Turbine unit for supercharging device

Abstract

The invention relates to a turbine unit (10) for a supercharging device (1), comprising a bearing housing (30) and a turbine housing (20), which is coupled to the bearing housing (30) by means of a flange connection (100). The flange connection (100) comprises a turbine housing side flange (110) and a bearing housing side flange (120). The turbine housing-side flange (110) and the bearing housing-side flange (120) are designed and coupled to each other in such a way that they form an axial spacing region (130) and an axial contact region (140) of the flange connection (100). The axial contact region (140) is arranged radially inward with respect to the axial spacing region (130). The radial distance (RD) between the outer radius (RKA) of the axial contact region and the circumferential radius (RF) of the bearing housing-side flange (120) is at least 3.50 mm.

Description

Technical Field

[0001] The present invention relates to a turbine unit for a supercharging device, a supercharging device for an internal combustion engine or a fuel cell having such a turbine unit, and an engine system having such a supercharging device. Background Art

[0002] An increasing number of new-generation vehicles are equipped with supercharging systems to meet demand targets and legal requirements. When developing supercharging systems, both individual components and the overall system are optimized for reliability and efficiency.

[0003] Known supercharging systems generally have at least one compressor with a compressor wheel connected to a drive unit via a common shaft. The compressor compresses fresh air drawn in by an internal combustion engine or fuel cell. This increases the amount of air or oxygen available to the engine for combustion or to the fuel cell for reaction. This, in turn, contributes to a power increase in the internal combustion engine or fuel cell. Supercharging systems can be equipped with various drive units. Known in the prior art are, in particular, electric superchargers (E-Laders), in which the compressor is driven by an electric motor, and turbochargers, in which the compressor is driven by a turbine (particularly a radial turbine). Compared to axial-flow turbines (such as those used in aircraft engines), which generally only allow axial inflow, in radial-flow turbines, the exhaust gas flow is directed from a spiral-shaped turbine inlet to the turbine wheel generally radially, and in the case of mixed-flow radial turbines, radially (i.e., with at least a small axial component). In addition to electric superchargers and turbochargers, a combination of these two systems, also known as an electric turbocharger (E-Turbo), is also described in the prior art. For example, an electric turbocharger can be an electrically assisted exhaust gas turbocharger or an electrically assisted supercharging unit or device for a fuel cell.

[0004] To improve turbine efficiency and adapt it to various operating conditions, modern superchargers are equipped with a power regulation device, which can be used to adjust or vary the power generated by the supercharger. Known power regulation devices include variable turbine geometry (VTG) or wastegate valves (WG). A variable turbine geometry is an adjustable guide device used to vary the inflow to the turbine wheel of a turbine. By varying the inflow (e.g., the flow cross-section and inflow angle), the flow velocity of the exhaust gas flow supplied to the turbine wheel can be varied, which results in a corresponding change in the power of the supercharger. Such systems are also known as variable guide vanes, VTG, guide grids, or VTG guide grids.

[0005] Turbine units comprising a bearing housing for supporting a shaft and a turbine housing are known from the prior art, which is connected to the bearing housing via a flange connection. However, current developments for turbines with guide devices, particularly variable turbine geometry with adjustable guide vanes, for use in the high-temperature range of Otto internal combustion engines (typically exceeding 850°C), present known problems with the flange connection. In particular, mechanical and thermal overloads can occur in the flange of the bearing housing after a certain number of temperature cycles during use (i.e., during operation and under various operating conditions). Consequently, cracks can form in areas close to the outer diameter of the bearing housing flange during high-temperature use, shortening the service life of the bearing housing. While this can be counteracted to some extent by optimizing and adapting the materials of the bearing housing or the bearing housing flange, this results in increased costs.

[0006] The object of the present invention is to provide a turbine unit having an improved flange connection between the turbine housing and the bearing housing and, in particular, reducing the thermal and mechanical loads on the flange of the bearing housing. Summary of the Invention

[0007] The present invention relates to a turbine unit for a supercharging device according to patent claim 1, a supercharging device for an internal combustion engine or a fuel cell having such a turbine unit according to patent claim 15, and an engine system having such a supercharging device according to patent claim 16. The dependent patent claims describe advantageous embodiments of the turbine unit.

[0008] According to a first aspect of the present invention, a turbine unit for a supercharger includes a support housing and a turbine housing, which is connected to the support housing via a flange connection. The flange connection includes a turbine housing flange and a support housing flange. The turbine housing flange and the support housing flange are designed and connected to each other in such a way that they form an axial spacing region and an axial contact region of the flange connection. The axial contact region is arranged radially inwardly relative to the axial spacing region. The radial spacing between the outer radius of the axial contact region and the circumferential radius of the support housing flange is at least 3.50 mm.

[0009] As a result, the axial contact between the bearing housing and the turbine housing, in particular between the bearing housing flange and the turbine housing flange, can be shifted radially inward from a region near the outer diameter of the bearing housing flange. This shifts the heat transfer from the turbine housing to the bearing housing and the resulting maximum temperature to a smaller radius, where susceptibility to crack formation in the bearing housing flange is reduced and improved heat dissipation or cooling can be achieved. Furthermore, by shifting the axial contact region radially inward by at least 3.5 mm, the force transmission in the flange connection during temperature cycles (where various thermal expansions may occur) can be improved, thereby reducing the mechanical loads on the bearing housing flange. This can result in cost savings, as, for example, the bearing housing flange and the bearing housing do not need to be made of higher-quality materials for high-temperature applications. The design according to the present invention can significantly increase the service life of the bearing housing flange. This advantageous effect is particularly achieved when the turbine unit includes a guide device in the form of a variable turbine geometry and is used in conjunction with an (Otto) internal combustion engine. Because, in particular in this embodiment, high exhaust gas temperatures (often exceeding 850° C.) can occur in the turbine housing, the flange connections, in particular the flange on the turbine housing and the flange on the bearing housing, must be larger (e.g., compared to applications without guides, where the turbine unit only has a wastegate and / or no (Otto) internal combustion engine). The optimized flange connections according to the invention can also provide the aforementioned advantageous effects for this application area.

[0010] In one embodiment, the turbine housing-side flange and the bearing housing-side flange can be in direct axial contact with one another in the axial contact region. In one embodiment, the turbine housing-side flange and the bearing housing-side flange can be continuously spaced apart from one another in the axial spacing region, in particular in the axial direction and along their radial extension. The axial spacing region can extend in the radial direction between an outer radius of the axial contact region and a circumferential radius of the bearing housing-side flange. The axial contact region can be arranged directly adjacent to the axial spacing region in the radial direction.

[0011] In one embodiment, the axial contact region can extend radially between an inner radius and an outer radius of the axial contact region. The inner radius of the axial contact region can correspond to an inner radius of the turbine housing adjacent to the bearing housing flange or adjacent to the turbine housing flange.

[0012] In one embodiment, the flange connection can include at least one connecting element coupled to the turbine housing flange and the support housing flange in such a manner that the connecting element generates an axial clamping force between the turbine housing flange and the support housing flange in the axial contact region. Specifically, the connecting element can be arranged in the radial direction such that the connecting element generates an axial force between the turbine housing flange and the support housing flange in the axial spacing region. The axial force is directly transmitted as a clamping force in the axial contact region. The radial location of the axial force exerted by the connecting element can be radially outside of the axial contact region. In one embodiment, the connecting element can be a V-clamp or a threaded connection.

[0013] In one embodiment, the axial contact region may have a first radial width. The axial spacing region may have a second radial width. The ratio of the first radial width to the second radial width may be in a range of 0.20 to 0.70. In one embodiment, the ratio may be in a range of 0.20 to 0.45. In particular, the ratio may be in a range of 0.24 to 0.30. These ratios can reduce the contact cross-section between the bearing housing flange and the turbine housing flange, through which axial heat transfer from the turbine housing to the bearing housing occurs. Furthermore, this ratio can improve the transmission of the clamping force applied axially between the bearing housing flange and the turbine housing flange, particularly in the axial contact region (or into the axial contact region). In particular, during temperature cycles (where various thermal expansions may occur in the flange connection), a gentler or more constant force transmission can be provided in the flange connection. Consequently, this ratio can reduce the thermal and / or mechanical loads on the bearing housing flange. This can reduce crack formation and increase service life.

[0014] The turbine housing-side flange and the bearing housing-side flange can be designed and coupled to one another in such a manner that they form at least one shoulder that provides a radial centering surface fit. In one embodiment, the shoulder can be formed between the outer circumferential surface of the bearing housing-side flange and an axially extending lip of the turbine housing-side flange, which at least partially circumferentially surrounds the bearing housing-side flange. In one embodiment, the at least one shoulder can be arranged radially in an axial spacing region. The shoulder can divide the axial spacing region into a first axial spacing region and at least one second axial spacing region. The first axial spacing region can be arranged radially between the shoulder and the axial contact region. The second axial spacing region can be arranged radially between the shoulder and the circumferential radius of the bearing housing-side flange.

[0015] In one embodiment, the turbine housing-side flange can include an annular projection that extends axially toward the bearing housing-side flange and forms an axial contact surface with the bearing housing-side flange. In particular, an axial contact region can be formed between the axial contact surface and the bearing housing-side flange. The first axial spacing region can be designed as at least one annular recess in the bearing housing-side flange and / or the turbine housing-side flange.

[0016] In one embodiment, the flange connection can include at least one sealing element that is clamped between the turbine housing-side flange and the bearing housing-side flange in an axial spacing region. The sealing element can provide an improved seal between the turbine housing and the bearing housing. The bearing housing-side flange and / or the turbine housing-side flange can include at least one annular recess in which the at least one sealing element is arranged. In one embodiment, the sealing element can be clamped in a first axial spacing region. Alternatively or additionally, the at least one sealing element can be clamped in at least one second axial spacing region.

[0017] The bearing housing side flange may be formed integrally with the bearing housing. The turbine housing side flange may be formed integrally with the turbine housing. The bearing housing side flange and the turbine housing side flange may each be designed to be annular and extend in the radial direction.

[0018] The bearing housing can have at least one annular cooling channel arranged radially inwardly relative to the bearing housing flange and close to the side of the bearing housing facing the turbine housing. The cooling channel in the bearing housing can provide improved heat removal from the bearing housing flange. Combined with the radially inward shifting of the axial contact area, the thermal load on the bearing housing flange can be reduced, thereby reducing crack formation.

[0019] The turbine unit may include a turbine wheel disposed in a receiving space of the turbine housing between a turbine housing inlet and a turbine housing outlet. The turbine unit may include a shaft rotatably supported in a support housing. The turbine wheel is non-rotatably connected to a first end of the shaft. The turbine unit may also include a guide device disposed radially outside of the turbine wheel in the receiving space and circumferentially surrounding the turbine wheel. The guide device may be spaced apart from the turbine housing in the radial direction. This reduces heat transfer to the flange on the turbine housing side and the flange on the support housing side.

[0020] According to a second aspect of the present invention, a supercharging device for an internal combustion engine or a fuel cell includes a turbine unit according to the first aspect of the present invention. Furthermore, the supercharging device includes a compressor having a compressor housing. The compressor housing is coupled to the support housing on a side of the support housing opposite from the turbine housing. The supercharging device can have all of the aforementioned advantageous technical effects. The turbine unit can have all of the aforementioned design options.

[0021] In one embodiment, the turbine unit may include a turbine wheel disposed in a receiving space of a turbine housing. The supercharging device, in particular the turbine unit, may include a shaft rotatably supported in a support housing. The compressor may include a compressor wheel. The turbine wheel and the compressor wheel may be coupled to the shaft at opposite ends thereof in a rotationally fixed manner.

[0022] According to a third aspect of the present invention, an engine system includes the supercharging device according to the second aspect of the present invention. The engine system also includes an internal combustion engine having multiple cylinders. The turbine unit is arranged downstream of the internal combustion engine, and a turbine housing inlet of the turbine housing is fluidically connected to the multiple cylinders. The engine system can have all of the aforementioned advantageous technical effects. The supercharging device can have all of the aforementioned design options.

[0023] In a design solution, the turbine unit may include a guide device. The guide device may have a plurality of adjustable guide blades. The turbine unit may include a turbine impeller, which is arranged in a receiving space of a turbine housing. The guide device may be arranged radially outside the turbine impeller in the turbine housing and circumferentially surround the turbine impeller. The above-mentioned advantageous effects of the flange connection can also be provided, in particular, for a combination of an internal combustion engine with a turbine unit and a guide device in the form of a variable cross-section turbine (i.e., with a plurality of adjustable guide blades). In a design solution, the compressor may be arranged upstream of the internal combustion engine. The compressor housing outlet of the compressor housing may be in fluid connection with the internal combustion engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 An isometric view showing an exemplary supercharging apparatus having a turbine unit and a compressor;

[0025] Figure 2 A sectional view of a turbine unit with a flange connection according to a first embodiment is shown;

[0026] Figure 3A 、 Figure 3B Show Figure 2 Detailed cross-sectional view of the turbine unit;

[0027] Figure 4A sectional view showing a turbine unit with a flange connection according to a second embodiment;

[0028] 5A to 5D Show Figure 4 Detailed cross-sectional view of the turbine unit;

[0029] Figure 6 a graph showing the force curve in a flange connection during temperature cycling;

[0030] Figure 7 A schematic diagram of an engine system with a supercharging device is shown. DETAILED DESCRIPTION

[0031] In the context of the present application, the expressions "axial" and "axial direction" relate to the axis of rotation R of the shaft 70 or turbine wheel 40, the axis of rotation of the turbine unit 10 and the guide device 50. Figures 1 to 5D ), the axial direction is indicated by reference numeral 22. The radial direction 24 is associated here with the axial direction 22. Likewise, the circumferential or peripheral direction 26 is associated here with the axial direction 22. The directions 22 and 24 extend orthogonally to one another.

[0032] Figure 1 A supercharging device 1 is shown. The supercharging device 1 can be used for an internal combustion engine or a fuel cell and / or can be designed or dimensioned accordingly. In other words, the internal combustion engine can include the supercharging device 1. The internal combustion engine can be an Otto internal combustion engine.

[0033] As in Figure 1 As shown in the figure, the supercharging device 1 includes a turbine unit 10 having a turbine and a support housing 30, and a compressor 60. The turbine unit 10 may include an actuating device 80. The supercharging device 1 may be a turbocharger. In the design solution, the supercharging device 1 may also be designed as an electric turbocharger (not shown in the drawings). The turbine unit 10, in particular the turbine, includes a turbine housing 20 in which a turbine wheel 40 is arranged. The turbine may in particular be a radial turbine. The turbine housing 20 defines a turbine housing inlet 21 and a turbine housing outlet 22. The turbine housing inlet 21 may also be referred to as a turbine housing spiral. The turbine wheel 40 is arranged in the receiving space 23 of the turbine housing 20 between the turbine housing inlet 21 and the turbine housing outlet 22. The turbine further comprises a turbine housing rear wall which is connected to the turbine housing 20 on the bearing housing side. Figures 2 to 5D As can be seen in FIG, the turbine housing rear wall can be designed as part of the support housing 30 (in particular by means of the side of the support housing 20 facing the turbine housing 20). Figure 1The supercharging device 1, in particular the turbine unit 10, further comprises a shaft 70 having an axis of rotation R, which is rotatably coupled to the turbine wheel 20. The shaft 70 is rotatably supported in the support housing 30. Here, the axial direction 22 is defined relative to the axis of rotation R. Figure 1 As shown, the compressor 60 includes a compressor housing 61 in which a compressor impeller 62 is arranged. The support housing 30 is coupled (or connected) to the turbine housing 20 by means of a flange connection 100, wherein the flange connection 100 will be described in detail further below. The compressor housing 61 is coupled (or connected) to the support housing 30 on the side of the support housing 30 opposite to the turbine housing 20. The compressor impeller 62 is coupled to the shaft 70 in a rotationally fixed manner at the end of the shaft 70 opposite to the turbine impeller 40. As shown in FIG. Figure 1 As shown, the turbine unit can include a guide device 50 which is arranged radially outside the turbine wheel 40 in the receiving space 23 and circumferentially surrounds the turbine wheel 40 .

[0034] In addition to the guide device, the turbine unit 10 may also include a power regulation device in the form of a wastegate flap, which is configured to close and open a wastegate of the turbine (not shown in the drawings) as required. The wastegate flap may be connected to the actuating device 80 via a rod and / or a control rod.

[0035] In one embodiment, the supercharging device 1 may further include an electric motor (not shown in the figures), which may be arranged in a motor space in the bearing housing 30 . The turbine wheel 40 and / or the compressor wheel 62 may be coupled to the electric motor via a shaft 70 . The electric motor may have a rotor and a stator, wherein the rotor may be coupled to the shaft 70 in a rotationally fixed manner, and the stator may surround the rotor and be coupled to the bearing housing 30 . Furthermore, power electronics for controlling the electric motor may be arranged in the receiving space in the bearing housing 30 . The electric motor may also include a generator mode.

[0036] Figures 2 to 5DA cross-sectional view of the turbine unit 10 is shown. As shown, the guide device 50 can be designed as a variable turbine geometry (VTG). The guide device 50 can include a carrier ring and a plurality of adjustable guide vanes, wherein the adjustable guide vanes are rotatably supported in the carrier ring. Alternatively or additionally, the guide device 50 can include a plurality of fixed guide vanes, wherein the fixed guide vanes are securely arranged on the carrier ring in a predetermined orientation. The guide device is configured to alter the inflow to the turbine wheel 40. Here, the guide device 50 can be configured as a scroll device mounted in the turbine housing 20. The guide device 50 can be preassembled as a scroll device and mounted on the rear wall of the turbine housing, particularly on the side of the support housing 30 facing the turbine housing 20, using at least three pins evenly spaced in the circumferential direction 26. The adjustable guide vanes can be adjusted between a first position, particularly a first end position, and a second position, particularly a second end position. Multiple intermediate positions can be set between the first and second positions. The first position corresponds to the most open position of the guide device 50. The second position corresponds to the least open position of the guide device 50. Thus, the fluid flow from the turbine housing inlet 21 can be variably directed through the flow channel (i.e., where the guide vanes are located) to the turbine wheel 40. Between adjacent guide vanes, nozzle cross-sections (also referred to as intermediate channels) are formed. These nozzle cross-sections are larger or smaller depending on the instantaneous position of the guide vanes and, accordingly, load the turbine wheel 40, which is supported on the axis of rotation R, with more or less fluid (e.g., exhaust gas) from the internal combustion engine or more or less fluid from the fuel cell, so that the turbine wheel 40 drives the compressor wheel 62, which is mounted on the same shaft 70, via the turbine wheel 40. Each guide vane has an inflow edge and an outflow edge. The position of the guide vanes can also be referred to as a positioning or operating position or operating positioning. Therefore, during operation of the turbine unit 10, every possible position of the guide vanes lies between a first position, where the flow channel / flow cross-section is maximized (i.e., most open), and a second position, where the flow channel / flow cross-section is minimized (i.e., least open or most closed). Each "possible position" can be understood as being a position that can be provided during operation. It is known to those skilled in the art that the operating position is variably and automatically changed during operation of the turbine. In order to control the movement or position of the guide vanes, an actuator 80 can be provided, which can be designed in any desired manner, for example electronically or pneumatically. The actuator 80 can be an actuator. Figure 1In the example of FIG, the actuating device 80 is designed pneumatically with a control housing (e.g., a pressurized tank) and a push rod mechanism that transmits the movement of the control housing via one or more intermediate elements, in particular via an adjustment shaft assembly, to the guide device 50 or the adjustable guide vanes. The guide device 50 can be arranged spaced apart from the turbine housing 20 in the radial direction 24.

[0037] Figures 2 to 5D The embodiment of a flange connection 100 between a turbine housing 20 and a bearing housing 30 according to an aspect of the present application is shown. The flange connection 100 comprises a turbine housing-side flange 110 and a bearing housing-side flange 120. The turbine housing-side flange 110 and the bearing housing-side flange 120 are designed and coupled to one another in such a way that they form an axial spacing region 130 and an axial contact region 140 of the flange connection 100. The axial contact region 140 is arranged radially inwardly relative to the axial spacing region 130. Figure 2 and Figure 4 As shown, the support housing side flange 110 includes a circumferential radius R F The axial contact region 140 includes an outer radius R KA At the outer radius R KA and the circumferential radius R F The radial spacing R is defined between D , in particular in the radial direction 24 at the outer radius R KA and the circumferential radius R F The radial distance R is measured between D At least 3.50 mm. In the design, the radial spacing R D Thus, the axial contact between the bearing housing 30 and the turbine housing 20, in particular between the bearing housing side flange 120 and the turbine housing side flange 110, can be formed from the outer diameter or circumferential radius R close to the bearing housing side flange 120. FThe region of contact 140 is shifted radially inward. This shifts the heat transfer from the turbine housing 20 to the bearing housing 30, and the resulting maximum temperature, to a smaller radius where the susceptibility to crack formation in the bearing housing-side flange 120 is reduced and improved heat dissipation or cooling can be achieved. During operation, the turbine unit 10 can be subjected to multiple temperature cycles. By shifting the axial contact region 140 radially inward by at least 3.5 mm, the force transmission in the flange connection 100 during temperature cycles (where various thermal expansions may occur) can be improved, thereby reducing the mechanical loads on the bearing housing-side flange 120. This can result in cost savings, as, for example, the bearing housing-side flange 120 and the bearing housing 30 do not need to be made of higher-quality materials suitable for high-temperature applications. The design of the flange connection 100 according to the present invention can significantly increase the service life of the bearing housing-side flange 120. The advantageous effects described herein can be achieved particularly when the turbine unit 10 includes a guide device 50 in the form of a variable turbine geometry and is used in conjunction with an (Otto) internal combustion engine 3. Because high exhaust gas temperatures (typically exceeding 850° C.) can occur in the turbine housing 20, particularly in this embodiment, the flange connection 100, in particular the flange 110 on the turbine housing side and the flange 120 on the bearing housing side, must be larger (e.g., compared to applications without guides, turbine units with only a wastegate, and / or without an (Otto) internal combustion engine). The advantageous effects described herein can also be achieved for this application area by means of the flange connection 100 optimized according to the invention.

[0038] The turbine housing flange 110 and the bearing housing flange 120 are to be understood as correspondingly designed components intended to be connected to the respective other component. These components can have correspondingly designed structures and surfaces, which will be described in more detail below. The axial contact area 140 and the axial spacing area 130 are to be understood as areas of the flange connection 100 oriented in the axial direction 22. The axial contact area 140 is the area in which there is axial contact in the axial direction 22 between the turbine housing flange 110 and the bearing housing flange 120. Figures 2 to 5D As shown, in the axial contact area 140, the turbine housing side flange 110 and the support housing side flange 130 can be in axial contact, in particular in direct or straight axial contact. In a design solution (which is not shown in the drawings), an intermediate component can be provided or clamped between the turbine housing side flange 110 and the support housing side flange 120, so that the turbine housing side flange 110 and the support housing side flange 120 are in indirect or indirect axial contact. The intermediate component can be, for example, a heat insulation element, a tensioning element (for example a disc spring) and / or a heat shield. The axial spacing area 130 can be in the radial direction 24 at the outer radius R of the axial contact area. KAThe circumferential radius R of the flange 120 on the support housing side F The bearing housing-side flange 120 and the turbine housing-side flange 110 can each be designed to be annular and extend in the radial direction 24 .

[0039] More precisely, if Figures 2 to 5D As shown, the turbine housing side flange 110 may have a first axial surface 111, and the support housing side flange 120 may have a second axial surface 121. The axial surfaces 111, 121 refer to surfaces oriented in the axial direction 22. The first axial surface 111 and the second axial surface 121 are arranged opposite to each other in the axial direction 22 in the flange connection 100 (especially at corresponding radial positions). More specifically, the axial surfaces 111, 121 are respectively annular surfaces extending in the radial direction 24, which, when viewed in the axial direction 22, are opposite to each other in the flange connection 100, i.e. between the inner periphery and the outer periphery of the flange connection 100 (especially at corresponding radial positions). Figure 2 and Figure 4 In the embodiment shown, the axial surfaces 111, 121 are arranged in the radial direction 24 between the inner circumference (or inner radius) of the turbine housing 20 directly on the flange 110 on the turbine housing side and the circumferential radius R of the flange 120 on the bearing housing side. F In the axial spacing region 130, the first axial surface 111 and the second axial surface 121 are spaced apart in the axial direction. In other words, the axial surfaces 111, 121 are spaced apart from each other in the axial spacing region 130 by an axial gap. Figures 2 to 5D As shown, the axial surfaces 111, 121 can be continuously spaced apart from each other in the axial direction 22 in the axial spacing region 130. In particular, the axial surfaces 111, 121 can be spaced apart from each other at an outer radius R of the axial contact region 140. KA The circumferential radius R of the flange 120 on the support housing side F are continuously spaced apart from each other along the axial direction 22. Figures 2 to 5D As shown, the axial surfaces 111 , 121 contact each other in an axial contact area 140 .

[0040] The turbine housing-side flange 110 and the bearing housing-side flange 120 can be spaced apart from each other continuously in the axial direction 22 in the axial spacing region 130. The axial contact region 140 is arranged directly adjacent to the axial spacing region 130 in the radial direction 24. In other words, the axial contact region 140 is arranged directly radially within the axial spacing region 130 in the radial direction 24 and is directly connected thereto. The axial contact region 140 is spaced apart from each other continuously in the axial direction 24 at an inner radius R of the axial contact region 140. KI With outer radius R KAIn particular, in the axial contact region 140 and viewed in the radial direction 24 , the turbine housing-side flange 110 and the bearing housing-side flange 120 can extend between the inner radius R KI With outer radius R KA There is continuous axial contact between the inner radius R KI This may correspond to an inner radius of the turbine housing 10 adjacent to the bearing housing-side flange 120 or directly on the turbine housing-side flange 110. In the axial contact region 140, forces, in particular clamping forces, may be applied or transmitted between the turbine housing-side flange 110 and the bearing housing-side flange 140. By reducing the axial and radial contact surface (or contact cross section) between the turbine housing-side flange 110 and the bearing housing-side flange 120, the heat transfer into the bearing housing 30 may be reduced.

[0041] like Figures 2 to 5D As shown, the bearing housing-side flange 120 can be formed integrally or in one piece with the bearing housing 30 . The turbine housing-side flange 110 can be formed integrally or in one piece with the turbine housing 20 . The bearing housing 30 and / or the turbine housing 20 can be manufactured as castings. The bearing housing 30 can be made of cast iron, for example. In one embodiment, the bearing housing 30 and / or the turbine housing 20 can be made of cast steel. In one embodiment, the bearing housing 30 can be made of cast iron, and the turbine housing 20 can be made of cast steel. The bearing housing-side flange 120 and the turbine housing-side flange 110 can then be processed accordingly to be coupled or connected via the flange connection 100 . In one embodiment (not shown in the figures), the bearing housing-side flange 120 and / or the turbine housing-side flange 110 can be designed as separate annular (or disk-shaped) components and can be coupled to corresponding components of the bearing housing 30 and the turbine housing 20 .

[0042] like Figure 3A and Figure 4 As shown, the axial contact region 140 has a first radial width R1, which is particularly large in the radial direction 24 at the inner radius R of the axial contact region 140. KI With outer radius R KA The axial spacing region 130 has a second radial width R2, which is measured in the radial direction 24 at the outer radius R of the axial contact region 140. KA The circumferential radius R of the flange 120 on the support housing side F Here, the second radial width R2 can be measured in particular with the radial spacing R D Here, the first radial width R1 and the second radial width R2, in particular the radial distance R D The ratio R1 / R2 can be in the range of 0.20 to 0.70. Figures 2 to 3B In the embodiment of the present invention, the ratio can be in particular in the range of 0.20 to 0.45, more precisely in the range of 0.24 to 0.30. Figures 4 to 5B In the embodiment of the invention, the ratio can be in particular in the range of 0.35 to 0.65, more precisely in the range of 0.40 to 0.60, and in particular in the range of 0.42 to 0.58. In addition to the advantageous effect of the radial displacement of the contact point radially inward, these ratio gaps can also reduce the axial contact cross-section between the bearing-housing-side flange 120 and the turbine-housing-side flange 110, through which axial heat transfer from the turbine housing 20 to the bearing housing 30 can occur. Furthermore, the ratio can improve the transmission of the axial clamping force applied in the axial direction 22 between the bearing-housing-side flange 120 and the turbine-housing-side flange 110, in particular in the axial contact region 140. In particular, during temperature cycles (where various thermal expansions may occur in the flange connection), a gentler or more constant force transmission can be provided in the flange connection 100. Consequently, the ratio can reduce the temperature and / or mechanical loads on the bearing-housing-side flange, reduce crack formation, and increase the service life. As mentioned above, the turbine unit 10 can therefore be subjected in particular to a plurality of temperature cycles during operation. Figure 6 The force diagram in the flange connection 100 during a temperature cycle is shown, in particular the axial clamping force in the axial contact area 140. A temperature cycle can also be referred to as a temperature change cycle. This temperature change cycle can include cyclic heating to the operating temperature and subsequent cooling, for example in the case of thrust operation. The corresponding force curve can be obtained by corresponding tests. Figure 6 In the graph of the temperature cycle, the force as a function of the time t (see abscissa) of the temperature cycle is plotted on the ordinate in percentage [%]. The force can in particular be in the range of kilonewtons [kN] and can be plotted in the range of 0% to 100% relative to the maximum design force. The time t can be in the range of several minutes. The curve B shown in succession shows the force curve (in particular the axial clamping force) during the temperature cycle of a conventional flange connection in which the axial contact area is arranged axially to the outside (i.e. directly adjacent to the circumferential radius of the flange on the support housing side). The dashed curve N shows the force curve according to the invention (e.g. for Figure 2The force curve (in particular the axial clamping force) during the temperature cycle of a flange connection 100 (design solution) in which the axial contact area 140 moves radially inward as described above and the ratio R1 / R2 as described above exists. With the help of curves B and N, it can be seen that the clamping forces initially possessed by the two flange connections in the axial contact area are similar, in particular both are in a force range slightly above 50%. At time t1 of the temperature cycle, the conventional connection (see curve B) has a force peak in its force curve and drops to the force valley of the conventional flange connection from time t2 to time t3 of the temperature cycle. Due to the force peaks and force valleys in the conventional flange connection (see curve B), the conventional flange connection experiences greater force changes, resulting in a higher mechanical load on the flange connection. In contrast, the flange connection 100 according to the present invention (see curve N) can achieve a very mild force curve without force peaks and force valleys, which achieves a smaller mechanical load on the components of the flange connection 100 and thus can reduce the number of cracks formed in the flange 120 on the support shell side and increase the service life. As Figure 6 As shown, the flange connection 100 according to the present invention has a clamping force of approximately 50% at time t1. At time t3, the flange connection 100 according to the present invention has a clamping force of approximately 30%. In contrast, a conventional flange connection has a force peak of approximately 90% at time t1. Conventional flange connections have a force valley of less than 20% at time t3.

[0043] like Figures 2 to 5D As shown, the turbine housing side flange 110 and the support housing side flange 120 are designed and connected to each other in such a way that they form at least one shoulder 160 that provides a radial centering surface match. The turbine housing side flange 110 and the support housing side flange 120 can in particular form a shoulder 160 in which the radial surfaces of the turbine housing side flange 110 and the support housing side flange 120 contact each other. A radial surface is to be understood as a surface oriented in the radial direction 24. A radial surface is in particular a surface that is opposite in the radial direction 24 (in particular at the same axial position). The shoulder 160 can provide radial support, in particular centering of the turbine housing side flange 110 relative to the support housing side flange 120. The shoulder 160 can be at least one shoulder. The turbine housing side flange 110 and the support housing side flange 120 can, for example, be designed and connected to each other in such a way that they provide a first radially outer shoulder 160 and at least one radially inner second shoulder. In the example Figures 4 to 5D In the embodiment shown, the shoulder 160 can be formed between the outer circumference of the bearing housing flange 120 and a lip 180 of the turbine housing flange 110 extending in the axial direction 22 and at least partially circumferentially surrounding the bearing housing flange 120. The lip 180 can also completely circumferentially surround the bearing housing flange 120. Figures 2 to 3B In the embodiment shown, the shoulder 160 can be formed in the flange connection 100 in the radial direction 24 at a circumferential radius R F With inner radius R KI In order to form the shoulder 160, the bearing housing side flange 120 or the turbine housing side flange 110 can have an axial projection 112, 122, which extends at least partially into a notch (or step) or recess of the respective other of the bearing housing side flange 120 and the turbine housing side flange 110, so that an overlap can be provided in the axial direction 22 and a support can be provided in the radial direction 24 (by means of mutually contacting relative radial surfaces). Figures 2 to 3B In the design scheme, the turbine housing side flange 110 has an axial protrusion 112 on its outer circumference and a notch (or step) located radially inward relative to it. The support housing side flange 120 has a radially inward axial protrusion 112 and a notch (or step) located radially outward relative to it. Corresponding notches and protrusions 112, 122 are formed in the circumferential direction. The corresponding protrusions 112, 122 extend at least partially into the corresponding notches and overlap in the axial direction 22. Thereby, the radial surfaces of the protrusions can form corresponding centering surface mating pairs. The above-mentioned design scheme can also be set in the opposite way (that is, the support housing side flange 120 and the turbine housing side flange 110 are interchanged). In Figures 2 to 3B In the design scheme, more than one shoulder 160 can be provided.

[0044] In a design solution, the at least one shoulder 160 can be arranged radially inwardly of the axial spacing region 130. The shoulder 160 can be arranged, for example, in the axial contact region 140. Figures 2 to 3B As shown, the shoulder 160 can be arranged in the axial spacing area 130. In a design solution, the first shoulder 160 and the at least one second shoulder 160 can be provided in the axial spacing area 130 and / or the axial contact area 140. In a design solution, the at least one shoulder 160 can divide the axial spacing area 130 into a first axial spacing area 131 and at least one second axial spacing area 132 (see, for example, FIG. Figure 2 ). The first axial spacing region 131 can be arranged spaced apart or offset from the second axial spacing region 132 in the axial direction 22. The first axial spacing region 131 can be arranged in the radial direction 24 between the shoulder 160 and the axial contact region 140. The second axial spacing region 132 can be arranged in the radial direction 24 between the shoulder 160 and the circumferential radius R of the bearing housing side flange 120. F Between (see for example Figure 2If an intermediate component is provided as described above, it can be spaced apart from the shoulder 160 in the radial direction 24, so that the first axial spacing region 131 can be provided by the axial width of the intermediate component (instead of or in addition to the annular recesses 114, 124). In one embodiment, the axial contact region 140 can include a first axial contact region and at least one second axial contact region, which are offset or spaced apart from each other in the axial direction 22. In this case, the shoulder 160 (or at least one shoulder) can be located in the axial contact region 140, and in particular between the first axial contact region and the at least one second axial contact region.

[0045] like Figures 2 to 5D As shown, the turbine housing-side flange 110 can have at least one radially inner annular projection 113, which extends in the axial direction 22 toward the bearing housing-side flange 120 and forms an axial contact surface with the bearing housing-side flange 120. The axial contact surface can form an axial contact region 140. The axial spacing region 130 (and / or the first axial spacing region 131) can be designed as at least one annular recess 114, 124 in the bearing housing-side flange 120 and / or the turbine housing-side flange 110.

[0046] Reference Figures 2 to 5D The flange connection 100 includes at least one connecting element 150 that connects the turbine-housing-side flange 110 and the bearing-housing-side flange 120 to one another. The connecting element 150 is particularly connected to the turbine-housing-side flange 110 and the bearing-housing-side flange 120 in such a way that it generates a clamping force in an axial contact region 140 between the turbine-housing-side flange 110 and the bearing-housing-side flange 120. Thus, axial forces F1, F2 are applied by the connecting element 150, acting in the direction of the turbine-housing-side flange 110 (or vice versa) as viewed from the bearing-housing-side flange 120. The axial forces F1, F2 can generate an axial clamping force in the axial contact region 140 (or can be transferred thereto). In other words, the axial forces F1, F2 are directly transferred as clamping forces in the axial contact region 140. The axial forces F1, F2 can be applied planarly to the bearing housing flange 120 and / or the turbine housing flange 110. The connecting element 150 can be arranged in the radial direction 24 in the axial spacing region 130, i.e., radially outside the axial contact region 140. In other words, the connecting element 150 can be arranged in the radial direction 24 such that the connecting element generates the axial forces F1, F2 in the axial spacing region 130 between the turbine housing flange 110 and the bearing housing flange 120. The radial positioning R of the axial forces F1, F2 applied by the connecting element VHere, it is located radially outside the axial contact region 140 , in particular at the outer radius R KA If the shoulder 160 in the flange connection 100 is arranged in the axially spaced region 130 , the radial positioning R of the axial forces F1 , F2 exerted by the connecting element 150 V It can be located radially outside the shoulder 160 (or radially inside, for example, in the case where the axial spacing area 130 then has a first axial spacing area 131 and at least one second spacing area 132). If a first shoulder 160 and at least one second shoulder 160 located radially inside thereof are provided, the radial positioning R V It may be located radially outside the first shoulder or between these shoulders.

[0047] As in Figures 2 to 3B As shown in the design of , the connecting element 150 can be a V-shaped clamp. In this case, the connecting element 150 can be arranged circumferentially around the flange 110 on the turbine housing side and the flange 120 on the support housing side. In this case, the connecting element 150 circumferentially engages the flange 110 on the turbine housing side and the flange 120 on the support housing side, so that the tensioning force of the connecting element 150 generates the above-mentioned axial forces F1, F2 in the axial spacing area 130 radially inward and thus generates an axial clamping force in the axial contact section 140. Figures 4 to 5D In a design, a connecting element 150 is provided in the form of at least one axial threaded connection. The threaded connection in the axial direction 22 generates the aforementioned axial force F1 in the axial spacing region 130 and, therefore, an axial clamping force in the axial contact section 140. The threaded connection can, in particular, comprise a threaded element and a stop washer. The threaded element is axially connected to a lip 180 of the turbine housing flange 110 extending in the axial direction 22. The stop washer is clamped between the lip 180 and the threaded element and, in a radially inner section, transmits the axial force F1 to the bearing housing flange 110, thereby generating an axial clamping force in the axial contact section 140. The at least one threaded connection can, in particular, comprise a plurality of threaded connections distributed in the circumferential direction.

[0048] like Figures 2 to 5DAs shown, the bearing housing 30 may have at least one annular cooling channel 31, which may be arranged radially inward relative to the bearing housing-side flange 120 and close to (or adjacent to) the side of the bearing housing 30 facing the turbine housing 20. The annular cooling channel 31 is particularly formed in the bearing housing 30. This annular cooling channel may be arranged in the axial direction 22 between the oil inlet and the side of the bearing housing facing the turbine housing 20. The bearing housing 30 having at least one cooling channel can provide improved heat removal from the bearing housing-side flange 120. Combined with the radially inward shifting of the axial contact area 140, the thermal load on the bearing housing-side flange 120 can be reduced, thereby reducing crack formation. This can thereby increase the service life of the bearing housing-side flange 120.

[0049] like Figures 2 to 5D As shown, the flange connection 100 can have at least one sealing element 170, which is clamped in the axial direction 22 between the turbine housing side flange 110 and the support housing side flange 120. The at least one sealing element 170 can be clamped in particular in the axial spacing area 130. The sealing element 170 is in particular annular and is clamped circumferentially between the turbine housing side flange 110 and the support housing side flange 120. The at least one sealing element 170 can be arranged radially outside and / or radially inside the at least one shoulder 160. The at least one sealing element 170 can be a V-ring. In the design solution, the at least one sealing element 170 can also be arranged (in addition or alternatively) in a circumferential groove in the axial contact area 140. As Figure 3A and Figure 3B As shown, the at least one sealing element 170 can be clamped in the first axially spaced region 131 and / or the second axially spaced region 132. The sealing element 170 can include a first sealing element 170a clamped in the first axially spaced region 131 and at least one second sealing element 170b clamped in the second axially spaced region 132.

[0050] The bearing housing side flange 120 and / or the turbine housing side flange 110 can have at least one annular recess 114, 124, in which the at least one sealing element 170 is arranged. The at least one annular recess 114, 124 can in particular be a circumferential groove. Figure 3A and Figures 4 to 5DThe turbine housing flange 110 and / or the bearing housing flange 120 may comprise at least one annular recess 114, 214 in the axial spacing section 130, in which the at least one sealing element 170 is arranged. The at least one annular recess 114, 214 is arranged in the axial direction 22 between the turbine housing flange 110 and the bearing housing flange 120, in particular in the corresponding axial surfaces 111, 121. The radial positioning of the at least one annular recess 114, 214 and the sealing element 170 may substantially correspond to the radial positioning R of the applied axial forces F1, F2. V Correspondingly. This can provide a better sealing effect. Figure 3A 、 Figure 5A 、 Figure 5C and Figure 5D In the design scheme, the turbine housing side flange 110 has an annular recess 114, which is substantially located at the radial position R of the applied axial forces F1 and F2 in the radial direction. V Sealing elements 170, 170b are arranged in the annular recess 114. Figure 3B 、 Figure 5B and Figure 5C As shown, additionally or alternatively, the annular recess 124 can also be correspondingly arranged in the bearing housing side flange 120. Figure 3B Alternatively or additionally, an annular recess 114 can be provided radially inwardly of a shoulder 160 in the turbine housing-side flange 110 and / or the bearing housing-side flange 120. A sealing element 170 can be arranged in this annular recess 114. The annular recess 114 can in particular be provided in the immediate vicinity of the axial contact region 140. This allows a defined clamping force to be applied to the sealing element 170. Figure 5A and Figure 5D As shown, at least one radial surface 125 of the centering surface pair of the at least one shoulder 160 can be chamfered at least partially in the axial direction 22. In particular, a chamfer can be provided between the radial surface of the shoulder 160 and the axial contact region 140 or the axial spacing region 130. This can reduce the radial contact cross-section between the turbine-housing-side flange 110 and the bearing-housing-side flange 120 (in particular, between the radial surfaces), and thus reduce the heat transfer from the turbine housing 20 to the bearing housing 30. In combination with the reduction of the axial contact cross-section by the described axial contact region 140, the heat transfer can be further reduced.

[0051] Figure 7 Shown with Figure 1Schematic diagram of an engine system 1 with a supercharging device 2 having a turbine unit 10 according to the invention. 32. The engine system 2 comprises a supercharging device 1 having a turbine unit 10, and an internal combustion engine 3. The internal combustion engine 3 may have a plurality of cylinders 4. The turbine unit is arranged downstream of the internal combustion engine 3. The turbine housing inlet 21 of the turbine housing 20 is in fluid connection with the internal combustion engine 3 (more specifically with the plurality of cylinders 4), in particular via a first connecting line 8. As described above, the turbine unit 10 may therefore comprise a guide device 50 (which in particular has a plurality of adjustable guide vanes) Figure 7 (not shown in the figure). The compressor 60 is arranged upstream of the internal combustion engine 3. The compressor housing outlet 63 of the compressor housing 61 is fluidically connected to the internal combustion engine 3, in particular via the second connecting line 7. The compressor housing inlet of the compressor 60 is fluidically connected to the atmospheric inlet 6 upstream of the compressor 60. The turbine housing outlet 22 is fluidically connected to the outlet 9 downstream of the turbine unit 10. The aforementioned advantageous effects of the flange connection 100 can also be provided, in particular, for the combination of the internal combustion engine 3 and the turbine unit 10, as well as the guide device 50 in the form of a variable-section turbine (i.e., having a plurality of adjustable guide vanes). In addition, the guide device 50 can also include fixed guide vanes, as described above.

[0052] Although the present invention has been described above and defined in the appended claims, it will be appreciated that the invention can alternatively be defined in terms of the following embodiments:

[0053] 1. A turbine unit (10) for a supercharging device (1), comprising:

[0054] Support housing (30), and

[0055] A turbine housing (20) connected to the support housing (30) via a flange connection (100), wherein the flange connection (100) comprises:

[0056] a turbine housing side flange (110), and

[0057] Supporting housing side flange (120),

[0058] wherein the turbine housing-side flange (110) and the bearing housing-side flange (120) are designed and connected to one another in such a way that they form an axial spacing region (130) and an axial contact region (140) of the flange connection (100),

[0059] wherein the axial contact region (140) is arranged radially inwardly relative to the axial spacing region (130),

[0060] It is characterized in that the outer radius of the axial contact area (R KA ) and the circumferential radius (R F ) between the radial spacing (R D ) is at least 3.50 mm.

[0061] 2. The turbine unit (10) according to embodiment 1, wherein the turbine housing-side flange (110) and the bearing housing-side flange (120) are in direct axial contact with each other in the axial contact area (140).

[0062] 3. The turbine unit (10) according to embodiment 1 or embodiment 2, wherein the turbine housing side flange (110) and the support housing side flange (120) are continuously spaced apart from each other in the axial direction (22) in the axial spacing region (130).

[0063] 4. The turbine unit (10) according to any one of the preceding embodiments, wherein the axial spacing region (130) is located at an outer radius (R) of the axial contact region in the radial direction (24). KA ) and the circumferential radius (R F ) extends between.

[0064] 5. The turbine unit (10) according to any one of the preceding embodiments, wherein the axial contact region (140) is arranged directly adjacent to the axial spacing region (130) in the radial direction (24).

[0065] 6. The turbine unit (10) according to any one of the preceding embodiments, wherein the axial contact area (140) is located at an inner radius (R KI ) and the outer radius (R KA ) extends between.

[0066] 7. The turbine unit (10) according to embodiment 6, wherein the inner radius (R KI ) corresponds to the inner radius of the turbine housing (10) close to the support housing side flange (110).

[0067] 8. A turbine unit (10) according to any one of the preceding embodiments, wherein the flange connection (100) comprises at least one connecting element (150), which is connected to the turbine housing side flange (110) and the support housing side flange (120) in such a way that the connecting element generates an axial clamping force in the axial contact area (140) between the turbine housing side flange (110) and the support housing side flange (120).

[0068] 9. A turbine unit (10) according to embodiment 8, wherein the connecting element (150) is arranged in the radial direction (24) such that the connecting element generates an axial force (F1, F2) in the axial spacing area (130) between the turbine housing side flange (110) and the support housing side flange (120), in particular wherein the clamping force is generated by the axial force (F1, F2).

[0069] 10. The turbine unit (10) according to embodiment 8 or embodiment 9, wherein the radial positioning (R V ) is located radially outside the axial contact area (140).

[0070] 11. The turbine unit (10) according to any one of the preceding embodiments 8 to 10, wherein the connection element (150) is a V-clamp or a threaded connection.

[0071] 12. A turbine unit (10) according to any one of the preceding embodiments, wherein the axial contact area (140) has a first radial width (R1), and wherein the axial spacing area (130) has a second radial width (R2), wherein the ratio of the first radial width (R1) to the second radial width (R2) is in the range of 0.20 to 0.70.

[0072] 13. The turbine unit (10) according to embodiment 12, wherein the ratio is in the range of 0.20 to 0.45, in particular wherein the ratio is in the range of 0.24 to 0.30.

[0073] 14. A turbine unit (10) according to any one of the preceding embodiments, wherein the turbine housing side flange (110) and the support housing side flange (120) are designed and connected to each other in such a manner that they constitute at least one shoulder (160) providing a radial centering surface fit pair.

[0074] 15. A turbine unit (10) according to embodiment 14, wherein the shoulder (160) is formed between the outer peripheral surface of the support housing side flange (120) and a ridge (180) of the turbine housing side flange (110) extending in the axial direction (22), and the ridge surrounds the support housing side flange (120).

[0075] 16. The turbine unit (10) according to embodiment 14, wherein the shoulder (160) is arranged in the axially spaced region (130) in the radial direction (22).

[0076] 17. The turbine unit (10) according to embodiment 14 or embodiment 16, wherein the shoulder (160) divides the axial spacing region (130) into a first axial spacing region (131) and at least one second axial spacing region (132), wherein the first axial spacing region (131) is arranged in the radial direction (24) between the shoulder (160) and the axial contact region (140), and wherein the second axial spacing region (132) is arranged in the radial direction (24) at a circumferential radius (R) of the shoulder (160) and the bearing housing side flange (120). F )between.

[0077] 18. A turbine unit (10) according to any one of the preceding embodiments, wherein the turbine housing side flange (110) has an annular protrusion (113), which extends in an axial direction (22) toward the support housing side flange (120) and forms an axial contact surface in contact with the support housing side flange (120).

[0078] 19. The turbine unit (10) according to embodiment 17 or embodiment 18, wherein the first axial spacing region (131) is designed as an annular recess in the bearing housing side flange (120) and / or the turbine housing side flange (110).

[0079] 20. A turbine unit (10) according to any one of the preceding embodiments, wherein the flange connection (100) has at least one sealing element (170) which is clamped between the turbine housing side flange (110) and the support housing side flange (120) in the axial spacing region (130).

[0080] 21. The turbine unit (10) according to embodiment 20 as appended to embodiment 17, wherein the sealing element (170) is clamped in the first axial spacing region (131).

[0081] 22. The turbine unit (10) according to embodiment 20 or embodiment 21 as appended to embodiment 17, wherein the sealing element (170) is clamped in the second axially spaced region (132).

[0082] 23. A turbine unit (10) according to any one of embodiments 20 to 22, wherein the support housing side flange (120) and / or the turbine housing side flange (110) has at least one annular recess (114, 124), and the sealing element (170) is arranged in the at least one annular recess.

[0083] 24. A turbine unit (10) according to any one of the preceding embodiments, wherein the support housing side flange (120) is implemented integrally with the support housing (30), and wherein the turbine housing side flange (110) is implemented integrally with the turbine housing (20).

[0084] 25. The turbine unit (10) according to any one of the preceding embodiments, wherein the bearing housing-side flange (120) and the turbine housing-side flange (110) are each designed to be annular and extend in a radial direction (24).

[0085] 26. A turbine unit (10) according to any one of the preceding embodiments, wherein the support housing (30) has at least one annular cooling channel (31), which is arranged radially inward relative to the support housing side flange (120) and close to the side of the support housing (30) facing the turbine housing (20).

[0086] 27. A turbine unit (10) according to any one of the preceding embodiments, comprising a turbine impeller (40) arranged in a receiving space (23) of the turbine housing (20) between a turbine housing inlet (21) and a turbine housing outlet (22).

[0087] 28. The turbine unit (10) according to embodiment 27 comprises a guide device (50) which is arranged radially outside the turbine impeller (40) in the receiving space (23) and circumferentially surrounds the turbine impeller (40).

[0088] 29. The turbine unit (10) according to embodiment 28, wherein the guide device (50) is arranged spaced apart from the turbine housing (20) in a radial direction (24).

[0089] 30. A supercharging device (1) for an internal combustion engine or a fuel cell, the supercharging device comprising:

[0090] A turbine unit (10) according to any one of the preceding embodiments, and a compressor (60) having a compressor housing (61),

[0091] The compressor housing (61) is coupled to the bearing housing (30) on a side of the bearing housing (30) opposite to the turbine housing (20).

[0092] 31. The supercharging device (1) according to embodiment 30, comprising a turbine wheel (40) arranged in the receiving space (23) of the turbine housing (20), and

[0093] a shaft (70) rotatably supported in the bearing housing (30), wherein the compressor (60) has a compressor impeller (62), and

[0094] The turbine wheel (40) and the compressor wheel (62) are non-rotatably coupled to the shaft (70) at opposite ends of the shaft (70).

[0095] 32. An engine system (2), comprising:

[0096] According to the supercharging device (1) of embodiment 30 or embodiment 31, and the internal combustion engine (3) having a plurality of cylinders (4),

[0097] wherein the turbine unit (10) is arranged downstream of the internal combustion engine (3), and a turbine housing inlet (21) of the turbine housing (20) is in fluid connection with the plurality of cylinders (4),

[0098] In particular, the turbine unit (10) comprises a guide device (50) having a plurality of adjustable guide blades.

[0099] 33. An engine system (2) according to embodiment 32, wherein the turbine unit (10) includes a turbine impeller (40) and the guide device (50), wherein the turbine impeller (40) is arranged in the receiving space (23) of the turbine housing (20), wherein the guide device (50) is arranged radially outside the turbine impeller (40) in the turbine housing (20) and circumferentially surrounds the turbine impeller (40).

[0100] 34. An engine system (2) according to embodiment 32 or embodiment 33, wherein the compressor (60) is arranged upstream of the internal combustion engine (3), and the compressor housing outlet (63) of the compressor housing (61) is in fluid connection with the internal combustion engine (3).

Claims

1. A turbine unit for a supercharging device (1), comprising: Support housing (30), and A turbine housing (20) is connected to the support housing (30) via a flange connection (100), wherein the flange connection (100) comprises: Turbine housing side flange (110) and Supporting housing side flange (120), The turbine housing-side flange (110) and the bearing housing-side flange (120) are designed and connected to one another in such a way that they form an axial spacing region (130) and an axial contact region (140) of the flange connection (100). wherein the axial contact region (140) is arranged radially inward relative to the axial spacing region (130), It is characterized in that the outer radius of the axial contact area (R KA ) and the circumferential radius (R F ) between the radial spacing (R D ) is at least 3.50 mm.

2. The turbine unit according to claim 1, wherein The turbine housing-side flange (110) and the bearing housing-side flange (120) are in direct axial contact with one another in the axial contact region (140).

3. The turbine unit according to claim 1, wherein: The turbine housing side flange (110) and the bearing housing side flange (120) are continuously spaced apart from each other in the axial direction (22) in the axial spacing region (130), and in particular the axial spacing region (130) is spaced apart in the radial direction (24) at an outer radius (R KA ) and the circumferential radius (R F ) extends between.

4. The turbine unit according to any one of claims 1 to 3, wherein: The axial contact area (140) is located at an inner radius (R) of the axial contact area (140) along the radial direction (24). KI ) and the outer radius (R KA ) and in particular the inner radius (R KI ) corresponds to the inner radius of the turbine housing (10) close to the support housing side flange (110).

5. The turbine unit according to any one of claims 1 to 3, wherein The flange connection (100) comprises at least one connecting element (150) which is coupled to the turbine housing-side flange (110) and the bearing housing-side flange (120) in such a way that the connecting element generates an axial clamping force in the axial contact area (140) between the turbine housing-side flange (110) and the bearing housing-side flange (120).

6. The turbine unit according to claim 5, wherein The connecting element (150) is arranged in the radial direction (24) such that it generates an axial force (F1, F2) between the turbine housing-side flange (110) and the bearing housing-side flange (120) in the axial spacing region (130), wherein the clamping force is generated by the axial force (F1, F2).

7. The turbine unit according to any one of claims 1 to 3, wherein: The axial contact region (140) has a first radial width (R1) and the axial spacing region (130) has a second radial width (R2), wherein a ratio of the first radial width (R1) to the second radial width (R2) is in the range of 0.20 to 0.

70.

8. The turbine unit according to claim 7, wherein The ratio is in the range of 0.20 to 0.45, in particular wherein the ratio is in the range of 0.24 to 0.

30.

9. The turbine unit according to any one of claims 1 to 3, wherein: The turbine housing-side flange (110) and the bearing housing-side flange (120) are designed and connected to one another in such a way that they form at least one shoulder (160) that provides a radial centering surface fit.

10. The turbine unit according to claim 9, wherein The shoulder (160) is arranged in the axial spacing area (130) in the radial direction (22), wherein the shoulder (160) divides the axial spacing area (130) into a first axial spacing area (131) and at least one second axial spacing area (132), wherein the first axial spacing area (131) is arranged between the shoulder (160) and the axial contact area (140) in the radial direction (24), and the second axial spacing area (132) is arranged in the radial direction (24) at a circumferential radius (R) between the shoulder (160) and the bearing housing side flange (120). F )between.

11. The turbine unit according to any one of claims 1 to 3, wherein: The flange connection (100) has at least one sealing element (170) which is clamped in the axial spacing region (130) between the turbine housing-side flange (110) and the bearing housing-side flange (120), and In particular, the bearing housing-side flange (120) and / or the turbine housing-side flange (110) have at least one annular recess (114, 124), in which the sealing element (170) is arranged.

12. The turbine unit according to claim 10, wherein The flange connection (100) has at least one sealing element (170) which is clamped in the axial spacing region (130) between the turbine housing-side flange (110) and the bearing housing-side flange (120), and the sealing element (170, 170a) is clamped in the first axial spacing region (131) and / or the sealing element (170, 170b) is clamped in the second axial spacing region (132).

13. The turbine unit according to any one of claims 1 to 3, wherein: The bearing housing-side flange (120) is implemented in one piece with the bearing housing (30), and the turbine housing-side flange (110) is implemented in one piece with the turbine housing (20).

14. The turbine unit according to any one of claims 1 to 3, wherein The bearing housing (30) has at least one annular cooling channel (31) which is arranged radially inwardly relative to the bearing housing-side flange (120) and close to the side of the bearing housing (30) facing the turbine housing (20).

15. A supercharging device for an internal combustion engine or a fuel cell, the supercharging device comprising: A turbine unit (10) according to any one of claims 1 to 14, and a compressor (60) having a compressor housing (61), The compressor housing (61) is connected to the bearing housing (30) on a side of the bearing housing (30) opposite to the turbine housing (20).

16. An engine system, comprising: The boosting device (1) according to claim 15, and Internal combustion engine (3), wherein the turbine unit (10) is arranged downstream of the internal combustion engine (3), and the turbine housing inlet (21) of the turbine housing (20) is fluidically connected to the internal combustion engine (3), and In particular, the turbine unit (10) comprises a guide device (50) having a plurality of adjustable guide blades.

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