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A method for decreasing combustor acoustics in gas turbine engines is provided. The method includes fabricating a plurality of premixers, chamfering a trailing edge of a main swirler shroud of each premixer, coupling a respective one of the chamfered premixers to each of a plurality of combustor dom

A method for decreasing combustor acoustics in gas turbine engines is provided. The method includes fabricating a plurality of premixers, chamfering a trailing edge of a main swirler shroud of each premixer, coupling a respective one of the chamfered premixers to each of a plurality of combustor domes, and coupling the plurality of combustor domes to an inlet of a combustor in a circumferential arrangement such that, during operation, the chamfered edge facilitates reducing combustor acoustics.

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What is claimed is: 1. A method for assembling a combustor in gas turbine engines comprising: providing a plurality of premixers that include a main swirler including a plurality of main swirler vanes; coupling a deflector plate to each premixer, such that the deflector plate is positioned downstre

What is claimed is: 1. A method for assembling a combustor in gas turbine engines comprising: providing a plurality of premixers that include a main swirler including a plurality of main swirler vanes; coupling a deflector plate to each premixer, such that the deflector plate is positioned downstream from the plurality of main swirler vanes; chamfering a trailing edge of the main swirler shroud of each premixer, wherein the chamfered trailing edge is positioned downstream with respect to a centerline of the gas turbine engine, from the plurality of main swirler vanes and upstream from the deflector plate with respect to the centerline; coupling a respective one of the chamfered premixers to each of a plurality of combustor domes; and coupling the plurality of combustor domes to an inlet of a combustor in a circumferential arrangement such that, during operation, the chamfered edge facilitates reducing combustor acoustics. 2. A method in accordance with claim 1 wherein chamfering a trailing edge of the main swirler shroud comprises chamfering a trailing edge of the main swirler shroud at an angle determined to suppress coupling of a vortex shedding at an outlet of said main swirler shroud with acoustic vibrations in the combustor. 3. A method in accordance with claim 2 wherein chamfering a trailing edge of the main swirler shroud at an angle determined to suppress a vortex shedding comprises chamfering a trailing edge of the main swirler shroud at an angle of approximately forty-five degrees relative to an inner surface of the main swirler shroud. 4. A method in accordance with claim 1 wherein providing a plurality of premixers comprises providing a plurality of dry low emission (DLE) premixers. 5. A fuel delivery apparatus for a dry low emission (DLE) combustor for a gas turbine engine comprising: a plurality of combustor domes circumferentially arranged and coupled to a combustor inlet; and a premixer coupled to a respective one of each of said plurality of domes, each said premixer comprising: a main swirler comprising a plurality of main swirler vanes; a deflector plate that is positioned downstream from said plurality of main swirler vanes; and a chamfered trailing edge defined on a main swirler shroud and positioned downstream with respect to a centerline of the gas turbine engine, from said plurality of main swirler vanes and upstream from said deflector plate with respect to the centerline, said chamfered trailing edge is configured to suppress coupling of a vortex shedding with acoustic vibrations in the combustor. 6. A fuel delivery apparatus in accordance with claim 5 wherein each said premixer further comprises a main swirler shroud and said chamfered trailing edge is positioned on said main swirler shroud. 7. A fuel delivery apparatus in accordance with claim 6 wherein said main swirler shroud includes an inner surface and said chamfered trailing edge is located at an aft end of said inner surface. 8. A fuel delivery apparatus in accordance with claim 7 wherein said chamfered trailing edge is formed at an angle of approximately forty-five degrees relative to said inner surface of said main swirler shroud. 9. A fuel delivery apparatus in accordance with claim 7 wherein said main swirler shroud further comprises a rounded transition corner joining said chamfered trailing edge to said inner surface. 10. A fuel delivery apparatus in accordance with claim 6 wherein said chamfered trailing edge is angled to facilitate altering a local pressure distribution within said main swirler shroud. 11. A fuel delivery apparatus in accordance with claim 5 wherein each said premixer comprises a dry low emission (DLE) premixer. 12. A gas turbine engine comprising: a combustor; and a fuel delivery system coupled to said combustor, said fuel delivery system comprising: a plurality of combustor domes circumferentially arranged and coupled to an inlet of said combustor; and a premixer coupled to a respective one of each of said plurality of domes, each said premixer comprising: a main swirler comprising a plurality of main swirler vanes; a deflector plate that is positioned downstream from said plurality of main swirler vanes; and a chamfered trailing edge defined on a main swirler shroud and positioned downstream with respect to a centerline of said gas turbine engine, from said plurality of main swirler vanes and upstream from said deflector plate with respect to the centerline, said chamfered trailing edge is configured to suppress coupling of a vortex shedding with acoustic vibrations in the combustor. 13. A gas turbine engine in accordance with claim 12 wherein each said premixer further comprises a main swirler shroud and said chamfered trailing edge is positioned on said main swirler shroud. 14. A gas turbine engine in accordance with claim 13 wherein said chamfered trailing edge is angled to facilitate altering a local pressure distribution within said main swirler shroud. 15. A gas turbine engine in accordance with claim 13 wherein said main swirler shroud includes an inner surface and said chamfered trailing edge is located at an aft end of said inner surface. 16. A gas turbine engine in accordance with claim 15 wherein said chamfered trailing edge is formed at an angle of approximately forty-five degrees measured relative to said inner surface of said main swirler shroud. 17. A gas turbine engine in accordance with claim 15 wherein said main swirler shroud further comprises a rounded transition corner joining said chamfered trailing edge to said inner surface. 18. A gas turbine engine in accordance with claim 12 wherein each said premixer comprises a dry low emission (DLE) premixer.