GUIDE BOWL FOR A GUIDE FACILITY

Abstract

Guide vane (200) for a guide device (100), comprising: a guide vane body (201) with a blade top (210), a blade bottom (220), a blade leading edge (230) and a blade trailing edge (240), a profile centerline (250) which is defined in a profile of the guide vane body (201) by the top of the blade (210) and the bottom of the blade (220) and runs between these from the leading edge of the blade (230) to the trailing edge of the blade (240), wherein the profile centerline (250) has an inflection point (TP), wherein the leading edge (230) and the trailing edge (240) of the shovel are connected by a profile chord (260), wherein the guide vane (200) has a guide vane rotation axis (PA), wherein the profile chord (260) forms an intersection point (S1, S2) with the blade leading edge (230) and the blade trailing edge (240), wherein a chord length (C) of the profile chord (260) is measured parallel to the profile chord (260) and between the intersection points (S1, S2), wherein the profile chord (260) defines an X-axis of a coordinate system (X, Y), wherein the X-axis extends along the profile chord (260) and from the leading edge (230) of the blade to the trailing edge (240), and wherein a Y-axis of the coordinate system (X, Y) is defined orthogonally to the X-axis and passes through the intersection (S1) of the profile chord (260) with the leading edge (230), and wherein the axis of rotation (PA) extends from the leading edge (230) towards the trailing edge (240) along the profile chord (260) between the leading edge (230) and the turning point (TP), characterized in that that the axis of rotation (PA) is located along the X-axis at a position that satisfies the condition 0.20 ≤ X PA / C ≤ 0.35 is satisfied and / or that the axis of rotation (PA) is located along the Y-axis at a position that satisfies the condition Y PA ≤ 0 fulfilled, where X PA as the distance between the axis of rotation (PA) and the leading edge of the blade (230) along the X-axis, and where Y PA as the distance between the axis of rotation (PA) and the profile chord (260) along the Y-axis.

Description

Technical field

[0001] The present invention relates to a guide vane for a guide device, in particular for a variable turbine geometry, a variable turbine geometry for a turbine with at least one such guide vane, a turbine for a charging device with such a guide device, a charging device for an internal combustion engine or a fuel cell with such a turbine, and an engine system with such a charging device. 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, primarily 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 electric turbochargers.

[0004] In current developments of internal combustion engines combined with turbocharging systems, it is crucial to achieve high efficiency of the turbine, turbocharger, and / or combustion engine while minimizing emissions, particularly of nitrogen oxides and soot. Conventional internal combustion engines feature multiple cylinders that can be fired sequentially. These cylinders have exhaust ports that can be opened at different times due to the sequential firing. If only one exhaust manifold is used to feed the exhaust gas to the turbine, pressure pulses during exhaust gas expulsion, resulting from the opening of the exhaust valves, can adversely affect those cylinders in a given charge cycle where the exhaust valves are closing – ultimately forcing hot exhaust gas back into these cylinders.This can lead to an increased tendency to knock and / or a reduction in fresh gas charge mass. To reduce or eliminate the aforementioned problems, new turbine housing designs can incorporate two inlet ports with two tongues, spaced circumferentially apart, each supplying fluid (particularly an exhaust gas mass flow) to the turbine wheel. These new turbine housing designs can feature two volutes or spirals, also known as the DualVolute design, or a single volute or spiral, also known as the MonoVolute design. In the DualVolute design, the volute geometry directs fluid to the turbine wheel over a specific circumferential area, reducing fluid mixing upstream of the turbine wheel. In the MonoVolute design, both inlet ports open into the single volute or spiral.Spiral, whereby fluid from both channels can mix upstream of the turbine wheel. Such turbine housings prove particularly advantageous when using the turbocharging device in conjunction with an internal combustion engine (e.g., a gasoline or diesel engine). Each intake channel can be connected to a cylinder bank (i.e., to several cylinders) of the internal combustion engine, thereby increasing the efficiency of both the engine and the turbine. This is because separate supply to the turbine housing reduces interactions between individual cylinders and allows more high pressure pulses to be delivered to the turbine wheel. This improved technique for supplying exhaust gas to the turbine wheel can also be referred to as pulse charging.

[0005] However, in these turbine housings, exhaust gas mass flows can occur between the volutes in conjunction with the respective cylinder groups, leading to an increased pressure level downstream of the respective cylinders during combustion engine operation. Furthermore, these turbine housings can often result in a deteriorated flow to the turbine wheel and thus lower turbine efficiency.

[0006] 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.

[0007] Known guide vanes, such as variable turbine geometries, often have a blade bearing ring with a multitude of adjustable guide vanes mounted in this bearing 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. DE 10 2009 006 209 A1 relates to a loading device with a variable turbine geometry and describes the design of guide vanes in the form of a swallowtail silhouette. The profile of each guide vane has a profile centerline with at least two inflection points. DE 10 2013 225 642 A1 describes a turbine with an adjustable guide vane grid that has a plurality of adjustable guide vanes. Furthermore, US 2015 / 0 104 296 A1 relates to a variable turbine geometry that also has a plurality of adjustable guide vanes.

[0008] The adjustable guide vanes are typically coupled to an adjusting ring via adjusting levers. This adjusting ring is arranged coaxially with the blade bearing ring. 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. Specifically, the actuating device is designed to generate control movements via the adjusting ring, which are then transmitted to the guide vanes. The actuating device usually includes an actuator that is coupled to the adjusting ring via an actuating shaft. The mechanical coupling of the actuating device to the adjusting ring is often achieved by an engagement of an internal lever with an actuating pin on the adjusting ring.

[0009] The large number of moving parts of the guide system, especially the variable turbine geometry, often requires complex and costly assembly and can lead to wear problems during operation.

[0010] Wear problems can frequently occur on the adjusting ring and the adjusting levers due to the interaction of the components during adjustment, as well as due to pulsating exhaust gas forces and their transmission via the guide vanes and the vane levers to the point of engagement. This can lead to damage to the adjusting ring and the adjusting levers, as well as a reduced service life of the guide device (e.g., the variable turbine geometry) or the turbine and / or turbocharging unit in which the guide device is used. The new turbine housing concepts described above can result in higher pulsation forces and excitations from the fluid flow being transmitted to the components of the guide device.In particular, the excitations and pulsation forces are absorbed by the guide vanes and transferred, for example, to the contact points between the vane lever and the adjusting ring. This can lead to increased wear between these components and thus to reduced service life. If the components are designed to be more robust, this often results in a larger required installation space, greater actuation forces (for adjusting the adjusting ring and thus the guide vanes), and consequently, larger dimensions for the actuating devices. This can also lead to higher costs and greater weight. Finding a satisfactory compromise between wear reduction and component sizing is a challenge.

[0011] The object of the present invention is to provide an improved guide vane for a guide device, in particular a variable turbine geometry, and in particular to provide an improved guide vane which can reduce the wear of other components of a guide device. Summary of the invention

[0012] The present invention relates to a guide vane for a guide device, in particular a variable turbine geometry, according to claim 1. The invention further relates to a guide device, in particular a variable turbine geometry, for a turbine according to claim 11, comprising such a guide vane. The invention further relates to a turbine for a charging device according to claim 13, 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 14, comprising such a turbine, and to a motor system according to claim 15, comprising such a charging device. The dependent claims describe advantageous embodiments of the guide vane, the guide device, the turbine, the charging device, and the motor system.

[0013] According to a first aspect of the present invention, a guide vane for a guide device, in particular for a variable turbine geometry, comprises a guide vane body with a blade top, a blade bottom, a blade leading edge, and a blade trailing edge. The guide vane further comprises a profile centerline, which is defined in a profile of the guide vane body by the blade top and the blade bottom and extends between them from the blade leading edge to the blade trailing edge. The profile centerline has an inflection point. A profile chord connects the blade leading edge and the blade trailing edge. The profile chord intersects the blade leading edge and the blade trailing edge at points. The profile chord defines an X-axis of a coordinate system, the X-axis extending along the profile chord from the blade leading edge to the blade trailing edge.The Y-axis of the coordinate system is defined orthogonally to the X-axis and runs through the intersection of the airfoil chord with the leading edge of the blade. A chord length of the airfoil chord is measured parallel to the airfoil chord and between the respective intersections of the airfoil chord with the leading and trailing edges of the blade. The guide vane has a guide vane rotation axis, which extends from the leading edge of the blade towards the trailing edge along the airfoil chord between the leading edge and the inflection point. The rotation axis is located along the X-axis at a position that satisfies the following condition: 0.20 ≤ X. PA / C ≤ 0.35, where X PA as the distance between the axis of rotation and the leading edge of the blade along the X-axis. Alternatively or additionally, the axis of rotation is located along the Y-axis at a position that satisfies the following condition: Y PA ≤ 0, where YPA as the distance between the axis of rotation and the profile chord along the Y-axis.

[0014] By designing the guide vane with the described arrangement of the guide vane axis of rotation relative to the inflection point of the profile centerline, reduced wear of the VTG components, such as blade levers and an adjusting ring (which are explained in more detail below), can be achieved, while simultaneously minimizing or eliminating the required actuation forces. This allows for a good compromise between the sum of all acting loads, torques, and forces (e.g., forces / impulses from the fluid flow, excitations upstream of a turbine wheel inlet, excitations / impulses between a guide vane and / or in a turbine casing, superposition of forces, flow enthalpy, etc.) on the guide vane and on a guide device, particularly on a variable turbine geometry, while minimizing or eliminating the required actuation forces for the guide device.Tests have shown that the inventive design of the guide vane reduces the absorption of pulsations and / or excitations from the fluid flow, thus resulting in fewer vibrations and / or alternating loads (in particular, alternating moments that can be transmitted to the guide vane by the fluid flow) and less vibration and / or alternating load being transmitted to the other components. The inventive guide vane design allows significantly fewer alternating moments to be transmitted to the guide vanes by the fluid flow during a motor cycle (i.e., fewer alternating moments). In other words, the guide vanes experience mostly or exclusively moments that are directed in one of the opening directions of the guide vanes.The guide vanes experience no or only minimal opposing moments, particularly those directed in the closing direction of the guide vanes, when the vanes are used in a VTG (Variable Turbine Geometry). Furthermore, the inventive design of the guide vane reduces the transmission of vibrations and / or alternating loads between the blade lever and the adjusting ring. The guide vane can be used for both mono-volute concepts (i.e., a turbine housing with only one volute or spiral) and dual-volute concepts (i.e., a turbine housing with two volutes or spirals) and provide the described advantageous effects. In addition, jamming of components of the guide system, particularly of the variable turbine geometry, can be prevented or reduced (especially between the adjusting ring and the blade lever).Kinematic damage to the components and uncontrollability of the applications of the control device at higher operating times and mileage can be prevented or reduced.

[0015] In some configurations, the axis of rotation can be located along the X-axis at a position that satisfies the following condition: 0.21 ≤ X PA / C ≤ 0.32, in particular 0.23 ≤ X PA / C ≤ 0.31.

[0016] In some configurations, the axis of rotation can be located along the Y-axis at a position that satisfies the following condition: -0.005 ≤ Y PA / C ≤ 0, preferably -0.004 ≤ Y PA / C ≤ 0.

[0017] In some configurations, the inflection point along the X-axis can be located at a position that fulfills the following condition: X PA < X TP , preferably 0.35 < X TP / C ≤ 0.6 and especially 0.40 ≤ X TP / C ≤ 0.45, where X TPas the distance between the inflection point and the leading edge of the blade along the X-axis.

[0018] In certain configurations, a distance between the turning point and the axis of rotation along the X-axis can satisfy the following condition: 0.05 ≤ X A / C ≤ 0.25, preferably 0.07 ≤ X A / C ≤ 0.22 and especially 0.09 ≤ X A / C ≤ 0.20, where X A as the distance between the inflection point and the axis of rotation along the X-axis.

[0019] In some configurations, the inflection point along the Y-axis can be located at a position that satisfies the following condition: 0 ≤ Y TP , in particular, 0 ≤ Y TP / C ≤ 0.02, preferably 0.01 ≤ Y TP / C ≤ 0.015, where Y TP as the distance between the inflection point and the profile chord along the Y-axis.

[0020] In some embodiments, the upper and lower surfaces of the blade can be designed such that the profile centerline has a wave-like shape with an inflection point. In particular, the profile centerline can have a first curved section and a second curved section, between which the inflection point is defined.

[0021] In various configurations, the upper and / or lower surface of the blade can have a concave section and a convex section with respect to the chord line. The upper surface of the blade can have a concave section followed by a convex section, extending from the leading edge towards the trailing edge and with respect to the chord line. Alternatively or additionally, the lower surface of the blade can have a convex section followed by a concave section, extending from the leading edge towards the trailing edge and with respect to the chord line.

[0022] In certain configurations, the profile centerline can define a first local extremum between the leading edge of the blade and the inflection point. The profile centerline can define a second local extremum between the inflection point and the trailing edge of the blade. In particular, the first local extremum can be a minimum point. The second local extremum can be a maximum point.

[0023] In some configurations, the first local extremum with respect to the axis of rotation and the inflection point along the X-axis can be located at a position that satisfies the following condition: XE1 <XPA<XTP, where X E1 as the distance between the first local extremum and the leading edge of the blade along the X-axis, and where X TP as the distance between the inflection point and the leading edge of the blade along the X-axis.

[0024] According to a second aspect of the present invention, a guide device, in particular a variable turbine geometry, comprises a blade bearing ring and at least one guide vane according to the first aspect of the present invention. The at least one guide vane is rotatably and adjustably mounted in the blade bearing ring via a blade shaft.

[0025] According to a third 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 second aspect of the present invention, which is arranged radially outside the turbine wheel in the turbine housing and surrounds the turbine wheel circumferentially.

[0026] According to a fourth 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 third aspect of the present invention. The turbine wheel and the compressor wheel are rotationally fixed to the shaft at opposite ends.

[0027] According to a fourth aspect of the present invention, an engine system comprises an internal combustion engine with a plurality of cylinders and a charging device according to the fourth aspect of the present invention. A turbine inlet of the turbine housing is fluidically connected to the plurality of cylinders downstream of the internal combustion engine.

[0028] The guide device, the turbine, the charging device and the motor system 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. 2A shows a cross-sectional view of the turbine; Fig. Figure 2B shows a more detailed cross-sectional view of the turbine. Fig. 2A; Fig. Figure 2C shows a perspective detail view of a guide device, in particular a variable turbine geometry (VTG); Fig. 3A, Fig. Figure 3B shows a perspective view and an exploded view of a guide device with a plurality of guide vanes according to the invention; Fig. Figures 4A to 4C show sectional views of the guide vane according to the present invention; Fig. Figure 5 shows in more detail the course of a profile centerline and the position of a rotation axis of the guide vane. Fig. 4A to 4C; Fig. 6A, Fig. 6B shows a top view and a rear view of the guide vane of the Fig. 4A to 4C; Fig. 7A, Fig. 7B shows a sectional view of the guide system. Fig. 3A (without cover plate and spacer elements) with the guide vanes according to the invention in a fully open position and a fully closed position; Fig. Figure 8 shows a perspective sectional view of a turbine with a guide device, in particular a VTG, and a plurality of guide vanes according to the invention; Fig. Figure 9 shows a schematic representation of an engine system with the turbine made of Fig. 8; Fig. 10A, Fig. Figure 10B shows a diagram in which the moments acting on the respective guide vanes during operation are plotted for conventional guide vanes in comparison to the optimized guide vanes according to the invention. Detailed description

[0029] In the context of this application, the terms axial and axial direction refer to a rotational axis X of the shaft 30 or the turbine wheel 12, the rotational axis of the turbine 10, the guide device 100 and / or the adjusting ring 200. With reference to the figures (see, for example, Fig. In figures 1 to 8, the axial direction is represented by the reference symbol 22. 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.

[0030] 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.

[0031] 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 11 in which a turbine wheel 12 is arranged. The turbine 10 can, in particular, be a radial turbine. The turbine housing 11 comprises a turbine inlet 13, a turbine outlet 14, and a receiving chamber 15, which is arranged between the turbine inlet 13 and the turbine outlet 14 and is fluidically connected to the turbine inlet 13 and the turbine outlet 14. The turbine wheel 12 is arranged in the receiving chamber 15. The turbine inlet 13 comprises at least one feed channel, and the turbine outlet 14 comprises an outlet channel. The turbine wheel 12 is arranged between the at least one feed channel and the outlet channel. As shown in Figure 1, the turbine inlet 13 comprises at least one feed channel and the turbine outlet 14 comprises an outlet channel. The turbine wheel 12 is arranged between the at least one feed channel and the outlet channel. Fig. As shown in Figure 8, the turbine inlet 13 can comprise a first feed channel 13a and a second feed channel 13b, which are spaced apart from each other in the circumferential direction 26. The turbine 10 also comprises a turbine back wall 16, which is coupled to the turbine housing 11 on the bearing housing side. As shown in the Fig. 2A and Fig. As can be seen in Figure 2B, the turbine rear wall 16 can be designed as part of the bearing housing 40. With reference to Fig. The charging device 1 further comprises a shaft 30 with a rotational axis X, which is rotatably coupled to the turbine wheel 12. The shaft 30 is rotatably mounted in the bearing housing 40. The axial direction 22 is defined with respect to the rotational axis X. 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 11. The bearing housing 40 is coupled (or connected) to the compressor housing 51. 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, with at least one, in particular a plurality of, guide vanes 200 according to the invention, which are explained in detail below.

[0032] 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 WG, which is designed to open and close a wastegate of the turbine 10 as needed. The wastegate flap WG can be connected to the actuating device 60 via a lever and / or a control rod.

[0033] In some embodiments, the charging device 1 can further comprise an electric motor (not shown in the figures), which can be arranged in a motor compartment within the bearing housing 40. The turbine wheel 12 and / or the compressor wheel 52 can be coupled to the electric motor via the shaft 30. The electric motor can have a rotor and a stator, in particular wherein the rotor can be arranged on the shaft 30, and wherein the stator surrounds the rotor. Furthermore, a power electronics circuit for controlling the electric motor can be arranged in a receiving compartment within the bearing housing 40. The electric motor can also include a generator mode.

[0034] Fig. 2A and Fig. Figure 2B shows sectional views of the turbine 10 with a guide device 100, in particular a variable turbine geometry. Fig. 3A and Fig. Figure 3B shows a perspective view and an exploded view of a guide device 100 with a plurality of guide vanes 200. The guide device 100, in particular the variable turbine geometry, is designed to modify the flow to the turbine wheel 12. The guide device 100 is arranged radially outside the turbine wheel 12, in particular, the guide device 100 surrounds the turbine wheel 12 completely. The guide device 100 can be provided as a cartridge mounted in the turbine housing 11. In particular, the guide device 100 can be pre-assembled as a cartridge and mounted on the rear wall 16 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.

[0035] As in the Fig. As shown in Figures 2A to 3B and 7A and 7B, the guide device 100, in particular the variable turbine geometry, comprises a blade bearing ring 110. Furthermore, the guide device 100 comprises at least one guide vane 200 according to the present invention (explained in detail below), which is rotatably and adjustably mounted in the blade bearing ring 110 via a blade shaft 270. The guide device can be configured or designated as a variable guide device 100. In particular, the guide device 100, in particular the variable turbine geometry 100, can have a plurality of adjustable guide vanes 200, each guide vane 200 of the plurality of guide vanes 200 being rotatably and adjustably mounted in the blade bearing ring 110 via a blade shaft 270.

[0036] Fig. Figures 4A to 4C show sectional views of a (optimized) guide vane 200 according to the invention for a guide device 100, in particular for a variable turbine geometry 100, cut along a longitudinal direction of a guide vane body 201. Fig. Figure 5 shows in detail the course of a profile centerline 250 and the position of a guide vane rotation axis PA of the guide vane 200. Fig. 4A to 4C. Referring to Fig. In sections 4A to 4C, the guide vane 200 has a guide vane body 201 with a leading edge 230 and a trailing edge 240. The guide vane body 201 also comprises a top surface 210 and a bottom surface 220. The bottom surface 220 is the side that, in the installed state of the guide vane 200, faces the turbine wheel 12 (or the axis of rotation R) (see Fig. 7A to 8). The upper surface of the guide vane 210 is the side which, in the installed state, faces away from the turbine wheel 12 (see Fig. 7A to 8). The guide vane 200 comprises a profile centerline 250, which is defined in a profile of the guide vane body 201 by the top of the blade 210 and the bottom of the blade 220, and runs between these from the leading edge 230 to the trailing edge 240. The profile centerline 250 has an inflection point TP. The leading edge 230 and the trailing edge 240 are connected by a profile chord 260. The guide vane 200 has a guide vane rotation axis PA, with the rotation axis PA extending from the leading edge 230 towards the trailing edge 240 along the profile chord 260 between the leading edge 230 and the inflection point TP. The guide vane rotation axis PA lies from the leading edge 230 towards the trailing edge 240 along the profile chord 260 between the leading edge 230 and the turning point TP.

[0037] By designing the guide vane 200 with the described arrangement of the guide vane rotation axis PA relative to the inflection point TP of the profile centerline, reduced wear of the VTG components, such as the blade lever 140 and the adjusting ring 120 (which are explained in more detail below), can be achieved while simultaneously minimizing or eliminating the required actuation forces. Thus, a good compromise can be reached between the sum of all acting loads, torques, and forces (e.g., forces / impulses from the fluid flow, excitations before turbine wheel entry, excitations / impulses between the inlet guide vane 170 and / or turbine casing 11, superposition of forces, flow enthalpy, etc.) on the guide vane 200 and the guide device 100, while minimizing or eliminating the required actuation forces.Tests have shown that the inventive design of the guide vane 200 reduces the absorption of pulsations and / or excitations from the fluid flow, thus resulting in fewer vibrations and / or alternating loads (in particular, alternating moments that can act on the guide vane 200 due to the fluid flow) and less vibration and / or alternating load is transmitted to the other components. In particular, the inventive design of the guide vane 200 reduces the transmission of vibrations and / or alternating loads between the blade lever 140 and the adjusting ring 120. The guide vane 200 can be used for both monovolute concepts (i.e., a turbine housing with only one volute or spiral) and dualvolute concepts (i.e., a turbine housing with two volutes or spirals).Furthermore, jamming of components of the guide unit 100, in particular the variable turbine geometry, can be prevented or reduced. Kinematic damage to the components and uncontrollability of the applications of the guide unit 100 at higher operating times and performance levels can be prevented or reduced.

[0038] The guide vane design according to the invention allows significantly fewer alternating moments to be transmitted to the guide vanes 200 by the fluid flow during a motor cycle (i.e., fewer alternating moments). In other words, the guide vanes 200 thus experience mostly or exclusively moments that are directed in an opening direction of the guide vanes 200. Referring to Fig. 2C means that the guide vane 200 transmits a moment to the blade lever 140, which acts circumferentially to the "right" on the adjusting ring 120 (whereby this abuts on the right side of the coupling area 130). The guide vanes 200 experience no or only a few opposing moments, in particular those directed in a closing direction of the guide vanes 200, when the vanes are used in a VTG.

[0039] Referring to Fig. 2C means that the guide vane 200 absorbs no or only minimal moments from the fluid flow, which act alternately "left" and "right" on the adjusting ring 120 in the circumferential direction 26, i.e., the vane lever 140 alternately strikes the coupling area 130 on the left and right sides. Alternating moments that contribute to wear can thus be reduced. Of course, a change can still occur when the adjusting ring 120 is actuated to adjust the guide vanes 200, since the respective stops of the vane levers in the coupling area 130 transmit the adjusting forces to the guide vanes 200 to move them between a first position 180 and a second position 190.

[0040] Fig. Figure 10A shows a diagram 700 in which the moments acting on the respective guide vanes during operation are plotted for conventional guide vanes compared to the guide vanes 200 according to the invention. "Operation" means that in this experiment the VTG with the guide vanes 200 according to the invention is in a turbine casing 11 (see Figure 10A). Fig. 8; described in detail below) is arranged and a fluid flow to the guide vanes 200 is provided through supply channels 13a, 13b. The fluid flow consists of exhaust gas, which is supplied to the turbine housing by an internal combustion engine during operation. Fig. Figure 10B specifies a direction of the moments 760 that can act on the respective guide vane. A negative moment (-), which in the illustrated embodiment is directed clockwise, is the standard moment that is to be transmitted to the guide vanes 200 during operation of the VTG, in particular the guide vanes 200, due to the fluid flow. This standard moment is thus intended to act in the opening direction of the guide vanes 200, as described above ("fail safe open"). The positive moment (+) represents an opposite moment that acts in the closed position of the guide vane (in the embodiment shown in Fig. 10B (also counterclockwise). In particular, these alternating moments for the guide vanes (i.e., alternating moments that switch between positive moments (+) and negative moments (-)) can significantly contribute to the wear of the VTG components. In Fig. Figure 10A shows a moment diagram 700 for a test conducted on a VTG with 13 (see numbers 1 to 13) guide vanes. The negative (-) and positive (+) moments 760 acting on these guide vanes during operation are plotted as percentages for the respective guide vanes. A dotted line 740 indicates the 0% line, at which a very small moment (or no moment) acts on the respective guide vane during operation. The dashed line 710 shows the test results for conventional guide vanes. The dash-dotted line 720 shows the test results for a VTG with the (optimized) guide vanes 200 according to the invention. The tests conducted have shown that alternating moments can be reduced or even prevented for all guide vanes by using the (optimized) guide vanes 200 according to the invention (see Fig. 10A: All moments are negative moments (-) or, in the case of guide vane number 5, "zero moments". Thus, all moments act in the opening direction of the respective guide vanes (in the case of guide vane number 5, no moment acts). This results in less wear of the VTG components, for example, with regard to Fig. 2C the adjusting levers 140 in the coupling area 130 do not alternately strike "left" and "right" (especially when no adjustment is made by the adjusting ring). In comparison, tests carried out with conventional guide vanes (see dashed line 710) under the same test conditions (e.g., same operating point and / or guide vane position) have shown that the conventional guide vanes number 1, 5, 6, 7, 8, 11, 12, 13 experience a positive moment (+) (which acts in the closing direction of the respective guide vane), while guide vanes number 2 to 4, 9 and 10 experience a negative moment (-) (which acts in the opening position of the respective guide vane), whereby these alternating moments increase the wear of the VTG components.

[0041] With regard to the Fig. In sections 4A to 5, the profile centerline 250 can also be referred to as the skeleton line or camber line of the guide vane body 201. The upper surface 210 and the lower surface 220 of the blade are designed such that the profile centerline 250 has a wave-like shape with the inflection point TP. Since the profile centerline 250 extends from the leading edge 230 to the trailing edge 240 of the blade between the upper surface 210 and the lower surface 220, its course can depend on the shape or design of the upper surface 210 and the lower surface 220. The guide vane 200 can have a larger radius at the leading edge 230 than at the trailing edge 240. The blade thickness or profile thickness is determined by the upper surface 210 and the lower surface 220 and can be measured orthogonally to the profile centerline 250 between them.The leading edge 230 and trailing edge 240 of the bucket can represent the respective points of intersection of the upper bucket surface 210 and the lower bucket surface 220. The guide vane rotation axis PA is the axis about which the guide vane 200 can rotate when it is mounted in a bucket bearing ring 110 (this is described in detail below).

[0042] The profile chord 260 defines a chord length C, in particular where the profile chord 260 runs as a linear connection between the blade leading edge 230 and the blade trailing edge 240. The terms "profile chord," "chord length," and "profile centerline" or "skeletal line" are common terms used to define profiles and are known to those skilled in the art. The profile chord 260 can form an intersection point S1, S2 with the blade leading edge 230 and the blade trailing edge 240, in particular at which the blade leading edge 230 and the blade trailing edge 240 each have a surface point with a smallest radius. In other words, the point on the blade leading edge 230 used to determine the profile chord 260 can be the surface point with the smallest radius (analogous for the blade trailing edge 240).The profile chord 260 can also pass through a starting point and an end point of the profile centerline 250 at the leading edge 230 and the trailing edge 240 of the blade. The profile centerline 250 represents an imaginary connecting line, starting from the intersection point S1 with the leading edge 230 and ending at the intersection point S2 with the trailing edge 240, between the centers of a plurality of imaginary circles arranged within the blade profile, each tangent to the upper and lower surfaces of the blade.

[0043] As in the Fig. As shown in Figures 4A to 5, the airfoil chord 260 can define an X-axis of a coordinate system X, Y, where the X-axis extends along the airfoil chord 260 and from the leading edge 230 of the blade to the trailing edge 240. A Y-axis of the coordinate system X, Y is defined orthogonal to the X-axis and passes through the intersection point S1 of the airfoil chord 260 with the leading edge 230 of the blade. In particular, the Y-axis is therefore also orthogonal to the airfoil chord 260. The Y-axis has positive values ​​extending from the airfoil chord 260 or X-axis in the direction of the blade top surface 210 or pressure side. As described above, the upper surface of the blade 210 is the side which, in an installed state, faces away from the axis of rotation R, 22 of the guide vane 200 (in particular the variable turbine geometry) or the turbine wheel 12. The Y-axis has negative values ​​extending from the chord line 260 and the X-axis in the direction of the lower surface of the blade 220.The suction side is the side that, in an installed state, faces the axis of rotation R, 22 of the guide vane 200 (especially the variable turbine geometry) or the turbine wheel 12, and is directed radially inwards. More precisely, the chord length C is measured parallel to the airfoil chord 260 and can be measured between the respective intersection points S1, S2 of the airfoil chord 260 with the blade leading edge 230 and the blade trailing edge 240. The chord length C can be measured between the respective intersection points S1, S2 of the airfoil chord 260 and the surface of the blade leading edge 230 and the blade trailing edge 240 at the surface point of the smallest radius in each case. The blade leading edge 230 is located at X=0 and the blade trailing edge 240 is located at X=C.

[0044] Regarding the Fig. 4A to 5, the guide vane rotation axis PA can be located along the X-axis (or profile chord 260) at a position that meets the following condition: 0.20 ≤ X PA / C ≤ 0.35, preferably 0.21 ≤ X PA / C ≤ 0.32 and especially 0.23 ≤ X PA / C ≤ 0.31, where X PA as the distance between the guide vane rotation axis PA and the blade leading edge 230 along the X-axis. In a particularly preferred embodiment, the guide vane rotation axis PA can be located along the X-axis at a position that satisfies the following condition: 0.28 ≤ X PA / C ≤ 0.31.

[0045] Furthermore, the guide vane rotation axis PA can be located along the Y-axis at a position that satisfies the following condition: Y PA ≤ 0, in particular -0.005 ≤ Y PA / C ≤ 0, preferably -0.004 ≤ Y PA / C ≤ 0, where Y PAas the distance between the guide vane rotation axis PA and the profile chord 260 along the Y-axis.

[0046] In particular, the guide vane rotation axis PA can be located along the X-axis and the Y-axis at a position that satisfies the following condition: 0.20 ≤ X PA / C ≤ 0.35 and -0.005 ≤ Y PA / C ≤ 0, in particular 0.23 ≤ X PA / C ≤ 0.31 and -0.004 ≤ Y PA / C ≤ 0, where X PA as defined as the distance between the guide vane rotation axis PA and the blade leading edge 230 along the X-axis, and where Y PA as the distance between the guide vane rotation axis PA and the profile chord 260 along the Y-axis.

[0047] For example, in Fig. As shown in Figure 5, the inflection point TP of the profile centerline 260 along the X-axis can be located at a position that satisfies the following condition: X PA < XTP , preferably 0.35 < X TP / C ≤ 0.6 and especially 0.40 ≤ X TP / C ≤ 0.45, where X TP as the distance between the inflection point TP and the leading edge of the blade 230 along the X-axis. A distance X A The following condition can be satisfied between the inflection point TP and the guide vane rotation axis PA along the X-axis: 0.05 ≤ X A / C ≤ 0.25, preferably 0.07 ≤ X A / C ≤ 0.22 and especially 0.09 ≤ X A / C ≤ 0.20, where X A as the distance between the inflection point TP and the guide vane rotation axis PA along the X-axis. In certain configurations, the following condition can be met: 0.09≤XA / C≤0.14.

[0048] The distance X A results from X A =X TP -X PA In preferred examples, the chord length C can be from 15 mm to 25 mm and a distance X Afrom 2 mm to 4 mm.

[0049] In some configurations, the inflection point TP can be located along the Y-axis at a position that satisfies the following condition: 0 ≤ Y TP , especially 0 ≤ Y TP / C ≤ 0.02, preferably 0.01 ≤ Y TP / C ≤ 0.015, where Y TP as the distance between the inflection point TP and the profile chord 260 along the Y-axis. A distance Y A The following condition can be satisfied between the inflection point TP and the guide vane rotation axis PA along the Y-axis: Y PA < Y TP , in particular 0.005 ≤ Y A / C ≤ 0.02, preferably 0.012 ≤ Y A / C ≤ 0.018, where Y A as the distance between the inflection point TP and the guide vane rotation axis PA along the Y-axis. The distance Y A results from the amount of Y A = Y TP -Y PA. These values ​​for the positions of the guide vane rotation axis PA and the inflection point TP can reduce or avoid the alternating moments described above, and reduce wear of the VTG components by lowering the absorption of pulsations and / or excitations of the guide vane 200 from the fluid flow.

[0050] The upper surface 210 and the lower surface 220 of the blade can be designed such that the profile centerline 250 has a wave shape with the inflection point TP. As briefly described above, the course of the profile centerline 250 depends on the shape or design of the upper surface 210 and the lower surface 220 of the blade, since it extends from the leading edge 230 to the trailing edge 240 of the blade between the upper surface 210 and the lower surface 220. In other words, a description of the course of the profile centerline 250 also allows conclusions to be drawn about the design of the upper surface 210 and / or the lower surface 220 of the blade. The upper surface 210 and / or the lower surface 220 of the blade can have a wave shape. As in the Fig. As shown in Figures 4A to 4C, the upper blade surface 210 and the lower blade surface 220 can each have a wave shape. The upper blade surface 210 and / or the lower blade surface 220 can have a concave section 211a, 221a and a convex section 211b, 221b with respect to the profile chord 260. According to the embodiment shown in the Fig. 4A to 4C, the upper surface of the blade 210 can have a concave section 211a followed by a convex section 211b, extending from the leading edge 230 towards the trailing edge 240 and with respect to the chord line 260. Alternatively or additionally, the lower surface of the blade 220 can have a convex section 221b followed by a concave section 221a, extending from the leading edge 230 towards the trailing edge 240 and with respect to the chord line 260. In other words, the upper surface of the blade 210 and / or the lower surface of the blade 220 can be S-shaped. As can be seen from the Fig. As can be seen from Figure 5, the profile centerline 250 (in particular, the path of the profile centerline 250) can have exactly one inflection point TP between the blade leading edge 210 and the blade trailing edge 220. The profile centerline 250 can have a wave shape with two oppositely curved regions 251a, 251b. The regions 251a, 251b can also be referred to as wave antinodes. In other words, the profile centerline 250 can have an S-shape. The profile centerline 250 can be, according to Figure 5, Fig. 5. The profile has a first curved section 251a and a second curved section 251b, between which the inflection point TP is defined. The profile centerline 250 has a continuous profile. In other words, the profile centerline 250, and in particular its path, is free of kinks. The profile centerline 250 has the values ​​X=0 and Y=0 at the leading edge 230 and the values ​​X=C and Y=0 at the trailing edge 240. In other words, and as already described above, the profile centerline 250 passes through the intersection points S1, S2 (as the starting and ending points) and then connects the imaginary centers of the imaginary circles that are tangent to the upper surface 210 and lower surface 220 of the guide vane body 201, respectively, between the intersection points S1, S2.

[0051] As also in the Fig. As can be seen in Figures 4A to 5, the profile centerline 250 can have negative Y-values ​​between the blade leading edge 230 and a zero crossing N0, where the zero crossing N0 is defined as an intersection between the profile centerline 250 and the profile chord 260 (or X-axis). The profile centerline 250 can have positive Y-values ​​between the zero crossing X0 and the blade trailing edge 240. Starting from the blade leading edge 230, the profile centerline 250 can have the first curved section 251a followed by the second curved section 251b, which is opposite in direction to the first curved section. The inflection point TP lies between the first curved section and the second curved section. The first curved section 251a can have negative Y-values ​​from the blade leading edge 230 to the zero crossing N0. The second curved region 251b can have positive Y values ​​after crossing zero N0 up to the inflection point TP.The second curved area 251b can have positive Y values ​​from the inflection point TP to the trailing edge of the blade 240.

[0052] As in the Fig. As shown in Figures 4A to 5, the profile centerline 250 can define a first local extremum E1 between the blade leading edge 230 and the inflection point TP. The profile centerline 250 can define a second local extremum E2 between the inflection point TP and the blade trailing edge 240. In particular, the first local extremum E1 can be a minimum point and the second local extremum E2 a maximum point. In particular, the first extremum E1 can be a first global extremum and the second extremum E2 can be a second global extremum. The first local extremum can lie between the blade leading edge 230 and the zero crossing N0. The second local extremum E2 can lie between the zero crossing N0 and the blade trailing edge 240.

[0053] Referring to Fig. 4B The first local extremum E1 and the second local extremum E2 can be located along the X-axis at a position that satisfies the following condition: X E1 < X E2 , and / or 0.08 ≤ X E1 / C ≤ 0.17, in particular 0.11 ≤ X E1 / C ≤ 0.14, and / or 0.50 ≤ X E2 / C ≤ 0.80, especially 0.60 ≤ X E2 / C ≤ 0.70, where X E1 as the distance between the first local extremum E1 and the leading edge of the blade 230 along the X-axis, and where X E2 as the distance between the second local extremum E2 and the leading edge of the blade 230 along the X-axis.

[0054] The first local extremum E1 can be located with respect to the guide vane rotation axis PA and the inflection point TP along the X-axis at a position that satisfies the following condition: XE1 <XPA<XTP, where X E1as the distance between the first local extremum E1 and the leading edge of the blade 230 along the X-axis, and where X TP as the distance between the inflection point TP and the blade leading edge 230 along the X-axis. The zero crossing N0 of the profile centerline 250 can be located with respect to the guide vane rotation axis PA and the inflection point TP along the X-axis at a position that satisfies the following condition: XPA <XN0<XTP, where X N0 as the distance between the zero crossing N0 and the blade leading edge 230 along the X-axis, where X PA as the distance between the axis of rotation PA and the leading edge of the blade 230 along the X-axis, and where X TP as the distance between the inflection point TP and the leading edge of the blade 230 along the X-axis.

[0055] The guide vanes 200 are positioned between a first position of 180 (see Fig. 7A), in particular a first end position, and a second position 190 (see Fig. 7B), in particular a second end position, adjustable. Several intermediate positions can be set between the first and second positions 180, 190. The first position 180 corresponds to a maximum open position of the guide device 100, in particular the variable turbine geometry. The second position 190 corresponds to a minimum open position of the guide device 100, in particular the variable turbine geometry. This allows a fluid flow from the turbine inlet 13 to be variably directed through a flow channel (in the receiving chamber), i.e., where the guide vanes 200 are arranged, onto the turbine wheel 12. Nozzle cross-sections (also called intermediate channels) are formed between adjacent guide vanes 200, which are larger or smaller depending on the current position of the guide vanes 200 and accordingly supply the turbine wheel 12, which is 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 to drive a compressor wheel 52, which is mounted on the same shaft 30, via the turbine wheel 12.

[0056] As described above, the chord length C is defined between the leading edge 230 (or the upstream edge) and the trailing edge 240 (or the downstream edge). The chord length C can be understood as the distance of the airfoil chord 260 between the intersection points S1 and S2. The leading edge 230 can be understood as the upstream area of ​​the guide vane 200 at its maximum distance from the guide vane axis of rotation PA. The trailing edge 240 can be understood as the downstream area of ​​the guide vane 200 at its maximum distance from the guide vane axis of rotation PA. In other words, the trailing edge 240 is located downstream of the leading edge 230 when viewed in the flow direction along the guide vane 200. A position of the guide vanes 200 can also be referred to as its position or operating position.This means that every possible position of a guide vane 200 during the operation of the turbine 10 is defined, ranging from the first position 180 at maximum flow / cross-section (i.e., fully open) to the second position 190 at minimum flow / cross-section (i.e., fully open or fully closed). 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 200, 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 200.

[0057] As in the Fig. Figures 2A to 3B, 7A and 7B also show that the guide device 100, in particular the variable turbine geometry 100, comprises an adjusting ring 120. The majority of adjustable guide vanes 200 are adjustable between the first position 180 and the second position 190 by means of a movement of the adjusting ring 120 in circumferential direction 26.

[0058] In particular, the actuating device 60 is operationally coupled to the adjusting ring 120 and designed to move the adjusting ring 120 in the circumferential direction 26. The actuating device 60 is coupled to the adjusting ring 120 via one or more levers and / or a control rod.

[0059] Fig. 6A and Fig. Figure 6B shows a top view and a rear view of the guide vane 200 of the Fig. 4A to 4C. Each guide vane 200 comprises a blade shaft 270, which is rotationally fixed to the guide vane body 201, in particular wherein the blade shaft 270 is designed such that the guide vane 200 can be rotatably mounted in the blade bearing ring 110 of the guide device 100 via the blade shaft 270. A longitudinal axis or axis of rotation of the blade shaft 270 defines the guide vane axis of rotation PA. In other words, the majority of guide vanes 200 are rotatably mounted in the blade bearing ring 110 via a blade shaft 270. The guide vanes 200 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 200 are rotatably mounted in the blade bearing ring 110 via the blade shafts 270, evenly distributed in the circumferential direction 26. The blade shafts 270 extend in the axial direction 22, in particular parallel to the axis of rotation R.Alternatively, the guide vanes 200 are rotationally 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 rotation axis R. An odd number of guide vanes 200 can be provided. More than eight guide vanes, in particular more than ten guide vanes (e.g., 11 guide vanes), preferably more than 12 guide vanes, can be provided. As, for example, in the . Fig. 7A and Fig. As shown in Figure 7B, exactly 13 guide vanes 200 can be provided. In other configurations, an even number of guide vanes 200 can be provided.

[0060] Referring to Fig. 6A and Fig. 6B, the guide vane body 201 can have a first side surface 202, wherein the blade shaft 270 is rotationally fixed to the guide vane body 201 at the first side surface 202. In embodiments, the guide vane 200, in particular the guide vane body 201, can have a disk-shaped stop section 204, which is adjacent to the first side surface 202 and substantially concentric with the blade shaft 270. The stop section 204 can have a (particularly maximum) diameter D P exhibiting a diameter greater than a blade shaft diameter D S and / or a maximum profile thickness of the guide vane body 201. The stop section 204 can have a diameter D P , which is larger than the inner diameter of a through-bore in the blade bearing ring 110, in which the blade shaft 270 can be mounted. Through the stop section 204 with diameter D PAdjacent to the through-hole in the blade bearing ring 110, gap losses can be reduced, as well as deposits in the through-hole, pressure losses, and / or turbulence in the fluid flow. Furthermore, a defined stop of the guide vane body 201 against the blade bearing ring 110 can be provided. The blade shaft 270 and the guide vane body 201 can be formed as a single piece. The blade shaft 270 can have a relief groove 271 adjacent to the first side surface 202. The relief groove 271 is understood to be a circumferential and, in particular, rotationally symmetrical removal of material. The relief groove has a diameter that is smaller than the blade shaft diameter D. S The relief groove allows for a defined bearing position of the guide vane 200 relative to the vane bearing ring 110. As shown in Fig. As shown in Figure 6A, the blade shaft 270 can be a first blade shaft 270a, which is rotationally fixed to the guide vane body 201 at a first side surface 202 of the guide vane body. The guide vane 200 can have a second blade shaft 270b, which is coaxially coupled or connected to the first blade shaft 270a at a second side surface 203 of the guide vane body 201, which is opposite the first side surface 202. The second blade shaft 270b has the same axis of rotation, in particular the guide vane axis of rotation PA, as the first blade shaft 270a. The second blade shaft 270b is designed to rotatably mount the guide vane 200 in a cover plate 150 (described in more detail below) of the guide device 100, in particular the variable turbine geometry, which is arranged opposite the blade bearing ring 110.The cover plate 150 is arranged concentrically to the blade bearing ring and also has the axis of rotation R, 22. The double-sided support of the guide vane 200 allows for more precise mounting, thereby reducing tilting of the guide vane 200 during operation and gap losses. Furthermore, higher absolute pressure levels, forces, and / or moments acting on the guide vane 200 can be controlled. The cover plate 150 can have a blind hole or a through hole designed to accommodate the second blade shaft 270b (ideally, in this configuration, a corresponding hole is provided in the cover plate 150 for each guide vane 200). In various configurations, the majority of adjustable guide vanes 200 can have the first and second blade shafts 270a, 270b. In other configurations, only the two guide vanes 200, which are located in the turbine housing 11, can be connected to a respective feed channel 13a, 13b or 13b respectively.closest to a tongue end 14, 14a, 14b, the first and second blade shafts have 270a, 270b. As in . Fig. As shown in Figure 6A, the guide vane body 201 can have a width with a lateral direction Z which runs orthogonal to the X-axis (or parallel to the axis of rotation PA) between the first side face 202 and the second side face 203. As shown in the figures, the guide vane body 201 can have a constant cross-section in the lateral direction Z between the first side face 202 and the second side face 203. In other embodiments, the cross-section of the guide vane body 201 can vary in the lateral direction Z between the first side face 202 and the second side face 203.

[0061] Each guide vane 200 of the majority of adjustable guide vanes 200 is rotationally fixed to a blade lever 140. Each blade lever 140 is at least partially received in a coupling area 130 of the adjusting ring 120 for adjusting the respective guide vane 200. In other words, the blade levers 140 are operationally coupled to the adjusting ring 120 (see Fig. 2C). When the adjusting ring 120 is rotated circumferentially 26, the guide vanes 200 can be adjusted. As described above, the guide vane bodies 201 are each rotationally fixed to the respective blade shaft 270 at a first end of the blade shaft 270. The blade lever 140 is connected to the blade shaft 270 at a second end of the blade shaft 130 opposite the first end. 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 120. In particular, the axial blade lever section 142 can extend axially, at least partially, into the respective coupling area 130.The axial blade lever section 142 can extend from the radial blade lever section 141 predominantly parallel to the blade shaft 270. As shown in the figures, the blade levers 140 and the guide vanes 200 can be arranged on opposite sides of the blade bearing ring 110.

[0062] Referring to the Fig. 7A and Fig. 7B The guide vane 200 can be arranged in the blade bearing ring 110 such that an angle of attack α of the guide vane 200 lies in a range of 15° ≤ α ≤ 65°, in particular 20° ≤ α ≤ 60°. The guide vane 200 (preferably each guide vane 200 or the majority of guide vanes 200) can have a first angle of attack α1 in the first position 180 (see Fig. 7A). The guide vane 200 (preferably each guide vane 200 of the majority of guide vanes 200) can have a second angle of attack α2 in the second position 190 (see Fig. 7B), in particular wherein the first angle of attack α1 is greater than the second angle of attack α2. In embodiments, the first angle of attack α1 can be from 52° to 65°, in particular from 56° to 60°. In embodiments, the second angle of attack α2 can be from 15° to 30°, in particular from 23° to 27°. The respective angle of attack α, α1, α2, is measured between the profile centerline 260 and a tangent 281 to a pitch circle 280 (with respect to the axis of rotation R, 22) at the leading edge of the blade 230. The respective pitch circle 280 (more specifically 180 in the first position and 190 in the second position) passes through the leading edge of the blade 230, in particular through the intersection point S1. The respective partial circle tangent 281 runs (more specifically in the first position 180 and the second position 190) through the leading edge of the blade 230, in particular through the intersection point S1. In embodiments (in the Figs.(not shown) the majority of guide vanes 200 can also be arranged in the blade bearing ring 110 such that individual guide vanes 200 have different angles of attack in the first position 180 and / or in the second position 190. For example, at least the two guide vanes 200 that are closest to a respective tongue end 14, 14a, 14b of two tongues of the turbine casing 11 can have a larger or smaller angle of attack compared to the other guide vanes 200 in the first position 180 and / or in the second position.

[0063] A first blade trailing edge distance R1 in the first position 180 can be smaller than a second blade trailing edge distance R2 in the second position 190. The first distance R1 and the second distance R2 can each be measured radially between the axial direction 22 and the blade trailing edge 240. The axial direction can correspond to a rotation axis R of the turbine wheel 12. The blade bearing ring 110 can have an inner radius R L exhibit a ratio of the inner radius R L The following condition can be met with respect to the first distance R1 and / or the second distance R2: 0.95 ≤ R L / R1 ≤ 0.995, in particular 0.97 ≤ R L / R1 ≤ 0.99, and / or 0.70 ≤ R L / R2 ≤ 0.80, especially 0.72 ≤ R L / R2 ≤ 0.78.

[0064] A guide vane rotation axis distance R PAThe distance between the axial direction 22 and the guide vane rotation axis PA of a guide vane 200 can be the same for each of the guide vanes. In certain embodiments, the turbine wheel 12 can have a turbine wheel radius R. TR exhibit a ratio of the turbine wheel radius R TR The following condition can be met for the first distance R1: 0.90 ≤ R TR / R1 ≤ 0.98, in particular 0.94 ≤ R TR / R1 ≤ 0.97.

[0065] In certain configurations, a ratio of the turbine wheel radius R can be used. TR The second distance R2 must meet the following condition: 0.65 ≤ R TR / R2 ≤ 0.80, especially 0.70 ≤ R TR / R2 ≤ 0.75.

[0066] As in the Fig. 2A, Fig. 2B, Fig. 3A and Fig. As shown in Figure 3B and as already described above, the guide device 100, in particular the variable turbine geometry 100, can comprise a cover plate 150 which is arranged parallel to the blade bearing ring 110 (as already mentioned above). The plurality of adjustable guide vanes 200 can be arranged between the cover plate 150 and the blade bearing ring 110. The guide device 100 can also comprise a plurality of spacer elements 160 which are arranged in the circumferential direction 26 on the blade bearing ring 110 such that they define an axial distance 161 of the blade bearing ring 110 to the cover plate 150 (see Figure 3B). Fig. 2A). In particular, the plurality of spacer elements 160 can comprise at least three spacer elements 10. In some embodiments, the cover plate 150 may also be omitted, and the plurality of spacer elements 160 can define an axial distance 161 to a section in the turbine housing 11 axially opposite the blade bearing ring 110. The spacer elements 160 ensure a minimum clearance for adjusting the guide vanes 200.

[0067] As in Fig. 2A, Fig. 2B, Fig. 7A and Fig. As indicated in Figure 7B, the guide device 100, in particular the variable turbine geometry, can further comprise a guide vane 170 which circumferentially surrounds the blade bearing ring 110 and / or the plurality of adjustable guide vanes 200. The guide vane 170 can have a plurality of fixed guide vanes 171. The fixed guide vanes 171 can each be arranged between two adjacent adjustable guide vanes 200, in particular within an outer circumference of the guide device 100. The fixed guide vanes 171 are provided with a fixed angle of attack. In other words, the guide vanes 171 are not rotatable or adjustable. The guide vane 170 can also replace the spacer elements 160 and ensure the axial distance 161 between the blade bearing ring 110 and the shroud 150 (or a section of the turbine casing 12).The guide vane 170 provides improved airflow to the guide vanes 200 and / or the turbine wheel 12.

[0068] As described above, the guide device 100, in particular the variable turbine geometry, has an adjusting ring 120 which comprises a disk-shaped body (or ring-shaped body) and in which the majority of coupling areas 130 are formed. The coupling areas 130 are spaced apart in the circumferential direction 26. Each coupling area 130 is designed to at least partially accommodate a blade lever 140 for adjusting a guide vane 120 of a guide device 100. As in the Fig. As shown in Figures 2A to 3A, each blade lever 140 is at least partially engaged in a coupling area 130 for adjusting the respective guide vane 120. In other words, the respective blade levers 140 are engaged with a coupling area 130, so that when the adjusting ring 200 moves, particularly in the circumferential direction 26, this movement can be transmitted to the blade levers 140 and thus to the adjustable guide vanes 200. In particular, a rotation of the adjusting ring 200 in the circumferential direction 26 leads to a rotation of the respective guide vanes 200 about their respective guide vane axis of rotation PA, and in particular to an adjustment of the respective guide vanes 200 between the first position 180 and the second position 190.In the embodiments shown, “partially included” means that the respective blade lever 140 extends into the respective coupling area 220, in particular in the axial direction 22, such that a force transmission between the adjusting ring 200 and the blade levers 140 can take place when the adjusting ring 120 moves in the circumferential direction 26.

[0069] Each coupling area 130 can be fully surrounded by the disk-shaped body (see, for example, Fig. 2C). In other words, each coupling area can be configured as a passage 131 with a circumferential wall 132 in the adjusting ring 120. In particular, the respective coupling area 130 can extend in the adjusting ring 200 in the axial direction 22. If the coupling areas 130 are provided with the circumferential wall 131 (i.e., fully enclosed by the disc-shaped body), the robustness of the adjusting ring 120 can be increased. Furthermore, this allows several functions to be integrated into the adjusting ring 120, such as the circumferential adjustment 26 of the blade levers 140, the provision of a first stop for the first position 180 (see above) and / or a second stop for the second position 190 (see above) for the adjustment of the guide device 100, as well as radial bearing 112 of the adjusting ring 120 in the guide device 100.

[0070] The surrounding wall 132 has lateral wall sections which extend essentially in a radial direction 24. Based on the two lateral wall sections (“left” and “right” in the passage 131 in Fig. 2C) By moving the adjusting ring 120 in the circumferential direction 26 relative to the blade bearing ring 110, the majority of guide vanes 200 can be adjusted. The design of the guide vane 200 according to the invention reduces wear on these two lateral wall sections due to contact between the blade levers and the lateral wall sections. A radially inner wall section of the circumferential wall 131 can provide a first stop for the first position 180. The radially inner wall section can also provide a second stop for the second position 190.More precisely, when the adjusting ring 120 is adjusted circumferentially 26, from a certain adjustment angle (clockwise or counterclockwise), measured with respect to the axis of rotation R between the first position 180 and the second position 190, the respective blade lever 140 can come into contact with the inner wall section in the coupling area 130. Thus, further adjustment in the circumferential direction 26 of the majority of guide vanes 140 can be limited. Furthermore, radial bearing of the adjusting ring 130 can be achieved by the blade levers 140 rolling (particularly on an outer side of the axial blade lever section 142 with respect to the axis of rotation R) on a radially outer wall section of the surrounding wall. In other words, radial rolling bearing can thus be provided between the respective axial blade lever sections 142 and the respective radially outer wall sections.An axial support for the adjusting ring 120 can be provided by the blade bearing ring 110. In particular, the blade bearing ring 110 can have a bearing 112 on one side 111 facing away from the majority of adjustable guide vanes 200 in order to axially support the adjusting ring 120. The adjusting ring 120 can be arranged predominantly radially outside the blade bearing ring 110 (see, for example, Figure 1). Fig. 2C).

[0071] For example, in the Fig. 2A and Fig. As shown in Figure 2B, the turbine 10 can include a clamping element 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 16. The clamping element 500 can be designed to clamp the guide device 100 against the turbine housing 11, in particular in the axial direction 22. The clamping element 500 can be designed as a disc spring. The clamping element 500 has a radially outer end and a radially inner end. The clamping element 500 can bear against the blade bearing ring 110 at its radially outer end and against the turbine rear wall 16 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 the compressor 50.The heat shield 600 can be arranged axially 22 between the turbine wheel 12 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.By means of the spacer elements 160 and / or the guide vane 170, the preload force generated by the clamping device 500 can be axially transferred from the blade bearing ring 110 to the turbine housing 11 or, if present, to the cover plate 150.

[0072] As described above, the guide device 100, in particular the variable turbine geometry, comprises at least one (optimized) guide vane 200 according to the invention, which is rotatably and adjustably mounted in the blade bearing ring 110 via a blade shaft 270. In special embodiments, the guide device 100 can, in addition to the at least one optimized guide vane 200, also have at least one other (or non-optimized) guide vane, for example, at least one fixed guide vane (i.e., a guide vane that is rotationally fixed to the blade bearing ring 110) or at least one guide vane that does not have the features described above. In preferred embodiments, however, the guide device 100 can have a plurality of adjustable (optimized) guide vanes 200, each of the plurality of guide vanes 200 being rotatably and adjustably mounted in the blade bearing ring 110 via a blade shaft 270.In one example, at least two optimized guide vanes 200 can be provided. For instance, only the two guide vanes 200 that are closest to each of the two feed channels 13a, 13b (or tongue ends 14, 14a, 14b of the feed channels) in the turbine housing 11 can be designed as optimized guide vanes 200 according to the present invention. In particularly preferred embodiments, all guide vanes 200 of the guide device 100 are designed according to the present invention (i.e., as optimized guide vanes 200). Although the guide vanes 200 are oriented counterclockwise in all figures (i.e., the respective leading edges of the vanes are oriented counterclockwise), they can, of course, also be oriented clockwise (i.e., the respective leading edges of the vanes are oriented clockwise).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 guide vanes 200 according to the invention are arranged (essentially) 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.

[0073] Fig. Figure 9 shows a schematic view of an engine system 1 with the charging device 2. Fig. 1, which comprises the turbine 10 with the guide device 100, in particular the variable turbine geometry, and the guide vanes 200 according to the invention. The engine system 1 includes an internal combustion engine 3 with a plurality of cylinders. The turbine inlet 13 of the turbine 11 is fluidically connected to the cylinders downstream of the internal combustion engine 3. The plurality of cylinders can form a first cylinder group 4 and a second cylinder group 5. In particular, the first cylinder group 4 can be arranged on a first cylinder bank. The second cylinder group 5 can be arranged on a second cylinder bank. In embodiments, several cylinders can form the first cylinder group 4. In embodiments, several cylinders can form the second cylinder group 5. Even if in Fig. If two cylinders are shown as the first cylinder group 4 (particularly on a first cylinder bank), and two further cylinders are shown as the second cylinder group 5 (particularly on a second cylinder bank), then only one cylinder per cylinder group 4, 5, or cylinder bank may be provided, or more than two cylinders may be provided in each case. In embodiments, the first cylinder group 4 and the second cylinder group 5 may each have a plurality of cylinders, each with a combustion chamber (or combustion chamber). The combustion chamber or combustion chamber is the space adjacent to a piston into which an air-fuel mixture is introduced, ignited, and burned. In embodiments, the first feed channel 13a of the turbine 10 downstream of the internal combustion engine 1 may be fluidically connected to the first cylinder group 4, and the second feed channel 13b downstream of the internal combustion engine 1 may be fluidically connected to the second cylinder group 5.

[0074] The compressor 50 can be arranged upstream of the internal combustion engine 1 and can also be fluidically connected to the first and second cylinder groups 4, 5, in particular to the cylinders. An intercooler can be arranged between the compressor 50 and the internal combustion engine 1 (not shown in the figures). The intercooler can cool the compressed fluid. An exhaust gas purification system 70, in particular a catalyst, can be arranged downstream of the turbine 10. An exhaust gas throttle valve can be provided downstream of the catalyst 70 (not shown). Exhaust gas recirculation can also be provided (also not shown).

[0075] As in Fig. As shown in Figure 9, the engine system 1 can comprise an intake channel 6, which is arranged upstream of the internal combustion engine 3 and is fluidically connected to the respective cylinders (in particular the combustion chambers) to supply fluid, in particular intake air, to the combustion chambers. Furthermore, the engine system 1 can comprise an exhaust channel 7, which is arranged downstream of the internal combustion engine 3 and is connected to the respective cylinders, in particular the combustion chambers, to discharge fluid, in particular exhaust gas, from the cylinders. In particular, the intake air can be ambient air, for example, at atmospheric pressure. The intake channel can have an atmospheric inlet 6a. As shown in Fig.As shown in Figure 9, the exhaust channel 7 can have a first exhaust section 8, which is fluidically connected to the cylinders of the first cylinder group 4. Furthermore, the exhaust channel 7 can have a second exhaust section 9, which is fluidically connected to the cylinders of the second cylinder group 5. In particular, the turbine 10 can be arranged in the exhaust channel 7. The first feed channel 13a can be fluidically connected to the first exhaust section 8. The second feed channel 13b can be fluidically connected to the second exhaust section 9. During operation, fluid, in particular exhaust gas, can be guided to the turbine wheel 12 via at least one guide vane 200, in particular the plurality of guide vanes 200. The compressor 50 can be arranged in the inlet channel 6.

Claims

[1] Guide vane (200) for a guide device (100), comprising: a guide vane body (201) with a blade top (210), a blade bottom (220), a blade leading edge (230) and a blade trailing edge (240), a profile centerline (250) which is defined in a profile of the guide vane body (201) by the top of the blade (210) and the bottom of the blade (220) and runs between these from the leading edge of the blade (230) to the trailing edge of the blade (240), wherein the profile centerline (250) has an inflection point (TP), wherein the leading edge (230) and the trailing edge (240) of the shovel are connected by a profile chord (260), wherein the guide vane (200) has a guide vane rotation axis (PA), wherein the profile chord (260) forms an intersection point (S1, S2) with the blade leading edge (230) and the blade trailing edge (240), wherein a chord length (C) of the profile chord (260) is measured parallel to the profile chord (260) and between the intersection points (S1, S2), wherein the profile chord (260) defines an X-axis of a coordinate system (X, Y), the X-axis extending along the profile chord (260) from the leading edge (230) to the trailing edge (240), and wherein a Y-axis of the coordinate system (X, Y) is defined orthogonal to the X-axis and passes through the intersection (S1) of the profile chord (260) with the leading edge (230), and wherein the axis of rotation (PA) extends from the leading edge (230) towards the trailing edge (240) along the profile chord (260) between the leading edge (230) and the inflection point (TP), characterized by , that that the axis of rotation (PA) is located along the X-axis at a position that satisfies the condition 0.20 ≤ X PA / C ≤ 0.35 is satisfied and / or that the axis of rotation (PA) is located along the Y-axis at a position that satisfies the condition Y PA ≤ 0 fulfilled, where X PA as the distance between the axis of rotation (PA) and the leading edge of the blade (230) along the X-axis, and where Y PA as the distance between the axis of rotation (PA) and the profile chord (260) along the Y-axis. [2] Guide vane (200) according to claim 1, wherein the axis of rotation (PA) is located along the X-axis at a position that satisfies the following condition: 0.21 ≤ X PA / C ≤ 0.32, in particular 0.23 ≤ X PA / C ≤ 0.

31. [3] Guide vane (200) according to claim 1 or claim 2, wherein the axis of rotation (PA) is located along the Y-axis at a position that satisfies the following condition: -0.005 ≤ YPA / C ≤ 0, preferably -0.004 ≤ Y PA / C ≤ 0. [4] Guide vane (200) according to any of the preceding claims, wherein the inflection point (TP) is located along the X-axis at a position which satisfies the following condition: X PA < X TP , preferably 0.35 < X TP / C ≤ 0.6 and especially 0.40 ≤ X TP / C ≤ 0.45, where X TP as the distance between the inflection point (TP) and the leading edge of the blade (230) along the X-axis. [5] Guide vane (200) according to any one of the preceding claims, wherein a distance (X) A ) between the inflection point (TP) and the axis of rotation (PA) along the X-axis the following condition is met: 0.05 ≤ X A / C ≤ 0.25, preferably 0.07 ≤ X A / C ≤ 0.22 and especially 0.09 ≤ X A / C ≤ 0.20, where X Aas the distance between the inflection point (TP) and the axis of rotation (PA) along the X-axis. [6] Guide vane (200) according to any one of claims 3 to 5, wherein the inflection point (TP) along the Y-axis is located at a position that satisfies the following condition: 0 ≤ Y TP , in particular, 0 ≤ Y TP / C ≤ 0.02, preferably 0.01 ≤ Y TP / C ≤ 0.015, where Y TP as the distance between the inflection point (TP) and the profile chord (260) along the Y-axis. [7] Guide vane (200) according to any of the preceding claims, wherein the upper surface of the vane (210) and the lower surface of the vane (220) are designed such that the profile centerline (250) has a wave shape with the inflection point (TP), in particular wherein the profile centerline (250) has a first curved area (251a) and a second curved area (251b) between which the inflection point (TP) is defined. [8] Guide vane (200) according to any of the preceding claims, wherein the top of the vane (210) and / or the bottom of the vane (220) has a concave section (211a, 221a) and a convex section (211b, 221b) with respect to the chord line (260), in particular wherein the top of the vane (210) has a concave section (211a) followed by a convex section (211b) extending from the leading edge (230) towards the trailing edge (240) and with respect to the chord line (260), and / or wherein the bottom of the vane (220) has a convex section (221b) followed by a concave section (221a) extending from the leading edge (230) towards the trailing edge (240) and with respect to the chord line (260). [9] Guide vane (200) according to any of the preceding claims, wherein the profile centerline (250) defines a first local extremum (E1) between the blade leading edge (230) and the inflection point (TP), and wherein the profile centerline (250) defines a second local extremum (E2) between the inflection point (TP) and the blade trailing edge (240), in particular wherein the first local extremum (E1) is a low point and wherein the second local extremum (E2) is a high point. [10] Guide vane (200) according to claim 9, wherein the first local extremum (E1) with respect to the axis of rotation (PA) and the inflection point (TP) along the X-axis is located at a position which satisfies the following condition: X E1 < X PA < X TP , where X E1 as the distance between the first local extremum (E1) and the leading edge of the blade (230) along the X-axis, and where X TPas the distance between the inflection point (TP) and the leading edge of the blade (230) along the X-axis. [11] Control device (100), comprising: a shovel bearing ring (110), and at least one guide vane (200) according to any of the preceding claims, wherein the at least one guide vane (200) is rotatably and adjustably mounted in the blade bearing ring (110) via a blade shaft (270). [12] Guide device (100) according to claim 11, wherein the guide device (100) is a variable turbine geometry. [13] Turbine (10) for a charging device (2), comprising: a turbine casing (11), a turbine wheel (12) which is rotatably arranged in the turbine housing (11), and a guide device (100) according to claim 11 or claim 12, which is arranged radially outside the turbine wheel (12) in the turbine housing (11) and surrounds the turbine wheel (12) circumferentially. [14] Charging device (2) for an internal combustion engine (3) or a fuel cell, comprising: a bearing housing (40), a shaft (30) which is rotatably mounted in the bearing housing (40), a compressor (50) with a compressor wheel (52), and a turbine (10) according to claim 13, wherein the turbine wheel (12) and the compressor wheel (52) are coupled to the shaft (30) at opposite ends of the shaft (30) in a rotationally fixed manner. [15] Engine system (1), comprising: an internal combustion engine (3) with a plurality of cylinders, and a charging device (2) according to claim 14, wherein a turbine inlet (13) of the turbine housing (11) is fluidically connected to the plurality of cylinders downstream of the internal combustion engine (3).

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