Patent ID: 7334408

Claim:
A combustion chamber for a gas turbine, formed of an outer combustion chamber wall and an inner combustion chamber wall, including a path for carrying a cooling fluid that flows between the inner and outer combustion chamber walls and has different pressure regions, the chamber also comprising: a first acoustic resonator device connected to a portion of the inner combustion chamber wall having a first resonance frequency, the first device including one or more first flow inlets and two or more first flow outlets; a second acoustic resonator device connected to a portion of the inner combustion chamber wall having a second resonance frequency, the second device including one or more second flow inlets and one or more second flow outlets, wherein a structure serves as both a first flow outlet of the first device and a second flow inlet of the second device so that at least one second flow inlet is positioned to receive fluid having passed through the first device, and wherein at least one second flow outlet of the second acoustic resonator device is positioned to pass cooling fluid into the combustion chamber, wherein cooling fluid at a first pressure flows into the first acoustic resonator device through at least one first flow inlet and out of the first acoustic resonator device through at least one of the first flow outlets, and wherein; cooling fluid at a second pressure flows directly from the at least one first flow outlet into the second acoustic resonator device through the second flow inlet and out of the second acoustic resonator device through the second flow outlet; and a second of the first flow outlets of the first acoustic resonator device is positioned to pass cooling fluid directly into the combustion chamber without first passing through another acoustic resonator device thereby providing at least two parallel flow paths.