Bearing compartment seal configuration for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11499442-B2
Application number	US-201916383018-A
Country	US
Kind code	B2
Filing date	Apr 12, 2019
Priority date	Apr 12, 2019
Publication date	Nov 15, 2022
Grant date	Nov 15, 2022

Abstract

A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.

First claim

The invention claimed is:

1. A bearing compartment seal for a gas turbine engine comprising:
at least one seal ring defining an axis and having a radially inward facing sealing surface;
a seal runner having a support portion constructed of a first material and an interface portion constructed of a second material distinct from the first material, the interface portion including a radially outward facing surface, the support portion including a radial section having a radially inward facing surface and an axial section extending axially from an end of the radial section, the axial section including a radially outward facing surface contacting the interface portion, the interface portion including a uniform radial thickness along a contact with the seal ring; and
wherein a first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.

2. The bearing compartment seal of claim 1 , wherein the first coefficient of thermal expansion is approximately identical to the second coefficient of thermal expansion.

3. The bearing compartment seal of claim 1 , wherein the at least one seal ring is constructed of a third material, and wherein the third material and the second material have at least one shared underlying component material.

4. The bearing compartment seal of claim 3 , wherein the third material and the second material are the same material.

5. The bearing compartment seal of claim 1 , wherein the at least one seal ring comprises a pair of seal rings.

6. The bearing compartment seal of claim 1 , wherein the interface portion is disposed circumferentially about the support portion, and extends at least a full axial length of the at least one seal ring.

7. The bearing compartment seal of claim 6 , wherein the interface portion extends a full axial length of the support portion.

8. The bearing compartment seal of claim 6 , wherein the support portion extends less than a full axial length of the interface portion.

9. The bearing compartment seal of claim 6 , wherein the interface portion extends less than a full length of the support portion.

10. The bearing compartment seal of claim 6 , wherein the support portion includes a radially outward extending axial retention tab at at least one axial end of the support portion, the axial retention tab being configured to retain the interface portion axially relative to the support portion.

11. The bearing compartment seal of claim 10 , wherein the axial retention tab extends a full radial height of the interface portion.

12. The bearing compartment seal of claim 10 , wherein the axial retention tab extends a full circumference of the support portion.

13. The bearing compartment seal of claim 1 , wherein the interface portion is retained relative to the support portion at least partially via a fastener.

14. The bearing compartment seal of claim 13 , wherein the fastener is disposed between the axial ends of the interface portion.

15. The bearing compartment seal of claim 1 , wherein the end of the radial section is opposite the radially inward facing surface.

16. The bearing compartment seal of claim 1 , wherein the interface portion includes a uniform radial thickness along an entire axial length of the interface portion.

17. A bearing compartment seal for a gas turbine engine comprising:
at least one seal ring defining an axis and having a radially inward facing sealing surface;
a seal runner having a support portion constructed of a first material and an interface portion constructed of a second material distinct from the first material, the interface portion including a radially outward facing surface, the support portion including a radial section having a radially inward facing surface and an axial section extending axially from an end of the radial section, the axial section including a radially outward facing surface contacting the interface portion; and
wherein a first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring; and
wherein the interface portion is disposed circumferentially about the support portion, and extends at least a full axial length of the at least one seal ring, wherein the support portion includes a radially outward extending axial retention tab at at least one axial end of the support portion, the axial retention tab being circumferentially intermittent and being configured to retain the interface portion axially relative to the support portion.

18. A bearing compartment seal for a gas turbine engine comprising:
at least one seal ring defining an axis and having a radially inward facing sealing surface;
a seal runner having a support portion constructed of a first material and an interface portion constructed of a second material distinct from the first material, the interface portion including a radially outward facing surface, the support portion including a radial section having a radially inward facing surface and an axial section extending axially from an end of the radial section, the axial section including a radially outward facing surface contacting the interface portion, the interface portion is retained relative to the support portion at least partially via a fastener, wherein the fastener protrudes through the interface portion and the support portion; and
wherein a first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Miller Jonathan Logan
• Ullah M Rifat

Classifications

• F01D25/183

  Sealing means · CPC title

• F05D2240/581

  Double or plural piston ring arrangements, i.e. two or more piston rings · CPC title

• F16J15/164

  the sealing action depending on movements; pressure difference, temperature or presence of leaking fluid · CPC title

• F02C7/06

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

• F01D11/025 Primary

  Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations · CPC title