a fuel injector configured to direct a stream of fuel and a separate stream of fuel air mixture to a combustion chamber of a turbine engine, comprising: a longitudinal axis;a barrel member coupled to the combustion chamber and disposed radially outwards the longitudinal axis, the barrel member including an end face facing the combustion chamber; andan end cap coupled to the barrel member, wherein the end cap and the end face form an array of Helmholtz resonators, the array of Helmholtz resonators includes a plurality of perforations exposed to the combustion chamber, and each of the plurality of perforations includes a central axis substantially parallel to the longitudinal axis. 12. The component of claim 11, wherein the plurality of perforations are located in the end cap and the end face includes a second plurality of perforations, each of the second plurality of perforations having an axis substantially parallel to the central axis. 13. The component of claim 11, wherein the plurality of perforations are annularly located around the longitudinal axis and the angular spacing between any two adjacent perforations of the plurality of perforations is substantially a constant. 14. The component of claim 11, wherein each perforation of the plurality of perforations has a diameter between about 0.05 inches and about 0.06 inches. 15. A fuel injector configured to deliver a premixed fuel air mixture to a combustor of a gas turbine engine, comprising: a central body formed around a common axis and containing a pilot injector, the pilot injector configured to inject a first stream of fuel out of a first axial end into the combustor;a barrel housing positioned around the central body to form an annular mixing duct there between, the mixing duct being configured to mix a second stream of fuel and air therein to create the premixed fuel air mixture, and deliver the premixed fuel air mixture to the combustor through the first axial end without mixing with the first stream of fuel;a ring-shaped end cap coupled to the barrel housing at the first axial end to form an array of Helmholtz resonators with a hollow cavity between the end cap and the barrel housing, the array of Helmholtz resonators being annularly positioned about the common axis; and,a plurality of perforations formed in the end cap and arranged in a radial pattern about the common axis, the perforations penetrating through the end cap to fluidly communicate the hollow cavity with the combustor, the perforations each defining an axis that is parallel to the common axis. 16. The fuel injector of claim 15 wherein the end cap is generally C-shaped in cross section and includes a third-element and a fifth element that are ring-shaped and revolved around the common axis with the third element being diametrically larger than and radially spaced from the fifth element, and a fourth element circumferentially spanning between and joining the third element and the fifth element, the plurality of perforations being formed through the fourth element. 17. The fuel injector of claim 16 wherein the barrel housing includes an end face at the first end, the end face comprising at least a second element that is ring-shaped and revolved around the common axis and extends axially away from the barrel housing, the second element being diametrically smaller than the fifth element of the end cap, the second element and the fifth element being joined together. 18. The fuel injector of claim 17 wherein the second element and the fifth element are brazed together. 19. The fuel injector of claim 17 wherein the end face further comprises a first element that extends radially outward from the barrel housing and is formed around the common axis and abuts the third element of the end cap, the first element and the second element of the end face making the end face L-shaped in cross section. 20. The fuel injector of claim 19, wherein the first element includes a plurality of purge holes formed there through, the purge holes being configured to permit compressed air from a compressor section of the gas turbine engine to enter the hollow cavity and eventually flow out into the combustor through the perforations. 21. The fuel injector of claim 15 wherein the perforations formed through the end cap are arranged in a single row circumferentially around the opening into the combustor, and the perforations are uniformly spaced from one another. 22. The fuel injector of claim 21, wherein each perforation of the plurality of perforations has a diameter between about 0.05 inches and about 0.06 inches. 23. The fuel injector of claim 21, wherein an angular spacing between two adjacent perforations of the plurality of perforations is between about 2 degrees and about 45 degrees.