Granted Patent B2

US 12,241,375 · App. 18/189,379 · Granted Mar 4, 2025

Inventors: Ravindra Shankar Ganiger (Bengaluru, IN); David Raju Yamarthi (Bengaluru, IN); Chandrashekhar Kandukuri (Bengaluru, IN); Deepak Trivedi (Halfmoon, NY); Narendra Anand Hardikar (Bengaluru, IN); Vidyashankar Ramasastry Buravalla (Bengaluru, IN); Steven Douglas Johnson (Milford, OH); Amit Goyal (Bengaluru, IN); Grant Robert Portune (Cincinnati, OH); Himanshu Gupta (Bengaluru, IN); Srinivasan Swaminathan (Bengaluru, IN); Shalini Thimmegowda (Bengaluru, IN); Guru Venkata Dattu Jonnalagadda (Ponnur, IN); Shalabh Saxena (Bengaluru, IN); Prateek Jalan (Bengaluru, IN)

Assignee: General Electric Company

F01D11/025F05D2240/53F05D2240/55F05D2260/38

Abstract

Claims (25)

1. A turbine engine defining an axial direction and a radial direction, the turbine engine comprising:

a rotor;

a stator comprising a carrier;

a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and

a seal support assembly comprising a spring arrangement extending between the carrier and the seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine, wherein the spring arrangement comprises a plurality of spring extensions extending between the carrier and the seal segment, wherein the seal segment defines a slot extending along the axial direction and a circumferential direction of the turbine engine, and wherein the plurality of spring extensions each includes a distal end positioned in the slot of the seal segment.

2. The turbine engine of claim 1 , wherein the seal segment and the distal ends of the plurality of spring extensions define a clearance gap along the axial direction.

3. The turbine engine of claim 1 , wherein the spring arrangement further includes a base extending along a circumferential direction, and wherein the plurality of spring extensions each extend from the base and are spaced along the circumferential direction.

4. The turbine engine of claim 3 , wherein the base is coupled to the carrier.

5. The turbine engine of claim 1 , wherein the seal support assembly comprises a plurality of spring arrangements spaced along a circumferential direction and an annular flange extending along the circumferential direction, wherein the annular flange is positioned between the plurality of spring arrangements and the carrier.

6. The turbine engine of claim 1 , wherein a base of the spring arrangement is coupled to or formed integrally with the carrier proximate the high-pressure side of the seal assembly, and wherein the plurality of spring extensions contact the seal segment proximate the low-pressure side.

7. The turbine engine of claim 1 , wherein the spring arrangement comprises a spring extension and a base, wherein the base is coupled to the carrier, wherein the spring extension has a distal end contacting the seal segment.

8. The turbine engine of claim 7 , wherein the carrier defines a radial face, and wherein the base is coupled to the carrier at the radial face.

9. The turbine engine of claim 1 , wherein the seal segment is a first seal segment, wherein the seal assembly further includes a second seal segment positioned adjacent the seal segment along a circumferential direction of the turbine engine and a piston seal extending along the circumferential direction and positioned between the carrier and the first and second seal segments.

10. The turbine engine of claim 1 , wherein the spring arrangement comprises one or more elements formed of shape memory alloy material, a bimetallic material, or both.

11. A turbine engine defining an axial direction and a radial direction, the turbine engine comprising:

a rotor;

a stator comprising a carrier;

a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and

a seal support assembly comprising a spring arrangement extending between the carrier and the seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine, wherein the spring arrangement includes a first cam and a second cam, wherein the first and second cams are rotatable about a common rotational axis, and wherein the spring arrangement includes a spring extension extending between the first and second cams.

12. The turbine engine of claim 11 , wherein the spring arrangement includes a spring extension arranged in tension.

13. A turbine engine defining an axial direction and a radial direction, the turbine engine comprising:

a rotor;

a stator comprising a carrier;

a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and

a seal support assembly comprising a spring arrangement extending between the carrier and the seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine, wherein the seal segment is a first seal segment, wherein the seal assembly further includes a second seal segment positioned adjacent the seal segment along a circumferential direction of the turbine engine and a piston seal extending along the circumferential direction and positioned between the carrier and the first and second seal segments.

Assignments (1)

Continuity (1)

References Cited (174)