Gas turbine engine defining a rotor cavity

A gas turbine engine defining a longitudinal centerline, a radial direction perpendicular to the longitudinal centerline, a circumferential direction around the longitudinal centerline, and an axial direction in line with the longitudinal centerline, the gas turbine engine comprising:

• a compressor section comprising a compressor, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, the compressor comprising an aft-most compressor stage;
• a stage of stator vanes located downstream of the aft-most compressor stage;
• a stator case coupled to the stage of stator vanes inward of the stage of stator vanes along the radial direction, the stator case including a seal pad;
• and
• a spool drivingly coupled to the compressor, the spool and the stator case together defining a rotor cavity in fluid communication with the working gas flowpath, the spool comprising a seal tooth assembly, the seal tooth assembly comprising:
• a seal support extension;
• a seal tooth extending from the seal support extension toward the seal pad;
• and
• a dampener coupled to and extending from with the seal support extension,
• wherein the spool further comprises a rotor arm extending at least partially along the radial direction, and wherein the seal tooth assembly is formed separately from the rotor arm and coupled to the rotor arm.