Aspirating face seal assembly and a method of operating the same

Patent metadata

Field	Value
Publication number	US-10428673-B2
Application number	US-201615143878-A
Country	US
Kind code	B2
Filing date	May 2, 2016
Priority date	May 2, 2016
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

An aspirating face seal assembly for a turbo-machine including a rotor assembly having a first radially extending portion defining a rotor surface is disclosed. The aspirating face seal assembly includes a seal body including a second radially extending portion defining a bearing surface and having a plurality of return channels. The second radially extending portion is disposed in the turbo-machine such that the bearing surface is disposed facing the rotor surface. The aspirating face seal assembly further includes an annular ring including one or more openings. The annular ring is concentrically disposed on the second radially extending portion and between the rotor surface and the second radially extending portion and configured to rotate in an event of rub between the first radially extending portion and the annular ring. A turbo-machine including the aspirating face seal assembly and a method for operating an aspirating face seal are also disclosed.

First claim

The invention claimed is:

1. An aspirating face seal assembly for a turbo-machine comprising a rotor assembly having a first radially extending portion defining a rotor surface, the aspirating face seal assembly comprising:
a seal body comprising a second radially extending portion defining a bearing surface and comprising one or more feed holes and a plurality of return channels, wherein the second radially extending portion is configured to be disposed in the turbo-machine such that the bearing surface is disposed facing the rotor surface, the one or more feed holes configured to enable a feed flow of a pressurized fluid toward the rotor surface; and
an annular ring comprising one or more openings and concentrically disposed on the second radially extending portion, wherein the annular ring is configured to be disposed between the rotor surface and the second radially extending portion and rotate in an event of rub between the first radially extending portion and the annular ring.

2. The aspirating face seal assembly of claim 1 , further comprising a stopper mechanism for restricting a rotational motion of the annular ring up to a predefined distance from a steady state position in the event of rub between the first radially extending portion and the annular ring.

3. The aspirating face seal assembly of claim 2 , wherein the stopper mechanism comprises a protrusion formed on the second radially extending portion and a stopper opening formed on the annular ring, wherein the protrusion is engaged to the stopper opening and configured to protrude towards the rotor surface, and wherein the predefined distance is defined by a width of the stopper opening.

4. The aspirating face seal assembly of claim 1 , wherein the second radially extending portion includes the one or more feed holes configured to enable the feed flow of the pressurized fluid from a first region toward the rotor surface.

5. The aspirating face seal assembly of claim 4 , wherein the one or more openings are configured to enable a return flow of the pressurized fluid toward a second region via the plurality of return channels.

6. The aspirating face seal assembly of claim 5 , wherein the annular ring, when rotated, blocks a portion of an entrance of one or more of the plurality of return channels to increase a force of the feed flow of the pressurized fluid to bias the second radially extending portion away from the rotor surface.

7. The aspirating face seal assembly of claim 5 , wherein one or more of the plurality of return channels are bifurcated into an axial conduit and a radial conduit to aid in the return flow of the pressurized fluid toward the second region.

8. The aspirating face seal assembly of claim 7 , wherein the annular ring further comprises one or more third radially extending portions, wherein each of the one or more third radially extending portions is disposed in the corresponding radial conduit.

9. The aspirating face seal assembly of claim 8 , wherein each of the one or more third radially extending portions is configured to block a portion of the corresponding radial conduit.

10. The aspirating face seal assembly of claim 8 , wherein the one or more third radially extending portions are configured to restrict a rotational motion of the annular ring up to a predefined distance from a steady state position in the event of rub between the first radially extending portion and the annular ring.

11. The aspirating face seal assembly of claim 1 , wherein the annular ring comprises an L-shaped cross section having a first end and a second end.

12. The aspirating face seal assembly of claim 11 , wherein the annular ring is disposed on the second radially extending portion such that the first end is configured to be oriented towards the rotor surface along an axial direction of the turbo-machine and the second end is configured to be oriented along a radial direction of the turbo-machine.

13. The aspirating face seal assembly of claim 11 , wherein the annular ring is disposed on the second radially extending portion such that the first end is offset from the bearing surface by an offset distance.

14. The aspirating face seal assembly of claim 13 , wherein the offset distance is in a range of 0 to 0.020 inches.

15. A turbo-machine comprising:
a stationary support;
a rotor assembly comprising a first radially extending portion defining a rotor surface; and
an aspirating face seal assembly coupled to the stationary support and disposed between the stationary support and the rotor assembly, wherein the aspirating face seal assembly comprises:
a seal body comprising a second radially extending portion defining a bearing surface and comprising one or more feed holes and a plurality of return channels, wherein the bearing surface is disposed facing the rotor surface, the one or more feed holes configured to enable a feed flow of a pressurized fluid toward the rotor surface; and
an annular ring comprising one or more openings and concentrically disposed on the second radially extending portion, wherein the annular ring is disposed between the rotor surface and the second radially extending portion and configured to rotate in an event of rub between the first radially extending portion and the annular ring.

16. The turbo-machine of claim 15 , wherein of the one or more feed holes are configured to enable the feed flow of the pressurized fluid from a first region toward the rotor surface, and wherein the one or more openings are configured to enable a return flow of the pressurized fluid toward a second region via the plurality of return channels.

17. The turbo-machine of claim 16 , wherein one or more of the plurality of return channels are bifurcated into an axial conduit and a radial conduit to aid in the return flow of the pressurized fluid towards the second region of low pressure.

18. The turbo-machine of claim 17 , wherein the annular ring further comprises one or more third radially extending portions, wherein each of the one or more third radially extending portions is disposed in the corresponding radial conduit.

19. A method for operating an aspirating face seal assembly, the method comprising:
feeding a pressurized fluid from a region of high pressure towards a rotor surface via a plurality of feed holes, wherein the rotor surface is defined by a first radially extending portion of a rotor assembly;
enabling a return flow of the pressurized fluid towards a second region of low pressure via one or more openings formed in an annular ring and a plurality of return channels formed in a second radially extending portion of the aspirating face seal assembly, wherein the second radially extending portion defines a bearing surface disposed facing the rotor surface and wherein the annular ring is concentrically disposed on the second radially extending portion and between the rotor surface and the second radially extending portion; and
rotating the annular ring in an event of rub between the annular ring and the first radially extending portion to partially block an entrance of one or more of the plurality of return channels thereby increasing a force of the feed flow of the pressurized fluid to bias the second radially extending portion away from the rotor surface.

20. The method of claim 19 , further comprising removing a material from the bearing surface due to friction between the first radially extending portion and the bearing surface prior to rotating the annular ring.

Assignees

• Gen Electric

Inventors

• Erdmenger Rodrigo Rodriguez
• Gibson Nathan Evan Mccurdy
• Nguyen Tran Quang Tue

Classifications

• F05D2240/24

  for turbines · CPC title

• F16J15/3404

  and characterised by parts or details relating to lubrication, cooling or venting of the seal · CPC title

• F16J15/342

  with means for feeding fluid directly to the face · CPC title

• F16J15/441

  with floating ring · CPC title

• F05D2220/32

  in gas turbines · CPC title