Granted Patent B2

US 12,416,243 · App. 18/357,282 · Granted Sep 16, 2025

Inventors: Sajinu Nangariyil (Bengaluru, IN); Ravindra Shankar Ganiger (Bengaluru, IN); Abhilash Pillai (Bengaluru, IN); Adam Tomasz Pazinski (Warsaw, PL); David Raju Yamarthi (Bengaluru, IN)

Assignees: General Electric Company; General Electric Company Polska Sp. z o.o

F01D11/22F01D11/001F01D11/08F05D2220/323F05D2240/11F05D2240/55

Abstract

Claims (30)

1. 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, the magnet coupled to and positioned at least partially within the magnet base, and

a plate coupling the magnet base to the carrier or the seal segment,

wherein the magnet is configured for biasing the seal segment along the radial direction.

2. The turbine engine of claim 1 , wherein the magnet is a first magnet coupled to the carrier, and wherein the magnet assembly further comprises a second magnet coupled to the seal segment, and wherein the second magnet is in a magnetic field of the first magnet.

3. The turbine engine of claim 2 , wherein the magnet base is a first magnet base, the first magnet coupled to and positioned at least partially within the first magnet base, and wherein the seal support assembly includes a second magnet base with the second magnet coupled to and positioned at least partially within the second magnet base.

4. The turbine engine of claim 3 , wherein the first and second magnet bases are each formed of a non-ferromagnetic material.

5. The turbine engine of claim 3 , wherein the first magnet base is coupled to the carrier and wherein the second magnet base is coupled to the seal segment.

6. The turbine engine of claim 3 , wherein the first magnet base includes a first bumper and the second magnet base includes a second bumper disposed inward of the first bumper in 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.

7. The turbine engine of claim 3 , wherein the magnet assembly further comprises a non-ferromagnetic plate positioned between the first magnet and the second magnet.

8. The turbine engine of claim 7 , wherein the non-ferromagnetic plate is a first non-ferromagnetic plate coupled to the first magnet base over a surface of the first magnet facing the second magnet, and wherein the magnet assembly further comprises a second non-ferromagnetic plate coupled to the second magnet base over a surface of the second magnet facing the first magnet.

9. The turbine engine of claim 2 , wherein the first and second magnets form a magnetic attraction force.

10. The turbine engine of claim 2 , wherein the first and second magnets form a magnetic repelling force.

11. The turbine engine of claim 2 , wherein the first magnet comprises a first surface facing the second magnet, wherein the second magnet comprises a second surface facing the first magnet, and wherein the first surface has a non-planar geometry complementary to the second surface.

12. The turbine engine of claim 1 , wherein the seal support assembly further comprises a particle shield surrounding at least in part the magnet assembly.

13. The turbine engine of claim 12 , wherein the particle shield is a bellows assembly extendable along the radial direction and coupled to the carrier and the seal segment.

14. The turbine engine of claim 1 , wherein the magnet comprises a plurality of sections arranged linearly, and wherein each section defines a north pole facing in a unique direction relative to one or both adjacent sections.

15. The turbine engine of claim 1 , wherein the magnet is a permanent magnet.

16. The turbine engine of claim 15 , wherein the magnet defines a Curie temperature greater than 1200 degrees Celsius.

17. The turbine engine of claim 1 , further comprising:

a turbine, wherein the rotor is a turbine rotor of the turbine.

18. The turbine engine of claim 17 , wherein the seal assembly includes a high-pressure side and a low-pressure side, and wherein the high-pressure side is located forward of the low-pressure side.

19. The turbine engine of claim 17 , 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.

20. The turbine engine of claim 19 , further comprising:

a compressor, wherein the turbine and the compressor together define in part a working gas flowpath of the turbine engine, and wherein the outer pressurization surface is in airflow communication with the working gas flowpath.

Assignments (2)

Priority Claims (1)

Continuity (1)

References Cited (176)