Patent ID: 8720204

Claim:
A resonator system for a turbine engine comprising: a hollow combustor component having an outer peripheral surface and an inner peripheral surface, a first plurality of holes extending substantially radially through the combustor component from the inner peripheral surface to the outer peripheral surface, the first plurality of holes being distributed circumferentially about the combustor component; a first plurality of resonators formed with the combustor component, each resonator having a radially outer wall and at least one side wall, each resonator having an inner cavity defined between the radially outer wall, the at least one side wall and the combustor component, the at least one side wall 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; and a first plurality of cooling passages extending generally longitudinally within the combustor component, each of the first plurality of cooling passages having an inlet in fluid communication with the exterior of the combustor component and an outlet in fluid communication with the inner cavity of a respective one of the resonators.