Face seal arrangement for reduced force and pressure

Patent metadata

Field	Value
Publication number	US-11624325-B2
Application number	US-202217747158-A
Country	US
Kind code	B2
Filing date	May 18, 2022
Priority date	Nov 25, 2020
Publication date	Apr 11, 2023
Grant date	Apr 11, 2023

Abstract

A bearing is mounted to a static structure outwardly of the shaft, and supporting the shaft. A bearing compartment is defined by face seal arrangements on each of two axial sides of a bearing. Each face seal arrangement includes a seal seat rotating with the shaft and a non-rotating sealing ring. The seal housing is exposed to high pressure air outward of the bearing compartment. A coil spring biases the seal housing towards the seal seat, such that the sealing face is biased into contact with the seal seat by a bias force including a net fluid force acting on the seal housing and the coil spring. The sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat. The feed portion includes a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove.

First claim

What is claimed is:

1. A gas turbine engine comprising: a seal seat connected for rotating with a shaft about an axis and a non-rotating sealing ring including a mount portion mounted to a seal housing and a sealing face biased into contact with said seal seat by a coil spring;
and wherein said sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat, said feed portion including a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove;
and wherein said sealing ring further includes a ditch at a radially outermost location adjacent to said seal housing, and said contact portion includes an axial nose portion defined as an annular portion radially outward of said at least one annular groove and radially inward of said ditch; and
at least one of the following is true:
the feed portion is recessed axially at a feed depth of D f from the sealing face, the axial nose portion extends axially forward from said ditch at an extension distance D n , and D n is less than D f ; or
the plurality of circumferentially spaced feed slots extend radially from an inner diameter of said sealing face to said at least one annular grove at a length L f , said axial nose portion extends radially outward from at least one annular groove to said ditch at a thickness L n and said feed slot length L f is less than said axial nose thickness L n .

2. The gas turbine engine of claim 1 , wherein high pressure air from outside the bearing compartment is communicated through the plurality of circumferentially spaced feed slots to the at least one annular groove.

3. The gas turbine engine of claim 2 , wherein the feed portion is recessed axially at the feed depth of D f from the sealing face, the axial nose portion extends axially forward from said ditch at the extension distance D n , and a ratio of feed depth D f to axial nose extension D n is greater than 1.0 and less than or equal to 10.0.

4. The gas turbine engine of claim 3 , wherein the ratio of feed depth D f to axial nose extension D n is greater than 1.0 and less than or equal to 1.4.

5. The gas turbine engine of claim 3 , wherein a ratio of feed slot length L f to axial nose thickness L n is greater than or equal to 0.07 and less than 1.0.

6. The gas turbine engine of claim 5 , wherein the ratio of feed slot length L f to axial nose thickness L n is greater than or equal to 0.5 and less than 1.0.

7. The gas turbine engine of claim 5 , wherein the contact portion further includes a plurality of segmented portions in between the circumferentially spaced feed slots.

8. The gas turbine engine of claim 1 , wherein the plurality of circumferentially spaced feed slots includes between 12 and 60 equally circumferentially spaced feed slots.

9. The gas turbine engine of claim 1 , wherein the feed portion includes at least two annular grooves and the feed slots extend from an inner diameter of the sealing face through an inner one of said at least two annular grooves and then to an outer one of said at least two annular grooves.

10. The gas turbine engine of claim 1 , wherein said shaft drives a fan through a gear reduction.

11. The gas turbine engine of claim 1 , wherein said non-rotating sealing ring is a carbon ring.

12. The gas turbine engine of claim 1 , wherein the feed portion is recessed axially at a feed depth of D f from the sealing face, the axial nose portion extends axially forward from said ditch at an extension distance D n , and a ratio of feed depth D f to axial nose extension D n is greater than 1.0 and less than or equal to 10.0.

13. The gas turbine engine of claim 12 , wherein the ratio of feed depth D f to axial nose extension D n is greater than 1.0 and less than or equal to 1.4.

14. The gas turbine engine of claim 13 , wherein a ratio of feed slot length L f to axial nose thickness L n is greater than or equal to 0.07 and less than 1.0.

15. The gas turbine engine of claim 1 , wherein a ratio of feed slot length L f to axial nose thickness L n is greater than or equal to 0.07 and less than 1.0.

16. The gas turbine engine of claim 14 , wherein the ratio of feed slot length L f to axial nose thickness L n is greater than or equal to 0.5 and less than 1.0.

17. A face seal arrangement comprising: a seal seat for rotating with a shaft about an axis and a non-rotating sealing ring including a mount portion mounted to a seal housing and a sealing face biased into contact with said seal seat by a coil spring;
wherein said sealing face is defined by a contact portion contacting the seal seat and a feed portion recessed from the seal seat, said feed portion including a plurality of circumferentially spaced feed slots fluidly connected to at least one annular groove; and
at least one of the following is true:
and wherein said sealing ring further includes a ditch at a radially outermost location adjacent to said seal housing, and said contact portion includes an axial nose portion defined as an annular portion radially outward of said at least one annular groove and radially inward of said ditch; and
at least one of the following is true:
the feed portion is recessed axially at a feed depth of D f from the sealing face, the axial nose portion extends axially forward from said ditch at an extension distance D n , and D n is less than D f ; or
the plurality of circumferentially spaced feed slots extend radially from an inner diameter of said sealing face to said at least one annular grove at a length L f , said axial nose portion extends radially outward from at least one annular groove to said ditch at a thickness L n and said feed slot length L f is less than said axial nose thickness L n .

18. The face seal arrangement of claim 17 , wherein said non-rotating sealing ring is a carbon seal.

19. The face seal arrangement of claim 17 , wherein a ratio of feed depth D f to axial nose extension D n is greater than 1.0 and less than or equal to 10.0.

20. The face seal arrangement of claim 17 , wherein a thickness L n , and a ratio of feed slot length L f to axial nose thickness L n is greater than or equal to 0.07 and less than 1.0.

Assignees

• Raytheon Tech Corp

Inventors

• Miller Jonathan Logan
• Craig Colin D
• Davis Michael M

Classifications

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F01D11/003 Primary

  by packing rings; Mechanical seals · CPC title

• F16H1/28

  with gears having orbital motion · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F05D2240/55

  Seals · CPC title