Face seal arrangement for reduced force and pressure

Patent metadata

Field	Value
Publication number	US-11434828-B2
Application number	US-202017104489-A
Country	US
Kind code	B2
Filing date	Nov 25, 2020
Priority date	Nov 25, 2020
Publication date	Sep 6, 2022
Grant date	Sep 6, 2022

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 core engine including a compressor section having at least one compressor rotor, a combustor section, and a turbine section including at least one turbine rotor, said at least one turbine rotor connected to drive a shaft about an engine axis which, in turn, is connected to drive said at least one compressor rotor, a bearing mounted to a static structure outwardly of said shaft, and supporting said shaft;
a bearing compartment defined by face seal arrangements on each of two axial sides of said bearing, each said face seal arrangement including a seal seat rotating with said shaft and a non-rotating sealing ring, each said non-rotating sealing ring mounted to a seal housing and including a sealing face biased into contact with said seal seat, said seal housing exposed to high pressure air outward of said bearing compartment, and a coil spring biasing said seal housing towards said seal seat, such that said sealing face is biased into contact with said seal seat by a bias force including a net fluid force acting on said seal housing and said 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;
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
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 f is less than D 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 1 , wherein a ratio of the feed depth D f to the axial nose extension D n is between 0.1 and less than 1.0.

4. The gas turbine engine of claim 3 , wherein the ratio of feed depth D f to axial nose extension D n is between 0.5 and less than 1.0.

5. The gas turbine engine of claim 3 , wherein the plurality of circumferentially spaced feed slots extend radially from an inner diameter of said sealing face to said at least one annular groove at a length of L f , said axial nose portion extends radially outward from said at least one annular groove to said ditch at a thickness L n , and L f is greater than L n .

6. The gas turbine engine as set forth in claim 5 , wherein a ratio of the feed slot length L f to axial nose thickness L n is greater than 1.0 and less than or equal to 12.4.

7. The gas turbine engine of claim 5 , wherein a ratio of feed slot length L f to axial nose thickness L n is greater than 1.0 and less than or equal to 4.94.

8. The gas turbine engine of claim 1 , wherein the contact portion further includes a plurality of segmented portions in between the circumferentially spaced feed slots.

9. 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.

10. 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.

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

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

13. 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; 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
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 the feed portion is recessed axially at a feed depth of D f front the sealing face, the axial nose portion extends axially forward from said ditch at an extension distance D n , and D f is less than D n .

14. The face seal arrangement of claim 13 , wherein said non-rotating sealing ring is a carbon seal.

15. The face seal arrangement of claim 13 , wherein
a ratio of feed depth D f to axial nose extension D n is between 0.1 and less than 1.0.

16. The face seal arrangement of claim 15 , wherein the plurality of circumferentially spaced feed slots extend radially from an inner diameter of said sealing face to said at least one annular groove at a length of L f , said axial nose portion extends radially outward from said at least one annular groove to said ditch at a thickness L n , and L f is greater than L n .

17. The face seal arrangement as set forth in claim 16 , wherein a ratio of the feed slot length L f to axial nose thickness L n is greater than 1.0 and less than or equal to 12.4.

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

• F01D25/162

  Bearing supports · CPC title

• F05D2240/55

  Seals · CPC title

• F16H1/28

  with gears having orbital motion · CPC title