Seal support assembly for a turbine engine
AssigneesGeneral Electric Company, General Electric Company Polska sp. z o.o.
InventorsSajinu Nangariyil, Ravindra Shankar Ganiger, Abhilash Pillai, Adam Tomasz Pazinski, David Raju Yamarthi
Life of this patent
Estimating the term…
Abstract
A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly including a magnet assembly having a magnet coupled to the carrier or the seal segment for biasing the first seal segment along the radial direction.
Claims20
A turbine engine defining a radial direction, comprising:
- a rotor;
- a stator comprising a carrier;
- a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment having a seal face configured to form a fluid bearing with the rotor;
- and
- a seal support assembly including a magnet assembly having:
- a magnet;
- a magnet base defining a radial wall, the magnet coupled to and positioned at least partially within the magnet base;
- and
- a bumper disposed on the radial wall of the magnet base, the bumper being spaced from the magnet in the radial direction
- wherein the magnet is configured for biasing the seal segment along the radial direction,
- wherein the seal support assembly further comprises a particle shield surrounding at least in part the magnet assembly.
A turbine engine defining a radial direction, comprising:
- a rotor;
- a stator comprising a carrier;
- a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment having a seal face configured to form a fluid bearing with the rotor;
- and
- a seal support assembly including a magnet assembly having:
- a first magnet coupled to the carrier;
- a second magnet coupled to the seal segment, wherein the second magnet is in a magnetic field of the first magnet;
- a first magnet base defining a radial wall, the first magnet coupled to and positioned at least partially within the first magnet base;
- a second magnet base, the second magnet coupled to and positioned at least partially within the second magnet base;
- a first bumper disposed on the radial wall of the first magnet base, the first bumper being spaced from the first magnet in the radial direction;
- and
- a second bumper disposed inward of the first bumper in the radial direction,
- wherein the first magnet is configured for biasing the seal segment along the radial direction,
- wherein the first bumper and the second bumper are configured to contact to prevent the first magnet from contacting the second magnet in the radial direction.
A turbine engine defining a radial direction, comprising a turbine, the turbine comprising:
- a turbine rotor;
- a stator comprising a carrier;
- a seal assembly disposed between the turbine rotor and the stator, the seal assembly comprising a seal segment having a seal face configured to form a fluid bearing with the rotor;
- and
- a seal support assembly including a magnet assembly having:
- a magnet;
- a magnet base defining a radial wall, the magnet coupled to and positioned at least partially within the magnet base;
- and
- a bumper disposed on the radial wall of the magnet base, the bumper being spaced from the magnet in the radial direction
- wherein the magnet is configured for biasing the seal segment along the radial direction,
- wherein the seal assembly includes a high-pressure side and a low-pressure side, wherein the seal segment includes a lip and a body, wherein the lip extends from the body along an axial direction of the turbine engine on the high-pressure side, and wherein the lip includes an outer pressurization surface along the radial direction of the turbine engine.
Dependencies are inferred from the claim text.