Rotating device

Abstract

To reduce the weight of the rotating device. [Solution] The rotating device C1 comprises an impeller 4, a housing 1 including an annular flow path 72, a plurality of vane bodies b1 arranged spaced apart from each other along the circumferential direction in the annular flow path 72, a plurality of first gears g1, each connected to each of the plurality of vane bodies b1, a plurality of second gears g2 arranged in some of a plurality of gaps between the plurality of first gears g1, each of the plurality of second gears g2 engaging with two adjacent first gears g1, and at least one actuator A1, A2 that rotates the plurality of first gears g1 and at least one of the plurality of second gears g2.

Description

Technical Field

[0001] The present disclosure relates to a rotating device.

Background Art

[0002] For example, a rotating device such as a centrifugal compressor may include a plurality of movable vanes disposed in a region radially outside the impeller. For example, Patent Document 1 discloses a centrifugal compressor including a plurality of movable vanes disposed in a diffuser flow path. The centrifugal compressor of Patent Document 1 includes a first drive ring for rotating a part of the plurality of vanes, a second drive ring for rotating the remaining of the plurality of vanes, a plurality of first drive links connecting the first drive ring and the vanes, and a plurality of second drive links connecting the second drive ring and the vanes.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] In this technical field, it may be desirable to further reduce the weight of the rotating device.

[0005] An object of the present disclosure is to provide a rotating device capable of reducing weight.

Means for Solving the Problems

[0006] To solve the above problems, a rotating device according to one aspect of the present disclosure includes an impeller; a housing that houses the impeller and includes an annular flow path located in a region radially outward of the impeller; a plurality of vane bodies arranged spaced apart from each other along the circumferential direction of the impeller in the annular flow path; a plurality of first gears, each connected to each of the plurality of vane bodies; a plurality of second gears, each of which is arranged in some of a plurality of gaps between the plurality of first gears, wherein each of the plurality of second gears engages with two adjacent first gears among the plurality of first gears; and at least one actuator for rotating the plurality of first gears and at least one of the plurality of second gears.

[0007] At least one of the multiple second gears may be a different adjustment gear from the others of the multiple second gears in terms of predetermined parameters, which may include at least one of diameter, number of teeth, distance from the axis of the impeller, and distance from an adjacent second gear among the multiple second gears.

[0008] The rotating device may be a centrifugal compressor, and the housing may include a scroll passage connected to an annular passage, and a tongue positioned between the annular passage and the scroll passage, and the adjusting gear may engage with a first gear of at least one of two vane bodies that form the space closest to the tongue in the flow of gas through the centrifugal compressor, among a plurality of spaces between the vane bodies, and the adjusting gear may differ from the others of a plurality of second gears in predetermined parameters such that the width of the space closest to the tongue is adjustable to be less than the width of the remaining spaces.

[0009] At least one actuator may include multiple actuators, and the multiple first gears and multiple second gears may form a single continuous force transmission path such that the force from each of the multiple actuators is transmitted to all of the multiple first gears and multiple second gears.

[0010] The number of multiple first gears N1, the number of multiple second gears N2, and the number of at least one actuator Na may satisfy the following equation (1). N1-1≧N2≧N1-Na···(1)

[0011] At least one actuator may include multiple actuators, and the multiple first gears and multiple second gears may form multiple independent force transmission paths, and the multiple force transmission paths may receive forces from different actuators among the multiple actuators. [Effects of the Invention]

[0012] According to this disclosure, the weight of the rotating device can be reduced. [Brief explanation of the drawing]

[0013] [Figure 1] Figure 1 is a schematic cross-sectional view of a turbocharger equipped with a centrifugal compressor according to the first embodiment. [Figure 2] Figure 2 is a schematic enlarged cross-sectional view of section Z in Figure 1. [Figure 3] Figure 3 is a schematic cross-sectional view obtained along the line III-III in Figure 1. [Figure 4] Figure 4 is a schematic cross-sectional view showing a centrifugal compressor according to the second embodiment. [Figure 5] Figure 5 is a schematic cross-sectional view showing a centrifugal compressor according to the third embodiment. [Figure 6] Figure 6 is a schematic cross-sectional view showing a centrifugal compressor according to the fourth embodiment. [Figure 7] Figure 7 is a schematic enlarged cross-sectional view of section Y in Figure 6. [Modes for carrying out the invention]

[0014] An embodiment of the present disclosure will be described below with reference to the accompanying drawings. The specific dimensions, materials, numerical values, etc. shown in the embodiment are merely examples for easy understanding and do not limit the present disclosure unless otherwise specified. In the present specification and drawings, elements having substantially the same functions and configurations are denoted by the same reference numerals to omit redundant descriptions, and elements not directly related to the present disclosure are not shown.

[0015] FIG. 1 is a schematic cross-sectional view of a supercharger TC including a centrifugal compressor C1 according to the first embodiment. In the present embodiment, the centrifugal compressor C1 is applied to the supercharger TC. For example, in other embodiments, the centrifugal compressor C1 may be applied to other devices such as an electric compressor, or may be a single unit. For example, the centrifugal compressor C1 of the present disclosure may be applied to a centrifugal compressor used in an aircraft.

[0016] For example, the supercharger TC includes a housing 1, a shaft 2, a turbine impeller 3, and a compressor impeller (impeller) 4.

[0017] As will be described later, the turbine impeller 3 and the compressor impeller 4 rotate integrally with the shaft 2. Therefore, in the present 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", "radial direction", and "circumferential direction", respectively, unless otherwise indicated. Further, in the present disclosure, the axis of the shaft 2, the turbine impeller 3, and the compressor impeller 4 may be simply referred to as the "axis" unless otherwise indicated.

[0018] The housing 1 includes a bearing housing 5, a turbine housing 6, and a compressor housing 7. In the axial direction, one end of the bearing housing 5 is connected to the turbine housing 6. In the axial direction, the other end of the bearing housing 5 is connected to the compressor housing 7.

[0019] The bearing housing 5 includes a bearing hole 51. The bearing hole 51 extends in the axial direction within the bearing housing 5. The bearing hole 51 houses a bearing 8. The bearing 8 rotatably supports the shaft 2. In this embodiment, two rolling bearings are shown as the bearing 8. However, the number of rolling bearings is not limited to two. Also, for example, in other embodiments, other radial bearings such as a full floating bearing or a semi-floating bearing may be used as the bearing 8.

[0020] In the axial direction, a turbine impeller 3 is provided at the first end of the shaft 2. The turbine impeller 3 rotates integrally with the shaft 2. The turbine housing 6 houses the turbine impeller 3.

[0021] In the axial direction, a compressor impeller 4 is provided at the second end of the shaft 2 on the side opposite to the first end. The compressor impeller 4 rotates integrally with the shaft 2. The compressor housing 7 houses the compressor impeller 4.

[0022] The compressor housing 7 includes an air inlet 71 at an end in the axial direction opposite to the bearing housing 5. For example, the air inlet 71 is connected to an air cleaner (not shown).

[0023] The bearing housing 5 and the compressor housing 7 define a diffuser flow path (annular flow path) 72 therebetween. The diffuser flow path 72 has an annular shape. The diffuser flow path 72 is located in a region radially outside the compressor impeller 4. The diffuser flow path 72 is in fluid communication with the air inlet 71 via the compressor impeller 4.

[0024] A plurality of diffuser vanes (movable vanes) V1 are arranged in the diffuser flow path 72. The plurality of diffuser vanes V1 are arranged spaced apart from each other along the circumferential direction. The diffuser vanes V1 will be described in detail later.

[0025] The compressor housing 7 includes a compressor scroll channel (scroll channel) 73. For example, the compressor scroll channel 73 is located in the radially outer region of the diffuser channel 72. The compressor scroll channel 73 is connected to the diffuser channel 72. The compressor scroll channel 73 is also in fluid communication with an unillustrated device that receives compressed air from the centrifugal compressor C1.

[0026] As the compressor impeller 4 rotates, air is drawn into the compressor housing 7 from the intake port 71. The air is accelerated and pressurized by centrifugal force as it passes through the compressor impeller 4. The air is further pressurized as it passes through the diffuser passage 72 and flows into the compressor scroll passage 73. The pressurized air flows out from an outlet (not shown) and is led to equipment (not shown). In the supercharger TC, the portion including the compressor impeller 4 and the compressor housing 7 functions as a centrifugal compressor C1.

[0027] The turbine housing 6 includes a discharge port 61 at the end opposite to the bearing housing 5 in the axial direction. For example, the discharge port 61 is connected to an exhaust gas purification device (not shown).

[0028] The turbine housing 6 includes a connecting channel (annular channel) 62. The connecting channel 62 has an annular shape. The connecting channel 62 is located in the radially outer region of the turbine impeller 3. The connecting channel 62 is in fluid communication with the discharge port 61 via the turbine impeller 3.

[0029] Multiple nozzle vanes V2 are arranged in the connecting channel 62. The multiple nozzle vanes V2 are spaced apart from each other along the circumferential direction. In this embodiment, the nozzle vanes V2 are fixed. In other embodiments, the nozzle vanes V2 may be movable and rotatable about a rotation axis parallel to the axis.

[0030] The turbine housing 6 includes a turbine scroll flow path 63. For example, the turbine scroll flow path 63 is located in a region radially outward from the connecting flow path 62. The turbine scroll flow path 63 is connected to the connecting flow path 62. The turbine scroll flow path 63 is also in fluid communication with a gas inlet (not shown). For example, the gas inlet receives exhaust gas discharged from equipment (not shown).

[0031] The exhaust gas is guided from the gas inlet to the turbine scroll passage 63, and further guided to the discharge port 61 via the connecting passage 62 and the turbine impeller 3. As the exhaust gas passes through the turbine impeller 3, it rotates the turbine impeller 3. The rotational force of the turbine impeller 3 is transmitted to the compressor impeller 4 via the shaft 2. As the compressor impeller 4 rotates, the air is pressurized as described above. In the supercharger TC, the portion including the turbine impeller 3 and the turbine housing 6 functions as the turbine T.

[0032] Next, we will explain the diffuser vane V1 in detail.

[0033] Figure 2 is a schematic enlarged cross-sectional view of section Z in Figure 1.

[0034] The diffuser vane V1 is rotatable around a rotation axis x1 parallel to the axis of the compressor impeller 4. In this embodiment, the diffuser vane V1 includes a vane body b1 and a first gear g1.

[0035] The vane body b1 is positioned in the diffuser channel 72. The vane body b1 changes the direction of the airflow through the diffuser channel 72 according to the angle around the rotation axis x1.

[0036] Figure 3 is a schematic cross-sectional view obtained along the line III-III in Figure 1. Note that Figures 3, as well as Figures 4, 5, and 6 described below, show only the vane body b1, the first gear g1, the second gear g2 (described later), the compressor impeller 4, and the inner wall of the housing 1 for better understanding. Furthermore, in Figures 3, 4, 5, and 6, the vane body b1 in the first position (which may also be referred to as the "reference position" in this disclosure) is shown by a solid line, and the vane body b1 in a second position different from the first position is shown by a dashed line. In this disclosure, the "position" of the vane body b1 may mean the angle of the vane body b1 with respect to the radial direction when viewed in the axial direction. Additionally, in Figures 3, 4, 5, and 6, the compressor impeller 4, the first gear g1, and the second gear g2 are simply shown as circles.

[0037] In this embodiment, the multiple vane bodies b1 are arranged on the same circle L1 centered on the axis x0 of the compressor impeller 4. In other words, in this embodiment, the distance from the axis x0 of the compressor impeller 4 to the axis of rotation x1 of the multiple vane bodies b1 is equal to that of the other. In this embodiment, the multiple vane bodies b1 are arranged at equal intervals along the circumferential direction. In this embodiment, the angle around the axis of rotation x1, i.e., the angle (orientation) with respect to the radial direction, is equal among the multiple vane bodies b1.

[0038] Referring to Figure 2, the first gear g1 is connected to one of the axial end faces of the vane body b1. For example, the vane body b1 may be provided with an annular flange to reduce air leakage, and the first gear g1 may be formed on the flange. The first gear g1 is provided with a first shaft s1. The first shaft s1 protrudes axially from the end face of the first gear g1 opposite to the vane body b1. For example, the first shaft s1 is rotatably supported in a hole formed in the bearing housing 5. The first gear g1 and the first shaft s1 rotate integrally with the vane body b1. Therefore, the axis of rotation x1 of the vane body b1 coincides with the axis of the first gear g1 and the first shaft s1.

[0039] For example, in this embodiment, the first gear g1 is a spur gear. For example, in other embodiments, the first gear g1 may be an external gear other than a spur gear. For example, the vane body b1, the first gear g1, and the first shaft s1 may be formed integrally with each other. In other embodiments, the vane body b1, the first gear g1, and the first shaft s1 may be formed separately and then connected to each other.

[0040] Referring to Figure 3, in this embodiment, the multiple first gears g1 are arranged on the same circle L1 centered on the axis x0 of the compressor impeller 4. In other words, as described above, in this embodiment, the distances from the axis x0 of the compressor impeller 4 to the multiple axes x1 are equal to each other. In this embodiment, the multiple first gears g1 are arranged at equal intervals in the circumferential direction.

[0041] Referring to Figure 2, the centrifugal compressor C1 is equipped with multiple second gears g2.

[0042] The second gear g2 engages with the first gear g1. The second gear g2 is provided with a second shaft s2. The second shaft s2 protrudes axially from one of the end faces of the second gear g2 in the axial direction. For example, the second shaft s2 is rotatably supported in a hole formed in the bearing housing 5. In this embodiment, the second gear g2 and the second shaft s2 are rotatable about a rotation axis x2 parallel to the axis of the compressor impeller 4.

[0043] For example, in this embodiment, the second gear g2 is a spur gear. For example, in other embodiments, the second gear g2 may be an external gear other than a spur gear. For example, the second gear g2 and the second shaft s2 may be formed integrally with each other. In other embodiments, the second gear g2 and the second shaft s2 may be formed separately and then connected to each other.

[0044] Referring to Figure 3, in this embodiment, the multiple second gears g2 are positioned in all of the multiple gaps between the multiple first gears g1. Therefore, in this embodiment, the number of first gears g1 N1 and the number of second gears g2 N2 are equal (N1 = N2).

[0045] Each second gear g2 engages with two adjacent first gears g1. Furthermore, as described above, in this embodiment, the multiple second gears g2 are positioned in all of the gaps between the multiple first gears g1. Therefore, in this embodiment, the first gears g1 and second gears g2 form a single continuous force transmission path in the circumferential direction. In other words, in this embodiment, the first gears g1 and second gears g2 form a single closed force transmission path.

[0046] In other embodiments, the number N2 of the second gear g2 may be one less than the number N1 of the first gear g1. In this case as well, the first gear g1 and the second gear g2 can form a single continuous force transmission path. In this case, the force transmission path is discontinuous at one point in the circumferential direction, i.e., it does not form a circular shape, so the first gear g1 and the second gear g2 form a single open force transmission path. Note that when the first gear g1 and the second gear g2 form a single closed force transmission path as described above, backlash between the first gear g1 and the second gear g2 can be reduced.

[0047] In this embodiment, the multiple second gears g2 are arranged on the same circle L2 centered on the axis x0 of the compressor impeller 4. In other words, in this embodiment, the distances from the axis x0 of the compressor impeller 4 to the multiple rotation axes x2 are equal to each other. In this embodiment, the multiple second gears g2 are arranged at equal intervals in the circumferential direction. The circle L2 on which the multiple second gears g2 are arranged is larger than the circle L1 on which the multiple first gears g1 are arranged. In other words, the distance from the axis x0 of the compressor impeller 4 to the rotation axis x2 is greater than the distance from the axis x0 to the rotation axis x1.

[0048] For example, in this embodiment, the diameter of the second gear g2 (e.g., the pitch circle diameter) is larger than the diameter of the first gear g1. Therefore, in this embodiment, the number of teeth of the second gear g2 is greater than the number of teeth of the first gear g1. For example, in another embodiment, the diameter of the second gear g2 may be smaller than the diameter of the first gear g1. In this case, the number of teeth of the second gear g2 may be less than the number of teeth of the first gear g1. Furthermore, in yet another embodiment, the diameter of the second gear g2 may be equal to the diameter of the first gear g1. In this case, the number of teeth of the second gear g2 may be the same as the number of teeth of the first gear g1.

[0049] Referring to Figure 2, for example, the bearing housing 5 may include grooves 52 for accommodating the first gear g1 and the second gear g2. In other embodiments, the grooves 52 may be formed in an annular plate, and the annular plate may be fixed to the bearing housing 5 (not shown).

[0050] Referring to Figure 3, the centrifugal compressor C1 includes at least one actuator that rotates at least one of a plurality of first gears g1 and a plurality of second gears g2. In this embodiment, the centrifugal compressor C1 includes two actuators A1 and A2. The number of actuators is not limited to two, and may be one or three or more. For example, the plurality of actuators A1 and A2 may be arranged at equal intervals in the circumferential direction.

[0051] In this embodiment, actuators A1 and A2 rotate two of the multiple second gears g2. In other embodiments, one or both actuators A1 and A2 may rotate one or two of the multiple first gears g1.

[0052] In this embodiment, two actuators A1 and A2 work together to rotate all of the first gear g1 and second gear g2. Therefore, the power required for each actuator A1 and A2 is reduced compared to, for example, a case where all of the first gear g1 and second gear g2 are rotated by a single actuator. Thus, the size of each actuator A1 and A2 can be reduced. For example, in the field of aircraft, it is desirable to further reduce the frontal area. According to this embodiment, since the size of each actuator A1 and A2 can be reduced, it can lead to a reduction in the total frontal area of ​​the centrifugal compressor C1.

[0053] Furthermore, in this embodiment, the force from each actuator A1 and A2 is transmitted to all first gears g1 and second gears g2. Therefore, even if one of actuators A1 or A2 is not functioning, all first gears g1 and second gears g2 can be rotated by the other actuator A1 or A2. Thus, the durability of the centrifugal compressor C1 can be improved.

[0054] Referring to Figure 1, for example, actuators A1 and A2 may be located outside the housing 1. Note that only actuator A1 is shown in Figure 1. For example, actuators A1 and A2 may be mounted on the outer surface of the bearing housing 5. In other embodiments, actuators A1 and A2 may be located at other positions on the centrifugal compressor C1. For example, actuators A1 and A2 may be motors. In other embodiments, the centrifugal compressor may be equipped with other types of actuators other than motors.

[0055] Referring to Figure 3, in the centrifugal compressor C1 described above, actuators A1 and A2 rotate two of the multiple second gears g2. As described above, in this embodiment, the first gear g1 and the second gear g2 form a single force transmission path that is continuous in the circumferential direction. Therefore, the force transmitted from actuators A1 and A2 to the two second gears g2 is further transmitted to all of the first gears g1 and second gears g2. When all of the first gears g1 rotate, all of the vane bodies b1 rotate simultaneously. In this way, the direction of the airflow through the diffuser channel 72 can be changed.

[0056] The centrifugal compressor C1 described above comprises a compressor impeller 4, a housing 1 that houses the compressor impeller 4 and includes a diffuser flow path 72 located in the radially outer region of the compressor impeller 4, a plurality of vane bodies b1 arranged spaced apart from each other along the circumferential direction in the diffuser flow path 72, a first gear g1, each connected to each of the plurality of vane bodies b1, and a plurality of second gears g2 arranged in some of the gaps between the plurality of first gears g1. Each second gear g2 engages with two adjacent first gears g1. Furthermore, the centrifugal compressor C1 includes at least one actuator A1, A2 that rotates at least one of the plurality of first gears g1 and the plurality of second gears g2. With such a configuration, for example, compared to Patent Document 1, the drive ring and drive link for transmitting force from the actuator can be eliminated. For example, if the drive ring is located in the radially outer region of the movable vane, the volume and weight of the drive ring tend to increase. Therefore, removing the drive ring leads to weight reduction. For example, in the field of aircraft in particular, it is desirable to reduce the weight of each component. According to this embodiment, the weight of the centrifugal compressor C1 can be reduced.

[0057] Furthermore, the centrifugal compressor C1 includes multiple actuators A1 and A2, and multiple first gears g1 and multiple second gears g2 form a single continuous force transmission path such that the force from each of the actuators A1 and A2 is transmitted to all of the first gears g1 and multiple second gears g2. With this configuration, the size of each actuator A1 and A2 can be reduced. Therefore, for example, the total frontal area of ​​the centrifugal compressor C1 can be reduced. Also, even if one of the actuators A1 and A2 is not functioning, all of the first gears g1 and second gears g2 can be rotated by the other actuator A1 or A2. Thus, the durability of the centrifugal compressor C1 can be improved.

[0058] Next, other embodiments will be described.

[0059] Figure 4 is a schematic cross-sectional view showing a centrifugal compressor C2 according to the second embodiment. Similar to Figure 3, Figure 4 corresponds to a cross-sectional view obtained along the line III-III in Figure 1.

[0060] The centrifugal compressor C2 differs from the centrifugal compressor C1 according to the first embodiment in that it comprises only a single actuator A1. In other configurations, the centrifugal compressor C2 may be the same as the centrifugal compressor C1.

[0061] In the centrifugal compressor C2 described above, similar to the centrifugal compressor C1 of the first embodiment, the drive ring and drive link for transmitting force from the actuator can be eliminated compared to Patent Document 1. Therefore, the weight of the centrifugal compressor C1 can be reduced.

[0062] Figure 5 is a schematic cross-sectional view showing a centrifugal compressor C3 according to the third embodiment. Similar to Figures 3 and 4, Figure 5 corresponds to a cross-sectional view obtained along the line III-III in Figure 1.

[0063] The centrifugal compressor C3 differs from the centrifugal compressor C1 according to the first embodiment in the number N2 of the second gear g2. For other configurations, the centrifugal compressor C3 may be the same as the centrifugal compressor C1.

[0064] Specifically, in centrifugal compressor C3, the first gear g1, the second gear g2, and actuators A1 and A2 satisfy the following equation (1). N1-1≧N2≧N1-Na···(1) Here, N1: Number of gears in the first gear N2: Number of gears in the second gear Na: Number of actuators

[0065] More specifically, in centrifugal compressor C3, the number of first gears g1 N1 is 18, and the number of actuators A1 and A2 is 2.

[0066] However, in centrifugal compressor C3, the number of second gears g2 N2 is 16. Specifically, centrifugal compressor C3 does not have a second gear g2 located to the right of the second gear g2 driven by actuator A1 in Figure 5. Also, centrifugal compressor C3 does not have a second gear g2 located to the left of the second gear g2 driven by actuator A2 in Figure 5.

[0067] With the configuration described above, the first gear g1 and the second gear g2 form two independent force transmission paths. In other words, in this embodiment, the first gear g1 and the second gear g2 form two open force transmission paths. From another viewpoint, the force transmission paths of the first gear g1 and the second gear g2 are divided into two force transmission paths.

[0068] In this embodiment, the two actuators A1 and A2 operate independently of each other. Actuator A1 rotates the first gear g1 and second gear g2 of one of the two force transmission paths (the left half of the first gear g1 and second gear g2 in Figure 5), while actuator A2 rotates the first gear g1 and second gear g2 of the other of the two force transmission paths (the right half of the first gear g1 and second gear g2 in Figure 5).

[0069] With the above configuration, the number N2 of the second gear g2 can be reduced. Therefore, the weight of the centrifugal compressor C3 can be further reduced.

[0070] Furthermore, with the above configuration, the two actuators A1 and A2 operate independently of each other. Therefore, it is not necessary to strictly synchronize the operation of actuator A1 and actuator A2.

[0071] In other embodiments, the number of actuators Na may be three or more. In this case, the number N2 of the second gear g2 can be reduced by a maximum of the number of actuators Na, and the force transmission paths of the first gear g1 and the second gear g2 can be divided into several force transmission paths, up to a maximum of the number of actuators Na.

[0072] The centrifugal compressor C3 described above has the same effects as the centrifugal compressor C1 of the first embodiment.

[0073] Furthermore, in the centrifugal compressor C3, the number of first gears g1 N1, the number of second gears g2 N2, and the number of actuators A1 and A2 Na satisfy the following equation (1). N1-1≧N2≧N1-Na···(1) With the above configuration, the number N2 of the second gear g2 can be reduced. Therefore, the weight of the centrifugal compressor C3 can be further reduced.

[0074] Furthermore, the centrifugal compressor C3 includes multiple actuators A1 and A2, and multiple first gears g1 and multiple second gears g2 form two independent force transmission paths, with the two force transmission paths receiving force from different actuators A1 and A2. With this configuration, the two actuators A1 and A2 operate independently of each other. Therefore, it is not necessary to strictly synchronize the operation of actuators A1 and A2.

[0075] Figure 6 is a schematic cross-sectional view showing the centrifugal compressor C4 according to the fourth embodiment. Similar to Figures 3, 4, and 5, Figure 6 corresponds to a cross-sectional view obtained along the line III-III in Figure 1. Note that the vane body b1 in the second position (dashed line in Figures 3, 4, and 5) is not shown in Figure 6.

[0076] The centrifugal compressor C4 differs from the centrifugal compressor C1 according to the first embodiment in the configuration of the diffuser vane V1a positioned upstream of the tongue portion 74, and the second gears g2a and g2b that engage with the diffuser vane V1a. In other configurations, the centrifugal compressor C4 may be the same as the centrifugal compressor C1.

[0077] Specifically, a tongue portion 74 is formed between the diffuser flow path 72 and the compressor scroll flow path 73. The tongue portion 74 protrudes from the inner wall of the housing 1 toward the flow path.

[0078] A space S is defined between each pair of adjacent vane bodies b1. The vane body b1a of the diffuser vane V1a is one of two vane bodies b1 that form the space Sa closest to the tongue 74, i.e., located immediately upstream of the tongue 74, in the gas flow through the centrifugal compressor C4, out of the multiple spaces S between the multiple vane bodies b1.

[0079] Figure 7 is a schematic enlarged cross-sectional view of section Y in Figure 6. In Figure 7, the vane body b1 in the first position is shown by a solid line, and the vane body b1 in the second position is shown by a dashed line.

[0080] The rotation axis x1a of diffuser vane V1a is positioned differently from the rotation axis x1 of other diffuser vanes V1. Specifically, in this embodiment, the rotation axis x1a of diffuser vane V1a is positioned in a region radially outward from the rotation axis x1 of other diffuser vanes V1. In other words, in this embodiment, the rotation axis x1 of diffuser vane V1 is positioned near the leading edge L of diffuser vane V1, while the rotation axis x1a of diffuser vane V1a is positioned near the center of diffuser vane V1.

[0081] With this configuration, in the first attitude, as shown by the solid line, the attitudes of diffuser vane V1a and the other diffuser vanes V1 are the same. Therefore, in the first attitude, the throat width t0a defined in space Sa is equal to the throat width t0 defined in the other space S. In this disclosure, "throat width" may also be referred to as "inter-wing width".

[0082] However, since the axis of rotation x1a of diffuser vane V1a is located near the center of diffuser vane V1, the leading edge La of diffuser vane V1a moves more, as shown by the dashed line. Therefore, in the second orientation, the orientation of diffuser vane V1a differs from that of the other diffuser vane V1, as shown by the dashed line. Consequently, in the second orientation, the throat width t1a defined in space Sa is narrower than the throat width t1 defined in the other space S.

[0083] A portion of the airflow from the space Sa located upstream of the tongue to the compressor scroll channel 73 is obstructed by the tongue 74. Consequently, a pressure distribution occurs in the opposite direction to the airflow, i.e., from the tongue 74 towards space Sa. This can lead to a decrease in the fatigue strength of the diffuser vane V1 around the tongue 74.

[0084] In this embodiment, as described above, the throat width t1a defined in space Sa is narrower than the throat width t1 defined in other spaces S, so the amount of air passing through space Sa can be reduced. Therefore, the pressure distribution generated by the tongue portion 74 can be reduced.

[0085] To achieve the above configuration, in this embodiment, the first gear g1a of the diffuser vane V1a is positioned in the region radially outward of the first gear g1 of the other diffuser vane V1.

[0086] Furthermore, in this embodiment, the two second gears g2a and g2b that engage with the first gear g1a of the diffuser vane V1a function as adjustment gears that differ from the other second gear g2 under predetermined parameters.

[0087] Referring to Figure 6, for example, the "predetermined parameter" may be at least one of the following: the diameter of the second gear g2 (e.g., the pitch circle diameter), the number of teeth of the second gear g2, the distance from the axis x0 of the compressor impeller 4 to the axis of rotation x2, and the distance from the adjacent second gear g2 to the adjustment gear.

[0088] Specifically, in this embodiment, the diameter of the second gear g2a is larger than the diameter of the other second gear g2. In other words, the number of teeth of the second gear g2a is greater than the number of teeth of the other second gear g2. Also, in this embodiment, the distance from the axis x0 of the compressor impeller 4 to the rotation axis x2a of the second gear g2a is greater than the distance from the axis x0 to the rotation axis x2 of the other second gear g2.

[0089] Furthermore, in this embodiment, the diameter of the second gear g2b is smaller than the diameter of the other second gear g2. In other words, the number of teeth of the second gear g2b is fewer than the number of teeth of the other second gear g2. Also, in this embodiment, the distance from the axis x0 of the compressor impeller 4 to the rotation axis x2b of the second gear g2b is smaller than the distance from the axis x0 to the rotation axis x2 of the other second gear g2. Moreover, in this embodiment, the distance from the second gear g2b to the adjacent second gear g2 (the second gear g2 on the right) is larger than the distance between the other second gears g2.

[0090] The centrifugal compressor C4 described above has the same effects as the centrifugal compressor C1 of the first embodiment.

[0091] Furthermore, in the centrifugal compressor C4, at least one of the multiple second gears g2 is a regulating gear g2a, g2b that differs from the others of the multiple second gears g2 in predetermined parameters, the predetermined parameters include at least one of diameter, number of teeth, distance from the axis x0 of the compressor impeller 4, and distance from adjacent second gears g2. With such a configuration, it is possible to individually set the predetermined orientation of the diffuser vane V1a.

[0092] Furthermore, in this embodiment, the rotating device is a centrifugal compressor C4, and the housing 1 includes a compressor scroll channel 73 connected to a diffuser channel 72, and a tongue portion 74 positioned between the diffuser channel 72 and the compressor scroll channel 73. The regulating gears g2a and g2b engage with at least one first gear g1a of two vane bodies b1 that form the space Sa closest to the tongue portion 74 in the flow of gas through the centrifugal compressor C4, among a plurality of spaces S between the plurality of vane bodies b1. The regulating gears g2a and g2b differ from the others among a plurality of second gears g2 in predetermined parameters so that the width t1a of the space Sa closest to the tongue portion 74 can be adjusted to be smaller than the remaining width t1 of the plurality of spaces S. With this configuration, the pressure distribution generated by the tongue portion 74 can be reduced.

[0093] Although one embodiment of the present disclosure has been described above with reference to the attached drawings, it goes without saying that the present disclosure is not limited to this embodiment. It will be obvious to those skilled in the art that various modifications or alterations can be conceived within the scope of the claims, and these will naturally also fall within the technical scope of the present disclosure.

[0094] For example, in the above embodiment, the rotating device of the Disclosure is applied to centrifugal compressors C1, C2, C3, and C4. Referring to Figure 1, for example, in another embodiment, the rotating device of the Disclosure may be applied to a turbine T. Specifically, the nozzle vanes V2 of the turbine T may be movable vanes that can rotate about a rotation axis parallel to the axis, and the configuration of the Disclosure may be applied to a device for rotating the nozzle vanes V2.

[0095] Furthermore, for example, in centrifugal compressor C3, the number of first gears g1 N1, the number of second gears g2 N2, and the number of actuators A1 and A2 Na satisfy the following equation (1). N1-1≧N2≧N1-Na···(1) The above equation (1) is also satisfied, for example, in the centrifugal compressor C1 according to the first embodiment, when the number of second gears g2 N2 is one less than the number of first gears g1 N1; in the centrifugal compressor C2 according to the second embodiment, when the number of second gears g2 N2 is one less than the number of first gears g1 N1; and in the centrifugal compressor C4 according to the fourth embodiment, when the number of second gears g2 N2 is one or two less than the number of first gears g1 N1. [Explanation of symbols]

[0096] 1 Housing 4. Compressor impeller 72 Diffuser channel (annular channel) 73 Compressor scroll channel (scroll channel) 74 Tongue A1 Actuator A2 Actuator b1 vane body b1a The vane body that defines the space closest to the tongue. C1 Centrifugal compressor (rotating device) C2 Centrifugal compressor (rotating device) C3 Centrifugal compressor (rotating device) C4 Centrifugal compressor (rotating device) g1 First gear g1a The first gear of the vane body that defines the space closest to the tongue. g2 Second gear g2a Second gear (adjustment gear) g2b Second gear (adjustment gear) N1 Number of first gears Number of second gears N2 Number of Na actuators S Space between diffuser vanes Sa: The space closest to the tongue t0 Throat width (width of space) t0a Throat width (width of space) t1 Throat width (width of space) t1a Throat width (width of space) x0 Axis of the compressor propeller

Claims

1. impeller and, A housing that houses the impeller and includes an annular channel located in the radially outer region of the impeller, In the annular flow path, a plurality of vane bodies are arranged spaced apart from each other along the circumferential direction of the impeller, Each of the multiple first gears is connected to each of the multiple vane bodies, A plurality of second gears positioned in some of the gaps between the plurality of first gears, each of the plurality of second gears engaging with two adjacent first gears among the plurality of first gears, At least one actuator that rotates at least one of the plurality of first gears and the plurality of second gears, Equipped with, Rotating device.

2. At least one of the plurality of second gears is an adjustment gear that differs from the others of the plurality of second gears in a predetermined parameter. The predetermined parameters include at least one of the diameter, the number of teeth, the distance from the axis of the impeller, and the distance from an adjacent second gear among the plurality of second gears. The rotating device according to claim 1.

3. The aforementioned rotating device is a centrifugal compressor, The aforementioned housing is A scroll channel connected to the aforementioned annular channel, A tongue portion is disposed between the annular channel and the scroll channel, Includes, The adjusting gear engages with the first gear of at least one of the two vane bodies that define the space closest to the tongue in the gas flow through the centrifugal compressor, among the multiple spaces between the multiple vane bodies. The adjusting gear is configured such that the width of the space closest to the tongue is adjustable to be smaller than the width of the remaining spaces among the plurality of gears, with a predetermined parameter different from that of the other second gears. The rotating device according to claim 2.

4. The at least one actuator includes a plurality of actuators, The plurality of first gears and the plurality of second gears form a single continuous force transmission path such that the force from each of the plurality of actuators is transmitted to all of the plurality of first gears and the plurality of second gears. The rotating device according to claim 1.

5. The rotating device according to claim 1, wherein the number N1 of the plurality of first gears, the number N2 of the plurality of second gears, and the number Na of at least one actuator satisfy the following formula (1). N1-1≧N2≧N1-Na...(1)

6. The at least one actuator includes a plurality of actuators, The plurality of first gears and the plurality of second gears form a plurality of independent force transmission paths. The aforementioned multiple force transmission paths receive force from different actuators among the aforementioned multiple actuators. The rotating device according to claim 5.

Images