CIRCUMFERENTIAL SEAL WITH SEAL DAMPENING ELEMENTS

• US 20160108750A1
• Filed: 10/14/2015
• Published: 04/21/2016
• Est. Priority Date: 10/17/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Wilson, Ross, McCaffrey, Michael G.
• Granted Patent: US 9,988,921 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 11/00 Preventing or minimising internal leakage of working-fluid, e.g. between stages sealings in general F16J ; sealing arrangements for transition ducts of combustor cans F01D9/023
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 11/003 by packing rings; Mechanical seals
• CPC Class Codes: F01D 11/02 by non-contact sealings, e.g. of labyrinth type for sealing space between rotor blade tips and stator F01D11/08
• CPC Class Codes: F01D 11/025 Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
• CPC Class Codes: F01D 25/04 Antivibration arrangements
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F16J 15/16 between relatively-moving surfaces F16J15/50, F16J15/52 take precedence; bellows pistons F16J3/06; piston-rings or ring sealings of similar construction F16J9/00
• CPC Class Codes: F16J 15/445 with means for adjusting the clearance

Abstract

The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a circumferential seal for a gas turbine engine includes a first beam, a second beam, a seal shoe and at least one feature between the first beam and second beam configured to retain a beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal. Another embodiment is directed to a circumferential seal including a beam spacer.

Claims

1. A circumferential seal for a gas turbine engine, the circumferential seal comprising:

a first beam;

a second beam;

a seal shoe; and

at least one feature between the first beam and second beam configured to retain a beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal.

2. The circumferential seal of claim 1, wherein the first beam is an outer beam of the circumferential seal.

3. The circumferential seal of claim 1, wherein the second beam is an inner beam of the circumferential seal.

4. The circumferential seal of claim 1, wherein the at least one feature is a cradle feature including a channel configured to receive a beam spacer along the axial depth of the circumferential seal.

5. The circumferential seal of claim 1, wherein the at least one feature includes raised portions of the first beam and raised portions of the second beam, wherein the raised portions of the inner and outer beam form a channel between the first and second beam to secure a beam spacer.

6. The circumferential seal of claim 1, wherein the at least one feature is configured to retain a beam spacer configured to dampen vibratory responses of the circumferential seal between the first and second beams.

7. The circumferential seal of claim 1, wherein the circumferential seal is a non-contact seal for a bearing compartment of the gas turbine engine.

8. The circumferential seal of claim 1, wherein the circumferential seal is at least one of a full ring and segmented seal.

9. The circumferential seal of claim 1, wherein the beam spacer is an elongated element having at least one of a pin, rod, cylindrical, round, square, rectangular, round, and oval shape, and wherein the beam spacer is configured to dampen beam and shoe response of the circumferential seal.

10. The circumferential seal of claim 1, further comprising a plurality of beam spacers and features to retain the beam spacer.

11. A circumferential seal for a gas turbine engine, the circumferential seal comprising:

a first beam;

a second beam;

a seal shoe;

a beam spacer between the first beam and second beam; and

at least one feature between the first beam and second beam configured to retain the beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal.

12. The circumferential seal of claim 11, wherein the first beam is an outer beam of the circumferential seal.

13. The circumferential seal of claim 11, wherein the second beam is an inner beam of the circumferential seal.

14. The circumferential seal of claim 11, wherein the at least one feature is a cradle feature including a channel configured to receive a beam spacer along the axial depth of the circumferential seal.

15. The circumferential seal of claim 11, wherein the at least one feature includes raised portions of the first beam and raised portions of the second beam, wherein the raised portions of the inner and outer beam form a channel between the first and second beam to secure a beam spacer.

16. The circumferential seal of claim 11, wherein the at least one feature is configured to retain a beam spacer configured to dampen vibratory responses of the circumferential seal between the first and second beams.

17. The circumferential seal of claim 11, wherein the circumferential seal is a non-contact seal for a bearing compartment of the gas turbine engine.

18. The circumferential seal of claim 11, wherein the circumferential seal is at least one of a full ring and segmented seal.

19. The circumferential seal of claim 11, wherein the beam spacer is an elongated element having at least one of a pin, rod, cylindrical, round, square, rectangular, round, and oval shape, and wherein the beam spacer is configured to dampen beam and shoe response of the circumferential seal.

20. The circumferential seal of claim 11, further comprising a plurality of beam spacers and features to retain the beam spacer.