TURBINE BLADE SEAL ASSEMBLY

• US 20120049467A1
• Filed: 06/02/2011
• Published: 03/01/2012
• Est. Priority Date: 06/11/2010
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Afanasiev, Gennadiy, Stewart, Jeffrey B., Rudolph, Ronald J.
• Granted Patent: US 8,820,754 B2
• Time in Patent Office: Days
• US Class Current: 277/641
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: F04D 29/083 especially adapted for elastic fluid pumps

Abstract

A seal assembly for an axial flow gas turbine engine includes a rotatable component having a radially extending mate face, a seal slot formed in the mate face, and a seal member slidably disposed in the seal slot. The seal slot includes a radially outer wall and an opposing radially inner wall extending into the component in a circumferential direction from the mate face. The radially outer wall is angled radially inwardly from the mate face toward an inner end portion of the seal slot. Rotation of the seal assembly during operation of the engine produces a centrifugal force on the seal member to effect movement of the seal member in the circumferential direction out of the seal slot.

Claims

1. A seal assembly for limiting gas leakage between a hot gas path and a cavity containing cooling air in a turbine engine, the seal assembly comprising:

a first blade assembly comprising a first platform and a first airfoil, said first platform comprising a first mate face;

a second blade assembly comprising a second platform and a second airfoil, said second platform comprising a second mate face located in opposing facing relationship with said first mate face;

a first seal slot formed in said first mate face and extending into said first platform in a circumferential direction of the engine, wherein said first seal slot is defined by opposing radially inner and radially outer first walls of said first seal slot and by opposing second walls of said first seal slot extending between said first walls, wherein at least the radially outer one of said first walls is angled relative to a line perpendicular to said first mate face such that an entry portion of said first seal slot located at said first mate face has a larger width than an inner end portion of said first seal slot;

a first seal member slidably disposed in said first seal slot and including a circumferentially facing contact surface; and

wherein rotation of the seal assembly during operation of the engine causes an exertion of a centrifugal force on said first seal member in the radial direction so as to cause said first seal member to slide circumferentially partially out of said first seal slot to engage said contact surface into contact with said second mate face.

2. The seal assembly of claim 1, wherein said first seal member comprises a generally flat first strip seal having opposing radially inner and radially outer end surfaces that engage said first walls when said first strip seal is located in said first seal slot, said radially outer end surface being angled from said contact surface of said first strip seal in generally the same direction as said radially outer first wall but having an angle relative to a line perpendicular to said contact surface that is smaller than an angle of said radially outer first wall relative to a line perpendicular to said first mate face.

3. The seal assembly of claim 1, wherein said first walls angle toward each other in a direction from said first mate face to said inner end portion of said first seal slot.

4. The seal assembly of claim 3, wherein said first seal member comprises a generally flat first strip seal having opposing end surfaces that engage said first walls when said first strip seal is located in said first seal slot, said end surfaces being angled from said contact surface of said first strip seal in generally the same direction as said respective first walls but having angles relative to respective lines perpendicular to said contact surface that are different than angles of said first walls relative to respective lines perpendicular to said first mate face.

5. The seal assembly of claim 4, wherein said first walls are angled within a range of about 30°

to about 60°

relative to respective lines perpendicular to said first mate face.

6. The seal assembly of claim 5, wherein said first walls are angled relative to the respective lines perpendicular to said first mate face about 5°

more than said end surfaces are angled relative to the respective lines perpendicular to said contact surface.

7. The seal assembly of claim 4, wherein said first strip seal comprises a thickness of about 2.5 mm.

8. The seal assembly of claim 1, further including a damper member positioned in a damper slot extending into said platform in the circumferential direction, said damper member comprising an elongated member having a longitudinal axis extending generally parallel to an axis of the engine, and said radially outer first wall of said first seal slot being located at a radial location substantially aligned with said longitudinal axis of said damper member.

9. The seal assembly of claim 1, wherein said first seal slot defines an elongated dimension extending across said first mate face from said radially inner first wall to said radially outer first wall, and said elongated dimension angles axially from an outer axial side of said first platform toward a central portion of said first platform, extending outwardly in the radial direction.

10. The seal assembly of claim 1, further comprising:

a second seal slot formed in said first mate face and extending into said first platform in the circumferential direction of the engine, wherein said second seal slot is defined by opposing radially inner and radially outer first walls of said second seal slot and by opposing second walls of said second seal slot extending between said first walls, wherein at least one of said first walls is angled relative to a line perpendicular to said first mate face such that an entry portion of said second seal slot located at said first mate face has a larger width than an inner end portion of said second seal slot;

a second seal member slidably disposed in said second seal slot and including a circumferentially facing contact surface; and

wherein rotation of the seal assembly during operation of the engine causes an exertion of a centrifugal force on said second seal member in the radial direction so as to cause said second seal member to slide circumferentially partially out of said second seal slot to engage said contact surface into contact with said second mate face.

11. A seal assembly for an axial flow gas turbine engine, the seal assembly comprising:

a rotatable component comprising a radially extending mate face;

a seal slot formed in said mate face, said seal slot including a radially outer wall and an opposing radially inner wall extending into said component in a circumferential direction from said mate face, said radially outer wall being angled radially inwardly from said mate face toward an inner end portion of said seal slot;

a seal member slidably disposed in said seal slot; and

wherein rotation of the seal assembly during operation of the engine produces a centrifugal force on said seal member to effect movement of said seal member in the circumferential direction out of said seal slot.

12. The seal assembly of claim 11, wherein said seal member comprises a generally flat strip seal and includes a radially outer end surface located for engagement with said radially outer wall.

13. The seal assembly of claim 12, wherein said radially outer end surface of said seal member is angled radially inwardly from a circumferentially outwardly facing contact surface to a circumferentially inwardly facing surface.

14. The seal assembly of claim 13, wherein:

said radially outer wall angles radially inwardly in a plane extending parallel to said seal slot at a first angle measured from a line perpendicular to said mate face;

said radially outer end surface angles radially inwardly at a second angle measured from a line perpendicular to said contact surface; and

said first angle is greater than said second angle to effect a greater engagement force of said radially outer end surface against said radially outer wall at a location along said radially outer end surface adjacent to said inwardly facing surface of said seal member.

15. The seal assembly of claim 14, wherein said first angle is about 5°

greater than said second angle.

16. The seal assembly of claim 15, wherein said first angle is within a range from about 35°

to about 45°

.

17. The seal assembly of claim 13, wherein said radially inner end surface of said seal member is angled radially outwardly from said contact surface to said inwardly facing surface.

18. The seal assembly of claim 17, wherein an angle of said radially inner end surface relative a line perpendicular to said contact surface is substantially equal to an angle of said radially outer end surface relative a line perpendicular to said contact surface.

19. The seal assembly of claim 11, wherein said seal slot defines an elongated dimension extending across said mate face from said radially inner wall to said radially outer wall, and said elongated dimension angles axially from an outer axial side of said component toward a central portion of said component, extending outwardly in the radial direction.

20. The seal assembly of claim 19, further including a damper member positioned in a damper slot extending into said component in the circumferential direction, said damper member comprising an elongated member having a longitudinal axis extending generally parallel to an axis of the engine, and said radially outer wall of said seal slot being located at a radial location substantially aligned with said longitudinal axis of said damper member.