Stabilizer passage of the compressor

Abstract

The invention relates to a stabilizer channel (10), in particular a stabilizer channel (10) of a radial compressor or a diagonal compressor, having an annular stabilizer chamber (12) which surrounds a main flow channel (13) in the inlet region of a compressor impeller (21), and which is delimited with respect to the main flow channel (13) by an annular web (14). The annular stabilizer channel (12) is connected to the main flow channel (13) via a downstream flow inlet (15) and an upstream flow outlet (16). At least one separating element (T) is arranged in at least one of the flow inlet (15) and the flow outlet (16) such that the inflow into the annular stabilizer chamber (12) and / or the outflow out of the annular stabilizer chamber (12) is / are laterally separated with respect to the main flow direction (1) of the main flow channel (13). Furthermore, at least one flow guiding element (17) is arranged in at least one of the flow inlet (15) and the flow outlet (16). In addition, the invention relates to a compressor, in particular a radial compressor or a diagonal compressor, comprising a stabilizer channel according to the invention, and to a turbine, in particular a turbocharger, comprising such a compressor.

Description

Technical Field

[0001] The present invention relates to the field of compressors, in particular radial compressors and diagonal compressors. In particular, the present invention relates to a stabilizer channel at the compressor inlet for improving the map width and the characteristic curve slope of a compressor stage. Background Art

[0002] Exhaust gas turbochargers are used to increase the power of internal combustion engines, in particular reciprocating piston engines. In this context, exhaust gas turbochargers typically have a radial or diagonal compressor and a radial or axial turbine.

[0003] The operating range of radial and diagonal compressors is limited by the surge limit / flow instability at low mass flow rates: when the compressor is throttled, the angle of incidence deteriorates gradually until flow separation and surge occur. The range of allowable angles of incidence where the flow still remains attached decreases with increasing flow Mach number. This means that in the case of stages with high pressure ratios and / or high absorption capacities, the map width tends to decrease.

[0004] As a characteristic curve stabilization measure, a bypass in the form of an annular cavity can be provided in the compressor housing above the impeller profile of the compressor impeller and parallel to the intake pipe. Such a bypass is also referred to as a stabilizer chamber or a recirculator. By using a recirculator, the mass flow rate at the compressor impeller inlet can be artificially increased near the surge limit. Some of the mass flow is diverted from the compressor impeller into the side chamber (bypass). This mass flow has a strong swirl component (in the direction of rotation of the impeller - co - rotating swirl). This co - rotating swirl results in a reduction of the work conversion in the compressor, and thus in a flattened characteristic curve near the surge limit.

[0005] In applications with pressure pulsations (e.g., due to valve movements in a supercharged internal combustion engine), a flattened characteristic curve near the surge limit can lead to unexpected surges. For this reason, a minimum pressure increase is required between the surge limit point of the operating speed characteristic and the operating point. Due to the high work conversion and the flattened work coefficient curve at constant mass flow rate, this requirement can hardly be met in stages with high pressure ratios and conventional bypass / stabilizer channels. Summary of the Invention

[0006] It is an object of the present invention to provide a stabilizer channel for a compressor, in particular for a radial compressor or a diagonal compressor, which is improved at least in one of the disadvantages known from the prior art. Furthermore, it is an object of the present invention to provide an improved compressor and an improved turbine, in particular an improved turbocharger.

[0007] To achieve the above object, a stabilizer passage of a compressor as described in independent claim 1 is provided, in particular a stabilizer passage of a radial compressor or a diagonal compressor. In addition, a compressor having a stabilizer passage according to an embodiment described herein and a turbine, in particular a turbocharger, having such a compressor are provided.

[0008] Other aspects, advantages and features of the present invention can be found in the dependent claims, the description and the drawings.

[0009] According to one aspect of the present invention, a stabilizer passage of a compressor is provided, in particular a stabilizer passage of a radial compressor or a diagonal compressor. The stabilizer passage includes an annular stabilizer chamber that surrounds a main flow passage in an intake region of a compressor impeller. The annular stabilizer chamber is defined relative to the main flow passage by an annular web. The annular stabilizer chamber is connected to the main flow passage via a downstream flow inlet and an upstream flow outlet. At least one separation element is provided in at least one of the flow inlet and the flow outlet, such that the inflow into the annular stabilizer chamber and / or the outflow from the annular stabilizer chamber is / are laterally separated with respect to the main flow direction of the main flow passage. In addition, at least one flow guiding element is provided in at least one of the flow inlet and the flow outlet.

[0010] Thus, a stabilizer passage is advantageously provided, which can improve the mapping width and the characteristic curve slope of a compressor stage. In particular, for example by the flow guiding elements described herein, the combination of flow splitting and flow guiding in the flow inlet and / or the flow outlet has the advantage that the tip clearance vortices in the impeller (e.g., a compressor impeller) can be better affected by a more uniform suction compared to the prior art. By appropriately arranging separation elements in the flow inlet and / or the flow outlet, in particular when using additional flow guiding elements, the penetration depth of the tip clearance vortices can be reduced and their orientation can be advantageously affected. Compared with a conventional configuration that does not separate the inflow into the stabilizer chamber and / or the outflow from the stabilizer chamber, improved stability and / or higher efficiency can be achieved using the embodiments described herein.

[0011] According to a second aspect of the present invention, a compressor is provided, in particular a radial compressor or a diagonal compressor, including a compressor impeller and a stabilizer passage according to one of the embodiments described herein. In particular, the compressor impeller includes a number N1 of compressor impeller blades and a number N2 of guiding elements in at least one of the at least one flow guiding element in a region where the flow inlet enters the stabilizer passage, where the number N2 ≥ 1.5×N1.

[0012] Accordingly, it is possible to advantageously provide a compressor having an improved characteristic mapping width and characteristic curve slope, in particular a compressor that reduces noise and vibration generation during compressor operation.

[0013] A third aspect of the present invention relates to a turbine, in particular a turbocharger, having a compressor according to one of the embodiments described herein, thereby advantageously providing a turbocharger that is improved compared to the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The present invention will be explained below with reference to exemplary embodiments, which are shown in the drawings and from which additional advantages and modifications can be obtained. Here:

[0015] FIG. 1 shows a schematic view of a stabilizer channel according to the prior art;

[0016] Figure 2 shows a schematic view of a stabilizer channel according to an embodiment described herein;

[0017] Figure 3a shows a schematic view of a stabilizer channel according to a further embodiment described herein, wherein the stabilizer channel is integrated into an insert;

[0018] Figure 3b shows a schematic view of a stabilizer channel according to a further embodiment described herein, wherein the stabilizer channel is part of the compressor inner casing;

[0019] Figure 4 FIGS. 5 to 8 show schematic views of stabilizer channels according to further embodiments described herein;

[0020] Figure 9a shows a schematic view of the configuration of a flow guiding element for generating a flow reverse vortex during flow through the guiding element in a downstream inlet channel;

[0021] Figure 9b shows a schematic view of the configuration of a flow guiding element for generating a flow reverse vortex during flow through the guiding element in an upstream outlet channel;

[0022] Figure 10a shows a schematic view of the configuration of a flow guiding element for reducing flow vortices during flow through the guiding element in a downstream inlet channel; and

[0023] Figure 10b shows a schematic view of the configuration of a flow guiding element for reducing flow vortices during flow through the guiding element in an upstream outlet channel. DETAILED DESCRIPTION

[0024] The following is a detailed description of various embodiments, one or more examples of which are shown in each figure. Each example is for explanatory purposes and should not be construed as limiting. For example, features shown or described as part of one embodiment can be used on or in combination with any other embodiment to obtain additional embodiments. It is intended that the present disclosure should include such modifications and variations.

[0025] In the following description of the drawings, the same reference numerals refer to the same or similar components. Generally, only the differences regarding the respective embodiments are described. Unless otherwise stated, the description of a part or aspect in one embodiment can also relate to the corresponding part or aspect in another embodiment.

[0026] FIG. 1 shows a schematic view of a stabilizer channel 10 according to the prior art. In particular, FIG. 1 shows a cross-section through the housing of a radial compressor along the axis of rotation 11 of the compressor impeller 21, which radial compressor is used, for example, for compressing air in an exhaust gas turbocharger. A stabilizer chamber 12 is provided in the compressor housing 5. The stabilizer chamber 12 is connected to the main flow channel 13 via an inlet channel 3 and an outlet opening 4. The stabilizer chamber 12 is delimited relative to the main flow channel 13 by an annular web 14. Retaining ribs 121 are provided in the stabilizer chamber 12, which connect the annular web 14 to the compressor housing.

[0027] Referring Figure 2 to FIGS. 1 to 10, embodiments of a stabilizer channel of a compressor according to the present disclosure are described. The compressor can be a radial compressor or a mixed-flow compressor.

[0028] According to one embodiment, which can be combined with other embodiments described herein, as shown by way of example in Figure 2 , the stabilizer channel 10 includes an annular stabilizer chamber 12 that surrounds the main flow channel 13 in the intake region of the compressor impeller 21. In other words, the stabilizer channel 10 is typically provided at the compressor inlet. In this context, it should be noted that in the present disclosure, the "stabilizer channel" should be understood to refer, in particular, to a channel in the compressor inlet that is configured to improve the map width of the compressor stage. For example, the stabilizer channel 10 can be a recirculation channel.

[0029] The annular stabilizer chamber 12 is delimited relative to the main flow channel 13 by an annular web 14. The annular stabilizer chamber 12 is connected to the main flow channel 13 via a downstream flow inlet 15 and an upstream flow outlet 16. The annular stabilizer chamber 12 can be of rotationally symmetric design.

[0030] At least one separation element T is provided in at least one of the flow inlet 15 and the flow outlet 16. Figure 2An exemplary embodiment is shown with a separating element T which is arranged in the flow inlet 15 leading into the annular stabilizer chamber 12. Figure 8a and 8b An exemplary embodiment is shown with a separating element T which is arranged in the flow outlet 16 leading out of the annular stabilizer chamber 12.

[0031] The separating element is arranged such that the inflow into and / or the outflow from the annular stabilizer chamber 12 is / are laterally separated with respect to the main flow direction 1 of the main flow channel 13. In other words, the separating element T is configured and arranged such that the flow is separated. For example, at least one separating element T can be configured and arranged in the flow inlet 15 such that the inflow into the stabilizer chamber 12 is divided. Alternatively or additionally, at least one separating element T can be configured and arranged in the flow outlet 16 such that the outflow from the stabilizer chamber 12 is divided. Generally, the separating element is implemented in the form of a partition wall having a continuous partition wall surface. Alternatively, the separating element, in particular the partition wall, can have one or more holes such that the partition wall surface is partially interrupted.

[0032] Furthermore, as Figure 2 shown by way of example, at least one flow guiding element 17 is arranged in at least one of the flow inlet 15 and the flow outlet 16. For example, at least one flow guiding element 17 can be in the form of a helix. Generally, at least one flow guiding element 17 includes a plurality of flow guiding elements which are circumferentially arranged around the central axis 11 of the main flow channel 13. In particular, the plurality of flow guiding elements 17 can be coaxially arranged around the central axis 11 of the main flow channel 13.

[0033] In the present disclosure, the terms “downstream” and “upstream” refer to the main flow in the main flow channel in the intake region of the compressor impeller. For better understanding, the main flow direction 1 is given in the figure. According to one example, as Figure 2 shown, the flow inlet 15 of the stabilizer chamber can be arranged downstream of the inlet edge 24 of the compressor impeller 21. The flow outlet 16 of the stabilizer chamber is generally arranged upstream of the inlet edge 24 of the compressor impeller 21.

[0034] According to one embodiment which can be combined with other embodiments described herein, as Figure 2 shown by way of example, the stabilizer channel 10 is an integral part of the compressor housing. Alternatively, as Figure 3a shown by way of example, the stabilizer channel 10 can be integrated into an insert 22 which can be installed in the intake region of the compressor. According to another example, the stabilizer channel can be part of the inner compressor housing 20A, as Figure 3bShown by way of example, a compressor 20 having a compressor inner housing 20A and a compressor outer housing 20B is shown.

[0035] According to one embodiment that can be combined with other embodiments described herein, as Figures 2 to 7 shown by way of example, at least one separating element T is provided in the flow inlet 15 such that two or more downstream inlet channels 150 are provided. As can be seen from Figures 2 to 7 the two or more downstream inlet channels 150 are axially spaced apart.

[0036] For example, at least one of the two or more downstream inlet channels 150 can be designed differently from another or other inlet channels, as Figure 4 , 5a , shown by way of example in 5b and 7. In particular, at least one of the two or more downstream inlet channels is different from another or other inlet channels in terms of channel width and / or channel shape. For example, the inlet channel width of at least one inlet channel can be smaller than another or other inlet channels of the two or more downstream inlet channels. For illustration, Figure 5a an exemplary embodiment showing three inlet channels 151, 152, 153 with different channel widths w1, w2 and w3 is shown. Alternatively or additionally, at least one inlet channel can have a cross-sectional taper in the radial direction. For illustration, the second inlet channel 152 is shown in Figure 4 to have a cross-sectional taper 173. Note the fact that the two or more downstream inlet channels 150 can also be of the same construction.

[0037] In the present disclosure, the term "inlet channel" should be understood to represent a channel that serves as a flow inlet channel for entering the stabilizer chamber. Generally, as Figure 5b and Figure 7 shown by way of example, the inlet channels 150 described herein include an inlet opening 15A on the main flow channel side and an outlet opening 15B on the stabilizer chamber side.

[0038] According to one embodiment that can be combined with other embodiments described herein, at least one flow guiding element 17 is provided in each of at least two of the two or more downstream inlet channels 150. For example, at least one flow guiding element 17 can be designed to be different in one inlet channel of the two or more downstream inlet channels 150 from that in another inlet channel of the two or more downstream inlet channels 150, particularly in terms of quantity and / or shape. For illustration, Figure 5a a first set of flow guiding elements 171 in the first inlet channel 151 and a second set of flow guiding elements 172 in the second inlet channel 152 and the third inlet channel 153 respectively are shown.

[0039] According to one embodiment that can be combined with other embodiments described herein, two or more downstream inlet channels 150 extend substantially in the radial direction. In the present disclosure, the term "substantially radial" should be understood to mean an angular range of -45° ≤ α ≤ 45° or less, particularly -25° ≤ α ≤ 25° or less, with respect to the radial direction r. As shown by way of example in the accompanying drawings, the radial direction r extends perpendicular to the central axis 11. According to one example, "substantially radial" should be understood to mean an angular range of ±10° or less with respect to the radial direction r. For better understanding, the inlet channel 150 that is inclined at an angle α and falls within the definition of "substantially radial" given above is shown by way of example in Figure 6 which. The angle α is in the x-r plane.

[0040] According to one embodiment that can be combined with other embodiments described herein, as Figure 7 shown by way of example in, two or more downstream inlet channels 150 can include a portion 15C that extends substantially radially and a portion 15D that extends substantially axially. A curved transition region 15F is typically present between the portion 15C that extends substantially radially and the portion 15D that extends substantially axially.

[0041] According to one embodiment that can be combined with other embodiments described herein, as Figure 2 shown by way of example in, two or more downstream inlet channels 150 are provided between an upstream portion 141 of the annular web 14 and a downstream portion 142 of the annular web 14. The upstream portion 141 of the annular web 14 can have a first extension 18 that extends substantially in the radial direction, as Figure 4 shown by way of example. The downstream portion 142 of the annular web 14 can include a second extension 19A that extends substantially in the radial direction. Alternatively or additionally, for example, as Figure 7 shown, the downstream portion 142 of the annular web 14 can include a second extension 19B that extends substantially in the axial direction.

[0042] According to one embodiment that can be combined with other embodiments described herein, as Figure 5b shown by way of example in, at least one flow guiding element 17 is provided in at least one outflow region 15E of two or more inlet channels 150 of the stabilizer chamber.

[0043] The outflow region of the inlet channel 150 described herein should be understood to mean the region on the same side of the outlet opening 15B of the inlet channel 150 that is on the stabilizer chamber side. For example, the outflow region can extend over half or less of the inlet channel length L. For better understanding, the outflow region 15E of the inlet channel 15 is shown inFigure 5b This is shown by way of example. Arranging at least one flow guiding element 17 in the outflow region of the inlet channel can have a favorable effect on flow losses and blade vibration excitation.

[0044] According to one embodiment that can be combined with other embodiments described herein, at least one separating element T is arranged in the upstream flow outlet 16. In particular, at least one separating element T is arranged in the upstream flow outlet 16 such that two or more upstream outlet channels 160 are provided.

[0045] As Figure 8a and 8b shown, the two or more upstream outlet channels 160 are axially spaced apart. In addition, at least one of the two or more upstream outlet channels 160 can be designed differently from the other or other outlet channels. In particular, at least one of the two or more upstream outlet channels 160 differs from the other or other outlet channels in terms of channel width and / or channel shape. For example, the outlet channel width of at least one outlet channel can be smaller than that of the other or other of the two or more upstream outlet channels. It should be noted that the fact that the two or more upstream outlet channels 160 can also be of the same construction.

[0046] According to one embodiment that can be combined with other embodiments described herein, as Figure 8b shown by way of example, at least one flow guiding element 17 is arranged in each of at least two of the two or more upstream outlet channels 160. For example, at least one flow guiding element 17 can be designed to be different in one of the two or more upstream outlet channels 160 from that in another of the two or more upstream outlet channels 160, in particular in terms of quantity and / or shape.

[0047] According to one embodiment that can be combined with other embodiments described herein, the two or more upstream outlet channels 160 extend substantially in the radial direction.

[0048] According to one embodiment that can be combined with other embodiments described herein, as Figure 8a and Figure 8b shown by way of example, the two or more upstream outlet channels 160 are arranged between the main flow channel wall 131 and the upstream portion 141 of the annular web 14. In particular, the two or more upstream outlet channels 160 are arranged between the third extension 18A extending substantially in the radial direction of the upstream portion 141 of the annular web 14 and the extension 132 extending substantially in the radial direction of the main flow channel wall 131.

[0049] According to one embodiment that can be combined with other embodiments described herein, asFigure 8b As shown by way of example, at least one flow guiding element 17 is arranged in at least one inflow region 16E of two or more outlet channels 160 of the stabilizer chamber.

[0050] The outflow region 16E of the outlet channel 160 described herein should be understood to represent the region of the outlet channel 160 that is on the same side of the stabilizer chamber 12. For example, the inflow region 16E can extend over half or less of the length of the outlet channel.

[0051] According to one embodiment that can be combined with other embodiments described herein, at least one flow guiding element 17 is designed and arranged to provide a deflection grid through which flow can occur. The deflection grid through which flow can occur can be a deflection grid through which flow can occur substantially radially therethrough.

[0052] According to an alternative embodiment that can be combined with other embodiments described herein, as Figure 7 shown by way of example, at least one flow guiding element 17 is designed and arranged to provide a deflection grid through which flow can occur substantially axially therethrough. In the present disclosure, the term "substantially axial" should be understood to represent an angular range of ±45° or less, particularly ±25° or less, relative to the axial direction x. As Figure 7 shown by way of example, the axial direction x extends along the central axis 11. According to one example, "substantially axial" should be understood to represent an angular range of ±10° or less relative to the axial direction x. For example, according to Figure 7 , a deflection grid through which flow can occur substantially axially therethrough can be provided by the configuration of the inlet channel 150 of the stabilizer chamber and the arrangement of at least one flow guiding element 17.

[0053] According to one embodiment that can be combined with other embodiments described herein, at least one of the at least one flow guiding element 17 is implemented as a separate component.

[0054] According to one embodiment that can be combined with other embodiments described herein, at least one of the at least one flow guiding element 17 is integrally (one-piece) formed with at least one adjacent component. As can be seen from the drawings, the components adjacent to at least one flow guiding element 17 are the separating element T, the upstream portion 141 of the annular web 14 (particularly having the first extension 18 and / or the third extension 18A), the downstream portion 142 of the annular web 14 (particularly having the second extension 19A or 19B), and the main flow channel wall 131 (particularly having the extension 132).

[0055] According to one embodiment, which can be combined with other embodiments described herein, at least one, in particular at least half or all, of the plurality of flow guiding elements 17 are formed by a Curtis - type blade profile. In particular, at least one, in particular at least half or all, of the plurality of flow guiding elements 17 can be a prismatic Curtis - type blade. Generally, the flow guiding elements 17 are designed as radially deflecting blades. Embodiments of flow guiding elements with a Curtis - type blade profile, in particular flow guiding elements in the form of prismatic Curtis - type blades, have the advantage that these flow guiding elements can be manufactured relatively thick, so that the flow guiding elements 17 can be better connected to adjacent components (e.g., by threaded joints or other suitable types of joints as specified herein).

[0056] According to one embodiment, which can be combined with other embodiments described herein, the downstream part 142 of the annular web 14 has a centering shoulder, in particular a cylindrical or conical centering shoulder. Alternatively or additionally, the separating element T can have a centering shoulder, in particular a cylindrical or conical centering shoulder. Alternatively or additionally, the upstream part 141 of the annular web 14 can have a centering shoulder, in particular a cylindrical or conical centering shoulder.

[0057] According to one embodiment, which can be combined with other embodiments described herein, the upstream part 141 of the annular web 14 and the downstream part 142 of the annular web 14 are connected via at least one flow guiding element 17, in particular via a plurality of flow guiding elements 17 and the separating element T (e.g., by a threaded joint or a pin joint). The threaded joint or the pin joint can extend through at least one flow guiding element 17, in particular can extend through one or more flow guiding elements 17 and the separating element T. It should be noted that the threaded joint or the pin joint can also be implemented in some other way such that they do not extend through at least one flow guiding element 17 or the separating element T. Alternatively or additionally, other types of connections, such as shrink - fitting or clamping, can also be used.

[0058] According to one embodiment, which can be combined with other embodiments described herein, at least one flow guiding element 17 has a centering seat, which is designed to circumferentially, in particular coaxially, arrange at least one flow guiding element 17 around the central axis 11 of the main flow channel 13 in the downstream flow inlet 15, in particular in one or more downstream inlet channels. Alternatively or additionally, at least one flow guiding element 17 has a centering seat, which is designed to circumferentially, in particular coaxially, arrange at least one flow guiding element 17 around the central axis 11 of the main flow channel 13 in the upstream flow outlet 16, in particular in one or more upstream outlet channels. The centering seat can be realized, for example, by one or more centering elements, one or more centering pins or centering edges on the component to be centered.

[0059] According to one embodiment, which can be combined with other embodiments described herein, at least one flow guiding element 17 has an inlet end 17A and an outlet end 17B. The downstream end of at least one flow guiding element 17 can be inclined in the circumferential direction relative to the inlet end 17A of at least one flow guiding element 17, so as to ensure a reduction in eddy currents or the generation of reverse eddy currents during the flow through. For the sake of explanation, Figure 9a and Figure 10a shows a cross-section of a downstream inlet channel 150 having a plurality of flow guiding elements 17, in which the rotation direction 2 of the compressor impeller that causes the flow to be affected by eddy currents is depicted. Figure 9a shows the structure of the flow guiding element 17, by which a reverse eddy current can be generated during the flow through, as shown by way of example by the arrow between the inlet end 17A and the outlet end 17B in Figure 9a . Figure 9b shows a schematic view of the structure of the flow guiding element 17 in the upstream outlet channel 160 for generating a flow reverse eddy current during the flow through the guiding element. Figure 10a shows the structure of the flow guiding element 17 in the downstream inlet channel 150, by which eddy currents can be reduced during the flow through. Figure 10b shows a schematic view of the structure of the flow guiding element 17 in the upstream outlet channel 160 for reducing flow eddy currents during the flow through the guiding element.

[0060] In addition, it should be noted that the flow guiding element 17 can be implemented flush with the inlet opening on the main flow channel side of the inlet channel 150 described herein and / or flush with the outlet opening on the stabilizer chamber side of the inlet channel 150 described herein. Alternatively, the flow guiding element 17 can be spaced apart from the inlet opening on the main flow channel side of the inlet channel 150 described herein and / or from the outlet opening on the stabilizer chamber side of the inlet channel 150 described herein.

[0061] In a similar manner, the flow guiding element 17 can be implemented flush with the outlet opening of the outlet channel 160 described herein on the main flow channel side and / or flush with the inlet opening of the outlet channel 160 described herein on the stabilizer chamber side. Alternatively, the flow guiding element 17 can be spaced apart from the outlet opening of the outlet channel 160 described herein on the main flow channel side and / or from the inlet opening of the outlet channel 160 described herein on the stabilizer chamber side.

[0062] According to one embodiment, which can be combined with other embodiments described herein, the annular stabilizer chamber 12 has no vanes. In other words, no vanes are provided in the annular stabilizer chamber 12, particularly no flow guiding vanes. In particular, the annular stabilizer chamber 12 can also have no support portions. In other words, the annular stabilizer chamber 12 can have no vanes and no support portions, and thus there are neither flow guiding vanes nor support portions in the annular stabilizer chamber 12.

[0063] According to a second aspect of the present disclosure, there is provided a compressor 20, particularly a radial flow compressor or a mixed flow compressor, comprising a compressor impeller 21 and a stabilizer channel 10 according to one of the embodiments described herein. According to one embodiment, which can be combined with other embodiments described herein, the compressor impeller 21 includes a number N1 of compressor impeller vanes 23 in the region of the flow inlet 15 and a number N2 of guiding elements in at least one flow guiding element 17, where N2 ≥ 1.5×N1.

[0064] Therefore, it is possible to advantageously provide a compressor having an improved characteristic map width and characteristic curve slope, particularly a compressor that reduces noise and vibration generation during compressor operation.

[0065] A third aspect of the present invention relates to a turbine, particularly a turbocharger, having a compressor according to one of the embodiments described herein, thereby advantageously providing a turbine, particularly a turbocharger, that is improved compared to the prior art.

[0066] Description of reference numerals

[0067] 1 Main flow direction

[0068] 2 Rotation direction of the compressor impeller

[0069] 3 Inlet channel according to the prior art

[0070] 4 Outlet opening according to the prior art

[0071] 5 Compressor housing

[0072] 10 Stabilizer channel

[0073] 11 Central axis / rotation axis of the compressor impeller

[0074] 12 Annular stabilizer chamber

[0075] 121 Support part

[0076] 13 Main flow channel

[0077] 131 Main flow channel wall

[0078] 132 Extension part of the main flow channel wall

[0079] 14 Annular web

[0080] 141 Upstream part of the annular web

[0081] 142 Downstream part of the annular web

[0082] 15 Downstream flow inlet of the stabilizer chamber

[0083] 150 Two or more downstream inlet channels

[0084] 151 First inlet channel

[0085] 152 Second inlet channel

[0086] 153 Third inlet channel

[0087] 15A Inlet openings of two or more inlet channels on the side of the main flow channel

[0088] 15B Outlet openings of two or more inlet channels on the side of the stabilizer chamber

[0089] 15C Substantially radially extending part of two or more inlet channels

[0090] 15D Substantially axially extending part of two or more inlet channels

[0091] 15E Outflow area of two or more inlet channels

[0092] 15F Transition area of two or more inlet channels

[0093] 16 Upstream flow outlet of the stabilizer chamber

[0094] 16E Inflow area of two or more outlet channels

[0095] 160 Two or more upstream outlet channels

[0096] 17 At least one flow guiding element / multiple flow guiding elements

[0097] 171 First group of flow guiding elements

[0098] 172 The second set of flow guiding elements

[0099] 173 Cross-sectional conical part

[0100] 17A Inlet end of the flow guiding element

[0101] 17B Outlet end of the flow guiding element

[0102] 18 The first extension extending substantially in the radial direction

[0103] 18A The third extension extending substantially in the radial direction

[0104] 19A The second extension extending substantially in the radial direction

[0105] 19B The second extension extending substantially in the axial direction

[0106] 20 Compressor

[0107] 20A Inner casing of the compressor

[0108] 20B Outer casing of the compressor

[0109] 21 Compressor impeller

[0110] 22 Insertion piece

[0111] 23 Compressor impeller blade

[0112] 24 Inlet edge of the compressor impeller

[0113] T Separation element

[0114] r Radial direction

[0115] x Axial direction

[0116] L Length of two or more inlet channels of the stabilizer chamber

[0117] w1 Channel width of the first inlet channel

[0118] w2 Channel width of the second inlet channel

[0119] w3 Channel width of the third inlet channel

[0120] α Angle in the x-r plane for interpreting "substantially radial"

Claims

1. A stabilizer channel (10) of a compressor, the stabilizer channel having an annular stabilizer chamber (12) which surrounds a main flow channel (13) in the intake region of a compressor impeller (21), and the annular stabilizer chamber being delimited relative to the main flow channel (13) by an annular web (14), wherein, The annular stabilizer chamber (12) is connected to the main flow channel (13) via a downstream flow inlet (15) and an upstream flow outlet (16), wherein at least one separating element (T) is provided in at least one of the flow inlet (15) and the flow outlet (16), such that at least one of the inflow into the annular stabilizer chamber (12) and the outflow out of the annular stabilizer chamber (12) is laterally separated with respect to the main flow direction (1) of the main flow channel (13), and wherein at least one flow guiding element (17) is provided in at least one of the flow inlet (15) and the flow outlet (16), wherein the at least one separating element (T) is provided in the flow inlet (15) such that two or more downstream inlet channels (150) are provided, and wherein the two or more downstream inlet channels (150) are provided between an upstream part (141) and a downstream part (142) of the annular web (14). Wherein, the upstream part (141) of the annular web (14) includes a first extension (18) extending substantially in the radial direction, the downstream part (142) of the annular web (14) includes a second extension (19A) extending substantially in the radial direction, and the first extension (18) and the second extension (19A) extend away from the annular web (14) and into the annular stabilizer chamber (12).

2. The stabilizer channel (10) according to claim 1, wherein, At least one of the two or more downstream inlet channels (150) is designed differently in at least one of channel width and channel shape.

3. The stabilizer channel (10) according to claim 2, wherein, The inlet channel width of the at least one inlet channel is smaller than another inlet channel of the two or more downstream inlet channels.

4. The stabilizer channel (10) according to claim 2, wherein, The at least one inlet channel has a cross-sectional taper (173) in the radial direction.

5. The stabilizer channel (10) according to any one of claims 1 to 4, wherein, The at least one separating element (T) is provided in the flow inlet (15) such that two or more downstream inlet channels (150) are provided, wherein at least one flow guiding element (17) is provided in each of at least two of the two or more downstream inlet channels (150).

6. The stabilizer channel (10) according to claim 5, wherein, The at least one flow guiding element (17) is designed to be different in one of the two or more downstream inlet channels (150) from that in another of the two or more downstream inlet channels (150).

7. The stabilizer channel (10) according to claim 5, wherein, The at least one flow guiding element (17) is designed to be different in at least one of quantity and shape in one of the two or more downstream inlet channels (150) from that in another of the two or more downstream inlet channels (150).

8. The stabilizer channel (10) according to any one of claims 2 to 4, wherein, The two or more downstream inlet channels (150) extend substantially in the radial direction, or the two or more downstream inlet channels (150) include a part (15C) extending substantially radially and a part (15D) extending substantially axially.

9. The stabilizer channel (10) according to any one of claims 2 to 4, wherein, The at least one flow guiding element (17) is arranged in at least one outflow region (15E) of two or more inlet channels of the stabilizer channel.

10. The stabilizer channel (10) according to any one of claims 1 to 4, wherein, The at least one separating element (T) is arranged in the upstream flow outlet (16) such that two or more upstream outlet channels (160) are provided.

11. The stabilizer channel (10) according to claim 10, wherein, At least one of the two or more upstream outlet channels (160) is designed to be different.

12. The stabilizer channel (10) according to claim 10, wherein, At least one of the two or more upstream outlet channels (160) is designed to be different in at least one of channel width and channel shape.

13. The stabilizer channel (10) according to claim 10, wherein, At least one flow guiding element (17) is arranged in each of at least two of the two or more upstream outlet channels (160).

14. The stabilizer channel (10) according to claim 13, wherein, The at least one flow guiding element (17) is designed to be different in one of the two or more upstream outlet channels (160).

15. The stabilizer channel (10) according to claim 13, wherein, The at least one flow guiding element (17) is designed to be different in at least one of quantity and shape in one of the two or more upstream outlet channels (160).

16. The stabilizer channel (10) according to claim 10, wherein, The two or more upstream outlet channels (160) extend substantially in the radial direction.

17. The stabilizer channel (10) according to claim 10, wherein, The two or more upstream outlet channels (160) are arranged between the main flow channel wall (131) and the upstream part (141) of the annular web (14).

18. The stabilizer channel (10) according to claim 17, wherein, The two or more upstream outlet channels (160) are arranged between a third extension (18A) extending in the radial direction along the upstream part (141) of the annular web (14) and an extension (132) extending in the radial direction along the main flow channel wall (131).

19. The stabilizer channel according to claim 10, wherein, The at least one flow guiding element (17) is arranged in at least one inflow region (16E) of two or more outlet channels (160) of the stabilizer chamber.

20. The stabilizer channel according to any one of claims 1 to 4, wherein The at least one flow guiding element (17) is designed and arranged to provide a deflection grid through which flow can occur.

21. The stabilizer channel according to any one of claims 1 to 4, wherein The at least one flow guiding element (17) is designed and arranged to provide a deflection grid through which at least one of radial flow and axial flow can occur.

22. The stabilizer channel according to any one of claims 1 to 4, wherein, At least one of the at least one flow guiding element (17) is implemented as a separate component.

23. The stabilizer channel according to any one of claims 1 to 4, wherein, At least one of the at least one flow guiding element (17) is integrally formed with at least one adjacent component.

24. The stabilizer channel according to claim 8, wherein, At least one of the downstream part (142) of the annular web (14), the separating element (T), and the upstream part (141) of the annular web (14) has a centering shoulder.

25. The stabilizer channel according to claim 24, wherein, The centering shoulder is cylindrical or conical.

26. The stabilizer channel according to any one of claims 1 to 4, wherein, The at least one flow guiding element (17) has a centering seat which is designed to circumferentially arrange the at least one flow guiding element (17) around the central axis (11) of the main flow channel (13) in at least one of the downstream flow inlet (15) and the upstream flow outlet (16).

27. The stabilizer channel according to claim 26, wherein, The centering seat is designed to arrange the at least one flow guiding element (17) coaxially about the central axis (11) of the main flow channel.

28. The stabilizer channel according to any one of claims 1 to 4, wherein, The at least one flow guiding element (17) has an inlet end (17A) and an outlet end (17B), wherein the outlet end (17B) is inclined relative to the inlet end (17A) in the circumferential direction, thereby ensuring that at least one of the following applies: reducing eddies and generating reverse eddies during the flow-through.

29. The stabilizer channel according to any one of claims 1 to 4, wherein, The compressor is a radial compressor or a diagonal flow compressor.

30. A compressor (20) having a compressor impeller (21) and a stabilizer channel (10) according to any one of claims 1 to 4.

31. The compressor according to claim 30, wherein, The compressor impeller (21) includes a number N1 of compressor impeller blades (23) and a number N2 of guiding elements of the at least one flow guiding element (17) in the region of the flow inlet (15) leading into the stabilizer channel (10), wherein the number N2 ≥ 1.5 × N1.

32. The compressor according to claim 30 or 31, wherein, The compressor is a radial compressor or a diagonal flow compressor.

33. A turbine having a compressor (20) according to claim 30.

34. The turbine according to claim 33, wherein, The turbine is a turbocharger.

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