Backfeed stage, radial turbo fluid energy machine

Patent metadata

Field	Value
Publication number	US-10422346-B2
Application number	US-201716079625-A
Country	US
Kind code	B2
Filing date	Mar 1, 2017
Priority date	Mar 1, 2016
Publication date	Sep 24, 2019
Grant date	Sep 24, 2019

Abstract

A backfeed stage of a radial turbo fluid energy machine for deflecting a flow direction of a process fluid issuing from a rotor, rotating around an axis, from radially outward to radially inward, having a backfeed duct which has three adjacent sections in the flow direction, wherein a first section is designed for conducting the process fluid radially outward, wherein a second section is designed for deflecting the process fluid from the radially outward to radially inward direction, wherein a third section is designed for conducting the process fluid radially inward, wherein the second section and third section, or only the third section, have/has first guide vanes which define flow passages of the backfeed duct in relation to each other in the circumferential direction.

First claim

The invention claimed is:

1. A backfeed stage of a radial turbo fluid energy machine for deflecting a flow direction of a process fluid issuing from a rotor, rotating around an axis, from radially outward to radially inward, comprising:
a backfeed duct, which has three adjacent sections in the flow direction,
wherein a first section is designed for conducting the process fluid radially outward,
wherein a second section is designed for deflecting the process fluid from radially outward to radially inward,
wherein a third section is designed for conducting the process fluid radially inward,
wherein the second section and the third section, or only the third section, have/has first guide vanes which define flow passages of the backfeed duct in relation to each other in the circumferential direction,
wherein the second section and the third section, or only the third section, have/has second guide vanes which are offset downstream by leading edges in relation to leading edges of the first guide vanes, which second guide vanes define flow passages of the backfeed duct in relation to each other in the circumferential direction,
wherein the second guide vanes are designed and arranged in such a way that in a radially extending plane in the region of the axial extent of the third section a connecting line through two trailing edges of adjacent first guide vanes is not divided in the middle by a radial line through the leading edge of a second guide vane which is arranged between the two first guide vanes in the circumferential direction,
wherein the first guide vanes each have a concave pressure side and a convex suction side and each flow passage in the region of the first guide vanes is defined by a pressure side of a first guide vane and a suction side of another adjacent first guide vane,
wherein the second guide vane which is arranged downstream between the two first guide vanes is arranged closer to the suction side of the other adjacent first guide vane in the circumferential direction, and
wherein a bend length (BLD) in the circumferential direction of the distance between the two trailing edges of adjacent first guide vanes is divided by the radial line through the leading edge of the second guide vane which is arranged between the two first guide vanes in the circumferential direction into a pressure-side section (PSD) and a suction-side section (SSD), wherein 0.2<SSD/BLD<0.4 applies.

2. The backfeed stage as claimed in claim 1 ,
wherein the first guide vanes and the second guide vanes are fixedly and immovably connected to a stator.

3. A radial turbocompressor comprising:
the backfeed stage as claimed in claim 1 .

4. The backfeed stage as claimed in claim 1 ,
wherein the radial turbo fluid energy machine comprises a radial turbocompressor.

Assignees

• Siemens Ag

Inventors

• Hermes Viktor

Classifications

• F04D29/666

  by means of rotor construction or layout, e.g. unequal distribution of blades or vanes · 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

• F04D29/444 Primary

  Bladed diffusers · CPC title

• F04D29/053

  Shafts · CPC title

• F04D29/4213

  suction ports · CPC title