Rotating device

Abstract

This rotation device comprises one or more plates 21, 22 defining a part of a flow path 10, and a plurality of vanes 23 disposed in the flow path 10. The vanes 23 each include a vane body 25 positioned inside the flow path 10, and a shaft 26 rotatably supported by one or more holes 21a, 22a provided in the one or more plates 21, 22, both axial-directional ends of a contact part between the shaft 26 and the one or more holes 21a, 22a including a rounded shape.

Description

[Technical Field]

[0001] This application claims the benefit of priority from Japanese Patent Application No. 2022-158185, filed on September 30, 2022, the contents of which are incorporated herein by reference. [Background technology]

[0002] Rotary devices such as turbines or compressors may be equipped with movable vanes for adjusting the width (cross-sectional area) of a flow path. For example, Patent Document 1 discloses a centrifugal turbine equipped with guide vanes. The guide vanes are connected to vane shafts. The vane shafts are rotatably attached to a housing. The guide vanes rotate integrally with the vane shafts. The width of the flow path is adjusted by controlling the rotation angle of the guide vanes. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Special Publication No. 2009-523957 Summary of the Invention [Problem to be solved by the invention]

[0004] The vane is subjected to a load from the fluid. When the load causes the shaft to tilt, the shaft may come into contact with the hole that supports the shaft in a localized area. Such localized contact may cause excessive contact stress and may prevent the vane from rotating smoothly.

[0005] An object of the present disclosure is to provide a rotary device that can reduce contact stress between a shaft and a hole in a movable vane. [Means for solving the problem]

[0006] In order to solve the above problems, a rotary device according to one aspect of the present disclosure includes a first plate and a second plate that define a part of a flow path, a plurality of vanes that are arranged in the flow path, each vane having a vane body positioned within the flow path, and a first shaft portion rotatably supported by a first through-hole provided in the first plate, and a second shaft portion rotatably supported by a second through-hole provided in the second plate; and a plurality of vanes, The first shaft portion includes, in order from closest to the vane body, a first contact portion that contacts the first through hole, a first tapered portion that tapers toward the end of the first shaft portion and is at least partially disposed inside the first through hole, and a first rounded R shape that connects the first contact portion and the first tapered portion; and the second shaft portion includes, in order from closest to the vane body, a second contact portion that contacts the second through hole, a second tapered portion that tapers toward the end of the second shaft portion and is at least partially disposed inside the second through hole, and a second rounded R shape that connects the second contact portion and the second tapered portion. The tip of the first shaft portion and the end face of the first plate are flush with each other. The radius of each of the first R shape and the second R shape is 0.5 mm or more and 1.0 mm or less. . [Effects of the Invention]

[0009] According to the present disclosure, in a rotary device, the contact stress between the shaft and the hole in the movable vane can be reduced. [Brief explanation of the drawings]

[0010] [Figure 1] FIG. 1 is a schematic cross-sectional view of a turbocharger including a turbine according to an embodiment. [Figure 2] FIG. 2 is an enlarged cross-sectional view of part A in FIG. [Figure 3] FIG. 3 is an enlarged cross-sectional view of part B in FIG. [Figure 4] FIG. 4 is an enlarged cross-sectional view of part C in FIG. DETAILED DESCRIPTION OF THE INVENTION

[0011] An embodiment of the present disclosure will be described in detail below with reference to the accompanying drawings. Specific dimensions, materials, numerical values, etc. shown in the embodiment are merely examples for ease of understanding and are not intended to be limiting unless otherwise specified. In this specification and drawings, elements having substantially the same functions and configurations are designated by the same reference numerals to avoid redundant explanation, and elements that are not directly related are not shown.

[0012] 1 is a schematic cross-sectional view of a turbocharger TC including a turbine 100 according to an embodiment. In this embodiment, the turbine (rotating device) 100 is incorporated into the turbocharger TC. In other embodiments, the turbine 100 may be incorporated into a device other than the turbocharger TC, or may be a standalone device.

[0013] The turbocharger TC includes a shaft 1 , a turbine impeller 2 , a compressor impeller 3 , a bearing housing 4 , a turbine housing 5 , and a compressor housing 6 .

[0014] A turbine housing 5 is connected to a first end face of the bearing housing 4 (the left end face in FIG. 1) by a fastening bolt B1. A compressor housing 6 is connected to a second end face of the bearing housing 4 opposite the first end face (the right end face in FIG. 2) by a fastening bolt B2.

[0015] The bearing housing 4 includes a bearing hole 4a. The bearing hole 4a extends within the bearing housing 4 along the axial direction of the shaft 1. The bearing hole 4a accommodates a bearing 7. In this embodiment, a semi-floating bearing is shown as an example of the bearing 7. In other embodiments, the bearing 7 may be a full-floating bearing or another radial bearing such as a rolling bearing. The bearing 7 rotatably supports the shaft 1.

[0016] A turbine impeller 2 is provided at a first end of the shaft 1, which is the left end in FIG. 1 . The turbine impeller 2 rotates integrally with the shaft 1. The turbine impeller 2 is rotatably housed in a turbine housing 5. A compressor impeller 3 is provided at a second end of the shaft 1 opposite the first end, which is the right end in FIG. 1 . The compressor impeller 3 rotates integrally with the shaft 1. The compressor impeller 3 is rotatably housed in a compressor housing 6.

[0017] The compressor housing 6 includes an intake port 6a at the end opposite the bearing housing 4. The intake port 6a is connected to an air cleaner (not shown). The bearing housing 4 and the compressor housing 6 define a diffuser passage 8 therebetween. The diffuser passage 8 has an annular shape. The diffuser passage 8 is located outside the compressor impeller 3 in the radial direction of the compressor impeller 3. The diffuser passage 8 communicates with the intake port 6a via the compressor impeller 3.

[0018] The compressor housing 6 includes a compressor scroll passage 9. The compressor scroll passage 9 is located outside the diffuser passage 8 in the radial direction of the compressor impeller 3. The compressor scroll passage 9 communicates with the diffuser passage 8. The compressor scroll passage 9 also communicates with an intake port of the engine (not shown).

[0019] When the compressor impeller 3 rotates, air is drawn into the compressor housing 6 through the intake port 6a. The intake air is accelerated and pressurized by centrifugal force while passing between the blades of the compressor impeller 3. The air is further pressurized in the diffuser passage 8 and the compressor scroll passage 9. The compressed air flows out from a discharge port (not shown) and is led to the intake port of the engine. In the turbocharger TC, the portion including the compressor impeller 3 and the compressor housing 6 functions as a centrifugal compressor 200.

[0020] The turbine housing 5 includes an exhaust port 5a at the end opposite the bearing housing 4. The exhaust port 5a is connected to an exhaust gas purification device (not shown). The turbine housing 5 includes a connecting passage 10. The connecting passage 10 has an annular shape. The connecting passage 10 is located outside the turbine impeller 2 in the radial direction of the turbine impeller 2. The connecting passage 10 communicates with the exhaust port 5a via the turbine impeller 2.

[0021] The turbine housing 5 includes a turbine scroll passage 11. The turbine scroll passage 11 is located outside the connecting passage 10 in the radial direction of the turbine impeller 2. The turbine scroll passage 11 communicates with the connecting passage 10. The turbine scroll passage 11 also communicates with a gas inlet (not shown). The gas inlet receives exhaust gas discharged from an exhaust manifold (not shown) of the engine.

[0022] The exhaust gas is guided from the gas inlet to the turbine scroll passage 11, and further guided to the exhaust port 5a via the connecting passage 10 and the turbine impeller 2. The exhaust gas rotates the turbine impeller 2 as it passes between the blades of the turbine impeller 2. The rotational force of the turbine impeller 2 is transmitted to the compressor impeller 3 via the shaft 1. When the compressor impeller 3 rotates, air is taken in from the intake port 6a and is accelerated and pressurized by the compressor impeller 3, as described above. In the turbocharger TC, the portion including the turbine impeller 2 and the turbine housing 5 functions as a turbine 100.

[0023] When the flow rate of exhaust gas introduced into the turbine housing 5 changes, the rotational amount of the turbine impeller 2 and the compressor impeller 3 also changes. Therefore, depending on the operating conditions of the engine, it may not be possible to pressurize the air introduced into the engine intake port to the desired pressure. The turbocharger TC of the present disclosure is equipped with a nozzle mechanism 20 that changes the width (area) of the flow passage in the turbine housing 5, specifically the width of the flow passage in the connecting flow passage 10, in order to adjust the flow velocity of the exhaust gas passing through the turbine impeller 2 according to the operating conditions of the engine.

[0024] The nozzle mechanism 20 changes the flow velocity of the exhaust gas guided to the turbine impeller 2 according to the flow rate of the exhaust gas. Specifically, the nozzle mechanism 20 reduces the width of the flow path when the engine speed is low and the flow rate of the exhaust gas is small. In this way, the flow velocity of the exhaust gas guided to the turbine impeller 2 increases, and the turbine impeller 2 can rotate with a small flow rate.

[0025] The nozzle mechanism 20 includes a first plate 21 and a second plate 22 (one or more plates), a plurality of movable nozzle vanes (vanes) 23, and a plurality of link plates 24. The nozzle mechanism 20 may further include other components (not shown), such as an actuator.

[0026] In this embodiment, the first plate 21 has a generally annular shape. The first plate 21 is disposed coaxially with the turbine impeller 2 between the turbine impeller 2 and the turbine scroll passage 11.

[0027] In this embodiment, the second plate 22 has a generally annular shape. The second plate 22 is disposed coaxially with the turbine impeller 2 between the turbine impeller 2 and the turbine scroll passage 11. The second plate 22 is disposed parallel to the first plate 21 and opposed to the first plate 21 with a gap therebetween.

[0028] The first plate 21 and the second plate 22 define therebetween the above-mentioned connecting flow path 10. That is, the first plate 21 and the second plate 22 define, within the turbine housing 5, a part of the flow path of the exhaust gas that extends from the gas inlet to the exhaust port 5a (the connecting flow path 10).

[0029] The nozzle vanes 23 are arranged in the connecting flow passage 10. That is, the nozzle vanes 23 are arranged between the first plate 21 and the second plate 22. The plurality of nozzle vanes 23 are arranged along the circumferential direction of the turbine impeller 2.

[0030] Fig. 2 is an enlarged cross-sectional view of part A in Fig. 1. In this embodiment, each nozzle vane 23 is rotatably supported by a first plate 21 and a second plate 22. Specifically, each nozzle vane 23 includes a vane body 25 and a shaft 26.

[0031] The vane body 25 is located within the connecting passage 10. That is, the vane body 25 is located between the first plate 21 and the second plate 22. The vane body 25 changes the direction of the flow of exhaust gas depending on the rotation angle.

[0032] The shaft 26 is coupled to the vane body 25. For example, the shaft 26 may be integrally formed with the vane body 25. Alternatively, the shaft 26 may be a separate part from the vane body 25 and may be fixed to the vane body 25 by, for example, welding or adhesive. In this embodiment, the shaft 26 includes a first shaft portion 27 and a second shaft portion 28.

[0033] The first shaft portion 27 protrudes from a first end surface 25a of the vane body 25, which is the left end surface in FIG. 2, toward the first plate 21. The first plate 21 includes a plurality of first through holes 21a along the circumferential direction of the turbine impeller 2. Note that only one first through hole 21a is shown in FIG. 2. The first shaft portion 27 is inserted into the first through hole 21a. The length of the first shaft portion 27 is approximately the same as the length of the first through hole 21a. In other words, the tip of the first shaft portion 27 and the end surface of the first plate 21 are approximately flush with each other.

[0034] The first shaft portion 27 includes, in the axial direction, a first narrowed portion 27a, a first tapered portion 27b, a first contact portion 27c, and a second tapered portion 27d, in that order from closest to the vane body 25.

[0035] The first constricted portion 27a is connected to the vane body 25. The first constricted portion 27a has a cylindrical shape. The first constricted portion 27a has a constant diameter along the axial direction. The diameter of the first constricted portion 27a is smaller than the inner diameter of the first through hole 21a. Therefore, there is a gap between the first constricted portion 27a and the first through hole 21a.

[0036] The first tapered portion 27b connects the first contact portion 27c and the first constricted portion 27a. The first tapered portion 27b tapers from the first contact portion 27c toward the first constricted portion 27a. The minimum diameter of the first tapered portion 27b is equal to the diameter of the first constricted portion 27a. The maximum diameter of the first tapered portion 27b is equal to the diameter of the first contact portion 27c.

[0037] The first contact portion 27c is connected to the first tapered portion 27b. The first contact portion 27c has a cylindrical shape. The first contact portion 27c has a constant diameter along the axial direction. The diameter of the first contact portion 27c is approximately the same as or slightly smaller than the inner diameter of the first through hole 21a. Therefore, the first shaft portion 27 contacts the first through hole 21a at the first contact portion 27c and is rotatably supported by the first through hole 21a.

[0038] Fig. 3 is an enlarged cross-sectional view of part B in Fig. 2. Fig. 3 shows the connection point between the first contact portion 27c and the second tapered portion 27d.

[0039] The second tapered portion 27d is connected to the first contact portion 27c. The second tapered portion 27d includes the tip of the first shaft portion 27. The second tapered portion 27d tapers from the first contact portion 27c toward the tip of the first shaft portion 27. As will be described later, there is no clear edge between the second tapered portion 27d and the first contact portion 27c, but the maximum diameter of the second tapered portion 27d is approximately equal to the diameter of the first contact portion 27c. The minimum diameter of the second tapered portion 27d is smaller than the inner diameter of the first through hole 21a. The entirety or most of the second tapered portion 27d is located inside the first through hole 21a. In other embodiments, the second tapered portion 27d may be partially located outside the first through hole 21a.

[0040] The connection between the first contact portion 27c and the second tapered portion 27d is rounded and includes the first R-shape R1. Therefore, the first contact portion 27c and the second tapered portion 27d are smoothly connected to each other without any edges. In other words, the second tapered portion 27d is formed continuously with the first R-shape R1.

[0041] Returning to FIG. 2, the second shaft portion 28 protrudes from the second end surface 25b of the vane body 25, which is the right end surface in FIG. 2, toward the second plate 22. The second shaft portion 28 is arranged parallel to and coaxial with the first shaft portion 27. The second plate 22 includes a plurality of second through holes 22a along the circumferential direction of the turbine impeller 2. Note that only one second through hole 22a is shown in FIG. 2. The second shaft portion 28 is inserted into the second through hole 22a. The second shaft portion 28 protrudes to the outside of the second through hole 22a. In other words, the tip of the second shaft portion 28 is located outside the second through hole 22a.

[0042] The second shaft portion 28 includes, in the axial direction, a second constricted portion 28a, a third tapered portion 28b, a second contact portion 28c, a fourth tapered portion 28d, and a coupling portion 28e, in that order from closest to the vane body 25.

[0043] The second constricted portion 28a is connected to the vane body 25. The second constricted portion 28a has a cylindrical shape. The second constricted portion 28a has a constant diameter along the axial direction. The diameter of the second constricted portion 28a is smaller than the inner diameter of the second through hole 22a. Therefore, there is a gap between the second constricted portion 28a and the second through hole 22a.

[0044] The third tapered portion 28b connects the second contact portion 28c and the second constricted portion 28a. The third tapered portion 28b tapers from the second contact portion 28c toward the second constricted portion 28a. The minimum diameter of the third tapered portion 28b is equal to the diameter of the second constricted portion 28a. The maximum diameter of the third tapered portion 28b is equal to the diameter of the second contact portion 28c.

[0045] The second contact portion 28c is connected to the third tapered portion 28b. The second contact portion 28c has a cylindrical shape. The second contact portion 28c has a constant diameter along the axial direction. The diameter of the second contact portion 28c is approximately the same as or slightly smaller than the inner diameter of the second through hole 22a. Therefore, the second shaft portion 28 contacts the second through hole 22a at the second contact portion 28c and is rotatably supported by the second through hole 22a. In this embodiment, the diameter of the second contact portion 28c is equal to the diameter of the first contact portion 27c. In other embodiments, the diameter of the second contact portion 28c may be different from the diameter of the first contact portion 27c.

[0046] The fourth tapered portion 28d connects the second contact portion 28c and the coupling portion 28e. The fourth tapered portion 28d tapers from the second contact portion 28c toward the coupling portion 28e. As described below, there is no clear edge between the fourth tapered portion 28d and the second contact portion 28c, but the maximum diameter of the fourth tapered portion 28d is approximately equal to the diameter of the second contact portion 28c. The minimum diameter of the fourth tapered portion 28d is equal to the diameter of the coupling portion 28e. As described below, the coupling portion 28e has a cylindrical shape including a notch 28f. In FIG. 2, the diameter of the coupling portion 28e is shown smaller due to the notch 28f. The entirety or most of the fourth tapered portion 28d is located inside the second through hole 22a. In other embodiments, the fourth tapered portion 28d may be partially located outside the second through hole 22a.

[0047] Fig. 4 is an enlarged cross-sectional view of part C in Fig. 2. Fig. 4 shows the connection point between the second contact portion 28c and the fourth tapered portion 28d.

[0048] The connection between the second contact portion 28c and the fourth tapered portion 28d is rounded and connected via the second R-shape R2. Therefore, the second contact portion 28c and the fourth tapered portion 28d are smoothly connected to each other without any edges. In other words, the fourth tapered portion 28d is formed continuously with the second R-shape R2.

[0049] Returning to FIG. 2, the coupling portion 28e is connected to the fourth tapered portion 28d. The coupling portion 28e includes the protruding end of the second shaft portion 28. The coupling portion 28e has a cylindrical shape with one or more notches 28f on its side. In FIG. 2, the coupling portion 28e includes two notches 28f. The coupling portion 28e has a constant diameter along the axial direction. The diameter of the coupling portion 28e is smaller than the inner diameter of the second through hole 22a. The coupling portion 28e is located outside the second through hole 22a.

[0050] A link plate 24 is provided for each of the plurality of nozzle vanes 23. The link plate 24 is attached to the coupling portion 28e. Specifically, the link plate 24 includes a through hole 24a. The through hole 24a has a cross section corresponding to the shape of the coupling portion 28e. The coupling portion 28e is inserted into the through hole 24a.

[0051] In the nozzle mechanism 20 described above, each link plate 24 is rotated around the corresponding shaft 26 together with the other link plates 24 by a single disk member (not shown) that is rotated by an actuator. When a link plate 24 rotates, the shaft 26 attached to the link plate 24 rotates integrally with the link plate 24. The vane body 25 also rotates integrally with the shaft 26. As a result, the width of the connecting flow passage 10 changes.

[0052] The vane body 25 receives a load from the exhaust gas. The load may cause the shaft 26 to tilt. In this case, the shaft 26 may come into contact with the through-holes 21a and 22a in localized areas.

[0053] Specifically, in this embodiment, as described above, shaft 26 includes first shaft portion 27 and second shaft portion 28. Therefore, shaft 26 contacts first through hole 21a at first contact portion 27c of first shaft portion 27, and contacts second through hole 22a at second contact portion 28c of second shaft portion 28.

[0054] When the shaft 26 tilts, the shaft 26 comes into contact with the through holes 21 a, 22 a at both axial ends of the entire contact portions 27 c, 28 c, specifically, at the connection between the first contact portion 27 c and the second tapered portion 27 d as one end and the connection between the second contact portion 28 c and the fourth tapered portion 28 d as the other end. Such localized contact may cause excessive contact stress, which may hinder smooth rotation of the nozzle vane 23.

[0055] However, in this embodiment, as shown in FIG. 3, the shaft 26 includes a first rounded (arc-shaped) R1 at one end of the contact portion in the axial direction, i.e., at the connection point between the first contact portion 27c and the second tapered portion 27d. Therefore, when the shaft 26 tilts, the first rounded R1 comes into contact with the first through hole 21a. As a result, point contact between the first shaft portion 27 and the first through hole 21a is avoided. This reduces the contact stress between the first shaft portion 27 and the first through hole 21a.

[0056] 4, the shaft 26 includes a second rounded (arc-shaped) R2 at the other end of the contact portion in the axial direction, i.e., at the connection point between the second contact portion 28c and the fourth tapered portion 28d. Therefore, when the shaft 26 tilts, the second rounded R2 comes into contact with the second through hole 22a. As a result, point contact between the second shaft portion 28 and the second through hole 22a is avoided. Therefore, the contact stress between the second shaft portion 28 and the second through hole 22a can be reduced.

[0057] For example, the radii of the first R-shape R1 and the second R-shape R2 may be determined through analysis, experiment, or the like so that the contact stress at the first R-shape R1 and the second R-shape R2 under expected load conditions does not exceed the plastic flow pressure. "Plastic flow pressure" refers to the stress at which a material begins to irreversibly deform. For example, the radii of the first R-shape R1 and the second R-shape R2 may be 0.5 mm or greater and 1.0 mm or less. If the radii are smaller than 0.5 mm, machining the R-shape may be difficult, increasing manufacturing costs. If the radii are larger than 1.0 mm, it may be difficult to ensure that the axial lengths of the contact portions 27c and 28c are sufficient to withstand expected load conditions. However, the radii of the first R-shape R1 and the second R-shape R2 are not limited to the above range and may be changed depending on various factors, such as the operating conditions of the turbine 100. For example, the first R-shape R1 and the second R-shape R2 may be formed by various processing methods, such as chamfering.

[0058] As described above, the turbine 100 according to this embodiment includes the first plate 21 and the second plate 22 that define the connecting passage 10, and a plurality of nozzle vanes 23 that are arranged in the connecting passage 10. Each nozzle vane 23 includes a vane body 25 that is located within the connecting passage 10, and a shaft 26 that is rotatably supported by a first through-hole 21a provided in the first plate 21 and a second through-hole 22a provided in the second plate 22. The shaft 26 includes R-shapes R1 and R2 at both axial ends of contact portions 27c and 28c between the shaft 26 and the through-holes 21a and 22a. With this configuration, when the shaft 26 tilts, Since the R shapes R1 and R2 come into contact with the through holes 21a and 22a, point contact between the shaft 26 and the through holes 21a and 22a is avoided, thereby reducing the contact stress between the shaft 26 and the through holes 21a and 22a.

[0059] Furthermore, in the turbine 100, the shaft 26 includes a second tapered portion 27d formed continuously with the first R-shape R1, and the second tapered portion 27d is at least partially disposed inside the first through hole 21a. With this configuration, the shaft 26 gradually moves away from the surface of the first through hole 21a at the second tapered portion 27d. Therefore, when the shaft 26 tilts, the first R-shape R1 is more likely to come into contact with the first through hole 21a, increasing the contact area between the first R-shape R1 and the first through hole 21a. This further reduces the contact stress between the shaft 26 and the first through hole 21a.

[0060] Similarly, in the turbine 100, the shaft 26 includes a fourth tapered portion 28d formed continuously with the second R-shape R2, and the fourth tapered portion 28d is at least partially disposed inside the second through hole 22a. With this configuration, the shaft 26 gradually moves away from the surface of the second through hole 22a at the fourth tapered portion 28d. Therefore, when the shaft 26 tilts, the second R-shape R2 is more likely to come into contact with the second through hole 22a, increasing the contact area between the second R-shape R2 and the second through hole 22a. This further reduces the contact stress between the shaft 26 and the second through hole 22a.

[0061] Furthermore, in the turbine 100, the radius of the R shapes R1 and R2 is 0.5 mm or more and 1.0 mm or less. With this configuration, it is possible to suppress an increase in manufacturing costs and to ensure a sufficient axial length of the contact portions 27c and 28c.

[0062] While one embodiment of the present disclosure has been described above with reference to the accompanying drawings, it goes without saying that the present disclosure is not limited to such an embodiment. It is clear that a person skilled in the art can conceive of various modifications or alterations within the scope of the claims, and it is understood that such modifications also fall within the technical scope of the present disclosure.

[0063] For example, in the above embodiment, the present invention is applied to the turbine 100. In other embodiments, the present invention may be applied to a variable displacement rotary device other than a turbine. For example, the present invention may be applied to a centrifugal compressor 200. In this case, a movable vane may be provided in, for example, the diffuser passage 8 of the centrifugal compressor 200.

[0064] 2, in the above embodiment, the shaft 26 is supported by both the first plate 21 and the second plate 22. In another embodiment, for example, the shaft 26 may be supported only by the second plate 22. In this case, the nozzle vane 23 may not include the first shaft portion 27. In this configuration, when the shaft 26 (the second shaft portion 28) tilts, the shaft 26 contacts the second through hole 22a at a connection point between the third tapered portion 28b and the contact portion 28c, which serves as one end of the contact portion 28c in the axial direction, and at a connection point between the contact portion 28c and the fourth tapered portion 28d, which serves as the other end of the contact portion 28c in the axial direction. Therefore, in this case, an R-shape may also be formed at the connection point between the third tapered portion 28b and the contact portion 28c.

[0065] In the above embodiment, the shaft 26 includes a second tapered portion 27d formed continuously with the first R shape R1 and a fourth tapered portion 28d formed continuously with the second R shape R2. In other embodiments, for example, the shaft 26 may include at least one of the second tapered portion 27d and the fourth tapered portion 28d. For example, the first shaft portion 27 may not include the second tapered portion 27d. In this case, the first R shape R1 may be provided at the tip of the first shaft portion 27. [Explanation of symbols]

[0066] 10 Connecting channel (part of the channel) 21 Plate 1 21a First through hole (hole provided in plate) 22 Second Plate 22a Second through hole (hole provided in plate) 23 Nozzle vane (vane) 25 Vane body 26 shaft 27c First contact portion (contact portion between shaft and hole) 27d Second tapered section 28c Second contact portion (contact portion between shaft and hole) 28d 4th tapered section 100 Turbine (rotating device) R1,R2 R shape

Claims

[Claim 1] a first plate and a second plate defining a portion of a flow path; a plurality of vanes disposed in the flow path, each vane comprising: a vane body positioned within the flow path; a first shaft portion rotatably supported by a first through hole provided in the first plate; a second shaft portion rotatably supported by a second through hole provided in the second plate; a plurality of vanes, Equipped with The first shaft portion is arranged in the order of proximity to the vane body as follows: a first contact portion that contacts the first through hole; a first tapered portion tapered toward a tip end of the first shaft portion and at least partially disposed within the first through hole; a first R shape that connects the first contact portion and the first tapered portion and has a rounded shape; Including, The second shaft portion is arranged in the order of proximity to the vane body as follows: a second contact portion that contacts the second through hole; a second tapered portion tapered toward a tip end of the second shaft portion and at least partially disposed within the second through hole; a second R shape that connects the second contact portion and the second tapered portion and has a rounded shape; Including, the tip of the first shaft portion and the end surface of the first plate are flush with each other, The radius of each of the first R shape and the second R shape is equal to or greater than 0.5 mm and equal to or less than 1.0 mm. Rotating device.

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