US20160061212A1

US20160061212A1 - Radial compressor stage

Info

Publication number: US20160061212A1
Application number: US14/842,397
Authority: US
Inventors: Thomas MOKULYS; Philipp JENNY; Christof SEEBASS-LINGGI; Yves BIDAUT; Samuel Schneider
Original assignee: MAN Diesel and Turbo SE
Current assignee: MAN Energy Solutions SE
Priority date: 2014-09-02
Filing date: 2015-09-01
Publication date: 2016-03-03
Also published as: RU2015135375A3; EP2993356A1; JP2016053359A; RU2015135375A; RU2667736C2; CN105387001A; DE102014012764A1

Abstract

A radial compressor stage includes: an impeller, rotatable relative to a stator, the impeller having multiple impeller blades on a rotor side; a diffuser positioned in a flow direction downstream of the impeller, the diffuser having multiple guide blades on the stator side; an impeller side gap formed between the impeller and the stator; and an intermediate flow channel extending between the impeller and the diffuser. A gap is formed between an outer edge of a downstream back side of the impeller and an opposite inner edge of the stator, the gap being sealed via a seal such that the seal seals the impeller side gap from the intermediate flow channel.

Description

BACKGROUND OF THE INVENTION

1. Field of the Invention
The invention relates to a radial compressor stage for a radial compressor.
2. Description of the Related Art
From DE 195 02 808 C2 the fundamental construction of a radial compressor having at least one radial compressor stage is known. Accordingly, it is disclosed in this prior art that the, or each, radial compressor stage of a radial compressor comprises an impeller rotating with respect to a stator, wherein the impeller comprises a hub and multiple impeller blades on the rotor side. Each impeller blade of the impeller comprises a flow inlet edge and a flow outlet edge, wherein between the flow inlet edge and the flow outlet edge of each impeller blade a suction side, a pressure side and an outer surface facing the stator extends, wherein the outer surface of the respective impeller blade borders the stator and serves for sealing relative to the stator. Such an impeller of a radial compressor, in which the outer surfaces of the impeller blades directly border the stator, does not comprise a shroud and is also called an open impeller. The impeller blades are positioned in an impeller flow channel that is bounded by the hub of the impeller and the stator.
Furthermore it is known from DE 195 02 808 C2 that the radial compressor stage comprises a diffuser positioned downstream of the impeller, which comprises multiple guide blades on the stator side. Each guide blade of the diffuser has a flow inlet edge and a flow outlet edge, wherein between the flow inlet edge and the flow outlet edge of each guide blade a suction side and a pressure side extends. The guide blades are positioned in a diffuser flow channel bounded by the stator.
From DE 195 02 802 C2 it is evident that between the impeller and the stator of the radial compressor stage shown there, a so-called impeller side gap is formed, namely between a back side of the impeller and the stator. This impeller side gap is connected to an intermediate flow channel that extends between the impeller flow channel and the diffuser flow channel.
A further radial compressor stage with such an impeller side gap is known from DE 10 2007 019 264 A1.
From EP 2 014 925 A1 a radial compressor stage with a diffuser is known, in which the angular spacing of flow inlet edges of two guide elements arranged adjacent to one another differs from the angular spacing of flow inlet edges of two other guide elements arranged adjacent to one another.
During the operation of a radial compressor, the radial compressor stages are exposed to mechanical excitations and oscillations, which can cause damage to the radial compressor stage, in particular to the impeller blades of the impeller of the radial compressor stage. Such mechanical excitations can be based on synchronous excitation mechanisms and on asynchronous excitation mechanisms.
In particular, three-dimensional and unsteady flow phenomena are generated through the interaction of rotating and stationary components. Under certain conditions, pressure fluctuations develop which have a character rotating in direction of rotation or in a direction that is opposite to the direction of rotation. The number and the rotating speed of these pressure fluctuations are arbitrary.
This phenomenon is the basis of an asynchronous excitation of open impellers in radial compressors. Up to now, no methods are known that can specifically counteract such asynchronous excitations in order to avoid a critical vibration excitation, in particular of the impeller blades of the impeller.
There is therefore a need for a radial compressor stage for a radial compressor, in which in particular the impeller blades of the impeller are exposed to low vibration excitation in particular through such asynchronous excitations.

SUMMARY OF THE INVENTION

Starting out from this, it is an object of the present invention to create a radial compressor stage for a radial compressor that fulfils the above requirements and accordingly is exposed to a low vibration excitation in particular through such asynchronous excitations.
According to a first aspect of the invention, this object is solved through a radial compressor stage such that a gap, which is formed between an outer edge of the downstream back side of the impeller and an opposite edge of the stator, is sealed via a seal in such a manner that the seal seals the impeller side gap from an intermediate flow channel extending between the impeller and the diffuser.
According to a second aspect of the invention, this object is solved through a radial compressor stage such that a gap, which is formed between an outer edge of a downstream back side of the impeller and an opposite inner edge of the stator, seen in circumferential direction, has a varying gap dimension.
With each of the two above aspects according to the invention, asynchronous excitations of open impellers in radial compressors can be easily and reliably counteracted, as a result of which the vibration excitation in particular for the impeller blades of the impeller of the radial compressor stage can be reduced. The aspects according to the invention are alternatively employed on a radial compressor stage.
The two above aspects according to the invention concern measures that relate to the coupling of the impeller side gap to the intermediate flow channel extending between the impeller flow channel and the diffuser flow channel. The vibration excitation for the impeller blades of the impeller of the radial compressor stage can be reduced.
According to an advantageous further development of the first and/or second aspect according to the invention it is provided that the flow inlet edges of the guide blades of the diffuser on the stator side lie on a first circle contour in such a manner that the flow inlet edges of all guide blades on the stator side have an identical spacing from the flow inlet edges of the respective adjacent guide blades. The flow outlet edges of the guide blades of the diffuser on the stator side lie on a second circle contour in such a manner that in at least one first circumferential position the flow outlet edge of the respective guide blade on the stator side has a spacing from the flow outlet edge of at least one adjacent guide blade other than in second circumferential positions.
According to a further advantageous further development of the first and/or second aspect according to the invention it is provided that at least one guide blade of the diffuser on the stator side has a curvature which deviates from the other guide blades on the stator side.
According to a further advantageous development of the first and/or second aspect of the invention it is provided that in at least one first circumferential position a diffuser flow channel section formed between adjacent guide blades of the diffuser on the stator side has a flow cross section that deviates with respect to the diffuser flow channel sections formed in second circumferential positions.
The above advantageous further developments of the first and/or second aspect according to the invention relate to measures for the design configuration of the diffuser.
Particularly preferred is a radial compressor stage on which one of the aspects according to the invention, which relate to the coupling of the impeller side gap to the intermediate flow channel, combined with at least one of the advantageous further developments, which relate to the configuration of the diffuser, are employed.
Other objects and features of the present invention will become apparent from the following detailed description considered in conjunction with the accompanying drawings. It is to be understood, however, that the drawings are designed solely for purposes of illustration and not as a definition of the limits of the invention, for which reference should be made to the appended claims. It should be further understood that the drawings are not necessarily drawn to scale and that, unless otherwise indicated, they are merely intended to conceptually illustrate the structures and procedures described herein.

BRIEF DESCRIPTION OF THE DRAWINGS

Preferred further developments of the invention are obtained from the following description. Exemplary embodiments of the invention are explained in more detail with the help of the drawings without being restricted to this. In the drawings:

FIG. 1: shows a meridional section of a radial compressor stage according to the invention according to a first aspect of the invention;

FIG. 2: shows a meridional section of a further radial compressor stage according to the invention according to the first aspect of the invention;

FIG. 3: shows a meridional section of a radial compressor stage according to the invention according to a second aspect of the invention;

FIG. 4: shows an axial section through the radial compressor stage of FIG. 3;

FIG. 5: shows an axial section through a radial compressor stage for illustrating a first advantageous further development of the first and/or second aspect according to the invention;

FIG. 6: shows an axial section through a radial compressor stage for illustrating a second advantageous further development of the first and/or second aspect according to the invention; and

FIG. 7: shows a meridional section through a radial compressor stage for illustrating a third advantageous further development of the first and/or second aspect according to the invention.

DETAILED DESCRIPTION OF THE PRESENTLY PREFERRED EMBODIMENTS

The present invention relates to a radial compressor with at least one radial compressor stage.
FIG. 1 shows a detail of a radial compressor stage according to the invention in meridional section according to a first aspect of the invention.
The radial compressor stage of FIG. 1 comprises an impeller 10 with multiple impeller blades 11 on the rotor side. The impeller 10 rotates relative to the stator 12. The stator 12 can be a housing or a stator ring or the like. The impeller blades 11 are positioned in an impeller flow channel 13 which is bounded by a hub contour 14 on the rotor side and a stator contour 15. Each impeller blade 12 comprises a flow inlet edge 16 and a flow outlet edge 17. Between the flow inlet edge 16 and the flow outlet edge 17 of each impeller blade 11 a pressure side, a suction side and radially outside on the impeller blade 11 an outer surface 18 of the respective impeller blade 11 facing the stator 12 extends. The outer surface 18 of the impeller blade 11 borders the stator 12 and serves for sealing relative to the stator 12. Such an impeller 10, in the case of which the outer surfaces 18 of the impeller blades 11 indirectly border the stator 12, does not have a shroud and is also called an open impeller.
According to FIG. 1, a diffuser 19 on the stator side is positioned downstream of the impeller 10. The diffuser 19 comprises multiple guide blades 20 on the stator side. The guide blades 20 of the diffuser 19 on the stator side are positioned in a diffuser flow channel 21 bounded by the stator 12, wherein each of the guide blades 20 of the diffuser 19 on the stator side comprises a flow inlet edge 22 and a flow outlet edge 23. Between the flow inlet edge 22 and the flow outlet edge 23 of the respective guide blade 20 on the stator side a suction side 24 and a pressure side 25 of the respective guide blade extends. (See FIG. 5.)
Between the impeller flow channel 13, in which the impeller blades 11 of the impeller 10 on the rotor side are positioned, and the diffuser flow channel 21, in which the guide blades 20 of the diffuser 19 on the stator side are positioned, an intermediate flow channel 26 extends, via which medium compressed in the radial compressor stage starting out from the impeller 10 can flow in the direction of the diffuser 16. According to FIG. 1, an impeller side gap 28 is formed between a back side 27 of the impeller 10 and the stator 12, wherein this impeller side gap 28 according to FIG. 1 is coupled to the intermediate flow channel 26 via a gap 34.
The details of a radial compressor stage described above making reference to FIG. 1 count among the prior art. The invention now relates to such details of a radial compressor stage with the help of which the danger of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers, can be reduced.
According to a first aspect of the invention (see FIG. 1, 2) it is proposed that the gap 34, which is formed between an outer edge 35 of the downstream back side 27 of the impeller 10 and an opposite inner edge 36 of the stator 12, and via which the impeller side gap 28 is coupled to the intermediate flow channel 26, is sealed via a seal 37.
Accordingly, the seal 37 seals the impeller side gap 28 from the intermediate flow channel 26 running between the impeller 10 and the diffuser 19. For this purpose, a honeycomb-shaped seal 37 is employed in the exemplary embodiment of FIG. 1, which is supported by the stator 12 and is located opposite the outer edge 35 of the downstream back side 27 of the impeller 10. Through such sealing of the gap 34 and thus of the impeller side gap 28 relative to the intermediate flow channel 26 the danger of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers, can be reduced.
FIG. 2 shows a configuration of a radial compressor stage according to the first aspect of the present invention, which differs from the exemplary embodiment of FIG. 1 by the specific configuration of the seal 37. Accordingly, no honeycomb seal is employed in FIG. 2. Rather, the seal in the exemplary embodiment of FIG. 2 is designed as a lip-type seal, with which accordingly a sealing lip 38 comes to lie against the outer edge 35 of the downstream back side 27 of the impeller 10. This sealing element 37 of FIG. 2 can, for example, be a wiping seal or touch seal or a brush seal.
A radial compressor stage according to a second aspect of the invention is shown in FIGS. 3 and 4. According to the second aspect of the invention it is proposed that the gap 34, via which the impeller side gap 28 is coupled to the intermediate flow channel 26, seen in circumferential direction, has a varying gap dimension. To this end, the inner edge 36′ of the stator 12 located opposite the outer edge 35 of the downstream back side 27 of the impeller 10 is contoured wavelike according to the dashed line course of FIG. 4, so that accordingly seen in circumferential direction the spacing between the inner edge 36′ of the stator 12 and of the outer edge 35 of the downstream back side 27 of the impeller 10 is not constant, but rather variable.
Through the wavelike contour of the inner edge 36′ of the stator 12, this gap dimension of the gap 34 that is variable in circumferential direction preferentially varies steadily, i.e., not step-like.
The above measures according to the first aspect of the invention and according to the second aspect of the invention are alternatives. Thus, these measures are not employed in combination with one another.
According to a first advantageous further development of the first aspect and/or second aspect of the invention it is provided (see FIG. 5) that all flow inlet edges 22 of all guide blades 20 of the diffuser 19 on the stator side lie on a first circle contour 29.
Here, the flow inlet edges 22 of the guide blades 20 of the diffuser 19 on the stator side lie on the first circle contour 29 such that the flow inlet edges 22 of all guide blades 20 on the stator side have an identical spacing from the flow inlet edges 22 of the respective adjacent guide blades 20. The flow inlet edges 22 of the guide blades 20 of the diffuser 19 located seen in circumferential direction of the diffuser flow channel 21 next to one another are accordingly evenly distributed seen in circumferential direction, so that accordingly all flow inlet edges 22, which lie on the first circle contour 29, have identical circumferential distances to adjacent flow inlet edges 22.
According to the first advantageous further development of the first aspect and/or second aspect of the invention it is provided, furthermore, that the flow outlet edges 23 of the guide blades 20 of the diffuser 19 on the stator side lie on a second circle contour 30.
Here, the flow outlet edges 23 of the guide blades 20 of the diffuser 19 on the stator side lie on the second circle contour 30 such that, in at least one first circumferential position of the diffuser flow channel 21, the flow outlet edge 23 of the respective guide blade 20 on the stator side positioned there has a distance from the flow outlet edge of at least one adjacent guide blade 20 other than in second circumferential positions of the diffuser flow channel 21.
Accordingly, in the region of the flow outlet edges 23, no equal distribution of the flow outlet edges 23 is provided seen in circumferential direction of the diffuser flow channel 21. On the contrary, the equal distribution of the flow outlet edges 23, which all lie on the second circle contour 30, is preferentially cancelled in the first circumferential positions in order to thereby reduce the risk of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers.
According to the first advantageous further development of the first aspect and/or second aspect of the invention it is possible in a first extreme case that the corresponding flow outlet edge 23 in a single circumferential position of the diffuser flow channel 21 has another distance from the respective adjacent flow outlet edges 23, that by contrast in the other circumferential positions the flow outlet edges 23 with respect to their circumferential positions are equally distributed.
It is likewise possible according to the first advantageous further development of the first aspect and/or second aspect of the invention in a second extreme case that in all circumferential positions of the diffuser flow channel 21 the flow outlet edges 23 have different distances in each case from the respective adjacent flow outlet edges 23.
In the second circumferential positions of the diffuser flow channel 21, the respective guide blades 20 of the diffuser 19 on the stator side preferentially all have identical, second stepping angles.
The guide blades 20 on the stator side positioned in the, or each, first circumferential position by contrast preferentially have a first stepping angle, which deviates from the second stepping angle, in particular by plus minus ±10°, preferably by plus minus ±7°, particularly preferably by ±5°, most preferably by ±3°.
According to the first advantageous further development of the first aspect and/or second aspect of the invention it is accordingly proposed for reducing the danger of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers, to reposition the flow outlet edges 23 of selected guide blades 20 of the diffuser 19 on the stator side in circumferential direction, preferentially subject to cancelling or interrupting the flow outlet edges 23 which, seen in the circumferential direction of the diffuser flow channel 21, are otherwise equally distributed.
In an extreme case, the flow outlet edges 23 of all guide blades 20 of the diffuser 19 on the stator side can have different distances from the respective adjacent flow outlet edges 23.
As is evident in FIG. 5, a flow outlet edge 23″ (see dashed line course of the in FIG. 5 right guide blade) in the direction of the pressure side 25 of the respective adjacent guide blade 20 or a flow outlet edge 23′ (see dashed line course of the in FIG. 5 left guide blade) can be relocated in circumferential direction in the direction of the suction side 24 of the respective adjacent guide blade 20 in such a manner that all flow outlet edges 23 as before still lie on the second circle contour 30.
This corresponds to a change of the stepping angle of the guide blades 20 of the diffuser 19 on the stator side in selected circumferential positions. In selected second circumferential positions of the diffuser 19, the respective guide blades 20 on the stator side have deviating stepping angles.
Those selected guide blades 20 which, compared with the remaining guide blades 20 on the stator side, have a different stepping angle are characterized in that their stepping angle deviates in particular by ±10°, and particularly preferably by ±5° from the stepping angles of the remaining guide blades 20 of the diffuser 19.
Through the above measures of the first advantageous further development of the first aspect and/or second aspect of the invention, a slightly higher or a slightly lower loading can be imposed on the guide blades 20 of the diffuser 19 in defined circumferential positions at uneven circumferential distances. The danger of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers, can thereby be further reduced.
According to a second advantageous further development of the first aspect and/or second aspect of the invention (see FIG. 6), it is proposed for reducing the danger of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers, that both the flow inlet edges 22 of the guide blades 20 of the diffuser 19 on the stator side positioned on the first circle contour 29 as well as the flow outlet edges 23 of the guide blades 20 of the diffuser 19 on the stator side positioned on the second circle contour 30 are equally distributed, i.e., in each case have identical circumferential distances.
According to the second advantageous further development of the first aspect and/or second aspect of the invention, however, at least one guide blade 20 of the diffuser 19 on the stator side has a deviating curvature between the flow inlet edge 22 and the flow outlet edge 23, namely a suction side 24′ and a pressure side 25′ with a curvature deviating relative to the other guide blades 20. This is shown in FIG. 6 by the dashed line course for the middle guide blade 20.
According to the second advantageous further development of the first aspect and/or second aspect of the invention, it is possible in a first extreme case that exclusively a single guide blade 20 of the diffuser 19 on the stator side has a deviating curvature, that by contrast all other guide blades 20 of the diffuser 19 on the stator side have identical curvatures.
According to the second advantageous further development of the first aspect and/or second aspect of the invention, it is likewise possible in a second extreme case that all guide blades 20 of the diffuser 19 on the stator side have curvatures that deviate from one another.
It is preferable to employ on the radial compressor stage the above first advantageous further development and the above second advantageous further development combined with the first aspect or the second aspect of the invention to reduce the danger of unsteady flow phenomena which can lead to an asynchronous excitation of the open impellers.
A third advantageous further development of the first aspect and/or second aspect of the invention is discussed in the following making reference to FIG. 7.
According to the third advantageous further development of the first aspect and/or second aspect of the invention, it is proposed, for reducing the danger of unsteady flow phenomena, which can lead to an asynchronous excitation of the open impellers, to change a diffuser flow channel section 33 formed between adjacent guide blades 20 of the diffuser 19 on the stator side in at least one first circumferential position of the diffuser flow channel 21 such that the same compared with the diffuser flow channel sections formed in second circumferential positions has a deviating flow cross section.
Accordingly it is evident from FIG. 7 that in a first circumferential position of the diffuser 19 between adjacent guide blades 20 on the stator side the respective diffuser flow channel section 33 has a reduced flow cross section, namely because of the fact that sidewalls 31, 32 on the stator side bounding the respective diffuser flow channel section 33 are curved towards the inside subject to reducing the flow cross section of the respective diffuser flow channel section 33. Even merely one of these sidewalls 31, 32 on the stator side bounding the respective diffuser flow channel section 33 can be curved into the respective diffuser flow channel section 33. It is likewise possible in selected circumferential positions to widen the respective diffuser flow channel section with respect to its flow cross section, whereby at least one of these sidewalls 31, 32 is then curved outwardly into the stator 12.
According to the third advantageous further development of the first aspect and/or second aspect of the invention, it is possible in a first extreme case that exclusively in a single circumferential position of the diffuser flow channel 21 the corresponding diffuser flow channel section 33 has a deviating flow cross section, but by contrast all other diffuser flow channel sections 33 have identical flow cross sections. According to the third advantageous further development of the first aspect and/or second aspect of the invention it is likewise possible in a second extreme case that in all circumferential positions of the diffuser flow channel 21 the diffuser flow channel sections 33 each have different flow cross sections.
The measures of the third advantageous further development can be employed combined with the measures of the first advantageous further development and/or the measures of the second advantageous further development combined with the first or the second aspect of the invention. Preferably, the measures of all three advantageous further developments are employed on a radial compressor stage combined with the first aspect or the second aspect.
Thus, while there have been shown and described and pointed out fundamental novel features of the invention as applied to a preferred embodiment thereof, it will be understood that various omissions and substitutions and changes in the form and details of the devices illustrated, and in their operation, may be made by those skilled in the art without departing from the spirit of the invention. For example, it is expressly intended that all combinations of those elements and/or method steps which perform substantially the same function in substantially the same way to achieve the same results are within the scope of the invention. Moreover, it should be recognized that structures and/or elements and/or method steps shown and/or described in connection with any disclosed form or embodiment of the invention may be incorporated in any other disclosed or described or suggested form or embodiment as a general matter of design choice. It is the intention, therefore, to be limited only as indicated by the scope of the claims appended hereto.

LIST OF REFERENCE NUMBERS

10 Impeller
11 Impeller blade
12 Stator
13 Impeller flow channel
14 Hub contour
15 Stator contour
16 Flow inlet edge
17 Flow outlet edge
18 Outer surface
19 Diffuser
20 Guide blade
21 Diffuser flow channel
22 Flow inlet edge
23 Flow outlet edge
24 Suction side
25 Pressure side
26 Intermediate flow channel
27 Back side
28 Impeller side gap
29 Circle contour
30 Circle contour
31 Sidewall
32 Sidewall
33 Diffuser flow channel section
34 Gap
35 Outer edge
36 Inner edge
37 Seal
38 Sealing lip

Claims

What is claimed is:

1. A radial compressor stage comprising:

an impeller (10), rotating relative to a stator (12), the impeller (10) having multiple impeller blades (11) on a rotor side;

a diffuser (19) positioned in a flow direction downstream of the impeller (10), the diffuser (19) having multiple guide blades (20) on the stator side;

an impeller side gap (28) formed between the impeller (10) and the stator (12); and

an intermediate flow channel (26) extending between the impeller (10) and the diffuser (19), wherein a gap (34) is formed between an outer edge (35) of a downstream back side (27) of the impeller (10) and an opposite inner edge (36) of the stator (12), the gap (34) being sealed via a seal (37) such that the seal (37) seals the impeller side gap (18) from the intermediate flow channel (26).

2. The radial compressor stage according to claim 1, wherein the seal (37) is supported by the stator (12) and is located opposite the outer edge (35) of the downstream back side (27) of the impeller (10).

3. A radial compressor stage comprising:

an impeller (10), rotatable relative to a stator (12), the impeller (10) having multiple impeller blades (11) on a rotor side;

a diffuser (19) positioned in a flow direction downstream of the impeller (10), the diffuser having multiple guide blades (20) on the stator side; and

an impeller side gap (28) formed between the impeller (10) and the stator (12),

wherein a gap (34) is formed between an outer edge (35) of a downstream back side (27) of the impeller (10) and an opposite inner edge (36) of the stator (12), the gap (34), seen in a circumferential direction, has a varying gap dimension.

4. The radial compressor stage according to claim 3, wherein the inner edge (36) of the stator (12), seen in a circumferential direction, has a wavelike contour.

5. The radial compressor stage according to claim 1, wherein

the guide blades (20) have flow inlet edges (22) on the stator side, wherein the flow inlet edges (22) lie on a first circle contour (29) such that the flow inlet edges (22) of all guide blades (20) on the stator side have an identical distance from the flow inlet edges (22) of the respective adjacent guide blades (20); and

the guide blades (20) have flow outlet edges (23) on the stator side, wherein the flow outlet edges (23) lie on a second circle contour (30), such that in at least one first circumferential position the flow outlet edge (23) of the respective guide blade (20) on the stator side has a distance to the flow outlet edge (23) that is different from the distance to the flow outlet edge (23) of at least one adjacent guide blade (20) in second circumferential positions.

6. The radial compressor stage according to claim 5, wherein

in the second circumferential positions the respective guide blades (20) on the stator side all have identical second stepping angles; and

in the, or each, first circumferential position the respective guide blades (20) on the stator side has a first stepping angle that deviates from the second stepping angle.

7. The radial compressor stage according to claim 6, wherein the first stepping angle deviates from the second stepping angle by ±10°.

8. The radial compressor stage according to claim 1, wherein at least one guide blade (20) on the stator side has a curvature that deviates from the other guide blades (20) on the stator side.

9. The radial compressor stage according to claim 1, further comprising a plurality of diffuser flow channel sections (33) each formed between adjacent guide blades (20) on the stator side, wherein in at least one first circumferential position a diffuser flow channel section (33) formed between adjacent guide blades (20) on the stator side has a flow cross section that deviates relative to the diffuser flow channel sections formed in second circumferential positions.

10. The radial compressor stage according to claim 9, wherein relative to the second circumferential positions in the, or each, first circumferential position between the adjacent guide blades (20) on the stator side at least one sidewall (31, 32) bounding the diffuser flow channel section (33) is curved inwardly into the diffuser flow channel section (33) so as to reduce the flow cross section and/or curved outwardly into the stator (12) subject so as to increase the flow cross section.

11. The radial compressor stage according to claim 6, wherein the first stepping angle deviates from the second stepping angle by ±7°.

12. The radial compressor stage according to claim 6, wherein the first stepping angle deviates from the second stepping angle by ±5°.