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 including:
• a seal support extension,
• a seal tooth extending from the seal support extension toward the seal pad,
• a base extension extending substantially parallel to the seal support extension,
• a first dampener coupled to and extending from the seal support extension in the radial direction toward the longitudinal centerline, and
• a second dampener coupled to and extending from the base extension in the radial direction away from the longitudinal centerline,
• wherein the first dampener and the second dampener are movable from a first position in which the first dampener and the second dampener are spaced from each other to a second position wherein the first dampener contacts the second dampener.