JP2018151030A - Thrust bearing device and supercharger - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a thrust bearing device which adapts load-carrying capacity to a load acting on a rotary shaft to achieve compactification of the device.SOLUTION: A thrust bearing device includes: a thrust sleeve 41 and a thrust ring 42 fixed to a rotary shaft 14; flange parts 52, 54 which are respectively provided at outer periphery parts of the thrust sleeve 41 and the thrust ring 42 so as to form a predetermined gap S with the outer periphery parts; a thrust bearing 23 in which an outer periphery part is supported by a housing 15 and an inner periphery part is disposed in the predetermined gap S; and a deformation part which increases a contact area between the flange parts 52, 54 and the thrust bearing 23 by the flange parts 52, 54 deforming when a thrust load acts on the rotary shaft 14.SELECTED DRAWING: Figure 2

Description

  The present invention relates to a thrust bearing device for supporting a rotating shaft rotatably and receiving a thrust load acting in an axial direction of the rotating shaft in a turbocharger configured by connecting a turbine and a compressor by a rotating shaft, The present invention relates to a supercharger to which a thrust bearing device is applied.

  In the exhaust turbine supercharger, a compressor and a turbine are integrally connected by a rotating shaft, and the compressor and the turbine are rotatably accommodated in a housing. Then, exhaust gas is supplied into the housing, and the rotating shaft is driven to rotate by rotating the turbine, thereby rotating the compressor. The compressor sucks air from the outside, pressurizes it with an impeller to form compressed air, and supplies this compressed air to an internal combustion engine or the like.

  In such an exhaust turbine supercharger, the rotating shaft is rotatably supported by a journal bearing and a thrust bearing with respect to the housing. A conventional thrust bearing device includes a thrust sleeve and a thrust ring fixed to an outer peripheral portion of a rotating shaft, and a thrust bearing having an outer peripheral portion fixed to a housing and an inner peripheral portion fitted between the thrust sleeve and the thrust ring. It is configured. Therefore, the thrust load acting on one side in the axial direction of the rotating shaft is received by the thrust bearing via the thrust sleeve, and the thrust load acting on the other side in the axial direction of the rotating shaft is received by the thrust bearing via the thrust ring. Take it.

  An example of such a thrust bearing device is described in Patent Document 1 below.

JP 2013-002559 A

  Generally, the thrust load increases with the increase in the rotation speed of the turbocharger. At this time, it is considered that the increase rate in the low rotation range is high and the increase rate in the high rotation range is low. It was. That is, when the variation of the thrust load with respect to the increase in the number of revolutions is represented by a graph, it can be represented by a curved shape that is convex upward. However, in reality, the rate of increase in the low rotation range is low and the rate of increase in the high rotation range is high, and when the variation in thrust load with respect to the increase in the rotational speed is represented by a graph, it becomes a convex shape downward It becomes such a curved shape. Therefore, there is a difference between the variation of the thrust load with respect to the rotational speed at the time of design and the variation of the thrust load with respect to the actual rotational speed, and the load capacity of the thrust bearing device may not be adapted to the load that actually acts on the rotating shaft. is there.

  An object of the present invention is to solve the above-described problems, and to provide a thrust bearing device and a supercharger that can reduce the size of the device by adapting the load capacity to a load that actually acts on a rotating shaft. To do.

  In order to achieve the above-mentioned object, a thrust bearing device of the present invention includes a cylindrical member fixed to a rotating shaft, and a disc provided on the outer periphery of the cylindrical member with a predetermined gap in the axial direction of the rotating shaft. A pair of flange portions having a shape, a thrust bearing in which an outer peripheral portion is supported by a housing and an inner peripheral portion is disposed in the predetermined gap, and the flange when a load is applied to one axial side of the rotary shaft Or a deformation portion that increases a contact area between the flange portion and the thrust bearing by deforming the portion or the thrust bearing.

  Therefore, when a thrust load is applied to the rotating shaft, the flange portion of the cylindrical member or the thrust bearing is deformed by the deforming portion, thereby increasing the contact area between the flange portion and the thrust bearing. That is, the bearing effective area changes according to the variation of the thrust load, and the apparatus can be made compact by adapting the bearing load capacity to the load actually acting on the rotating shaft.

  In the thrust bearing device of the present invention, an inclined surface having a ring shape in which an outer diameter side is located on the thrust bearing side and an inner diameter side is located on the flange portion side is provided on one surface of the flange portion and the thrust bearing facing each other. It is characterized by being able to.

  Therefore, by providing the inclined surface on the flange portion or the thrust bearing, the deformation amount of the flange portion or the thrust bearing of the cylindrical member increases as the thrust load acting on the rotating shaft increases, and the inclined surface and the flange portion or the thrust bearing are increased. As a result, the bearing effective area can be appropriately changed according to the variation of the thrust load.

  In the thrust bearing device of the present invention, the inclined surface is provided on a surface of the flange portion facing the thrust bearing, and an inner diameter side is separated from the thrust bearing compared to an outer diameter side.

  Therefore, by providing the inclined surface on the surface of the flange portion that faces the thrust bearing, the inclined surface can be easily provided without changing the shape of the thrust bearing.

  In the thrust bearing device of the present invention, the deforming portion is provided in a ring shape at a connecting portion between the cylindrical member and the flange portion, and a thickness of the rotating shaft in an axial direction is the rotating shaft in the flange portion. The thin-walled portion is set to be thinner than the thickness in the axial direction.

  Therefore, by making the deformed portion a thin portion, when a thrust load is applied to the rotating shaft, the flange portion of the cylindrical member can be easily deformed to increase the contact area with the thrust bearing, thereby simplifying the structure. Can be achieved.

  In the thrust bearing device of the present invention, the cylindrical member is a thrust sleeve and a thrust ring fixed in series in the axial direction on the outer peripheral portion of the rotating shaft.

  Therefore, by using the existing thrust sleeve and thrust ring as the cylindrical member, it is possible to prevent an increase in the number of parts and suppress an increase in cost, and the thrust load on one side and the other side in the axial direction of the rotating shaft. Can respond.

  In the thrust bearing device of the present invention, the inclined surface is provided on a surface of the thrust bearing that faces the flange portion, and an outer diameter side is separated from the thrust bearing as compared with an inner diameter side.

  Accordingly, by providing the inclined surface on the surface of the thrust bearing that faces the flange portion, only the shape of the thrust bearing needs to be changed, and an increase in the number of components can be prevented and an increase in manufacturing cost can be suppressed.

  In the thrust bearing device of the present invention, the deforming portion is provided in a ring shape on an inner peripheral portion of the thrust bearing, and a thickness in the axial direction of the rotating shaft is equal to that of the rotating shaft in the outer peripheral portion of the thrust bearing. The thin-walled portion is set to be thinner than the thickness in the axial direction.

  Therefore, by making the deformed part a thin part, when a thrust load is applied to the rotating shaft, the thrust bearing can be easily deformed to increase the contact area with the flange part, and the structure can be simplified. Can do.

  In the thrust bearing device of the present invention, the deforming portion is a pair of deforming flange portions having a disk shape provided in the inner peripheral portion of the thrust bearing with a deformation gap in the axial direction of the rotating shaft. It is a feature.

  Therefore, by making the deformed portion a deformed flange portion, when a thrust load acts on the rotating shaft, the deformed flange portion can be easily deformed and the contact area with the flange portion can be increased.

  The turbocharger according to the present invention includes a hollow housing, the thrust bearing device mounted on the housing, a rotating shaft rotatably supported by the thrust bearing device on the housing, and the rotating shaft. And a compressor provided at the other end of the rotating shaft in the axial direction.

  Accordingly, the turbine is rotated by the exhaust gas, and the rotational force is transmitted to the turbine via the rotating shaft, so that the turbine rotates. At this time, when a thrust load is applied to the rotating shaft, the flange portion of the cylindrical member or the thrust bearing is deformed by the deformable portion, thereby increasing the contact area between the flange portion and the thrust bearing. That is, the bearing effective area changes according to the variation of the thrust load, and the apparatus can be made compact by adapting the bearing load capacity to the load actually acting on the rotating shaft.

  The turbocharger according to the present invention includes a hollow housing, a rotating shaft rotatably supported by the housing, a turbine provided at one end of the rotating shaft in an axial direction, and a shaft of the rotating shaft. A compressor provided at the other end in the direction, a pressure adjusting space provided in a ring shape between the back side of the compressor and the housing, a discharge port side space of the compressor, and the pressure adjusting space And a second seal gap provided between the space for pressure adjustment and the space on the rotary shaft side.

  Therefore, when the pressure in the discharge side space is increased, a thrust load to the turbine side acts on the rotating shaft via the compressor, and the first seal gap is increased, while the second seal gap is reduced, and pressure adjustment is performed. The pressure in the space increases. When the pressure in the pressure adjusting space increases, a thrust load to the compressor side acts on the rotating shaft via the compressor. As a result, the thrust load can be reduced by the differential pressure between the discharge port side space and the pressure adjusting space, and the device can be made compact by adapting the load capacity to the load actually acting on the rotating shaft. be able to.

  According to the thrust bearing device and the supercharger of the present invention, the device can be made compact by adapting the load capacity to the load that actually acts on the rotating shaft.

FIG. 1 is an overall configuration diagram illustrating an exhaust turbine supercharger according to a first embodiment. FIG. 2 is a cross-sectional view illustrating the thrust bearing device according to the first embodiment. FIG. 3 is a cross-sectional view illustrating the operation of the thrust bearing device. FIG. 4 is a cross-sectional view illustrating the operation of the thrust bearing device. FIG. 5 is a graph showing the thrust load with respect to the turbocharger rotational speed. FIG. 6 is a cross-sectional view illustrating a thrust bearing device according to the second embodiment. FIG. 7 is a cross-sectional view illustrating a thrust bearing device according to a third embodiment. FIG. 8 is a graph showing the thrust load with respect to the turbocharger rotational speed.

  Exemplary embodiments of a thrust bearing device and a supercharger according to the present invention will be explained below in detail with reference to the accompanying drawings. In addition, this invention is not limited by this embodiment, and when there are two or more embodiments, what comprises combining each embodiment is also included.

[First Embodiment]
FIG. 1 is an overall configuration diagram illustrating an exhaust turbine supercharger according to the first embodiment, and FIG. 2 is a cross-sectional view illustrating a thrust bearing device according to the first embodiment.

  As shown in FIG. 1, the exhaust turbine supercharger 11 is mainly composed of a turbine 12, a compressor 13, and a rotating shaft 14, which are accommodated in a housing 15.

  The housing 15 is hollow and has a turbine housing 15A that forms a first space S1 that houses the configuration of the turbine 12, a compressor housing 15B that forms a second space S2 that houses the configuration of the compressor 13, and a rotation And a bearing housing 15 </ b> C forming a third space S <b> 3 that accommodates the shaft 14. The third space S3 of the bearing housing 15C is located between the first space S1 of the turbine housing 15A and the second space S2 of the compressor housing 15B.

  The rotary shaft 14 is rotatably supported at its end on the turbine 12 side by a journal bearing 21 that is a turbine side bearing, and is rotatably supported at its end on the compressor 13 side by a journal bearing 22 that is a compressor side bearing. The thrust bearing 23 restricts movement in the axial direction in which the rotating shaft 14 extends. The rotating shaft 14 has a turbine disk 24 of the turbine 12 fixed to one end in the axial direction. The turbine disk 24 is accommodated in the first space S1 of the turbine housing 15A, and a plurality of turbine blades 25 having an axial flow type are provided on the outer peripheral portion at predetermined intervals in the circumferential direction. The rotary shaft 14 has a compressor impeller 26 of the compressor 13 fixed to the other end in the axial direction. The compressor impeller 26 is accommodated in the second space S2 of the compressor housing 15B, and a plurality of blades 27 are provided on the outer peripheral portion at predetermined intervals in the circumferential direction.

  The turbine housing 15 </ b> A is provided with an exhaust gas inlet passage 31 and an exhaust gas outlet passage 32 with respect to the turbine blades 25. The turbine housing 15 </ b> A is provided with a turbine nozzle 33 between the inlet passage 31 and the turbine blade 25, and the axial exhaust gas flow statically expanded by the turbine nozzle 33 is supplied to the plurality of turbine blades 25. By being guided, the turbine 12 can be driven and rotated. The compressor housing 15B is provided with a suction port 34 and a compressed air discharge port 35 with respect to the compressor impeller 26. In the compressor housing 15 </ b> B, a diffuser 36 is provided between the compressor impeller 26 and the compressed air discharge port 35. The air compressed by the compressor impeller 26 is exhausted through the diffuser 36.

  Therefore, in the exhaust turbine supercharger 11, the turbine 12 is driven by exhaust gas discharged from an engine (not shown), the rotation of the turbine 12 is transmitted to the rotating shaft 14, and the compressor 13 is driven. Compresses the combustion gas and supplies it to the engine. Therefore, the exhaust gas from the engine passes through the exhaust gas inlet passage 31 and is statically expanded by the turbine nozzle 33, and the exhaust gas flow in the axial direction is guided to the plurality of turbine blades 25. The turbine 12 is driven to rotate through the turbine disk 24 to which is fixed. The exhaust gas that has driven the plurality of turbine blades 25 is discharged to the outside from the outlet passage 32. On the other hand, when the rotating shaft 14 is rotated by the turbine 12, the integrated compressor impeller 26 is rotated and air is sucked through the suction port 34. The sucked air is pressurized by the compressor impeller 26 to become compressed air, and this compressed air passes through the diffuser 36 and is supplied to the engine from the compressed air discharge port 35.

  In the above-described exhaust turbine supercharger 11, as shown in FIGS. 1 and 2, the thrust bearing device 40 of the first embodiment includes a thrust sleeve (cylinder member) 41, a thrust ring (cylinder member) 42, A thrust bearing 23 and a leaf spring 43 are provided.

  The rotary shaft 14 is provided with a large diameter portion 14A supported by the journal bearings 21 and 22 and a small diameter portion 14B supported by the thrust bearing 23, and a stepped portion is provided between the large diameter portion 14A and the small diameter portion 14B. 14C is provided. The thrust bearing 23 has a disk shape in which a through-hole 23a through which the rotary shaft 14 passes is formed, and pressure receiving surfaces 23A and 23B that are substantially orthogonal to the axial direction of the rotary shaft 14 are provided on each plane side.

  The thrust sleeve 41 is fixed to the outer peripheral portion of the small-diameter portion 14B of the rotating shaft 14 so as not to be relatively movable in the circumferential direction and the axial direction. The thrust sleeve 41 includes a sleeve body 51 having a cylindrical shape, and a flange portion 52 having a disc shape and integrally provided on one side of the sleeve body 51 in the axial direction. The thrust ring 42 is fixed to the outer peripheral portion of the small-diameter portion 14B of the rotating shaft 14 so as not to be relatively movable in the circumferential direction and the axial direction. The thrust ring 42 includes a cylindrical ring main body 53 and a disk-shaped flange portion 54 that is integrally provided on one side of the ring main body 53 in the axial direction. In the thrust sleeve 41 and the thrust ring 42, the sleeve main body 51 and the ring main body 53 are arranged in series in the axial direction of the rotary shaft 14, and one end of the sleeve main body 51 and one end of the ring main body 53 are in contact with each other. The thrust sleeve 41 has the other end of the sleeve body 51 abutted against the back surface 26a of the compressor impeller 26, and the thrust ring 42 has the other end of the ring body 53 on the end surface of the stepped portion 14C of the rotating shaft 14. It is in contact.

  The thrust sleeve 41 and the thrust ring 42 are fixed in series on the outer peripheral portion of the rotating shaft 14, whereby a predetermined gap S <b> 4 along the axial direction of the rotating shaft 14 is provided between the flange portions 52 and 54. The thrust bearing 23 has an outer peripheral portion fixed to the bearing housing 15C and an inner peripheral portion disposed in the predetermined gap S4. The leaf spring 43 has a disk shape with a through hole provided at the center, and the outer peripheral portion is fixed to the bearing housing 15 </ b> C, and the inner peripheral portion is in contact with the flange portion 52 of the thrust sleeve 41. In other words, the leaf spring 43 presses the thrust sleeve 41 toward the thrust ring 42 via the flange portion 52 by its urging force.

  In the present embodiment, the thrust bearing device 40 according to the first embodiment has the flange portions 52 and 54 of the thrust sleeve 41 and the thrust ring 42 when a load is applied to one axial side of the rotary shaft 14. As a result of deformation, a deformation portion is provided that increases the contact area between the flange portions 52 and 54 and the thrust bearing 23.

  The thrust sleeve 41 includes an outer peripheral side inclined surface 61, an inner peripheral side inclined surface 62, a top portion 63, and a thin portion 64. The outer peripheral inclined surface 61 is provided on the surface of the flange portion 52 that faces the thrust bearing 23 and is arranged on the outer peripheral portion side so that the outer diameter side is separated from the pressure receiving surface 23A of the thrust bearing 23 compared to the inner diameter side. It has a flat inclined surface. The inner peripheral inclined surface 62 is provided on the surface of the flange portion 52 that faces the thrust bearing 23, and is disposed on the inner peripheral portion side so that the inner diameter side is separated from the pressure receiving surface 23A of the thrust bearing 23 compared to the outer diameter side. It is a flat inclined surface that forms a ring shape. The top 63 is a vertex that forms a ring shape provided between the outer peripheral inclined surface 61 and the inner peripheral inclined surface 62. Since the outer peripheral side inclined surface 61 and the inner peripheral side inclined surface 62 are inclined in the radial direction with respect to the pressure receiving surface 23A of the thrust bearing 23, the apex 63 contacts the pressure receiving surface 23A of the thrust bearing 23. Yes. The inclined surfaces 61 and 62 may be curved surfaces that are curved in the radial direction.

  The thin portion 64 is provided in a ring shape at the connecting portion between the sleeve body 51 and the flange portion 52. The thin portion 64 is set such that the thickness of the rotating shaft 14 in the axial direction is thinner than the thickness of the flange portion 52 in the axial direction of the rotating shaft 14. Therefore, the thrust sleeve 41 can be elastically deformed in the axial direction of the rotary shaft 14 with the thin portion 64 as a fulcrum with respect to the sleeve body 51 when a thrust load acts on the flange portion 52. Therefore, the thin portion 64 functions as the deformed portion described above.

  Further, the thrust ring 42 is provided with an inclined surface 65, a top portion 66, and a thin portion 67. The inclined surface 65 is provided on a surface of the flange portion 54 facing the thrust bearing 23, and is a flat inclined surface having a ring shape in which the inner diameter side is separated from the pressure receiving surface 23B of the thrust bearing 23 as compared to the outer diameter side. ing. The top portion 66 is a vertex having a ring shape provided at the outer diameter side end portion of the inclined surface 65. Since the inclined surface 65 is inclined in the radial direction with respect to the pressure receiving surface 23B of the thrust bearing 23, the top 66 is in contact with the pressure receiving surface 23B of the thrust bearing 23. Each inclined surface 65 may be a curved surface curved in the radial direction.

  The thin portion 67 is provided in a ring shape at the connection portion between the ring main body 53 and the flange portion 54. The thin portion 67 is set such that the thickness of the rotating shaft 14 in the axial direction is thinner than the thickness of the flange portion 54 in the axial direction of the rotating shaft 14. Therefore, the thrust ring 42 can be elastically deformed in the axial direction of the rotary shaft 14 with the thin portion 67 as a fulcrum with respect to the ring body 53 when the thrust load acts on the flange portion 54. Therefore, this thin portion 67 functions as the deformed portion described above.

  Here, the effect | action of the thrust bearing apparatus 40 mentioned above is demonstrated. 3 and 4 are cross-sectional views showing the operation of the thrust bearing device.

  Therefore, when the exhaust turbine supercharger 11 is stopped and the rotation of the rotary shaft 14 is stopped, the thrust sleeve 41 is only the top 63 of the flange portion 52 in the thrust bearing device 40 as shown in FIG. Is in contact with the pressure receiving surface 23A of the thrust bearing 23, and the thrust ring 42 is in contact with the pressure receiving surface 23B of the thrust bearing 23 only at the top 66 of the flange portion 54.

  Then, when the exhaust turbine supercharger 11 is operated to rotate the rotating shaft 14 and a thrust load F1 acts on one side of the rotating shaft 14 in the axial direction as shown in FIG. 3, the bearing housing 15C is fixed. The rotating shaft 14, the thrust sleeve 41, and the thrust ring 42 are slightly moved in the same direction with respect to the thrust bearing 23 thus formed. Then, in the thrust ring 42, the flange portion 54 is deformed in the direction opposite to the thrust load F1 with the thin portion 67 as a fulcrum, and a part or all of the inclined surface 65 contacts the pressure receiving surface 23B of the thrust bearing 23. That is, the contact area between the flange portion 54 of the thrust ring 42 and the pressure receiving surface 23B of the thrust bearing 23 increases. That is, as the thrust load F1 increases, the amount of deformation of the flange portion 54 increases, so that the contact area between the inclined surface 65 and the pressure receiving surface 23B of the thrust bearing 23 increases. Therefore, the thrust bearing 23 has a bearing effective area that increases with an increase in the thrust load F1, so that a thrust load capacity corresponding to the magnitude of the thrust load F1 is ensured.

  On the other hand, as shown in FIG. 4, when a thrust load F2 acts on the other side in the axial direction with respect to the rotating shaft 14, the rotating shaft 14, the thrust sleeve 41, and the thrust bearing 23 to which the bearing housing 15C is fixed. The thrust ring 42 moves slightly in the same direction. Then, in the thrust sleeve 41, the flange portion 52 is deformed in the direction opposite to the thrust load F2 with the thin portion 64 as a fulcrum, and part or all of the inner peripheral inclined surface 62 contacts the pressure receiving surface 23A of the thrust bearing 23. . That is, the contact area between the flange portion 52 of the thrust sleeve 41 and the pressure receiving surface 23A of the thrust bearing 23 increases. That is, as the thrust load F2 increases, the deformation amount of the flange portion 52 increases, so that the contact area between the inner peripheral inclined surface 62 and the pressure receiving surface 23A of the thrust bearing 23 increases. Therefore, the thrust bearing 23 has a bearing effective area that increases with an increase in the thrust load F2, so that a thrust load capacity commensurate with the magnitude of the thrust load F2 is ensured.

  In the above description, as shown in FIG. 3, when the thrust load F1 is applied to the rotating shaft 14, the flange portion 54 of the thrust ring 42 is deformed by the thrust bearing 23, but the thrust is applied by the urging force of the leaf spring 43. The flange portion 52 of the sleeve 41 is also deformed, but may or may not contact the pressure receiving surface 23A of the thrust bearing 23. Further, as shown in FIG. 4, when a thrust load F2 is applied to the rotating shaft 14, the flange portion 52 of the thrust sleeve 41 is deformed by the thrust bearing 23, but the flange portion 54 of the thrust ring 42 may not be deformed. Also good.

  FIG. 5 is a graph showing the thrust load with respect to the turbocharger rotational speed. Conventionally, as shown by the solid line in FIG. 5, it is considered that the thrust load increases with the increase in the turbocharger rotation speed, the increase rate in the low rotation range is high, and the increase rate in the high rotation range is low. It is represented by a curved shape that is convex upward. However, according to the experiment by the present applicant, the thrust load with respect to the turbocharger rotation speed is represented by a plurality of black spots, the increase rate in the low rotation range is low, and the increase rate in the high rotation range is high. As shown by the alternate long and short dash line in FIG. Therefore, according to the thrust bearing device 40 of the present embodiment, as described above, the contact area between the flange portions 52 and 54 and the thrust bearing 23 increases as the thrust load increases. 5 and the thrust load are represented by a one-dot chain line in FIG. 5, and a thrust load capacity corresponding to the magnitude of the thrust load can be ensured.

  As described above, in the thrust bearing device according to the first embodiment, the thrust sleeve 41 and the thrust ring 42 fixed to the rotating shaft 14 are provided, and the thrust sleeve 41 and the thrust ring 42 are provided with a predetermined gap S4 between them. Flange portions 52, 54, the thrust bearing 23 whose outer peripheral portion is supported by the housing 15 and whose inner peripheral portion is disposed in the predetermined gap S 4, and the flange portions 52, 54 when a thrust load is applied to the rotary shaft 14. The deformation part which increases the contact area of the flange parts 52 and 54 and the thrust bearing 23 is provided.

  Therefore, when a thrust load is applied to the rotary shaft 14, the flange portions 52 and 54 of the thrust sleeve 41 and the thrust ring 42 are deformed by the deformed portion, thereby reducing the contact area between the flange portions 52 and 54 and the thrust bearing 23. Will increase. That is, the bearing effective area changes according to the variation of the thrust load, and the apparatus can be made compact by adapting the bearing load capacity to the load actually acting on the rotating shaft 14.

  In the thrust bearing device of the first embodiment, inclined surfaces 62 and 65 having a ring shape are provided on the surfaces of the flange portions 52 and 54 of the thrust sleeve 41 and the thrust ring 42 facing the thrust bearing 23. Therefore, by providing the inclined surfaces 62, 65 on the flange portions 52, 54, the amount of deformation of the flange portions 52, 54 increases as the thrust load acting on the rotating shaft 14 increases, and the inclined surfaces 62, 65 The contact area with the thrust bearing 23 is increased, and the effective bearing area can be appropriately changed according to the variation of the thrust load.

  In this case, the inclined surfaces 62 and 65 can be easily provided without changing the shape of the thrust bearing 23 by providing the inclined surfaces 62 and 65 on the flange portions 52 and 54 of the thrust sleeve 41 and the thrust ring 42, respectively. it can. Further, by using the existing thrust sleeve 41 and the thrust ring 42, it is possible to prevent an increase in the number of parts and suppress an increase in cost, and the thrust load on one side and the other side in the axial direction of the rotating shaft 14 Can respond.

  In the thrust bearing device of the first embodiment, thin portions 64 and 67 are provided on the thrust sleeve 41 and the thrust ring 42 as deforming portions. Therefore, by making the deformed portions thin-walled portions 64 and 67, when a thrust load is applied to the rotating shaft 14, the flange portions 52 and 54 can be easily deformed to increase the contact area with the thrust bearing 23. The structure can be simplified.

  Further, in the supercharger of the first embodiment, the hollow housing 15, the thrust bearing device 40 mounted on the housing 15, and the rotation supported rotatably on the housing 15 by the thrust bearing device 40. A shaft 14, a turbine 12 provided at one end of the rotating shaft 14 in the axial direction, and a compressor 13 provided at the other end of the rotating shaft 14 in the axial direction are provided.

  Accordingly, the turbine 12 is rotated by the exhaust gas, and the rotational force is transmitted to the turbine 12 via the rotating shaft 14 to rotate the turbine 12. At this time, when a thrust load is applied to the rotary shaft 14, the flange portions 52 and 54 of the thrust sleeve 41 and the thrust ring 42 are deformed by the deforming portion, so that the contact area between the flange portions 52 and 54 and the thrust bearing 23 is changed. Will be increased. That is, the bearing effective area changes according to the variation of the thrust load, and the apparatus can be made compact by adapting the bearing load capacity to the load actually acting on the rotating shaft 14.

[Second Embodiment]
FIG. 6 is a cross-sectional view illustrating a thrust bearing device according to the second embodiment. In addition, the same code | symbol is attached | subjected to the member which has the same function as embodiment mentioned above, and detailed description is abbreviate | omitted.

  In the second embodiment, as shown in FIG. 6, the thrust bearing device 70 includes a thrust sleeve (cylinder member) 71, a thrust ring (cylinder member) 72, a thrust bearing 73, and a leaf spring 43. .

  The thrust sleeve 71 is fixed to the outer peripheral portion of the small-diameter portion 14B of the rotating shaft 14 so as not to be relatively movable in the circumferential direction and the axial direction. The thrust sleeve 71 includes a sleeve body 81 having a cylindrical shape and a flange portion 82 having a disk shape and integrally provided on one side of the sleeve body 81 in the axial direction. Further, the thrust ring 72 is fixed to the outer peripheral portion of the small-diameter portion 14B of the rotating shaft 14 so as not to be relatively movable in the circumferential direction and the axial direction. The thrust ring 72 includes a cylindrical ring main body 83 and a disk-shaped flange portion 84 that is integrally provided on one side of the ring main body 83 in the axial direction. In the thrust sleeve 71 and the thrust ring 72, the sleeve main body 81 and the ring main body 83 are arranged in series in the axial direction of the rotating shaft 14, and one end of the sleeve main body 81 and one end of the ring main body 83 are in contact with each other. The thrust sleeve 71 has the other end of the sleeve main body 81 in contact with the back surface 26a of the compressor impeller 26, and the thrust ring 72 has the other end of the ring main body 83 on the end surface of the stepped portion 14C of the rotating shaft 14. It is in contact.

  The thrust sleeve 71 and the thrust ring 72 are fixed in series on the outer peripheral portion of the rotating shaft 14, whereby a predetermined gap S <b> 4 along the axial direction of the rotating shaft 14 is provided between the flange portions 82 and 84. The thrust bearing 73 has a disk shape in which a through hole 73a through which the rotary shaft 14 passes is formed, and pressure-receiving surfaces 73A and 73B that are substantially orthogonal to the axial direction of the rotary shaft 14 are provided on each plane side. The thrust bearing 73 has an outer peripheral portion fixed to the bearing housing 15C and an inner peripheral portion disposed in the predetermined gap S4. The plate spring 43 has a disk shape with a through hole provided in the center, and the outer peripheral portion is fixed to the bearing housing 15 </ b> C, and the inner peripheral portion is in contact with the flange portion 82 of the thrust sleeve 71. That is, the leaf spring 43 presses the thrust sleeve 71 toward the thrust ring 72 via the flange portion 82 by its own urging force.

  In the present embodiment, the thrust bearing device 70 according to the second embodiment is configured such that when a load is applied to one axial side of the rotary shaft 14, the thrust bearing 73 is deformed, whereby each flange portion 82, A deforming portion for increasing the contact area between the thrust bearing 84 and the thrust bearing 73 is provided.

  The thrust bearing 73 is provided with a pair of deformation flange portions 91 and 92 having a disk shape with a deformation gap S5 in the axial direction of the rotary shaft 14 in the inner peripheral portion. The first deformation flange portion 91 is provided with a first inclined surface 93, a top portion 94, and a thin portion 95. The first inclined surface 93 is provided on a surface facing the thrust sleeve 71 in the first deformation flange portion 91, and the outer diameter side is separated from the facing surface of the flange portion 82 of the thrust sleeve 71 compared to the inner diameter side. It is a flat inclined surface. The top portion 94 is a vertex having a ring shape provided at the inner diameter side end portion of the first inclined surface 93. The top 94 is in contact with the thrust sleeve 71 because the first inclined surface 93 is inclined in the radial direction with respect to the thrust sleeve 71.

  The thin portion 95 is provided in a ring shape at the branch portion of the first deformation flange portion 91. The thin portion 95 is set such that the thickness of the rotating shaft 14 in the axial direction is thinner than the thickness of the thrust bearing 73 in the axial direction of the rotating shaft 14. Therefore, the thrust bearing 73 can be elastically deformed in the axial direction of the rotary shaft 14 with the thin deformation portion 95 serving as a fulcrum when the thrust load is applied to the first deformation flange portion 91. Therefore, this thin portion 95 functions as the deformed portion described above. The thin portion 95 is formed thinner than the inner diameter side end portion of the first deformation flange portion 91.

  Further, the second deformation flange portion 92 is provided with a second inclined surface 96, a top portion 97, and a thin portion 98. The second inclined surface 96 is provided on the surface facing the thrust ring 72 in the second deformed flange portion 92, and the outer diameter side is separated from the facing surface of the flange portion 84 of the thrust ring 72 compared to the inner diameter side. It is a flat inclined surface. The top portion 97 is a vertex having a ring shape provided at the inner diameter side end portion of the second inclined surface 96. The top 97 is in contact with the thrust ring 72 because the second inclined surface 96 is inclined in the radial direction with respect to the thrust ring 72.

  The thin portion 98 is provided in a ring shape at the branch portion of the second deformation flange portion 92. The thin portion 98 is set such that the thickness of the rotating shaft 14 in the axial direction is thinner than the thickness of the thrust bearing 73 in the axial direction of the rotating shaft 14. Therefore, the thrust bearing 73 can be elastically deformed in the axial direction of the rotary shaft 14 with the thin portion 98 as a fulcrum when the thrust load is applied to the second deformation flange portion 92. Therefore, the thin portion 98 functions as the deformed portion described above. The thin portion 98 is formed thinner than the inner diameter side end portion of the second deformation flange portion 92.

  Therefore, when the exhaust turbine supercharger 11 is stopped and the rotation of the rotary shaft 14 is stopped, in the thrust bearing device 70, the thrust bearing 73 has only the top portions 94 and 97 of the deformed flange portions 91 and 92. The flanges 82 and 84 of the thrust sleeve 71 and the thrust ring 72 are in contact with each other.

  Then, when the exhaust turbine supercharger 11 is operated to rotate the rotating shaft 14 and a thrust load acts on one side (left side in FIG. 6) in the axial direction with respect to the rotating shaft 14, the bearing housing 15C is fixed. The rotating shaft 14, the thrust sleeve 71, and the thrust ring 72 are slightly moved in the same direction with respect to the thrust bearing 73 thus formed. Then, in the thrust bearing 73, the second deformation flange portion 92 is deformed in the same direction as the thrust load with the thin portion 98 as a fulcrum, and a part or all of the second inclined surface 96 (pressure receiving surface 73B) contacts the flange portion 84. To do. That is, the contact area between the flange portion 84 of the thrust ring 72 and the pressure receiving surface 73B of the thrust bearing 73 increases. That is, as the thrust load increases, the amount of deformation of the second deformation flange portion 92 increases, so that the contact area between the second inclined surface 96 (pressure receiving surface 73B) and the flange portion 84 increases. For this reason, the thrust bearing 73 has a bearing effective area that increases as the thrust load increases, so that a thrust load capacity corresponding to the magnitude of the thrust load is ensured.

  On the other hand, when a thrust load acts on the other side (right side in FIG. 6) in the axial direction with respect to the rotating shaft 14, the rotating shaft 14, the thrust sleeve 71, and the thrust bearing 73 to which the bearing housing 15C is fixed. The thrust ring 72 moves slightly in the same direction. Then, in the thrust bearing 73, the first deformation flange portion 91 is deformed in the same direction as the thrust load with the thin portion 95 as a fulcrum, and part or all of the first inclined surface 93 is in contact with the flange portion 82. That is, the contact area between the flange portion 82 of the thrust sleeve 71 and the pressure receiving surface 23A of the thrust bearing 73 increases. That is, as the thrust load increases, the deformation amount of the first deformation flange portion 91 increases, so that the contact area between the first inclined surface 93 (pressure receiving surface 73A) and the flange portion 82 increases. For this reason, the thrust bearing 73 has a bearing effective area that increases as the thrust load increases, so that a thrust load capacity corresponding to the magnitude of the thrust load is ensured.

  As described above, in the thrust bearing device according to the second embodiment, the thrust sleeve 71 and the thrust ring 72 fixed to the rotating shaft 14 and the outer periphery of the thrust sleeve 71 and the thrust ring 72 are provided with a predetermined gap S4. The flange portions 82 and 84, the thrust bearing 73 whose outer peripheral portion is supported by the housing 15 and whose inner peripheral portion is disposed in the predetermined gap S4, and the thrust bearing 73 is deformed when a thrust load is applied to the rotary shaft 14. By doing so, a deformed portion that increases the contact area between the flange portions 82 and 84 and the thrust bearing 73 is provided.

  Therefore, when a thrust load is applied to the rotating shaft 14, the thrust bearing 73 is deformed by the deforming portion, and the contact area between the flange portions 82 and 84 and the thrust bearing 73 is increased. That is, the bearing effective area changes according to the variation of the thrust load, and the apparatus can be made compact by adapting the bearing load capacity to the load actually acting on the rotating shaft 14.

  In the thrust bearing device of the second embodiment, the inclined surfaces 93 and 96 are provided on the surface of the thrust bearing 73 that faces the flange portions 82 and 84. Therefore, it is only necessary to change the shape of the thrust bearing 73, and an increase in the number of parts can be prevented and an increase in manufacturing cost can be suppressed.

  In the thrust bearing device of the second embodiment, thin portions 95 and 98 are provided on the inner peripheral side of the thrust bearing 73 as the deforming portion. Therefore, by making the deformed portions thin-walled portions 95 and 98, when a thrust load is applied to the rotating shaft 14, the thrust bearing 73 can be easily deformed and the contact area with the flange portions 82 and 84 can be increased. The structure can be simplified.

  In the thrust bearing device of the second embodiment, as a deforming portion, a pair of deforming flange portions 91 and 92 are provided with a deformation gap S5 provided in the inner peripheral portion of the thrust bearing 73. Therefore, the deformed portions are the deformed flange portions 91 and 92, so that when the thrust load is applied to the rotating shaft 14, the deformed flange portions 91 and 92 are easily deformed to increase the contact area with the flange portions 82 and 84. Can be made.

[Third embodiment]
FIG. 7 is a sectional view showing the thrust bearing device of the third embodiment, and FIG. 8 is a graph showing the thrust load with respect to the supercharger rotation speed. In addition, the same code | symbol is attached | subjected to the member which has the same function as embodiment mentioned above, and detailed description is abbreviate | omitted.

  In the third embodiment, as shown in FIG. 7, the exhaust turbine supercharger 100 is mainly configured by a turbine 12 (see FIG. 1), a compressor 13, and a rotating shaft 14, which are in a housing 15. Is housed in.

  In the compressor 13, the compressor impeller 26 is provided with a flange portion 101 on the outer peripheral portion along the circumferential direction, and a cover member 102 is fixed to an end surface facing the diffuser 36 in the bearing housing 15 </ b> C. The cover member 102 has a disk shape with a through-hole formed in the center, the outer peripheral portion is fixed to the bearing housing 15C, and the inner peripheral portion has a predetermined gap with respect to the flange portion 101 of the compressor impeller 26. Thus, they are positioned so as to overlap in the axial direction of the rotating shaft 14. The bearing housing 15 </ b> C has a concave portion 103 formed at a position facing the rear surface 26 a of the compressor impeller 26 and a convex portion 104 that protrudes toward the rear surface 26 a of the compressor impeller 26.

  A pressure adjusting space P2 is provided in a ring shape between the back surface 26a of the compressor impeller 26 and the bearing housing 15C. Further, a first seal gap S11 is provided between the discharge port side space P1 on the compressed air discharge port 35 (diffuser 36) side and the pressure adjusting space P2 in the compressor 13. The first seal gap S11 is an axial gap between the flange portion 101 of the compressor impeller 26 and the cover member 102. Further, a second seal gap S12 is provided between the pressure adjusting space P2 and the rotary shaft side space P3. The rotary shaft side space P3 is a space where the thrust sleeve 71 constituting the thrust bearing device is disposed, and the second seal gap S12 is formed between the back surface 26a of the compressor impeller 26 and the convex portion 104 of the bearing housing 15C. It is an axial gap between them.

  Therefore, when the pressure in the discharge port side space portion P <b> 1 increases during the rotation of the compressor 13, the compressor 13 is pressed toward the turbine 12 and a thrust load toward the turbine 12 is applied to the rotating shaft 14. Then, the compressor 13 is moved to the turbine 12 side by this thrust load, and the first seal gap S11 is increased while the second seal gap S12 is decreased. Then, since the volume of the pressure adjusting space P2 decreases and the pressure increases, the pressure that presses the compressor 13 against the bearing housing 15C increases, and the thrust load toward the compressor 13 with respect to the rotating shaft 14 increases. Works. Then, this thrust load causes the compressor 13 to move to the opposite side of the turbine 12, and the first seal gap S11 is reduced while the second seal gap S12 is increased. That is, the size of the first seal gap S11 and the second seal gap S12 fluctuates due to pressure fluctuations in the discharge port side space P1 and the pressure adjustment space P2, and the thrust load can be reduced. As a result, the apparatus can be made compact by adapting the load capacity to the load that actually acts on the rotating shaft 14.

  FIG. 8 is a graph showing the thrust load with respect to the turbocharger rotational speed. Conventionally, as indicated by the solid line in FIG. 8, it is considered that the thrust load increases with the increase in the turbocharger rotation speed, the increase rate in the low rotation range is high, and the increase rate in the high rotation range is low. It is represented by a curved shape that is convex upward. However, according to the experiment by the present applicant, the thrust load with respect to the turbocharger rotation speed is represented by a plurality of black spots, the increase rate in the low rotation range is low, and the increase rate in the high rotation range is high. As shown by the alternate long and short dash line in FIG. Therefore, according to the exhaust turbine supercharger 100 of the present embodiment, as described above, the thrust load acting on the rotary shaft 14 is reduced by the differential pressure between the discharge port side space portion P1 and the pressure adjusting space portion P2. Therefore, the relationship between the turbocharger rotation speed and the thrust load is represented by a one-dot chain line in FIG. 8, and the thrust load capacity corresponding to the magnitude of the thrust load can be ensured.

  In the turbocharger of the third embodiment, a hollow housing 15, a rotating shaft 14 rotatably supported by the housing 15, and a turbine 12 provided at one end of the rotating shaft 14 in the axial direction, The compressor 13 provided at the other axial end of the rotary shaft 14, the pressure adjusting space P <b> 2 provided in a ring shape between the back surface 26 a of the compressor 13 and the housing 15, and the discharge port of the compressor 13 A first seal gap S11 provided between the side space portion P1 and the pressure adjustment space portion P2, and a second seal gap S11 provided between the pressure adjustment space portion P2 and the rotation shaft side space portion P3. Provided.

  Accordingly, when the pressure in the discharge port side space portion P1 increases, a thrust load to the turbine 12 side acts on the rotary shaft 14 via the compressor 13, and the first seal gap S11 increases, while the second seal gap S12 increases. The pressure is reduced and the pressure in the pressure adjusting space P2 is increased. When the pressure in the pressure adjusting space P <b> 2 increases, a thrust load toward the compressor 13 is applied to the rotating shaft 14 via the compressor 13. As a result, the thrust load can be reduced by the differential pressure between the discharge port side space portion P1 and the pressure adjusting space portion P2, and the compactness of the apparatus can be achieved by adapting the load capacity to the load actually acting on the rotating shaft 14. Can be achieved.

11,100 Exhaust turbine supercharger 12 Turbine 13 Compressor 14 Rotating shaft 15 Housing 21, 22 Journal bearing 23, 73 Thrust bearing 24 Turbine disk 25 Turbine blade 26 Compressor impeller 27 Blade 40, 70 Thrust bearing device 41, 71 Thrust sleeve 42, 72 Thrust ring 43 Leaf spring 51, 81 Sleeve main body 52, 54, 82, 84 Flange 53, 83 Ring main body 61 Outer peripheral side inclined surface 62 Inner peripheral side inclined surface 63, 66, 94, 97 Top 64, 67, 95, 98 Thin portion 65 Inclined surface 91 First deformed flange portion 92 Second deformed flange portion 93 First inclined surface 96 Second inclined surface P1 Discharge port side space portion P2 Pressure adjusting space portion P3 Rotating shaft side space portion S11 First 1 seal gap S12 2nd seal gap

Claims (10)

A cylindrical member fixed to the rotating shaft;
A pair of flange portions having a disk shape provided in the outer circumferential portion of the cylindrical member with a predetermined gap in the axial direction of the rotation shaft;
A thrust bearing having an outer peripheral portion supported by the housing and an inner peripheral portion disposed in the predetermined gap;
A deforming portion that increases a contact area between the flange portion and the thrust bearing by deforming the flange portion or the thrust bearing when a load is applied to one axial side of the rotating shaft;
A thrust bearing device comprising:   An inclined surface having a ring shape in which an outer diameter side is positioned on the thrust bearing side and an inner diameter side is positioned on the flange portion side is provided on one surface of the flange portion and the thrust bearing facing each other. The thrust bearing device according to 1.   The thrust bearing device according to claim 2, wherein the inclined surface is provided on a surface of the flange portion facing the thrust bearing, and an inner diameter side is separated from the thrust bearing as compared with an outer diameter side.   The deforming portion is provided in a ring shape at a connecting portion between the cylindrical member and the flange portion, and the axial thickness of the rotating shaft is set to be smaller than the thickness of the flange portion in the axial direction of the rotating shaft. The thrust bearing device according to claim 3, wherein the thrust bearing device is a thinned portion.   5. The thrust bearing device according to claim 3, wherein the cylindrical member is a thrust sleeve and a thrust ring fixed in series in an axial direction to an outer peripheral portion of the rotating shaft.   The thrust bearing device according to claim 2, wherein the inclined surface is provided on a surface of the thrust bearing that faces the flange portion, and an outer diameter side is separated from the thrust bearing as compared with an inner diameter side.   The deforming portion is provided in a ring shape on the inner peripheral portion of the thrust bearing, and the axial thickness of the rotating shaft is set to be thinner than the axial thickness of the rotating shaft in the outer peripheral portion of the thrust bearing. The thrust bearing device according to claim 6, wherein the thrust bearing device is a thin-walled portion.   The said deformation | transformation part is a pair of deformation | transformation flange part which makes the disk shape provided in the inner peripheral part of the said thrust bearing with the clearance gap for a deformation | transformation in the axial direction of the said rotating shaft. Item 8. The thrust bearing device according to Item 7. A hollow housing;
The thrust bearing device according to any one of claims 1 to 8, which is mounted on the housing;
A rotating shaft rotatably supported by the thrust bearing device on the housing;
A turbine provided at one axial end of the rotating shaft;
A compressor provided at the other axial end of the rotating shaft;
A turbocharger comprising: A hollow housing;
A rotating shaft rotatably supported by the housing;
A turbine provided at one axial end of the rotating shaft;
A compressor provided at the other axial end of the rotating shaft;
A pressure adjusting space provided in a ring shape between the compressor back side and the housing;
A first seal gap provided between a discharge port side space of the compressor and the pressure adjusting space;
A second seal gap provided between the pressure adjusting space and the rotary shaft side space,
A turbocharger comprising:

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