Gas turbine engine defining a rotor cavity
AssigneeGeneral Electric Company
InventorNarendra Anand Hardikar
Life of this patent
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Abstract
A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining a working gas flowpath, a compressor of the compressor section comprising an aft-most compressor stage; a stage of stator vanes located downstream of the aft-most compressor stage; a 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, and a dampener operable with the seal support extension.
Claims10
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.
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.
Dependencies are inferred from the claim text.