Turbo Fluid Machinery

Abstract

To provide a turbo type fluid machine capable of effectively cooling a foil bearing without making the axial body large.SOLUTION: A second plate 16 which partitions the inside of a housing 11 into a first impeller chamber 13b where a first impeller 25 is housed and a thrust bearing housing chamber S2 where a thrust foil bearing 30 is housed comprises a support part 60 which has an end face 60a protruding axially toward a third supported part 24d. In the end face 60a of the support part 60, a grooved passage 61 is recessed which extends radially up to an outer peripheral surface. One foil bearing 30 is fitted to the end face 60a of the support part 60 so that the position of the passage 61 corresponds to the position of a gap between bump foils 32 and the position of a gap between top foils 32 and the third supported part 24d and the passage 61 face each other in the axial direction.SELECTED DRAWING: Figure 6

Description

[Technical field]

[0001] The present invention relates to a turbo fluid machine. [Background technology]

[0002] Patent Document 1 discloses a conventional turbo fluid machine. This turbo fluid machine includes a rotating shaft that rotates about an axis, a plate-shaped thrust collar, an actuator, and a housing that accommodates the rotating shaft, the thrust collar, and the actuator. The thrust collar extends radially from the circumferential surface of the rotating shaft and is capable of rotating integrally with the rotating shaft. The actuator rotates integrally with the rotating shaft to pump an external fluid.

[0003] The turbo fluid machine further includes a plate-shaped support member and a foil bearing. The support member has an insertion hole through which the rotating shaft is inserted. The foil bearing supports the thrust collar in the axial direction of the rotating shaft so as to be rotatable relative to the support member.

[0004] The foil bearing comprises a plurality of bump foils made of corrugated elastic thin plates, and a number of top foils made of elastic thin plates. The bump foils are attached in a line with intervals around the insertion hole on the end face of the shaft support member on the thrust collar side. One surface of the top foil faces the thrust collar, and the other surface is elastically supported by each bump foil. The end face of the top foil on the thrust collar side serves as a bearing surface, and the end face of the thrust collar on the top foil side serves as a borne surface that faces the bearing surface in the axial direction.

[0005] In foil bearings, the top foil supports the thrust collar that rotates relative to the shaft when the shaft is rotating at low speeds, and supports the thrust collar in a non-contact state when the shaft is rotating at high speeds with a fluid film that forms in the bearing gap between the bearing surface and the bearing surface.

[0006] In this type of foil bearing, the top foil is made of an elastic thin plate with a small heat capacity and is therefore prone to becoming hot, which can cause problems with the heat resistance of the top foil.

[0007] In the conventional turbo fluid machine described above, a cooling passage for cooling the foil bearing is provided in the housing (third embodiment, see Figs. 7 and 8). The cooling fluid in the cooling passage is introduced into a space on the opposite side of the thrust collar with respect to the support member (hereinafter referred to as "opposite side space" as appropriate). The fluid introduced into the opposite side space is guided to a space between the support member and the thrust collar (hereinafter referred to as "bearing space" as appropriate) via a gap between the insertion hole of the support member and the rotating shaft, and a through hole penetrating the support member in the axial direction. The cooling fluid guided to the bearing space flows radially outward through a circumferential gap extending radially between circumferentially adjacent bump foils to cool the top foil and the bump foils. [Prior art documents] [Patent documents]

[0008] [Patent Document 1] International Publication No. 2020 / 130124 Summary of the Invention [Problem to be solved by the invention]

[0009] However, in such a turbo fluid machine, when the opposite space includes a compression space in which the working body is accommodated, a partition wall that separates the compression space from the support member must be provided in the opposite space to prevent a decrease in the compression efficiency of the external fluid compressed by the working body when a cooling fluid for cooling the foil bearing is introduced into the opposite space of the support member. In this case, the axial size of the turbo fluid machine increases by the amount of the partition wall.

[0010] The present invention has been made in consideration of the above-mentioned conventional situation, and has as its problem to be solved the provision of a turbo fluid machine that can effectively cool foil bearings without increasing the axial size. [Means for solving the problem]

[0011] The turbo fluid machine of the present invention comprises: A rotating shaft that rotates around an axis; a plate-shaped thrust collar extending radially from a circumferential surface of the rotary shaft and rotatable integrally with the rotary shaft; an actuator that rotates integrally with the rotary shaft to pump the external fluid; a housing that accommodates the rotating shaft, the thrust collar, and the actuator; a partition member having an insertion hole through which the rotary shaft is inserted and dividing an interior of the housing into a compression space in which the working body is accommodated and a bearing space in which the thrust collar is accommodated; a foil bearing that supports the thrust collar in the axial direction so as to be rotatable relative to the partition member, the partition member includes a support portion having an end surface protruding in the axial direction toward the thrust collar, The support portion has a groove that is recessed in the end surface and extends in the radial direction to an outer circumferential surface, the foil bearing comprises: a plurality of bump foils arranged around the insertion hole with gaps therebetween and made of corrugated elastic thin plates attached to the end faces; and a plurality of top foils arranged around the insertion hole with gaps therebetween, one surface of which faces the thrust collar and the other surface of which is made of an elastic thin plate elastically supported by each of the bump foils, The foil bearing is attached to the support portion such that the position of the groove corresponds to the position of the gap between the bump foils and the position of the gap between the top foils, and the thrust collar and the groove face each other in the axial direction. 、 The groove does not communicate with the insertion hole. It is characterized by:

[0012] In foil bearings, when the thrust collar rotates around the axis together with the rotating shaft, the top foil supports the thrust collar, which rotates relative to the top foil, in a contact state during low-speed rotation. At this time, the end face of the top foil facing the thrust collar becomes the bearing surface, and the end face of the thrust collar facing the top foil, i.e., the surface facing the bearing surface of the top foil in the axial direction of the rotating shaft, becomes the borne surface. When the rotating shaft rotates at high speed, the fluid film pressure in the bearing gap between the bearing surface of the top foil and the borne surface of the thrust collar is increased. As a result, the top foil, which is elastically supported by the bump foil, floats up from the thrust collar while accompanying the elastic deformation of the bump foil, and supports the thrust collar in a non-contact state via the fluid film generated in the bearing gap.

[0013] At low rotation speeds, the top foil supports the thrust collar, which rotates relative to the top foil, in contact with it, generating heat as the two slide against each other. At high rotation speeds, the fluid film between the thrust collar and the top foil is sheared, generating heat. The top foil is made of a thin elastic plate with a small heat capacity. For this reason, the top foil is prone to becoming hot, which can cause problems with its heat resistance.

[0014] In the turbo fluid machine of the present invention, a thrust collar is supported by a foil bearing relative to a partition member, and the partition member divides the space into a compression space that accommodates a working body and a bearing space that accommodates the thrust collar. A groove is provided in an end face of the partition member on the thrust collar side as a cooling passage for cooling the foil bearing. In other words, the cooling passage for cooling the foil bearing does not penetrate the partition member in the plate thickness direction, but is a groove-shaped passage provided in the end face of the partition member. Therefore, there is no need to provide a separate partition wall for dividing and separating the compression space in the opposite space opposite the bearing space relative to the partition member, and the axial size does not become large.

[0015] The partition member has a support portion that protrudes in the axial direction toward the thrust collar, and a groove is recessed in the end face of the support portion. This groove extends in the radial direction of the rotating shaft to the outer circumferential surface of the support portion. That is, the groove (hereinafter, appropriately referred to as the "passage") as a cooling passage for cooling the foil bearing has an inflow opening in the outer circumferential surface of the support portion. This passage is located corresponding to the position of the gap between the bump foils adjacent in the circumferential direction of the rotating shaft. In other words, at least a part of this passage is located between the bump foils adjacent in the circumferential direction of the rotating shaft. The positional relationship between the passage and the top foil is also the same as above. In addition, this passage is groove-shaped recessed in the axial direction from the end face of the support portion. For this reason, the cooling fluid that flows into the passage from the inflow opening flows from the outer circumferential side to the inner circumferential side in the radial direction, and flows out of the passage in the circumferential gap extending in the radial direction between the bump foils adjacent in the circumferential direction. Since the passage faces the thrust collar, the cooling fluid that flows out of the passage into the circumferential gap of the bump foil is subjected to centrifugal force of the thrust collar and flows from the inner periphery to the outer periphery in a direction intersecting the circumferential direction, thereby cooling the bump foil and the top foil. In this way, the top foil can be effectively cooled by the cooling fluid flowing from the inner periphery to the outer periphery in a direction intersecting the circumferential direction.

[0016] Therefore, in this turbo fluid machine, the foil bearings can be effectively cooled without increasing the size in the axial direction.

[0017] Rotation axis Of a pair of groove side surfaces that are opposed to each other in the circumferential direction and that define the groove, it is preferable that the groove side surface on the rotational direction side of the rotating shaft extends at an incline so as to proceed in the rotational direction as it proceeds axially from the bottom surface of the groove toward the opening edge. In this case, the cooling fluid in the passage receives a rotational force from the thrust collar that rotates in the rotational direction of the rotating shaft, and flows smoothly out into the foil bearing along the inclined groove side surface on the rotational direction side.

[0018] It is preferable that the grooves extend at an angle so as to proceed in the direction of rotation as they extend radially from the outer periphery side to the inner periphery side. In this case, the cooling fluid in the grooves receives a rotational force from the thrust collar that rotates in the rotational direction of the rotating shaft, and thereby flows smoothly in the radial direction from the outer periphery side to the inner periphery side within the grooves. Effect of the Invention

[0019] According to the turbo fluid machine of the present invention, the foil bearings can be effectively cooled without increasing the size in the axial direction. [Brief description of the drawings]

[0020] [Figure 1] FIG. 1 is a cross-sectional view of a turbo compressor according to a first embodiment. [Diagram 2] FIG. 2 is an enlarged cross-sectional view of a part of the turbo compressor of the first embodiment. [Diagram 3] FIG. 3 is an enlarged cross-sectional view of a part of the turbo compressor of the first embodiment. [Figure 4] FIG. 4 is a perspective view of a fourth plate according to the turbo compressor of the first embodiment. [Diagram 5] FIG. 5 is a perspective view showing a second plate serving as a partition member in the turbo compressor of the first embodiment. [Figure 6] FIG. 6 is a plan view showing a state in which the bump foil is disposed on the support portion of the partition member in the turbo compressor of the first embodiment. [Figure 7] FIG. 7 is a plan view of the turbo compressor according to the first embodiment, showing a state in which the top foil is disposed on the support portion of the partition member. [Figure 8] FIG. 8 is a sectional view for explaining the operation of the thrust foil bearing in the turbo compressor according to the first embodiment. [Figure 9] FIG. 9 is a sectional view illustrating the operation of the thrust foil bearing in the turbo compressor of the first embodiment. [Figure 10] FIG. 10 is a perspective view showing a second plate serving as a partition member in a turbo compressor according to a second embodiment. [Figure 11] FIG. 11 relates to a turbo compressor according to a second embodiment, and is a cross-sectional view taken along line XI-XI in FIG. [Figure 12] FIG. 12 is a plan view of the turbo compressor according to the third embodiment, showing a state in which the top foil is disposed on a support portion of the partition member. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0021] Hereinafter, first to third embodiments of the present invention will be described with reference to the drawings.

[0022] Example 1 In this embodiment, the turbo fluid machine of the present invention is embodied in a turbo compressor 10. The turbo compressor 10 is mounted on a fuel cell vehicle equipped with a fuel cell system 1. The fuel cell system 1 supplies oxygen and hydrogen to an on-board fuel cell to generate power. The turbo compressor 10 compresses air containing oxygen that is supplied to the on-board fuel cell.

[0023] As shown in Fig. 1, a turbo compressor 10, which is a turbo fluid machine, includes a housing 11. The housing 11 is made of a metal material, for example, an aluminum alloy. The housing 11 includes a motor housing 12, a compressor housing 13, a turbine housing 14, a first plate 15, a second plate 16, a third plate 17, and a fourth plate 29. The second plate 16 corresponds to the partition member in the present invention.

[0024] The motor housing 12 has a plate-like end wall 12a and a peripheral wall 12b. The peripheral wall 12b extends in a cylindrical shape from the outer periphery of the end wall 12a. The first plate 15 is connected to an end of the peripheral wall 12b of the motor housing 12 on the opening side, and closes the opening of the peripheral wall 12b.

[0025] A motor chamber S1 is defined by an inner surface 121a of the end wall 12a of the motor housing 12, an inner circumferential surface 121b of the peripheral wall 12b, and an end surface 15a of the first plate 15 facing the motor housing 12. An electric motor 18 is accommodated in the motor chamber S1.

[0026] The first plate 15 has a first bearing retaining portion 20. The first bearing retaining portion 20 protrudes from the center of the end face 15a of the first plate 15 toward the electric motor 18. The first bearing retaining portion 20 is cylindrical.

[0027] A recess 15c having a bottom surface 15d is formed on an end surface 15b of the first plate 15 opposite the motor housing 12. The recess 15c is a circular hole. The inside of the cylinder of the first bearing holder 20 penetrates the first plate 15 and opens to the bottom surface 15d of the recess 15c. The axis of the recess 15c and the axis of the first bearing holder 20 coincide with each other. An inner peripheral surface 15e of the recess 15c connects the end surface 15b and the bottom surface 15d.

[0028] The motor housing 12 has a second bearing retaining portion 22. The second bearing retaining portion 22 protrudes from the center of an inner surface 121a of an end wall 12a of the motor housing 12 toward the electric motor 18. The second bearing retaining portion 22 is cylindrical. The inside of the cylinder of the second bearing retaining portion 22 penetrates the end wall 12a of the motor housing 12 and opens to an outer surface 122a of the end wall 12a. The axis of the first bearing retaining portion 20 and the axis of the second bearing retaining portion 22 coincide with each other.

[0029] As shown in FIG. 2, the fourth plate 29 is connected to the end face 15b of the first plate 15. As shown in FIG. 4, the fourth plate 29 is formed in an annular shape having a central hole 29a. The central hole 29a communicates with the inside of the recess 15c. A communication groove 29c is recessed in the end face 29b of the fourth plate 29 opposite to the first plate 15. The communication groove 29c extends in the radial direction of the fourth plate 29 and opens to the outer peripheral surface and the inner peripheral surface of the fourth plate 29. The communication groove 29c extends in a centripetal direction from the outer peripheral surface of the fourth plate 29 toward the axis of the rotation shaft 24a.

[0030] The second plate 16 is connected to an end face 29b of the fourth plate 29. A shaft insertion hole 16a is formed in the center of the second plate 16. The shaft insertion hole 16a communicates with the inside of the recess 15c via the central hole 29a. The axis of the shaft insertion hole 16a coincides with the axis of the central hole 29a, the axis of the recess 15c, and the axis of the first bearing holder 20. A thrust bearing accommodating chamber S2 is defined by the end face 16b of the second plate 16 on the fourth plate 29 side, the central hole 29a of the fourth plate 29, and the recess 15c of the first plate 15. The thrust bearing accommodating chamber S2 corresponds to the bearing space in the present invention.

[0031] The compressor housing 13 is cylindrical and has a circular suction port 13a through which air is drawn. The compressor housing 13 is connected to an end face 16c of the second plate 16 opposite to the first plate 15. The axis of the suction port 13a of the compressor housing 13, the axis of the shaft insertion hole 16a of the second plate 16, and the axis of the first bearing holder 20 are aligned. The suction port 13a opens into the end face of the compressor housing 13 opposite to the second plate 16.

[0032] Between the compressor housing 13 and the end face 16c of the second plate 16, a first impeller chamber 13b, a discharge chamber 13c, and a first diffuser passage 13d are formed. The first impeller chamber 13b communicates with the suction port 13a. The discharge chamber 13c extends around the axis of the suction port 13a around the periphery of the first impeller chamber 13b. The first diffuser passage 13d communicates with the first impeller chamber 13b and the discharge chamber 13c. The first impeller chamber 13b communicates with the shaft insertion hole 16a of the second plate 16. The first impeller chamber 13b corresponds to the compression space in the present invention.

[0033] As shown in Fig. 3, the third plate 17 is connected to an outer surface 122a of the end wall 12a of the motor housing 12. A shaft insertion hole 17a is formed in the center of the third plate 17. The shaft insertion hole 17a communicates with the inside of the cylinder of the second bearing holder 22. The axis of the shaft insertion hole 17a coincides with the axis of the second bearing holder 22.

[0034] The turbine housing 14 is cylindrical and has a circular discharge port 14a through which air is discharged. The turbine housing 14 is connected to an end face 17b of the third plate 17 opposite the motor housing 12. The axis of the discharge port 14a of the turbine housing 14, the axis of the shaft insertion hole 17a of the third plate 17, and the axis of the second bearing holder 22 are aligned. The discharge port 14a opens into the end face of the turbine housing 14 opposite the third plate 17.

[0035] Between the turbine housing 14 and the end face 17b of the third plate 17, a second impeller chamber 14b, a suction chamber 14c, and a second diffuser passage 14d are formed. The second impeller chamber 14b is in communication with the discharge port 14a. The suction chamber 14c extends around the axis of the discharge port 14a around the periphery of the second impeller chamber 14b. The second diffuser passage 14d is in communication with the second impeller chamber 14b and the suction chamber 14c. The second impeller chamber 14b is in communication with the shaft insertion hole 17a of the third plate 17.

[0036] As shown in FIG. 1, a rotating body 24 is accommodated in the housing 11. The rotating body 24 has a rotating shaft 24a as a shaft portion, a first supported portion 24b, a second supported portion 24c, and a third supported portion 24d. The rotating shaft 24a has a first end portion 24e which is an end portion on the compressor housing 13 side, and a second end portion 24f which is an end portion on the turbine housing 14 side. The first supported portion 24b is provided at a portion close to the first end portion 24e on the outer circumferential surface 240a of the rotating shaft 24a, and is disposed in the cylinder of the first bearing holder 20. The first supported portion 24b is integrally formed with the rotating shaft 24a, and protrudes in an annular shape from the outer circumferential surface 240a of the rotating shaft 24a.

[0037] The second supported portion 24c is provided on the outer circumferential surface 240a of the rotating shaft 24a at a position close to the second end 24f, and is disposed within the cylinder of the second bearing holder 22. The second supported portion 24c is cylindrical and fixed to the outer circumferential surface 240a of the rotating shaft 24a in a state where it protrudes in an annular shape from the outer circumferential surface 240a of the rotating shaft 24a. The second supported portion 24c is rotatable integrally with the rotating shaft 24a.

[0038] The third supported portion 24d is disposed in the thrust bearing accommodating chamber S2. The third supported portion 24d is disk-shaped and fixed to the outer circumferential surface 240a of the rotating shaft 24a in a state in which it extends radially from the outer circumferential surface 240a of the rotating shaft 24a and protrudes in an annular shape. The third supported portion 24d can rotate integrally with the rotating shaft 24a. The third supporting portion 24d is disposed at a position spaced apart from the electric motor 18 in the axial direction of the rotating shaft 24a. The third supported portion 24d corresponds to the thrust collar in the present invention.

[0039] In the following description, the axial direction, circumferential direction, and radial direction refer to the axial direction, circumferential direction, and radial direction, respectively, of the rotating shaft 24a. The first end 24e side of the rotating shaft 24a is defined as one side in the axial direction, and the second end 24f side of the rotating shaft 24a is defined as the other side in the axial direction.

[0040] A first impeller 25 serving as an actuator is connected to a first end 24e of the rotating shaft 24a. The first impeller 25 is disposed closer to the first end 24e than the third supported portion 24d of the rotating shaft 24a. The first impeller 25 is accommodated in the first impeller chamber 13b. A second impeller 26 is connected to a second end 24f of the rotating shaft 24a. The second impeller 26 is disposed closer to the second end 24f than the second supported portion 24c of the rotating shaft 24a. The second impeller 26 is accommodated in the second impeller chamber 14b. The housing 11 accommodates the first impeller 25, the second impeller 26, and the rotor 24.

[0041] A first seal member 27 is provided between the shaft insertion hole 16a of the second plate 16 and the rotating shaft 24a. The first seal member 27 seals the gap between the shaft insertion hole 16a and the rotating shaft 24a to suppress air leakage from the first impeller chamber 13b toward the motor chamber S1. A second seal member 28 is provided between the shaft insertion hole 17a of the third plate 17 and the rotor 24. The second seal member 28 seals the gap between the shaft insertion hole 17a and the rotating shaft 24a to suppress air leakage from the second impeller chamber 14b toward the motor chamber S1. The first seal member 27 and the second seal member 28 are, for example, seal rings. The first seal member 27 corresponds to the sealing member in the present invention.

[0042] The second plate 16 has a first seal member 27 inside the shaft insertion hole 16a that seals the gap between the shaft insertion hole 16a and the rotating shaft 24a, so that the inside of the housing 11 is divided into a first impeller chamber 13b and a thrust bearing accommodating chamber S2.

[0043] The electric motor 18 includes a cylindrical rotor 31 and a cylindrical stator 32. The rotor 31 is fixed to the rotating shaft 24a. The stator 32 is fixed to the housing 11. The rotor 31 is disposed radially inside the stator 32 and rotates integrally with the rotating body 24. The rotor 31 includes a cylindrical rotor core 31a fixed to the rotating shaft 24a and a plurality of permanent magnets (not shown) provided on the rotor core 31a. The stator 32 surrounds the rotor 31. The stator 32 includes a cylindrical stator core 33 fixed to the inner circumferential surface 121b of the peripheral wall 12b of the motor housing 12 and a coil 34 wound around the stator core 33. The rotating body 24 rotates integrally with the rotor 31 when a current flows from a battery (not shown) to the coil 34.

[0044] The fuel cell system 1 includes a fuel cell stack 100 as an on-board fuel cell, a turbo compressor 10, a supply flow path L1, a discharge flow path L2, and a branch flow path L3. The fuel cell stack 100 is composed of a plurality of fuel cells. The supply flow path L1 connects the discharge chamber 13c and the fuel cell stack 100. The discharge flow path L2 connects the fuel cell stack 100 and the suction chamber 14c. An intercooler 110 is provided midway along the branch flow path L3 that branches off from the supply flow path L1. The intercooler 110 cools the air flowing through the branch flow path L3.

[0045] When the rotating body 24 rotates integrally with the rotor 31, the first impeller 25 and the second impeller 26 rotate integrally with the rotating body 24. Then, air sucked in from the intake port 13a is compressed by the first impeller 25 in the first impeller chamber 13b, passes through the first diffuser passage 13d, and is discharged from the discharge chamber 13c. The air discharged from the discharge chamber 13c is supplied to the fuel cell stack 100 through the supply passage L1. The air supplied to the fuel cell stack 100 is used to generate power in the fuel cell stack 100, and then discharged to the discharge passage L2 as the exhaust gas of the fuel cell stack 100. The exhaust gas of the fuel cell stack 100 is sucked into the intake chamber 14c through the discharge passage L2. The exhaust gas of the fuel cell stack 100 sucked into the intake chamber 14c is discharged to the second impeller chamber 14b through the second diffuser passage 14d. The second impeller 26 is rotated by the exhaust gas from the fuel cell stack 100 discharged into the second impeller chamber 14b. The rotor 24 is rotated not only by the drive of the electric motor 18, but also by the rotation of the second impeller 26 which is rotated by the exhaust gas from the fuel cell stack 100. Thus, the first impeller 25 as an actuator rotates integrally with the rotor 24 and pumps air as an external fluid. The exhaust gas from the fuel cell stack 100 discharged into the second impeller chamber 14b is discharged to the outside from the discharge port 14a.

[0046] In the following description, it is assumed that the rotating body 24 rotates integrally with the rotor 31 in a rotation direction R. As the rotation direction of the rotating shaft 24a is indicated by an arrow R in Figs. 6 to 9, the rotating body 24 and the rotor 31 rotate in the counterclockwise direction in Fig. 6.

[0047] The turbo compressor 10 has a pair of thrust foil bearings 30, 30 and a pair of radial foil bearings 40, 40. The pair of thrust foil bearings 30, 30 support the third supported portion 24d of the rotor 24 in the axial direction of the rotating shaft 24a so as to be rotatable relative to the housing 11. The pair of radial foil bearings 40, 40 support the first supported portion 24b and the second supported portion 24c of the rotor 24 in a direction perpendicular to the axial direction of the rotating shaft 24a so as to be rotatable relative to the housing 11.

[0048] The pair of thrust foil bearings 30, 30 are arranged in the thrust bearing accommodating chamber S2. The pair of thrust foil bearings 30, 30 are arranged to sandwich the third supported portion 24d serving as a thrust collar. The pair of thrust foil bearings 30, 30 face the third supported portion 24d in the axial direction of the rotating shaft 24a. One thrust foil bearing 30 is arranged on the first end 24e side of the rotating shaft 24a with respect to the third supported portion 24d. The other thrust foil bearing 30 is arranged on the second end 24f side of the rotating shaft 24a with respect to the third supported portion 24d.

[0049] 2, an end face of the third supported portion 24d on the first end 24e side of the rotating shaft 24a is a bearing surface 241d that is axially supported by one of the thrust foil bearings 30. Similarly, an end face of the third supported portion 24d on the second end 24f side of the rotating shaft 24a is a bearing surface 241d that is axially supported by the other thrust foil bearing 30.

[0050] 2 and 5, a support portion 60 is provided integrally with the end surface 16b of the second plate 16 on the fourth plate 29 side. The support portion 60 protrudes in the axial direction toward the third support portion 24d at the center of the second plate 16. The shaft insertion hole 16a also extends continuously into the center of the support portion 60. The support portion 60 is disposed within the central hole 29a of the fourth plate 29.

[0051] The support part 60 has six grooves recessed from its protruding end face 60a in the axial direction. That is, six groove-like passages 61 are formed in the end face 60a of the support part 60. The passages 61 are equally spaced in the circumferential direction of the rotating shaft 24a. Each passage 61 extends to the outer circumferential surface 60b of the support part 60. That is, each passage 61 has an inlet opening 61a that opens on the outer circumferential surface 60b of the support part 60 (see Figs. 6 and 7). Each passage 61 extends in a centripetal direction from the outer circumferential surface 60b of the support part 60 toward the axial center of the rotating shaft 24a. The inner end of each passage 61 extends to the vicinity of the shaft insertion hole 16a.

[0052] 2, one thrust foil bearing 30 is attached to an end surface 60a of a support portion 60 of the second plate 16, and the other thrust foil bearing 30 is attached to a bottom surface 15d of a recess 15c of the first plate 15. The other thrust foil bearing 30 may be attached to a cover member (not shown), and the cover member may be joined to the first plate 15 while being screwed to the support portion.

[0053] As shown in Fig. 6, six plate-shaped bump foils 32 are attached to the end surface 60a of the support portion 60 and are arranged at equal intervals around the shaft insertion hole 16a. As shown in Fig. 8, each bump foil 32 is fixed to the end surface 60a of the support portion 60 by welding at one end in the circumferential direction. That is, the end on one side in the circumferential direction of the bump foil 32 is the fixed end 32a, and the end on the other side in the circumferential direction is the free end 32b. Note that the end on the other side in the circumferential direction of the bump foil 32 may be the fixed end, and the end on one side in the circumferential direction may be the free end.

[0054] The bump foil 32 has an outer shape that is substantially fan-shaped in a plan view. The bump foil 32 is made of an elastic thin plate made of metal such as stainless steel, and has a corrugated shape in which peaks 32c and valleys 32d are alternately arranged in the circumferential direction of the rotating shaft 24a. The ridges 32e of the peaks 32c are arranged in the circumferential direction of the rotating shaft 24a. Each peak 32c protrudes toward the third support portion 24d and can elastically support the top foil 33 by contacting the top foil 33.

[0055] As shown in FIG. 7, six plate-shaped top foils 33 are attached to the end surface 60a of the support portion 60 in a line around the shaft insertion hole 16a. As shown in FIG. 8, the other circumferential end of each top foil 33 is bent toward the support portion 60, and the tip portion is fixed to the end surface 60a of the support portion 60 by welding. That is, the other circumferential end of the top foil 33 is the fixed end 33a, and the one circumferential end is the free end 33b. The outer shape of the top foil 33 is approximately fan-shaped in a plan view. The top foil 33 is formed by forming an elastic thin plate made of metal such as stainless steel into a predetermined shape.

[0056] The top foils 33 are disposed at equal intervals in the circumferential direction of the rotating shaft 24a to correspond to the bump foils 32, and are elastically supported by the bump foils 32. One surface of the top foil 33 faces the third supported portion 24d serving as a thrust collar, and the other surface of the top foil 33 is elastically supported by the bump foil 32. The surface of the top foil 33 opposite the surface elastically supported by the bump foil 32 serves as a bearing surface 33c that faces the bearing surface 241d of the third supported portion 24d in the axial direction.

[0057] The thrust foil bearing 30 is attached to the end face 60a of the support part 60 so that the positions of the passages 61 correspond to the positions of the intervals between the bump foils 32 and the positions of the intervals between the top foils 33, and the third support part 24d as a thrust collar and the passages 61 face each other in the axial direction. That is, the bump foils 32 and the top foils 33 are arranged at equal intervals in the circumferential direction of the rotating shaft 24a while avoiding the six passages 61. The bump foils 32 and the top foils 33 are attached to the end face 60a of the support part 60 at positions avoiding the passages 61. This allows the load of each bump foil 32 to be reliably received by the end face 60a of the support part 60. The passages 61 are arranged in the circumferential gaps 32f extending in the radial direction, which is the direction intersecting the circumferential direction, between the bump foils 32 adjacent in the circumferential direction (see FIG. 6). In the following description, the gap extending in a direction intersecting the circumferential direction between adjacent bump foils 32 in the circumferential direction of the rotating shaft 24a will be simply referred to as a circumferential gap 32f.

[0058] Each passage 61 extends continuously from the outer circumferential edge to the vicinity of the inner circumferential edge of the bump foil 32 in the circumferential gap 32f. When projected onto an imaginary plane perpendicular to the axial direction of the rotating shaft 24a, the circumferential gap 32f and the passage 61 overlap in the radial direction, which is a direction intersecting the circumferential direction, over most of the range of the radial width of the bump foil 32.

[0059] The other thrust foil bearing 30 attached to the recess 15 c also includes six bump foils 32 and six top foils 33 , similar to the one thrust foil bearing 30 attached to the support portion 60 .

[0060] One radial foil bearing 40 is disposed in the first bearing holder 20, and the other radial foil bearing 40 is disposed in the second bearing holder 22. In the first bearing holder 20, the first supported portion 24b of the rotating body 24 is rotatably supported by one radial foil bearing 40. The outer peripheral surface of the first supported portion 24b is a radial bearing surface 24g supported by one radial foil bearing 40 in a direction perpendicular to the axial direction. In the second bearing holder 22, the second supported portion 24c of the rotating body 24 is rotatably supported by the other radial foil bearing 40. The outer peripheral surface of the second supported portion 24c is a radial bearing surface 24g supported by the other radial foil bearing 40 in a direction perpendicular to the axial direction.

[0061] Since the pair of radial foil bearings 40, 40 basically have the same configuration, only the configuration of one radial foil bearing 40 will be described, and the description of the configuration of the other radial foil bearing 40 will be omitted.

[0062] The radial foil bearing 40 includes a radial bump foil 42 and a radial top foil 43. The radial bump foil 42 and the radial top foil 43 are both substantially cylindrical and formed by forming an elastic thin plate made of metal such as stainless steel into a predetermined shape. The radial bump foil 42 and the radial top foil 43 have the other circumferential end bent radially outward and fixed to the inner circumferential surface of the first bearing holder 20. That is, the radial bump foil 42 and the radial top foil 43 have the other circumferential end as a fixed end and the one circumferential end as a free end.

[0063] The radial bump foil 42 has a corrugated shape in which the ridgelines of the peaks protruding toward the radial top foil 43 are aligned in the circumferential direction of the rotating shaft 24a. The radial bump foil 42 can elastically support the radial top foil 43 by each peak, with each valley located between adjacent peaks being supported by the first bearing retaining portion 20. In the radial top foil 43, the surface opposite to the surface elastically supported by the radial bump foil 42 is a radial bearing surface 43a (see FIGS. 2 and 3) that faces the radial bearing surface 24g in the radial direction.

[0064] As shown in Figure 8, in a pair of thrust foil bearings 30, 30, the rotating shaft 24a is supported with the bearing surface 33c of the top foil 33 in contact with the bearing surface 241d of the third supported portion 24d until the rotational speed of the rotating shaft 24a reaches a floating rotational speed at which the thrust foil bearing 30 floats the third supported portion 24d as a thrust collar.

[0065] 9, when the rotation speed of the rotating shaft 24a reaches the levitation rotation speed, the third supported portion 24d is levitated relative to the thrust foil bearing 30 by the fluid film pressure generated between the third supported portion 24d and the top foil 33. As a result, the thrust foil bearing 30 supports the rotating shaft 24a in a state of not contacting the third supported portion 24d.

[0066] Similarly, in the pair of radial foil bearings 40, 40, the radial bearing surface 43a of the radial top foil 43 and the radial bearing surfaces 24g of the first supported portion 24b and the second supported portion 24c are in contact with each other to support the rotating shaft 24a until the rotation speed of the rotating shaft 24a reaches a floating rotation speed at which the first supported portion 24b and the second supported portion 24c are floated by the radial foil bearing 40. When the rotation speed of the rotating shaft 24a reaches the floating rotation speed, the first supported portion 24b and the second supported portion 24c are floated relative to the radial foil bearing 40 due to the fluid film pressure generated between the first supported portion 24b and the second supported portion 24c and the top foil 43. As a result, the radial foil bearing 40 supports the rotating shaft 24a in a non-contact state with the first supported portion 24b and the second supported portion 24c.

[0067] As shown in Figs. 1 to 3, a cooling flow passage 50 is formed in the housing 11. Cooling air flows as a fluid through the cooling flow passage 50. The cooling flow passage 50 is formed across the second plate 16, the fourth plate 29, the first plate 15, the motor housing 12, and the third plate 17. The cooling flow passage 50 has a first flow passage 51 and a second flow passage 52. Each passage 61 constitutes a part of the cooling flow passage 50.

[0068] The first flow passage 51 is provided in the second plate 16 and the fourth plate 29. An inlet 51a of the first flow passage 51 is formed by an open end on the outer circumferential side of the communication groove 29c of the fourth plate 29. The branch flow passage L3 connects the supply flow passage L1 and the inlet 51a of the first flow passage 51. The first flow passage 51 communicates with the motor chamber S1 via the communication groove 29c and the central hole 29a of the fourth plate 29, the thrust bearing accommodating chamber S2, and one of the radial foil bearings 40.

[0069] The second flow passage 52 is provided in the third plate 17. The second flow passage 52 has an outlet 52a provided in a side end surface of the third plate 17. The second flow passage 52 communicates with the motor chamber S1 via the other radial foil bearing 40.

[0070] A portion of the air flowing through the supply passage L1 toward the fuel cell stack 100 flows into the first passage 51 via the branch passage L3. The air flowing into the first passage 51 is cooled by the intercooler 110 while flowing through the branch passage L3.

[0071] The cooling air that has flowed into the inlet 51a of the first flow passage 51 passes through the communication groove 29c of the fourth plate 29 and reaches the central hole 29a. The cooling air that has reached the central hole 29a mainly cools one of the thrust foil bearings 30. That is, the cooling air that has flowed out from the communication groove 29c to the central hole 29a flows around the central hole 29a in the circumferential direction and flows into each passage 61 from each inlet opening 61a. The cooling air that has flowed into each passage 61 flows from the outer circumferential side to the inner circumferential side in the radial direction, and flows out of each passage 61 at each circumferential gap 32f that extends radially between circumferentially adjacent bump foils 32. Since each passage 61 faces the third supported portion 24d serving as a thrust collar, the cooling air flowing out from each passage 61 into each circumferential gap 32f receives the centrifugal force of the third supported portion 24d and flows from the inner periphery side to the outer periphery side in a direction intersecting the circumferential direction, cooling each bump foil 32 and each top foil 33. In this way, the top foil 33 can be effectively cooled by the cooling air flowing from the inner periphery side to the outer periphery side in a direction intersecting the circumferential direction.

[0072] The cooling air after cooling one thrust foil bearing 30 passes radially outward of the third supported portion 24d and flows inside the other thrust foil bearing 30 from the outer circumferential side to the inner circumferential side, thereby cooling the other thrust foil bearing 30. Note that a portion of the cooling air that flows out from the communicating hole 29c to the central hole 29a directly cools the other thrust foil bearing 30 without cooling the one thrust foil bearing 30.

[0073] The cooling air that has passed through the thrust bearing accommodating chamber S2 flows from one side to the other side in the axial direction within one radial foil bearing 40, cooling one radial foil bearing 40. The cooling air that has passed through one radial foil bearing 40 flows into the motor chamber S1.

[0074] The air that has flowed into the motor chamber S1 passes between the rotor 31 and the stator 32, for example, and flows into the second flow passage 52 via the other radial foil bearing 40, and is discharged from the exhaust port 52a.

[0075] In this manner, as the cooling air flows through the cooling passage 50, the electric motor 18, the pair of thrust foil bearings 30, 30, and the pair of radial foil bearings 40, 40 are directly cooled by the cooling air.

[0076] In the thrust foil bearing 30 and the radial foil bearing 40, the heat resistance of the top foil 33 and the radial top foil 43 can easily become an issue. In this regard, in the turbo compressor 10, cooling air flows inside the thrust foil bearing 30 and the radial foil bearing 40, so that the top foil 33 and the radial top foil 43 can be cooled by the cooling air, and problems with the heat resistance of the top foil 33 and the radial top foil 43 can be suppressed.

[0077] In particular, in this turbo compressor 10, a large thrust load acts on one of the pair of thrust foil bearings 30, 30, the thrust foil bearing 30 on the first impeller 25 side, so it is desirable to actively cool this one thrust foil bearing 30.

[0078] In this regard, as described above, in the turbo compressor 10, in each circumferential gap 32f in one thrust foil bearing 30, a passage 61 is formed extending from the outer peripheral edge to the vicinity of the inner peripheral edge of each bump foil 32, and cooling air is introduced into this passage 61. Therefore, the one thrust foil bearing 30 on which a large thrust load acts can be actively cooled.

[0079] In addition, in this turbo compressor 10, the gap between the shaft insertion hole 16a of the second plate 16 and the rotating shaft 24a is sealed with a first seal member 27, and the second plate 16 separates the first impeller chamber 13b as a compression space from the thrust bearing accommodation chamber S2 as a bearing space. A passage 60 for cooling one of the thrust foil bearings 30 does not penetrate the second plate 16 in the plate thickness direction, but is a groove-like passage provided in an end face 60a of a support portion 60 integrally provided with the second plate 16. For this reason, it is not necessary to separately provide a partition wall for partitioning and separating the first impeller chamber 13b in the opposite space on the opposite side of the second plate 16 from the thrust bearing accommodation chamber S2, and the axial size does not become large.

[0080] Therefore, in this turbo compressor 10, one of the thrust foil bearings 30 on which a particularly large thrust load acts can be effectively cooled without increasing the axial size of the turbo compressor 10.

[0081] In this turbo compressor 10, a passage 61 is formed in the circumferential gap 32f in one thrust foil bearing 30. In addition, this passage 61 extends across almost the entire radial width of the thrust bump foil 32. Therefore, in one thrust foil bearing 30, the cooling air flowing out from each passage 61 can effectively cool almost the entire area of ​​all thrust top foils 33.

[0082] Example 2 As shown in Figs. 10 and 11, in this turbo compressor, the shape of each passage 61 formed in a support portion 60 in the turbo compressor 10 of the first embodiment is changed.

[0083] In each passage 61, of a pair of groove side surfaces 61b, 61c which are opposed circumferentially to define the groove, the groove side surface 61c on the rotational direction R side of the rotating shaft 24a extends at an angle of θ1 so as to proceed in the rotational direction R as it proceeds axially from the bottom surface 61d of the groove toward the opening edge 61e.

[0084] As a result, the cooling fluid in the passage 61 receives a rotational force from the third supported portion 24d rotating in the rotational direction R, and flows smoothly out into one of the thrust foil bearings 30 along the inclined groove side surface 61c on the rotational direction R side.

[0085] The other configurations and operations are similar to those of the turbo compressor 10 of the first embodiment.

[0086] Example 3 As shown in FIG. 12, in this turbo compressor, in the turbo compressor 10 of Example 1, the shape of each passage 61 formed in the support portion 60 is changed, and the shapes of each bump foil 32 and each top foil 33 in one of the thrust foil bearings 30 are changed in correspondence with the change in the shape of the passage 61.

[0087] Each passage 61 extends in the radial direction from the outer periphery side to the inner periphery side, while being inclined at an angle of θ2 so as to proceed in the rotational direction R of the rotary shaft 24a.

[0088] Corresponding to the change in the shape of the passage 61, the shapes of the bump foils 32 and the top foils 33 in one thrust foil bearing 30 are changed. That is, the positions of the passages 61 correspond to the positions of the gaps between the bump foils 32 and the positions of the gaps between the top foils 33, and the third supported portion 24d and the passages 61 face each other in the axial direction, and the bump foils 32 and the top foils 33 are attached to the support portion 60 such that the third supported portion 24d and the passages 61 face each other in the axial direction. The bump foils 32 and the top foils 33 are attached to the end face 60a of the support portion 60 at locations avoiding the passages 61. This allows the load of the bump foils 32 to be reliably received by the end face 60a of the support portion 60.

[0089] In this case, the cooling fluid in each passage 61 receives a rotational force from the third supported portion 24d rotating in the rotational direction R, and thereby flows smoothly from the outer circumferential side to the inner circumferential side within the passage 61 in a direction intersecting the circumferential direction.

[0090] The other configurations and operations are similar to those of the turbo compressor 10 of the first embodiment.

[0091] In the above, the present invention has been described based on Examples 1 to 3. However, the present invention is not limited to Examples 1 to 3, and it goes without saying that the present invention can be modified and applied as appropriate without departing from the spirit of the present invention.

[0092] For example, in the thrust foil bearing 30 in the first to third embodiments, six bump foils 32 and six top foils 33 are used, but the numbers of bump foils 32 and top foils 33 are not limited to this, and the same number of each may be used. Also, a disc-type bump foil in which multiple bump foils are integrated by a ring portion, or a disc-type top foil in which multiple top foils are integrated by a ring portion may be used.

[0093] In the first to third embodiments, the passages 61 are provided in all the circumferential gaps 32f, but the present invention is not limited to this configuration, and the passages 61 may be provided in only some of the circumferential gaps 32f.

[0094] In Examples 1 to 3, the inner end of the passage 61 extends to near the inner edge of the bump foil 32, but the present invention is not limited to this configuration, and the inner end of the passage 61 may also extend to, for example, approximately half the radial width of the bump foil 32.

[0095] In the first to third embodiments, the second plate 16 as the partition member and the support portion 60 are integrally formed, but the second plate 16 and the support portion 60 may be separate bodies.

[0096] In the first to third embodiments, the second plate 16 and the fourth plate 29 serving as the partition members are separate bodies, but the second plate 16 and the fourth plate 29 may be integrated together. In this case, a through hole penetrating from the outer peripheral surface of the integrated body to the inner peripheral surface of the central hole 29a can be formed instead of the communication groove 29c.

[0097] It is also possible to configure a combination of Example 2 and Example 3. In this case, the top foil 33 of one of the thrust foil bearings 30 can be cooled more effectively. [Industrial Applicability]

[0098] The present invention can be used in an air compressor or the like used in a fuel cell system. [Explanation of symbols]

[0099] 11. Housing 13b…First impeller chamber (compression space) S2: Thrust bearing housing (bearing space) 16...Second plate (partition member) 16a...Shaft insertion hole (insertion hole) 24a…Rotating shaft 24d…Third supported part (thrust collar) 25…First impeller (actuator) 30...Thrust foil bearing (foil bearing) 32…Bump foil 33…Top foil 60...Support part 60a...End face 61...Aisle (groove) 61b, 61c…Groove side

Claims

1. A rotating shaft that rotates around an axis; a plate-shaped thrust collar extending radially from a circumferential surface of the rotary shaft and rotatable integrally with the rotary shaft; an actuator that rotates integrally with the rotary shaft to pump the external fluid; a housing that accommodates the rotating shaft, the thrust collar, and the actuator; a partition member having an insertion hole through which the rotary shaft is inserted and dividing an interior of the housing into a compression space in which the working body is accommodated and a bearing space in which the thrust collar is accommodated; a foil bearing that supports the thrust collar in the axial direction so as to be rotatable relative to the partition member, the partition member includes a support portion having an end surface protruding in the axial direction toward the thrust collar, The support portion has a groove that is recessed in the end surface and extends in the radial direction to an outer circumferential surface, the foil bearing comprises: a plurality of bump foils arranged around the insertion hole with gaps therebetween and made of corrugated elastic thin plates attached to the end faces; and a plurality of top foils arranged around the insertion hole with gaps therebetween, one surface of which faces the thrust collar and the other surface of which is made of an elastic thin plate elastically supported by each of the bump foils, the foil bearing is attached to the support portion such that the position of the groove corresponds to the position of the gap between the bump foils and the position of the gap between the top foils, and the thrust collar and the groove face each other in the axial direction; The turbo fluid machine according to claim 1, wherein the groove does not communicate with the insertion hole.

2. 2. The turbo-type fluid machine according to claim 1, wherein of a pair of groove side surfaces that face each other circumferentially around the rotating shaft and define the groove, the groove side surface on the rotational direction side of the rotating shaft extends at an angle so as to progress in the rotational direction as it progresses from a bottom surface of the groove toward an opening end edge in the axial direction.

3. 3. The turbo fluid machine according to claim 1, wherein the grooves extend in the radial direction from an outer circumferential side to an inner circumferential side, and incline so as to progress in the rotational direction as the grooves extend in the radial direction.

4. A rotating shaft that rotates around an axis, a plate-shaped thrust collar extending radially from a circumferential surface of the rotary shaft and rotatable integrally with the rotary shaft; an actuator that rotates integrally with the rotary shaft to pump the external fluid; a housing that accommodates the rotating shaft, the thrust collar, and the actuator; a partition member having an insertion hole through which the rotary shaft is inserted and dividing an interior of the housing into a compression space in which the working body is accommodated and a bearing space in which the thrust collar is accommodated; a foil bearing that supports the thrust collar in the axial direction so as to be rotatable relative to the partition member, the partition member includes a support portion having an end surface protruding in the axial direction toward the thrust collar, The support portion has a groove that is recessed in the end surface and extends in the radial direction to an outer circumferential surface, the foil bearing comprises: a plurality of bump foils arranged around the insertion hole with gaps therebetween and made of corrugated elastic thin plates attached to the end faces; and a plurality of top foils arranged around the insertion hole with gaps therebetween, one surface of which faces the thrust collar and the other surface of which is made of an elastic thin plate elastically supported by each of the bump foils, the foil bearing is attached to the support portion such that the position of the groove corresponds to the position of the gap between the bump foils and the position of the gap between the top foils, and the thrust collar and the groove face each other in the axial direction; a pair of groove side surfaces that define the groove and face each other in the circumferential direction of the rotating shaft, the groove side surface on the rotational direction side of the rotating shaft extends at an angle so as to progress in the rotational direction as it progresses from a bottom surface of the groove toward an opening end edge in the axial direction.

5. A turbo fluid machine as described in claim 4, wherein the groove extends at an angle so as to progress in the rotational direction as it extends radially from the outer circumferential side to the inner circumferential side.

6. A rotating shaft that rotates around an axis, a plate-shaped thrust collar extending radially from a circumferential surface of the rotary shaft and rotatable integrally with the rotary shaft; an actuator that rotates integrally with the rotary shaft to pump the external fluid; a housing that accommodates the rotating shaft, the thrust collar, and the actuator; a partition member having an insertion hole through which the rotary shaft is inserted and dividing an interior of the housing into a compression space in which the working body is accommodated and a bearing space in which the thrust collar is accommodated; a foil bearing that supports the thrust collar in the axial direction so as to be rotatable relative to the partition member, the partition member includes a support portion having an end surface protruding in the axial direction toward the thrust collar, The support portion has a groove that is recessed in the end surface and extends in the radial direction to an outer circumferential surface, the foil bearing comprises: a plurality of bump foils arranged around the insertion hole with gaps therebetween and made of corrugated elastic thin plates attached to the end faces; and a plurality of top foils arranged around the insertion hole with gaps therebetween, one surface of which faces the thrust collar and the other surface of which is made of an elastic thin plate elastically supported by each of the bump foils, the foil bearing is attached to the support portion such that the position of the groove corresponds to the position of the gap between the bump foils and the position of the gap between the top foils, and the thrust collar and the groove face each other in the axial direction; The turbo-type fluid machine, wherein the groove extends in the radial direction from an outer circumferential side to an inner circumferential side, and is inclined so as to progress in the rotational direction as the groove extends in the radial direction.

Images