JP7643214B2 - Centrifugal Rotating Device - Google Patents

Description

This disclosure relates to a centrifugal rotating device.

In this technical field, for example, Patent Document 1 discloses a vaned diffuser. In this vaned diffuser, at least one of the leading edge diameter, blade thickness, or mounting angle of the vanes is non-uniform among a plurality of vanes. This configuration reduces resonance. Similarly, in the diffuser of Patent Document 2, the angle between two guide vanes arranged adjacent to each other is different from the angle between other pairs. This configuration reduces resonance.

Diffusers with fixed and movable vanes are also known in this technical field (see, for example, Patent Documents 3 and 4). In such a configuration, for example, a fixed vane is attached to one of the opposing surfaces, and a movable vane is attached to the other. For example, adjusting the position of the movable vane can lead to a reduction in resonance.

JP 2019-167871 A Special table 2017-519154 publication JP 2008-111368 A International Publication No. 2012/077231

Further configurations to reduce resonance are desired in this technical field.

The present disclosure aims to provide a centrifugal rotating device that can reduce resonance.

In order to solve the above problems, a centrifugal rotating device according to one aspect of the present disclosure includes an impeller, a housing that accommodates the impeller, the housing including a first surface and a second surface that are located radially outward of the impeller and face each other in the direction of the central axis of the impeller, and an annular flow path formed between the first surface and the second surface, and a plurality of vane pairs that are arranged in the flow path along the circumferential direction of the impeller, each of the plurality of vane pairs including a first vane fixed to the first surface and protruding from the first surface toward the second surface, and a second vane fixed to the second surface and protruding from the second surface toward the first surface, the first vane and the second vane of each vane pair being combined to define a single fixed stator vane, and at least one of the shape, attitude, or circumferential position of the vane pairs being non-uniform among the plurality of vane pairs.

The total height of the first vane and the second vane may be non-uniform among multiple vane pairs.

The leading edge diameter of the vane pairs may be non-uniform among multiple vane pairs.

The total thickness of the first vane and the second vane may be non-uniform among multiple vane pairs.

The inlet blade angle of a vane pair may be non-uniform among multiple vane pairs.

The angles between adjacent vane pairs may be non-uniform among multiple vane pairs.

The combined height of the first vane and the second vane may be greater than the distance between the first surface and the second surface.

The first vane and the second vane may be at least partially in contact with each other in the circumferential direction.

The first vane and the second vane may be interlocked such that the outer surface of the first vane and the outer surface of the second vane are continuous with each other.

This disclosure makes it possible to reduce resonance.

FIG. 1 is a schematic cross-sectional view of a turbocharger including a centrifugal rotating device according to an embodiment. FIG. 2 is a schematic enlarged cross-sectional view of a portion A in FIG. FIG. 3 is a schematic cross-sectional view taken along line III-III in FIG. FIG. 4 is a schematic cross-sectional view showing a vane pair according to another embodiment. FIG. 5 is a schematic cross-sectional view showing a vane pair according to still another embodiment.

Embodiments of the present disclosure will be described in detail below with reference to the attached drawings. Specific dimensions, materials, 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 denoted by the same reference numerals to avoid duplicated explanations, and elements not directly related to the present disclosure are not illustrated.

Figure 1 is a schematic cross-sectional view of a turbocharger TC equipped with a centrifugal rotating device C according to an embodiment. In this embodiment, the centrifugal rotating device is applied to a compressor C of the turbocharger TC. For example, the turbocharger TC is applied to an engine. The turbocharger TC includes a housing 1, a shaft 7, a turbine impeller 8, and a compressor impeller 9.

As described below, the turbine impeller 8 and the compressor impeller 9 rotate integrally with the shaft 7. Therefore, the central axial direction, radial direction, and circumferential direction of the shaft 7 are common to the turbine impeller 8 and the compressor impeller 9. In this disclosure, the central axial direction, radial direction, and circumferential direction of the shaft 7, the turbine impeller 8, and the compressor impeller 9 may be referred to simply as the "central axial direction," the "radial direction," and the "circumferential direction," respectively, unless otherwise specified.

The housing 1 includes a bearing housing 2, a turbine housing 3, and a compressor housing 4. In the central axial direction, one end of the bearing housing 2 is connected to the turbine housing 3 by a fastening mechanism 21a such as a G coupling. In the central axial direction, the other end of the bearing housing 2 is connected to the compressor housing 4 by a fastening mechanism 21b such as a fastening bolt.

The bearing housing 2 includes a bearing hole 22. The bearing hole 22 extends in the central axis direction within the bearing housing 2. The bearing hole 22 accommodates bearings 50 and 60. The bearings 50 and 60 rotatably support the shaft 7.

A turbine impeller 8 is provided at a first end of the shaft 7 in the central axial direction. The turbine impeller 8 is rotatably housed in the turbine housing 3. A compressor impeller 9 is provided at a second end of the shaft 7 opposite the first end in the central axial direction. The compressor impeller 9 is rotatably housed in the compressor housing 4.

The compressor housing 4 includes an intake port 10 at the end opposite the bearing housing 2 in the central axial direction. The intake port 10 is connected to an air cleaner (not shown). The bearing housing 2 and the compressor housing 4 define a diffuser passage 11 therebetween. The diffuser passage 11 has an annular shape. The diffuser passage 11 is located radially outward relative to the compressor impeller 9. The diffuser passage 11 communicates with the intake port 10 via the compressor impeller 9.

The compressor housing 4 includes a compressor scroll passage 12. The compressor scroll passage 12 has an annular shape. The compressor scroll passage 12 is located radially outward of the diffuser passage 11. The compressor scroll passage 12 communicates with the diffuser passage 11. The compressor scroll passage 12 also communicates with an intake port of an engine (not shown).

In the compressor C, when the compressor impeller 9 rotates, air is drawn into the compressor housing 4 through the intake port 10. The intake air is accelerated by centrifugal force as it passes through the space between the blades of the compressor impeller 9. The accelerated air is pressurized in the diffuser passage 11 and the compressor scroll passage 12. The pressurized air flows out from a discharge port (not shown) and is led to the intake port of the engine.

The turbine housing 3 includes a discharge port 13 at the end opposite the bearing housing 2 in the central axial direction. The discharge port 13 is connected to an exhaust gas purification device (not shown). The turbine housing 3 includes a flow passage 14 and a turbine scroll flow passage 15. The turbine scroll flow passage 15 and the flow passage 14 each have an annular shape. The turbine scroll flow passage 15 is located radially outside the flow passage 14. The flow passage 14 is located radially outside the turbine impeller 8. A nozzle 16 is arranged in the flow passage 14.

The turbine scroll passage 15 communicates with a gas inlet (not shown). The gas inlet receives exhaust gas discharged from an exhaust manifold (not shown) of the engine. The turbine scroll passage 15 also communicates with the passage 14. The passage 14 communicates with the discharge port 13 via the turbine impeller 8.

In the turbine T, the exhaust gas is guided from the gas inlet to the turbine scroll passage 15, and then through the passage 14 and the turbine impeller 8 to the discharge port 13. The exhaust gas rotates the turbine impeller 8 as it passes through the spaces between the blades of the turbine impeller 8.

The rotational force of the turbine impeller 8 is transmitted to the compressor impeller 9 via the shaft 7. When the compressor impeller 9 rotates, the air is pressurized as described above. The pressurized air is then guided to the engine intake port.

Next, we will explain compressor C in detail.

Figure 2 is a schematic enlarged cross-sectional view of part A in Figure 1. Compressor C includes the compressor impeller 9 and a housing 1 including a bearing housing 2 and a compressor housing 4. Compressor C also includes multiple vane pairs BP. Note that only one vane pair BP is shown in Figure 2.

The housing 1 includes the above-mentioned diffuser passage 11. The diffuser passage 11 is located radially outside the compressor impeller 9. The diffuser passage 11 has an annular shape. The diffuser passage 11 is defined by a first surface S1 of the bearing housing 2 and a second surface S2 of the compressor housing 4. The first surface S1 and the second surface S2 face each other in the central axis direction. For example, each of the first surface S1 and the second surface S2 extends perpendicular to the central axis direction. For example, the first surface S1 and the second surface S2 are parallel to each other.

The vane pairs BP are arranged in the diffuser passage 11 along the circumferential direction. The vane pairs BP are spaced apart from one another in the circumferential direction. Each vane pair BP includes a first vane B1 and a second vane B2.

The first vane B1 is provided on the first surface S1. For example, the first vane B1 is fixed to the first surface S1. The first vane B1 protrudes in the central axial direction from the first surface S1 toward the second surface S2. The tip of the first vane B1 may be spaced apart from the second surface S2. In other embodiments, the tip of the first vane B1 may contact the second surface S2 in a non-operating state of the turbocharger TC.

The second vane B2 is provided on the second surface S2. For example, the second vane B2 is fixed to the second surface S2. The second vane B2 protrudes in the central axial direction from the second surface S2 toward the first surface S1. The tip of the second vane B2 may be spaced apart from the first surface S1. In other embodiments, the tip of the second vane B2 may contact the first surface S1 in a non-operating state of the turbocharger TC.

In this embodiment, the total height of the first vane B1 and the second vane B2 is greater than the distance between the first surface S1 and the second surface S2 in the central axis direction. The "height" of the first vane B1 and the second vane B2 means the "length in the central axis direction" of the first vane B1 and the second vane B2. In other words, the first vane B1 and the second vane B2 at least partially overlap in the central axis direction.

Figure 3 is a schematic cross-sectional view taken along line III-III in Figure 2. Note that in Figure 3, for better understanding, only the first surface S1 and three vane pairs BP are shown. However, the compressor C may have more than three vane pairs BP.

The first vane B1 and the second vane B2 of each vane pair BP combine to define a fixed stator vane. For example, the first vane B1 includes a pressure surface Ps and the second vane B2 includes a suction surface Ss. In other embodiments, the first vane B1 may include a suction surface Ss and the second vane B2 may include a pressure surface Ps.

The first vane B1 and the second vane B2 are at least partially in contact with each other in the circumferential direction. Specifically, the first vane B1 includes a first contact surface B11, and the second vane B2 includes a second contact surface B21. The first contact surface B11 and the second contact surface B21 have complementary contours. The first contact surface B11 and the second contact surface B21 are in contact with each other. The "contact" between the first contact surface B11 and the second contact surface B21 does not have to be full-surface, but may be partial, as is common in normal contact parts. In other words, a gap (non-contact portion) may be partially formed between the first contact surface B11 and the second contact surface B21, as is common in normal contact parts.

In this embodiment, the first contact surface B11 and the second contact surface B21 pass through the leading edge LE and the rear edge RE. In other embodiments, the leading edge LE may be formed by only one of the first vane B1 or the second vane B2. Also, in other embodiments, the rear edge RE may be formed by only one of the first vane B1 and the second vane B2.

In a cross section perpendicular to the central axis direction at the position where the first vane B1 and the second vane B2 overlap in the central axis direction, the outer surface of the first vane B1 and the outer surface of the second vane B2 are formed to be smoothly continuous with each other. In other words, in the above cross section, the boundary between the outer surface of the first vane B1 and the outer surface of the second vane B2 does not have a step.

In this embodiment, the leading edge diameter, inlet blade angle, and angle between adjacent vane pairs BP are non-uniform among multiple vane pairs BP.

The leading edge diameter is the distance (radius) from the central axis to the leading edge LE of each vane pair BP. For example, in FIG. 3, the leading edge diameter R3 of the right vane pair BP is larger than the leading edge diameter R2 of the middle vane pair BP, which is larger than the leading edge diameter R1 of the left vane pair BP.

The inlet vane angle is the angle defined by the pressure surface Ps and the circumferential tangent at the leading edge LE of each vane pair BP. For example, in FIG. 3, the inlet vane angle β3 of the right vane pair BP is greater than the inlet vane angle β2 of the middle vane pair BP, which is greater than the inlet vane angle β1 of the left vane pair BP.

The angle between adjacent vane pairs BP is the angle defined by the line segment connecting the central axis and the leading edge LE between adjacent vane pairs BP. For example, in FIG. 3, the angle α2 between the right vane pair BP and the middle vane pair BP is greater than the angle α1 between the middle vane pair BP and the left vane pair BP.

The leading edge diameter, inlet vane angle and angle between adjacent vane pairs BP can be determined, for example, by computer simulation, so that pressure fluctuations in a particular frequency range do not occur in compressor C.

The leading edge diameter, inlet vane angle, and angle between adjacent vane pairs BP may be different between all of the vane pairs BP, including vane pairs BP not shown in FIG. 3. In contrast, the leading edge diameter, inlet vane angle, and angle between adjacent vane pairs BP may be different between only some of the vane pairs BP.

In FIG. 3, the leading edge diameter, inlet vane angle, and angle between adjacent vane pairs BP are all different between the multiple vane pairs BP. However, in other embodiments, only one or two of the leading edge diameter, inlet vane angle, or angle between adjacent vane pairs BP may be different between the multiple vane pairs BP.

In this embodiment, the leading edge diameter and inlet blade angle located on the inner circumference side of the vane pair BP are made non-uniform. This is because resonance can be further suppressed by making the structure close to the opposing rotor blade on the inner circumference side non-uniform. However, resonance can also be suppressed even if the structure on the outer circumference side of the vane pair BP, that is, the outlet blade angle and trailing edge diameter, are made non-uniform.

The compressor C as described above includes a compressor impeller 9, a housing 1 that accommodates the compressor impeller 9, and a plurality of vane pairs BP. The housing 1 includes a first surface S1 and a second surface S2 that are located radially outward from the compressor impeller 9 and face each other in the central axial direction, and an annular diffuser passage 11 formed between the first surface S1 and the second surface S2. The plurality of vane pairs BP are arranged in the diffuser passage 11 along the circumferential direction, and each of the plurality of vane pairs BP includes a first vane B1 that is fixed to the first surface S1 and protrudes from the first surface S1 toward the second surface S2, and a second vane B2 that is fixed to the second surface S2 and protrudes from the second surface S2 toward the first surface S1. The first vane B1 and the second vane B2 of each vane pair BP are combined to define one fixed stator vane.

In such a compressor C, at least one of the shape, attitude, or circumferential position of the vane pair BP is non-uniform among the vane pairs BP. Specifically, in the compressor C, the leading edge diameter, inlet blade angle, and angle between adjacent vane pairs BP are non-uniform among the vane pairs BP. With this configuration, pressure fluctuations in a specific frequency range can be avoided and resonance can be reduced. In addition, in the compressor C, one stationary blade is defined by two vanes B1 and B2 protruding from opposing surfaces S1 and S2. Therefore, the shape of the vane pair BP can be changed more flexibly. In addition, in the compressor C, both the first vane B1 and the second vane B2 are fixed. Therefore, no mechanism for moving them is required. This allows the device to be simplified.

In addition, in the compressor C, the total height of the first vane B1 and the second vane B2 is greater than the distance between the first surface S1 and the second surface S2. That is, the first vane B1 protruding from the first surface and the second vane B2 protruding from the second surface overlap in the central axis direction. Therefore, no gap is formed in the central axis direction between the surface of the diffuser passage 11 and the stator blade defined by the first vane B1 and the second vane B2. In addition, since the first vane B1 and the second vane B2 overlap in the central axis direction, even if the distance between the first surface S1 and the second surface S2 increases due to thermal expansion, it is possible to prevent a gap from being formed in the central axis direction. Therefore, it is possible to suppress a decrease in the efficiency of the compressor C due to thermal expansion.

In addition, in the compressor C, the first vane B1 and the second vane B2 are in at least partial contact with each other in the circumferential direction. Therefore, the amount of fluid flowing through the gap between the first vane B1 and the second vane B2 can be reduced. This makes it possible to suppress a decrease in the efficiency of the compressor C.

In addition, in the compressor C, the first vane B1 and the second vane B2 are combined so that the outer surface of the first vane B1 and the outer surface of the second vane B2 are continuous with each other. Therefore, the fluid flowing through the gap between the first vane B1 and the second vane B2 can be reduced. Therefore, the decrease in the efficiency of the compressor C can be suppressed.

Next, we will explain other embodiments.

Figure 4 is a schematic cross-sectional view showing a vane pair BP according to another embodiment, which corresponds to a cross-sectional view taken along line IV-IV in Figure 2. Note that in Figure 4, for better understanding, only the first surface S1, the second surface S2 and three vane pairs BP are shown. However, the compressor C1 may have more than three vane pairs BP. Also, in Figure 4, for better understanding, the first surface S1 and the second surface S2 are shown as planes.

In the embodiment of FIG. 4, the total height of the first vane B1 and the second vane B2 is not uniform among the vane pairs BP. For example, in FIG. 4, the height H1 of the first vane B1 of the upper vane pair BP is greater than the height H2 of the first vane B1 of the middle vane pair BP, and the height H2 is greater than the height H3 of the first vane B1 of the lower vane pair BP. The height of the second vane B2 is equal among the three vane pairs BP. Therefore, the total height of the first vane B1 and the second vane B2 of the upper vane pair BP is greater than the total height of the first vane B1 and the second vane B2 of the middle vane pair BP. Also, the total height of the first vane B1 and the second vane B2 of the middle vane pair BP is greater than the total height of the first vane B1 and the second vane B2 of the lower vane pair BP.

The total height of the first vane B1 and the second vane B2 may differ from one another among all of the plurality of vane pairs BP, including vane pairs BP not shown in FIG. 4. In contrast, the total height of the first vane B1 and the second vane B2 may differ from one another among only some of the plurality of vane pairs BP.

In FIG. 4, only the height H of the first vane B1 is non-uniform among the vane pairs BP. However, in other embodiments, the height of the second vane B2 may be non-uniform among the vane pairs BP as well, or only the height of the second vane B2 may be non-uniform among the vane pairs BP. For example, if the height H1 of the first vane B1 of the upper vane pair BP is greater than the height H2 of the first vane B1 of the middle vane pair BP, the height of the second vane B2 of the upper vane pair BP may be smaller or greater than the height of the second vane B2 of the middle vane pair BP.

Compressor C1, which has multiple vane pairs BP, has the same effect as compressor C described above.

Figure 5 is a schematic cross-sectional view showing a vane pair BP according to yet another embodiment, which corresponds to a cross-sectional view taken along line IV-IV in Figure 2. In Figure 5, for better understanding, only the first surface S1, the second surface S2 and three vane pairs BP are shown. However, the compressor C2 may have more than three vane pairs BP. Also, in Figure 5, for better understanding, the first surface S1 and the second surface S2 are shown as planes.

In the embodiment of FIG. 5, the total thickness of the first vane B1 and the second vane B2 is non-uniform among the vane pairs BP. The "thickness" of the first vane B1 and the second vane B2 means the "length in the circumferential direction" of the first vane B1 and the second vane B2. For example, in FIG. 5, the thickness W1 of the first vane B1 of the upper vane pair BP is smaller than the thickness W2 of the first vane B1 of the middle vane pair BP, and the thickness W2 is smaller than the thickness W3 of the first vane B1 of the lower vane pair BP. The thickness of the second vane B2 is equal among the three vane pairs BP. Therefore, the total thickness of the first vane B1 and the second vane B2 of the upper vane pair BP is smaller than the total thickness of the first vane B1 and the second vane B2 of the middle vane pair BP. In addition, the total thickness of the first vane B1 and the second vane B2 of the middle vane pair BP is smaller than the total thickness of the first vane B1 and the second vane B2 of the lower vane pair BP.

The total thickness of the first vane B1 and the second vane B2 may differ from one another among all of the vane pairs BP, including vane pairs BP not shown in FIG. 5. In contrast, the total thickness of the first vane B1 and the second vane B2 may differ from one another among only some of the vane pairs BP.

In FIG. 5, only the thickness W of the first vane B1 is non-uniform among the vane pairs BP. However, in other embodiments, the thickness of the second vane B2 may be non-uniform among the vane pairs BP as well, or only the thickness of the second vane B2 may be non-uniform among the vane pairs BP. For example, if the thickness W1 of the first vane B1 of the upper vane pair BP is smaller than the thickness W2 of the first vane B1 of the middle vane pair BP, the thickness of the second vane B2 of the upper vane pair BP may be smaller or larger than the thickness of the second vane B2 of the middle vane pair BP.

Compressor C2, which has multiple vane pairs BP, has the same effect as compressor C described above.

Although the embodiments have been described above with reference to the attached 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 modified or revised examples within the scope of the claims, and it is understood that these also naturally fall within the technical scope of the present disclosure.

For example, in the above embodiment, the centrifugal rotating device according to the present disclosure is applied to the compressor C of the turbocharger TC. However, in other embodiments, the centrifugal rotating device according to the present disclosure may be applied to the turbine T of the turbocharger TC.

For example, referring to FIG. 1, the nozzle 16 of the turbine T may include a first vane B3 and a second vane B4. The first vane B3 is fixed to a plate P1 attached to the turbine housing 3, and the second vane B4 is fixed to a plate P2 attached to the turbine housing 3. The first vane B3 protrudes in the central axis direction from the plate P1 toward the plate P2, and the second vane B4 protrudes in the central axis direction from the plate P2 toward the plate P1. The first vane B3 and the second vane B4 are combined to define one fixed stator vane. Such a turbine T includes a turbine impeller 8, a turbine housing 3 that houses the turbine impeller 8, and a plurality of vane pairs BP each including a first vane B3 and a second vane B4. The turbine housing 3 includes a first surface of a plate P1 and a second surface of a plate P2 that are located radially outward from the turbine impeller 8 and face each other in the central axial direction, and an annular flow passage 14 formed between the first surface of the plate P1 and the second surface of the plate P2. A plurality of vane pairs BP are arranged in the flow passage 14 along the circumferential direction.

Even among multiple vane pairs BP of such a turbine T, at least one of the shape, attitude, or circumferential position of the vane pair BP, for example, the trailing edge diameter (i.e., the inner circumferential side facing the rotor blade) of the vane pair BP, the combined thickness of the first vane B3 and the second vane B4, the outlet side (i.e., the inner circumferential side facing the rotor blade) blade angle of the vane pair BP, the combined height of the first vane B3 and the second vane B4, or the angle between adjacent vane pairs BP, may be non-uniform.

The centrifugal rotating device according to the present disclosure may also be applied to devices other than the turbocharger TC.

In the above embodiment, the total height of the first vane B1 and the second vane B2 is greater than the distance between the first surface S1 and the second surface S2 in the central axis direction. However, in other embodiments, the total height of the first vane B1 and the second vane B2 may be less than or equal to the distance between the first surface S1 and the second surface S2 in the central axis direction. In another expression, the first vane B1 and the second vane B2 may not overlap in the central axis direction. In yet another expression, there may be a gap in the central axis direction between the first vane B1 and the second vane B2.

REFERENCE SIGNS LIST 1 Housing 2 Bearing housing 3 Turbine housing 4 Compressor housing 8 Turbine impeller 9 Compressor impeller 11 Diffuser flow passage 14 Flow passage B1 First vane B2 Second vane B3 First vane B4 Second vane BP Vane pair C Compressor (centrifugal rotating device)
C1 Compressor (Centrifugal Rotating Device)
C2 Compressor (Centrifugal Rotating Device)
R1 Leading edge diameter R2 Leading edge diameter R3 Leading edge diameter S1 First surface S2 Second surface T Turbine (centrifugal rotating device)
α1 Angle between adjacent vane pairs α2 Angle between adjacent vane pairs β1 Inlet blade angle β2 Inlet blade angle β3 Inlet blade angle

Claims (6)

The impeller,
a housing that accommodates the impeller, the housing including a first surface and a second surface that are located radially outward with respect to the impeller and that face each other in a central axial direction of the impeller, and an annular flow path that is formed between the first surface and the second surface;
A plurality of vane pairs arranged in the flow passage along a circumferential direction of the impeller,
each of the plurality of vane pairs includes a first vane projecting from the first surface toward the second surface and a second vane projecting from the second surface toward the first surface;
the first vane and the second vane of each vane pair combine to define a fixed stator vane;
At least one of the shape, the attitude, or the position in the circumferential direction of the vane pairs is non-uniform among the plurality of vane pairs.
A plurality of vane pairs;
A centrifugal rotating device comprising: The centrifugal rotating device of claim 1, wherein the total height of the first vane and the second vane is non-uniform among the plurality of vane pairs. The centrifugal rotating device according to claim 1 or 2, wherein the edge diameters of the inner circumference of the vane pairs are non-uniform among the vane pairs. The centrifugal rotating device according to any one of claims 1 to 3, wherein the total thickness of the first vane and the second vane is non-uniform between the plurality of vane pairs. The centrifugal rotating device according to any one of claims 1 to 4, wherein the blade angles on the inner circumference side of the vane pairs are non-uniform among the vane pairs. The centrifugal rotating device according to any one of claims 1 to 5, wherein the angles between adjacent vane pairs are non-uniform among the plurality of vane pairs.

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