Patent ID: 7076956

Claim:
A gas turbine engine combustion section, comprising an annular region defined by a combustion chamber inner casing and a combustion chamber outer casing; a combustion chamber located in the annular region and comprising at least one Helmholtz resonator having a cavity and a damping tube in flow communication with the interior of the combustion chamber, wherein the damping tube extends into the interior of the combustion chamber, and the at least one Helmholtz resonator is supported independently of the combustion chamber by the combustion chamber inner casing, and the at least one Helmholtz resonator is supported by the combustion chamber inner casing with the at least one Helmholtz resonator positioned on the radially inner side of the combustion chamber and enclosed within a cavity provided between the combustion chamber inner casing and a windage shield on a radially inner side of the casing.