Guide vane for guide device

Abstract

The invention relates to a guide vane (200) for a guide device (100), comprising a guide vane body (201) having a vane top side (210), a vane bottom side (220), a vane front edge (230) and a vane rear edge (240). The guide vane (200) further comprises a contour centerline (250) defined in the contour of the guide vane body (201) by the vane top side (210) and the vane bottom side (220) and extending between the vane top side and the vane bottom side from the vane leading edge (230) to the vane trailing edge (240), where the contour centerline (250) has an inflection point (TP). A chord line (260) connects the blade leading edge (230) and the blade trailing edge (240). The guide vane (200) has a guide vane axis of rotation (PA). The axis of rotation (PA), starting from the blade leading edge (230), lies between the blade leading edge (230) and the inflection point (TP) in the direction of the blade trailing edge (240) along the chord line (260).

Description

Technical Field

[0001] The invention relates to a guide vane for a guide device, in particular for a variable turbine geometry, a variable turbine geometry for a turbine having at least one such guide vane, a turbine for a supercharging device having such a guide device, a supercharging device for an internal combustion engine or a fuel cell having such a turbine, and an engine system having such a supercharging device. Background Art

[0002] More and more vehicles of the newer generation are equipped with supercharging in order to meet demand targets and legal requirements. When developing supercharging systems, both individual components and the entire system are optimized with regard to their reliability and efficiency.

[0003] Most known supercharging devices have at least one compressor with a compressor impeller, which is connected to a drive unit via a common shaft. The compressor compresses the fresh air sucked in by the internal combustion engine or the 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 promotes the increase in the power of the internal combustion engine or the fuel cell. The supercharging device can be equipped with different drive units. In the prior art, in particular, electric superchargers (E-Laders) are known, in which the compressor is driven via an electric motor; and turbochargers, in which the compressor is driven via a turbine (especially a radial turbine). Compared with axial turbines (for example, those provided in aircraft engines), in which only axial inflow is generally achieved, in radial turbines, the exhaust gas flow is directed from the spiral turbine inlet to the turbine impeller generally radially and in the case of mixed-flow radial turbines radially (i.e. with at least a smaller axial component). In addition to electric superchargers and turbochargers, combinations of both systems are also described in the prior art, which are also referred to as electric turbochargers (E-Turbo).

[0004] In the current development process of internal combustion engines combined with supercharging devices, it is important to provide high efficiency of turbines, supercharging devices and / or internal combustion engines with low emissions (especially nitrogen oxides and smoke). Known internal combustion engines have multiple cylinders that can be burned in sequence. The cylinders have exhaust channels that can be opened at different times due to the sequential combustion. If only the exhaust manifold is used to supply the exhaust gas to the turbine, the pressure pulses generated by the opening of the exhaust valve when the exhaust gas is discharged may have an adverse effect on the cylinders in which the exhaust valve is in the closing process during the gas exchange and eventually push the hot exhaust gas back into these cylinders. This may lead to an increased tendency to knock and / or a reduction in the fresh gas charge. In order to reduce or eliminate the above-mentioned problems, the new concept of the turbine housing can have two inlet channels with two tongue-shaped pieces, which are circumferentially spaced from each other and supply fluids (especially exhaust mass flow) to the turbine impeller respectively. These new concepts of the turbine housing can have two volutes or spirals (this is also called double volute concept) or a single volute or spiral (this is also called single volute concept). In the double volute concept, the fluid is supplied to the turbine wheel via a specific circumferential area by means of the volute geometry; mixing of the fluid upstream of the turbine wheel is reduced. In the single volute concept, two inlet channels merge into a single volute or spiral, wherein the fluid from the two channels can already mix upstream of the turbine wheel. Such a turbine housing has proven to be advantageous, in particular when the supercharging device is used with an internal combustion engine, such as an Otto engine or a diesel engine. Each inlet channel can be connected to a cylinder group of the internal combustion engine (i.e., a cylinder group with a plurality of cylinders), and thus an increase in the efficiency of the internal combustion engine and the turbine can be achieved, because the mutual influence between the individual cylinders can be reduced by supplying the turbine housing separately and higher pressure pulses can be supplied to the turbine wheel. This improved technology for applying exhaust gas to the turbine wheel can also be referred to as pulse charging. However, in the case of these turbine housings being connected to the corresponding cylinder groups, an exhaust gas mass flow can be caused between the volutes, whereby an increased pressure level can be caused downstream of the individual cylinders during operation of the internal combustion engine. Furthermore, these turbine housings can often lead to poor inflow to the turbine wheel and thus to lower efficiency of the turbine.

[0005] In order to further improve the efficiency of the turbine and adapt it to various operating conditions, modern supercharging equipment is equipped with a power regulating device, by means of which the power generated by the supercharging equipment can be adjusted or changed. Known power regulating devices are, for example, guide devices, such as variable turbine geometry (VTG) or wastegate valve flaps (WG). Guide devices (especially variable turbine geometry) are adjustable guide mechanisms for changing the inflow to the turbine impeller of the turbine. By changing the inflow (such as the flow cross section and the inflow angle), the flow velocity of the exhaust flow supplied to the turbine impeller can be changed in particular, which causes the power of the supercharging equipment to change accordingly. Such systems are also called variable guide vanes, VTG, guide grids or VTG guide grids.

[0006] Known guide devices, such as variable cross-section turbines, usually have a blade bearing ring with a plurality of adjustable guide vanes supported in the blade bearing ring in the form of an annular ring, which can be adjusted from a position substantially tangential to the annular ring to a position close to a radial position or a more radial position. The adjustable guide vanes are in most cases connected to an adjusting ring via an adjusting rod, which is arranged coaxially with the blade bearing ring. By the movement of the adjusting ring, for example, the rotation in the circumferential direction, the guide vanes can be adjusted and the inflow to the turbine impeller can be changed. Here, the rotation of the adjusting ring in the circumferential direction is provided via an actuating device. In particular, the actuating device is arranged to generate a control movement that will be transmitted to the guide device via the adjusting ring. The actuating device usually has an actuator, which is connected to the adjusting ring via an adjusting shaft assembly. In order to mechanically couple the actuating device to the adjusting ring, it is usually proposed to engage the inner rod with the adjusting pin of the adjusting ring. The multiple movable individual components of the guide device, especially the variable cross-section turbine, usually require complex and expensive assembly and may cause wear problems during operation.

[0007] Due to the interaction between the components during adjustment, and also due to the pulsed exhaust force and its transmission to the engagement position via the guide vanes and the vane rod, wear problems may usually occur on the adjustment ring and the adjustment rod. This may lead to damage to the adjustment ring and the adjustment rod, and may lead to a shorter life of the guide device (such as a variable cross-section turbine) or the turbine and / or supercharging device in which the guide device is used. The above-mentioned new concept of the turbine housing may lead to higher pulse forces and excitations caused by the fluid flow being transmitted to the components of the guide device. In particular, the excitation and pulse forces are absorbed by the guide vanes and, for example, are transmitted to the contact point between the vane rod and the adjustment ring, which may lead to greater wear between these components and therefore lower operating power. If the components are designed to be more robust, it may usually lead to a larger required structural space, a larger actuating force (for adjusting the adjustment ring and thus the guide vanes), and therefore a larger size of the actuating device. This may also lead to higher costs and greater weight. It is a challenge to find a satisfactory compromise between wear reduction and component size.

[0008] 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 by which the wear of other components of the guide device can be reduced. Summary of the invention

[0009] The invention relates to a guide vane for a guide device, in particular for a variable-geometry turbine, according to claim 1. The invention also relates to a guide device, in particular for a variable-geometry turbine, for a turbine, according to claim 12, having such a guide vane. The invention also relates to a turbine for a supercharging device, having such a guide device, according to claim 14. The invention also relates to a supercharging device for an internal combustion engine or a fuel cell, having such a turbine, according to claim 15, and an engine system having such a supercharging device, according to claim 16. The dependent claims describe advantageous embodiments of the guide vanes, the guide device, the turbine, the supercharging device and the engine system.

[0010] According to a first aspect of the invention, a guide vane for a guide device, in particular for a variable cross-section turbine, comprises a guide vane body having a blade top side, a blade bottom side, a blade front edge and a blade rear edge. In addition, the guide vane comprises a profile center line, which is defined in the profile of the guide vane body by the blade top side and the blade bottom side and extends from the blade front edge to the blade rear edge between the blade top side and the blade bottom side. The profile center line has an inflection point. A chord line (profile chord) connects the blade front edge and the blade rear edge. The guide vane has a guide vane rotation axis, wherein the rotation axis is located between the blade front edge and the inflection point along the chord line starting from the blade front edge in the direction toward the blade rear edge. By means of the design of the guide vane having the described arrangement of the inflection point of the guide vane rotation axis with respect to the profile center line, it is possible to reduce the wear of VTG components, such as the blade rod and the adjustment ring (which will be explained in detail below), while the required actuation force is not increased or increased very little. Here, a good compromise can be achieved for the sum of all loads, torques and forces acting on the guide vanes and the guide device (especially the variable cross-section turbine) (for example, forces / pulses from the fluid flow, excitations before the turbine wheel inlet, excitations / pulses between the pre-guide grid and the turbine housing or in the turbine housing, superposition of forces, flow enthalpy, etc.), but the actuation force for the guide device is not increased or increased very little. Tests have shown that, by the design of the guide vanes according to the invention, the absorption of pulses and / or excitations from the fluid flow can be reduced, and thus fewer vibrations and / or alternating loads (especially alternating torques that can be transmitted to the guide vanes by the fluid flow) occur, and fewer vibrations and / or alternating loads are transmitted to other components. By the design of the guide vanes according to the invention, the alternating torques transmitted to the guide vanes by the fluid flow during the engine cycle can be significantly less (i.e., less alternating torques). In other words, the guide vanes are therefore mostly subjected to or only subjected to torques directed in the opening direction of the guide vanes. When the vanes are used in a VTG, the guide vanes are not subjected to or only to a small amount of reverse torques (especially torques directed in the closing direction of the guide vanes). Furthermore, due to the design of the guide vanes according to the invention, the vibrations and / or alternating loads transmitted between the blade shaft and the adjusting ring can be reduced. Here, the guide vanes can be used for single-volute concepts (i.e. turbine housings with only one volute or spiral) as well as for double-volute concepts (i.e. turbine housings with two volutes or spirals) and provide the described advantageous effects. Furthermore, it is possible to prevent or reduce the jamming of components of the guide device, in particular of the variable cross-section turbine (in particular between the adjusting ring and the blade shaft). Dynamic damage to components and uncontrollability of the use of the guide device can be prevented or reduced during high operating times and operating powers.

[0011] In a design solution, the chord line may form intersections with the blade front edge and the blade rear edge, respectively. The chord line may define an X-axis of a coordinate system, wherein the X-axis extends along the chord line and extends from the blade front edge to the blade rear edge. The chord length of the chord line may in particular be parallel to the chord line and measured between the respective intersections of the chord line with the blade front edge and the blade rear edge.

[0012] In the design solution, the axis of rotation can be located along the X-axis at a position that satisfies the following conditions:

[0013] 0.20≤X PA / C≤0.35, preferably 0.21≤X PA / C≤0.32, especially

[0014] 0.23≤X PA / C≤0.31,

[0015] Where X PA Defined as the distance between the axis of rotation and the leading edge of the blade along the X-axis.

[0016] In the design solution, the Y axis of the coordinate system can be defined as being orthogonal to the X axis and can extend through the intersection of the chord line and the leading edge of the blade. In particular, the rotation axis can be located along the Y axis at a position that satisfies the following conditions:

[0017] Y PA ≤0, especially -0.005≤Y PA / C≤0, preferably -0.004≤Y PA / C≤0,

[0018] where Y PA Defined as the distance between the axis of rotation and the chord along the Y axis.

[0019] In the design solution, the inflection point can be located along the X-axis at a position that satisfies the following conditions:

[0020] X PA <X TP , preferably 0.35 <X TP / C≤0.6, especially 0.40≤X TP / C≤0.45,

[0021] Where X TP Defined as the distance between the inflection point and the leading edge of the blade along the X-axis.

[0022] In the design, the distance between the inflection point and the rotation axis along the X-axis can meet the following conditions:

[0023] 0.05≤X A / C≤0.25, preferably 0.07≤X A / C≤0.22, especially

[0024] 0.09≤X A / C≤0.20,

[0025] Where X A Defined as the distance along the X-axis between the inflection point and the axis of rotation.

[0026] In the design solution, the inflection point can be located along the Y axis at a position that satisfies the following conditions:

[0027] 0≤Y TP , especially 0≤Y TP / C≤0.02, preferably 0.01≤Y TP / C≤0.015,

[0028] where Y TP Defined as the distance between the inflection point and the chord along the Y axis.

[0029] In a design solution, the blade top side and the blade bottom side can be designed so that the profile center line has a wave shape with an inflection point. The profile center line can especially have a first curved region and a second curved region, and the inflection point is defined between these curved regions.

[0030] In a design solution, the blade top side and / or the blade bottom side can have a concave section and a convex section with respect to the chord line. The blade top side can start from the blade front edge in the direction of the blade rear edge and have a concave section with respect to the chord line followed by a convex section. Alternatively or additionally, the blade bottom side can start from the blade front edge in the direction of the blade rear edge and have a convex section with respect to the chord line followed by a concave section.

[0031] In the design solution, the contour centerline may define a first local extremum between the leading edge of the blade and the inflection point. The contour centerline may define a second local extremum between the inflection point and the trailing edge of the blade. The first local extremum may in particular be a low point. The second local extremum may be a high point.

[0032] In the design solution, the first local extreme value can be located at a position satisfying the following conditions along the X-axis with respect to the rotation axis and the inflection point:

[0033] X E1 <X PA <X TP ,

[0034] Where X E1 is defined as the distance between the first local extremum and the leading edge of the blade along the X axis, and where X TP Defined as the distance between the inflection point and the leading edge of the blade along the X-axis.

[0035] According to a second aspect of the invention, a guide device, in particular a variable geometry turbine, comprises a blade bearing ring and at least one guide vane according to the first aspect of the invention. The at least one guide vane is rotatably and adjustably mounted in the blade bearing ring via a blade shaft.

[0036] According to a third aspect of the present invention, a turbine for a supercharging device includes a turbine housing, a turbine impeller rotatably arranged in the turbine housing, and a guide device according to the second aspect of the present invention, which is arranged in the turbine housing radially outside the turbine impeller and surrounds the turbine impeller in the circumferential direction.

[0037] According to a fourth aspect of the present invention, a supercharging device for an internal combustion engine or a fuel cell comprises: a support housing; a shaft rotatably supported in the support housing; a compressor having a compressor impeller; and a turbine according to the third aspect of the present invention. The turbine impeller and the compressor impeller are non-rotatably coupled to the shaft at opposite ends of the shaft.

[0038] According to a fourth aspect of the present invention, an engine system comprises an internal combustion engine having a plurality of cylinders and a supercharging device according to the fourth aspect of the present invention. A turbine inlet of a turbine housing is in fluid connection with the plurality of cylinders downstream of the internal combustion engine.

[0039] In this regard, the guide device, the turbine, the supercharging device and the engine system according to these aspects of the present invention can provide the above-mentioned advantages and can have the above-mentioned embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 An isometric view showing an exemplary supercharging apparatus having a turbine and a compressor;

[0041] Figure 2A showing a cross-sectional view of a turbine;

[0042] Figure 2B Show Figure 2A A more detailed cross-sectional view of the turbine;

[0043] Figure 2C A perspective detail view of a guide device, in particular a variable turbine geometry (VTG);

[0044] Figure 3A , Figure 3B A perspective view and an exploded view of a guide device having a plurality of guide blades according to the invention are shown;

[0045] FIG. 4A to FIG. 4C A cross-sectional view showing a guide vane according to the invention;

[0046] Figure 5 More accurately show FIG. 4A to FIG. 4C The direction of the center line of the guide blade profile and the position of the axis of rotation;

[0047] Fig. 6A , Figure 6B Show FIG. 4A to FIG. 4C A top view and a rear view of the guide blade;

[0048] Fig. 7A , Figure 7B Show Figure 3A A sectional view of a guide device (without a cover disc and a spacer element) with the guide vanes according to the invention in a fully open position and in a fully closed position;

[0049] Figure 8 A perspective sectional view of a turbine having a guide device, in particular a VTG, and a plurality of guide blades according to the invention;

[0050] Fig. 9 Shown with Figure 8 A schematic diagram of an engine system of a turbine;

[0051] Fig. 10A , Fig. 10B A diagram is shown in which the moments acting on the individual guide blades during operation are plotted in comparison with a conventional guide blade and an optimized guide blade according to the invention. DETAILED DESCRIPTION

[0052] In the context of the present application, the expressions "axial" and "axial direction" relate to the axis of rotation X of the shaft 30 or the turbine wheel 12, to the axis of rotation of the turbine 10, the guide device 100 and / or the adjustment ring 200. Figures 1 to 8 ), the axial direction is indicated by reference numeral 22. A radial direction 24 is associated here with the axial direction 22. Likewise, a peripheral or circumferential direction 26 is associated here with the axial direction 22. Directions 22 and 24 extend orthogonally to one another.

[0053] Figure 1 An exemplary supercharging device 1 is shown. In this case, the supercharging device 1 can be used for an internal combustion engine or a fuel cell and / or can be designed or dimensioned accordingly.

[0054] As in Figure 1 As shown in FIG. 1 , the supercharging device 1 includes a turbine 10, a support housing 40 and a compressor 50. Figure 1As shown, the supercharging device 1 may include an actuating device 60. The supercharging device 1 may be a turbocharger. In the design scheme, the supercharging device 1 may also be designed as an electric turbocharger (not shown in the drawings). The turbine 10 includes a turbine housing 11 in which a turbine impeller 12 is arranged. The turbine 10 may be a radial turbine in particular. The turbine housing 11 includes a turbine inlet 13, a turbine outlet 14 and a receiving space 15, which is arranged between the turbine inlet 13 and the turbine outlet 14 and is in fluid connection with the turbine inlet 13 and the turbine outlet 14. The turbine impeller 12 is arranged in the receiving space 15. The turbine inlet 13 includes at least one supply channel, and the turbine outlet 14 includes a discharge channel. The turbine impeller 12 is arranged between the at least one supply channel and the discharge channel. As shown Figure 8 As shown, the turbine inlet 13 may include a first supply channel 13a and a second supply channel 13b, which are arranged spaced apart from each other in the circumferential direction 26. The turbine 10 also includes a turbine rear wall 16, which is connected to the turbine housing 11 on the bearing housing side. Figure 2A and Figure 2B As can be seen in FIG. 1 , the turbine rear wall 16 can be designed as part of the support housing 40 . Figure 1 The supercharging device 1 further comprises a shaft 30 having an axis of rotation X, which is rotatably coupled to the turbine impeller 12. The shaft 30 is rotatably supported in a support housing 40. Here, the axial direction 22 is defined relative to the axis of rotation X. Figure 1 As shown, the compressor 50 includes a compressor housing 51 in which a compressor impeller 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 impeller 52 is coupled to the shaft 30 at the end of the shaft 30 opposite to the turbine impeller 12 so as to be non-rotatable relative to the shaft 30. Figure 1 It can be seen that the turbine 10 comprises a guide device 100 , in particular a variable turbine geometry, which has at least one, in particular a plurality of, guide blades 200 according to the invention, which will be explained in more detail below.

[0055] In addition to the guide device 100, the turbine 10 may also include a power regulating device (not shown in the drawings) in the form of a wastegate flap WG, which is arranged to be able to close and open the wastegate of the turbine 10 as required. Here, the wastegate flap WG can be connected to the actuating device 60 via a rod and / or a control tie rod.

[0056] In the design solution, the supercharging device 1 can also include an electric motor (not shown in the drawings), which can be arranged in a motor space in the bearing housing 40. Here, the turbine impeller 12 and / or the compressor impeller 52 can be connected to the electric motor via the shaft 30. The electric motor can have a rotor and a stator, in particular, the rotor can be arranged on the shaft 30, and the stator surrounds the rotor. In addition, a power electronic circuit can be arranged in the receiving space in the bearing housing 40 for controlling the electric motor. The electric motor can also include a generator mode.

[0057] Figure 2A and Figure 2B A sectional view of a turbine 10 with a guide device 100 , in particular a variable turbine geometry, is shown. Figure 3A and Figure 3B A perspective view and an exploded view of a guide device 100 with a plurality of guide blades 200 are shown. The guide device 100, in particular a variable cross-section turbine, is provided for changing the inflow to the turbine wheel 12. The guide device 100 is arranged radially outside the turbine wheel 12, in particular wherein the guide device 100 circumferentially surrounds the turbine wheel 12. Here, the guide device 100 can be provided as a scroll device mounted in the turbine housing 11. The guide device 100 can be preassembled as a scroll device and can be mounted on the turbine housing rear wall 16, in particular on the bearing housing 40, via at least three pins evenly spaced apart in the circumferential direction 26.

[0058] like FIG. 2A to FIG. 3B as well as Fig. 7A and Figure 7B As shown, the guide device 100, in particular the variable cross-section turbine 100, comprises a blade bearing ring 110. In addition, the guide device 100 comprises at least one guide vane 200 according to the present invention (to be explained in detail below), which is rotatably and adjustably supported in the blade bearing ring 110 via a blade shaft 270. The guide device can be designed or referred to as a variable guide device 100. The guide device 100, in particular the variable cross-section turbine 100, can in particular have a plurality of adjustable guide vanes 200, wherein each guide vane 200 of the plurality of guide vanes 200 is rotatably and adjustably supported in the blade bearing ring 110 via a blade shaft 270.

[0059] FIG. 4A to FIG. 4C A sectional view in the longitudinal direction of a guide blade body 201 of an (optimized) guide blade 200 according to the invention is shown for a guide device 100 , in particular for a variable geometry turbine 100 . Figure 5 Shown in detail FIG. 4A to FIG. 4C The direction of the contour center line 250 of the guide blade 200 and the position of the guide blade rotation axis PA. FIG. 4A to FIG. 4C, the guide vane 200 has a guide vane body 201, which has a blade front edge 230 or inflow edge and a blade rear edge 240 or outflow edge. The guide vane body 201 also includes a blade top side 210 and a blade bottom side 220. The blade bottom side 220 is the side that faces the turbine impeller 12 (or the rotation axis R) in the installed state of the guide vane 200 (see FIG. 7A to FIG. 8 The blade tip side 210 is the side facing away from the turbine wheel 12 in the installed state of the guide blade 200 (see FIG. 7A to FIG. 8 ). The guide vane 200 comprises a profile centerline 250 which is defined in the profile of the guide vane body 201 by the blade top side 210 and the blade bottom side 220 and extends between the blade top side and the blade bottom side from the blade front edge 230 to the blade rear edge 240. The profile centerline 250 has an inflection point TP. A chord line 260 connects the blade front edge 230 and the blade rear edge 240. The guide vane 200 has a guide vane rotation axis PA, wherein the rotation axis PA is located between the blade front edge 230 and the inflection point TP along the chord line 260 starting from the blade front edge 230 in the direction toward the blade rear edge 240. The guide vane rotation axis PA is located between the blade front edge 230 and the inflection point TP along the chord line 260 starting from the blade front edge 230 in the direction toward the blade rear edge 240.

[0060] By means of the design of the guide vane 200 with the described arrangement of the inflection point TP of the guide vane axis of rotation PA with respect to the profile center line, it is possible to achieve a reduction in the wear of the VTG components, for example the blade shaft 140 (to be explained in detail below) and the adjusting ring 120, while at the same time the required actuation force is not increased or increased only very little. Thus, a good compromise can be achieved for the sum of all loads, torques and forces acting on the guide vane 200 and the guide device 100 (for example, forces / pulses from the fluid flow, excitations before the turbine wheel inlet, excitations / pulses between the pre-guide grid 170 and / or the turbine housing 11, superposition of forces, flow enthalpy, etc.), but the required actuation force is hardly increased. Tests have shown that by means of the design of the guide vane 200 according to the invention, the absorption of impulses and / or excitations from the fluid flow can be reduced, and therefore fewer vibrations and / or alternating loads (in particular alternating torques that can act on the guide vane 200 by the fluid flow) occur, and fewer vibrations and / or alternating loads are transmitted to other components. In particular, by the design of the guide vane 200 according to the invention, the vibrations and / or alternating loads transmitted between the blade shaft 140 and the adjusting ring 120 can be reduced. The guide vane 200 can be used for a single volute concept (i.e. a turbine housing with only one volute or spiral) and a double volute concept (i.e. a turbine housing with two volutes or spirals). In addition, the components of the guide device 100, in particular the variable cross-section turbine, can be prevented or reduced from getting stuck. Dynamic damage to the components and the uncontrollability of the application of the guide device 100 can be prevented or reduced during high operating times and operating powers.

[0061] By means of the guide vane design according to the invention, the alternating torque transmitted to the guide vane 200 by the fluid flow during the engine cycle can be significantly less (i.e. less alternating torque). In other words, the guide vane 200 thus experiences mostly or only a torque directed in the opening direction of the guide vane 200. Figure 2C , which means that the guide vane 200 transmits a torque to the vane shaft 140, which acts on the adjustment ring 120 "to the right" in the circumferential direction (where the vane shaft hits the right side of the coupling area 130). When the vane is used in a VTG, the guide vane 200 is not subject to or is subject to only a small amount of counter torque (in particular a torque directed in the closing direction of the guide vane 200). Figure 2C, which means that the guide vane 200 does not absorb torques or only absorbs small torques due to the fluid flow, which act on the adjustment ring 120 alternately "to the left" and "to the right" in the circumferential direction 26, i.e. the blade rod 140 strikes the left and right sides of the coupling region 130 alternately. As a result, alternating torques that cause wear can be reduced. Of course, when the adjustment ring 120 is actuated to adjust the guide vane 200, a changeover can also occur, because due to the corresponding collision of the blade rod in the coupling region 130, an adjustment force is transmitted to the guide vane 200 to move the guide vane between the first position 180 and the second position 190.

[0062] Fig. 10A A graph 700 is shown in which the torque acting on the individual guide blades during operation is plotted compared with a conventional guide blade and a guide blade 200 according to the invention. "Operation" means that in this experiment, a VTG with a guide blade 200 according to the invention was arranged in a turbine housing 11 (see Figure 8 ; described in detail below), and provides a fluid flow to the guide vanes 200 via the supply channels 13a, 13b. In operation, the fluid flow supplied from the internal combustion engine to the turbine housing forms exhaust gas. Fig. 10B The direction of the torque 760 that can act on the individual guide vanes is indicated. In the illustrated embodiment, the negative torque (-) pointing clockwise is the standard torque that should be transmitted to the guide vanes 200 due to the fluid flow during the operation of the VTG, in particular the guide vanes 200. As described above, this standard torque should therefore act in the direction of opening the guide vanes 200 ("fail safe open"). The positive torque (+) forms a reverse torque that acts in the direction of the closed position of the guide vanes (in Fig. 10B These alternating moments of the guide vanes (i.e. alternating moments that alternate between positive (+) and negative (-) moments) can cause significant wear on VTG components, in particular. Fig. 10A , a torque diagram 700 of an experiment performed on a VTG having 13 (see numbers 1 to 13) guide blades is shown. The negative (-) moments and positive (+) moments acting on these guide blades during operation are plotted as percentages 760 for each guide blade. The dotted line 740 indicates the 0% line, where very small moments (or no moments) act on the individual guide blades during operation. The dashed line 710 indicates the experimental results for conventional guide blades. The dash-dotted line 720 shows the experimental results for a VTG having (optimized) guide blades 200 according to the present invention. The experiments performed have shown that, by means of the (optimized) guide blades 200 according to the present invention, alternating moments can be reduced or alternating moments can be prevented for all guide blades (see Fig. 10A: All torques are negative (-) or "zero torque" in the case of guide vane number 5). Therefore, all torques act in the direction of the opening of the individual guide vanes (no torque acts in the case of guide vane number 5). This results in less wear on the VTG components, because for example Figure 2C , the adjusting rod 140 does not collide alternately "to the left" and "backward" in the coupling area 130 (especially when the adjusting ring is not performing an adjustment). In contrast, experiments performed with conventional guide vanes (see dashed line 710) and under the same experimental conditions (e.g., the same operating point and / or position of the guide vanes) showed that conventional guide vanes No. 1, 5, 6, 7, 8, 11, 12, 13 experience positive moments (+) (i.e., the positive moments act in the closing direction of the respective guide vanes), while guide vanes No. 2 to 4, 9 and 10 experience negative moments (-) (the negative moments act in the opening position of the respective guide vanes), wherein these alternating moments increase the wear of the VTG components.

[0063] Reference FIG. 4A to FIG. 5 , the contour center line 250 can also be referred to as the skeleton line or bending line of the guide blade body 201. The blade top side 210 and the blade bottom side 220 are designed so that the contour center line 250 has a wavy shape with an inflection point TP. Since the contour center line 250 extends between the blade top side 210 and the blade bottom side 220 from the blade front edge 230 toward the blade rear edge 240, the direction of the contour center line can depend on the shape or design of the blade top side 210 and the blade bottom side 220. The radius of the guide blade 200 at the blade front edge 230 can be greater than the radius at the blade rear edge 240. The blade thickness or contour thickness is determined by the blade top side 210 and the blade bottom side 220, and can be measured between the blade top side and the blade bottom side orthogonally to the contour center line 250. The blade front edge 230 and the blade rear edge 240 can be the corresponding intersection points of the blade top side 210 and the blade bottom side 220. The guide vane rotation axis PA is the axis about which the guide vane 200 is rotatable when it is supported in the vane bearing ring 110 (this will be described in detail below).

[0064] The chord line 260 defines a chord length C, in particular wherein the chord line 260 extends as a linear connection between the blade leading edge 230 and the blade trailing edge 240. The terms "chord line", "chord length" and "profile centerline" or "skeleton line" are common terms used to define a profile and are known to a person skilled in the art. The chord line 260 may form intersection points S1, S2 with the blade leading edge 230 and the blade trailing edge 240, respectively, in particular at the intersection points the blade leading edge 230 and the blade trailing edge 240, respectively, having a surface point with the smallest radius. In other words, the point of the blade leading edge 230 used to determine the chord line 260 may be a surface point with the smallest radius (similar content applies to the blade trailing edge 240). Here, the chord line 260 may also extend through the starting point and the end point of the profile centerline 250 on the blade leading edge 230 and the blade trailing edge 240. The contour center line 250 is an imaginary connecting line between the centers of multiple imaginary circles starting from the intersection S1 with the blade front edge 230 to the intersection S2 with the blade rear edge 240. These imaginary circles are arranged inside the blade contour and are tangent to the blade top side and the blade bottom side respectively.

[0065] like FIG. 4A to FIG. 5 As shown, the chord line 260 can define the X-axis of the coordinate system X, Y, wherein the X-axis extends along the chord line 260 and extends from the blade front edge 230 to the blade rear edge 240. The Y-axis of the coordinate system X, Y is defined to be orthogonal to the X-axis and extends through the intersection S1 of the chord line 260 and the blade front edge 230. Therefore, the Y-axis also extends in particular orthogonally to the chord line 260. The Y-axis has a positive value in the direction of the blade top side 210 or the pressure side starting from the chord line 260 or the X-axis. As described above, the blade top side 210 is the side that faces away from the rotation axis R, 22 of the guide device 100 (in particular a variable cross-section turbine) or the turbine impeller 12 in the installed state of the guide vane 200. The Y axis has negative values ​​starting from the chord line 260 or the X axis towards the blade bottom side 220 or the suction side, which is the side that, in the installed state of the guide vane 200, faces the axis of rotation R, 22 of the guide device 100 (in particular a variable geometry turbine) or the turbine wheel 12, in particular points radially inward. More precisely, the chord length C is measured parallel to the chord line 260 and can be measured between the respective intersection points S1, S2 of the chord line 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 chord line 260 with the surface points of the respective minimum radius of the surface of the blade leading edge 230 and the blade trailing edge 240. The blade leading edge 230 is at X=0 and the blade trailing edge 240 is at X=C.

[0066] refer to FIG. 4A to FIG. 5 , the guide vane rotation axis PA may be located along the X-axis (or chord line 260) at a position satisfying the following conditions:

[0067] 0.20≤X PA / C≤0.35, preferably 0.21≤X PA / C≤0.32, especially

[0068] 0.23≤X PA / C≤0.31,

[0069] Where X PA It is defined as the distance between the guide vane rotation axis PA and the blade front edge 230 along the X axis. In a particularly preferred design, the guide vane rotation axis PA can be located along the X axis at a position that satisfies the following conditions: 0.28≤X PA / C≤0.31.

[0070] Furthermore, the guide vane rotation axis PA may be located along the Y axis at a position satisfying the following conditions:

[0071] Y PA ≤0, especially -0.005≤Y PA / C≤0, preferably -0.004≤Y PA / C≤0,

[0072] where Y PA Defined as the distance between the guide vane rotation axis PA and the chord line 260 along the Y-axis.

[0073] 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 conditions:

[0074] 0.20≤X PA / C≤0.35 and -0.005≤Y PA / C≤0,

[0075] Especially 0.23≤X PA / C≤0.31 and -0.004≤Y PA / C≤0,

[0076] Where X PA is defined as the distance between the guide vane rotation axis PA and the vane leading edge 230 along the X axis, and wherein Y PA Defined as the distance between the guide vane rotation axis PA and the chord line 260 along the Y-axis.

[0077] For example, Figure 5 As shown in FIG. 2 , the inflection point TP of the profile centerline 260 may be located along the X-axis at a position satisfying the following conditions:

[0078] X PA <X TP , preferably 0.35 <X TP / C≤0.6, especially 0.40≤X TP / C≤0.45,

[0079] Where X TP It is defined as the distance between the inflection point TP and the blade front edge 230 along the X axis. The distance X between the inflection point TP and the guide vane rotation axis PA along the X axis A The following conditions can be met:

[0080] 0.05≤X A / C≤0.25, preferably 0.07≤X A / C≤0.22, especially

[0081] 0.09≤X A / C≤0.20,

[0082] Where X A It is defined as the distance between the inflection point TP and the guide vane rotation axis PA along the X axis. In the design scheme, the following conditions can be met:

[0083] 0.09≤X A / C≤0.14.

[0084] Spacing X A By X A =X TP -X PA In a preferred example, the chord length C can be 15 mm to 25 mm, and the spacing X A 2mm to 4mm.

[0085] In the design solution, the inflection point TP can be located along the Y axis at a position that satisfies the following conditions:

[0086] 0≤Y TP , especially 0≤Y TP / C≤0.02, preferably 0.01≤Y TP / C≤0.015,

[0087] where Y TP It is defined as the distance between the inflection point TP and the chord line 260 along the Y axis. The distance Y between the inflection point TP and the guide vane rotation axis PA along the Y axis A The following conditions can be met:

[0088] Y PA <Y TP , especially 0.005≤Y A / C≤0.02, preferably 0.012≤Y A / C≤0.018,

[0089] where Y A It is defined as the distance between the inflection point TP and the guide vane rotation axis PA along the Y axis.A From Y A =Y TP -Y PA The values ​​of are obtained. These values ​​of the position of the guide vane rotation axis PA and the inflection point TP can reduce or avoid the above-mentioned alternating torque, and the wear of the VTG components can be reduced by the guide vane 200 absorbing less pulses and / or excitations from the fluid flow.

[0090] The blade top side 210 and the blade bottom side 220 can be designed so that the contour center line 250 has a wavy shape with an inflection point TP. As has been briefly described above, the direction of the contour center line 250 depends on the shape or design of the blade top side 210 and the blade bottom side 220, because the contour center line extends between the blade top side 210 and the blade bottom side 220 from the blade front edge 230 to the blade rear edge 240. In other words, the description of the direction of the contour center line 250 also allows the design of the blade top side 210 and / or the blade bottom side 220 to be inferred. The blade top side 210 and / or the blade bottom side 220 can have a wavy shape. As in FIG. 4A to FIG. 4C As shown in FIG. 2 , the blade top side 210 and the blade bottom side 220 may each have a wave shape. The blade top side 210 and / or the blade bottom side 220 may have concave sections 211a, 221a and convex sections 211b, 221b about the chord line 260. FIG. 4A to FIG. 4C In the design scheme in the embodiment, the blade top side 210 can start from the blade front edge 230 in the direction of the blade rear edge 240 and have a concave section 211a followed by a convex section 211b with respect to the chord line 260. Alternatively or additionally, the blade bottom side 220 can start from the blade front edge 230 in the direction of the blade rear edge 240 and have a convex section 221a followed by a concave section 221b with respect to the chord line 260. In other words, the blade top side 210 and / or the blade bottom side 220 can be designed to be S-shaped. Figure 5 It follows that the contour center line 250 (in particular the direction of the contour center line 250) can have exactly one inflection point TP between the blade front edge 210 and the blade rear edge 220. The contour center line 250 can have a wave shape with two oppositely curved regions 251a, 251b. The regions 251a, 251b can also be referred to as antinodes. In other words, the contour center line 250 can have an S shape. According to Figure 5, the contour center line 250 may have a first bending region 251a and a second bending region 251b, and the inflection point TP is defined between these bending regions. The contour center line 250 has a continuous (or continuous) course. In other words, the contour center line 250, in particular the course of the contour center line 250, is kink-free. The contour center line 250 has values ​​X=0 and Y=0 at the blade leading edge 230, and has values ​​X=C and Y=0 at the blade trailing edge 240. In other words and as already described above, the contour center line 250 extends through the intersection points S1, S2 (as the starting point and the end point) and then connects the imaginary centers of the imaginary circles between the intersection points S1, S2, which are tangent to the blade top side 210 and the blade bottom side 220 in the guide vane body 201, respectively.

[0091] As in FIG. 4A to FIG. 5 As can be seen in FIG, the contour centerline 250 may have a negative Y value between the leading edge 230 of the blade and the zero crossing point N0, wherein the zero crossing point N0 is defined as the intersection between the contour centerline 250 and the chord line 260 (or the X-axis). The contour centerline 250 may have a positive Y value between the zero crossing point X0 and the trailing edge 240 of the blade. Starting from the leading edge 230 of the blade, the contour centerline 250 may have a first curved region 251a, followed by a second curved region 251b that is opposite to the first curved region. The inflection point TP is located between the first curved region and the second curved region. The first curved region 251a may have a negative Y value from the leading edge 230 of the blade to the zero crossing point N0. The second curved region 251b may have a positive Y value after the zero crossing point N0 to the inflection point TP. The second curved region 251b may have a positive Y value from the inflection point TP to the trailing edge 240 of the blade.

[0092] like FIG. 4A to FIG. 5 2. It is shown that the contour centerline 250 can define a first local extreme value E1 between the leading edge 230 of the blade and the inflection point TP. The contour centerline 250 can define a second local extreme value E2 between the inflection point TP and the trailing edge 240 of the blade. In particular, the first local extreme value E1 can be a low point, and the second local extreme value E2 can be a high point in particular. In particular, the first extreme value E1 can be a first global extreme value, and the second extreme value E2 can be a second global extreme value. The first local extreme value can be located between the leading edge 230 of the blade and the zero crossing point N0. The second local extreme value E2 can be located between the zero crossing point N0 and the trailing edge 240 of the blade.

[0093] Reference Figure 4B , the first local extremum E1 and the second local extremum E2 can be located along the X-axis at positions that satisfy the following conditions:

[0094] X E1 <X E2 , and / or

[0095] 0.08≤X E1 / C≤0.17, especially 0.11≤X E1 / C≤0.14, and / or

[0096] 0.50≤X E2 / C≤0.80, especially 0.60≤X E2 / C≤0.70,

[0097] Where X E1 is defined as the distance between the first local extremum E1 and the blade front edge 230 along the X axis, and where X E2 It is defined as the distance between the second local extreme value E2 and the blade leading edge 230 along the X-axis.

[0098] The first local extreme value E1 may be located along the X-axis at a position satisfying the following conditions with respect to the guide vane rotation axis PA and the inflection point TP:

[0099] X E1 <X PA <X TP ,

[0100] Where X E1 is defined as the distance between the first local extremum E1 and the blade front edge 230 along the X axis, and where X TP is defined as the distance between the inflection point TP and the blade leading edge 230 along the X-axis. The zero crossing point N0 of the profile centerline 250 may be located at a position satisfying the following conditions along the X-axis with respect to the guide vane rotation axis PA and the inflection point TP:

[0101] X PA <X N0 <X TP ,

[0102] Where X N0 is defined as the distance between the zero crossing point N0 and the leading edge 230 of the blade along the X axis, where X PA is defined as the distance between the rotation axis PA and the blade leading edge 230 along the X axis, and wherein X TP It is defined as the distance between the inflection point TP and the blade leading edge 230 along the X-axis.

[0103] The guide vane 200 may be in a first position 180 (see Fig. 7A ), especially the first extreme position and the second position 190 (see Figure 7B), in particular the second extreme position. A plurality of intermediate positions can be set between the first position and the second position 180, 190. The first position 180 corresponds to the position of the guide device 100, in particular the variable cross-section turbine, which is opened to the maximum extent. The second position 190 corresponds to the position of the guide device 100, in particular the variable cross-section turbine, which is opened to the minimum extent. Thus, the fluid flow of the turbine inlet 13 can be variably guided to the turbine impeller 12 through the flow channel (i.e., the flow channel in the receiving space in which the guide vanes 200 are arranged). Between adjacent guide vanes 200, nozzle cross sections (also referred to as intermediate channels) are formed, which are larger or smaller depending on the instantaneous position of the guide vanes 200 and correspondingly load the turbine impeller 12 supported on the rotation axis R with more or less fluid (e.g. exhaust gas) of the internal combustion engine or more or less fluid of the fuel cell, so as to drive the compressor impeller 52 arranged on the same shaft 30 via the turbine impeller 12.

[0104] As mentioned above, a chord length C is defined between the blade leading edge 230 (or inflow edge) and the blade trailing edge 240 (or outflow edge). The chord length C can be understood as the distance between the chord line 260 at the intersection points S1, S2. The blade leading edge 230 can be understood as the inflow area of ​​the guide vane 200 that is at the maximum distance from the guide vane rotation axis PA. The blade trailing edge 240 can be understood as the outflow area of ​​the guide vane 200 that is at the maximum distance from the guide vane rotation axis PA. In other words, the blade trailing edge 240 is located downstream of the blade leading edge 230, as seen in the flow direction along the guide vane 200. The position of the guide vane 200 can also be referred to as a positioning or operating position or operating positioning. Therefore, during the operation of the turbine 10, each possible position of the guide vane 200 is between the first position 180 when the flow / flow cross section is maximum (i.e., maximally open) and the second position 190 when the flow / flow cross section is minimum (i.e., minimally open or maximally closed). Each "possible position" can be understood as those positions that can be provided during operation. It is known to a person skilled in the art that the operating position is variably and automatically changed during operation of a turbine 10 with a guide device 100 or a variable turbine section. In order to control the movement or position of the guide vanes 200, an actuating device 60 may be provided as described above, which may be designed in any manner, for example electronically or pneumatically, to name a few minor examples. The actuating device 60 may be an actuator. In Figure 1 In the example, the actuator 60 is pneumatically formed with a control housing (e.g. a pressurized tank) and a push rod mechanism, which transmits the movement of the control housing to the guide device 100 or the guide vane 200 via one or more intermediate elements, in particular via an adjusting shaft assembly.

[0105] As in FIG. 2A to FIG. 3B , Fig. 7A and Figure 7B As shown in , the guide device 100, in particular the variable cross-section turbine 100, comprises an adjustment ring 120. The plurality of adjustable guide vanes 200 can be adjusted between a first position 180 and a second position 190 by means of a movement of the adjustment ring 120 in the circumferential direction 26. The actuating device 60 is in particular operatively coupled to the adjustment ring 120 and is designed to move the adjustment ring 120 in the circumferential direction 26. The actuating device 60 is coupled to the adjustment ring 120 via one or more rods and / or control rods.

[0106] Fig. 6A and Figure 6B Shows FIG. 4A to FIG. 4C 1 and 2 are top views and rear views of guide blades 200. Each guide blade 200 comprises a blade shaft 270, which is non-rotatably connected to the guide blade body 201, and in particular the blade shaft 270 is designed so that the guide blade 200 can be rotatably supported in the blade bearing ring 110 of the guide device 100 via the blade shaft 270. The longitudinal axis or the rotation axis of the blade shaft 270 defines the guide blade rotation axis PA. In other words, each of the plurality of guide blades 200 is rotatably supported in the blade bearing ring 110 via the blade shaft 270. The guide blades 200 are rotatably supported in the blade bearing ring 110 and can be rotated or adjusted via the adjustment ring 120. The adjustable guide blades 200 are rotatably supported in the blade bearing ring 110, in particular, via the blade shaft 270 in a manner uniformly distributed in the circumferential direction 26. The blade shaft 270 here extends in the axial direction 22, in particular parallel to the rotation axis R. Alternatively, the guide vanes 200 are supported in the blade bearing ring 110 so as to rotate along the respective guide vane rotation axis PA, wherein the respective guide vane rotation axis PA extends parallel to the axial direction 22 or the rotation axis R. An odd number of guide vanes 200 may be provided. More than eight guide vanes, in particular more than ten guide vanes (for example 11 guide vanes), preferably more than 12 guide vanes may be provided. For example, in Fig. 7A and Figure 7B , it is shown that exactly 13 guide blades 200 can be provided. In other embodiments, an even number of guide blades 200 can be provided.

[0107] Reference Fig. 6A and Figure 6B, the guide vane body 201 may have a first side surface 202, wherein the blade shaft 270 is connected to the guide vane body 201 on the first side surface 202 so as to be non-rotatable. In a design solution, the guide vane 200, in particular the guide vane body 201, may have a disk-shaped stop section 204, which is adjacent to the first side surface 202 and is substantially concentric with the blade shaft 270. The stop section 204 may have a (in particular maximum) diameter D P , which is larger than the blade shaft diameter D S and / or the maximum profile thickness of the guide vane body 201. The stop section 204 may have a diameter D P , which is larger than the inner diameter of the through hole in the blade bearing ring 110, in which the blade shaft 270 can be supported. P The stop section 204 can reduce the gap losses and can reduce the deposits, pressure losses and / or swirl of the fluid flow in the through hole. In addition, a defined stop between the guide vane body 201 and the blade bearing ring 110 can be provided. The blade shaft 270 and the guide vane body 201 can be designed in one piece. The blade shaft 270 can have an undercut 271 adjacent to the first side surface 202. The undercut 271 should be understood as a circumferential and, in particular, rotationally symmetrical material removal. Here, the undercut has a diameter that is smaller than the blade shaft diameter D S The undercut grooves can provide a defined support of the guide vane 200 relative to the vane bearing ring 110. Fig. 6AAs shown, the blade shaft 270 can be a first blade shaft 270a, which is non-rotatably connected to the guide blade body 201 on the first side 202 of the guide blade body. The guide blade 200 can have a second blade shaft 270b, which is coaxially connected or connected to the guide blade body 201 on the second side 203 of the guide blade body 201, which is opposite to the first side 202. The second blade shaft 270b has the same rotation axis as the first blade shaft 270a, especially the guide blade rotation axis PA. The second blade shaft 270b is designed to rotatably support the guide blade 200 in the guide device 100, especially the cover disk 150 (described in detail below) arranged opposite to the blade bearing ring 110 of the variable cross-section turbine. The cover disk 150 is arranged concentrically with the blade bearing ring and also has a rotation axis R, 22. By supporting the guide vanes 200 on both sides, the guide vanes 200 can be supported in a more defined manner, whereby the tilting and clearance losses of the guide vanes 200 during operation can be reduced. In addition, higher absolute pressure levels, forces and / or moments acting on the guide vanes 200 can be adjusted. The cover disk 150 can have a blind hole or a through hole, which is designed to accommodate the second blade shaft 270b (in this design it makes sense to provide a corresponding hole in the cover disk 150 for each guide vane 200). In one design, the plurality of adjustable guide vanes 200 can have a first blade shaft and a second blade shaft 270a, 270b. In other designs, only the two guide vanes 200 that are closest to the corresponding supply channel 13a, 13b or tongue-shaped piece end 14, 14a, 14b in the turbine housing 11 can have a first blade shaft and a second blade shaft 270a, 270b. As Fig. 6A As shown, the guide vane body 201 may have a width along the width direction Z, which extends orthogonally to the X axis (or parallel to the rotation axis PA) between the first side 202 and the second side 203. As shown in the drawings, the guide vane body 201 may have a constant cross-section between the first side 202 and the second side 203 in the width direction Z. In other designs, the cross-section of the guide vane body 201 may vary between the first side 202 and the second side 203 in the width direction Z.

[0108] Each of the plurality of adjustable guide vanes 200 is connected to a blade rod 140 in a non-rotatable manner. Each blade rod 140 is at least partially received in a coupling region 130 of the adjustment ring 120 for adjusting the corresponding guide vane 200. In other words, the blade rod 140 is operatively coupled to the adjustment ring 120 (see Figure 2C). When the adjusting ring 120 rotates in the circumferential direction 26, the guide vane 200 can be adjusted. As described above, the guide vane body 201 is each connected to the corresponding blade shaft 270 at the first end of the blade shaft 270 so as to be non-rotatable relative to each other. The blade rod 140 is connected to the blade shaft 270 at the second end of the blade shaft 130 opposite to the first end. Each blade rod 140 can have a radial blade rod section 141 extending radially from the blade shaft 130. In addition, each blade rod 140 can have an axial blade rod section 142 extending axially from the radial blade rod section 141 toward the adjusting ring 120. The axial blade rod section 142 can extend at least partially in the axial direction into the corresponding coupling area 130. Here, the axial blade rod section 142 can extend from the radial blade rod section 141 approximately parallel to the blade shaft 270. As shown in the accompanying drawings, the blade rod 140 and the guide vane 200 can be arranged on opposite sides of the blade bearing ring 110.

[0109] Reference Fig. 7A and Figure 7B The guide vane 200 can be arranged in the blade bearing ring 110 so that the inflow angle α of the guide vane 200 is in the range of 15°≤α≤65°, in particular 20°≤α≤60°. The guide vane 200 (preferably each guide vane 200 of the plurality of guide vanes 200) can have a first inflow angle α1 (see Fig. 7A The guide vane 200 (preferably each guide vane 200 of the plurality of guide vanes 200 ) may have a second inflow angle α2 in the second position 190 (see Figure 7B), in particular wherein the first inflow angle α1 is greater than the second inflow angle α2. In a design solution, the first inflow angle α1 can be 52° to 65°, in particular 56° to 60°. In a design solution, the second inflow angle α2 can be 15° to 30°, in particular 23° to 27°. The corresponding inflow angles α, α1, α2 are measured between the contour center line 260 and the tangent 281 on the pitch circle 280 (with respect to the rotation axis R, 22) at the blade front edge 230. Here, the corresponding pitch circle 280 (more specifically at the first position 180 and the second position 190) extends through the blade front edge 230, in particular the intersection S1. . The corresponding pitch circle tangent 281 (more specifically at the first position 180 and the second position 190) extends through the blade front edge 230, in particular the intersection S1. In a design solution (not shown in the drawings), the plurality of guide vanes 200 can also be arranged in the blade bearing ring 110 so that the individual guide vanes 200 have different inflow angles in the first position 180 and / or in the second position 190. For example, at least two guide vanes 200 closest to the respective tongue ends 14, 14a, 14b of the two tongues of the turbine housing 11 can have a larger or smaller deflection angle in the first position 180 and / or in the second position than the other guide vanes 200.

[0110] The first blade trailing edge spacing R1 of the first position 180 may be smaller than the second blade trailing edge spacing R2 of the second position 190. The first spacing R1 and the second spacing R2 may each be measured radially between the axial direction 22 and the blade trailing edge 240. The axial direction may correspond to the rotation axis R of the turbine wheel 12. The blade bearing ring 110 may have an inner radius R L . Inner radius R L The ratio to the first spacing R1 and / or the second spacing R2 may satisfy the following conditions:

[0111] 0.95≤R L / R1≤0.995, especially 0.97≤R L / R1≤0.99, and / or

[0112] 0.70≤R L / R2≤0.80, especially 0.72≤R L / R2≤0.78.

[0113] The guide blade rotation axis distance R between the axial direction 22 and the guide blade rotation axis PA of the guide blade 200 PA The guide blades may be of the same size for each guide blade. In one embodiment, the turbine wheel 12 may have a turbine wheel radius R TR Here, the turbine wheel radius R TRThe ratio to the first spacing R1 can satisfy the following conditions:

[0114] 0.90≤R TR / R1≤0.98, especially 0.94≤R TR / R1≤0.97.

[0115] In the design solution, the turbine impeller radius R TR The ratio with the second spacing R2 can satisfy the following conditions:

[0116] 0.65≤R TR / R2≤0.80, especially 0.70≤R TR / R2≤0.75.

[0117] like Figure 2A , Figure 2B , Figure 3A and Figure 3B As shown and as described above, the guide device 100, in particular the variable geometry turbine 100, can include a cover disk 150, which is arranged parallel to the blade bearing ring 110 (as mentioned above). The plurality of adjustable guide vanes 200 can be arranged between the cover disk 150 and the blade bearing ring 110. The guide device 100 can also include a plurality of spacer elements 160, which are arranged on the blade bearing ring 110 in a distributed manner in the circumferential direction 26, so that the plurality of spacer elements define an axial spacing 161 (see Figure 2A ). The plurality of spacer elements 160 may in particular include at least three spacer elements 10. In a design solution, the cover disk 150 may also be omitted, and the plurality of spacer elements 160 may define an axial spacing 161 from a section of the turbine housing 11 axially opposite to the blade bearing ring 110. The spacer elements 160 may ensure a minimum play for adjusting the guide vanes 200.

[0118] like Figure 2A , Figure 2B , Fig. 7A and Figure 7BIt is pointed out that the guide device 100, in particular the variable cross-section turbine, can also include a pre-guide grid 170, which surrounds the blade bearing ring 110 and / or the plurality of adjustable guide blades 200 in the circumferential direction. The pre-guide grid 170 can have a plurality of fixed pre-guide blades 171. The fixed pre-guide blades 171 can be arranged between two adjacent adjustable guide blades 200, in particular, arranged in the outer circumference of the guide device 100. The fixed pre-guide blades 171 are provided with a fixed deflection angle here. In other words, the pre-guide blades 171 cannot be rotated or adjusted. The pre-guide grid 170 can also replace the spacer element 160 and ensure the axial spacing 161 between the blade bearing ring 110 and the cover disk 150 (or a section of the turbine housing 12). The pre-guide grid 170 can provide a better inflow for the guide blades 200 and / or the turbine impeller 12.

[0119] As already described above, the guide device 100, in particular the variable cross-section turbine, has an adjustment ring 120, which comprises a disk-shaped body (or annular body) and in which a plurality of coupling regions 130 are formed. The coupling regions 130 are spaced apart in the circumferential direction 26. Each coupling region 130 is designed to at least partially receive a blade rod 140 for adjusting the guide blade 120 of the guide device 100. As in Figures 2A to 3A , each blade rod 140 is at least partially received in each case in a coupling region 130 for adjusting the respective guide vane 120. In other words, the respective blade rod 140 is in engagement with each coupling region 130 so that, when the adjusting ring 200 moves, in particular in the circumferential direction 26, this movement can be transmitted to the blade rod 140 and thus to the adjustable guide vane 200. In particular, a rotation of the adjusting ring 200 in the circumferential direction 26 causes the respective guide vane 200 to rotate about its respective guide vane rotation axis PA and, in particular, causes the respective guide vane 200 to be adjusted between the first position 180 and the second position 190. In the illustrated embodiment, “partially received” means that the respective blade rod 140 extends, in particular in the axial direction 22, into the respective coupling region 220 in such a way that a force transmission between the adjusting ring 200 and the blade rod 140 can take place when the adjusting ring 120 moves in the circumferential direction 26.

[0120] Each coupling region 130 may be completely surrounded by a disk-shaped body (see, for example, Figure 2C). In other words, each coupling region can be designed as a channel 131 with a surrounding wall 132 in the adjustment ring 120. The corresponding coupling region 130 can extend in the adjustment ring 200 in particular in the axial direction 22. The robustness of the adjustment ring 120 can be increased if the coupling region 130 is provided with a surrounding wall 131 (i.e. completely surrounded by the disk-shaped body). In addition, a plurality of functions can thereby be integrated into the adjustment ring 120: for example, adjustment of the blade rod 140 in the circumferential direction 26, 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 adjusting the guide device 100, and radial support 112 of the adjustment ring 120 in the guide device 100.

[0121] The surrounding wall 132 has lateral wall sections which extend substantially in the radial direction 24. When the adjustment ring 120 moves in the circumferential direction 26 relative to the blade bearing ring 110, the two lateral wall sections ( Figure 2C The plurality of guide blades 200 are adjusted by adjusting the adjusting ring 120 to the “left side” and “right side” of the central channel 131. It is on these two lateral wall sections that the wear caused by the contact of the blade rod with the lateral wall sections can be reduced by the design of the guide blades 200 according to the invention. The radially inner wall section of the surrounding 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 in the circumferential direction 26, starting from a certain adjustment angle (measured clockwise or counterclockwise relative to the rotation axis R between the first position 180 and the second position 190), the corresponding blade rod 140 may come into contact with the inner wall section in the coupling area 130. Further adjustment of the plurality of guide blades 140 in the circumferential direction 26 can therefore be limited. In addition, by rolling the blade shaft 140 (in particular on the outside of the axial blade shaft section 142 with respect to the rotation axis R), the adjusting ring 130 can be radially supported on a radially outer wall section of the surrounding wall. In other words, a radial rolling support can be provided between the corresponding axial blade shaft section 142 and the corresponding radially outer wall section. The adjusting ring 120 can be axially supported via the blade bearing ring 110. The blade bearing ring 110 can have a support portion 112 on a side 111 facing away from the plurality of adjustable guide blades 200, in particular, to axially support the adjusting ring 120. The adjusting ring 120 can be mainly arranged radially outside the blade bearing ring 110 (see, for example Figure 2C ).

[0122] For example, FIG. 2A to FIG. 2BAs shown, the turbine 10 can include a tensioning device 500, which is arranged between the guide device 100 (especially the blade bearing ring 110) and the turbine rear wall 16 in the axial direction 22. The tensioning device 500 can be designed to tension the guide device 100 on the turbine housing 11 (especially in the axial direction 22). The tensioning device 500 can be designed as a disc spring. The tensioning device 300 has a radial outer end and a radial inner end. The tensioning device 500 can be in contact with the blade bearing ring 110 at its radial outer end and in contact with the turbine rear wall 16 at its radial inner end. In addition, the turbine 10 can include a heat shield 600. The heat shield 600 can reduce the heat transfer from the turbine 10 to the bearing housing 40 and / or to the compressor 50. The heat shield 600 can be arranged between the turbine impeller 12 and the bearing housing 40 in the axial direction 22, especially between the guide device 100 and the bearing housing 40. More particularly, the heat shield 600 can be clamped between the tensioning device 500 and the blade bearing ring 110. The heat shield 600 can be clamped in particular between the blade bearing ring 110 and the radially outer end of the tensioning device 500. The tensioning device 500 can be in indirect contact with the blade bearing ring 110 via the heat shield 600. Here, the tensioning device 500 can form a line contact with the bearing housing 40 and in particular form a surface contact with the heat shield 600 at its radially outer end. However, in an alternative design, the tensioning device 500 can also be in direct contact with the blade bearing ring 110. The preload force generated by the tensioning device 500 can be axially transmitted from the blade bearing ring 110 to the turbine housing 11 or to the cover disk 150 (if it is present) by means of the spacer element 160 and / or the pre-guide grid 170.

[0123] As described above, the guide device 100, in particular the variable geometry turbine, therefore comprises at least one (optimized) guide vane 200 according to the invention, which is rotatably and adjustably supported in the blade bearing ring 110 via a blade shaft 270. In a special design, the guide device 100 can have at least one other (or non-optimized) guide vane in addition to the at least one optimized guide vane 200, for example at least one fixed guide vane (i.e. a guide vane connected to the blade bearing ring 110 in a non-rotatable manner) or at least one guide vane that does not have the above-mentioned features. However, in a preferred design, the guide device 100 can have a plurality of adjustable (optimized) guide vanes 200, wherein each guide vane 200 of the plurality of guide vanes 200 is rotatably and adjustably supported in the blade bearing ring 110 via a blade shaft 270. In the example, at least two optimized guide vanes 200 can be provided. Here, for example, only the two guide vanes 200 closest to the respective one of the two supply channels 13a, 13b (or the tongue-shaped end 14, 14a, 14b of the supply channel) in the turbine housing 11 are designed as optimized guide vanes 200 according to the invention. In a particularly preferred design, all guide vanes 200 of the guide device 100 are designed according to the invention (i.e., designed 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), these guide vanes can naturally also be oriented clockwise (i.e., the respective leading edges of the vanes are oriented clockwise). Although the guide device 100 is designed to be substantially annular and the guide vanes 200 are shown to be spaced apart from each other in the circumferential direction 26, in other designs, the guide device 100 can also be arranged so that the guide vanes 200 according to the invention are (substantially) linearly arranged side by side and spaced apart from each other. In such a design, the other components of the guide device 100 are naturally adapted accordingly.

[0124] Fig. 9 Shows that there is Figure 1 Schematic view of an engine system 1 of a supercharging device 2, which has a turbine 10, which has a guide device 100, in particular a variable-geometry turbine and guide vanes 200 according to the invention. The engine system 1 comprises an internal combustion engine 3 having a plurality of cylinders. A turbine inlet 13 of a turbine 11 is in fluid connection with the cylinders downstream of the internal combustion engine 3. The plurality of cylinders can constitute a first cylinder group 4 and a second cylinder group 5. The first cylinder group 4 can in particular be arranged on a first cylinder row. The second cylinder group 5 can be arranged on a second cylinder row. In a design solution, the first cylinder group 4 can be formed by a plurality of cylinders. In a design solution, the second cylinder group 5 can be formed by a plurality of cylinders. Although in Fig. 9In the figure, two cylinders are shown as the first cylinder group 4 (especially on the first cylinder bank) and two other cylinders are shown as the second cylinder group 5 (especially on the second cylinder bank), but only one cylinder or more than two cylinders can also be provided for each cylinder group 4, 5 or cylinder bank. In the design scheme, the first cylinder group 4 and the second cylinder group 5 can each have a plurality of cylinders, each of which has a combustion chamber (or combustion cavity). The combustion chamber or combustion cavity is a space adjacent to the piston, into which the air-fuel mixture is introduced, ignited and burned. In the design scheme, the first supply channel 13a of the turbine 10 can be in fluid connection with the first cylinder group 4 downstream of the internal combustion engine 1, and the second supply channel 13b can be in fluid connection with the second cylinder group 5 downstream of the internal combustion engine 1.

[0125] The compressor 50 can be arranged upstream of the internal combustion engine 1 and is also in fluid connection with the first cylinder group and the second cylinder group 4, 5 (especially the cylinders). A charge air cooler (not shown in the drawings) can be arranged between the compressor 50 and the internal combustion engine 1. The charge air cooler can cool the compressed fluid. An exhaust gas purification device 70, especially a catalyst, can be arranged downstream of the turbine 10. An exhaust throttle valve (not shown) can be provided downstream of the catalyst 70. In addition, an exhaust gas recirculation device (also not shown) can be provided.

[0126] like Fig. 9 As shown, the engine system 1 may include an inlet channel 6, which is arranged upstream of the internal combustion engine 3 and is in fluid connection with each cylinder (especially the combustion chamber) so as to supply fluid (especially intake air) to the combustion chamber. The engine system 1 may also include an outlet channel 7, which is arranged downstream of the internal combustion engine 3 and is connected with each cylinder (especially the combustion chamber) so as to discharge fluid (especially exhaust gas) from the cylinder. The intake air may be, in particular, ambient air, for example, ambient air at atmospheric pressure. The inlet channel may have an inlet 6a on the atmosphere side. As shown in FIG. Fig. 9 As shown, the exhaust channel 7 can have a first exhaust sub-channel 8, which is in fluid connection with the cylinders of the first cylinder group 4. In addition, the exhaust channel 7 can have a second exhaust sub-channel 9, which is in fluid connection with the cylinders of the second cylinder group 5. The turbine 10 can be arranged in particular in the exhaust channel 7. Here, the first supply channel 13a can be in fluid connection with the first exhaust sub-channel 8. The second supply channel 13b can be in fluid connection with the second exhaust sub-channel 9. During operation, the fluid (especially exhaust gas) can be guided to the turbine impeller 12 via the at least one guide vane 200, especially the plurality of guide vanes 200. The compressor 50 can be arranged in the inlet channel 6.

[0127] Although the present invention has been described above and defined in the appended claims, it should be understood that the invention can alternatively be defined according to the following embodiments:

[0128] 1. A guide blade (200) for a guide device (100), the guide blade comprising:

[0129] A guide blade body (201), the guide blade body having a blade top side (210), a blade bottom side (220), a blade front edge (230) and a blade rear edge (240);

[0130] a profile centerline (250) which is defined in the profile of the guide vane body (201) by the blade top side (210) and the blade bottom side (220) and extends between the blade top side and the blade bottom side from the blade leading edge (230) to the blade trailing edge (240), wherein the profile centerline (250) has an inflection point (TP);

[0131] wherein a chord line (260) connects the leading edge (230) of the blade and the trailing edge (240) of the blade,

[0132] wherein the guide vane (200) has a guide vane rotation axis (PA), and

[0133] The rotation axis (PA) is located between the blade leading edge (230) and the inflection point (TP) along the chord line (260) starting from the blade leading edge (230) in the direction toward the blade trailing edge (240).

[0134] 2. The guide vane (200) according to embodiment 1, wherein the chord line (260) defines a chord length (C), in particular wherein the chord line (260) extends as a linear connection between the blade leading edge (230) and the blade trailing edge (240).

[0135] 3. A guide blade (200) according to embodiment 1 or embodiment 2, wherein the chord line (260) forms intersection points (S1, S2) with the leading edge (230) and the trailing edge (240) of the blade, respectively, and in particular, at the intersection points, the leading edge (230) and the trailing edge (240) of the blade respectively have surface points with the smallest radius.

[0136] 4. A guide blade (200) according to embodiment 2 or embodiment 3, wherein the chord line (260) defines an X-axis of a coordinate system (X, Y), wherein the X-axis extends along the chord line (260) and extends from the blade leading edge (230) toward the blade trailing edge (240), in particular wherein the chord length (C) is parallel to the chord line (260) and is measured between respective intersection points (S1, S2) of the chord line (260) with the blade leading edge (230) and the blade trailing edge (240).

[0137] 5. The guide vane (200) according to embodiment 4, wherein the vane leading edge (230) is located at X=0, and wherein the vane trailing edge (240) is located at X=C.

[0138] 6. The guide vane (200) according to embodiment 4 or embodiment 5, wherein the rotation axis (PA) is located along the X-axis at a position that satisfies the following conditions:

[0139] 0.20≤X PA / C≤0.35, preferably 0.21≤X PA / C≤0.32, especially

[0140] 0.23≤X PA / C≤0.31,

[0141] Where X PA Defined as the distance between the rotation axis (PA) and the leading edge (230) of the blade along the X-axis.

[0142] 7. A guide vane (200) according to any one of embodiments 4 to 6, wherein the Y axis of the coordinate system (X, Y) is defined as being orthogonal to the X axis and extending through the intersection of the chord line (260) and the leading edge (230) of the blade.

[0143] 8. The guide vane (200) according to embodiment 7, wherein the rotation axis (PA) is located along the Y axis at a position that satisfies the following conditions:

[0144] Y PA ≤0, especially -0.005≤Y PA / C≤0, preferably -0.004≤Y PA / C≤0,

[0145] where Y PA Defined as the distance between the rotation axis (PA) and the chord line (260) along the Y-axis.

[0146] 9. The guide vane (200) according to embodiment 7, wherein the rotation axis (PA) is located along the X-axis and the Y-axis at a position satisfying the following conditions:

[0147] 0.20≤X PA / C≤0.35 and -0.005≤Y PA / C≤0,

[0148] Especially 0.23≤X PA / C≤0.31 and -0.004≤Y PA / C≤0,

[0149] Where X PA is defined as the distance between the rotation axis (PA) and the leading edge (230) of the blade along the X-axis, and

[0150] where Y PA Defined as the distance between the rotation axis (PA) and the chord line (260) along the Y-axis.

[0151] 10. The guide vane (200) according to any one of embodiments 4 to 9, wherein the inflection point (TP) is located at a position along the X-axis that satisfies the following conditions:

[0152] X PA <X TP , preferably 0.35 <X TP / C≤0.6, especially 0.40≤X TP / C≤0.45,

[0153] Where X TP Defined as the distance between the inflection point (TP) and the leading edge (230) of the blade along the X-axis.

[0154] 11. The guide vane (200) according to any one of embodiments 4 to 10, wherein the distance (X) between the inflection point (TP) and the rotation axis (PA) along the X-axis is A ) meets the following conditions:

[0155] 0.05≤X A / C≤0.25, preferably 0.07≤X A / C≤0.22, especially

[0156] 0.09≤X A / C≤0.20,

[0157] Where X A Defined as the distance between the inflection point (TP) and the rotation axis (PA) along the X-axis.

[0158] 12. The guide vane (200) according to any one of embodiments 7 to 11, wherein the inflection point (TP) is located along the Y-axis at a position that satisfies the following conditions:

[0159] 0≤Y TP , especially 0≤Y TP / C≤0.02, preferably 0.01≤Y TP / C≤0.015,

[0160] where Y TP Defined as the distance between the inflection point (TP) and the chord line (260) along the Y-axis.

[0161] 13. The guide vane (200) according to any one of embodiments 7 to 12, wherein the distance (Y) between the inflection point (WP) and the rotation axis (PA) along the Y axis is A ) meets the following conditions:

[0162] Y PA <Y TP , especially 0.005≤Y A / C≤0.02, preferably 0.012≤Y A / C≤0.018,

[0163] where Y A Defined as the distance between the inflection point (TP) and the rotation axis (PA) along the Y-axis.

[0164] 14. The guide vane (200) according to any one of the preceding embodiments, wherein the blade top side (210) and the blade bottom side (220) are designed such that the contour center line (250) has a wavy shape with the inflection point (TP).

[0165] 15. The guide vane (200) according to any one of the preceding embodiments, wherein the blade top side (210) and / or the blade bottom side (220) has a wave shape.

[0166] 16. A guide vane (200) according to any one of the preceding embodiments, wherein the blade top side (210) and / or the blade bottom side (220) has a concave section (211a, 221a) and a convex section (211b, 221b) with respect to the chord line (260).

[0167] 17. A guide blade (200) according to embodiment 16, wherein the blade top side (210) has a concave section (211a) followed by a convex section (211b) starting from the blade leading edge (230) in the direction toward the blade trailing edge (240) and with respect to the chord line (260), and / or the blade bottom side (220) has a convex section (221a) followed by a concave section (221b) starting from the blade leading edge (230) in the direction toward the blade trailing edge (240) and with respect to the chord line (260).

[0168] 18. The guide vane (200) according to any one of the preceding embodiments, wherein the profile centerline (250) has exactly one inflection point (TP).

[0169] 19. The guide vane (200) according to any one of the preceding embodiments, wherein the contour center line (250) has a wave shape having two oppositely curved regions (251a, 251b).

[0170] 20. The guide vane (200) according to embodiment 19, wherein the contour centerline (250) has a first bending region (251a) and a second bending region (251b), and the inflection point (TP) is defined between the first bending region and the second bending region.

[0171] 21. A guide blade (200) according to any one of the aforementioned embodiments 7 to 20, wherein the contour center line (250) has values ​​X=0 and Y=0 at the leading edge (230) of the blade, and has values ​​X=C and Y=0 at the trailing edge (240) of the blade, and in particular wherein the contour center line (250) has a kink-free course.

[0172] 22. A guide blade (200) according to any one of the preceding embodiments 7 to 21, wherein the contour centerline (250) has a negative Y value between the leading edge (230) of the blade and a zero crossing point (N0), wherein the zero crossing point (N0) is defined as the intersection between the contour centerline (250) and the chord line (260).

[0173] 23. The guide vane (200) according to embodiment 22, wherein the contour centerline (250) has a positive Y value between the zero crossing point (X0) and the blade trailing edge (240).

[0174] 24. A guide blade (200) according to any one of the preceding embodiments, wherein the contour centerline (250) defines a first local extreme value (E1) between the leading edge (230) of the blade and the inflection point (TP), and wherein the contour centerline (250) defines a second local extreme value (E2) between the inflection point (TP) and the trailing edge (240) of the blade, in particular wherein the first local extreme value (E1) is a low point, and wherein the second local extreme value (E2) is a high point.

[0175] 25. The guide vane (200) according to embodiment 24 dependent on embodiments 2 and 4, wherein the first local extremum (E1) and the second local extremum (E2) are located along the X-axis at positions satisfying the following conditions:

[0176] X E1 <X E2 , and / or

[0177] 0.08≤X E1 / C≤0.17, especially 0.11≤X E1 / C≤0.14, and / or

[0178] 0.50≤X E2 / C≤0.80, especially 0.60≤X E2 / C≤0.70,

[0179] Where X E1 is defined as the distance between the first local extremum (E1) and the leading edge (230) of the blade along the X-axis, and wherein X E2 is defined as the distance between the second local extremum (E2) and the leading edge (230) of the blade along the X-axis.

[0180] 26. The guide vane (200) according to embodiment 24 or embodiment 25 dependent on embodiment 4, wherein the first local extremum (E1) is located at a position along the X-axis with respect to the rotation axis (PA) and the inflection point (TP) that satisfies the following conditions:

[0181] X E1 <X PA <X TP ,

[0182] Where X E1 is defined as the distance between the first local extremum (E1) and the leading edge (230) of the blade along the X-axis, and

[0183] Where X TP Defined as the distance between the inflection point (TP) and the leading edge (230) of the blade along the X-axis.

[0184] 27. The guide vane (200) according to any one of embodiments 22 to 26 depending on embodiment 4, wherein the zero crossing point (N0) of the profile centerline (250) is located at a position along the X-axis with respect to the rotation axis (PA) and the inflection point (TP) that satisfies the following conditions:

[0185] X PA <X N0 <X TP ,

[0186] Where X N0 is defined as the distance between the zero crossing point (N0) and the leading edge (230) of the blade along the X-axis,

[0187] Where X PA is defined as the distance between the rotation axis (PA) and the leading edge (230) of the blade along the X-axis, and

[0188] Where X TP Defined as the distance between the inflection point (TP) and the leading edge (230) of the blade along the X-axis.

[0189] 28. The guide vane (200) according to any one of the preceding embodiments, wherein an inflow angle (α) of the guide vane (200) is in the range of 15°≤α≤65°.

[0190] 29. A guide vane (200) according to any one of the aforementioned embodiments, wherein the guide vane (200) has a blade shaft (270), which is non-rotatably connected to the guide vane body (201), and in particular wherein the blade shaft (270) is designed so that the guide vane (200) can be rotatably supported in a guide device (100), in particular a blade bearing ring (110) of a variable cross-section turbine, via the blade shaft (270).

[0191] 30. The guide blade (200) according to embodiment 29, wherein the guide blade body (201) has a first side surface (202), and the blade shaft (270) is non-rotatably connected to the guide blade body (201) on the first side surface (202).

[0192] 31. The guide vane (200) according to embodiment 30, wherein the guide vane body (201) has a disc-shaped stop section (204), which is adjacent to the first side surface (202) and is formed substantially concentrically with the vane shaft (270).

[0193] 32. The guide vane according to embodiment 31, wherein the stop section (204) has a diameter (D P ) is larger than the blade shaft diameter (D S ) and / or the maximum profile thickness of the guide blade body (201).

[0194] 33. The guide vane (200) according to any one of embodiments 30 to 32, wherein the vane shaft (270) has a relief groove (271) adjacent to the first side surface (202).

[0195] 34. A guide blade (200) according to any one of embodiments 29 to 33, wherein the blade shaft (270) is a first blade shaft (270a), which is non-rotatably connected to the guide blade body (201) on a first side surface (202) of the guide blade body, and the guide blade (200) has a second blade shaft (270b), which is coaxial with the first blade shaft (270a) and non-rotatably connected to the guide blade body (201) on a second side surface (203) of the guide blade body (201), and the second side surface is opposite to the first side surface (202).

[0196] 35. A guiding device (100), comprising:

[0197] a blade bearing ring (110), and

[0198] at least one guide blade (200) according to any of the preceding embodiments, wherein the at least one guide blade (200) is rotatably and adjustably mounted in the blade bearing ring (110) via a blade shaft (270),

[0199] In particular, it comprises a plurality of guide blades (200) according to any one of the aforementioned embodiments, wherein each guide blade (200) of the plurality of guide blades (200) is rotatably and adjustably supported in the blade bearing ring (110) via a blade shaft (270).

[0200] 36. According to the guide device (100) described in embodiment 35, the guide device also includes an adjustment ring (120), which has a plurality of connection areas (130), and the connection areas are correspondingly spaced from each other in the circumferential direction (26) in the adjustment ring (120), wherein each guide blade (200) of the plurality of guide blades (200) is respectively connected to a blade rod (140) in a non-rotatable manner relative to each other, and in particular each blade rod (140) is at least partially received in the corresponding connection area (130) for adjusting the corresponding guide blade (200).

[0201] 37. The guide device (100) according to embodiment 35 or embodiment 36, wherein each coupling region (130) is designed as a channel (131) having a surrounding wall (132) in the adjustment ring (120).

[0202] 38. A guide device (100) according to embodiment 36 or embodiment 37, wherein the guide blade body (201) is non-rotatably connected to the blade shaft (270) at a first end of the blade shaft (270), and the corresponding blade rod (140) is non-rotatably connected to the blade shaft (270) at a second end of the blade shaft (270) opposite to the first end.

[0203] 39. A guide device (100) according to any one of embodiments 35 to 38, wherein each blade rod (140) has a radial blade rod section (141) extending radially from the blade shaft (140), and an axial blade rod section (142) extending axially from the radial blade rod section (141) toward the adjustment ring (120), in particular wherein the axial blade rod section (140) extends at least partially in the axial direction into the corresponding connection area (130).

[0204] 40. According to any one of embodiments 35 to 39, the guide device (100) further comprises a cover plate (150), which is arranged in parallel with the blade bearing ring (110), wherein the plurality of adjustable guide blades (200) are arranged between the cover plate (150) and the blade bearing ring (110).

[0205] 41. A guide device (100) according to embodiment 40, wherein the blade shaft (270) is a first blade shaft (270a) and has a blade axis, the blade axis defines the guide blade rotation axis (PA), and wherein the guide blade (200) is a second blade shaft (270b), the second blade shaft is opposite to the first blade shaft (270a) and is non-rotatably connected to the guide blade body (201), wherein the second blade shaft (270b) is rotatably supported in the cover disk (150).

[0206] 42. A guide device (100) according to any one of embodiments 35 to 41, wherein the adjustable guide blade (200) is rotatably supported in the blade bearing ring (110) via the blade shaft (270) in a manner evenly distributed in the circumferential direction (26).

[0207] 43. The guide device (100) according to any one of embodiments 35 to 42, wherein the guide device (100) has an odd number of adjustable guide blades (200).

[0208] 44. A guide device (100) according to any one of embodiments 40 to 43, wherein the guide device (100) has a plurality of spacer elements (160), and the plurality of spacer elements are arranged on the blade bearing ring (110) in a distributed manner in a circumferential direction (26), so that the plurality of spacer elements limit the axial spacing (161) between the blade bearing ring (110) and the cover disk (150), in particular wherein the plurality of spacer elements (160) include at least three spacer elements (160).

[0209] 45. A guide device (100) according to any one of embodiments 35 to 44, wherein the plurality of adjustable guide blades (200) can be adjusted between a first position (180) and a second position (190), in particular by means of movement of the adjustment ring (130) along a circumferential direction (26), the first position corresponding to a maximally open position of the guide device (100) and the second position corresponding to a minimally open position of the guide device (100).

[0210] 46. ​​A guide device (100) according to embodiment 45, wherein the guide device (100) defines an axial direction (22), and wherein a first blade rear edge spacing (R1) at the first position (180) is smaller than a second blade rear edge spacing (R2) at the second position (190), wherein the first spacing (R1) and the second spacing (R2) are each measured radially between the axial direction (22) and the blade rear edge (240).

[0211] 47. The guide device (100) according to embodiment 46, wherein the blade bearing ring (110) defines an inner radius (R L ), and the inner radius (R L ) and the first spacing (R1) and / or the second spacing (R2) satisfy the following conditions:

[0212] 0.95≤R L / R1≤0.995, especially 0.97≤R L / R1≤0.99, and / or

[0213] 0.70≤R L / R2≤0.80, especially 0.72≤R L / R2≤0.78.

[0214] 48. A guide device (100) according to any one of embodiments 45 to 47, wherein the guide vane (200) has a first inflow angle (α1) in the first position (180), and wherein the guide vane (200) has a second inflow angle (α2) in the second position (190), in particular wherein the first inflow angle (α1) is greater than the second inflow angle (α2).

[0215] 49. According to the guiding device (100) described in any one of embodiments 35 to 48, the guiding device also includes an actuating device (60), which is operably connected to the adjusting ring (120) and is designed to move the adjusting ring (120) along the circumferential direction (26), especially wherein the actuating device (60) is connected to the adjusting ring (120) via one or more rods and / or regulating rods.

[0216] 50. A guide device (100) according to any one of embodiments 35 to 49, wherein the guide device (100) further comprises a pre-guide grid (170), which circumferentially surrounds the blade bearing ring (110) and / or the plurality of adjustable guide blades (200), wherein the pre-guide grid (170) has a plurality of fixed, flow-optimized spacers (171), wherein the fixed, flow-optimized spacers (171) are each arranged between two adjacent adjustable guide blades (200), in particular adjacent to the outer periphery (101) of the guide device (100).

[0217] 51. The guide device (100) according to any one of embodiments 35 to 50, wherein the guide device (100) is a variable-section turbine.

[0218] 52. A turbine (10) for a supercharging device (2), the turbine comprising:

[0219] Turbine housing (11);

[0220] a turbine impeller (12) arranged in the turbine housing (11); and

[0221] According to the guide device (100) described in any one of embodiments 35 to 51, in particular a variable cross-section turbine, the guide device is arranged in the turbine housing (11) radially outside the turbine impeller (12) and circumferentially surrounds the turbine impeller (12).

[0222] 53. A turbine (10) according to embodiment 52, wherein the turbine housing (11) includes a turbine inlet (13), a turbine outlet (14) and a receiving space (15), the receiving space being arranged between the turbine inlet (13) and the turbine outlet (14) and being in fluid connection with the turbine inlet (13) and the turbine outlet (14), and wherein the turbine impeller (12) is arranged in the receiving space (15).

[0223] 54. A turbine (10) according to embodiment 52 or embodiment 53, wherein the plurality of adjustable guide vanes (200) are capable of being adjusted between a first position (180) and a second position (190), the first position corresponding to a position of maximum opening of the guide device (100) and the second position corresponding to a position of minimum opening of the guide device (100).

[0224] 55. A turbine (10) according to any one of embodiments 52 to 54, wherein the turbine (10) defines an axial direction (22), and wherein the first blade trailing edge spacing (R1) at the first position is less than the second blade trailing edge spacing (R2) at the second position, wherein the first spacing (R1) and the second spacing (R2) are each measured radially between the axial direction (22) and the blade trailing edge (240).

[0225] 56. The turbine (10) according to embodiment 55, wherein the turbine wheel (12) has a turbine wheel radius (R TR ), where the turbine wheel radius (R TR ) and the first spacing (R1) satisfy the following conditions:

[0226] 0.90≤R TR / R1≤0.98, especially 0.94≤R TR / R1≤0.97.

[0227] 57. The turbine (10) according to embodiment 55 or embodiment 56, wherein the turbine impeller (12) has a turbine impeller radius (R TR ), where the turbine wheel radius (R TR ) and the second spacing (R2) satisfy the following conditions:

[0228] 0.65≤R TR / R2≤0.80, especially 0.70≤R TR / R2≤0.75.

[0229] 58. The turbine (10) according to any one of embodiments 52 to 57, wherein the turbine (10) is a radial turbine.

[0230] 59. According to a turbine (10) described in any one of embodiments 52 to 58, the turbine also includes a tensioning device (500), wherein the tensioning device (500) is arranged in an axial direction (22) between the guide device (100), in particular the blade bearing ring (110) and the turbine rear wall (15), in particular wherein the tensioning device (500) is designed to tension the guide device (100) onto the turbine housing (11).

[0231] 60. The turbine (10) according to embodiment 59, wherein the tensioning device (500) abuts against the blade bearing ring (110) at its radially outer end and against the turbine rear wall (16) at its radially inner end.

[0232] 61. The turbine (10) according to embodiment 58 or embodiment 59, wherein a heat shield (600) is clamped between the tensioning device (500) and the blade bearing ring (110).

[0233] 62. The turbine (10) according to any one of embodiments 59 to 61, wherein the turbine rear wall (16) is designed as a part of the support housing (40).

[0234] 63. A turbine (10) according to any one of embodiments 53 to 62, wherein the turbine inlet (13) includes a first supply channel (13a) and a second supply channel (13b), and the first supply channel and the second supply channel are arranged spaced apart from each other in a circumferential direction (26).

[0235] 64. A supercharging device (2) for an internal combustion engine (3) or a fuel cell, the supercharging device comprising:

[0236] A support housing (40);

[0237] a shaft (30) rotatably supported in the support housing (40);

[0238] a compressor (50) having a compressor impeller (52); and

[0239] A turbine (10) according to any one of embodiments 52 to 63, wherein the turbine impeller (12) and the compressor impeller (52) are non-rotatably coupled to the shaft (30) at opposite ends of the shaft (30).

[0240] 65. A supercharging device (2) according to embodiment 64, wherein the compressor (50) includes a compressor housing (51), the compressor impeller (52) is arranged in the compressor housing, and the support housing (40) is connected to the turbine housing (12) and the compressor housing (52).

[0241] 66. According to the boosting device (2) described in embodiment 64 or embodiment 65, the boosting device also includes an electric motor, which is arranged in a motor space in the support housing (40), wherein the turbine impeller (12) and / or the compressor impeller (52) are connected to the electric motor via the shaft (30).

[0242] 67. An engine system (1), the engine system comprising:

[0243] An internal combustion engine (3) having a plurality of cylinders; and

[0244] A supercharging device (2) according to any one of embodiments 64 to 66, wherein a turbine inlet (13) of the turbine housing (11) is in fluid connection with the plurality of cylinders downstream of the internal combustion engine (3).

[0245] 68. An engine system (1) according to embodiment 67, wherein the plurality of cylinders form a first cylinder group and a second cylinder group, and wherein the turbine inlet (13) includes a first supply channel (13a) and a second supply channel (13b), the first supply channel and the second supply channel are spaced apart from each other in a circumferential direction (26), wherein the first cylinder group is in fluid connection with the first supply channel (13a), and wherein the second cylinder group is in fluid connection with the second supply channel (13b).

[0246] 69. An engine system (1) according to embodiment 68, wherein the first cylinder group (4) and the second cylinder group (5) each have a plurality of cylinders, each of which has a combustion chamber, in particular wherein the first cylinder group (4) is arranged on a first cylinder bank and the second cylinder group (5) is arranged on a second cylinder bank.

[0247] 70. According to the engine system (1) described in any one of embodiments 67 to 69, the engine system further includes: an intake channel (6), which is arranged upstream of the internal combustion engine (3) and is fluidically connected to each cylinder so as to supply intake air to the cylinder; and an exhaust channel (7), which is arranged downstream of the internal combustion engine (3) and is connected to each cylinder so as to discharge fluid, especially exhaust gas, from the cylinder.

[0248] 71. An engine system (1) according to embodiment 70, wherein the turbine (10) is arranged in the exhaust passage (7), wherein during operation, the fluid is guided to the turbine impeller (12) via the plurality of guide vanes (200), and wherein the compressor (50) is arranged in the inlet passage (6).

Claims

1. A guide blade for a guide device (100), the guide blade comprising: A guide blade body (201), the guide blade body having a blade top side (210), a blade bottom side (220), a blade front edge (230) and a blade rear edge (240); a profile centerline (250) which is defined in the profile of the guide vane body (201) by the blade top side (210) and the blade bottom side (220) and extends between the blade top side and the blade bottom side from the blade leading edge (230) to the blade trailing edge (240), wherein the profile centerline (250) has an inflection point (TP); wherein a chord line (260) connects the leading edge (230) of the blade and the trailing edge (240) of the blade, wherein the guide vane (200) has a guide vane rotation axis (PA), and The rotation axis (PA) is located between the blade leading edge (230) and the inflection point (TP) along the chord line (260) starting from the blade leading edge (230) in the direction toward the blade trailing edge (240).

2. The guide vane according to claim 1, wherein the chord line (260) forms an intersection point (S1, S2) with each of the blade leading edge (230) and the blade trailing edge (240), and the chord line (260) defines an X-axis of a coordinate system (X, Y), the X-axis extending along the chord line (260) and extending from the blade leading edge (230) toward the blade trailing edge (240), wherein a chord length (C) of the chord line (260) is parallel to the chord line (260) and is measured between the respective intersection points (S1, S2) of the chord line (260) with the blade leading edge (230) and the blade trailing edge (240).

3. The guide vane according to claim 2, wherein the rotation axis (PA) is located along the X-axis at a position that satisfies the following conditions: 0.20≤X PA / C≤0.35, Where X PA Defined as the distance between the rotation axis (PA) and the leading edge (230) of the blade along the X-axis.

4. The guide vane according to claim 2, wherein the rotation axis (PA) is located along the X-axis at a position satisfying the following conditions: 0.23≤X PA / C≤0.31, Where X PA Defined as the distance between the rotation axis (PA) and the leading edge (230) of the blade along the X-axis.

5. The guide vane according to claim 2, wherein the Y axis of the coordinate system (X, Y) is defined as being orthogonal to the X axis and extending through the intersection of the chord line (260) and the blade leading edge (230), wherein the rotation axis (PA) is located along the Y axis at a position satisfying the following conditions: Y PA ≤0, where Y PA Defined as the distance between the rotation axis (PA) and the chord line (260) along the Y-axis.

6. The guide vane according to claim 2, wherein the Y axis of the coordinate system (X, Y) is defined as being orthogonal to the X axis and extending through the intersection of the chord line (260) and the blade leading edge (230), wherein the rotation axis (PA) is located along the Y axis at a position satisfying the following conditions: -0.005≤Y PA / C≤0, where Y PA Defined as the distance between the rotation axis (PA) and the chord line (260) along the Y-axis.

7. The guide vane according to claim 2, wherein the inflection point (TP) is located along the X-axis at a position satisfying the following conditions: X PA <X TP , Where X TP Defined as the distance between the inflection point (TP) and the leading edge (230) of the blade along the X-axis.

8. The guide vane according to claim 2, wherein the inflection point (TP) is located along the X-axis at a position satisfying the following conditions: 0.40≤X TP / C≤0.45, Where X TP Defined as the distance between the inflection point (TP) and the leading edge (230) of the blade along the X-axis.

9. The guide vane according to claim 2, wherein the distance (X) between the inflection point (TP) and the rotation axis (PA) along the X axis is A ) meets the following conditions: 0.05≤X A / C≤0.25, Where X A Defined as the distance between the inflection point (TP) and the rotation axis (PA) along the X-axis.

10. The guide vane according to claim 2, wherein the distance (X) between the inflection point (TP) and the rotation axis (PA) along the X axis is A ) meets the following conditions: 0.09≤X A / C≤0.20, Where X A Defined as the distance between the inflection point (TP) and the rotation axis (PA) along the X-axis.

11. The guide vane according to claim 2, wherein the Y axis of the coordinate system (X, Y) is defined as being orthogonal to the X axis and extending through the intersection of the chord line (260) and the blade leading edge (230), wherein the inflection point (TP) is located along the Y axis at a position satisfying the following conditions: 0≤Y TP , where Y TP Defined as the distance between the inflection point (TP) and the chord line (260) along the Y-axis.

12. A guide blade according to any one of claims 1 to 11, wherein the blade top side (210) and the blade bottom side (220) are designed so that the contour center line (250) has a wavy shape with the inflection point (TP), wherein the contour center line (250) has a first bending area (251a) and a second bending area (251b), and the inflection point (TP) is defined between the first bending area and the second bending area.

13. A guide vane according to any one of claims 1 to 11, wherein the blade top side (210) has a concave section (211a) followed by a convex section (211b) starting from the blade leading edge (230) in the direction of the blade trailing edge (240) and with respect to the chord line (260), and / or the blade bottom side (220) has a convex section (221a) followed by a concave section (221b) starting from the blade leading edge (230) in the direction of the blade trailing edge (240) and with respect to the chord line (260).

14. A guide vane according to any one of claims 1 to 11, wherein the contour centerline (250) defines a first local extreme value (E1) between the leading edge (230) of the blade and the inflection point (TP), and the contour centerline (250) defines a second local extreme value (E2) between the inflection point (TP) and the trailing edge (240) of the blade, the first local extreme value (E1) being a low point, and the second local extreme value (E2) being a high point.

15. The guide vane according to claim 2, wherein the contour centerline (250) defines a first local extremum (E1) between the leading edge (230) of the blade and the inflection point (TP), and the contour centerline (250) defines a second local extremum (E2) between the inflection point (TP) and the trailing edge (240) of the blade, the first local extremum (E1) being located at a position along the X-axis with respect to the rotation axis (PA) and the inflection point (TP) that satisfies the following conditions: X E1 <X PA <X TP , Where X E1 is defined as the distance between the first local extremum (E1) and the leading edge (230) of the blade along the X-axis, and Where X TP Defined as the distance between the inflection point (TP) and the leading edge (230) of the blade along the X-axis.

16. A guiding device, comprising: a blade bearing ring (110), and At least one guide vane (200) according to any one of claims 1 to 15, wherein the at least one guide vane (200) is rotatably and adjustably mounted in the vane bearing ring (110) via a vane shaft (270).

17. The guide device (100) according to claim 16, wherein the guide device (100) is a variable-geometry turbine.

18. A turbine for a supercharging device (2), the turbine comprising: Turbine housing (11); a turbine impeller (12) rotatably arranged in the turbine housing (11); as well as According to the guide device (100) of claim 16 or claim 17, the guide device is arranged in the turbine housing (11) radially outside the turbine impeller (12) and circumferentially surrounds the turbine impeller (12).

19. A supercharging device for an internal combustion engine (3) or a fuel cell, the supercharging device comprising: A support housing (40); a shaft (30) rotatably supported in the support housing (40); A compressor (50) having a compressor impeller (52); as well as The turbine (10) of claim 18, wherein the turbine wheel (12) and the compressor wheel (52) are non-rotatably coupled to the shaft (30) at opposite ends of the shaft (30).

20. An engine system, the engine system comprising: An internal combustion engine (3) having a plurality of cylinders; as well as The supercharging device (2) according to claim 19, wherein the turbine (10) has a turbine housing (11), and a turbine inlet (13) of the turbine housing (11) is in fluid connection with the plurality of cylinders downstream of the internal combustion engine (3).

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