Compressor and turbomachine having a compressor

Abstract

The invention relates to a compressor (10), in particular a radial / diagonal compressor. The compressor (10) comprises an outer compressor housing (11) and an inner compressor housing (12) which provide a spiral space (13). Furthermore, the compressor (10) comprises a diffuser (14) with a diffuser channel (15) which is formed by a first side wall (151) and a second side wall (152). The first side wall (151) is provided by the inner compressor housing (12). The second side wall (152) is provided by a diffuser plate (16). The second side wall (152) which is formed by the diffuser plate (16) is a side wall of the diffuser channel (15) on the bearing housing side. The diffuser plate (16) comprises a curved outflow region (161) which is designed to deflect a flow after the latter emerges from the diffuser channel (15). A first radial position (R1) of a first interface (S1) between the diffuser plate (16) and the outer compressor housing (11) is smaller than a second radial position (R2) of a second interface (S2) between the outer compressor housing (11) and the inner compressor housing (12).

Description

COMPRESSOR AND TURBO MACHINE WITH ONE COMPRESSOR TECHNICAL FIELD

[0001] The invention relates to the field of compressors, in particular radial / diagonal compressors. Furthermore, the invention relates to the field of turbomachines with a compressor, in particular turbochargers. TECHNICAL BACKGROUND

[0002] Compressors play a crucial role in turbomachinery, particularly in turbochargers used in internal combustion engines. Their primary purpose is to increase the amount of air required in the combustion chambers by compressing the incoming air. This provides a higher air mass to optimize the combustion process, resulting in improved engine performance and efficiency.

[0003] Radial / diagonal compressors are a special type of compressor widely used in turbomachinery. They are characterized by their high pressure gain, allowing them to generate a large pressure difference and offer high power density. Furthermore, their compact design and ability to operate at high speeds make them well-suited for applications with limited space, such as internal combustion engines.

[0004] It has been found that the compressors known from the state of the art can still be improved in terms of production costs, ease of assembly, and interface architecture, especially for turbomachinery with cartridge concept.

[0005] The object of the present invention is therefore to provide a compressor and a turbomachine with which one or more of the Disadvantages known from the state of the art, particularly with regard to production costs, ease of assembly and interface architecture, can be partially or completely overcome. BRIEF DESCRIPTION OF THE INVENTION

[0006] To achieve the above-mentioned object, a compressor and a turbomachine according to the independent claims are provided. Further aspects, advantages, and features of the present invention can be found in the dependent claims, the description, and the accompanying figures.

[0007] According to one aspect of the invention, a compressor, in particular a radial Z-diagonal compressor, is provided. The compressor comprises an outer compressor housing and an inner compressor housing, which provide a spiral chamber. Furthermore, the compressor comprises a diffuser with a diffuser channel formed by a first side wall and a second side wall. The first side wall is provided by the inner compressor housing. The second side wall is provided by a diffuser plate. The second side wall formed by the diffuser plate is a bearing housing-side side wall of the diffuser channel. The diffuser plate comprises a curved outflow region designed to redirect a flow after exiting the diffuser channel.A first radial position of a first interface between the diffuser plate and the outer compressor housing is smaller than a second radial position of a second interface between the outer compressor housing and the inner compressor housing.

[0008] This advantageously provides a compressor that is improved in terms of ease of assembly and interface architecture for turbomachinery with a cartridge concept, especially turbochargers. In particular, additional installation space is advantageously created in the radial direction for the design of an improved interface architecture between the compressor housing and the bearing housing.

[0009] According to a second aspect of the invention, a turbomachine, in particular a turbocharger, is provided. The turbomachine comprises a compressor according to one of the embodiments described herein and a bearing housing. As described herein, the compressor comprises an outer compressor housing and an inner compressor housing, which provide a spiral space. The outer compressor housing is connected to the bearing housing. In particular, the outer compressor housing has a fastening means receptacle, which is arranged behind a diffuser plate on the bearing housing side and is designed to connect the outer compressor housing to a bearing housing. Typically, an intermediate space is provided between the diffuser plate and the outer compressor housing, which intermediate space is arranged at least partially behind the curved outflow region of the diffuser plate on the bearing housing side.In particular, the gap is designed to accommodate part of a fastener, such as a screw head or a screw nut, for connecting the outer compressor housing to a bearing housing.

[0010] Thus, a turbomachine is advantageously provided which has an improved connection between the outer compressor housing and the bearing housing, so that the ease of assembly can be improved. BRIEF DESCRIPTION OF THE CHARACTERS

[0011] The invention will be explained below with reference to exemplary embodiments illustrated in the figures, from which further advantages and modifications emerge. Herein: Figure 1 is a schematic sectional view of a compressor according to embodiments described herein; and Figure 2 is a schematic sectional view of a turbomachine according to embodiments described herein. DETAILED DESCRIPTION OF THE FIGURES

[0012] Various embodiments are described below, one or more examples of which are shown in each figure. Each example is provided for illustrative purposes and is not intended to be limiting. For example, features shown or described as part of one embodiment may be used on or in conjunction with any other embodiment to obtain a further embodiment. The present disclosure is intended to encompass such modifications and variations.

[0013] In the following description of the figures, the same reference numbers refer to the same or similar components. Generally, only the differences between the individual embodiments are described. Unless otherwise stated, the description of a part or aspect in one embodiment may also refer to a corresponding part or aspect in another embodiment.

[0014] The coordinate system shown in Figures 1 and 2 shows the radial direction r and the axial direction x referred to in the present disclosure.

[0015] With reference to Figure 1, a compressor 10 according to the present disclosure is described. In particular, the compressor 10 is a compressor for a turbomachine, such as a turbocharger. For example, the compressor may be a radial compressor or a diagonal compressor.

[0016] In turbomachinery, radial and diagonal compressors refer to different types of compressors used in turbomachinery such as gas turbines, compressors, or turbochargers. A radial compressor typically comprises a housing with a central rotor, typically equipped with curved blades. The working medium, usually gas, is sucked in axially and then compressed radially outwards to increase the pressure of the working medium.

[0017] A diagonal compressor is similar in operation to a radial compressor. The main difference is that the blades in a diagonal compressor are arranged at a diagonal angle to the rotational axis. This results in a combination of radial and axial compression of the gas. Diagonal compressors are often used in applications where both high pressure increases and high flow rates are required.

[0018] Both centrifugal and diagonal compressors play an important role in turbomachinery to improve performance, increase pressure, and generate the required flow rate. The choice between a centrifugal and diagonal compressor depends on the specific application requirements, operating conditions, and other factors.

[0019] According to one embodiment, which can be combined with other embodiments described herein, the compressor 10 comprises an outer compressor housing 11 and an inner compressor housing 12, which provide a spiral space 13. The outer compressor housing can be formed as a single piece. In other words, the outer compressor housing can be formed from a single integral component. Alternatively, the outer compressor housing can consist of several housing components, which together form the outer compressor housing. Likewise, the inner compressor housing can be formed as a single piece, i.e., consist of a single integral component. Alternatively, the inner compressor housing can be formed from several housing components, which together provide the inner compressor housing.

[0020] As can be seen from Figure 1, the outer compressor housing 11 and the inner compressor housing 12 are designed such that together they form a spiral space 13.

[0021] In the present disclosure, the term "volute chamber" typically refers to the chamber or channel formed by the outer compressor casing and the inner compressor casing. The volute chamber is a spiral-shaped chamber that directs the flow of gas through the compressor and is typically designed to continuously guide the gas to the compressor outlet, resulting in a uniform pressure buildup. The spiral arrangement of the volute chamber has the advantage of enabling good use of the available space and reducing flow resistance. This ensures efficient and low-friction gas flow, leading to improved compressor performance.

[0022] Furthermore, the compressor 10 includes a diffuser 14 with a diffuser channel 15. The diffuser 14 is typically arranged downstream of the rotor 102, in particular the compressor wheel. The main function of the diffuser is to reduce the gas velocity and increase the static pressure. In other words, the diffuser enables a slowing of the flow velocity of the compressed gas and an increase in the static pressure. This is achieved by expanding the diffuser channel 15, whose cross-section typically gradually increases in the flow direction.

[0023] As shown by way of example in Figure 1, the diffuser channel 15 is formed by a first side wall 151 and a second side wall 152. The first side wall 151 is provided by the inner compressor housing 12. The second side wall 152 is provided by a diffuser plate 16. The second side wall 152 formed by the diffuser plate 16 is a bearing housing-side side wall of the diffuser channel 15. Typically, the diffuser plate 16 is an annular disk. The diffuser plate 16 comprises a curved outflow region 161 designed to redirect a flow after exiting the diffuser channel 15. Typically, the outflow region 161 is concavely curved. Thus, part of the flow redirection of the spiral can advantageously already take place in the diffuser.

[0024] As shown by way of example in Figure 1, a first radial position Ri of a first interface S1 between the diffuser plate 16 and the outer compressor housing 11 is smaller than a second radial position R2 of a second interface S2 between the outer compressor housing 11 and the inner compressor housing 12. As shown in Figure 1, the first interface S1 is typically arranged on the bearing housing side. Compared to the first interface S1, the second interface S2 is further away from the bearing housing 20 in the axial direction x.

[0025] From the embodiments described herein, it is evident that a compressor is advantageously provided that is improved for turbomachines with a cartridge concept, in particular turbochargers, in terms of ease of assembly and interface architecture. In particular, additional installation space is advantageously created in the radial direction for designing an optimal interface architecture between the compressor housing and the bearing housing.

[0026] In turbomachinery, the cartridge concept refers to a design in which the core of the turbomachinery is designed as a separate unit, known as a cartridge. This cartridge typically comprises one or more impellers, such as a compressor wheel and / or a turbine wheel, and the associated bearings. In turbochargers, the cartridge concept refers to a design in which the turbocharger is divided into several components or modules. Each module performs a specific function and can be serviced or replaced independently of the others.

[0027] In the cartridge concept, the turbocharger is typically divided into three main components. The first main component is the turbine housing. The turbine housing is the part of the turbocharger that comes into contact with the hot exhaust gases. The turbine housing surrounds the turbine wheel. The second main component is the compressor housing, which in the turbocharger is responsible for is responsible for compressing the fresh air. The compressor housing surrounds the compressor wheel. The compressor housing is connected to the engine's intake system and can be replaced separately from the turbine housing. The cartridge can be considered the third main component. The cartridge is the true core of the cartridge concept. The cartridge comprises one or more impellers, such as the compressor wheel and / or the turbine wheel, and the bearing units. The cartridge is considered a standalone unit and can be completely removed and replaced without having to remove the turbine or compressor housing, thus simplifying turbocharger maintenance and repair.

[0028] According to one embodiment, which can be combined with other embodiments described herein, a transition from the curved downstream flow area 161 of the diffuser plate 16 to a spiral chamber interior 131 of the outer compressor housing 11 is formed tangentially. In the above context, the term "transition" refers to the structural connection or interface concept between the curved downstream flow area 161 of the diffuser plate 16 and the spiral chamber interior 131 of the outer compressor housing 11.

[0029] A tangential transition design means that the two adjacent areas have a smooth and continuous connection, with the flow direction smoothly transitioning from the curved surface of the diffuser plate to the inside of the volute chamber of the outer compressor casing. Typically, the transition is free of sharp edges or sudden changes in direction. A tangential transition is advantageous for minimizing flow losses, turbulence, or pressure losses and ensuring efficient flow guidance.

[0030] According to an embodiment that can be combined with other embodiments described herein, the diffuser 14 has a blade ring with a plurality of blades 17 that are at least partially arranged in the diffuser channel 15. In other words, the plurality of Vanes 17 may be arranged partially or completely within the diffuser channel 15. The plurality of vanes 17 may be connected to the first side wall 151 and / or the second side wall 152. For example, the vanes 17 may be formed integrally with the first side wall 151 and / or the second side wall 152.

[0031] According to one embodiment, which can be combined with other embodiments described herein, the curved outflow region 161 of the diffuser plate 16 is designed to be rotationally symmetrical to the central rotation axis 101 of the compressor 10. A rotationally symmetrical design of the curved outflow region is advantageous with regard to cost-effective machining and manufacturing.

[0032] According to an embodiment that can be combined with other embodiments described herein, the first side wall 151 and the second side wall 152 are arranged at least partially divergent from one another in the flow direction.

[0033] According to an embodiment that can be combined with other embodiments described herein, a radial starting position R k of the curved portion 161 between a radial position R A an outflow edge of a blade 17 of the diffuser 14 and a radius R of the diffuser plate 16. In other words, the radial position R A an outflow edge of a blade 17 of the diffuser 14 is less than the radial starting position R k of the curved area 161, wherein the radial starting position R k of the curved area 161 is less than the radius R of the diffuser plate 16 (R A < R k< R). For example, the radial starting position R k of the curved portion 161 between the radial position R A an outflow edge of a blade 17 of the diffuser 14 and a radial position R D an outlet opening of the diffuser 14 (R A < R k < R D ). Alternatively, the radial starting position R k of the curved portion 161 between the radial position R D the outlet opening of the diffuser 14 and the radius R of the diffuser plate 16 (R D < R k < R).

[0034] According to an embodiment that can be combined with other embodiments described herein, a ratio D / R of a thickness D of the diffuser plate to the radius R of the diffuser plate 16 is selected from a range 0.02 < D / R < 0.10.

[0035] According to one embodiment, which can be combined with other embodiments described herein, the outer compressor housing 11 has one or more fastener receptacles 111 arranged behind the diffuser plate 16 on the bearing housing side. In particular, the one or more fastener receptacles 111 are arranged between the diffuser plate 16 and the bearing housing 20. As can be seen from Figure 1, the one or more fastener receptacles 111 are designed to connect the outer compressor housing 11 to the bearing housing 20 by means of one or more fasteners 22. Typically, the one or more fastener receptacles 111 are one or more axial fastener receptacles. The one or more axial fastener receptacles typically extend parallel to the central rotation axis 101 of the compressor 10.

[0036] According to one embodiment, which can be combined with other embodiments described herein, an intermediate space 18 is provided between the diffuser plate 16 and the outer compressor housing 11, which intermediate space is arranged at least partially behind the curved outflow region 161 of the diffuser plate 16 on the bearing housing side, as shown by way of example in Figure 1. The intermediate space 18 is designed to accommodate a part of one or more fastening means 22 for connecting the outer compressor housing 11 to a bearing housing 20. For example, the part of the fastening means 22 accommodated in the intermediate space 18 can be a detachable fastening element, in particular a screw head or a screw nut.

[0037] Figure 2 shows a schematic sectional view of a turbomachine 40 according to the present disclosure. For example, the turbomachine 40 may be a turbocharger.

[0038] According to one embodiment, which can be combined with other embodiments described herein, the turbomachine 40 comprises a compressor 10 with an outer compressor housing 11 and an inner compressor housing 12 according to one of the embodiments described herein. The turbomachine further comprises a bearing housing 20 connected to the outer compressor housing.

[0039] According to one embodiment that can be combined with other embodiments described herein, the turbomachine 40 further comprises a gas outlet casing 31 of a turbine 30. Typically, the gas outlet casing 31, the bearing housing 20, and the outer compressor casing 11 are connected to one another by means of one or more fastening means 22. The one or more fastening means 22 typically extend through one or more axial fastening means receptacles 21 through the bearing housing 20. Typically, the one or more axial fastening means receptacles 21 are through-openings, in particular through-bores, that extend through the bearing housing 20.

[0040] According to one embodiment, which can be combined with other embodiments described herein, the turbine 30 is an axial turbine. The turbine 30 can have a turbine diffuser 32. The turbine diffuser 32 can be a single piece or consist of two or more parts. Typically, the turbine diffuser 32 is connected to the gas outlet casing 31 via an axial fastening 33. As shown by way of example in Figure 2, an outer radius R4 of the turbine diffuser 32 is typically less than a radial position R3 of the one or more fastening means 22 with which the outer compressor casing 11, the bearing housing 20, and the gas outlet casing 31 are connected. It is understood that the radial position R3 of the one or more fastening means 22 is typically less as the first radial position Ri of the first interface S1 between the diffuser plate 16 and the outer compressor housing 11.

[0041] As is apparent from the embodiments described herein, according to the invention, a compressor and a turbomachine are advantageously provided which are advantageously improved with regard to the interface architecture for the cartridge concept, so that the ease of assembly, in particular in the case of servicing, is improved, whereby the associated costs can be reduced. LIST OF REFERENCE SYMBOLS 10 compressors 101 Rotation axis 102 Rotor 11 outer compressor housing 111 Fastener holder of the outer compressor housing 12 inner compressor housing 13 Spiral Room 131 Spiral space inside 14 Diffuser 15 Diffuser channel 151 first page wall 152 second side wall 16 Diffuser plate 161 curved outflow duct 17 shovels 18 gap 20 bearing housings 21 axial fastener holder 22 fasteners 30 turbines 31 Gas outlet housing 32 Turbine diffuser 33 axial fastening 34 Turbine wheel 40 Turbomachine Ri first radial position R2 second radial position R3radial position of the fastener 22 R4outer radius of the turbine diffuser RA radial position of a diffuser blade trailing edge R D radial position of a diffuser outlet opening Rk radial start position of the curved area 51 first interface 52 second interface D Thickness of the diffuser plate R Radius of the diffuser plate x axial direction r radial direction

Claims

CLAIMS 1. Compressor (10), in particular radial Z-diagonal compressor, comprising: - an outer compressor housing (11) and an inner compressor housing (12) which provide a spiral space (13), - a diffuser (14) with a diffuser channel (15) formed by a first side wall (151) and a second side wall (152), wherein the first side wall (151) is provided by the inner compressor housing (12), and wherein the second side wall (152) is provided by a diffuser plate (16), wherein the second side wall (152) formed by the diffuser plate (16) is a bearing housing-side side wall of the diffuser channel (15), wherein the diffuser plate (16) comprises a curved outflow region (161) designed to deflect a flow after exiting the diffuser channel (15), wherein a first radial position (RI) of a first interface (SI) between the diffuser plate (16) and the outer compressor housing (11) is smaller than a second radial position (R2) of a second interface (S2) between the outer compressor housing (11) and the inner compressor housing (12).

2. Compressor (10) according to claim 1, wherein a transition from the curved outflow region (161) of the diffuser plate (16) to a spiral space inner side (131) of the outer compressor housing (11) is formed tangentially.

3. Compressor (10) according to claim 1 or 2, wherein the diffuser (14) has a blade ring with a plurality of blades (17) which are arranged at least partially in the diffuser channel (15).

4. Compressor (10) according to one of claims 1 to 3, wherein the curved outflow region (161) of the diffuser plate (16) is rotationally symmetrical to the central axis of rotation (101) of the compressor.

5. Compressor (10) according to one of claims 1 to 4, wherein the first side wall (151) and the second side wall (152) are arranged at least partially divergent from one another in the flow direction.

6. Compressor (10) according to one of claims 1 to 5, wherein a radial starting position (R k) of the curved region (161) between a radial position (R A ) an outflow edge of a blade (17) of the diffuser (14) and a radius R of the diffuser plate (16).

7. Compressor (10) according to one of claims 1 to 6, wherein a ratio D / R of a thickness D of the diffuser plate to the radius R of the diffuser plate (16) is 0.02 < D / R < 0.

10.

8. Compressor (10) according to one of claims 1 to 7, wherein the outer compressor housing (11) has a fastening means receptacle (111) which is arranged on the bearing housing side behind the diffuser plate (16) and is designed to connect the outer compressor housing (11) to a bearing housing (20), in particular wherein the fastening means receptacle (111) is an axial fastening means receptacle.

9. Compressor (10) according to one of claims 1 to 8, wherein an intermediate space (18) is provided between the diffuser plate (16) and the outer compressor housing (11), which intermediate space is arranged at least partially behind the curved outflow region (161) of the diffuser plate (16) on the bearing housing side, and which is designed to accommodate part of a fastening means (22) for connecting the outer compressor housing (11) to a bearing housing (20), in particular wherein the part of the fastening means (22) is a screw head or a screw nut.

10. Turbomachine (40), in particular turbocharger, with a compressor (10) according to one of claims 1 to 9 and a bearing housing (20), wherein the outer compressor housing (11) is connected to the bearing housing (20), in particular wherein the compressor (10) is a compressor according to claim 8 and / or 9.

11. Turbomachine (40) according to claim 10, further comprising a gas outlet housing (31) of a turbine (30), wherein the gas outlet housing (31), the bearing housing (20) and the outer compressor housing (11) are connected to one another by means of a fastening means (22), and wherein the fastening means (22) extends through an axial fastening means receptacle (21), in particular a bore, through the bearing housing (20).

12. Turbomachine (40) according to claim 11, wherein the turbine (30) is an axial turbine and has a turbine diffuser (32) connected to the gas outlet casing (31) via an axial fastening (33), wherein an outer radius (R4) of the turbine diffuser (32) is less than a radial position (R3) of the fastening means (22).

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