Compressors and turbomachinery having compressors
The centrifugal/mixed-flow compressor with a helical space and diffuser passage improves assembly and interface structure in turbomachinery by creating additional radial installation space and utilizing a tangential transition and fastening means, addressing manufacturing cost and ease of assembly challenges.
Patent Information
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- アクセラロン スウィツァーランド リミテッド
- Filing Date
- 2024-06-18
- Publication Date
- 2026-07-01
AI Technical Summary
Conventional compressors and turbomachinery face challenges in manufacturing cost, ease of assembly, and interface structure, particularly in turbomachinery employing a cartridge concept.
The design of a centrifugal/mixed-flow compressor with a helical space and a diffuser passage featuring a diffuser plate with a curved outlet region, creating additional radial installation space for improved interface structure and ease of assembly, utilizing a tangential transition and fastening means to couple the compressor housing to the bearing housing.
Enhances ease of assembly and interface structure, reducing maintenance costs and improving operational efficiency in turbomachinery, particularly turbochargers, by providing a more efficient and cost-effective coupling mechanism.
Smart Images
Figure 2026521773000001_ABST
Abstract
Description
[Technical Field]
[0001] This invention relates to the field of compressors, particularly to centrifugal / mixed-flow compressors. Furthermore, this invention relates to the field of turbomachinery with compressors, particularly to turbochargers. [Background technology]
[0002] The compressor plays a crucial role in turbomachinery used in internal combustion engines, particularly turbochargers. Its primary purpose is to increase the amount of air required in the combustion chamber by compressing the incoming air. As a result, a larger volume of air becomes available to optimize the combustion process, leading to improved engine power and efficiency.
[0003] Centrifugal / mixed-flow compressors are a specialized type of compressor widely used in turbomachinery. They are characterized by their high pressure boost, which generates a large pressure difference and thus provides high power density. Furthermore, their compact structure and high-speed operation make them suitable for applications with limited installation space, such as internal combustion engines.
[0004] It is known that conventional compressors can be further improved in terms of manufacturing cost, ease of assembly, and interface structure, especially in turbomachinery employing a cartridge concept. [Overview of the project] [Problems that the invention aims to solve]
[0005] Accordingly, an object of the present invention is to provide compressors and turbomachinery that can partially or completely overcome one or more of the drawbacks known from the prior art, particularly those relating to manufacturing cost, ease of assembly, and interface structure. [Means for solving the problem]
[0006] To achieve the above-mentioned objectives, compressors and turbomachinery described in the independent claims are provided. Further aspects, advantages, and features of the present invention can be found in the dependent claims, specification, and accompanying drawings.
[0007] According to one aspect of the present invention, a compressor, more particularly a centrifugal / mixed-flow compressor, is provided. The compressor comprises an outer compressor housing and an inner compressor housing that provide a helical space. Furthermore, the compressor comprises a diffuser having a diffuser passage 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 side wall of the diffuser passage on the bearing housing side. The diffuser plate has a curved outlet region designed to deflect the flow after it leaves the diffuser passage. The first radial position of the first interface between the diffuser plate and the outer compressor housing is lower than the second radial position of the second interface between the outer compressor housing and the inner compressor housing.
[0008] Accordingly, the compressor provided is advantageously improved in terms of ease of assembly and interface structure for turbomachinery, specifically turbochargers, employing a cartridge concept. Specifically, additional radial installation space is advantageously created to constitute an improved interface structure between the compressor housing and the bearing housing.
[0009] A second aspect of the present invention provides a turbomachinery, more particularly a turbocharger. The turbomachinery 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 providing a helical space. The outer compressor housing is coupled to the bearing housing. More specifically, the outer compressor housing has fastening means receiving portions, which are located on the bearing housing side behind the diffuser plate and are designed to couple the outer compressor housing to the bearing housing. Typically, a space is provided between the diffuser plate and the outer compressor housing, and this space is located on the bearing housing side behind at least a portion of the curved outflow region of the diffuser plate. More specifically, this space is designed to accommodate fastening means, such as a portion of a screw head or nut, for couple the outer compressor housing to the bearing housing.
[0010] Therefore, a turbomachine is advantageously provided in which the coupling between the outer compressor housing and the bearing housing is improved, thereby improving ease of assembly.
[0011] The present invention will be described below with reference to exemplary embodiments shown in the drawings, from which further advantages and modifications can be derived. [Brief explanation of the drawing]
[0012] [Figure 1] This is a schematic cross-sectional view of a compressor according to an embodiment described herein. [Figure 2] This is a schematic cross-sectional view of a turbomachinery according to an embodiment described herein. [Modes for carrying out the invention]
[0013] The following describes various embodiments in which one or more examples are shown in each figure. Each example is for illustrative purposes and should not be construed in a limiting sense. For example, features shown or described as part of one embodiment can be used on or in combination with other embodiments to obtain other embodiments. The present disclosure intends to include such modifications and variations.
[0014] In the following description of the drawings, the same reference numerals refer to the same or similar components. Generally, only the differences regarding individual embodiments are described. Unless otherwise specified, the description of a component or aspect in one embodiment can refer to the corresponding component or corresponding aspect in another embodiment.
[0015] The coordinate systems shown in FIGS. 1 and 2 indicate the radial direction r and the axial direction x referred to in the present disclosure.
[0016] Referring to FIG. 1, the compressor 10 according to the present disclosure will be described. Specifically, the compressor 10 is a compressor for a turbomachine, such as a turbocharger. For example, the compressor can be a radial compressor or a diagonal compressor.
[0017] Regarding turbomachines, radial compressors and diagonal compressors refer to different types of compressors used in turbomachines such as gas turbines, superchargers or turbochargers. Generally, a radial compressor includes a housing having a central rotor with generally curved blades attached thereto. The working medium, usually a gas, is sucked in axially and compressed radially outward to increase the pressure of the working medium.
[0018] The axial-flow compressor has an operating method similar to that of a centrifugal compressor. The main difference is that the blades of the axial-flow compressor are arranged at an oblique angle to the axis of rotation. This combines the radial and axial compression of the gas. Axial-flow compressors are often used in applications where both a high level of pressure rise and a large volume flow rate are required.
[0019] Both centrifugal compressors and axial-flow compressors play important roles in turbo machinery in improving output, increasing pressure, and generating the required volume flow rate. The choice between a centrifugal compressor and an axial-flow compressor depends on the specific requirements of the application, operating conditions, and other factors.
[0020] According to one embodiment that 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 spiral space 13. The outer compressor housing can be of an integrated design. In other words, the outer compressor housing can be formed by a single integrated component. Alternatively, the outer compressor housing can be composed of a plurality of housing components that together form the outer compressor housing. Similarly, the inner compressor housing can be of an integrated design, i.e., it can be composed of a single integrated component. Alternatively, the inner compressor housing can be formed by a plurality of housing components that together form the inner compressor housing.
[0021] As can be seen from FIG. 1, the outer compressor housing 11 and the inner compressor housing 12 are configured to together form a spiral space 13.
[0022] In this disclosure, the term “helical space” typically refers to a space or flow path formed by an outer compressor housing and an inner compressor housing. A helical space is a spirally shaped space that guides the flow of gas through a compressor, and is typically configured to guide the gas continuously to the compressor outlet and to achieve a uniform pressure rise. The spiral shape of the helical space has the advantage of making effective use of available space and reducing flow resistance. As a result, an efficient and frictionless flow of gas is ensured, leading to an increase in compressor output.
[0023] In addition, the compressor 10 is equipped with a diffuser 14 having a diffuser passage 15. The diffuser 14 is typically located downstream of the rotor 102, more specifically, downstream of the compressor wheel. The main function of the diffuser is to reduce the velocity of the gas and increase its static pressure. In other words, the diffuser allows for a slower flow velocity and increased static pressure of the compressed gas. This is achieved by widening the diffuser passage 15, whose cross-section typically gradually increases in the direction of flow.
[0024] As illustrated in Figure 1, the diffuser flow path 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 flow path 15 on the bearing housing side. The diffuser plate 16 is typically an annular disc. The diffuser plate 16 includes a curved outflow region 161, which is designed to deflect the flow after it leaves the diffuser flow path 15. The outflow region 161 is typically concave. Thus, advantageously, some of the helical flow deflection can be performed by the diffuser itself.
[0025] As illustrated in Figure 1, the first radial position R1 of the first interface S1 between the diffuser plate 16 and the outer compressor housing 11 is lower than the second radial position R2 of the 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 located 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 x direction.
[0026] From the embodiments described herein, it is evident that the compressors provided are advantageously improved in terms of ease of assembly and interface structure for turbomachinery, particularly turbochargers employing a cartridge concept. In particular, additional radial installation space is advantageously created to constitute an optimal interface structure between the compressor housing and the bearing housing.
[0027] In the case of turbomachinery, the cartridge concept refers to a structural configuration in which the core of the turbomachinery is composed of a self-contained unit, which is called a cartridge. This cartridge typically comprises one or more rotors, such as a compressor wheel and / or a turbine wheel, and associated bearing assemblies. In the case of turbochargers, the cartridge concept refers to a structural configuration in which the turbocharger is subdivided into multiple components or modules. Each module performs one specific function and can be serviced or replaced independently of the other modules.
[0028] In the cartridge concept, 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 surrounds the turbine wheel. The compressor housing can be considered the second main component, and in the turbocharger, this is responsible for compressing the outside 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 actual heart of the cartridge concept. This cartridge comprises one or more rotors, such as a compressor wheel and / or a turbine wheel, and a bearing unit. The cartridge is considered a self-contained unit and can be removed and replaced as a whole without removing the turbine housing or compressor housing, thus facilitating maintenance and repair of the turbocharger.
[0029] According to one embodiment, which can be combined with other embodiments described herein, the transition from the curved outlet region 161 of the diffuser plate 16 to the inner helical space 131 of the outer compressor housing 11 is a tangential design. In connection with the foregoing, the term “transition” refers to the concept of a structural connection or joint between the curved outlet region 161 of the diffuser plate 16 and the inner helical space 131 of the outer compressor housing 11.
[0030] A tangential configuration of the transition means that the two adjacent regions have a gradual and continuous connection, and the flow direction transitions uniformly from the curved surface of the diffuser plate to the inside of the helical space of the outer compressor housing. Typically, this transition does not have sharp edges or abrupt changes of direction. A tangential transition is advantageous for minimizing flow loss, turbulence, or pressure loss and ensuring efficient flow guidance.
[0031] According to one embodiment that can be combined with other embodiments described herein, the diffuser 14 has a vane ring including a plurality of vanes 17 that are at least partially disposed within the diffuser flow path 15. In other words, the plurality of vanes 17 can be partially or fully disposed within the diffuser flow path 15. The plurality of vanes 17 can be coupled 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.
[0032] According to one embodiment that can be combined with other embodiments described herein, the curved outflow region 161 of the diffuser plate 16 has a rotationally symmetric design with respect to the central rotation axis 101 of the compressor 10. The rotationally symmetric embodiments of the curved outflow region are advantageous for cost-effective machining or manufacturing.
[0033] According to one embodiment that can be combined with other embodiments described herein, the first side wall 151 and the second side wall 152 are arranged to be at least partially divergent from each other in the direction of the flow.
[0034] According to one embodiment that can be combined with other embodiments described herein, the radial starting position R of the curved region 161 k is located between the radial position R of the trailing edge of the vane 17 of the diffuser 14 A and the radius R of the diffuser plate 16. In other words, the radial position R of the outflow end of the vane 17 of the diffuser 14 A is lower than the radial starting position R of the curved region 161 k , and the radial starting position R of the curved region 161 k is lower than the radius R of the diffuser plate 16 (R A < R k < R). For example, the radial starting position R of the curved region 161 k is the radial position R of the outflow end of the vane 17 of the diffuser 14 A and the radial position R of the outlet opening of the diffuser 14D It can be located between (R A <R k ≤R D Alternatively, the radial starting position R of the curved region 161. k R is the radial position of the outlet opening of the diffuser 14. D It can be positioned between the radius R of the diffuser plate 16 (R D <R k ≤R).
[0035] According to one embodiment that 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.
[0036] According to one embodiment, which can be combined with other embodiments described herein, the outer compressor housing 11 has one or more fastening means receiving portions 111 located on the bearing housing side behind the diffuser plate 16. More specifically, the one or more fastening means receiving portions 111 are located between the diffuser plate 16 and the bearing housing 20. As can be seen from Figure 1, the one or more fastening means receiving portions 111 are designed to connect the outer compressor housing 11 to the bearing housing 20 by one or more fastening means 22. Typically, the one or more fastening means receiving portions 111 are one or more axial fastening means receiving portions. The one or more axial fastening means receiving portions typically extend parallel to the central rotation axis 101 of the compressor 10.
[0037] According to one embodiment, which can be combined with other embodiments described herein, an interspace 18 is provided between the diffuser plate 16 and the outer compressor housing 11, the interspace being located on the bearing housing side behind at least a portion of the curved outflow region 161 of the diffuser plate 16, as illustrated in Figure 1. The interspace 18 is designed to accommodate a portion of one or more fastening means 22 for coupling the outer compressor housing 11 to the bearing housing 20. For example, the portion of the fastening means 22 accommodated in the interspace 18 may be a releasable fastening element, more specifically, a screw head or a nut.
[0038] Figure 2 is a schematic cross-sectional view of the turbomachinery 40 according to this disclosure. For example, the turbomachinery 40 can be a turbocharger.
[0039] According to one embodiment that can be combined with other embodiments described herein, the turbomachine 40 comprises a compressor 10 having an outer compressor housing 11 and an inner compressor housing 12 according to one of the embodiments described herein. Furthermore, the turbomachine comprises a bearing housing 20 coupled to the outer compressor housing.
[0040] According to one embodiment, which can be combined with other embodiments described herein, the turbomachinery 40 further comprises a gas outlet housing 31 for the turbine 30. Typically, the gas outlet housing 31, the bearing housing 20, and the outer compressor housing 11 are connected to each other by one or more fastening means 22. The one or more fastening means 22 typically extend through the bearing housing 20 by one or more axial fastening means receiving portions 21. Typically, the one or more axial fastening means receiving portions 21 are through openings, more specifically through holes, that extend through the bearing housing 20.
[0041] According to one embodiment, which can be combined with other embodiments described herein, the turbine 30 is an axial flow turbine. The turbine 30 may have a turbine diffuser 32. The turbine diffuser 32 may be a single unit or composed of two or more parts. Typically, the turbine diffuser 32 is coupled to the gas outlet housing 31 via axial fasteners 33. As illustrated in Figure 2, the outer radius R4 of the turbine diffuser 32 is typically lower than the radial position R3 of one or more fasteners 22 to which the outer compressor housing 11, the bearing housing 20, and the gas outlet housing 31 are coupled. It is obvious that the radial position R3 of one or more fasteners 22 is typically lower than the first radial position R1 of the first interface S1 between the diffuser plate 16 and the outer compressor housing 11.
[0042] As will be apparent from the embodiments described herein, the present invention advantageously provides compressors and turbomachinery with an advantageously improved interface structure for the cartridge concept, and thus, in particular, ease of assembly in the case of maintenance can be improved, thereby reducing the associated costs. [Explanation of symbols]
[0043] 10 Compressor 101 Rotation axis 102 Rotor 11. External compressor housing 111 Fastening means receiving part of the outer compressor housing 12. Internal compressor housing 13 Spiral space 131 Inside the spiral space 14 Diffuser 15 Diffuser channel 151 First side wall 152 Second side wall 16 Diffuser Plates 161 Curved Outflow Region 17 Bane 18 Space 20 Bearing Housing 21 Axial fastening means receiving part 22 Fastening means 30 Turbine 31 Gas outlet housing 32 Turbine Diffuser 33 Axial fasteners 34 Turbine Wheel 40 Turbomachinery R1 First radial position R2 Second radial position Radial position of R3 fastening means 22 R4 Turbine Diffuser Outer Radius R A Radial position of the trailing edge of the diffuser vane R D Radial position of the diffuser outlet opening R k Radial starting position of the curved region S1 First interface S2 Second interface D Diffuser plate thickness R Diffuser plate radius x-axis direction r radial direction
Claims
1. Compressor (10), more specifically a centrifugal / mixed-flow compressor, An outer compressor housing (11) and an inner compressor housing (12) that provide a spiral space (13), A diffuser (14) having a diffuser channel (15) formed by a first side wall (151) and a second side wall (152), Equipped with, A compressor (10) wherein the first side wall (151) is provided by the inner compressor housing (12), and 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 flow path (15) on the bearing housing side, the diffuser plate (16) includes a curved outlet region (161) designed to deflect the flow after it has exited the diffuser flow path (15), and the first radial position (R1) of the first interface (S1) between the diffuser plate (16) and the outer compressor housing (11) is lower than the second radial position (R2) of the second interface (S2) between the outer compressor housing (11) and the inner compressor housing (12).
2. The compressor (10) according to claim 1, wherein the transition from the curved outflow region (161) of the diffuser plate (16) to the inner helical space (131) of the outer compressor housing (11) is tangentially designed.
3. The compressor (10) according to claim 1 or 2, wherein the diffuser (14) has a vane ring comprising a plurality of vanes (17) at least partially arranged within the diffuser flow path (15).
4. The compressor (10) according to any one of claims 1 to 3, wherein the curved outlet region (161) of the diffuser plate (16) is designed to be rotationally symmetric with respect to the central rotation axis (101) of the compressor.
5. The compressor (10) according to any one of claims 1 to 4, wherein the first side wall (151) and the second side wall (152) are arranged to diverge at least partially from each other in the direction of flow.
6. The radial starting position (R) of the curved outflow region (161) k ) is the radial position (R) of the trailing edge of the vane (17) of the diffuser (14). A A compressor (10) according to any one of claims 1 to 5, located between the ) 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 D / R of the thickness D of the diffuser plate (16) 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 means receiving portion (111), the fastening means receiving portion (111) is located on the bearing housing side behind the diffuser plate (16), and is designed to connect the outer compressor housing (11) to the bearing housing (20), and in particular the fastening means receiving portion (111) is an axial fastening means receiving portion.
9. A space (18) is provided between the diffuser plate (16) and the outer compressor housing (11), the space being located on the bearing housing side behind at least a portion of the curved outflow region (161) of the diffuser plate (16) and designed to accommodate a portion of fastening means (22) for coupling the outer compressor housing (11) to the bearing housing (20), the portion of which is a screw head or a nut, according to any one of claims 1 to 8.
10. Turbomachinery (40), more specifically a turbocharger, comprising a compressor (10) according to any one of claims 1 to 9 and a bearing housing (20), wherein the outer compressor housing (11) is coupled to the bearing housing (20), and more specifically the compressor (10) is the compressor according to claim 8 and / or 9.
11. The turbomachinery (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 each other by fastening means (22), the fastening means (22) extending through an axial fastening means receiving portion (21), and more specifically through a bore, into the bearing housing (20).
12. The turbomachinery (40) according to claim 11, wherein the turbine (30) is an axial flow turbine and has a turbine diffuser (32) coupled to the gas outlet housing (31) by an axial fastener (33), and the outer radius (R4) of the turbine diffuser (32) is lower than the radial position (R3) of the fastener (22).