Rotating device

Abstract

This rotating device is provided with: one or more plates (21, 22) that define a part of a flow path (10); and a plurality of blades (23) disposed in the flow path (10), each blade (23) comprising: a blade body (25) located in 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), the shaft (26) including an R shape at both axial ends of a contact portion between the shaft (26) and the one or more holes (21a, 22a).

Description

Technical Field

[0001] The present disclosure relates to a rotating device. This application claims the benefit of priority based on Japanese Patent Application No. 2022-158185 filed on September 30, 2022, the contents of which are incorporated herein by reference. Background Art

[0002] Rotating devices such as turbines or compressors sometimes have movable blades for adjusting the width (cross-sectional area) of a flow path. For example, Patent Document 1 discloses a centrifugal turbine having guide blades. The guide blades are connected to a blade shaft. The blade shaft is rotatably mounted on a housing. The guide blades rotate integrally with the blade shaft. The width of the flow path is adjusted by controlling the rotation angle of the guide blades.

[0003] Prior art literature

[0004] Patent Literature

[0005] Patent Document 1: Japanese Patent Application No. 2009-523957 Summary of the invention

[0006] Problems to be solved by the invention

[0007] The blades receive load from the fluid. If the shaft tilts due to the load, the shaft can contact the hole supporting the shaft in a local area. Such local contact may cause excessive contact stress and may hinder the smooth rotation of the blades.

[0008] An object of the present disclosure is to provide a rotating device capable of reducing contact stress between a shaft and a hole in a movable blade.

[0009] Means for solving problems

[0010] In order to solve the above-mentioned problems, a rotating device of one embodiment of the present invention comprises: one or more plates which define a part of a flow path; and a plurality of blades which are arranged in the flow path, each blade comprising: a blade body which is located in the flow path; and a shaft which is rotatably supported by one or more holes provided in the one or more plates, and includes R shapes at both axial ends of the contact portion between the shaft and the one or more holes.

[0011] The shaft may include at least one tapered portion continuously formed in an R-shape, and the at least one tapered portion may be at least partially disposed inside the one or more holes.

[0012] The radius of the R shape may be greater than or equal to 0.5 mm and less than or equal to 1.0 mm.

[0013] Effects of the Invention

[0014] According to the present disclosure, in the rotary device, it is possible to reduce the contact stress between the shaft and the hole in the movable blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic cross-sectional view of a supercharger including a turbine according to an embodiment.

[0016] Figure 2 yes Figure 1 An enlarged cross-sectional view of section A in FIG.

[0017] Figure 3 yes Figure 2 An enlarged cross-sectional view of part B in FIG.

[0018] Figure 4 yes Figure 2 An enlarged cross-sectional view of section C in FIG. DETAILED DESCRIPTION

[0019] Hereinafter, an embodiment of the present disclosure will be described in detail with reference to the accompanying drawings. The specific dimensions, materials, and numerical values ​​shown in this embodiment are merely examples for easy understanding, and do not limit the present disclosure unless otherwise specified. In addition, in this specification and the accompanying drawings, for elements having substantially the same function and structure, repeated descriptions are omitted by marking the same reference numerals, and elements that are not directly related are omitted from the drawings.

[0020] Figure 1 1 is a schematic cross-sectional view of a supercharger TC equipped with a turbine 100 according to an embodiment. In this embodiment, the turbine (rotating device) 100 is assembled to the supercharger TC. In other embodiments, the turbine 100 may be assembled to a device other than the supercharger TC, or may be a single unit.

[0021] The supercharger 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 .

[0022] On the first end surface of the bearing housing 4, Figure 1 The turbine housing 5 is connected to the left end face of the bearing housing 4 by a fastening bolt B1. Figure 2 The compressor housing 6 is connected to the right end surface in the middle by fastening bolts B2.

[0023] The bearing housing 4 includes a bearing hole 4a. The bearing hole 4a extends in the axial direction of the shaft 1 in the bearing housing 4. 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 also be a full floating bearing or other radial bearings such as a rolling bearing. The bearing 7 rotatably supports the shaft 1.

[0024] At the first end of the shaft 1, Figure 1 The turbine impeller 2 is provided at the left end in the middle. The turbine impeller 2 rotates integrally with the shaft 1. The turbine impeller 2 is rotatably accommodated in the turbine housing 5. The second end of the shaft 1 opposite to the first end, Figure 1 The compressor impeller 3 is provided at the right end in the middle. The compressor impeller 3 rotates integrally with the shaft 1. The compressor impeller 3 is rotatably accommodated in the compressor housing 6.

[0025] The compressor housing 6 includes an air inlet 6a at an end portion on the side opposite to the bearing housing 4. The air inlet 6a is connected to an air filter (not shown). The bearing housing 4 and the compressor housing 6 define a diffuser flow path 8 therebetween. The diffuser flow path 8 has an annular shape. The diffuser flow path 8 is located outside the compressor impeller 3 in the radial direction of the compressor impeller 3. The diffuser flow path 8 is connected to the air inlet 6a via the compressor impeller 3.

[0026] The compressor housing 6 includes a compressor scroll flow path 9. The compressor scroll flow path 9 is located outside the diffuser flow path 8 in the radial direction of the compressor impeller 3. The compressor scroll flow path 9 is connected to the diffuser flow path 8. In addition, the compressor scroll flow path 9 is connected to an intake port of an engine (not shown).

[0027] When the compressor impeller 3 rotates, air is sucked into the compressor housing 6 from the air inlet 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 flow path 8 and the compressor vortex flow path 9. The pressurized air flows out from the exhaust port not shown in the figure and is guided to the air inlet of the engine. In the supercharger TC, the part including the compressor impeller 3 and the compressor housing 6 functions as a centrifugal compressor 200.

[0028] The turbine housing 5 includes an exhaust port 5a at an end portion on the side opposite to 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 flow path 10. The connecting flow path 10 has an annular shape. The connecting flow path 10 is located outside the turbine impeller 2 in the radial direction of the turbine impeller 2. The connecting flow path 10 is connected to the exhaust port 5a via the turbine impeller 2.

[0029] The turbine housing 5 includes a turbine scroll flow path 11. The turbine scroll flow path 11 is located outside the connecting flow path 10 in the radial direction of the turbine impeller 2. The turbine scroll flow path 11 is connected to the connecting flow path 10. In addition, the turbine scroll flow path 11 is connected to a gas inlet (not shown). The gas inlet receives exhaust gas discharged from an exhaust manifold of an engine (not shown).

[0030] The exhaust gas is guided from the gas inlet to the turbine vortex flow path 11, and then guided to the exhaust port 5a via the connecting flow path 10 and the turbine impeller 2. The exhaust gas rotates the turbine impeller 2 while passing 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, as described above, air is sucked in from the intake port 6a, and is accelerated and pressurized by the compressor impeller 3. In the supercharger TC, the portion including the turbine impeller 2 and the turbine housing 5 functions as a turbine 100.

[0031] If the flow rate of the exhaust gas introduced to the turbine housing 5 changes, the rotation amount of the turbine impeller 2 and the compressor impeller 3 also changes. Therefore, depending on the operating conditions of the engine, the air introduced to the intake port of the engine may not be pressurized to a desired pressure. The supercharger TC disclosed in the present invention includes a nozzle mechanism 20 that changes the width (area) of the flow path of the turbine housing 5, specifically, the width of the flow path in the connecting flow path 10, so as to adjust the flow rate of the exhaust gas passing through the turbine impeller 2 according to the operating conditions of the engine.

[0032] 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 is increased, and the turbine impeller 2 can rotate at a small flow rate.

[0033] 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.

[0034] In the present embodiment, the first plate 21 has a substantially annular shape and is disposed coaxially with the turbine impeller 2 and between the turbine impeller 2 and the turbine scroll flow path 11 .

[0035] In the present embodiment, the second plate 22 has a substantially annular shape and is disposed coaxially with the turbine impeller 2 and between the turbine impeller 2 and the turbine scroll flow path 11. The second plate 22 is disposed parallel to the first plate 21 and opposed to it with a gap therebetween.

[0036] The first plate 21 and the second plate 22 define the above-mentioned connecting flow path 10 therebetween. That is, the first plate 21 and the second plate 22 define a portion of the exhaust gas flow path (connecting flow path 10) extending from the gas inlet to the exhaust port 5a in the turbine housing 5.

[0037] The nozzle vanes 23 are arranged in the connecting flow path 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.

[0038] Figure 2 yes Figure 1 In the present embodiment, each nozzle vane 23 is rotatably supported by the first plate 21 and the second plate 22. Specifically, each nozzle vane 23 includes a vane body 25 and a shaft 26.

[0039] The blade body 25 is located in the connection flow path 10. That is, the blade body 25 is located between the first plate 21 and the second plate 22. The blade body 25 changes the flow direction of the exhaust gas according to the rotation angle.

[0040] The shaft 26 is connected to the blade body 25. For example, the shaft 26 may be formed integrally with the blade body 25. Alternatively, the shaft 26 may be a component different from the blade body 25, for example, it may be fixed to the blade body 25 by welding or bonding. In the present embodiment, the shaft 26 includes a first shaft portion 27 and a second shaft portion 28.

[0041] The first shaft portion 27 extends from the first end surface 25a in the blade body 25 to the Figure 2 The left end face in the middle protrudes 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. Figure 2 Only one first through hole 21a is shown in the figure. The first shaft portion 27 is inserted into the first through hole 21a. The length of the first shaft portion 27 is substantially the same as the length of the first through hole 21a. That is, the protruding end of the first shaft portion 27 and the end surface of the first plate 21 are substantially coplanar with each other.

[0042] The first shaft portion 27 includes, in order of approaching the blade body 25 along the axial direction, a first constricted portion 27 a , a first tapered portion 27 b , a first contact portion 27 c , and a second tapered portion 27 d .

[0043] The first constricted portion 27a is connected to the blade body 25. The first constricted portion 27a has a cylindrical shape. The first constricted portion 27a has a certain diameter in 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.

[0044] The first tapered portion 27b connects the first contact portion 27c and the first constricted portion 27a. The first tapered portion 27b gradually 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. In addition, the maximum diameter of the first tapered portion 27b is equal to the diameter of the first contact portion 27c.

[0045] 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 substantially 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.

[0046] Figure 3 yes Figure 2 An enlarged cross-sectional view of part B in FIG. Figure 3 The connecting portion between the first contact portion 27c and the second tapered portion 27d is shown.

[0047] The second tapered portion 27d is connected to the first contact portion 27c. The second tapered portion 27d includes a protruding end of the first shaft portion 27. The second tapered portion 27d tapers gradually from the first contact portion 27c toward the protruding end of the first shaft portion 27. As 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 substantially equal to the diameter of the first contact portion 27c. In addition, the minimum diameter of the second tapered portion 27d is smaller than the inner diameter of the first through hole 21a. The entirety or a majority of the second tapered portion 27d is located inside the first through hole 21a. In other embodiments, the second tapered portion 27d may also be partially located outside the first through hole 21a.

[0048] The connection portion between the first contact portion 27c and the second tapered portion 27d has a rounded corner and includes a first R-shape R1. Therefore, the first contact portion 27c and the second tapered portion 27d are smoothly connected to each other without an edge. In other words, the second tapered portion 27d is formed continuously with the first R-shape R1.

[0049] return Figure 2 The second shaft portion 28 extends from the second end surface 25b of the blade body 25 to the Figure 2 The right end face in the middle protrudes toward the second plate 22. The second shaft portion 28 is arranged parallel to and coaxially 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. Figure 2 Only one second through hole 22a is shown in the figure. 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. That is, the protruding end of the second shaft portion 28 is located outside the second through hole 22a.

[0050] The second shaft portion 28 includes, in order from approaching the blade body 25 in the axial direction, a second constricted portion 28 a , a third tapered portion 28 b , a second contact portion 28 c , a fourth tapered portion 28 d , and a coupling portion 28 e .

[0051] The second constricted portion 28a is connected to the blade 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.

[0052] 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. In addition, the maximum diameter of the third tapered portion 28b is equal to the diameter of the second contact portion 28c.

[0053] 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 substantially 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 the present 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 also be different from the diameter of the first contact portion 27c.

[0054] The fourth tapered portion 28d connects the second contact portion 28c and the coupling portion 28e. The fourth tapered portion 28d tapers gradually from the second contact portion 28c toward the coupling portion 28e. As described later, 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 substantially equal to the diameter of the second contact portion 28c. In addition, the minimum diameter of the fourth tapered portion 28d is equal to the diameter of the coupling portion 28e. In addition, as described later, the coupling portion 28e has a cylindrical shape including a cutout 28f. Figure 2 In the figure, the diameter of the coupling portion 28e is shown to be smaller due to the cutout 28f. The entire 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 also be partially located outside the second through hole 22a.

[0055] Figure 4 yes Figure 2 An enlarged cross-sectional view of section C in FIG. Figure 4 The connecting portion between the second contact portion 28c and the fourth tapered portion 28d is shown.

[0056] The connection between the second contact portion 28c and the fourth tapered portion 28d has a rounded corner and is 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 an edge. In other words, the fourth tapered portion 28d is formed continuously with the second R shape R2.

[0057] return Figure 2 The coupling portion 28e is connected to the fourth tapered portion 28d. The coupling portion 28e includes a protruding end of the second shaft portion 28. The coupling portion 28e has a cylindrical shape including one or more cutouts 28f on the side. Figure 2 In the embodiment, the coupling portion 28e includes two cutouts 28f. The coupling portion 28e has a constant diameter in 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.

[0058] The 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.

[0059] In the nozzle mechanism 20 as described above, each link plate 24 is rotated by a circular plate member (not shown) rotated by an actuator, and rotates around the corresponding shaft 26 together with other link plates 24. When the link plate 24 rotates, the shaft 26 attached to the link plate 24 rotates integrally with the link plate 24. In addition, the blade body 25 rotates integrally with the shaft 26. As a result, the width of the connection flow path 10 changes.

[0060] The blade body 25 receives a load from the exhaust gas. The load can cause the shaft 26 to tilt. In this case, the shaft 26 can contact the through holes 21a and 22a in a local area.

[0061] Specifically, in this embodiment, as described above, the shaft 26 includes the first shaft portion 27 and the second shaft portion 28. Therefore, the shaft 26 contacts the first through hole 21a at the first contact portion 27c of the first shaft portion 27 and contacts the second through hole 22a at the second contact portion 28c of the second shaft portion 28.

[0062] When the shaft 26 is tilted, the shaft 26 contacts the through holes 21a and 22a at both ends of the entire contact portions 27c and 28c in the axial direction, specifically, at the connection between the first contact portion 27c and the second tapered portion 27d at one end and at the connection between the second contact portion 28c and the fourth tapered portion 28d at the other end. Such local contact may cause excessive contact stress and may hinder the smooth rotation of the nozzle vane 23.

[0063] However, in this embodiment, if Figure 3 As shown in FIG. 1 , one end of the contact portion of the shaft 26 in the axial direction, that is, the connection portion between the first contact portion 27c and the second tapered portion 27d includes a first R-shaped portion R1 having a rounded corner (arc shape). Therefore, when the shaft 26 is tilted, the first R-shaped portion R1 contacts the first through hole 21a. As a result, point contact between the first shaft portion 27 and the first through hole 21a can be avoided. Therefore, the contact stress between the first shaft portion 27 and the first through hole 21a can be reduced.

[0064] In addition, in this embodiment, if Figure 4 As shown in FIG. 1 , the other end of the contact portion of the shaft 26 in the axial direction, that is, the connection portion between the second contact portion 28c and the fourth tapered portion 28d includes a second R-shaped portion R2 having a rounded corner (arc shape). Therefore, when the shaft 26 is tilted, the second R-shaped portion R2 contacts the second through hole 22a. As a result, point contact between the second shaft portion 28 and the second through hole 22a can be avoided. Therefore, the contact stress between the second shaft portion 28 and the second through hole 22a can be reduced.

[0065] For example, the radius of the first R shape R1 and the second R shape R2 can also be determined by analysis or experiment so that the contact stress of the first R shape R1 and the second R shape R2 does not exceed the plastic flow pressure under the assumed load conditions. "Plastic flow pressure" refers to the stress at which the material begins to deform irreversibly. For example, the radius of the first R shape R1 and the second R shape R2 can also be greater than 0.5 mm and less than 1.0 mm. When the radius is less than 0.5 mm, the processing of the R shape is difficult and the manufacturing cost may increase. When the radius is greater than 1.0 mm, it may be difficult to fully ensure the axial length of the contact portion 27c, 28c that can withstand the assumed load conditions. However, the radius of the first R shape R1 and the second R shape R2 is not limited to the above range, and can also change according to various factors such as the operating conditions of the turbine 100. For example, the first R shape R1 and the second R shape R2 can also be formed by various processing methods such as chamfering.

[0066] As described above, the turbine 100 of the present embodiment includes the first plate 21 and the second plate 22 that define the connection flow path 10, and the plurality of nozzle blades 23 arranged in the connection flow path 10. Each nozzle blade 23 includes: a blade body 25 that is located in the connection flow path 10; and a shaft 26 that is rotatably supported by the first through hole 21a provided in the first plate 21 and the second through hole 22a provided in the second plate 22. The shaft 26 includes R shapes R1 and R2 at both ends in the axial direction of the contact portions 27c and 28c between the shaft 26 and the through holes 21a and 22a. According to such a structure, when the shaft 26 is tilted, since the R shapes R1 and R2 are in contact with the through holes 21a and 22a, point contact between the shaft 26 and the through holes 21a and 22a can be avoided. Therefore, the contact stress between the shaft 26 and the through holes 21a and 22a can be reduced.

[0067] In the turbine 100, the shaft 26 includes a second tapered portion 27d formed continuously with the first R-shaped portion R1, and the second tapered portion 27d is at least partially disposed inside the first through hole 21a. According to such a structure, the shaft 26 gradually leaves the surface of the first through hole 21a at the second tapered portion 27d. Therefore, when the shaft 26 is tilted, the first R-shaped portion R1 is more likely to contact the first through hole 21a, and the contact area between the first R-shaped portion R1 and the first through hole 21a increases. Therefore, the contact stress between the shaft 26 and the first through hole 21a can be further reduced.

[0068] Similarly, in the turbine 100, the shaft 26 includes a fourth tapered portion 28d formed continuously with the second R-shaped portion R2, and the fourth tapered portion 28d is at least partially arranged inside the second through hole 22a. According to such a structure, the shaft 26 gently leaves the surface of the second through hole 22a at the fourth tapered portion 28d. Therefore, when the shaft 26 is inclined, the second R-shaped portion R2 is more likely to contact the second through hole 22a, and the contact area between the second R-shaped portion R2 and the second through hole 22a increases. Therefore, the contact stress between the shaft 26 and the second through hole 22a can be further reduced.

[0069] In the turbine 100, the radius of the R-shaped R1 and R2 is 0.5 mm or more and 1.0 mm or less. According to such a structure, it is possible to suppress an increase in manufacturing cost and ensure a sufficient axial length of the contact portions 27c and 28c.

[0070] The above describes one embodiment of the present disclosure with reference to the accompanying drawings, but the present disclosure is not limited to the embodiment. It is obvious that a person skilled in the art can think of various changes or modifications within the scope of the claims, and it is understood that they also belong to the technical scope of the present disclosure.

[0071] For example, in the above-mentioned embodiment, the present invention is applied to the turbine 100. In other embodiments, the present invention may also be applied to a variable capacity type rotary device other than a turbine. For example, the present invention may also be applied to a centrifugal compressor 200. In this case, the movable blades may also be provided in, for example, the diffuser flow path 8 of the centrifugal compressor 200.

[0072] In addition, refer to Figure 2 In the above-mentioned embodiment, the shaft 26 is supported by both the first plate 21 and the second plate 22. In other embodiments, 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 such a structure, when the shaft 26 (second shaft portion 28) is inclined, the shaft 26 contacts the second through hole 22a at the connection portion between the third tapered portion 28b, which is one end of the contact portion 28c in the axial direction, and the contact portion 28c, which is the connection portion between the contact portion 28c and the fourth tapered portion 28d, which is the other end of the contact portion 28c in the axial direction. Therefore, in this case, an R shape may be formed at the connection portion between the third tapered portion 28b and the contact portion 28c.

[0073] In addition, in the above-mentioned embodiment, the shaft 26 includes the second tapered portion 27d formed continuously with the first R shape R1 and the 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 protruding end of the first shaft portion 27.

[0074] Explanation of symbols

[0075] 10: Connecting flow path (part of the flow path)

[0076] 21: First board

[0077] 21a: First through hole (hole provided on the plate)

[0078] 22: Second board

[0079] 22a: Second through hole (hole provided on the plate)

[0080] 23: Nozzle blade (blade)

[0081] 25: Blade body

[0082] 26: Axis

[0083] 27c: First contact portion (contact portion between the shaft and the hole)

[0084] 27d: Second tapered portion

[0085] 28c: Second contact portion (contact portion between the shaft and the hole)

[0086] 28d: Fourth cone

[0087] 100: Turbine (rotating device)

[0088] R1, R2: R shape

Claims

1. A rotating device, characterized in that: have: one or more plates that define a portion of the flow path; as well as A plurality of blades are arranged in the flow path, each blade comprising: a blade body located in the flow path; and a shaft rotatably supported by the one or more holes provided in the one or more plates, wherein both ends of the axial direction of a contact portion between the shaft and the one or more holes include an R shape.

2. The rotating device according to claim 1, characterized in that: The shaft includes at least one tapered portion continuously formed into the R shape, The at least one tapered portion is at least partially disposed within the interior of the one or more holes.

3. The rotating device according to claim 1 or 2, characterized in that: The radius of the R shape is greater than or equal to 0.5 mm and less than or equal to 1.0 mm.

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