Compressor and turbomachine having compressor
By optimizing the flow deflection of the spiral space and diffuser channel, the interface architecture and assembly ease of the compressor are improved, solving the problems of production cost and interface design in the prior art, especially in turbomachinery with sleeve design.
Patent Information
- Application Number
- CN202480038362.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2023-07-06
- Filing Date
- 2024-06-18
- Publication Date
- 2026-01-02
AI Technical Summary
There is room for improvement in the production cost, ease of assembly, and interface architecture of existing compressors, especially in turbomachinery with a sleeve design.
A radial or diagonal compressor is designed, including an outer compressor housing and an inner compressor housing, providing helical space and optimizing flow deflection through the diffuser channel and the curved outflow area of the diffuser plate, creating additional radial mounting space, improving the interface architecture, and simplifying assembly through fastener housing and clearance design.
It improves ease of assembly, reduces related costs, and optimizes the interface architecture of turbomachinery, especially in turbochargers with sleeve designs.
Smart Images
Figure CN121263607A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of compressors, particularly radial or diagonal compressors. It also relates to the field of turbomachinery incorporating compressors, particularly 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 chamber by compressing the incoming air. This provides a higher quality of air to optimize the combustion process, thereby improving engine power and efficiency.
[0003] Radial compressors, or diagonal compressors, are a special type of compressor widely used in turbomachinery. They are characterized by high pressure rise, thus generating large pressure differentials and providing high power density. Furthermore, their compact design and high-speed operation make them ideal for applications with limited installation space, such as in internal combustion engines.
[0004] It has been found that compressors known in the prior art can be further improved in terms of production cost, ease of assembly, and interface architecture, especially for turbomachinery involving sleeve design.
[0005] Therefore, the object of the present invention is to provide a compressor and a turbomachinery that can partially or completely overcome one or more disadvantages known in the prior art, particularly in terms of production cost, ease of assembly and interface architecture. Summary of the Invention
[0006] To achieve the above objectives, compressors and turbomachinery as claimed in the independent claims are provided. Other aspects, advantages, and features of the invention can be found in the dependent claims, the specification, and the drawings.
[0007] According to one aspect of the invention, a compressor, particularly a radial compressor or a diagonal compressor, is provided. The compressor includes an outer compressor housing and an inner compressor housing, which provide a helical space. Furthermore, the compressor includes a diffuser with a diffuser channel formed by a first sidewall and a second sidewall. The first sidewall is provided by the inner compressor housing. The second sidewall is provided by a diffuser plate. The second sidewall formed by the diffuser plate is the sidewall of the diffuser channel on the bearing housing side. The diffuser plate includes a curved outflow region designed to deflect the flow after it exits the diffuser channel. A first radial position of the first interface between the diffuser plate and the outer compressor housing is lower than a second radial position of the second interface between the outer compressor housing and the inner compressor housing.
[0008] Thus, the compressor provided is advantageously a compressor which is improved with regard to assembly simplicity and interface architecture for turbo-machinery, in particular turbochargers, involving a sleeve design. In particular, an additional radial installation space is advantageously created for configuring an improved interface architecture between the compressor housing and the bearing housing.
[0009] According to a second aspect of the present application, a turbo-machinery, in particular a turbocharger, is provided. The turbo-machinery comprises a bearing housing and a compressor according to one of the embodiments described herein. 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 accommodation arranged at the bearing housing side behind the diffuser plate and designed to connect the outer compressor housing to the bearing housing. Typically, a gap is provided between the diffuser plate and the outer compressor housing which is arranged at the bearing housing side at least partially behind the curved outflow area of the diffuser plate. In particular, the gap is designed to accommodate parts of the fastening means, such as screw heads or nuts, for connecting the outer compressor housing to the bearing housing.
[0010] Thus, advantageously a turbo-machinery is provided which has an improved connection between the outer compressor housing and the bearing housing, thereby enabling an improved assembly simplicity. BRIEF DESCRIPTION OF DRAWINGS
[0011] The application will be described below with reference to exemplary embodiments, which are shown in the drawings, and from which other advantages and modifications can be deduced. Herein:
[0012] Figure 1 a schematic cross-sectional view of a compressor according to an embodiment described herein is shown; and
[0013] Figure 2 a schematic cross-sectional view of a turbo-machinery according to an embodiment described herein is shown. DETAILED DESCRIPTION
[0014] Various embodiments are described below, each of which illustrates one or more examples. Each example is intended to illustrate and not to limit the scope of the application. For example, features shown or described as part of one embodiment can be used with any other embodiment or combined with any other embodiment to form another embodiment. The disclosure is intended to include such modifications and variations.
[0015] In the following description of drawings, like reference numerals refer to like or similar components. Generally, only the differences between the various embodiments are described. Descriptions of one part or aspect in one embodiment can also refer to a corresponding part or corresponding aspect in another embodiment, unless otherwise stated.
[0016] Figure 1 and Figure 2 The coordinate system shown illustrates the radial direction r and the axial direction x mentioned in this disclosure.
[0017] refer to Figure 1 A compressor 10 according to this disclosure is described. In particular, the compressor 10 is a compressor for turbomachinery (e.g., a turbocharger). For example, the compressor may be a radial compressor or a diagonal compressor.
[0018] In the context of turbomachinery, radial compressors and diagonal compressors refer to different types of compressors used in turbomachinery such as gas turbines, turbochargers, or turbochargers. Radial compressors typically consist of a housing with a central rotor, which is usually fitted with curved blades. The working medium, typically a gas, is drawn in axially and then compressed radially outward to increase its pressure.
[0019] Diagonal compressors operate similarly to radial compressors. The main difference lies in the arrangement of the blades in a diagonal compressor, which are angled diagonally to the axis of rotation. This results in a combination of radial and axial compression of the gas. Diagonal compressors are typically used in applications requiring high pressure boosting and large volumetric flow rates.
[0020] Both radial and diagonal compressors play a crucial role in turbomachinery by increasing power, pressure, and the volumetric flow rate required. The choice between radial and diagonal compressors depends on the specific requirements of the application, operating conditions, and other factors.
[0021] According to one embodiment, which can be combined with other embodiments described herein, the compressor 10 includes an outer compressor housing 11 and an inner compressor housing 12, which provide a helical space 13. The outer compressor housing may be a one-piece design. In other words, the outer compressor housing may be formed from a single integral component. Alternatively, the outer compressor housing may be composed of several housing components that together form the outer compressor housing. Similarly, the inner compressor housing may be a one-piece design, i.e., it may be composed of a single integral component. Alternatively, the inner compressor housing may be formed from several housing components that together form the inner compressor housing.
[0022] from Figure 1 It can be seen that the outer compressor housing 11 and the inner compressor housing 12 are configured such that they together form a helical space 13.
[0023] In the present disclosure, the term "spiral space" generally refers to a space or channel formed by the outer compressor housing and the inner compressor housing. The spiral space is a spiral-shaped space which guides the gas flow through the compressor and is generally configured such that the gas is continuously guided to the outlet of the compressor and a uniform pressure build-up is generated. The spiral-shaped arrangement of the spiral space has the advantage that it enables a good utilization of the available space and reduces flow resistance. Thus, an efficient and low-friction flow of the gas is ensured, which increases the compressor power.
[0024] Furthermore, the compressor 10 comprises a diffuser 14 having a diffuser channel 15. The diffuser 14 is generally arranged downstream of the rotor 102, in particular of the compressor wheel. The main function of the diffuser is to reduce the velocity of the gas and to increase the static pressure. In other words, the diffuser enables to slow down the flow velocity of the compressed gas and to increase the static pressure. This is achieved by widening the diffuser channel 15, the cross-section of which generally increases gradually in the flow direction.
[0025] As Figure 1 shown in the example of Fig. 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 the diffuser plate 16. The second side wall 152 formed by the diffuser plate 16 is the side wall of the diffuser channel 15 at the bearing housing side. The diffuser plate 16 is generally an annular disc. The diffuser plate 16 comprises a curved outflow area 161 which is designed to deflect the flow after it flows out of the diffuser channel 15. The outflow area 161 is generally concavely curved. Thus, a partial flow deflection of the spiral can advantageously take place in the diffuser itself.
[0026] As Figure 1 shown in the example of Fig. 1, a first radial position R1 of a first interface S1 between the diffuser plate 16 and the outer compressor housing 11 is lower than a second radial position R2 of a second interface S2 between the outer compressor housing 11 and the inner compressor housing 12. As Figure 1 shown in the example of Fig. 1, the first interface S1 is generally arranged at the bearing housing side. In comparison to the first interface S1, the second interface S2 is further away from the bearing housing 20 in the axial direction x.
[0027] As can be seen from the embodiments described herein, it is apparent that the provided compressor is advantageously an improved compressor in terms of assembly simplicity and interface architecture for turbomachinery involving sleeve designs, in particular turbochargers. In particular, an additional radial installation space is advantageously created for configuring an optimal interface architecture between the compressor housing and the bearing housing.
[0028] For turbomachinery, the cartridge design refers to a construction pattern in which the core of the turbomachinery is configured as a self-contained unit, called a cartridge. The cartridge typically includes one or more rotors, such as compressor and / or turbine wheels, and associated bearing assemblies. In the case of a turbocharger, the cartridge design refers to a construction pattern in which the turbocharger is subdivided into multiple components or modules. Each module performs a specific function and can be serviced or replaced independently of the other modules.
[0029] In the cartridge design, the turbocharger is typically subdivided into three main components. The turbine housing can be considered the first main component. The turbine housing is the part of the turbocharger that comes into contact with the hot exhaust gases. The turbine housing encloses the turbine wheel. The compressor housing of the compressor can be considered the second main component and, in the case of a turbocharger, it is responsible for compressing fresh air. The compressor housing encloses the compressor wheel. The compressor housing is connected to the intake system of the engine and can be replaced independently of the turbine housing. The cartridge can be considered the third main component. The cartridge is the actual core of the cartridge design. The cartridge includes one or more rotors, such as compressor and / or turbine wheels, and bearing units. The cartridge is considered a self-contained unit and can be removed and replaced as a whole without removing the turbine housing or the compressor housing, thus making servicing and repair of the turbocharger easier.
[0030] According to an embodiment, which can be combined with other embodiments described herein, the transition from the curved outflow area 161 of the diffuser plate 16 to the inner side 131 of the spiral space of the outer compressor housing 11 is tangentially designed. In the context described above, the term "transition" refers to the structural connection or joint design between the curved outflow area 161 of the diffuser plate 16 and the inner side 131 of the spiral space of the outer compressor housing 11.
[0031] The tangential configuration of the transition means that the two adjacent areas have a smooth and continuous connection, where the flow direction transitions uniformly from the curved surface of the diffuser plate to the inner side of the spiral space of the outer compressor housing. Typically, the transition has no sharp edges or sudden changes in direction. The tangential transition is advantageous for minimizing flow losses, turbulence, or pressure losses and ensuring efficient flow guidance.
[0032] According to an embodiment, which can be combined with other embodiments described herein, the diffuser 14 has a vane ring comprising a plurality of vanes 17 arranged at least partially in the diffuser channel 15. In other words, the plurality of vanes 17 can be arranged partially or completely in the diffuser channel 15. The plurality of vanes 17 can be connected to the first side wall 151 and / or the second side wall 152. For example, the vanes 17 can be integrally formed with the first side wall 151 and / or the second side wall 152.
[0033] According to an embodiment, which can be combined with other embodiments described herein, the curved outflow region 161 of the diffuser plate 16 is a rotationally symmetrical design with respect to the central rotational axis 101 of the compressor 10. The rotationally symmetrical embodiment of the curved outflow region is advantageous in terms of cost-effectiveness of the machining or production.
[0034] According to an embodiment, which can be combined with other embodiments described herein, the first side wall 151 and the second side wall 152 are arranged so as to diverge from each other in the flow direction at least partially.
[0035] According to an embodiment, which can be combined with other embodiments described herein, the radial starting position R k of the curved region 161 is located between the radial position R A of the trailing edge of the blade 17 of the diffuser 14 and the radius R A of the diffuser plate 16. In other words, the radial position R k of the outflow edge of the blade 17 of the diffuser 14 is located below the radial starting position R k of the curved region 161 and above the radius R A of the diffuser plate 16. For example, the radial starting position R k of the curved region 161 is located between the radial position R k of the outflow edge of the blade 17 of the diffuser 14 and the radial position R A of the outlet opening of the diffuser 14 (R D < R A ≤ R k ≤ R D ). Alternatively, the radial starting position R k of the curved region 161 is located between the radial position R D of the outlet opening of the diffuser 14 and the radius R D of the diffuser plate 16 (R k ≤ R
[0036] According to an embodiment, which can be combined with other embodiments described herein, the ratio D / R of the thickness D of the diffuser plate to the radius R of the diffuser plate 16 is selected from the range 0.02 ≤ D / R ≤ 0.10.
[0037] According to an embodiment, which can be combined with other embodiments described herein, the outer compressor housing 11 has one or more fastening means receptacles 111, which are arranged on the bearing housing side, behind the diffuser plate 16. In particular, the one or more fastening means receptacles 111 are arranged between the diffuser plate 16 and the bearing housing 20. From Figure 1It can be seen that the one or more fastening device receptacles 111 are designed to connect the outer compressor housing 11 to the bearing housing 20 by means of one or more fastening devices 22. Typically, the one or more fastening device receptacles 111 are one or more axial fastening device receptacles. The one or more axial fastening device receptacles typically extend parallel to a central rotational axis 101 of the compressor 10.
[0038] According to an embodiment, which can be combined with other embodiments described herein, a gap 18 is provided between the diffuser plate 16 and the outer compressor housing 11, which gap is arranged at the bearing housing side, at least partially behind the curved outflow region 161 of the diffuser plate 16, as shown in the example of Figure 1 The gap 18 is designed to accommodate a portion of one or more fastening devices 22 for connecting the outer compressor housing 11 to the bearing housing 20. For example, the portion of the fastening device 22 accommodated in the gap 18 can be a releasable fastening element, in particular a screw head or a nut.
[0039] Figure 2 A schematic cross-sectional view of a turbomachine 40 according to the present disclosure is shown. For example, the turbomachine 40 can be a turbocharger.
[0040] According to an embodiment, which can be combined with other embodiments described herein, the turbomachine 40 comprises a compressor 10 according to one embodiment described herein, which compressor has an outer compressor housing 11 and an inner compressor housing 12. Furthermore, the turbomachine comprises a bearing housing 20, which is connected to the outer compressor housing.
[0041] According to an embodiment, which can be combined with other embodiments described herein, the turbomachine 40 further comprises a gas outlet housing 31 of a turbine 30. Typically, the gas outlet housing 31, the bearing housing 20 and the outer compressor housing 11 are connected to each other by means of one or more fastening devices 22. The one or more fastening devices 22 typically extend through the bearing housing 20 by means of one or more axial fastening device receptacles 21. Typically, the one or more axial fastening device receptacles 21 are through openings, in particular through holes, which extend through the bearing housing 20.
[0042] According to an 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 one piece or can consist of two or more parts. Typically, the turbine diffuser 32 is connected to the gas outlet housing 31 by means of axial fasteners 33. As Figure 2As shown by way of example, the outer radius R4 of the turbine diffuser 32 is generally lower than the radial position R3 of the one or more fastening means 22 by means of which the outer compressor casing 11, the bearing casing 20 and the gas outlet casing 31 are connected. It goes without saying that the radial position R3 of the one or more fastening means 22 is generally lower than the first radial position R1 of the first interface S1 between the diffuser plate 16 and the outer compressor casing 11.
[0043] As can be seen from the embodiments described herein, the present application advantageously provides a compressor and a turbomachine which are advantageously improved in terms of the interface architecture of the sleeve design, with a consequent improvement in assembly simplicity, in particular in the case of maintenance, thus enabling a reduction in the associated costs.
[0044] List of reference signs
[0045] 10 compressor
[0046] 101 rotational axis
[0047] 102 rotor
[0048] 11 outer compressor casing
[0049] 111 fastening means accommodation of the outer compressor casing
[0050] 12 inner compressor casing
[0051] 13 spiral space
[0052] 131 inner side of the spiral space
[0053] 14 diffuser
[0054] 15 diffuser channel
[0055] 151 first side wall
[0056] 152 second side wall
[0057] 16 diffuser plate
[0058] 161 curved outflow region
[0059] 17 blade
[0060] 18 gap
[0061] 20 bearing casing
[0062] 21 axial fastening means accommodation
[0063] 22 fastening means
[0064] 30 turbine
[0065] 31 gas outlet housing
[0066] 32 turbine diffuser
[0067] 33 axial fastener
[0068] 34 turbine wheel
[0069] 40 turbomachinery
[0070] R1 first radial position
[0071] R2 second radial position
[0072] R3 radial position of fastening means 22
[0073] R4 outer radius of turbine diffuser
[0074] R A radial position of diffuser blade trailing edge
[0075] R D radial position of diffuser outlet opening
[0076] R k radial start position of bend region
[0077] S1 first interface
[0078] S2 second interface
[0079] D thickness of diffuser plate
[0080] R radius of diffuser plate
[0081] x axial direction
[0082] r radial direction
Claims
1. A compressor (10), particularly a radial compressor or a diagonal compressor, comprising: - The outer compressor housing (11) and the inner compressor housing (12) provide the helical space (13). - A diffuser (14) having a diffuser channel (15) formed by a first sidewall (151) and a second sidewall (152), wherein the first sidewall (151) is provided by the inner compressor housing (12), and wherein the second sidewall (152) is provided by a diffuser plate (16), wherein the second sidewall (152) formed by the diffuser plate (16) is the sidewall of the diffuser channel (15) on the bearing housing side, wherein the diffuser plate (16) includes a curved outflow region (161) designed to deflect the flow after it flows out of the diffuser channel (15), wherein a first radial position (R1) of a first interface (S1) between the diffuser plate (16) and the outer compressor housing (11) is lower than a second radial position (R2) of a second interface (S2) between the outer compressor housing (11) and the inner compressor housing (12).
2. The compressor (10) as claimed in claim 1, wherein the transition from the curved outflow region (161) of the diffuser plate (16) to the inner side (131) of the spiral space of the outer compressor housing (11) is tangentially designed.
3. The compressor (10) of claim 1 or 2, wherein the diffuser (14) has a blade ring comprising a plurality of blades (17) arranged at least partially in the diffuser channel (15).
4. The compressor (10) as claimed in any one of claims 1 to 3, wherein the curved outflow region (161) of the diffuser plate (16) is designed to be rotationally symmetrical about the central axis of rotation (101) of the compressor.
5. The compressor (10) as claimed in any one of claims 1 to 4, wherein the first sidewall (151) and the second sidewall (152) are arranged such that they are at least partially diverging from each other in the flow direction.
6. The compressor (10) as claimed in any one of claims 1 to 5, wherein the radial starting position (R) of the curved region (161) k The radial position (R) of the trailing edge of the blade (17) of the diffuser (14) A The radius R between the diffuser plate (16) and the radius R of the diffuser plate (16).
7. The compressor (10) according to any one of claims 1 to 6, wherein the ratio of the thickness D of the diffuser plate to the radius R of the diffuser plate (16) is 0.02 ≤ D / R ≤ 0.
10.
8. The compressor (10) according to any one of claims 1 to 7, wherein the outer compressor housing (11) has a fastening device receiving portion (111) arranged on the bearing housing side behind the diffuser plate (16) and designed to connect the outer compressor housing (11) to the bearing housing (20), wherein the fastening device receiving portion (111) is an axial fastening device receiving portion.
9. The compressor (10) as claimed in any one of claims 1 to 8, wherein a gap (18) is provided between the diffuser plate (16) and the outer compressor housing (11), the gap being arranged on the bearing housing side, at least partially behind the curved outflow region (161) of the diffuser plate (16), and designed to accommodate a portion of a fastening device (22) for connecting the outer compressor housing (11) to the bearing housing (20), wherein, in particular, a portion of the fastening device (22) is a screw head or nut.
10. A turbomachinery (40), particularly a turbocharger, having a bearing housing (20) and a compressor (10) as claimed in any one of claims 1 to 9, wherein an outer compressor housing (11) is connected to the bearing housing (20), and particularly wherein the compressor (10) is a compressor as claimed in claims 8 and / or 9.
11. The turbomachinery (40) of claim 10, further comprising a gas outlet housing (31) of the turbine (30), wherein the gas outlet housing (31), the bearing housing (20) and the external compressor housing (11) are connected to each other by means of a fastening device (22), wherein the fastening device (22) extends through the bearing housing (20) via an axial fastening device receptacle (21), the axial fastening device receptacle (21) being, in particular, a bore.
12. The turbomachinery (40) of claim 11, wherein the turbine (30) is an axial turbine and has a turbine diffuser (32) connected to the gas outlet housing (31) by an axial fastener (33), wherein the outer radius (R4) of the turbine diffuser (32) is lower than the radial position (R3) of the fastening device (22).