Patent ID: 7340900

Claim:
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.