turbocharger

Abstract

Turbocharger (C) with: a warehouse (30); a bearing wall section (21) which has a bearing bore (21a) in which the bearing (30) is arranged; a partition wall section (23) which is provided on a radially outer side of the bearing bore (21a) with reference to the bearing wall section (21) and which forms an interior space (S) with the bearing wall section (21); an oil drain connection (23a) which is formed in the partition section (23) and which is connected to the interior (S); and a guide section (25) with which the bearing wall section (21) facing the interior (S) is provided and which is an inclined surface inclined to move further away from the oil discharge port (23a) in the direction of a plane perpendicular to a central axis of the bearing (30) as it approaches the oil discharge port (23a) in a direction of the central axis, characterized in that an end section of the guide section (25) is arranged opposite the side of the oil discharge port (23a) in the central axis direction (O) at a position of an end surface of the bearing (30).

Description

TECHNICAL FIELD OF THE INVENTION

[0001] The present disclosure relates to a turbocharger including a bearing. This application claims the benefit of priority based on Japanese Patent Application No. 2017-162263, filed on August 25, 2017, and the contents thereof are incorporated herein. TECHNICAL BACKGROUND

[0002] Previously, a turbocharger was known in which a shaft was axially supported by a bearing. A turbine impeller is located at one end of the shaft. A compressor impeller is located at the other end of the shaft. The turbocharger is connected to an engine. The turbine impeller is rotated by exhaust gas discharged from the engine. The rotation of the turbine impeller causes the compressor impeller to rotate through the shaft. The turbocharger compresses air through the rotation of the compressor impeller and delivers the compressed air to the engine.

[0003] For example, in a turbocharger described in Patent Literature 1, a bearing bore (sliding bearing portion) is formed for accommodating a bearing in a housing. A guide groove is formed in the bearing bore. The guide groove is designed to downwardly guide lubricating oil that has flowed into a gap between the bearing and the bearing bore. The lubricating oil is discharged from an oil discharge port.

[0004] A turbocharger according to the preamble of claim 1 of the present invention is shown in Patent Literature 2. Other turbochargers are shown in Patent Literatures 3 to 6. LIST OF SOURCESPatent literature Patent literature 1: JP 2015- 203 360 A Patent literature 2: EP 3 249 192 A1 Patent literature 3: US 9,638,198 B2 Patent literature 3: DE 11 2013 005 883 T5 Patent literature 4: DE 11 2017 001 796 T5 Patent literature 5: DE 697 34 370 T2 SUMMARYTechnical problem

[0005] According to the technology described in Patent Literature 1, lubricating oil is supplied to the oil discharge port, thus improving oil discharge performance. To accommodate higher rotational speeds, there have been attempts to improve bearing performance by increasing the supply amount of lubricating oil. Adapting to the increased supply amount of lubricating oil has created a need for the development of a technology to improve oil discharge performance.

[0006] The present disclosure has an object to provide a turbocharger that can improve oil discharge performance. Solution to the problem

[0007] To solve the aforementioned problem, according to one embodiment of the present disclosure, a turbocharger is provided having all the features of claim 1. Advantageous further developments are the subject of the dependent claims. Effects of revelation

[0008] According to the present disclosure, it is possible to make a turbocharger safer which can improve oil discharge performance. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a schematic sectional view of a turbocharger. Fig. 2 is an enlarged view of the dash-dot line section of Fig. 1. Fig. 3A is a sectional view showing the same as Fig. 1 is. Fig. Figure 3B is a sectional view taken along line IIIB-IIIB of Fig. 3A is generated. Fig. Figure 4 is a sectional view taken along line IV-IV of Fig. 3B is generated. Fig. 5 is an explanatory view for illustrating a modification example. DESCRIPTION OF THE EMBODIMENT

[0009] Now, an embodiment of the present disclosure will be described in detail with reference to the accompanying drawings. The dimensions, materials, and other specific numerical values ​​illustrated in the embodiment are merely examples used to assist in understanding the present disclosure and do not limit the scope of the present disclosure, unless otherwise specifically noted. Elements having substantially the same functions and configurations herein and in the drawings are denoted by the same reference numerals to omit redundant description thereof, and illustrations of elements having no direct relationship to the present disclosure are omitted.

[0010] Fig. 1 is a schematic sectional view of a turbocharger C. In the following description, the direction indicated by the arrow L shown in Fig. 1, a left side of the turbocharger C and the direction indicated by the arrow R, shown in Fig. 1, corresponds to a right side of the turbocharger C. As shown in Fig. 1, the turbocharger C includes a turbocharger main body 1. The turbocharger main body 1 includes a bearing housing 20. A turbine housing 3 is coupled to the left side of the bearing housing 20 via a fastening mechanism 2. A compressor housing 5 is coupled to the right side of the bearing housing 20 via a fastening bolt 4. The bearing housing 20, the turbine housing 3, and the compressor housing 5 are integrally molded.

[0011] A protrusion 20a is provided on an outer peripheral surface of the bearing housing 20. The protrusion 20a is formed near the turbine housing 3. The protrusion protrudes in a radial direction of the bearing housing 20. In addition, a protrusion 3a is provided on an outer peripheral surface of the turbine housing 3. The protrusion 3a is provided near the bearing housing 20. The protrusion 3a protrudes in a radial direction of the turbine housing 3. The bearing housing 20 and the turbine housing 3 are assembled by band-fastening the protrusions 20a and 3a via the fastening mechanism 2. The fastening mechanism 2 is configured, for example, from a G-joint for clamping the protrusions 20a and 3a.

[0012] The bearing housing 20 includes a bearing wall portion 21. A bearing bore 21a is formed in the bearing wall portion 21. The bearing bore 21a extends in a right-and-left direction of the turbocharger C. A bearing 30 is provided in the bearing bore 21a. In Fig. 1, a semi-loose bearing is shown as an example of the bearing 30. However, the bearing 30 may be another radial bearing, such as a fully loose bearing or a roller ball bearing. A shaft 6 is supported by the bearing 30 so as to be rotatable. A left end portion of the shaft 6 is provided with a turbine impeller 7. The turbine impeller 7 is housed in the turbine housing 3 so as to be rotatable. Furthermore, a right end portion of the shaft 6 is provided with a compressor impeller 8. The compressor impeller 8 is housed in the compressor housing 5 so as to be rotatable.

[0013] A suction port 9 is formed in the compressor housing 5. The suction port 9 is opened on the right side of the turbocharger 10. The suction port 9 is connected to an air cleaner (not shown). Furthermore, in a state where the bearing housing 20 and the compressor housing 5 are coupled to each other via the fastening bolt 4, a distribution flow passage 10 is formed. The distribution flow passage 10 is formed on opposite surfaces of the bearing housing 20 and the compressor housing 5. In the distribution flow passage 10, the air is increased in pressure. The distribution flow passage 10 has an annular shape extending from a radially inner side to a radially outer side of the shaft 6. The distribution flow passage 10 is connected to the suction port 9 on the above-mentioned radially inner side via the compressor impeller 8.

[0014] Furthermore, the compressor housing 5 is provided with a compressor scroll flow passage 11. The compressor scroll flow passage 11 has an annular shape. The compressor scroll flow passage 11 is positioned on the radially outer side of the shaft 6 with respect to the distribution flow passage 10. The compressor scroll flow passage 11 is connected to a suction port of an engine (not shown). The compressor scroll flow passage 11 is also connected to the distribution flow passage 10. Thus, air is sucked into the compressor housing 5 through the suction port 9 when the compressor impeller 8 is rotated. The sucked air is compressed and its velocity is increased during a flow path between blades of the compressor impeller 8.The pressure of the compressed air and the increased velocity of the air is increased in the distribution flow passage 10 and the compressor scroll flow passage 11. The increased pressure air is supplied to the suction port of the engine.

[0015] A discharge port 12 is formed in the turbine housing 3. The discharge port 12 is opened on the left side of the turbocharger C. The discharge port 12 is connected to an exhaust gas purification unit (not shown). Furthermore, a flow passage 13 and a turbine scroll flow passage 14 are formed in the turbine housing 3. The turbine scroll flow passage 14 has an annular shape. The turbine scroll flow passage 14 is positioned on the radially outer side of the turbine impeller 7 with respect to the flow passage 13. The turbine scroll flow passage 14 is connected to a gas inflow port (not shown). The exhaust gas discharged from an exhaust manifold of the engine (not shown) is supplied to the gas inflow port. The turbine spiral flow passage 14 is also connected to the turbine blade wheel 7 via the flow passage 13.Thus, exhaust gas supplied to the turbine spiral flow passage 14 via the gas inlet port is supplied to the discharge port 12 via the flow passage 13 and the turbine impeller 7. The exhaust gas to be supplied to the discharge port 12 causes the turbine impeller 7 to rotate during a flow path.

[0016] Then, a rotational force of the turbine impeller 7 is transmitted to the compressor impeller 8 via the shaft 6. The rotational force of the compressor impeller 8 causes the air to be increased in pressure and supplied to the suction port of the engine, as previously described.

[0017] Fig. 2 is an enlarged view of the dash-dot line section of Fig. 1. As in Fig. 2, an oil passage 22 is formed in the bearing housing 20. The oil passage 22 penetrates from an outer side of the bearing housing 20 to the bearing bore 21a. The lubricating oil flows into the bearing bore 21a from the oil passage 22. The bearing 30 is disposed in the bearing bore 21a. An insertion hole 32 is formed in a main body portion 31 of the bearing 30. The insertion hole 32 penetrates in an axial direction of the shaft 6 (hereinafter referred to simply as "axial direction"). The shaft 6 is inserted through the insertion hole 32. Two bearing surfaces 34 and 35 are formed on an inner peripheral surface 33 of the insertion hole 32. The bearing surfaces 34 and 35 are separated from each other in the axial direction.

[0018] A part of the lubricating oil that has been supplied to the bearing bore 21 passes through the oil hole 36 and flows inside the inner peripheral surface 33 of the main body portion 31. The oil hole 36 penetrates through the main body portion 31 from the inner peripheral surface 33 to the outer peripheral surface 37. The lubricating oil that has been distributed spreads to the right and left in Fig. 2 from the oil hole 36. The lubricating oil that has flowed in is supplied to a gap between the shaft 6 and each of the bearing surfaces 34 and 35. The shaft 6 is axially supported by an oil film pressure of the lubricating oil that has been supplied to the gap between the shaft 6 and each of the bearing surfaces 34 and 35.

[0019] Furthermore, the main body portion 31 is provided with a through hole 38. The through hole 38 penetrates from the inner peripheral surface 33 to the outer peripheral surface 37. The bearing wall portion 21 has a pin hole 21b. The pin hole 21b is formed at a location opposite the through hole 38. The pin hole 21b penetrates a wall portion forming the bearing hole 21a. A positioning pin 50 is inserted into the pin hole 21b from a lower side in Fig. 2. A distal end of the positioning pin 50 is inserted into the through hole 38 of the bearing 30. The positioning pin 50 controls rotation and axial movement of the bearing 30.

[0020] Furthermore, the shaft 6 is provided with an oil separator component 60. The oil separator component 60 is on the right side in Fig. 2 (compressor impeller 8 side) with respect to the main body portion 31. The oil separator component 60 is an annular component. The oil separator component 60 causes the lubricating oil that has flowed to the compressor impeller 8 side along the shaft 6 to be distributed to the radially outer side. This means that the oil separator component 60 prevents lubricating oil from leaking to the compressor impeller 8 side.

[0021] An opposing surface 61 of the oil separator component 60 faces the main body portion 31 in the axial direction. Furthermore, the shaft 6 has a flange 6a. The flange 6a is formed on the left side in Fig. 2 (side of the turbine blade wheel 7) with respect to the main body portion 31. The flange 6a is opposite to the main body portion 31 in the axial direction.

[0022] As previously described, the axial movement of the main body portion 31 is controlled by the positioning pin 50. The main body portion 31 is disposed between the oil separator member 60 and the flange 6a in the axial direction. Lubricating oil is supplied to a gap between the main body portion 31 and the oil separator member 60 and a gap between the main body portion 31 and the flange 6a. When the shaft 6 moves in the axial direction, the oil separator member 60 or the flange 6a is supported by an oil film pressure generated between the main body portion 31 and the oil separator member 60 or the flange 6a. This means that both end surfaces of the main body portion 31 in the bearing 30 in the axial direction are thrust bearing surfaces 41 and 42. The thrust bearing surfaces 41 and 42 receive an axial load.

[0023] Furthermore, damper portions 39 and 40 are formed on both sides of the outer peripheral surface of the main body portion 31 in the axial direction. The damper portions 39 and 40 prevent vibration of the shaft 6 due to the oil film pressure of the lubricating oil supplied to the gap formed with the inner peripheral surface of the bearing bore 21a.

[0024] Fig. 3A is a sectional view which is the same as Fig. 1. Fig. Figure 3B is a sectional view taken along line IIIB-IIIB of Fig. 3A is generated. As in Fig. 3A, a partition wall portion 23 is formed in the bearing housing 20. The partition wall portion 23 is formed on a radially outer side (lower side in Fig. 3A) of the bearing bore with respect to the bearing wall portion 21. The partition wall portion 23 forms an internal space S with the bearing wall portion 21. An oil discharge port 23a is formed in the partition wall portion 23. The oil discharge port 23a is connected to the internal space S.

[0025] A groove portion 24 is formed in the bearing wall portion 21. The groove portion 24 is formed on a radially outer side of an end portion on the left side in Fig. 3A (side of the turbine blade wheel 7) in the main body portion 31 of the bearing 30. The groove portion 24 is opened to the inner space S at a position corresponding to the side of the oil discharge port 23a (lower side in Fig. 3A) in the groove portion 24. A conical surface 24a is formed in the groove portion 24. The conical surface 24a is formed on an inner wall surface on the left side in Fig. 3A (side of the turbine blade wheel 7) in the groove portion 24. The conical surface 24a is inclined in the direction facing the left side in Fig. 3A (side of the turbine blade wheel 7) while extending toward the radially inner side. The tapered surface 24a is formed on a radially outer side of the thrust bearing surface 41.

[0026] A guide plate 70 is provided on a radially outer side of the oil separator component 60. The guide plate 70 is on the right side in Fig. 3A (side of the compressor impeller 8) with respect to the bearing wall portion 21. A gap in the axial direction is formed between the guide plate 70 and the bearing wall portion 21. The gap is connected to the internal space S. The guide plate 70 has a tapered surface 71. The tapered surface 71 is formed on an end surface on the left side in Fig. 3A (side of the turbine blade wheel 7, side of the bearing 30) on the guide plate 70. The conical surface 71 is inclined in the direction extending in Fig. 3A approaches the right side (compressor impeller 8 side) while extending toward the radially inner side. The tapered surface 71 is formed on a radially outer side relative to the thrust bearing surface 42.

[0027] As in Fig. 3B, the inner space S is on the radially outer side of the bearing wall section 21 and on the side of the oil discharge connection 23a (lower side in Fig. 3B) and extends in the rotational direction of the shaft 6. The inner space S has, for example, a fan shape on the radially outer side of the bearing wall portion 21. The inner space S is formed to include an arcuate wall surface 21c on the radially outer side of the shaft 6 and straight wall portions 21d on the front and rear sides in the rotational direction of the shaft 6. The wall surface 21c is an outer surface of the bearing wall portion 21 on the inner space S side. In addition, the inner space S does not extend on a side opposite to the oil discharge port 23a (upper side in Fig. 3B) with respect to the bearing wall portion 21. The lubricating oil which has been distributed from the thrust bearing surface 41 to the radially outer side is guided by the tapered surface 24a to the right side in Fig. 3A (side of the compressor impeller 8, side of the oil discharge port 23a in the central axis direction O). The lubricating oil passes through the fan-shaped interior S, which is in Fig. 3B, and is fed to the oil discharge port 23a.

[0028] Together with the rotation of the shaft 6, the lubricating oil is circulated in the same direction as the rotation of the shaft 6 (in Fig. 3B (the direction indicated by arrow A). The lubricating oil strikes the wall surface 21d of the bearing wall portion 21 on a front side in the rotation direction of the shaft 6 with respect to the internal space S. If an oil amount is large, oil clogging may occur near the wall surface 21d.

[0029] The flow of the lubricating oil was measured with respect to the cross section on the side of the turbine blade wheel 7 in Fig. 3B. However, a flow of the lubricating oil on the compressor impeller 8 side is similar to that on the turbine impeller 7 side. This means that the lubricating oil that has been spread to the radially outer side of the thrust bearing surface 42 is discharged from the tapered surface 71 to the left side. Fig. 3A (side of the turbine blade wheel 7, side of the oil discharge port 23a in the central axis direction O). The lubricating oil impacts the wall surface 21d of the bearing wall portion 21. If an oil amount is large, oil clogging may occur near the wall surface 21d.

[0030] Fig. 4 is a sectional view taken along the line IV-IV of Fig. 3B is generated. In Fig. 4, the oil discharge port 23a and the internal space S, which differ in a position in the direction of rotation of the shaft 6 and which do not appear in the cross section, are shown by dashed lines near the oil discharge port 23a. As shown in Fig. 4, the wall surface 21d of the bearing wall portion 21 serves as a guide portion 25. The guide portion 25 is, for example, an inclined surface. The guide portion 25 separates from the oil discharge port 23a to the upper side in Fig. 4, with one point of it in the right-and-left direction in Fig. 4 approaches the oil discharge port 23a. This means that the guide portion 25 separates from the oil discharge port 23a in a direction of a plane perpendicular to a center axis of the bearing 30, and a position thereof in the center axis direction O of the bearing 30 (i.e., approximately the axial direction) approaches the oil discharge port 23a.

[0031] In Fig. 4, the turbocharger C is arranged, for example, so that it is aligned with an upper side thereof being a vertical upper side, and a lower side thereof being a vertical lower side. In this case, the guide portion 25 is inclined so that it is aligned toward the vertically upper side, with a position thereof in the right-and-left direction in Fig. 4 approaches the oil discharge connection 23a.

[0032] The guide portion 25 includes a first guide portion 25a and a second guide portion 25b. The first guide portion 25a extends from the side of the oil discharge port 23a to the side of the turbine blade wheel 7 (left side in Fig. 4). In an example shown in Fig. 4, the first guide portion 25a is an inclined surface inclined so as to be oriented toward the vertical upper side, approaching the oil discharge port 23a from the turbine impeller 7 side. However, a part of the first guide portion 25a may be an inclined surface inclined so as to be oriented toward the vertical upper side, approaching the oil discharge port 23a from the turbine impeller 7 side. The second guide portion 25b extends toward the compressor impeller 8 side (right side in Fig. 4) with respect to the first guide section 25a. In an example shown in Fig. 4, the second guide portion 25b is an inclined surface inclined to face the vertical upper side, approaching the oil discharge port 23a from the compressor impeller 8 side. However, a part of the second guide portion 25b may be an inclined surface inclined to face the vertical upper side, approaching the oil discharge port 23a from the compressor impeller 8 side.

[0033] In the guide portion 25, an upper portion 25c is formed between the first guide portion 25a and the second guide portion 25b. A location between the upper portion 25c and the central axis direction O of the bearing 30 (indicated by the dash-dotted line in Fig. 4) may coincide with a position of the oil discharge port 23a in the central axis direction O of the bearing 30. In this case, the upper portion 25c is positioned within a range of the oil discharge port 23a in the central axis direction O of the bearing 30.

[0034] As described above, the lubricating oil guided from the tapered surface 24a and 71 to the oil discharge port 23a side in the central axis direction O of the bearing 30 is circulated with the rotation of the shaft 6. The lubricating oil is spread in the rotation direction of the shaft 6 and impinges on the guide portion 25 (wall surface 21d). The lubricating oil that has impinged on the guide portion 25 is guided from the guide portion 25 to the upper portion 25c side. The lubricating oil that has reached the upper portion 25c from the first guide portion 25a side and the lubricating oil that has reached the upper portion 25c from the second guide portion 25b side collide with each other. The collided lubricating oil flows down to the oil discharge port 23a. Thus, oil clogging near the wall surface 21d is prevented. The oil drainage performance is improved.

[0035] The case where the position of the upper portion 25c in the central axis direction O of the bearing 30 coincides with the position of the oil discharge port 23a in the central axis direction O of the bearing 30 has been described. In this case, the oil is likely to move to the oil discharge port 23a. However, the position of the upper portion 25c in the central axis direction O of the bearing 30 may not coincide with the position of the oil discharge port 23a in the central axis direction O of the bearing 30. The position of the upper portion 25c in the central axis direction O of the bearing 30 may be on the turbine impeller 7 side with respect to the oil discharge port 23a. The position of the upper portion 25c in the central axis direction O of the bearing 30 may be on the compressor impeller 8 side with respect to the oil discharge port 23a.

[0036] Furthermore, the case where the guide portion 25 includes the first guide portion 25a and the second guide portion 25b has been described. In this case, the oil discharge performance from both the turbine impeller 7 side and the compressor impeller 8 side is improved. However, the guide portion 25 may also include only one of the first guide portion 25a and the second guide portion 25b. In this case, too, the lubricating oil is guided to the oil discharge port 23a side from the first guide portion 25a or the second guide portion 25b. Therefore, oil clogging near the wall surface 21d is prevented. As a result, the oil discharge performance is improved.

[0037] Fig. 5 is an exemplary view for illustrating a modification example. In Fig. 5 shows a section at a location corresponding to the two-dotted line area of Fig. 4 in the modification example. As in Fig. 5, in the modified example, a guide portion 125 is formed to include a first guide portion 125a and a second guide portion 125b. The first guide portion 125a has portions having a different inclination from each other depending on a position thereon in the right-and-left direction in Fig. 5 (central axis direction O of bearing 30).

[0038] Namely, in the first guide section 125a, a first inclined section 125aa is formed on the left side in Fig. 5 (side of the turbine blade wheel 7). In the first guide section 125a, a second inclined section 125ab is formed on the right side in Fig. 5 (side of the compressor impeller 8). The first inclined portion 125aa has a greater inclination than that of the second inclined portion 125ab. The second inclined portion 125ab is aligned closer to the central axis direction O of the bearing 30 than the first inclined portion 125aa.

[0039] For example, the discussion will be carried out in the case where the lubricating oil is directed to the left side in Fig. 5 (turbine impeller 7 side) of the first guide portion 125a. When the first inclined portion 125aa is provided in a region corresponding to the position where the lubricating oil hits the first guide portion 25a, the lubricating oil that has hit the first guide portion 125a is more likely to be guided to the upper portion 125c side. In addition, when the second inclined portion 125ab is provided with respect to the first inclined portion 125aa in the first guide portion 125a on the oil discharge port 23a side, the enlargement of the internal space S on the oil discharge port 23a side can be prevented. For example, the discussion will be made of the case where, depending on the configurations on the engine side or the like, a cooling liquid (coolant) flows in a vicinity of the internal space S.Interference between the internal space S and a passage space for allowing the coolant to flow therethrough is likely to be prevented, and design freedom is improved. As described above, if the guide portion 125 includes a portion having different inclinations depending on a position thereon in the right-and-left direction in FIG. 1, the oil discharge performance is improved without unnecessarily enlarging the internal space S. Fig. 5 (central axis direction O of bearing 30).

[0040] The case has been described where in the first guide section 125a, the section (first inclined section 125aa) on the left side is Fig. 5 (side of the turbine blade wheel 7) has an inclination that is greater than that of the section (second inclined section 125ab) on the right side in Fig. 5 (side of the compressor impeller 8). However, in the first guide section 125a, the section (first inclined section 125aa) on the left side can be Fig. 5 (side of the turbine blade wheel 7) have an inclination which is smaller than that of the section (second inclined section 125ab) on the right side in Fig. 5 (side of the compressor impeller 8). A spatial relationship between the first inclined portion 125aa and the second inclined portion 125ab can be appropriately changed in accordance with a flow of the lubricating oil. Furthermore, either the first inclined portion 125aa or the second inclined portion 125ab may have a smaller inclination. Either the first inclined portion 125aa or the second inclined portion 125ab, which has a smaller inclination, may be parallel to the central axis. Furthermore, either the first inclined portion 125aa or the second inclined portion 125ab, which has a smaller inclination, may be inclined in a direction approaching the oil discharge port 23a (for example, toward the vertical lower side), extending to the right side in Fig. 5 (side of the compressor impeller 8).

[0041] The case has been described in which the first guide section 125a has sections having a different pitch from each other depending on a position thereon in the right-and-left direction in Fig. 5 (center axis direction O of the bearing 30). However, the second guide portion 125b may have portions having a different inclination from each other depending on a position thereon in the right-and-left direction in Fig. 5 (center axis direction O of the bearing 30). Both the first guide portion 125a and the second guide portion 125b may have portions having a different pitch from each other, depending on a position thereon in the right-and-left direction in Fig. 5 (central axis direction O of bearing 30).

[0042] The embodiment has been described above with reference to the accompanying drawings, but it should be understood that the present disclosure is not limited to the aforementioned embodiment. It is obvious that those skilled in the art can arrive at various modifications and alterations within the scope of the claims, and these examples are construed as naturally falling within the technical scope of the present disclosure. Industrial applicability

[0043] The present disclosure is applicable to a turbocharger that includes a bearing. List of reference symbols 7 Turbine blade wheel 8 Compressor impeller 21 bearing wall section 21a Bearing bore 23 Partition section 23a Oil drain connection 25, 125 guide section 25a, 125a First guide section 25b, 125b Second guide section 25c Upper Section 30 warehouses C Turbocharger O Central axis direction S interior

Claims

[1] Turbocharger (C) with: a warehouse (30); a bearing wall portion (21) having a bearing bore (21a) in which the bearing (30) is arranged; a partition wall portion (23) provided on a radially outer side of the bearing bore (21a) with respect to the bearing wall portion (21) and forming an inner space (S) with the bearing wall portion (21); an oil discharge port (23a) formed in the partition wall portion (23) and connected to the interior space (S); and a guide portion (25) provided on the bearing wall portion (21) facing the interior space (S) and which is an inclined surface inclined to move further away from the oil discharge port (23a) in the direction of a plane perpendicular to a central axis of the bearing (30) as it approaches the oil discharge port (23a) in a direction of the central axis, characterized by , that an end portion of the guide portion (25) is arranged opposite the side of the oil discharge port (23a) in the central axis direction (O) at a position of an end surface of the bearing (30). [2] The turbocharger (C) according to claim 1, wherein the guide portion (125) has portions having a different inclination from each other depending on a position in the direction of the central axis. [3] Turbocharger (C) according to claim 1 or 2, wherein the guide portion (25) includes: a first guide portion (25a) extending away from the oil discharge port (23a) toward the turbine blade wheel (7); and a second guide portion (25b) extending toward the compressor impeller (8) with respect to the first guide portion (25a). [4] A turbocharger (C) according to claim 3, further comprising an upper portion (25c) formed between the first guide portion (25a) and the second guide portion (25b), wherein a position of the upper portion (25c) in the direction of the central axis coincides with a position of the oil discharge port (23a) in the direction of the central axis.

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