Return channels for a multi-stage turbocompressor

Patent metadata

Field	Value
Publication number	US-11519424-B2
Application number	US-201916685147-A
Country	US
Kind code	B2
Filing date	Nov 15, 2019
Priority date	Jun 27, 2017
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

A return geometry fluidically connects a first and a second compressor stage of the turbocompressor. The return geometry has multiple partial helices that are evenly or unevenly distributed in the circumferential direction. The multiple partial helices extend at least in part in the circumferential direction. They form flow channels that extend at least in some sections, separately from each other, to fluidically connect the first and second compressor stages.

First claim

What is claimed is:

1. A turbocompressor return geometry fluidically connecting a first and a second compressor stage of the turbocompressor, the return geometry comprises:
multiple partial flow channels are arranged evenly or unevenly distributed in the circumferential direction, the multiple partial flow channels extend at least in part in the circumferential direction and the multiple partial flow channels extending at least in some sections separately from each other for fluidically connecting the first and second compressor stages;
the flow channels extend from an inlet region that can be associated with the first compressor stage to an outlet region that can be associated with the first compressor stage and merge in the outlet region to form a circumferentially symmetrical overall channel; and
in a transition to the overall channel, the individual flow channels in each case includes curved portions and curved struts, on the curved portions, extending from the curved portions into the flow channels that are designed to impart a vortex to the flow as it enters the overall channel, so that the flow at the outlet region into the second compressor stage has a predefined vortex.

2. The return geometry according to claim 1 , wherein the flow channels form multiple successively arranged bends that multiply deflect the flow between the first and second compressor stages.

3. The return geometry according to claim 2 , wherein the bends of the flow channels guide the flow from a radial outflow direction into a first axial direction in the direction of the second compressor stage and subsequently back into a radial inflow direction that runs counter to the outflow direction.

4. The return geometry according to claim 3 , wherein, subsequently to the inflow direction, one of the bends of the flow channels guides the flow into a second axial direction that runs counter to the first axial direction.

5. The return geometry according to claim 4 , wherein, after the bends that guide the flow into the second axial direction, the flow channels merge in flow direction to form the overall channel.

6. The return geometry according to claim 3 , wherein the bend formed in each case in the flow channels, that deflects the flow from the radial outflow direction into the first axial direction in the direction of the second compressor stage, in each case has a guide strut that extends along the respective flow channel in a radial direction outward and into the first axial direction.

7. The return geometry according to claim 3 , wherein the flow channels in which the flow is guided into the first axial direction in the direction of the second compressor stage, have an axial section, and the axial section of the flow channels is designed as a diffuser.

8. The return geometry according to claim 1 , wherein a spacer housing of the turbocompressor that separates the first compressor stage from the second compressor stage.

9. The return geometry according to claim 8 , wherein the flow channels are formed by the spacer housing and a turbocompressor housing, the flow channels are formed by a channel clearance between an outer surface of the spacer housing and an inner wall surface of the turbocompressor housing.

10. The return geometry according to claim 8 , wherein the spacer housing has an axial opening for receiving the compressor impeller of the first compressor stage with an axial opening radius R 1 , and the flour channels extend starting from a tongue radius R 2 of the spacer housing, the tongue radius is greater than the axial opening radius R 1 by the factor of 1.4-1.8.

11. The return geometry according to claim 10 , wherein the flow channels extend radially outward in the circumferential direction at an inlet of the flow channels, that is determined by the tongue radius R 2 , at an angle a 3 =60°-80° with respect to a radial plane.

12. The return geometry according to Claire 13 , wherein a ratio of the extension (a 1 ) of the flow channels in circumferential direction with respect to adjoining circumferential sections (a 2 ) without flow channels is formed so that 0.2≤a 1 /(a 1 +a 2 )≤0.5.

13. The return geometry according to claim 1 , wherein at least two of the flow channels for fluidically connecting the first and second compressor stages have a different overall flow cross section.

14. A turbocompressor of radial design with a return geometry fluidically connecting a first and a second compressor stage of the turbocompressor, the return geometry comprises:
multiple partial flow channel arranged evenly or unevenly distributed in the circumferential direction, the multiple partial flow channel extend at least in part in the circumferential direction and the multiple partial flow channels extending at least in some sections separately from each other for fluidically connecting the first and second compressor stages;
the flow channels extend from an inlet region that can be associated with the first compressor stage to an outlet region that can be associated with the first compressor stage and merge in the outlet region to form a circumferentially symmetrical overall channel; and
in a transition to the overall channel, the individual flow channels in each case includes curved portions and curved struts, on the curved portions, extending from the curved portions into in the flow channels that are designed to impart a vortex to the flow as it enters the overall channel, so that the flow at the outlet region into the second compressor stage has a predefined vortex.

Assignees

• Ebm Papst Mulfingen Gmbh & Co Kg

Inventors

• Engert Markus
• Klostermann Angelika
• Conrad Daniel

Classifications

• F04D29/30

  Vanes · CPC title

• F04D17/12

  Multi-stage pumps · CPC title

• F04D29/444 Primary

  Bladed diffusers · CPC title

• F04D17/122

  the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors · CPC title

• F04D29/441

  especially adapted for elastic fluid pumps · CPC title