Creep resistant axial ring seal

Patent metadata

Field	Value
Publication number	US-10408074-B2
Application number	US-201615137395-A
Country	US
Kind code	B2
Filing date	Apr 25, 2016
Priority date	Apr 25, 2016
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

Aspects of the disclosure are directed to a seal comprising: a first leg that emanates from a center point of the seal and is configured to contact a first component, a second leg that emanates from the center point and is configured to contact a second component that is operative at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius, and a third leg that emanates from the center point.

First claim

What is claimed is:

1. An assembly, comprising:
a first component;
a second component; and
a seal body extending circumferentially around an axial centerline, the seal body comprising a first leg, a second leg and a third leg;
the first leg projecting diagonally, in a first radial direction relative to the axial centerline and a first axial direction relative to the axial centerline, out from a center point on the seal body, and the first leg contacting the first component;
the second leg projecting diagonally, in a second radial direction relative to the axial centerline and a second axial direction relative to the axial centerline, out from the center point, and the second leg contacting the second component that is operative at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius; and
the third leg projecting diagonally, in the first radial direction and the second axial direction, out from the center point, wherein the third leg does not contact the second component.

2. The assembly of claim 1 , wherein the first leg has a first length, the second leg has a second length, and the third leg has a third length.

3. The assembly of claim 2 , wherein the third length is at least 10% of at least one of the first length or the second length.

4. The assembly of claim 1 , further comprising:
a fourth leg projecting diagonally, in the second radial direction and the first axial direction, out from the center point.

5. The assembly of claim 2 , further comprising a fourth leg that emanates from the center point, wherein the fourth leg has a fourth length, and wherein a summation of the third length and the fourth length is at least 10% of at least one of the first length or the second length.

6. The assembly of claim 4 , wherein the third leg is separated from each of the first leg and the second leg by approximately 90 degrees.

7. The assembly of claim 6 , wherein the fourth leg is separated from each of the first leg and the second leg by approximately 90 degrees.

8. The assembly of claim 1 , wherein the third leg is separated from each of the first leg and the second leg by approximately 90 degrees.

9. The assembly of claim 1 , wherein the seal includes a nickel alloy.

10. An engine with an axial centerline, comprising:
a compressor section;
a combustor section axially downstream of the compressor section relative to the axial centerline;
a turbine section axially downstream of the combustor section relative to the axial centerline, the turbine section including a first component and a second component; and
a seal incorporated in the turbine section, the seal including:
a first leg that emanates from a center point on the seal, the first leg axially contacting the first component in a first axial direction relative to the axial centerline;
a second leg that emanates from the center point, the second leg axially contacting the second component in a second axial direction relative to the axial centerline that is opposite the first axial direction; and
a third leg that emanates from the center point, wherein the third leg does not contact the second component.

11. The engine of claim 10 , wherein the second component is configured to operate at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius.

12. The engine of claim 10 , wherein the second component includes a blade outer air seal support.

13. The engine of claim 12 , wherein the first component includes an outer case.

14. The engine of claim 10 , wherein the seal is configured to interface to a pressure load.

15. The engine of claim 14 , wherein the pressure load includes air sourced from the compressor section.

16. The engine of claim 10 , wherein the first leg has a first length, the second leg has a second length, and the third leg has a third length.

17. The engine of claim 16 , wherein the third length is at least 10% of at least one of the first length or the second length, and wherein the third length is less than 200% of each of the first length and the second length.

18. The engine of claim 10 , further comprising:
a fourth leg that emanates from the center point.

19. The engine of claim 18 , wherein the fourth leg has a fourth length, and wherein a summation of the third length and the fourth length is at least 10% of at least one of the first length or the second length, and wherein the summation of the third length and the fourth length is less than 200% of each of the first length and the second length.

Assignees

• United Technologies Corp

Inventors

• Mclaughlin Brian C
• Clark Thomas E
• Milligan Peter J
• McDowell Dairus Deylan
• Schweitzer Jaimie
• Drake Jeremy
• Hayford Richard K

Classifications

• F16J15/0887

  the sealing effect being obtained by elastic deformation of the packing · CPC title

• F05D2250/10

  Two-dimensional · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F02C7/28

  Arrangement of seals · CPC title

• F05D2240/55

  Seals · CPC title