Rotation device

Abstract

A rotation device T1 comprises: an impeller 3; a plurality of vanes V which are disposed along a circumferential direction in a region outside in a radial direction with respect to the impeller 3 and protrude in an axial direction; a first wall surface W1 which opposes a protruding end Va of each of the plurality of vanes V in the axial direction; and an inclined surface S which is formed on at least one of the first wall surface W1 and the protruding end Va of each of the plurality of vanes V and is inclined with respect to the radial direction of the impeller 3.

Description

Rotating device

[0001] This application claims the benefit of priority from Japanese Patent Application No. 2023-102413, filed on June 22, 2023, the contents of which are incorporated herein by reference.

[0002] A rotary device such as a turbine or a centrifugal compressor may include vanes arranged radially outward from an impeller. For example, Patent Document 1 discloses a fixed vane arranged radially outward from a turbine impeller. The fixed vane is arranged in a passage between a bearing housing and a turbine housing. The fixed vane includes a plurality of vane bodies and an annular movable member. The plurality of vane bodies are fixed to a front surface of the movable member. The ends of the vane bodies face the turbine housing. A disc spring is arranged in the space between the back surface of the movable member and the bearing housing. The disc spring presses the vane body against the turbine housing. With this configuration, the clearance between the vane body and the turbine housing is reduced. Therefore, a decrease in turbine efficiency is reduced.

[0003] International Publication No. 2012 / 036122

[0004] As described above, in a rotary device, it is desirable to reduce the clearance between the vane and the housing in order to prevent a decrease in efficiency.

[0005] An object of the present disclosure is to provide a rotating device that can reduce the clearance between a vane and a housing.

[0006] A rotary device according to one aspect of the present disclosure comprises an impeller, a plurality of vanes arranged circumferentially in a region radially outward from the impeller and protruding in the axial direction, a first wall surface axially facing the tip of each of the plurality of vanes, and an inclined surface formed on at least one of the first wall surface and the tip of the plurality of vanes and inclined relative to the radial direction of the impeller.

[0007] The rotating device may comprise an annular vane plate arranged radially outward from the impeller and including a first surface facing the axial direction and a second surface opposite the first surface, wherein the plurality of vanes protrude from the first surface of the vane plate; a second wall surface sandwiching the vane plate and the plurality of vanes and facing the first wall surface in the axial direction, the second wall surface facing the second surface of the vane plate; and an elastic body arranged between the second surface of the vane plate and the second wall surface and pushing the vane plate and the plurality of vanes toward the first wall surface.

[0008] The inclined surface may be formed on the first wall surface, and the first wall surface may be located radially inward from the tips of the plurality of vanes and include a discontinuity protruding from the inclined surface.

[0009] According to the present disclosure, the clearance between the vane and the housing can be reduced.

[0010] FIG. 1 is a schematic cross-sectional view of a turbocharger including a turbine according to a first embodiment. FIG. 2 is a schematic enlarged cross-sectional view showing part A in FIG. 1. FIG. 3 is a schematic enlarged cross-sectional view showing a deformation mode of a vane plate of a turbine not including an inclined surface when the vane plate is heated. FIG. 4 is a schematic enlarged cross-sectional view showing a deformation mode of a vane plate of a turbine not including an inclined surface when the vane plate is cooled. FIG. 5 is a schematic enlarged cross-sectional view showing the behavior of the vanes when the vane plate in FIG. 2 is heated. FIG. 6 is a schematic enlarged cross-sectional view of a turbine according to a second embodiment. FIG. 7 is a schematic enlarged cross-sectional view of a turbine according to a third embodiment. FIG. 8 is a schematic enlarged cross-sectional view of a turbine according to a fourth embodiment. FIG. 9 is a schematic enlarged cross-sectional view of a turbine according to a fifth embodiment.

[0011] Hereinafter, embodiments of the present disclosure will be described in detail with reference to the accompanying drawings. Specific dimensions, materials, numerical values, etc. shown in the embodiments are merely examples for ease of understanding and do not limit the present disclosure 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 not directly related to the present disclosure are not shown.

[0012] 1 is a schematic cross-sectional view of a turbocharger 100 including a turbine T1 according to a first embodiment. The turbine T1 according to this embodiment is applied to the turbocharger 100. In other embodiments, the turbine T1 may be applied to equipment other than the turbocharger 100, or may be a standalone unit. The turbocharger 100 includes a housing 1, a shaft 2, a turbine impeller 3, and a compressor impeller 4.

[0013] As will be described later, the turbine impeller 3 and the compressor impeller 4 rotate integrally with the shaft 2. Therefore, in this disclosure, the axial direction, radial direction, and circumferential direction of the shaft 2, the turbine impeller 3, and the compressor impeller 4 may be simply referred to as the "axial direction," the "radial direction," and the "circumferential direction," respectively, unless otherwise specified. Also, in this disclosure, the central axis of the shaft 2, the turbine impeller 3, and the compressor impeller 4 may be simply referred to as the "central axis," unless otherwise specified.

[0014] The housing 1 includes a bearing housing 5, a turbine housing 6, and a compressor housing 7. One end of the bearing housing 5 is axially connected to the turbine housing 6 by a fastener such as a G-coupling. The other end of the bearing housing 5 is axially connected to the compressor housing 7 by a fastener such as a bolt.

[0015] The bearing housing 5 includes a bearing hole 5a. The bearing hole 5a extends in the axial direction within the bearing housing 5. The bearing hole 5a accommodates a bearing B. The bearing B rotatably supports the shaft 2. In this embodiment, a pair of rolling bearings is used as the bearing B. In other embodiments, other radial bearings such as full-floating bearings or semi-floating bearings may be used as the bearing B.

[0016] A turbine impeller 3 is provided at a first end of the shaft 2 in the axial direction. The turbine impeller 3 rotates integrally with the shaft 2. A turbine housing 6 rotatably accommodates the turbine impeller 3. A compressor impeller 4 is provided at a second end of the shaft 2 opposite the first end in the axial direction. The compressor impeller 4 rotates integrally with the shaft 2. A compressor housing 7 rotatably accommodates the compressor impeller 4.

[0017] The compressor housing 7 includes an air intake port 71 at an end opposite to the bearing housing 5 in the axial direction. The air intake port 71 is connected to an air cleaner (not shown).

[0018] The bearing housing 5 and the compressor housing 7 define a diffuser passage 72 therebetween. The diffuser passage 72 has an annular shape. The diffuser passage 72 is located radially outward from the compressor impeller 4. The diffuser passage 72 is in fluid communication with the intake port 71 via the compressor impeller 4.

[0019] The compressor housing 7 includes a compressor scroll passage 73. The compressor scroll passage 73 is located radially outward of the diffuser passage 72. The compressor scroll passage 73 communicates with the diffuser passage 72. The compressor scroll passage 73 also fluidly communicates with an intake port of the engine (not shown).

[0020] When the compressor impeller 4 rotates, air is drawn into the compressor housing 7 through the intake port 71. The air is accelerated and pressurized by centrifugal force while passing through the compressor impeller 4. The air is further pressurized when passing through the diffuser passage 72 and the compressor scroll passage 73. The pressurized air flows out from a discharge port (not shown) and is led to the intake port of the engine. In the turbocharger 100, a portion including the compressor impeller 4 and the compressor housing 7 functions as a centrifugal compressor C.

[0021] The turbine housing 6 includes a discharge port 61 at an end opposite to the bearing housing 5 in the axial direction. The discharge port 61 is connected to an exhaust gas purification device (not shown).

[0022] The turbine housing 6 includes a connecting passage 62. The connecting passage 62 has an annular shape. The connecting passage 62 is located radially outward from the turbine impeller 3. The connecting passage 62 is fluidly connected to the discharge port 61 via the turbine impeller 3. A plurality of vanes V are arranged in the connecting passage 62. The plurality of vanes V are arranged along the circumferential direction in a region radially outward from the turbine impeller 3. The vanes V will be described in detail later.

[0023] The turbine housing 6 includes a turbine scroll passage 63. The turbine scroll passage 63 is located radially outward of the connecting passage 62. The turbine scroll passage 63 is in fluid communication with the connecting passage 62. The turbine scroll passage 63 also communicates with a gas inlet (not shown). The gas inlet receives exhaust gas discharged from an exhaust manifold (not shown) of the engine.

[0024] Exhaust gas is guided from the gas inlet to the turbine scroll passage 63, and then through the connecting passage 62 and the turbine impeller 3 to the discharge port 61. The exhaust gas rotates the turbine impeller 3 while passing through it. The rotational force of the turbine impeller 3 is transmitted to the compressor impeller 4 via the shaft 2. When the compressor impeller 4 rotates, the air is compressed as described above. The compressed air is then guided to the intake port of the engine.

[0025] Next, the vane V will be described.

[0026] Figure 2 is a schematic enlarged cross-sectional view showing part A in Figure 1. Figure 2 shows the vane plate 8 and vanes V without thermal deformation. Note that in the drawings of this disclosure, the angle of an inclined surface S, which will be described later, relative to the radial direction is exaggerated for better understanding. The turbine T1 includes the vane plate 8 and an elastic body 9.

[0027] The vane plate 8 has an annular shape. The vane plate 8 is disposed radially outward from the turbine impeller 3. The vane plate 8 is disposed concentrically with the turbine impeller 3. In this embodiment, the turbine housing 6 includes a groove 64 for disposing the vane plate 8 therein. The vane plate 8 is disposed in the groove 64.

[0028] The vane plate 8 includes a first surface 81 and a second surface 82 facing in the axial direction. The second surface 82 is located opposite the first surface 81. The first surface 81 and the second surface 82 extend in the radial direction. The first surface 81 and the second surface 82 have an annular shape.

[0029] The housing 1 includes a first wall surface W1 and a second wall surface W2 that are opposed to each other in the axial direction with the vane plate 8 and the vane V interposed therebetween.

[0030] The first wall surface W1 axially faces the tip Va of the vane V. In this embodiment, the first wall surface W1 is the surface farthest from the discharge port 61 out of a pair of surfaces that face each other axially across the connecting flow passage 62. In this embodiment, the first wall surface W1 is formed on the bearing housing 5.

[0031] The second wall surface W2 faces the second surface 82 of the vane plate 8 in the axial direction. In the present embodiment, the second wall surface W2 is the surface closer to the discharge port 61 of a pair of surfaces facing each other in the axial direction with the connecting flow passage 62 in between. In the present embodiment, the second wall surface W2 is formed on the turbine housing 6. In the present embodiment, the second wall surface W2 is a surface that defines the groove 64. The second wall surface W2 defines the groove 64 in the axial direction.

[0032] The first wall surface W1 and the second wall surface W2 extend radially. The first wall surface W1 and the second wall surface W2 have an annular shape. In this embodiment, the connecting flow passage 62 is defined by the first wall surface W1 and the first surface 81 of the vane plate 8.

[0033] The vanes V protrude in the axial direction from the first surface 81 of the vane plate 8. The vanes V are fixed to the first surface 81. For example, the vanes V may be formed integrally with the vane plate 8. Alternatively, the vanes V may be formed separately from the vane plate 8 and connected to the vane plate 8. The tips Va of the vanes V face the first wall surface W1.

[0034] The elastic body 9 is disposed between the second surface 82 of the vane plate 8 and the second wall surface W2 of the turbine housing 6. In this embodiment, the elastic body 9 is disposed in the groove 64. The elastic body 9 presses the vane plate 8 and the vanes V toward the first wall surface W1. Therefore, the protruding ends Va of the vanes V are pressed against the first wall surface W1. In this embodiment, the elastic body 9 is a disc spring. In other embodiments, other elastic bodies, such as multiple coil springs, may be used as the elastic body 9. In this embodiment, the elastic body 9 has a frusto-conical shape. The elastic body 9 is disposed concentrically with the turbine impeller 3.

[0035] 3 is a schematic enlarged cross-sectional view showing the deformation mode of the vane plate 8 of a turbine T that does not include an inclined surface S when the vane plate 8 is heated. The turbine T of FIG. 3 and the following FIG. 4 does not include an inclined surface S, as will be described later. Also, in FIGS. 3 and 4, the deformation of the vane plate 8 is exaggerated for better understanding.

[0036] For example, when an engine (not shown) accelerates, hot exhaust gas from the engine flows through the connecting passage 62. In this case, the first surface 81 of the vane plate 8, which faces the connecting passage 62, becomes hotter than the second surface 82 on the opposite side. Therefore, the first surface 81 expands radially outward more than the second surface 82. The vanes V tilt together with the vane plate 8. In this deformation mode, the outermost diameter portion of the tip Va of the vane V moves away from the first wall surface W1, and a clearance is formed between the vane V and the first wall surface W1. Therefore, the efficiency of the turbine T1 decreases.

[0037] FIG. 4 is an enlarged schematic cross-sectional view showing the deformation mode of the vane plate 8 of a turbine T that does not include an inclined surface S when the vane plate 8 is cooled.

[0038] For example, when cooling the turbocharger 100, cooling air flows through the connecting flow passage 62. In this case, the first surface 81 of the vane plate 8, which faces the connecting flow passage 62, becomes cooler than the second surface 82 on the opposite side. Therefore, the first surface 81 contracts radially inward relative to the second surface 82. The vane V tilts together with the vane plate 8. In this deformation mode, the innermost diameter portion of the tip Va of the vane V moves away from the first wall surface W1, and a clearance is formed between the vane V and the first wall surface W1. Therefore, the efficiency of the turbine T1 decreases.

[0039] 2, in this embodiment, an inclined surface S is formed on the first wall surface W1 in order to reduce the clearance formed by the above-described deformation of the vane plate 8. In this embodiment, when the vane plate 8 is heated (the situation shown in FIG. 3), the inclined surface S is formed in a direction that reduces the clearance between the vane V and the first wall surface W1.

[0040] Specifically, as shown in FIG. 3 , when the vane plate 8 is heated, the outermost diameter portion of the tip Va of the vane V moves away from the first wall surface W1. Referring to FIG. 2 , in order to accommodate such deformation, in this embodiment, the inclined surface S is formed on the first wall surface W1 so as to be inclined toward the outermost diameter portion of the tip Va in a state without thermal deformation. In this embodiment, the inclined surface S has a linear shape in a cross section parallel to and including the central axis. In this embodiment, the inclined surface S is formed so as to overlap the entire length of the tip Va in the radial direction. For example, the angle of the inclined surface S with respect to the radial direction may be determined based on the amount of deformation of the vane plate 8 when the vane plate 8 is heated under predetermined operating conditions. For example, the amount of deformation of the vane plate 8 may be determined by analysis or experiment.

[0041] Figure 5 is a schematic enlarged cross-sectional view showing the behavior of the vanes V when the vane plate 8 in Figure 2 is heated. In Figure 5, the deformation of the vane plate 8 is also exaggerated for better understanding.

[0042] As described above, when the vane plate 8 is heated, the vane plate 8 is deformed so that the outermost diameter portions of the tips Va of the vanes V move away from the first wall surface W1. However, in this embodiment, the inclined surface S is formed on the first wall surface W1 so as to be inclined in a direction approaching the outermost diameter portions of the tips Va. Therefore, the tips Va of the vanes V move to a position parallel to the inclined surface S. As a result, the contact area between the tips Va and the inclined surface S increases, and the clearance between the vanes V and the first wall surface W1 is reduced.

[0043] In another embodiment, the inclined surface S may be formed in a direction that reduces the clearance between the vane V and the first wall surface W1 when the vane plate 8 is cooled (the situation shown in FIG. 4 ). In this case, the inclined surface S is formed on the first wall surface W1 so as to be inclined in a direction away from the outermost diameter portion of the tip Va.

[0044] The turbine T1 according to this embodiment as described above includes a turbine impeller 3, a plurality of vanes V arranged circumferentially in a region radially outward of the turbine impeller 3 and protruding in the axial direction, a first wall surface W1 facing a tip Va of each of the plurality of vanes V in the axial direction, and an inclined surface S formed on the first wall surface W1 and inclined relative to the radial direction. With this configuration, when the wall surface supporting the vane V is heated or cooled, the tip Va of the vane V moves to a position parallel to the inclined surface S. As a result, the contact area between the tip Va and the inclined surface S increases, and the clearance between the vane V and the first wall surface W1 is reduced.

[0045] The turbine T1 also includes an annular vane plate 8 disposed radially outward relative to the turbine impeller 3 and including a first surface 81 facing the axial direction and a second surface 82 opposite the first surface 81, and the plurality of vanes V are provided with: a vane plate 8 protruding from the first surface 81 of the vane plate 8; a second wall surface W2 axially opposing the first wall surface W1 across the vane plate 8 and the plurality of vanes V, the second wall surface W2 opposing the second surface 82 of the vane plate 8; and an elastic body 9 disposed between the second surface 82 of the vane plate 8 and the second wall surface W2 and pressing the vane plate 8 and the vanes V toward the first wall surface W1. With this configuration, the elastic body 9 can firmly press the tip Va of the vane V against the inclined surface S.

[0046] Next, other embodiments will be described.

[0047] Figure 6 is a schematic enlarged cross-sectional view of a turbine T2 according to a second embodiment. In Figure 6 and the following Figures 7, 8, and 9, the vane plate 8 and vanes V before thermal deformation are shown by solid lines, and the vane plate 8 and vanes V after thermal deformation are shown by dashed lines. Also, in Figures 6, 7, 8, and 9, the deformation of the vane plate 8 is exaggerated for better understanding.

[0048] The turbine T2 according to this embodiment differs from the turbine T1 according to the first embodiment in that the inclined surface S is formed on the tip Va of the vane V, instead of on the first wall surface W1. In other respects, the turbine T2 may be the same as the turbine T1.

[0049] In this embodiment, the inclined surface S is formed in a direction that reduces the clearance between the vane V and the first wall surface W1 when the vane plate 8 is heated. Specifically, in this embodiment, the inclined surface S is formed on the head end Va so that the outermost diameter portion of the head end Va protrudes axially toward the first wall surface W1 more than the innermost diameter portion. In this embodiment, the inclined surface S is formed over the entire length of the head end Va in the radial direction. In other embodiments, the inclined surface S may be formed only on a portion of the head end Va in the radial direction. For example, the inclined surface S may be formed only on the radially inner region of the head end Va. In this case, the remainder of the head end Va may be parallel or approximately parallel to the first wall surface W1 in an undeformed state.

[0050] In the turbine T2 according to this embodiment, when the vane plate 8 is heated, the inclined surface S of the vane V moves to a position parallel to the first wall surface W1. As a result, as shown by the dashed line of the vane V, the contact area between the inclined surface S of the tip Va and the first wall surface W1 increases, reducing the clearance between the vane V and the first wall surface W1. Therefore, the turbine T2 achieves substantially the same effects as the turbine T1 according to the first embodiment.

[0051] 7 is a schematic enlarged cross-sectional view of a turbine T3 according to a third embodiment. The turbine T3 according to this embodiment differs from the turbine T1 according to the first embodiment in that the arrangement of the vane plate 8 and the vanes V is upside down in the axial direction compared to those in FIGS. 2 to 6 , and the inclined surface S is formed on the turbine housing 6 instead of the bearing housing 5. Therefore, in this embodiment, the groove 51 that accommodates the vane plate 8 and the elastic body 9 is formed on the bearing housing 5. In other respects, the turbine T3 may be the same as the turbine T1.

[0052] In this embodiment, the first wall surface W1 facing the tip Va of the vane V is the surface closest to the discharge port 61 of a pair of surfaces facing each other in the axial direction with the connecting flow passage 62 in between. In this embodiment, the first wall surface W1 is formed on the turbine housing 6. In this embodiment, the second wall surface W2 facing the second surface 82 of the vane plate 8 is the surface farthest from the discharge port 61 of a pair of surfaces facing each other in the axial direction with the connecting flow passage 62 in between. In this embodiment, the second wall surface W2 is formed on the bearing housing 5. In this embodiment, the second wall surface W2 is a surface that defines the groove 51. The second wall surface W2 defines the groove 51 in the axial direction.

[0053] In this embodiment, when the vane plate 8 is heated, the inclined surface S is formed in a direction that reduces the clearance between the vane V and the first wall surface W1. Specifically, when an engine (not shown) accelerates, hot exhaust gas from the engine flows through the connecting passage 62. In this case, the first surface 81 of the vane plate 8 that faces the connecting passage 62 becomes hotter than the second surface 82 on the opposite side. Therefore, as shown by the dashed line of the vane plate 8, the first surface 81 expands radially outward more than the second surface 82.

[0054] In this embodiment, the inclined surface S is formed on the first wall surface W1 so that, in a state without thermal deformation, it is inclined in a direction approaching the outermost diameter portion of the tip Va of the vane V. In this embodiment, the inclined surface S is formed so as to overlap the entire length of the tip Va in the radial direction.

[0055] In another embodiment, the inclined surface S may be formed in a direction that reduces the clearance between the vane V and the first wall surface W1 when the vane plate 8 is cooled. In this case, the inclined surface S is formed on the first wall surface W1 so as to be inclined in a direction away from the outermost diameter portion of the tip Va of the vane V in a state without thermal deformation.

[0056] In the turbine T3 according to this embodiment as described above, when the vane plate 8 is heated, the tips Va of the vanes V move to a position parallel to the inclined surface S. As a result, the contact area between the tips Va and the inclined surface S increases, and the clearance between the vanes V and the first wall surface W1 is reduced. Therefore, the turbine T3 achieves substantially the same effects as the turbine T1 according to the first embodiment.

[0057] 8 is a schematic enlarged cross-sectional view of a turbine T4 according to a fourth embodiment. The turbine T4 according to this embodiment differs from the turbine T3 according to the third embodiment in that the inclined surface S is shorter in the radial direction. In other respects, the turbine T4 may be the same as the turbine T3.

[0058] In this embodiment, the inclined surface S overlaps only a portion of the tip Va in the radial direction. In this embodiment, the inclined surface S overlaps only a radially inner region of the tip Va. The first wall surface W1 includes a surface that is radially outward from the inclined surface S and parallel to the radial direction.

[0059] In the turbine T4 according to the present embodiment as described above, when the vane plate 8 is heated, the tip Va of the vane V moves to a position parallel to the inclined surface S. As a result, the radially inner region of the tip Va is pressed against the inclined surface S. Therefore, the clearance between the vane V and the first wall surface W1 is reduced compared to when only the innermost diameter portion of the tip Va is pressed against the first wall surface W1.

[0060] 9 is a schematic enlarged cross-sectional view of a turbine T5 according to a fifth embodiment. The turbine T5 according to this embodiment differs from the turbine T3 according to the third embodiment in that a discontinuous portion 65 is formed in the first wall surface W1. In other respects, the turbine T5 may be the same as the turbine T3. Note that the axial height of the discontinuous portion 65 is exaggerated.

[0061] The discontinuous portion 65 protrudes from the inclined surface S in a generally axial direction. The discontinuous portion 65 is located radially inward of the tip Va of the vane V. For example, the discontinuous portion 65 may be continuous in the circumferential direction. In this embodiment, the discontinuous portion 65 is smoothly connected to the shroud 66 and is continuous with the shroud 66.

[0062] The turbine T5 according to this embodiment as described above achieves substantially the same effects as the turbine T3 according to the third embodiment. In particular, in the turbine T5, the inclined surface S is formed on the first wall surface W1, which is located radially inward of the tip Va of the vane V and includes a discontinuous portion 65 that protrudes from the inclined surface S. With this configuration, the vane V is positioned deeper than the discontinuous portion 65, thereby reducing the gap at the tip Va of the vane V.

[0063] Although the embodiments have been described above with reference to the accompanying drawings, the present disclosure is not limited to the above-described embodiments. 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.

[0064] For example, in the above embodiment, the rotating device is the turbine T1, T2, T3, T4, or T5, and the inclined surface S is formed on the vane V disposed in the connecting passage 62 or on the wall surface defining the connecting passage 62. In another embodiment, for example, the rotating device may be the centrifugal compressor C, and the inclined surface S may be formed on the diffuser vane disposed in the diffuser passage 72 or on the wall surface defining the diffuser passage 72.

[0065] In the above embodiment, the rotating device includes the elastic body 9. In other embodiments, the rotating device may not include the elastic body 9. In this case, the rotating device may not include the vane plate 8, and the vanes V may protrude directly from the wall surface that defines the flow path in which the vanes V are arranged.

[0066] In the above embodiment, the inclined surface S is formed on one of the first wall surface W1 and the tip Va of the vane V. In other embodiments, the inclined surface S may be formed on both the first wall surface W1 and the tip Va of the vane V. In this case, for example, the angle of the inclined surface S may be determined so that the sum of the absolute value of the angle of the inclined surface S formed on the first wall surface W1 relative to the radial direction and the absolute value of the angle of the inclined surface S formed on the tip Va relative to the radial direction corresponds to the amount of deformation of the vane plate 8. In this case, the inclined surface S formed on the first wall surface W1 and the inclined surface S formed on the tip Va are inclined in opposite directions relative to the radial direction. For example, in this case, the inclined surface S may be formed on the first wall surface W1 so as to be half the angle shown in FIG. 2, and the inclined surface S may be formed on the tip Va so as to be half the angle shown in FIG. 6.

[0067] 3 Turbine impeller 4 Compressor impeller 8 Vane plate 9 Elastic body 65 Discontinuous portion 81 First surface 82 Second surface C Centrifugal compressor (rotating device) S Inclined surface T1 Turbine (rotating device) T2 Turbine (rotating device) T3 Turbine (rotating device) T4 Turbine (rotating device) T5 Turbine (rotating device) V Vane Va Tip of vane W1 First wall surface W2 Second wall surface

Claims

1. A rotating device comprising: an impeller; a plurality of vanes arranged circumferentially in a radially outer region of the impeller and protruding in the axial direction; a first wall surface facing each end of the plurality of vanes in the axial direction; and an inclined surface formed on at least one of the first wall surface and the ends of the plurality of vanes, the inclined surface being inclined relative to the radial direction of the impeller.

2. A rotating device as claimed in claim 1, comprising: an annular vane plate arranged radially outwardly with respect to the impeller and including a first surface facing the axial direction and a second surface opposite to the first surface, wherein the plurality of vanes protrude from the first surface of the vane plate; a second wall surface facing the first wall surface in the axial direction, sandwiching the vane plate and the plurality of vanes, the second wall surface facing the second surface of the vane plate; and an elastic body arranged between the second surface of the vane plate and the second wall surface, for pushing the vane plate and the plurality of vanes towards the first wall surface.

3. A rotating device as described in claim 1 or 2, wherein the inclined surface is formed on the first wall surface, and the first wall surface is located radially inward from the tips of the plurality of vanes and includes a discontinuous portion protruding from the inclined surface.