Gas turbine engine defining a rotor cavity

1 . 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 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;

wherein the seal support extension includes a first flange and a second flange, wherein the rotor arm includes a first bracket defining a first gap and a second bracket defining a second gap, and wherein the first flange is positioned in the first gap and the second flange is positioned within the second gap.

2 . The gas turbine engine of claim 1 , wherein the dampener is configured as a seal ring positioned on an inner side of the seal support extension along the radial direction.

3 . The gas turbine engine of claim 2 , wherein the seal ring is a piston ring configured to bias the seal support extension outwardly along the radial direction.

4 . The gas turbine engine of claim 3 , wherein the piston ring defines an overlap joint configured to overlap when elastically deformed.

5 . The gas turbine engine of claim 2 , wherein the rotor arm comprises a housing, and wherein the seal ring is positioned at least partially within the housing to form a fluid seal between the housing and the seal support extension.

6 . The gas turbine engine of claim 1 , wherein the second bracket is a two-piece construction including a first member formed integrally with the rotor arm and a second member coupled to the first member with a mechanical fastener.

7 . The gas turbine engine of claim 6 , wherein the second gap is defined by the second member.

8 . The gas turbine engine of claim 6 , wherein the second member is positioned at least partially outward of the first member in the radial direction.

9 . The gas turbine engine of claim 1 , wherein the rotor arm is part of the spool which is a high pressure spool.

10 . 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 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;

wherein the dampener is configured as a seal ring positioned on an inner side of the seal support extension along the radial direction;

wherein the rotor arm comprises a housing, and wherein the seal ring is positioned at least partially within the housing to form a fluid seal between the housing and the seal support extension.