Hybrid seal dual runner

Patent metadata

Field	Value
Publication number	US-11879396-B2
Application number	US-202217992019-A
Country	US
Kind code	B2
Filing date	Nov 22, 2022
Priority date	Feb 5, 2021
Publication date	Jan 23, 2024
Grant date	Jan 23, 2024

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 two-stage first seal system isolating the bearing compartment and comprising:
a runner;
an inner seal encircling the runner; and
an outer seal encircling the runner outward of the inner seal,

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

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

3. The turbomachine of claim 2 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.

4. The turbomachine of claim 1 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.

5. The turbomachine of claim 1 wherein:
the runner first piece comprises stainless steel; and
the runner second piece a molybdenum alloy or a ceramic.

6. The turbomachine of claim 1 wherein:
an oil source is positioned to direct an oil flow to an inner diameter surface of the runner first piece; and
the turbomachine lacks an oil source positioned to direct an oil flow to an inner diameter surface of the runner second piece.

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

8. The turbomachine of claim 1 further comprising:
a knife edge seal system between the first seal system, and a buffer chamber.

9. The turbomachine of claim 1 wherein:
the inner seal has a static clearance with the runner first piece; and
the outer seal has a static clearance with the runner second piece, greater than the inner seal static clearance.

10. The turbomachine of claim 9 wherein:
the inner seal static clearance is zero.

11. The turbomachine of claim 9 wherein:
a circumferential spring biasing the inner seal into engagement with the runner first piece.

12. A method for using a turbomachine, the turbomachine comprising:
a bearing in a bearing compartment; and
a first seal system isolating 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,

the method comprising:
directing an oil flow to an inner diameter surface of the runner first piece; and
not directing an oil flow to an inner diameter surface of the runner second piece.

13. The method of claim 12 further 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.

14. The method of claim 12 wherein:
the runner first piece comprises an inner portion cantilevered inward;
the runner second piece comprises an outer portion cantilevered outward;
the inner portion thermally deforms to cone inward in the inward direction; and
the outer portion thermally deforms to cone outward in the outward direction.

15. A method for using a turbomachine, the 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; and
the outer seal has a static clearance with the second runner, greater than the inner seal static clearance,

the method comprising:
driving rotation of a shaft carrying the first runner and the second runner; and
preferentially cooling the first runner relative to the second runner.

16. The method of claim 15 further comprising:
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.

17. The method of claim 16 wherein:
a portion of the airflow passes into the bearing compartment; and
the oil leakage flow and the remainder of the airflow are scuppered from the interstage.

18. The method of claim 15 wherein:
the preferentially cooling comprises directing an oil flow to an inner diameter surface of the first runner.

19. The method of claim 18 wherein:
the preferentially cooling comprises not directing an oil flow to an inner diameter surface of the second runner while directing said oil flow to said inner diameter surface of the first runner.

20. The method of claim 15 wherein:
the first runner comprises an inner portion cantilevered inward;
the second runner comprises an outer portion cantilevered outward;
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.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

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

Classifications

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F01D25/183 Primary

  Sealing means · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F05D2220/323

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

• F05D2240/55

  Seals · CPC title