Patent ID: 8413443

Claim:
A resonator system for a turbine engine comprising: a combustor component having an outer peripheral surface and an inner peripheral surface, a first plurality of holes extending through the combustor component from the outer peripheral surface to the inner peripheral surface, the first plurality of holes being distributed circumferentially about the combustor component; a fluid flow within the combustor component, the fluid proximate to the inner peripheral surface of the combustor component having relatively hot regions alternating with relatively cold regions in the circumferential direction about the inner peripheral surface of the combustor component, and a first plurality of resonators formed with the combustor component, each resonator having a resonator plate and at least one side wall, the resonator plate including a plurality of holes therein, each resonator having an inner cavity defined between the resonator plate, the at least one side wall and the outer peripheral surface of the combustor component, the at least one sidewall of each resonator surrounding a subset of the first plurality of holes, the first plurality of resonators being substantially circumferentially aligned about the combustor component to form a first row of resonators, wherein a portion of the resonators are high flow resonators, wherein each high flow resonator is formed in a location that is substantially aligned with one of the relatively hot regions, wherein a portion of the resonators are low flow resonators, wherein each low flow resonator is formed in a location that is substantially aligned with one of the relatively cold regions, and wherein the first plurality of resonators are arranged so that there is a single high flow resonator associated with each hot region and a single low flow resonator associated with each cold region, whereby a single high flow resonator alternates with a single low flow resonator about the outer peripheral surface of the combustor component.