阅读说明：本技术 具有单件式冲击式涡轮的分离组件 (Separation assembly with single-piece impulse turbine ) 是由 彼得·K·赫尔曼 奇拉格·D·帕里克 于 2019-02-01 设计创作，主要内容包括：一种分离组件,其包括壳体、在壳体内排出流体的喷射器、以及定位在壳体内并定位成以便与从喷射器排出的流体接触的涡轮。流体使得涡轮在壳体内围绕中心旋转轴线旋转。涡轮包括第一轴向端、第二轴向端和相对于中心旋转轴线从第一轴向端轴向地延伸到第二轴向端的多个轮叶。多个轮叶在多个轮叶中的每一个轮叶之间界定轴向地延伸的通道。第一轴向端是轴向地开放的,使得流体可以畅通无阻地轴向地流过第一轴向端并且流入通道中。喷射器被定位成使得流体的至少一部分通过第一轴向端进入涡轮中。(A separator assembly includes a housing, an ejector discharging fluid within the housing, and a turbine positioned within the housing and positioned so as to be in contact with the fluid discharged from the ejector. The fluid causes the turbine to rotate within the housing about a central axis of rotation. The turbine includes a first axial end, a second axial end, and a plurality of buckets extending axially from the first axial end to the second axial end relative to the central axis of rotation. The plurality of vanes define an axially extending channel between each of the plurality of vanes. The first axial end is axially open such that fluid may flow unimpeded axially through the first axial end and into the channel. The ejector is positioned such that at least a portion of the fluid enters the turbine through the first axial end.)

1. A breakaway assembly comprising:

a housing;

an ejector to discharge fluid within the housing; and

a turbine positioned within the housing and positioned so as to be in contact with the fluid discharged from the injector, the fluid causing the turbine to rotate within the housing about a central axis of rotation,

the turbine including a first axial end, a second axial end, and a plurality of vanes extending axially from the first axial end to the second axial end relative to the central axis of rotation, the plurality of vanes defining an axially extending passage between each of the plurality of vanes, the first axial end being axially open such that fluid can flow unimpeded axially through the first axial end and into the passage,

wherein the injector is positioned such that at least a portion of the fluid enters the turbine through the first axial end.

2. The separator assembly of claim 1 wherein said turbine is formed as a single piece.

3. The separation assembly of claim 1, wherein each of the plurality of lobes extends axially between a top end and a bottom end, wherein the top end is closer to the first axial end of the turbine than the bottom end, wherein each of the plurality of lobes includes a vertical top portion that extends parallel to the central axis of rotation.

4. The separation assembly of claim 1, wherein each of the plurality of lobes extends axially between a top end and a bottom end, the top end being closer to the first axial end of the turbine than the bottom end, wherein each of the plurality of lobes includes an impingement surface on a first side thereof and a back side on a second side thereof, wherein the fluid from the ejector is directed directly to the impingement surface,

and wherein a portion of the impingement surface at the tip of each of the plurality of vanes is more forward in a direction of rotation of the turbine than a remainder of the impingement surface.

5. The separation assembly of claim 1, wherein the turbine defines a complete axial gap between each of the plurality of buckets and within the passage, the axial gap extending straight, axially unobstructed, from the first axial end to the second axial end of the turbine.

6. The separator assembly of claim 1, wherein adjacent vanes of the plurality of vanes do not overlap one another in an axial direction parallel to the central axis of rotation.

7. The separator assembly of claim 1 wherein neither the first axial end nor the second axial end of the turbine is closed such that fluid can flow unimpeded axially between and through the first axial end and the second axial end.

8. The separation assembly of claim 1, wherein the turbine does not include a plate or ring extending along any portion of a radial length of the plurality of buckets.

9. The separation assembly of claim 1, wherein the ejector is positioned at an angle relative to a horizontal radial-tangential plane of the turbine, and wherein the horizontal radial-tangential plane of the turbine is perpendicular to the central axis of rotation.

10. The separator assembly of claim 9 wherein said angle of said ejector is about 22 ° to 26 ° relative to said horizontal radial-tangential plane of said turbine.

11. The separator assembly of claim 1 wherein said injector is angled downwardly toward said first axial end of said turbine.

12. The separation assembly of claim 1, wherein each of the plurality of lobes extends axially between a top end and a bottom end, wherein the top end is closer to the first axial end of the turbine than the bottom end, wherein each of the plurality of lobes includes an impingement surface on a first side thereof and a back side on a second side thereof, wherein the fluid from the injector is directed directly to the impingement surface, and wherein each of the plurality of lobes includes a chamfer between the back side and the top end of each of the plurality of lobes.

13. The separation assembly of claim 12, wherein the apex is substantially perpendicular to the impact surface and the respective top portion of the back side.

14. The separation assembly of claim 12, wherein the chamfer is angled relative to the apex and the back side and extends substantially linearly between the apex and the back side.

15. The separator assembly of claim 1 wherein said turbine includes 13 to 15 vanes spaced about a hub of said turbine.

16. The separation assembly of claim 1, wherein each of the plurality of vanes extends axially between a top end and a bottom end, the top end being closer to the first axial end of the turbine wheel than the bottom end, wherein the top end of each of the plurality of vanes is forward of the bottom end of each of the plurality of vanes in a direction of rotation of the turbine wheel at a same radial distance from the central axis of rotation.

17. The separation assembly of claim 1, wherein each of the plurality of lobes extends axially between a top end and a bottom end, the top end being closer to the first axial end of the turbine than the bottom end, wherein each of the plurality of lobes curves between the top end and the bottom end of each of the plurality of lobes with respect to an axial direction, wherein the axial direction is parallel to the central axis of rotation.

18. The separator assembly of claim 1, wherein each vane of the plurality of vanes is curved relative to a radial direction between an inner radial edge and an outer radial edge.

19. A turbine for use in a separation assembly, the turbine sized for positioning within a housing of the separation assembly and positionable for contact with fluid discharged from an injector of the separation assembly to cause the turbine to rotate within the housing about a central axis of rotation, the turbine comprising:

at the first axial end of the shaft,

a second axial end, and

a plurality of vanes extending axially relative to the central axis of rotation from the first axial end to the second axial end, the plurality of vanes defining an axially extending passage between each of the plurality of vanes, the first axial end being axially open such that fluid can flow unimpeded axially through the first axial end and into the axially extending passage.

20. The turbine of claim 19, wherein the turbine is formed as a single piece.

21. The turbine of claim 19, wherein the turbine defines a complete axial gap between each of the plurality of buckets and within the passage, the axial gap extending straight from the first axial end to the second axial end of the turbine axially unobstructed.

22. The turbine of claim 19, wherein adjacent vanes of the plurality of vanes do not overlap each other in an axial direction parallel to the center axis of rotation.