Separation assembly with a two-piece impulse turbine

Patent metadata

Field	Value
Publication number	US-11352999-B2
Application number	US-201917044371-A
Country	US
Kind code	B2
Filing date	Apr 16, 2019
Priority date	Apr 17, 2018
Publication date	Jun 7, 2022
Grant date	Jun 7, 2022

Abstract

A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine assembly positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet. The fluid causes the turbine assembly to rotate about a center rotational axis within the housing. The turbine assembly comprises a first turbine portion and a second turbine portion that are separately formed from each other and attachable together. The first turbine portion comprises a plurality of first vanes and the second turbine portion comprises a plurality of second vanes.

First claim

What is claimed is:

1. A separation assembly comprising:
a housing;
a jet that expels a fluid within the housing; and
a turbine assembly positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet, the fluid causing the turbine assembly to rotate about a center rotational axis within the housing,
the turbine assembly comprising a first turbine portion and a second turbine portion that are separately formed from each other and attachable together, the first turbine portion comprising a plurality of first vanes, a plurality of first ribs defining a plurality of first recesses, and a plurality of first inner walls, and the second turbine portion comprising a plurality of second vanes, a plurality of second ribs defining a plurality of second recesses, and a plurality of second inner walls;
the plurality of first vanes and the plurality of second vanes defining axially-extending channels that each extend radially between one of the plurality of first vanes and one of the plurality of second vanes when the turbine assembly is assembled,
the plurality of first inner walls are each positioned between two of the plurality of first ribs; and
the plurality of second inner walls are each positioned between two of the plurality of second ribs.

2. The separation assembly of claim 1 , wherein at least a portion of each of the first vanes extends along and from a respective one of the first ribs and at least a portion of each of the second vanes extends along and from a respective one of the second ribs.

3. The separation assembly of claim 2 , wherein the plurality of first vanes and the plurality of second vanes each extend radially between an inner side edge and an outer side edge, where the entire inner side edge of each of the plurality of first vanes extends along and from the respective one of the plurality of first ribs and the entire inner side edge of each of the plurality of second vanes extends along and from the respective one of the plurality of second ribs.

4. The separation assembly of claim 2 , wherein the plurality of first ribs and the plurality of second ribs are complementary to each other such that the plurality of first ribs and the plurality of second ribs circumferentially and axially align the first turbine portion and the second turbine portion.

5. The separation assembly of claim 1 , wherein, when the first turbine portion and the second turbine portion are attached together, the plurality of first vanes and the plurality of second vanes are alternatively arranged with each other about a circumference of the turbine assembly.

6. The separation assembly of claim 1 , wherein the plurality of first vanes of the first turbine portion is exactly half of the total number of vanes within the turbine assembly, and the plurality of second vanes of the second turbine portion is exactly the other half of the total number of vanes within the turbine assembly.

7. The separation assembly of claim 1 , wherein the distance between individual vanes of the plurality of first vanes is greater than the distance between each of the plurality of first vanes and the plurality of second vanes once the first turbine portion and the second turbine portion are attached together.

8. The separation assembly of claim 1 , wherein, once the first turbine portion and the second turbine portion are attached to each other, the plurality of first vanes and the plurality of second vanes are all circumferentially and axially aligned with each other.

9. The separation assembly of claim 1 , wherein the plurality of first vanes are each full vanes and the plurality of second vanes are each full vanes before the first turbine portion and the second turbine portion are attached together.

10. The separation assembly of claim 1 , wherein each of the plurality of first vanes and each of the plurality of second vanes extends axially between and curve relative to an axial direction between a top end and a bottom end, wherein the axial direction is parallel to the center rotational axis, and
wherein each of the plurality of vanes curve relative to a radial direction between a radially inner side edge and a radial outer side edge of the plurality of vanes.

11. The separation assembly of claim 1 , wherein the plurality of first vanes and the plurality of second vanes each comprise an undercut feature that partially blocks fluid from the jet in an axial direction.

12. The separation assembly of claim 11 , wherein the undercut feature is a top undercut feature that extends along at least a portion of a respective top end of each of the plurality of the first vanes and each of the plurality of the second vanes, wherein the jet is positioned such that at least a portion of the fluid enters into the turbine assembly along the respective top ends of the plurality of first vanes and the plurality of second vanes.

13. The separation assembly of claim 1 , wherein the first turbine portion comprises a first center hub that the first plurality of vanes extends from and the second turbine portion comprises a second center hub that the second plurality of vanes extends from.

14. The separation assembly of claim 13 ,
wherein the plurality of first ribs and the plurality of first recesses of the first hub are complementary to the plurality of second ribs and the plurality of second recesses of the second hub such that each of the plurality of first ribs fits securely within a respective one of the plurality of second recesses and between two of the plurality of second ribs.

15. The separation assembly of claim 14 ,
wherein the plurality of first inner walls and the plurality of second inner walls are recessed relative to an outermost radial surface of the plurality of first ribs and the plurality of second ribs, respectively.

16. The separation assembly of claim 15 , wherein inner surfaces of the plurality of first ribs and the plurality of second ribs are complementary to outer surfaces of the plurality of second inner walls and the plurality of first inner walls, respectively.

17. The separation assembly of claim 13 , wherein the second hub comprises an extension that extends through and beyond the first hub when the first turbine portion and the second turbine portion are attached together such that the first turbine portion is positioned axially between opposite axial ends of the second turbine portion.

18. The separation assembly of claim 17 , wherein the second turbine portion comprises a threaded feature positioned along at least a portion of an outer surface of the extension and configured to threadably attach to a rotor portion of the separation assembly.

19. The separation assembly of claim 1 , wherein the first turbine portion and the second turbine portion are each individually and integrally created as a single, unitary part.

20. The separation assembly of claim 1 , wherein the jet is positioned at an angle relative to a horizontal radial-tangential plane of the turbine assembly, and wherein the horizontal radial-tangential plane of the turbine assembly is perpendicular to the center rotational axis.

21. The separation assembly of claim 1 , wherein each of the plurality of first vanes and each of the plurality of second vanes extends axially between a top end and a bottom end and comprise an impingement surface on a first side thereof, a backside on a second side thereof, and a chamfer between the backside and the top end, and
wherein the jet is positioned such that at least a portion of the fluid

Assignees

• Cummins Filtration Ip Inc

Inventors

• Parikh Chirag D

Classifications

• B01D46/26

  rotatable · CPC title

• B04B5/12

  Centrifuges in which rotors other than bowls generate centrifugal effects in stationary containers · CPC title

• F05B2240/121

  Baffles or ribs · CPC title

• B01D46/0056

  with rotational movement · CPC title

• F05B2260/201

  by impingement of a fluid · CPC title