Turbine engine having a multicavity damper

A gas turbine engine comprising:

• a compressor section for compressing air flowing therethrough to provide a compressed air flow;
• a combustor including a combustion chamber, the combustion chamber configured to combust a mixture of a fuel flow and the compressed air flow to generate combustion products, the combustion products producing an instability in the combustion chamber, the instability having at least one frequency;
• a turbine section having at least one turbine driven by the combustion products;
• and
• a multicavity damper in fluid communication with the combustion chamber to damp the instability generated by the combustion products in the combustion chamber, the multicavity damper having an axial direction and including:
• a bottom surface fluidly connected to the combustion chamber;
• a top surface opposite the bottom surface, the top surface having a first top surface and a second top surface, the first top surface located between the second top surface and the bottom surface in the axial direction;
• a cylindrical surface extending from the bottom surface to the top surface in the axial direction;
• a first inner wall extending in the axial direction from the bottom surface, the top surface, or both the bottom surface and the top surface;
• and
• a second inner wall positioned at the first top surface and extending from the first inner wall to the cylindrical surface,
• wherein the bottom surface, the cylindrical surface, the first inner wall and the second inner wall define a first cavity volume therebetween, the first cavity volume having a first cavity volume length, and the bottom surface, the second top surface, the cylindrical surface, and the first inner wall define a second cavity volume therebetween, the second cavity volume having a second cavity volume length that is different from the first cavity volume length, wherein the first cavity volume and the second cavity volume together define a main damper cavity.