Separation assembly with a single-piece impulse turbine

Patent metadata

Field	Value
Publication number	US-11458484-B2
Application number	US-201716465931-A
Country	US
Kind code	B2
Filing date	Dec 1, 2017
Priority date	Dec 5, 2016
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine positioned within the housing. The fluid causes the turbine to rotate about a center rotational axis within the housing. The turbine comprises a first axial end, a second axial end, and a plurality of vanes extending axially relative to the center rotational axis from the first axial end to the second axial end. The plurality of vanes defines axially-extending channels between each of the plurality of vanes. The first axial end comprises a radially-extending structure that axially blocks the flow of the fluid through the first axial end. The second axial end does not comprise any structure that axially blocks the flow of the fluid through the second axial end.

First claim

What is claimed is:

1. A separation assembly comprising:
a housing;
a jet that expels a fluid within the housing;
a turbine positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet, the fluid causing the turbine to rotate about a center rotational axis within the housing,
the turbine comprising a first axial end, a second axial end, and a plurality of vanes extending axially relative to the center rotational axis from the first axial end to the second axial end, the plurality of vanes defining axially-extending channels between each of the plurality of vanes,
the first axial end comprising a radially-extending structure that axially blocks the flow of the fluid through the first axial end, the second axial end being axially open such that fluid can flow unblocked axially through the second axial end,
the fluid flowing unblocked axially within the channels between the plurality of vanes from a bottom surface of the radially extending structure to the second axial end of the turbine.

2. The separation assembly of claim 1 , wherein the turbine is formed as a single piece.

3. The separation assembly of claim 1 , wherein outer edges of the plurality of vanes extend axially in a substantially parallel manner relative to the center rotational axis.

4. The separation assembly of claim 1 , wherein outer edges of the plurality of vanes extend axially at a twist angle relative to the center rotational axis such that the plurality of vanes have a helical twist.

5. The separation assembly of claim 4 , where an upper portion of the outer edge is in a different circumferential position along the circumference of the turbine than a lower portion of the outer edge.

6. The separation assembly of claim 1 , wherein the plurality of vanes each comprise an impingement surface on a first side thereof and a backside on a second side thereof, the backside having a substantially continuous surface.

7. The separation assembly of claim 1 , wherein the plurality of vanes each have an impingement surface on a first side thereof and a backside on a second side thereof, wherein the impingement surface and the backside converge at an outer edge of the respective vane.

8. The separation assembly of claim 7 , wherein the backside of each of the plurality of vanes comprises a drip-release edge that is at least partially radially spaced from the outer edge of the respective vane.

9. The separation assembly of claim 8 , wherein the drip-release edge extends substantially parallel to the outer edge of the respective vane.

10. The separation assembly of claim 8 , wherein the drip-release edge extends axially in a linear manner from a bottom edge of the respective vane and axially terminates at an area underneath where the jet is expelling the fluid onto the turbine.

11. The separation assembly of claim 10 , wherein, along the area underneath where the jet is expelling the fluid onto the turbine and here the drip-release edge axially terminates, the drip-release edge extends toward the outer edge of the vane along a direction substantially parallel to the bottom edge of the vane.

12. The separation assembly of claim 1 , wherein the radially-extending structure comprises a plate that extends over spaces defined by the axially-extending channels.

13. The separation assembly of claim 1 , wherein the jet is positioned toward the first axial end of the turbine such that the jet directs fluid directly beneath the radially extending structure.

14. The separation assembly of claim 1 , wherein the turbine is configured to rotate a rotor portion within the separation assembly.

15. The separation assembly of claim 1 , wherein the turbine does not comprise any undercut geometry features that extend radially and/or tangentially from the plurality of vanes, an outer surface of a center hub of the turbine between the vanes, or a bottom of the second axial end of the turbine and that block axial fluid flow through the second axial end of the turbine.

16. The separation assembly of claim 1 , wherein the plurality of vanes extend linearly in the axial direction and do not extend outward tangentially or radially along the length of the plurality of vanes in such a manner that would axially block fluid from axially flowing from the first axial end to the second axial end of the turbine.

17. The separation assembly of claim 1 , wherein a cross-sectional area taken along a plane perpendicular to the center rotational axis along a top portion of each respective vane proximate the radially-extending structure is approximately equal to or greater than a corresponding cross-sectional area along a bottom portion of the respective vane.

18. A turbine for a separation assembly and positioned to be contacted by fluid expelled by a jet, the turbine comprising:
a first axial end comprising a radially-extending structure that axially blocks the flow of the fluid through the first axial end;
a second axial end being axially open such that the fluid can flow unblocked axially through the second axial end; and
a plurality of vanes extending axially relative to a center rotational axis from the first axial end to the second axial end, the plurality of vanes defining axially-extending channels between each of the plurality of vanes,
the fluid flowing, unblocked axially within the channels between the plurality of vanes from a bottom surface of the radially extending structure to the second axial end of the turbine,
the fluid causing the turbine to rotate about the center rotational axis.

19. The turbine of claim 18 , wherein the turbine is positioned within a housing of the separation assembly, wherein the jet expels the fluid within the housing.

20. The turbine of claim 18 , wherein the turbine is formed as a single piece.

21. The turbine of claim 18 , wherein the radially-extending structure comprises a plate that extends over spaces defined by the axially-extending channels.

22. The turbine of claim 18 , wherein the turbine does not comprise any undercut geometry features that extend radially and/or tangentially from the plurality of vanes, an outer surface of a center hub of the turbine between the plurality of vanes, or a bottom of the second axial end of the turbine and that block axial fluid flow through the second axial end of the turbine.

23. A method of making a turbine for a separation assembly, the method comprising:
forming the turbine as a single-piece of material such that the turbine does not require any assembly of parts, the turbine comprising
a first axial end comprising a radially-extending structure that axially blocks a flow of a fluid from a jet through the first axial end;
a second axial end being axially open such that the fluid can flow unblocked axially through the second axial end; and
a plurality of vanes extending axially relative to a center rotational axis from the first axial end to the second axial end, the plurality of vanes defining axially-extending channels between each of the plurality of vanes, the field flowing unblocked axially within the channels between the plurality of vanes from a bottom surface of the radially extending structure to the second axial end of the turbine, the fluid causing the turbine to rotate about the center rotational axis.

24. The method of claim 23 , wherein forming the turbine comprises at least one of molding, casting, or extruding the turbine.

25. A separation assembly compr

Assignees

• Cummins Filtration Ip Inc

Inventors

• Herman Peter K
• Janakiraman Arun P

Classifications

• B04B5/005

  Centrifugal separators or filters for fluid circulation systems, e.g. for lubricant oil circulation systems · CPC title

• Y02B10/50

  Hydropower in dwellings · CPC title

• F03B1/02

  Buckets; Bucket-carrying rotors · CPC title

• F05B2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05B2230/00

  Manufacture · CPC title