GUIDE DEVICE FOR A TURBINE

Abstract

The present invention relates to a guide device (100) for a turbine (10), comprising a blade bearing ring (110), a cover plate (150) arranged parallel to and axially spaced (22) from the blade bearing ring (110) by spacer elements (160), and a plurality of adjustable guide vanes (120) rotatably and adjustably mounted in the blade bearing ring (110). The adjustable guide vanes (120) are arranged between the cover plate (150) and the blade bearing ring (110). The adjustable guide vanes (120) are adjustable between a first guide vane position, in which the guide vanes are minimally open, and a second guide vane position (122), in which the guide vanes are maximally open.The respective guide vane position is linked to a corresponding mass flow rate through the guide device (100) during operation, in particular where the mass flow rate is 100% in the second guide vane position. The blade bearing ring (110) and / or the cover plate (150) has a chamfer (200, 200a, 200b) which extends on a side (111, 151) of the blade bearing ring (110) and / or the cover plate (150) facing the adjustable guide vanes from an inner circumference (112, 152) of the blade bearing ring (110) and / or the cover plate (152) in a radial direction (24) to an outer chamfer radius (RA). The adjustable guide vanes (120) each have a guide vane trailing edge (123).The guide vane trailing edge (123) lies in the area of ​​the chamfer (200, 200a, 200b) in the radial direction (24) for guide vane positions corresponding to a mass flow range from a first mass flow value to a second mass flow value, where the first mass flow value is a maximum of 35%.

Description

Technical field

[0001] The present invention relates to a guide device, in particular a variable turbine geometry, a turbine for a charging device with such a guide device, and a charging device for an internal combustion engine or a fuel cell with such a turbine. background

[0002] More and more newer generation vehicles are being equipped with charging systems to meet performance targets and legal requirements. When developing charging systems, it is essential to optimize both the individual components and the system as a whole in terms of reliability and efficiency.

[0003] Known supercharging devices typically include at least one compressor with a compressor wheel connected to a drive unit via a common shaft. The compressor compresses the fresh air drawn in for an internal combustion engine or a 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, leads to an increase in the power output of the internal combustion engine or the fuel cell. Supercharging devices can be equipped with different drive units. In the prior art, electric superchargers, 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, are known.Unlike an axial turbine (as used, for example, in aircraft engines), where the exhaust flow is essentially exclusively axial, in a radial turbine the exhaust flow is directed onto the turbine wheel from a spiral turbine inlet, essentially radially, and in the case of a mixed-flow radial turbine, semi-radially, i.e., with at least a small axial component. Besides the electric supercharger and the turbocharger, combinations of both systems are described in the prior art, which are also referred to as e-turbos.

[0004] To further increase turbine efficiency and adapt it to different operating points, modern turbocharging systems are equipped with a power control device that allows the power output of the turbocharger to be adjusted or changed. Well-known power control devices include guide vanes such as variable turbine geometry (VTG) or a wastegate (WG). A guide vane, particularly variable turbine geometry, is an adjustable guide apparatus for modifying the flow to a turbine wheel. By changing the flow (e.g., the flow cross-section and the angle of attack), the flow velocity of the exhaust gas supplied to the turbine wheel can be altered, resulting in a corresponding change in the turbocharger's power output. Such systems are also referred to as variable guide vanes, VTG, guide grids, or VTG guide vanes.

[0005] Common guide vane systems, such as variable turbine geometry (VTGs), often feature a blade bearing ring with a multitude of adjustable guide vanes mounted in this ring in the form of a ring. Each guide vane can be adjusted from a substantially tangential position relative to the ring to an approximately radial position or a more radial position. The adjustable guide vanes are usually coupled to an adjusting ring, which is arranged coaxially with the blade bearing ring, via adjusting levers. By moving the adjusting ring, for example, by rotating it circumferentially, the guide vanes can be adjusted, thus altering the flow to the turbine wheel. This circumferential rotation of the adjusting ring is provided by an actuating device. In particular, the actuating device is designed to generate control movements via the adjusting ring, which are then transmitted to the guide vane system.The adjusting device typically includes an actuator that is coupled to the adjusting ring via an adjusting shaft arrangement. For the mechanical coupling of the adjusting device to the adjusting ring, an engagement of an internal lever with an adjusting pin of the adjusting ring is often provided.

[0006] In known guide vane systems, a shroud is often provided, which is arranged coaxially to the blade bearing ring and, together with the blade bearing ring, defines a flow channel in which the guide vanes are arranged. The flow channel width (i.e., an axial distance between the blade bearing ring and the shroud) is determined by spacers. The axial width of the guide vanes is less than the flow channel width, allowing the guide vanes to be adjustable within the flow channel. In other words, an axial gap is provided between the guide vanes and the blade bearing ring or the shroud. To ensure high efficiency of the guide vane system, it is important to keep the axial gap as small as possible.On the other hand, operating the guide vane system at high temperatures can lead to thermal expansion of the components, particularly the blade bearing ring and / or the shroud. If the axial gap is too small for certain guide vane opening positions, this can cause the blades to jam, resulting in high adjustment forces. This, in turn, can lead to increased wear of the guide vane system components (e.g., at the interface between the adjustment lever and the adjustment ring). Furthermore, in known guide vane systems, sudden axial channel widenings may occur in the flow channel leading to the turbine wheel for certain guide vane positions, which can impair the flow of fluid (especially exhaust gas) to the turbine wheel. The flow channel, particularly the blade bearing ring and / or the shroud, may also have insufficient radial extension (i.e.,The flow channel is too small in the radial direction, causing sections of the guide vanes to leave the flow channel prematurely during operation at smaller guide vane opening positions, and also resulting in a sudden widening of the flow channel. The above-mentioned issues can lead to reduced efficiency of the guide vane system during operation.

[0007] The object of the present invention is to provide an improved guidance device, in particular one that provides high efficiency over a wide operating range. Summary of the invention

[0008] The present invention relates to a guide device for a turbine, in particular a variable turbine geometry, according to claim 1. The invention further relates to a turbine for a charging device according to claim 11, comprising such a guide device. The invention also relates to a charging device for an internal combustion engine or a fuel cell according to claim 15, comprising such a turbine. The dependent claims describe advantageous embodiments of the guide device and the turbine.

[0009] According to a first aspect of the present invention, a guide vane assembly for a turbine comprises a blade bearing ring and a shroud, wherein the shroud is arranged parallel or coaxially and axially spaced from the blade bearing ring by spacer elements. The guide vane assembly also comprises a plurality of adjustable guide vanes, each rotatably and adjustably mounted in the blade bearing ring, the adjustable guide vanes being arranged between the shroud and the blade bearing ring. The adjustable guide vanes are adjustable between a first guide vane position, in which the guide vanes are minimally open, and a second guide vane position, in which the guide vanes are maximally open. During operation of the guide vane assembly, the respective guide vane position is linked to a corresponding mass flow rate through the assembly.In particular, the mass flow rate can be 100% in the second guide vane position. The blade bearing ring and / or the cover plate have a chamfer that extends radially from an inner circumference of the blade bearing ring and / or the cover plate to an outer chamfer radius on a side of the blade bearing ring and / or the cover plate facing the adjustable guide vanes. The adjustable guide vanes each have a trailing edge. For guide vane positions corresponding to a mass flow rate range from a first mass flow rate value to a second mass flow rate value, the trailing edge lies radially within the chamfer. Preferably, the first mass flow rate value is a maximum of 35%.

[0010] In other words, this means that the chamfer extends radially such that, from a mass flow rate of 35% of the maximum mass flow rate through the guide vane, the trailing edge of the guide vane is located radially within the chamfered area, or moves into this area from this mass flow rate. In guide vane positions corresponding to the mass flow rate range through the guide vane 100, the (especially the complete) guide vane can be located radially within the flow channel, i.e., in the area where the shroud and the blade bearing ring are axially opposed. Consequently, in guide vane positions corresponding to the described mass flow rate range, the trailing edge of the guide vane can lie radially within the chamfer(s) and within the flow channel from the first mass flow rate value to the second mass flow rate value.To achieve these corresponding guide vane positions, the guide vanes are rotated around their respective axis of rotation, thereby changing the radial position of the guide vane's trailing edge. The operation of the guide vane system can be described using a standard combustion chamber measurement for guide vanes, particularly variable turbine geometry (VTGs), where the measuring range is defined in equal flow parameter steps for different guide vane positions, depending on the mass flow rate or mass throughput through the guide vane system. By chamfering the blade bearing ring and / or the cover plate in the area for specific "open" guide vane positions, the efficiency of the guide vane system can be increased, especially for a specific range of "open" guide vane positions.The fact that the trailing edge of the adjustable guide vanes is located in the radial direction in the area of ​​the chamfer for guide vane positions corresponding to the mass flow range necessitates a specific radial arrangement and extent of the chamfer, as well as the cover plate and / or the blade bearing ring with respect to the guide vanes and thus the corresponding guide vane positions.

[0011] Furthermore, the guide device according to the invention can provide a continuous flow profile and achieve improved flow to the turbine wheel. Sudden widenings or changes in the flow channel width can also be prevented, as the chamfer(s) provide an optimized transition, for example, to the turbine housing and / or the turbine wheel. Additionally, enthalpy losses when using the guide device in a turbine can be compensated. When used with an internal combustion engine, improved fuel consumption can be achieved. Furthermore, the chamfer can reduce or prevent jamming of the guide vanes at high temperatures (and corresponding thermal expansion of the components).

[0012] In various configurations, the first mass flow rate value can be a maximum of 30%, in particular a maximum of 20%, specifically 10%. In configurations that can be combined arbitrarily with the described first mass flow rates, the second mass flow rate value can be at least 55%, in particular at least 65%, specifically 70%. The described first and second mass flow rates result in the corresponding mass flow rate ranges, which are linked to the respective guide vane positions and for which at least a section of the guide vane, in particular the trailing edge of the guide vane, lies radially in the area of ​​the chamfer. A larger mass flow rate range consequently requires a larger radial arrangement and extent of the chamfer, as well as of the shroud, the blade bearing ring, and / or the flow channel formed by these components with respect to the guide vanes or guide vane positions.The trailing edge of the guide vane can be located in the radial direction in the area of ​​the chamfer (and in particular in the area of ​​the chamfer and in the flow channel) according to the following preferred mass flow ranges for guide vane positions: • The first mass throughput value can be 35% and the second mass throughput value can be 55%, resulting in a mass throughput range of 35% to 55%; • The first mass throughput value can be 30% and the second mass throughput value can be 65%, resulting in a mass throughput range of 30% to 65%; • The first mass throughput value can be 20% and the second mass throughput value can be 70%, resulting in a mass throughput range of 20% to 70%; or • The first mass throughput value can be 10% and the second mass throughput value can be 70%, resulting in a mass throughput range of 10% to 70%.

[0013] However, other mass throughput ranges can also be formed using the first and second mass throughput values ​​mentioned above.

[0014] A trailing edge radius is defined between the axial direction and the trailing edge of the guide vane. This trailing edge radius decreases as the guide vanes open (and thus as the guide vane position becomes increasingly "open"). Depending on the mass flow rate range, the trailing edge radius can be equal to or smaller than the outer radius of the chamfer. Depending on the mass flow rate range, the trailing edge radius can also be equal to or larger than the inner circumferential radius of the blade bearing ring and / or the shroud. In other words, starting from a guide vane position corresponding to the first mass flow rate value, the trailing edge radius can be equal to or smaller than the outer radius of the chamfer. Consequently, the chamfer extends radially such that the trailing edge of the guide vane is located within the chamfer area, at least from the first mass flow rate value onward.Up to a guide vane position corresponding to the second mass flow rate value, the trailing edge radius can be equal to or greater than the inner circumferential radius of the blade bearing ring and / or the shroud. In other words, the inner circumferential radius of the blade bearing ring and / or the shroud is selected, or the guide vanes are arranged in the guide assembly, such that the guide vanes are no longer completely outside the flow channel (i.e., in the area where the blade bearing ring and the shroud are axially opposed) in the radial direction only at values ​​higher than the second mass flow rate value. At least one section, particularly the guide vane trailing edge, is arranged radially inside the corresponding (larger) inner circumferential radius for these guide vane positions. This radial extension of the blade bearing ring and / or the shroud can reduce or prevent performance deficiencies.

[0015] The blade bearing ring and the shroud define a flow channel in which the adjustable guide vanes are arranged. The flow channel can have a flow channel width measured axially between the blade bearing ring and the shroud. The flow channel width can be constant between the outer circumference of the blade bearing ring and / or the shroud and the outer radius of the chamfer. The flow channel width can increase between the outer radius of the chamfer and the inner circumference of the blade bearing ring and / or the shroud. In preferred embodiments, the flow channel width can increase constantly in this region. The axial width of the guide vane(s) is less than the flow channel width.

[0016] The adjustable guide vanes each have a guide vane axis of rotation. The outer radius of the chamfer can be smaller than the radius of the axis of rotation, which is measured between the axial direction and the guide vane axis of rotation. In some configurations, the chamfer radius can be a maximum of 10% smaller than the radius of the axis of rotation.

[0017] The guide vanes are mounted in the blade bearing ring with uniform circumferential bearing pressure. Adjacent guide vanes can be spaced apart from each other in the first guide vane position. In other words, adjacent guide vanes do not contact each other in the first guide vane position. Even in the first guide vane position, a minimum mass throughput of > 0% can therefore be provided by the guide system.

[0018] In preferred embodiments, the cover plate and the blade bearing ring can have the chamfer. In other embodiments, only the cover plate or only the blade bearing ring can have the chamfer. That is, in this case, the other part of the cover plate and the blade bearing ring does not have the chamfer. The side of the blade bearing ring or the cover plate facing the chamfer that does not have the chamfer can extend (particularly continuously) in the radial direction or (particularly continuously) perpendicular to the axial direction.

[0019] In certain embodiments, the cover plate can have an outer radius, wherein the ratio of the chamfer's outer radius to the outer radius is between 0.60 and 0.85, particularly between 0.65 and 0.80. In certain embodiments, the inner circumferential radius of the blade bearing ring can be smaller than the inner circumferential radius of the cover plate.

[0020] In certain embodiments, the cover plate can have an axial, disc-shaped extension on a side facing away from the adjustable guide vanes, which is arranged in a radially outer region of the cover plate. Consequently, the cover plate has a recess on the opposite side in a radially inner region. In particular, the axial extension forms an axial surface that serves as an axial bearing surface and for the axial transmission of forces when the guide vanes are mounted in a turbine housing. Specifically, the disc-shaped extension can be arranged radially in the region of the spacer elements. This arrangement allows the forces transmitted to the cover plate by the spacer elements to be directly introduced axially into the turbine housing via the extension. This improves the surface pressure.

[0021] In various embodiments, the chamfer between the inner circumference of the blade bearing ring and / or the cover plate can be flat (or linear in cross-section) and / or curved in the radial direction up to the outer radius of the chamfer. A chamfer angle can be measured between the facing side (or the section extending radially or perpendicular to the axial direction) and the chamfer. In particular, the chamfer can be flat in this embodiment. In some embodiments, the chamfer angle can be from 0.5° to 5.0°. In some embodiments, both the blade bearing ring and the cover plate can have the chamfer. A first chamfer angle of the cover plate chamfer can be greater than a second chamfer angle of the blade bearing ring chamfer. In some embodiments, the chamfer angle can be from 1° to 4°, in particular from 2° to 3°.

[0022] In embodiments where the blade bearing ring and the cover plate have a chamfer, the chamfer of the cover plate can have a first slope and the chamfer of the blade bearing ring can have a second slope. The first slope can be greater than the second slope, in particular where the ratio of the first slope to the second slope at radial positions (i.e., in the radial area of ​​the chamfers) for guide vane positions corresponding to the mass flow range is from 2.00 to 5.00, more specifically from 3.00 to 4.00, and in particular from 3.25 to 3.75.

[0023] In embodiments where the blade bearing ring and the cover plate have the chamfer, or only the cover plate has the chamfer, in the radial direction in the area of ​​the chamfer(s) (or in the area of ​​the flow channel where the chamfers of the blade bearing ring and the cover plate are opposite each other in the axial direction) at any radial position a first axial distance between the guide vane and the cover plate can be greater than a second axial distance between the guide vane and the blade bearing ring.

[0024] The chamfer can extend completely along the facing side. In other configurations, the chamfer can extend only partially around the circumference. In some configurations, the chamfer can have at least two chamfer sections, each extending over a circumferential segment. The respective circumferential segments can be of equal size. Webs can be arranged between the respective circumferential segments, separating them from one another. Thus, the chamfer can be provided only in the area of ​​specific guide vanes.

[0025] In various embodiments, the guide vane assembly can be a variable turbine geometry. The guide vane assembly can include an adjusting ring, wherein the adjusting ring comprises a plurality of coupling areas. Each adjustable guide vane of the plurality of adjustable guide vanes can be non-rotatably connected to a blade lever. In particular, each blade lever can be at least partially accommodated in a coupling area for adjusting the respective adjustable guide vane. The adjustable guide vane can be non-rotatably connected to a blade shaft at a first end of the blade shaft. The blade lever can be connected to the blade shaft at a second end of the blade shaft opposite the first end.Each blade lever can have a radial blade lever section extending radially from the blade shaft and an axial blade lever section extending axially from the radial blade lever section towards the adjusting ring. In particular, the axial blade lever section can extend axially, at least partially, into the respective coupling area. The adjustable guide vanes can be rotatably mounted in the blade bearing ring, evenly distributed around the circumference of the blade shafts. The guide assembly can have an odd number of adjustable guide vanes. In some embodiments, at least three spacer elements can be provided, each of which is coupled or connected to at least the blade bearing ring at uniform circumferential intervals.In some embodiments, the spacer elements can be arranged radially between the outer radius of the chamfer and an outer radius of the cover plate and the blade bearing ring. The respective spacer elements can be rigidly connected to the cover plate and / or the blade bearing ring. The guide device can include an actuating device that is operationally coupled to the adjusting ring and is designed to move the adjusting ring circumferentially. The actuating device can be coupled to the adjusting ring via one or more levers and / or a control rod.

[0026] According to a second aspect of the present invention, a turbine for a charging device comprises a turbine housing, a turbine wheel rotatably arranged in the turbine housing, and a guide device according to the first aspect of the present invention. The guide device is arranged radially outside the turbine wheel in the turbine housing and surrounds the turbine wheel completely.

[0027] In certain embodiments, the turbine housing can have a shoulder for the axial and radial support of the shroud. The shoulder can have an annular, axial projection which is arranged radially inside the shroud and forms a radial surface pair with an inner circumference of the shroud. The shoulder, and in particular the projection, can have an end face. The shroud can have a chamfer, the chamfer being flush with the end face of the shoulder in the axial direction on the inner circumference of the shroud. This allows for a smooth transition between the guide vanes, in particular the shroud, and the turbine housing on the side facing the guide vanes. Furthermore, it allows for a more uniform flow to the turbine wheel.

[0028] The shoulder can have an axial surface, and the cover plate can have an axial, disc-shaped extension located in a radially outer region of the cover plate. The axial surface of the shoulder and the axial, disc-shaped extension can form an axial surface pairing.

[0029] In certain embodiments, the cover plate can have a chamfer and an inner circumferential radius, where the inner circumferential radius is equal to or greater than the turbine wheel radius. In particular, the ratio of the turbine wheel radius to the inner circumferential radius can be from 0.75 to 1.00, more specifically from 0.80 to 0.98, and more specifically from 0.85 to 0.95. This embodiment allows for a greater radial extent of the flow channel and improved flow to the turbine wheel.

[0030] In some embodiments, the turbine can include a clamping device, the clamping device being arranged axially between the guide element, in particular the blade bearing ring, and a turbine rear wall. The clamping device can be designed to clamp the guide element against the turbine housing such that an axial force is introduced into the turbine housing via its axial, disk-shaped extension. The clamping device can bear against the blade bearing ring at its radially outer end and against the turbine rear wall at its radially inner end. In some embodiments, a heat shield can be clamped between the clamping device and the blade bearing ring. In some embodiments, the turbine rear wall can be designed as part of a bearing housing.

[0031] According to a third aspect of the present invention, a charging device for an internal combustion engine or a fuel cell comprises a bearing housing, a shaft rotatably mounted in the bearing housing, a compressor with a compressor wheel, and a turbine according to the second aspect of the present invention. The turbine wheel and the compressor wheel are rotationally fixed to the shaft at opposite ends.

[0032] In some embodiments, the compressor can comprise a compressor housing in which the compressor wheel is arranged. The bearing housing can be connected to the turbine housing and the compressor housing. The charging device can include an electric motor, which is arranged in a motor compartment within the bearing housing, with the turbine wheel and / or the compressor wheel being coupled to the electric motor via the shaft.

[0033] The turbine and the charging device according to the aspects of the present invention can provide the advantages described above and have the configurations described above. Brief description of the characters Fig. Figure 1 shows an isometric view of an exemplary charging device with a turbine and a compressor; Fig. 2 shows a sectional view of the turbine with a guide device according to aspects of the present invention; Fig. Figures 3A to 3C show detailed sectional views of the turbine and the guide vane system. Fig. 2; Fig. 4A and Fig. Figure 4B shows a perspective view and an exploded view of the guidance system; Fig. Figures 5A to 5C show sectional views and a top view of a cover plate of the guide device; Fig. 6A and Fig. 6B shows a sectional view through the guide mechanism of the Fig. 2 to 4B (cut through the guide vanes in the flow channel and in top view of the cover plate), wherein the guide vanes of the guiding device are in different guide vane positions; Fig. 7A and Fig. 7B shows a sectional view through the guide mechanism of the Fig. 2 to 4B (section through the guide vanes in the flow channel and in top view of the blade bearing ring); Fig. 8A to 9H indicate the control device of the Fig. 2 to 7B schematically show different radial positions of the guide vane trailing edge with respect to the chamfer(s) for different guide vane positions according to the mass flow range; Fig. Figure 10 shows a diagram in which the efficiency is plotted against the mass flow rate for different guide vane positions of the guide device according to the invention, compared with an ordinary guide device. Detailed description

[0034] In the context of this application, the terms axial and axial direction refer to a rotational axis R of the shaft 70 or the turbine wheel 20, the rotational axis R of the turbine 10 and / or the guide device 100. With reference to the figures (see, for example, Fig. In figures 1 to 9H, the axial direction is represented by the reference symbol 22. The axial direction 22 runs in the direction of the axis of rotation R. A radial direction 24 refers to the axial direction 22. Likewise, a circumference or circumferential direction 26 refers to the axial direction 22. Directions 22 and 24 are orthogonal to each other.

[0035] Fig. Figure 1 shows an exemplary charging device 1. The charging device 1 can be used for an internal combustion engine or a fuel cell and / or be designed or dimensioned accordingly.

[0036] As in Fig. As shown in Figure 1, the charging device 1 comprises a turbine 10, a bearing housing 40, and a compressor 50. As shown in Fig. As shown in Figure 1, the charging device 1 can include an actuating device 60. The charging device 1 can be a turbocharger. In embodiments, the charging device 1 can also be designed as an electric turbocharger (not shown in the figures). The turbine 10 comprises a turbine housing 30 in which a turbine wheel 20 is arranged. The turbine 10 can, in particular, be a radial turbine. The turbine housing 30 comprises a turbine inlet 33, a turbine outlet 34, and a receiving chamber, which is arranged between the turbine inlet 33 and the turbine outlet 34 and is fluidically connected to the turbine inlet 33 and the turbine outlet 34. The turbine wheel 20 is arranged in the receiving chamber. The turbine 10 also comprises a turbine back wall 32, which is coupled to the turbine housing 30 on the bearing housing side. As shown in Figure 1, the turbine housing 30 is connected to the turbine housing 30. Fig. 2, Fig. 3A and Fig. As can be seen in 3B, the turbine rear wall 32 can be designed as part of the bearing housing 40. With reference to Fig. The charging device 1 further comprises a shaft 70 with a rotational axis R, which is rotatably coupled to the turbine wheel 20. The shaft 70 is rotatably mounted in the bearing housing 40. The axial direction 22 is defined with respect to the rotational axis R. As in Fig. As shown in Figure 1, the compressor 50 comprises a compressor housing 51 in which a compressor wheel 52 is arranged. The bearing housing 40 is coupled (or connected) to the turbine housing 30. The compressor wheel 52 is rotationally fixed to the shaft 30 at an end opposite the turbine wheel 12. As shown in Fig. As can be seen in Figure 1, the turbine 10 comprises a guide device 100, in particular a variable turbine geometry, which is explained in detail below.

[0037] In addition to the guide device 100, the turbine 10 (not shown in the figures) can include a power control device in the form of a wastegate flap, which is designed to open and close a wastegate of the turbine 10 as needed. The wastegate flap can be connected to the actuating device 60 via a lever and / or a control rod.

[0038] In some embodiments, the charging device 1 may further include an electric motor (not shown in the figures), which may be arranged in a motor compartment within the bearing housing 40. The turbine wheel 20 and / or the compressor wheel 52 may be coupled to the electric motor via the shaft 70. The electric motor may have a rotor and a stator, in particular wherein the rotor may be arranged on the shaft 30, and wherein the stator surrounds the rotor. Furthermore, a power electronics circuit for controlling the electric motor may be arranged in a receiving compartment within the bearing housing 40. The electric motor may also include a generator mode.

[0039] Fig. Figure 2 shows a first sectional view of the turbine 10 with a guide device 100 according to the invention, in particular a variable turbine geometry. Fig. Figures 3A to 3B show more detailed sectional views of turbine 10. Fig. 2. Fig. 3C, Fig. 4A and Fig. Figure 4B shows a sectional view, a perspective view, and an exploded view of a guide device 100 according to the invention. The guide device 100 is designed to modify the flow to the turbine wheel 20. The guide device 100 is arranged radially outside the turbine wheel 20, in particular, the guide device 100 surrounds the turbine wheel 20 completely. The guide device 100 can be provided as a cartridge mounted in the turbine housing 30. In particular, the guide device 100 can be pre-assembled as a cartridge and mounted on the rear wall 32 of the turbine housing, in particular on the bearing housing 40, by means of at least three pins spaced evenly spaced in the circumferential direction 26. The pins can be connected to the guide device 100 and the rear wall 32 of the turbine housing by means of a press fit.

[0040] As in the Fig. As shown in Figures 2 to 4B and 7A to 9H, the guide device 100 comprises a blade bearing ring 110. The guide device 100 also comprises a cover plate 150, which is arranged parallel or coaxially and spaced axially 22 from the blade bearing ring 110 by spacer elements 160. In particular, the guide device 100 comprises a plurality of spacer elements 160, which are arranged circumferentially 26 distributed on the blade bearing ring 110 such that they provide an axial distance or a flow channel width X. S define the position of the blade bearing ring 110 towards the cover plate 150 (see Fig. 3B). In particular, the plurality of spacer elements 160 can comprise at least three spacer elements. The guide device 100 comprises a plurality of adjustable guide vanes 120, each of which is rotatably and adjustably mounted in the blade bearing ring 110. The adjustable guide vanes 120 are arranged between the cover plate 150 and the blade bearing ring 110. The spacer elements 160 ensure minimal clearance for adjusting the guide vanes 120. In embodiments, the spacer elements 160 can be positioned radially 24 between an outer chamfer radius R. A and an outer radius R D , R S The respective spacer elements 160 can be arranged on the cover plate 150 and / or the blade bearing ring 110. The spacer elements 160 can be rigidly connected to the cover plate 150 and / or the blade bearing ring 110.

[0041] In the Fig. Figures 6A to 9H show the guide vanes 120 in various guide vane positions. The guide vanes 120 are shown between a first guide vane position (see e.g. Fig. 8B, Fig. 9B), and a second guide vane position (see e.g. Fig. 3C) adjustable. In the first guide vane position, the guide vanes are minimally open (a "minimally open position" of the guide vanes). In the second guide vane position, the guide vanes are maximally open (a "maximally open position" of the guide vanes). Several intermediate positions 121, 122 can be set between the first and second guide vane positions (see e.g. Fig. 6A and Fig. 6B). This allows a fluid flow from the turbine inlet 33 to be variably directed through a flow channel, i.e., where the guide vanes 120 are arranged, onto the turbine wheel 20. Nozzle cross-sections D are located between adjacent guide vanes 120. V(also called intermediate channel) are formed, which are larger or smaller depending on the current position of the guide vanes 120 and accordingly supply the turbine wheel 20, mounted on the axis of rotation R, with more or less fluid from an internal combustion engine (e.g., exhaust gas) or a fuel cell in order to drive, for example, a compressor wheel 52 mounted on the same shaft 70 via the turbine wheel 20. The guide vanes 120 can be mounted in the blade bearing ring 110 with uniform circumferential bearing 26. The respective guide vane position is linked to a corresponding mass flow rate through the guide device 100 during operation. In particular, the mass flow rate can be 100% in the second guide vane position. Even in the first guide vane position, a minimum mass flow rate > 0% can be provided by the guide device 100.More precisely, the guide device 100 can provide a mass flow rate in the first guide vane position, since there are still respective nozzle cross-sections D. V between the guide vanes 120. The guide vanes 120 can therefore be uniformly supported in the blade bearing ring 110 in the circumferential direction 26, and adjacent guide vanes 120 can be spaced apart from each other in the first guide vane position. In other words, adjacent guide vanes 120 do not contact each other in the first guide vane position.

[0042] The guide vanes each have a leading edge (or upstream edge) and a trailing edge 123 (or downstream edge). The leading edge can be understood as the upstream area of ​​the guide vane 120 at its maximum distance from the guide vane's axis of rotation PA. The trailing edge can be understood as the downstream area of ​​the guide vane 120 at its maximum distance from the guide vane's axis of rotation PA. In other words, the trailing edge is located downstream of the leading edge when viewed in the flow direction along the guide vane 120. A position of the guide vanes 120 can also be referred to as a position or operating position.This includes every possible position of a guide vane 120 during the operation of the turbine 10 between the first guide vane position (at minimum flow / cross-section) and the second guide vane position (at maximum flow / cross-section). Each "possible position" can be understood as any position that may be present during operation. It is known to those skilled in the art that the operating positions change variably and automatically during the operation of the turbine 10 with the guide vane 100, or the variable turbine geometry. To control the movement or position of the guide vanes 120, an actuating device 60 can be provided, as described above. This device can be of any design, for example, electronic or pneumatic, to name just a few examples. The actuating device 60 can be an actuator. In the example of... Fig. 1 The actuating device 60 is pneumatically designed with a control housing (for example a pressure capsule) and a plunger element, which transmits the movement of the control housing via one or more intermediate elements, in particular via an adjusting shaft arrangement, to the guide device 100 or the guide vanes 120.

[0043] As in the Fig. As shown in Figures 2 to 9H, the blade bearing ring 110 and / or the cover plate 150 has a chamfer 200, 200a, 200b. The chamfer 200, 200a, 200b extends on a side 111, 151 of the blade bearing ring 110 and / or the cover plate 150 facing the adjustable guide vanes from an inner circumference 112, 152 of the blade bearing ring 110 and / or the cover plate 152 in a radial direction 24 to an outer chamfer radius R. AIn preferred embodiments, the cover plate 150 and the blade bearing ring 110 can have the chamfer 200a, 200b. However, in other embodiments, only the cover plate 150 or only the blade bearing ring 110 can have the chamfer 200a, 200b. In this case, the other part of the cover plate 150 and the blade bearing ring 110 does not have the chamfer 200a, 200b. The side 111, 151 facing the blade bearing ring 110 or the cover plate 150 that does not have the chamfer 200a, 200b can extend (particularly continuously) in the radial direction 24 or (particularly continuously) perpendicular to the axial direction 22 between the inner and outer circumferences.

[0044] The Fig. Figures 2 to 9H show the radial position of the guide vane trailing edge 123 for several guide vane positions with respect to the chamfer(s) 200, 200a, 200b. As described above, the adjustable guide vanes 120 each have a guide vane trailing edge 123. At least a section of the guide vane 120, in particular the guide vane trailing edge 123, lies in the region of the chamfer 200, 200a, 200b in the radial direction 24 for guide vane positions corresponding to a mass flow range from a first mass flow value to a second mass flow value. Preferably, the first mass flow value is a maximum of 35%.In other words, this means that the chamfer 200, 200a, 200b extends in radial direction 24 such that, from a guide vane position corresponding to a mass flow rate of 35%, relative to a maximum mass flow rate (in particular of 100%) through the guide device 100, the trailing edge of the guide vane 123 is located in the region of the chamfer 200, 200a, 200b in radial direction 24, or moves into this region from this mass flow rate value. In the guide vane positions corresponding to the mass flow rate range through the guide device 100, the (in particular complete) guide vane 120 can be located in the flow channel in radial direction 24, i.e., in the region where the shroud 150 and the blade bearing ring 110 are opposite each other in axial direction 22.Consequently, the guide vane trailing edge can be located in the radial direction in the area of ​​the chamfer(s) 200, 200a, 200b and in the flow channel, i.e., in the area where the shroud 150 and the blade bearing ring 110 are axially opposed 22, corresponding to the described mass flow rate range from the first mass flow rate value to the second mass flow rate value. To achieve these corresponding guide vane positions, the guide vanes 120 are rotated about a respective axis of rotation PA of the guide vane 120, thereby changing the radial position of the guide vane trailing edge 123. The "operation" of the guide device 100 can be described by a standard combustion chamber measurement for guide devices 100, in particular VTGs, in which the measuring range is defined in equally sized flow rate parameter steps for different guide vane positions depending on the mass flow rate or mass throughput through the guide device 100.The chamfer 200, 200a, 200b in the blade bearing ring 110 and / or the cover plate 150 in the area for certain "open" guide vane positions increases the efficiency of the guide vane system 100, particularly for a specific range of "open" guide vane positions. The fact that the trailing edge 123 of the adjustable guide vanes 120 is located radially 24 in the area of ​​the chamfer 200, 200a, 200b for guide vane positions corresponding to the mass flow range necessitates a specific radial arrangement and extent of the chamfer 200, 200a, 200b, as well as the cover plate 150 and / or the blade bearing ring 110 (or the flow channel formed by these components) with respect to the guide vanes 120 and thus the corresponding guide vane positions.

[0045] Furthermore, a continuous flow pattern can be provided by the guide device 100 according to the invention, and improved flow to the turbine wheel 20 can be achieved. In addition, sudden widenings or changes in the flow channel width X can be prevented. S Enthalpy losses when using the guide vane 100 in a turbine 10 can be compensated for. Improved fuel consumption can be achieved when used with an internal combustion engine. Furthermore, the chamfer 200, 200a, 200b can reduce or prevent jamming of the guide vanes 120 at high temperatures (and corresponding thermal expansion of the components).

[0046] In preferred embodiments, the first mass flow rate value can be a maximum or exactly 30%, in particular a maximum or exactly 20%, or more specifically a maximum or exactly 10%. In preferred embodiments, which can be combined arbitrarily with the described first mass flow rates, the second mass flow rate value can be at least or exactly 55%, or more specifically at least or exactly 65%, or in particular at least or exactly 70%. The described first and second mass flow rates result in the corresponding mass flow rate ranges, which are linked to respective guide vane positions and for which at least one section of the guide vane 120, in particular the trailing edge 123 of the guide vane, lies in the radial direction 24 in the region of the chamfer 200, 200a, 200b.A larger mass flow range consequently necessitates a larger radial arrangement and extent of the chamfer(s) 200, 200a, 200b, as well as the cover plate 150 and / or the blade bearing ring 110 with respect to the guide vanes 120 or guide vane positions. The guide vane trailing edge 123 can be located in the radial direction 24 in the area of ​​the chamfer(s) 200, 200a, 200b (and in particular in the area of ​​the chamfer(s) and in the flow channel) according to the following preferred mass flow ranges: • The first mass throughput value can be 35% and the second mass throughput value can be 55%, resulting in a mass throughput range of 35% to 55%; • The first mass throughput value can be 30% and the second mass throughput value can be 65%, resulting in a mass throughput range of 30% to 65%; • The first mass throughput value can be 20% and the second mass throughput value can be 70%, resulting in a mass throughput range of 20% to 70%; or • The first mass throughput value can be 10% and the second mass throughput value can be 70%, resulting in a mass throughput range of 10% to 70%.

[0047] However, other mass throughput ranges can also be formed using the first and second mass throughput values ​​mentioned above.

[0048] As an alternative to defining a guide vane position according to a mass flow range from a first mass flow value to a second mass flow value, the respective guide vane position of a guide vane 120 can also be defined geometrically. "Geometrically defined" means that the position of the guide vane 120 is not defined by the mass flow through the guide device, but, for example, by an angle of attack of the guide vane between the first and second guide vane positions. For example, an angle of attack of 50% could mean that the guide vane is 50% open between the angle in the first guide vane position and the angle in the second guide vane position. It should be noted, however, that the mass flow values ​​and ranges described above, based on a maximum mass flow of 100% through the guide device 100, are not directly related to an angle of attack value.These ranges can be equated. They differ from each other and generally do not behave linearly.

[0049] The Fig. Figures 6A to 9H show different guide vane positions of the guide device 100 according to the invention, corresponding to the respective mass flow rates or mass flow ranges described above. Fig. 6A and Fig. Figure 6B shows a sectional view through the guide device 100 of the Fig. 2 to 4B, cut through the guide vanes 120 in the flow channel and in top view of the cover plate 150. Fig. 7A and Fig. Figure 7B shows a sectional view through the guide device 100 of the Fig. 2 to 4B, sectioned through the guide vanes 120 in the flow channel and in top view of the blade bearing ring 110. The Fig. Figures 8A to 9H show several guide vane positions and the respective radial position of the guide vane trailing edge 123 with respect to the chamfer(s) 200, 200a, 200b. A trailing edge radius R can be defined between the axial direction 22 and the guide vane trailing edge 123. L The trailing edge radius R is defined or measured. L This decreases as the guide vanes open more fully (and thus as the guide vane position becomes increasingly "open"). In other words, the trailing edge 123 of the guide vane moves radially inwards as the guide vanes 120 open more fully due to the rotation around the axis of rotation PA. Fig. 6A to 9H are different guide vane positions and the corresponding trailing edge radii R L , R L1 -R L6 (i.e., the corresponding radial position of the trailing edge 123) is shown. The trailing edge radius R LDepending on the guide vane position, the outer radius of the chamfer R can be equal to or smaller than the mass flow range. A be. The trailing edge radius R L Depending on the guide vane position, the inner circumferential radius R can be equal to or greater than the mass flow range. I1 , R I2 of the blade bearing ring 110 and / or the cover plate 150. In other words, from a guide vane position corresponding to the first mass flow rate value, the trailing edge radius R can be L equal to or less than the chamfer outer radius R A The chamfer 200, 200a, 200b therefore extends in radial direction 24 such that the trailing edge 123 of the guide vane is located in the radial direction within the chamfer 200, 200a, 200b at least from the first mass flow value onwards. Fig. 6A, 7A, 7B, and 8A to 8D and 9A to 9D show the respective trailing edge radii R. L , R L1-6The trailing edge of the guide vane 123 with respect to the chamfer(s) for guide vane positions corresponding to the mass flow values ​​described above. The trailing edge radius R L This can be achieved with a first mass throughput value of a maximum of 35% (see R). L1 ), specific maximum 30% (between R L1 and R L2 ), more specifically 20% (see R L2 ), in particular 10% (see R L3 ), equal to or less than the chamfer outer radius R A If the first mass flow rate value is, for example, 10%, then the chamfer must extend radially outwards to this guide vane position. For smaller guide vane positions corresponding to the 10% mass flow rate, the trailing edge radius R can be L larger than the chamfer outer radius R A be (see e.g. R) L in Fig. 8A, Fig. 8B, Fig. 9A and Fig. 9B). In other words, the trailing edge of the guide vane is not (yet) located in the radial direction 24 in the area of ​​the chamfer(s) 200, 200a, 200b. A smaller initial mass flow rate necessitates a greater radial outward extension of the chamfer 200, 200a, 200b.

[0050] The trailing edge radius R L Depending on the guide vane position, the inner circumferential radius R can be equal to or greater than the mass flow range. I1 , R I2 of the blade bearing ring 110 and / or the cover plate 150. As shown in the figures, the inner circumferential radius R can also be I2 The diameter of the blade bearing ring must be 110 smaller than the inner circumferential radius R. I1of the cover plate 150. In this case, the cover plate 150 can be arranged with respect to the blade bearing ring 110 such that the guide vane trailing edge 123, in guide vane positions corresponding to the second mass flow value in the radial direction, lies in the region of the chamfer 200, 200a, 200b and in the flow channel. Only at values ​​higher than the second mass flow value can the guide vanes 120 no longer be completely located in the flow channel (i.e., in the region where the blade bearing ring 110 and the cover plate 150 are opposite each other in the axial direction 22). At least one section, in particular the guide vane trailing edge 123, is radially inside the corresponding larger inner circumferential radius R for these guide vane positions. I1 , R I2 (in the example shown above, inner circumference radius R) I1the cover plate 150). The second mass flow rate value can therefore result in a radial extension of the blade bearing ring 110 and / or the cover plate 150, as well as the chamfer(s) (in particular, an extension of the chamfer(s) and the flow channel radially inwards). Performance deficits can be reduced or avoided by the described second mass flow rate values. In the Fig. 6B, 8E to 8H and 9E to 9H represent the guide vane positions corresponding to the second mass flow values ​​described above. The trailing edge radius R L can be achieved up to the second mass throughput value of at least 55% (see R L4 ), specifically at least 65% (between R L5 ), more specifically at least 70% (see R L6 ), equal to or greater than the inner circumferential radius R I1 , R I2of the blade bearing ring 110 and / or the shroud 150 (or the flow channel defined by the shroud and blade bearing ring). If the second mass flow rate value is, for example, 70%, the chamfer (and in particular the chamfer(s) and the flow channel) must extend radially inwards to this guide vane position. In the example of the Fig. 6B contains the guide vane trailing edge 123 and the trailing edge radius (see R L7) at mass flow rates higher than 70%, the guide vane trailing edge 123 extends radially inward to the shroud 150 (or the flow channel). After the second mass flow rate, the guide vane trailing edge 123 consequently leaves the radial area of ​​the chamfer(s) and the flow channel. The radial extension of the chamfer(s) 200, 200a, 200b, the blade bearing ring 110, and / or the shroud 150 (or the flow channel formed by these components) described above can reduce or prevent performance deficits.

[0051] Fig. Figure 10 shows a diagram 300 in which the efficiency 320 is plotted against the mass flow rate 310 for various guide vane positions of the guide device 100 according to the invention (see first curve 330), compared to an ordinary guide device (see second curve 340). The curves were determined by tests and simulations for an expansion coefficient in operation (definition see above) of the respective guide devices. In contrast to the guide device 100 according to the invention, the ordinary guide device has no chamfer(s) and also lacks the radial arrangement or extension of the cover plate 150 and / or the blade bearing ring 110 (or the flow channel) with respect to the guide vanes 120. In diagram 300, the efficiency 320 (or η) is plotted on the ordinate, which is related to the efficiency of the guide device in operation. The mass throughput is given as a percentage on the abscissa.Figures 330 and 340 represent different guide vane positions of the guide device 100 according to the invention and of the conventional guide device. Figures 330 and 340 each have second guide vane positions corresponding to a maximum mass flow rate of 100%. Each figure also has a first guide vane position corresponding to a minimum mass flow rate greater than 0%. A comparison of Figures 330 and 340 shows that the features of the guide device 100 according to the invention increase the efficiency, particularly for guide vane positions corresponding to at least 20% to 60% mass flow rates, and especially 10% to 70% mass flow rates. Consequently, the efficiency of the guide device 100 according to the invention can also be increased in this range. This also applies to the guide vane positions of the guide device 100 according to the invention corresponding to the described mass flow rate ranges.

[0052] As mentioned above, the blade bearing ring 110 and the cover plate 150 can define a flow channel in which the adjustable guide vanes 120 are arranged. The flow channel can have a flow channel width X. S exhibiting, which is measured in the axial direction 22 between the blade bearing ring 110 and the cover plate 120 (see Fig. 3B and Fig. 3C). The flow channel width X S can in the radial area between an outer circumference R D , R S of the blade bearing ring 110 and / or the cover plate 150 and the chamfer outer radius R A essentially constant, in particular constant (this region can be called the constant region). The flow channel width X S can be used to distinguish between the chamfer outer radius R Aand the inner circumference 112, 152 of the blade bearing ring 110 and / or the cover plate 150 increase (this area can be referred to as the chamfer area). In particular, the flow channel width X can S The axial width X increases constantly in the chamfered area. V The guide vane(s) 120 is smaller than the flow channel width X S In various configurations, the flow channel width X can be S from the chamfer outer radius R A The chamfer increases constantly up to the inner circumference 112, 152, i.e., in the widening area. In some embodiments, the chamfer area can have at least a second constant area. In one embodiment, the chamfer can extend from the inner circumference 112, 152 in the radial direction 24 to the outer chamfer radius R. AThe flow channel can be seen to have a second constant section, followed by the chamfer 200, 200a, 200b. In other words, the flow channel can taper from the second constant section through the chamfer to the (first) constant section. In embodiments, the chamfer 200, 200a, 200b can have at least two chamfers with different slopes in the radial direction 22. If the chamfer 200a, 200b is provided in the blade bearing ring 110 and in the cover plate 150, the chamfer can be symmetrical with respect to the guide vanes 120, or it can be configured differently. If the blade bearing ring 110 has a smaller inner circumferential radius R I2 than the cover plate 150 (see R I1If the chamfer 200b (or the widening area) of the blade bearing ring 110 has a chamfer, then it can extend further radially inwards than the chamfer 200a of the cover plate 150. In embodiments (not shown in the figures) in which the cover plate and the blade bearing ring each have the chamfer, both chamfers have the same outer chamfer radius R. A In other embodiments, the chamfer 200a of the cover plate 150 can extend to a first chamfer outer radius, and the chamfer 200b of the blade bearing ring 110 can extend to a second chamfer outer radius. The first chamfer outer radius can be larger or smaller than the second chamfer outer radius.

[0053] As described above and in the Fig. As shown in 6A to 9H, the adjustable guide vanes 120 can each have a guide vane rotation axis PA, wherein the chamfer outer radius R Aless than a rotation axis radius R PA is measured radially between the axial direction 22 and the guide vane rotation axis PA. In particular, the chamfer outer radius R can be A a maximum of 15%, in particular a maximum of 10%, less than the radius of the axis of rotation R PA be. In the Fig. 6A to 8E, the guide vanes 120 have a first axial position X PA1 the guide vane rotation axis PA, especially those in the range of 0.40 ≤ X PA1 / C ≤ 0.50. In the Fig. 9A to 9H, the guide vanes 120 have a second axial position X PA2 the guide vane rotation axis PA, which is offset towards the guide vane leading edge compared to the first axial position and in particular which is in the range of 0.20 ≤ X PA2 / C ≤ 0.35. The respective axial position X PA1 , X PA2The distance can be measured parallel to a profile chord C of the guide vane 120 between the guide vane leading edge and the pivot point PA. The profile chord C is a straight line that intersects the guide vane leading and trailing edges at their midpoints and is known for describing a profile geometry. The guide vane positions described above, corresponding to the mass flow ranges, and the associated radial positions of the guide vane trailing edge with respect to the chamfer(s) (or flow channel) can also be applied analogously to this configuration (offset of the axis of rotation from the leading edge). Only the radial position of the axis of rotation R is required. PA with regard to the blade bearing ring 110 (i.e. the bearing of the guide vanes in the blade bearing ring) adapted, whereby the radial position of the axis of rotation R PA The measurement is taken between the axial direction 22 and the pivot point PA. For the first axial position X PA1The axis of rotation PA of the guide vane 120 has a first radial position R PA1 up. For the second axial position X PA2 The axis of rotation PA of the guide vane 120 has a second radial position R PA2 on. The second radial position R PA2 is larger than the first radial position R PA1 In other words, the movement of the guide vane trailing edge 123 can be compensated for by a change in the axial position of the axis of rotation PA by an offset of the radial position of the axis of rotation, so that the principles described herein are applicable to various arrangements of the guide vane axis of rotation PA. In the embodiments described above, each guide vane has the same axial and radial position of the axis of rotation.

[0054] In certain embodiments, the guide device 100, in particular the cover plate 150 and / or the blade bearing ring 110, can have an outer radius R. D , R Sexhibiting a ratio of the chamfer outer radius R A to the outer radius R D , R S from 0.60 to 0.85, in particular from 0.65 to 0.80. In certain embodiments, the inner circumferential radius R can be I2 the diameter of the blade bearing ring 110 must be smaller, equal to, or larger than the inner circumferential radius R I1 the cover plate 150.

[0055] With reference to the Fig. In sections 2 to 3C and 5A to 5C, the cover plate 150 is described in more detail below. The cover plate 150 can have an axial, disk-shaped extension 154 on a side 153 facing away from the adjustable guide vanes 120. This extension can be located in a radially outer region of the cover plate 150. Consequently, the cover plate 150 has a recess 156 on the far side 153 in a radially inner region, in particular extending in the radial direction 24 between the inner circumference 152 and the axial extension 154. As in Fig. As shown in Figure 5B, the cover plate 150 can therefore have a first axial width b1 in the region of the extension 154, and a second, smaller axial width b2 in the region of the recess 156. In particular, the axial extension 154 has an axial surface 155, which serves as an axial bearing surface and for the introduction of forces in the axial direction 22 when the guide device 100 is mounted in a turbine housing 30. In particular, the disk-shaped extension 154 can be arranged in the radial direction 24 in the region of the spacer elements 160. This arrangement allows the forces transmitted to the cover plate 150 by the spacer elements 160 to be introduced directly axially into the turbine housing 30 via the extension 154. This improves the surface pressure. More specifically, the radial width of the extension can be greater than the radial width of the spacer elements 160.

[0056] As in Fig. 3C and Fig. 5B for the cover plate 150 (the same applies to the blade bearing ring 100), the chamfer 200, 200a, 200b between the inner circumference 112, 152 of the blade bearing ring 110 and / or the cover plate 150 can extend in radial direction 24 to the chamfer outer radius R AThe chamfers are flat and / or curved (especially convex with respect to the guide vanes). A chamfer angle α, β can be measured between the facing side 111, 151 and the chamfer 200, 200a, 200b. In certain embodiments, the chamfer angle α, β can range from 0.5° to 5.0°. In this embodiment, the chamfer (in cross-section) can be linear. In certain embodiments, the blade bearing ring 110 and the cover plate 150 can have the chamfer 200a, 200b. A first chamfer angle α of the chamfer 110 of the cover plate 150 can be greater than a second chamfer angle β of the chamfer 200a of the blade bearing ring 110. In certain embodiments, the chamfer angle α can range from 1° to 4°, particularly from 2° to 3°. In the embodiments in which the blade bearing ring 110 and the cover plate 150 form the chamfer 200a, 200b (see Fig. 3C), the chamfer 200a of the cover plate 150 can have a first slope and the chamfer 200b of the blade bearing ring 110 can have a second slope. The first slope can be greater than the second slope, in particular where the ratio of the first slope to the second slope at radial positions (i.e., in the radial area of ​​the chamfers 200a, 200b) for guide vane positions corresponding to the mass flow range is 2.00 to 5.00, more specifically 3.00 to 4.00, and in particular 3.25 to 3.75. In embodiments in which the blade bearing ring 110 and the cover plate 150 have the chamfer 200a, 200b, in the radial direction 24 in the area of ​​the chamfers 200a, 200b, a first axial distance S1 between the guide vane 120 and the cover plate 150 can be greater than a second axial distance S2 between the guide vane 120 and the blade bearing ring 120 at any radial position (see Fig. 3C).

[0057] As in Fig. 5C and Fig. As shown in Figure 7A, the chamfer 200, 200a, 200b extends completely around the circumference of the facing side 111, 151. In other embodiments, the chamfer 200, 200a, 200b may extend only partially around the circumference. In some embodiments, the chamfer 200, 200a, 200b may have at least two chamfer sections, each extending over a circumferential section (e.g., the circumferential area in which the respective guide vanes or their trailing edge are located). The respective circumferential sections may be of the same size. Webs may be arranged between the respective circumferential sections, separating them from one another. Thus, the chamfer 200, 200a, 200b may also be provided only in the area of ​​certain guide vanes 120.If the chamfer 200, 200a, 200b extends only partially around the circumference, then only certain guide vane trailing edge(s), positioned accordingly, can be located within the chamfer 200, 200a, 200b for the described mass flow ranges. For example, the chamfer 200, 200a, 200b can have the (above-described) at least two chamfer sections, each extending over a specific circumferential section. The guide vanes can be arranged with respect to the chamfer sections such that at least one guide vane trailing edge is located within the area of ​​a respective chamfer section for the described mass flow ranges.

[0058] As in Fig. As shown in Figures 2 to 3B, the turbine housing 30 has a shoulder 31 for the axial and radial support of the cover plate 150. The shoulder 31 can have an annular, axial projection 31a, which extends towards the bearing housing 40, is arranged radially inside the cover plate 150, and forms a radial surface pairing with an inner circumference 152 of the cover plate 150. The shoulder 31, in particular the projection 31a, has an end face 31c (see Figure 2 to 3B). Fig. 3B). If the cover plate 150 has the chamfer 200a, the chamfer 200a on the inner circumference 152 of the cover plate 150 can be flush with the end face 31c of the shoulder 31 in the axial direction 22. This allows for a smooth transition between the guide vane 100, in particular the cover plate 150, and the turbine housing 30 on the side facing the guide vanes 120. Furthermore, it allows for a more uniform flow from the flow channel to the turbine wheel 20. The shoulder 31 can have an axial surface 31b. The axial surface 31b of the shoulder 31 and the axial, disk-shaped extension 154 of the cover plate 150 can form an axial surface pairing by means of which the axial forces described above can be transferred from the guide vane 100 into the turbine housing 30.

[0059] The turbine wheel 20 has a turbine wheel back wall 21 and a hub wall 21b opposite the turbine back wall 21. The turbine wheel 20 has a plurality of turbine wheel blades, each of which has a leading edge 21c (see Fig. 3B). In preferred embodiments, the facing side of the blade bearing ring 110 (whether or not the blade bearing ring 110 includes the chamfer) can be flush with the hub wall 21b on the inner circumference 112 in the axial direction 22 at a turbine wheel radius R T (measured radially between the axial direction 22 and the outer circumference of the turbine wheel 20). The axial width of the flow channel X SThe inner circumference 152 of the cover plate 150 can be wider than the axial width of the leading edge 21c. In some embodiments, a first axial distance between the blade bearing ring 110 and the cover plate 150 and / or the end face 31c of the shoulder 31, measured along the inner circumference 152 of the cover plate 150 in the axial direction 22, can be equal to or greater than a second axial distance between the blade bearing ring 110 and a point on the leading edge 21c furthest from the blade bearing ring. The features described above enable improved and more uniform flow to the turbine wheel 20 from the flow channel of the guide vane 100.

[0060] As from Fig. As can be seen in 3B, if the cover plate 150 has the chamfer 200a, the inner circumferential radius R I1 the cover plate 150 equal to or greater than the turbine wheel radius R T be. In particular, a ratio of the turbine wheel radius R can beT to the inner circumference radius R I1 The ratio can range from 0.75 to 1.00, in particular from 0.80 to 0.98, and more specifically from 0.85 to 0.95. This design allows for a greater radial extent of the flow channel and improved flow to the turbine wheel. In some embodiments, the ratio can also be greater than 1.00. In this case, the shoulder 31 of the turbine housing 30 can be offset radially inwards or omitted entirely (for example, the radial support of the cover plate can then be replaced by suitable connecting means such as positive or force-fit connections).

[0061] As in the Fig. As shown in Figures 2 to 4B, 7A and 7B, the guide device 100 comprises an adjusting ring 170. The majority of adjustable guide vanes 120 are adjustable between the first guide vane position and the second guide vane position by moving the adjusting ring 170 in the circumferential direction 26. In particular, the adjusting device 60 is operationally coupled to the adjusting ring 170 and designed to move the adjusting ring 170 in the circumferential direction 26. The adjusting device 60 is coupled to the adjusting ring 170 via one or more levers and / or a control rod. Each guide vane 120 comprises a blade shaft 130, which is rotationally fixed to a guide vane body, in particular wherein the blade shaft 130 is designed such that the guide vane 120 can be rotatably mounted in the blade bearing ring 110 of the guide device 100 via the blade shaft 130. A longitudinal axis or rotational axis of the blade shaft 130 defines the guide vane rotational axis PA.In other words, the majority of guide vanes 120 are rotatably mounted in the blade bearing ring 110 via a blade shaft 130. The guide vanes 120 are rotatably mounted in the blade bearing ring 110 and can be rotated or adjusted via the adjusting ring 120. In particular, the adjustable guide vanes 120 are rotatably mounted in the blade bearing ring 110 via the blade shafts 130, evenly distributed in the circumferential direction 26. The blade shafts 130 extend in the axial direction 22, in particular parallel to the axis of rotation R. Alternatively, the guide vanes 120 are rotatably mounted in the blade bearing ring 110 along a respective guide vane rotation axis PA, wherein the respective guide vane rotation axis PA runs parallel to the axial direction 22 or axis of rotation R. An odd number of guide vanes 120 can be provided. More than eight guide vanes, especially more than ten guide vanes (e.g.11 guide vanes), preferably more than 12 guide vanes may be provided. Exactly 13 guide vanes 120 may be provided. In other embodiments, an even number of guide vanes 120 may be provided.

[0062] Each guide vane 120 of the majority of adjustable guide vanes 120 is rotationally fixed to a blade lever 140. Each blade lever 140 is at least partially received in a coupling area 180 of the adjusting ring 170 for adjusting the respective guide vane 120. In other words, the blade levers 140 are operatively coupled to the adjusting ring 170 (see Fig. 4A, Fig. 7A). When the adjusting ring 170 is rotated circumferentially 26, the guide vanes 120 can be adjusted. As described above, the guide vane bodies are each rotationally fixed to the respective blade shaft 130 at a first end of the blade shaft 130. The blade lever 140 is connected to the blade shaft 130 at a second end opposite the first end of the blade shaft 130. Each blade lever 140 can have a radial blade lever section 141, which extends radially from the blade shaft 130. In addition, each blade lever 140 can have an axial blade lever section 142, which extends axially from the radial blade lever section 141 towards the adjusting ring 170. In particular, the axial blade lever section 142 can extend axially, at least partially, into the respective coupling area 180.The axial blade lever section 142 can extend from the radial blade lever section 141 predominantly parallel to the blade shaft 130. As shown in the figures, the blade levers 140 and the guide vanes 120 can be arranged on opposite sides of the blade bearing ring 110.

[0063] As in Fig. 2 and Fig. As indicated in Figure 3B, the guide device 100 can further comprise a pre-guide grid 190, which circumferentially surrounds the blade bearing ring 110 and / or the plurality of adjustable guide vanes 120. The pre-guide grid 190 can have a plurality of fixed pre-guide vanes. The fixed pre-guide vanes can each be arranged between two adjacent, adjustable guide vanes 120, in particular within an outer circumference of the guide device 100. The fixed pre-guide vanes are provided with a fixed angle of attack. In other words, the pre-guide vanes are not rotatable or adjustable. In embodiments, the pre-guide grid 190 can also replace the spacer elements 160 and determine the axial distance or the flow channel width X. S Ensure between the blade bearing ring 110 and the cover plate 150.

[0064] As described above, the guide device 100 has an adjusting ring 170, which comprises a disk-shaped (or ring-shaped) body and in which the majority of coupling areas 180 are formed. The coupling areas 180 are spaced apart in the circumferential direction 26. The respective blade levers 140 are each engaged with a coupling area 180, so that when the adjusting ring 170 moves in the circumferential direction 26, this movement can be transmitted to the blade levers 140 and thus to the adjustable guide vanes 120. In particular, a rotation of the adjusting ring 170 in the circumferential direction 26 leads to a rotation of the respective guide vanes 120 about their respective guide vane axis of rotation PA, and in particular to an adjustment of the respective guide vanes 120.In the embodiments shown, “partially incorporated” means that the respective blade lever 140 extends into the respective coupling area 180, in particular in the axial direction 22, such that a force transmission between the adjusting ring 170 and the blade levers 140 can take place when the adjusting ring 170 moves in the circumferential direction 26.

[0065] For example, in the Fig. 2, Fig. 3A and Fig. As shown in Figure 3B, the turbine 10 can include a clamping device 500, which is arranged in the axial direction 22 between the guide device 100, in particular the blade bearing ring 110, and the turbine rear wall 32. The clamping device 500 can be designed to clamp the guide device 100 against the turbine housing 30 such that an axial force is introduced into the turbine housing 30 in the axial direction 22 via the axial, disk-shaped extension 154. The clamping device 500 can be designed as a disc spring. The clamping device 500 has a radially outer end and a radially inner end. The clamping device 500 can bear against the blade bearing ring 110 at its radially outer end and against the turbine rear wall 32 at its radially inner end. The turbine 10 can also include a heat shield 600. The heat shield 600 can reduce heat transfer from the turbine 10 to the bearing housing 40 and / or to the compressor 50.The heat shield 600 can be arranged axially 22 between the turbine wheel 20 and the bearing housing 40, in particular between the guide device 100 and the bearing housing 40. More specifically, the heat shield 600 can be clamped between the clamping device 500 and the blade bearing ring 110. In particular, the heat shield 600 can be clamped between the blade bearing ring 110 and the radially outer end of the clamping device 500. The clamping device 500 can indirectly contact the blade bearing ring 110 via the heat shield 600. The clamping device 500 can form line contact with the bearing housing 40 and surface contact with the heat shield 600, in particular at its radially outer end. In alternative embodiments, the clamping device 500 can also directly contact the blade bearing ring 110.The preload force generated by the clamping device 500 can be axially transferred from the blade bearing ring 110 to the cover plate 150 and the turbine housing 30 by means of the spacer elements 160 and / or the guide vane 190.

[0066] In the embodiments described above, reference is often made only to a chamfer 200. The embodiments described above apply to the chamfer 200, 200a of the cover plate 150, the chamfer 200, 200b of the blade bearing ring, and / or to the chamfers 200a, 200b of the blade bearing ring 110 and the cover plate 150, respectively. As described above, the guide assembly 100 comprises a plurality of adjustable guide vanes 120. In special embodiments, the guide assembly 100 can also have at least one fixed guide vane (i.e., a guide vane that is rotationally fixed to the blade bearing ring 110). Although the guide vanes 200, viewed in the axial direction 22 towards the cover plate 150, are in the Fig. While guide vanes 2 to 4B, 6A and 6B are oriented counterclockwise (i.e., the respective leading edges of the blades are oriented counterclockwise), they can also be oriented clockwise (i.e., the respective leading edges of the blades are oriented clockwise), as is the case with guide vanes 120, for example, in the Fig. Figures 7A to 9H are shown. Naturally, in a guide device 100 according to the invention, all guide vanes 120 are aligned in the same way. Although the guide device 100 is essentially ring-shaped and the guide vanes 200 are shown spaced apart from each other in the circumferential direction 26, in other embodiments the guide device 100 can also be provided such that the adjustable guide vanes are arranged linearly next to each other and spaced apart from each other. Naturally, in such an embodiment, the other components of the guide device 100 are adapted accordingly.

[0067] Although the present invention has been described above and is defined in the attached claims, it should be understood that the invention can alternatively also be defined according to the following embodiments: 1. Guide device (100) for a turbine (10), comprising: a shovel bearing ring (110), a cover plate (150) which is arranged parallel to and spaced in the axial direction (22) from the blade bearing ring (110) by means of spacer elements (160), and a plurality of adjustable guide vanes (120), each rotatable and adjustable guide vanes (120) are mounted in the blade bearing ring (110), wherein the adjustable guide vanes are arranged between the cover plate (150) and the blade bearing ring (110), wherein the adjustable guide vanes (120) between a first guide vane position, in which the guide vanes are minimally open, and a second guide vane position (122) in which the guide vanes are maximally open, are adjustable wherein the respective guide vane position in the operation of the guide device (100) is linked to a corresponding mass throughput through the guide device (100), in particular where the mass throughput is 100% in the second guide vane position, wherein the blade bearing ring (110) and / or the cover plate (150) has a chamfer (200, 200a, 200b) which extends on a side (111, 151) of the blade bearing ring (110) and / or the cover plate (150) facing the adjustable guide vanes from an inner circumference (112, 152) of the blade bearing ring (110) and / or the cover plate (152) in a radial direction (24) to a chamfer outer radius (R) A extends wherein the adjustable guide vanes (120) each have a guide vane trailing edge (123), wherein the guide vane trailing edge (123) is located in the area of ​​the chamfer (200, 200a, 200b) in guide vane positions corresponding to a mass flow range from a first mass flow value to a second mass flow value in radial direction (24), where the first mass throughput value is a maximum of 35%. 2. Guide device (100) according to embodiment 1, wherein the first mass throughput value is a maximum of 30%, in particular a maximum of 20%, more specifically 10%. 3. Guide device (100) according to embodiment 1 or embodiment 2, wherein the second mass throughput value is at least 55%, more specifically at least 65%, in particular 70%. 4. Guide device (100) according to any of the preceding embodiments, wherein the first mass throughput value is 35% and the second mass throughput value is 55%, or where the first mass throughput value is 30% and the second mass throughput value is 65%, or where the first mass throughput value is 20% and the second mass throughput value is 70%, or where the first mass throughput value is 10% and the second mass throughput value is 70%. 5. Guide device (100) according to any of the preceding embodiments, wherein a trailing edge radius (R) L ) between the axial direction (22) and the guide vane trailing edge (123), where the trailing edge radius (R) L ) decreases with increasingly opening guide vanes, and wherein the guide vane trailing edge (123) is located in a flow channel in which the cover disk (150) and the blade bearing ring (110) are opposite each other in the axial direction (22) in the guide vane positions corresponding to the mass flow range from the first mass flow value to the second mass flow value. 6. Guide device (100) according to embodiment 5, wherein the trailing edge radius (R L ) for guide vane positions corresponding to the mass flow range equal to or smaller than the chamfer outer radius (R) A ) is. 7. Guide device (100) according to embodiment 5 or 6, wherein the trailing edge radius (R) L ) for guide vane positions equal to or greater than an inner circumferential radius (R) corresponding to the mass flow range I1 , R I2 ) of the blade bearing ring (110) and / or the cover plate (150). 8. Guide device (100) according to any of the preceding embodiments, wherein the blade bearing ring (110) and the cover plate (150) define a flow channel in which the adjustable guide vanes (120) are arranged, where the flow channel has a flow channel width (X) S) exhibits, which is measured in the axial direction (22) between the blade bearing ring (110) and the cover plate (150), where the flow channel width (X) S ) between an outer circumference of the blade bearing ring (110) and / or the cover plate (150) and the chamfer outer radius (R) A ) is constant, and where the flow channel width (X) S ) between the chamfer outer radius (R A ) and the inner circumference (112, 152) of the blade bearing ring (110) and / or the cover plate (150) increases. 9. Guide device (100) according to any of the preceding embodiments, wherein the adjustable guide vanes (120) each have a guide vane rotation axis (PA), wherein the chamfer outer radius (R) A ) less than a rotation axis radius (R PA ) is which is measured between the axial direction (22) and the guide vane rotation axis (PA), in particular where the chamfer radius (R) A) at most 10% less than the radius of the axis of rotation (R) PA ) is. 10. Guide device (100) according to any of the preceding embodiments, wherein the guide vanes (120) are uniformly supported in the circumferential direction (26) in the vane bearing ring (110), and wherein adjacent guide vanes (120) are spaced apart from each other in the first guide vane position. 11. Guide device (100) according to any of the preceding embodiments, wherein the cover plate (150) comprises the chamfer (200, 200a), in particular wherein the facing side (111) of the blade bearing ring (110) is perpendicular to the axial direction (22). 12. Guide device (100) according to any of the preceding embodiments, wherein an inner circumferential radius (R) I2 ) of the blade bearing ring (110) is smaller than an inner circumferential radius (R I1 ) the cover plate (150). 13. Guide device (100) according to any of the preceding embodiments, wherein the cover plate (150) has the chamfer (200a) and wherein the cover plate (150) has an outer radius (R D ) shows, where a ratio of the chamfer outer radius (R A ) to the outer radius (R D ) from 0.60 to 0.85, in particular from 0.65 to 0.80. 14. Guide device (100) according to any of the preceding embodiments, wherein the cover plate (150) has an axial, disk-shaped extension (154) on a side (153) facing away from the adjustable guide vanes (120), which is arranged in a radially outer region of the cover plate (150). 15. Guide device (100) according to embodiment 14, wherein the disk-shaped extension (154) is arranged in the radial direction (24) in the area of ​​the spacer elements (160). 16. Guide device (100) according to any of the preceding embodiments, wherein the chamfer (200, 200a, 200b) extends between the inner circumference (112, 152) of the blade bearing ring (110) and / or the cover plate (152) in a radial direction (24) to the chamfer outer radius (R) A ) runs flat and / or curved. 17. Guide device (100) according to any of the preceding embodiments, wherein a chamfer angle (α, β) is measured between the facing side (111, 151) and the chamfer (200, 200a, 200b), wherein the chamfer angle (α) is from 0.5° to 5.0°. 18. Guide device (100) according to embodiment 17, wherein the blade bearing ring (110) and the cover plate (150) have the chamfer (200a, 200b), wherein a first chamfer angle (α) of the chamfer (200a) of the cover plate (150) is greater than a second chamfer angle (β) of the chamfer (200b) of the blade bearing ring (110). 19. Guide device (100) according to embodiment 17 or 18, wherein the cover plate (150) has the chamfer (200a), wherein the chamfer angle (α) of the chamfer (200a) is from 1° to 4°, in particular from 2° to 3°. 20. Guide device (100) according to any of the preceding embodiments, wherein the blade bearing ring (110) and the cover plate (150) have the chamfer (200a, 200b), wherein the chamfer (200a) of the cover plate (150) has a first slope and wherein the chamfer (200b) of the blade bearing ring (110) has a second slope, wherein the first slope is greater than the second slope, in particular wherein the ratio of the first slope to the second slope at radial positions for guide vane positions corresponding to the mass flow range is from 2.00 to 5.00, more specifically from 3.00 to 4.00, in particular from 3.25 to 3.75. 21. Guide device (100) according to any of the preceding embodiments, wherein the blade bearing ring (110) and the cover plate (150) have the chamfer (200a, 200b), wherein in the radial direction (24) in the region of the chamfers (200a, 200b) at each radial position a first axial distance (S1) between the guide vane (120) and the cover plate (150) is greater than a second axial distance (S2) between the guide vane (120) and the blade bearing ring (120). 22. Guide device (100) according to any of the preceding embodiments, wherein the chamfer (200, 200a, 200b) extends completely circumferentially on the facing side (111, 151). 23. Guide device (100) according to any of the preceding embodiments, wherein the guide device (100) is a variable turbine geometry. 24. Guide device (100) according to any of the preceding embodiments, wherein the guide device (100) comprises an adjusting ring (170), wherein the adjusting ring (170) comprises a plurality of coupling areas (180), and wherein each adjustable guide vane (120) of the plurality of adjustable guide vanes (120) is rotationally fixed to a vane lever (140), in particular wherein each vane lever (140) is at least partially received in a coupling area (180) for adjusting the respective adjustable guide vane (120). 25. Guide device (100) according to embodiment 24, wherein the adjustable guide vane (120) is non-rotatably connected to a blade shaft (130) at a first end of the blade shaft (130), and wherein the blade lever (140) is connected to the blade shaft (130) at a second end of the blade shaft (130) opposite the first end. 26. Guide device (100) according to embodiment 24 or embodiment 25, wherein each blade lever (140) has a radial blade lever section (141) which extends radially from the blade shaft (130) and an axial blade lever section (142) which extends axially from the radial blade lever section (441) to the adjusting ring (170), in particular wherein the axial blade lever section (142) extends axially at least partially into the respective coupling area (180). 27. Guide device (100) according to any of embodiments 24 to 26, wherein the adjustable guide vanes (120) are rotatably mounted in the blade bearing ring (110) via the blade shafts (130) in the circumferential direction (26) evenly distributed. 28. Guide device (100) according to any of the preceding embodiments, wherein the guide device (100) has an odd number of adjustable guide vanes (120). 29. Guide device (100) according to any of the preceding embodiments, wherein at least three spacer elements (160) are provided, each of which is connected to at least the blade bearing ring (110) at uniform intervals in the circumferential direction (26). 30. Guide device (100) according to any of the preceding embodiments, wherein the spacer elements (160) extend in a radial direction (24) between the chamfer outer radius (R) A ) and an outer radius (R D , R S ) the cover plate (150) and the blade bearing ring (110), in particular wherein the respective spacer elements (160) are firmly connected to the cover plate (150) and / or the blade bearing ring (110). 31. Guide device (100) according to any of the preceding embodiments 24 to 30, comprising an actuating device (60) which is operationally coupled to the adjusting ring (170) and is designed to move the adjusting ring (170) in the circumferential direction (26), in particular wherein the actuating device (60) is coupled to the adjusting ring (170) via one or more levers and / or a control rod. 32. Turbine (10) for a charging device (1), comprising: a turbine housing (30), a turbine wheel (20) which is rotatably arranged in the turbine housing (30), and a guide device (100) according to any of the preceding embodiments, which is arranged radially outside the turbine wheel (20) in the turbine housing (30) and surrounds the turbine wheel (20) completely. 33. Turbine (10) according to embodiment 32, wherein the turbine housing (30) has a shoulder (31) for axial and radial support of the cover plate (150), in particular wherein the shoulder (31) has an annular axial projection (31a) which is arranged radially inside the cover plate (150) and forms a radial surface pairing with an inner circumference (152) of the cover plate (150). 34. Turbine (10) according to embodiment 33, wherein the shoulder (31), in particular the projection (31a), has an end face (31c), and wherein the cover plate (150) has the chamfer (200, 200a), wherein the chamfer (200, 200a) is flush with the end face (31c) of the shoulder (31) on the inner circumference (152) of the cover plate (150) in the axial direction (22). 35. Turbine (10) according to embodiment 33 or embodiment 34, wherein the shoulder (31) has an axial surface (31b) and wherein the cover plate (150) has an axial, disk-shaped extension (154) which is arranged in a radially outer region of the cover plate (150), wherein the axial surface (31b) of the shoulder and the axial, disk-shaped extension (154) form an axial surface pairing. 36. Turbine (10) according to any of embodiments 32 to 35, wherein the cover plate (150) has the chamfer (200, 200a) and an inner circumferential radius (R I1 ) has the inner circumferential radius (R I1 ) equal to or greater than a turbine wheel radius (R) T ) is, in particular wherein a ratio of a turbine wheel radius (R T ) to the inner circumferential radius (R I1 ) from 0.75 to 1.00, in particular from 0.80 to 0.98, more specifically from 0.85 to 0.95. 37. Turbine (10) according to any of the embodiments 32 to 36, comprising a clamping means (500), wherein the clamping means (500) is arranged in the axial direction (22) between the guide device (100) and a turbine rear wall (32), in particular wherein the clamping means (500) is designed to clamp the guide device (100) against the turbine housing (30) such that an axial force is introduced into the turbine housing (30) via the axial, disk-shaped extension (154). 38. Turbine (10) according to embodiment 37, characterized in that the clamping means (500) bears against the blade bearing ring (110) at its radially outer end and against the turbine rear wall (32) at its radially inner end. 39. Turbine (10) according to embodiment 37 or embodiment 38, characterized in that a heat shield (600) is clamped between the clamping means (500) and the blade bearing ring (110). 40. Turbine (10) according to any of the embodiments 37 to 39, characterized in that the turbine rear wall (32) is designed as part of a bearing housing (40). 41. Charging device (1) for an internal combustion engine or a fuel cell, comprising: a bearing housing (40), a shaft (70) which is rotatably mounted in the bearing housing (40), a compressor (50) with a compressor wheel (52), and a turbine (10) according to any of embodiments 32 to 40, wherein the turbine wheel (20) and the compressor wheel (52) are coupled to the shaft (70) at opposite ends of the shaft (70) in a rotationally fixed manner. 42. Charging device (1) according to embodiment 42, wherein the compressor (50) comprises a compressor housing (51) in which the compressor wheel (52) is arranged, wherein the bearing housing (40) is connected to the turbine housing (30) and the compressor housing (51). 43. Charging device (1) according to embodiment 41 or embodiment 42, comprising an electric motor which is arranged in a motor compartment in the bearing housing (40), wherein the turbine wheel (20) and / or the compressor wheel (52) is coupled to the electric motor via the shaft (70).

Claims

[1] Guide device (100) for a turbine (10), comprising: a shovel bearing ring (110), a cover plate (150) which is arranged parallel to and spaced in the axial direction (22) from the blade bearing ring (110) by means of spacer elements (160), and a plurality of adjustable guide vanes (120), each rotatable and adjustable guide vanes (120) are mounted in the blade bearing ring (110), wherein the adjustable guide vanes are arranged between the cover plate (150) and the blade bearing ring (110), wherein the adjustable guide vanes (120) between a first guide vane position, in which the guide vanes are minimally open, and a second guide vane position (122) in which the guide vanes are maximally open, are adjustable wherein the respective guide vane position in the operation of the guide device (100) is linked to a corresponding mass throughput through the guide device (100), in particular where the mass throughput is 100% in the second guide vane position, wherein the blade bearing ring (110) and / or the cover plate (150) has a chamfer (200, 200a, 200b) which extends on a side (111, 151) of the blade bearing ring (110) and / or the cover plate (150) facing the adjustable guide vanes from an inner circumference (112, 152) of the blade bearing ring (110) and / or the cover plate (152) in a radial direction (24) to a chamfer outer radius (R) A ) extends, wherein the adjustable guide vanes (120) each have a guide vane trailing edge (123), wherein the guide vane trailing edge (123) is located in the area of ​​the chamfer (200, 200a, 200b) in guide vane positions corresponding to a mass flow range from a first mass flow value to a second mass flow value in radial direction (24), where the first mass throughput value is a maximum of 35%. [2] Guide device (100) according to claim 1, wherein the first mass throughput value is a maximum of 30%, in particular a maximum of 20%, more specifically 10%. [3] Guide device (100) according to claim 1 or claim 2, wherein the second mass throughput value is at least 55%, more specifically at least 65%, in particular 70%. [4] Guide device (100) according to any of the preceding claims, wherein the first mass throughput value is 35% and the second mass throughput value is 55%, or where the first mass throughput value is 30% and the second mass throughput value is 65%, or where the first mass throughput value is 20% and the second mass throughput value is 70%, or where the first mass throughput value is 10% and the second mass throughput value is 70%. [5] Guide device (100) according to any one of the preceding claims, wherein a trailing edge radius (R L ) between the axial direction (22) and the guide vane trailing edge (123), where the trailing edge radius (R) L ) decreases with increasingly opening guide vanes, and wherein the guide vane trailing edge (123) is located in a flow channel in which the cover disk (150) and the blade bearing ring (110) are opposite each other in the axial direction (22) in the guide vane positions corresponding to the mass flow range from the first mass flow value to the second mass flow value. [6] Guide device (100) according to any of the preceding claims, wherein the blade bearing ring (110) and the cover plate (150) define a flow channel in which the adjustable guide vanes (120) are arranged, where the flow channel has a flow channel width (X) S ) exhibits, which is measured in the axial direction (22) between the blade bearing ring (110) and the cover plate (150), where the flow channel width (X) S ) between an outer circumference of the blade bearing ring (110) and / or the cover plate (150) and the chamfer outer radius (R) A ) is constant, and where the flow channel width (X) S ) between the chamfer outer radius (R A ) and the inner circumference (112, 152) of the blade bearing ring (110) and / or the cover plate (150) increases. [7] Guide device (100) according to any one of the preceding claims, wherein the adjustable guide vanes (120) each have a guide vane rotation axis (PA), wherein the chamfer outer radius (R) A ) less than a rotation axis radius (R PA ) is which is measured between the axial direction (22) and the guide vane rotation axis (PA), in particular where the chamfer radius (R) A ) at most 10% less than the radius of the axis of rotation (R) PA ) is. [8] Guide device (100) according to any one of the preceding claims, wherein the cover plate (150) has the chamfer (200a) and wherein the cover plate (150) has an outer radius (R D ) exhibits a ratio of the chamfer outer radius (R) A ) to the outer radius (R D ) from 0.60 to 0.85, in particular from 0.65 to 0.

80. [9] Guide device (100) according to any of the preceding claims, wherein the blade bearing ring (110) and the cover plate (150) have the chamfer (200a, 200b), wherein a chamfer angle (α, β) is measured between the facing side (111, 151) and the chamfer (200, 200a, 200b), wherein a first chamfer angle (α) of the chamfer (200a) of the cover plate (150) is greater than a second chamfer angle (β) of the chamfer (200b) of the blade bearing ring (110), and wherein the first chamfer angle (α) is from 0.5° to 5.0°, more specifically from 1° to 4°, in particular from 2° to 3°. [10] Guide device (100) according to any of the preceding claims, wherein the chamfer (200, 200a, 200b) extends completely circumferentially on the facing side (111, 151). [11] Turbine (10) for a charging device (1), comprising: a turbine housing (30), a turbine wheel (20) which is rotatably arranged in the turbine housing (30), and a guide device (100) according to any of the preceding claims, which is arranged radially outside the turbine wheel (20) in the turbine housing (30) and surrounds the turbine wheel (20) circumferentially. [12] Turbine (10) according to claim 11, wherein the turbine housing (30) has a shoulder (31) for axial and radial support of the cover plate (150), wherein the shoulder (31) has an annular, axial projection (31a) which is arranged radially inside the cover plate (150) and forms a radial surface pairing with an inner circumference (152) of the cover plate (150), and wherein the shoulder (31) has an axial surface (31b) and wherein the cover plate (150) has an axial, disk-shaped extension (154) which is arranged in a radially outer region of the cover plate (150), wherein the axial surface (31b) of the shoulder and the axial, disk-shaped extension (154) form an axial surface pairing. [13] Turbine (10) according to claim 11 or claim 12, wherein the turbine housing (30) has a shoulder (31) for axial and radial support of the cover plate (150), wherein the shoulder (31) has an annular axial projection (31a) with an end face (31c), and wherein the cover plate (150) has the chamfer (200, 200a), wherein the chamfer (200, 200a) is flush with the end face (31c) of the shoulder (31) on the inner circumference (152) of the cover plate (150) in the axial direction (22). [14] Turbine (10) according to any one of claims 11 to 13, wherein the cover plate (150) has the chamfer (200, 200a) and an inner circumferential radius (R I1 ) has, where the inner circumferential radius (R I1 ) equal to or greater than a turbine wheel radius (R) T ) is, in particular where a ratio of the turbine wheel radius (R) T ) to the inner circumferential radius (R I1 ) from 0.75 to 1.00, in particular from 0.80 to 0.98, more specifically from 0.85 to 0.

95. [15] Charging device (1) for an internal combustion engine or a fuel cell, comprising: a bearing housing (40), a shaft (70) which is rotatably mounted in the bearing housing (40), a compressor (50) with a compressor wheel (52), and a turbine (10) according to any one of claims 11 to 14, wherein the turbine wheel (20) and the compressor wheel (52) are coupled to the shaft (70) at opposite ends of the shaft (70) in a rotationally fixed manner.

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