Abstract: Aspects of the invention are directed to an acoustic resonator with improved impingement cooling effectiveness. The resonator includes a plate with an inside face and an outside face. A plurality of passages extend through the plate. The resonator includes a side wall that extends from and about the plate. A plurality of cooling tubes are attached to the resonator plate such that an inner passage of each cooling tube is in fluid communication with a respective passage in the resonator plate. The resonator can be secured to a surface of a turbine engine combustor component to define a closed cavity. The ends of the cooling tubes are spaced from the surface. Thus, a coolant can enter the passages in the plate and can be directed to the surface so as to impingement cool the surface. The cooling tubes can minimize coolant loss by dispersion in the cavity.

Abstract: A gas turbine engine (120) includes a cylindrical basket (146) having an axis (14) and a single main burner assembly (12) disposed within the basket. A burner insert (34) is disposed in an annular space between the burner assembly and the basket. The insert includes a face perpendicular to the axis of the basket. A plurality of passageways (114) are formed in the basket, positioned proximate to and downstream of the burner insert for allowing passage of a portion of an oxidizer flow (42) into a combustion chamber (30). A fluid flow path (38), defined between a combustion chamber liner portion (32) of the basket and a casing (40) spaced radially outward from the combustion liner portion, discharges a fluid into a flow reversal region (118) proximate an inlet (20) of the burner assembly. A fuel outlet (44) is disposed in the flow reversal region.