Hybrid seal dual runner

Patent metadata

Field	Value
Publication number	US-11549444-B2
Application number	US-202117168768-A
Country	US
Kind code	B2
Filing date	Feb 5, 2021
Priority date	Feb 5, 2021
Publication date	Jan 10, 2023
Grant date	Jan 10, 2023

Abstract

A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.

First claim

What is claimed is:

1. A turbomachine comprising:
a bearing in a bearing compartment; and
a first seal system isolating the bearing compartment and comprising:
a first runner;
a second runner;
an inner seal encircling the first runner; and
an outer seal encircling the second runner,

wherein:
the inner seal has a static clearance with the first runner;
the outer seal has a static clearance with the second runner, greater than the inner seal static clearance;
the first runner comprises an inner portion cantilevered inward; and
the second runner comprises an outer portion cantilevered outward.

2. The turbomachine of claim 1 wherein:
the inner seal static clearance is zero.

3. The turbomachine of claim 2 wherein:
the outer seal static clearance is 0.0010 inch to 0.0050 inch (0.025 to 0.13 mm) radially.

4. The turbomachine of claim 1 wherein:
the inner seal is a non-archbound seal; and
the outer seal is an archbound seal.

5. The turbomachine of claim 1 further comprising:
a circumferential spring biasing the inner seal into engagement with the first runner.

6. The turbomachine of claim 1 wherein:
the inner seal is a carbon seal; and
the outer seal is a carbon seal.

7. The turbomachine of claim 1 wherein:
the inner seal is circumferentially segmented; and
the outer seal is circumferentially segmented.

8. The turbomachine of claim 1 wherein:
the first runner comprises an inner portion cantilevered inward; and
the second runner comprises an outer portion cantilevered outward.

9. The turbomachine of claim 1 wherein:
the first runner has a mounting flange; and
the second runner has a mounting flange abutting the inner portion mounting flange.

10. The turbomachine of claim 1 wherein:
the first runner has a first coefficient of thermal expansion; and
the second runner has second coefficient of thermal expansion lower than the first coefficient of thermal expansion.

11. The turbomachine of claim 1 further comprising:
an oil source positioned to direct oil to preferentially cool the inner portion relative to the outer portion.

12. The turbomachine of claim 11 further comprising:
a buffer air source introducing air past the outer seal to an interstage.

13. The turbomachine of claim 12 further comprising:
an outlet from the interstage.

14. A method for using the turbomachine of claim 1 , the method comprising:
driving rotation of a shaft carrying the first runner and the second runner; and
passing an airflow between the outer seal and the second runner to mix with an oil leakage flow in an interstage of the seal system.

15. The method of claim 14 further comprising:
directing a cooling oil flow to an inner diameter surface of the first runner inner portion.

16. The method of claim 14 wherein:
the first runner inner portion thermally deforms to cone inward in the inward direction; and
the second runner outer portion thermally deforms to cone outward in the outward direction.

17. A turbomachine comprising:
a bearing in a bearing compartment; and
a first seal system isolating the bearing compartment at one of a forward end of the bearing compartment and an aft end of the bearing compartment and comprising:
a runner;
an inner seal encircling the runner; and
an outer seal encircling the runner,

wherein the runner has:
a first piece encircled by the inner seal; and
a second piece encircled by the outer seal.

18. The turbomachine of claim 17 wherein:
the runner first piece comprises an inner portion cantilevered inward; and
the runner second piece comprises an outer portion cantilevered outward.

19. The turbomachine of claim 18 wherein:
an oil source is positioned to direct an oil flow to an inner diameter surface of the runner first piece inner portion; and
the turbomachine lacks an oil source positioned to direct an oil flow to an inner diameter surface of the runner second piece outer portion.

20. The turbomachine of claim 17 wherein:
the runner first piece has a first coefficient of thermal expansion; and
the runner second piece has second coefficient of thermal expansion lower than the first coefficient of thermal expansion.

21. The turbomachine of claim 17 wherein:
the runner first piece comprises stainless steel; and
the runner second piece a molybdenum alloy or a ceramic.

22. A turbomachine comprising:
a bearing in a bearing compartment; and
a two-stage first seal system isolating the bearing compartment and comprising:
a first runner;
a second runner;
an inner seal encircling the first runner; and
an outer seal encircling the second runner,

wherein:
the inner seal has a static clearance with the first runner;
the outer seal has a static clearance with the second runner, greater than the inner seal static clearance; and
the turbomachine includes means for preferentially cooling the first runner relative to the second runner.

Assignees

• Raytheon Tech Corp

Inventors

• Beinor Michael A
• Castaldo Timothy J
• Valva Christopher M
• Shuaib Nasr A
• Panton Mitchell D

Classifications

• F05D2300/224

  Carbon, e.g. graphite · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2260/232

  characterized by the cooling medium · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F01D25/183 Primary

  Sealing means · CPC title