WO2017046842A1 - ターボチャージャ - Google Patents
ターボチャージャ Download PDFInfo
- Publication number
- WO2017046842A1 WO2017046842A1 PCT/JP2015/076005 JP2015076005W WO2017046842A1 WO 2017046842 A1 WO2017046842 A1 WO 2017046842A1 JP 2015076005 W JP2015076005 W JP 2015076005W WO 2017046842 A1 WO2017046842 A1 WO 2017046842A1
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- WO
- WIPO (PCT)
- Prior art keywords
- compressor
- turbine
- floating bearing
- oil supply
- oil
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
- F02B39/14—Lubrication of pumps; Safety measures therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/12—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load
- F16C17/18—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with floating brasses or brushing, rotatable at a reduced speed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/02—Parts of sliding-contact bearings
- F16C33/04—Brasses; Bushes; Linings
- F16C33/06—Sliding surface mainly made of metal
- F16C33/10—Construction relative to lubrication
- F16C33/1025—Construction relative to lubrication with liquid, e.g. oil, as lubricant
- F16C33/1045—Details of supply of the liquid to the bearing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
- F16C2360/24—Turbochargers
Definitions
- the present disclosure relates to a turbocharger, and more particularly to a turbocharger provided with a floating bearing as a bearing for supporting a rotating shaft.
- a turbocharger includes a rotating shaft, a compressor provided at one end of the rotating shaft, and a turbine provided at the other end of the rotating shaft. Then, the turbocharger is configured to rotate the rotation shaft via the turbine by the exhaust energy of the exhaust gas and to compress the intake air by the compressor.
- the lubricating oil filled in these gaps is supplied through an oil supply passage formed in the center housing.
- the oil supply passage includes an oil supply passage that supplies lubricating oil to the floating bearing on the compressor side and an oil supply passage that supplies lubricating oil to the floating bearing on the turbine side.
- the lubricating oil supplied via these oil supply passages cools the rotating shaft via the floating bearing on the compressor side and the floating bearing on the turbine side. And the lubricating oil which cooled the rotating shaft is discharged
- the temperature of the lubricating oil supplied to the floating bearing on the compressor is the same as the temperature of the lubricating oil supplied to the floating bearing on the turbine In comparison, it is considered to be relatively low. Therefore, the viscosity of the lubricating oil supplied to the floating bearing on the compressor side becomes higher than the viscosity of the lubricating oil supplied to the floating bearing on the turbine side, and the pressure loss in the oil supply passage on the compressor side increases. The oil pressure of the lubricating oil supplied to the floating bearing on the side may be reduced. As a result, the floating bearing on the compressor side may be burned.
- At least one embodiment of the present invention is an invention made on the basis of the state of the prior art, and an object thereof is to reduce the risk of burning of the floating bearing on the compressor side. To provide.
- a turbocharger is With the rotation axis, A compressor provided at one end of the rotating shaft; A turbine provided on the other end side of the rotating shaft; A compressor-side floating bearing rotatably supporting the rotating shaft; A turbine-side floating bearing that rotatably supports the rotating shaft, and is arranged with a space in the axial direction of the rotating shaft with respect to the compressor-side floating bearing, and the rotating shaft is disposed closer to the compressor-side floating bearing A turbine-side floating bearing disposed on the turbine side in the axial direction of A turbine side oil supply passage for receiving oil supplied to the turbine side floating bearing, and a compressor side oil supply passage for oil supplied to the compressor side floating bearing, accommodating the compressor side floating bearing and the turbine side floating bearing And an internally formed bearing housing; The ratio of the oil supply pressure of the oil at the outlet of the compressor side oil supply passage to the oil supply pressure of the oil at the outlet of the turbine side oil supply passage is larger than 1.0 and smaller than 1.5.
- the ratio of the oil supply pressure of the oil at the outlet of the compressor side oil supply passage to the oil supply pressure of the oil at the outlet of the turbine side oil supply passage is larger than 1.0 and smaller than 1.5. It is configured. Therefore, even if the viscosity of the oil flowing through the compressor-side oil supply passage is higher than the viscosity of the oil flowing through the turbine-side oil supply passage, the oil supply amount of the oil flowing through the compressor-side oil supply passage can be increased. Therefore, the amount of oil flowing to the compressor-side floating bearing can be increased, and the possibility of the compressor-side floating bearing burning can be reduced.
- the compressor side oil supply passage includes at least a compressor side oil supply hole extending toward the compressor side floating bearing
- the turbine side oil supply passage includes at least a turbine side oil supply hole extending toward the turbine side floating bearing.
- the cross-sectional area of the compressor-side oil supply through hole is configured to be larger than the cross-sectional area of the turbine side oil supply hole.
- the cross-sectional area of the compressor-side oil supply through hole is configured to be larger than the cross-sectional area of the turbine side oil supply hole. For this reason, the oil supply pressure of the oil at the outlet of the compressor side oil supply passage can be increased, and the oil supply amount of the oil supplied to the compressor side floating bearing can be increased. Thus, the risk of the compressor-side floating bearing being burned can be reduced.
- the bearing housing has one end opened to the outer surface of the bearing housing and the other end extending to the rotation shaft And an oil introduction passage communicating with the compressor side oil supply passage and the turbine side oil supply passage.
- the oil introduction passage is disposed at a position close to the compressor-side floating bearing in the axial direction of the rotation shaft.
- the flow passage length of the compressor-side oil supply hole is configured to be shorter than the flow passage length of the turbine-side oil supply hole.
- the oil introduction passage is disposed at a position closer to the compressor-side floating bearing than the turbine-side floating bearing in the axial direction of the rotation shaft. Therefore, the distance between the oil introduction passage and the compressor-side floating bearing can be shortened as compared with the distance between the oil introduction passage and the turbine-side floating bearing. Therefore, the flow path length of the compressor side oil supply hole can be made shorter than the flow path length of the turbine side oil supply hole, and the pressure loss of the oil flowing through the compressor side oil supply hole can be reduced. Thus, the amount of oil supplied from the outlet of the compressor-side oil supply passage to the compressor-side floating bearing can be increased, and the possibility of the compressor-side floating bearing burning can be reduced.
- the compressor-side oil supply passage may include a compressor-side oil supply hole extending toward the compressor-side floating bearing And an compressor-side oil supply groove extending along the outer periphery of the compressor-side floating bearing and opening toward the outer periphery of the compressor-side floating bearing at an end of the outlet side of the compressor-side oil supply hole Ru.
- the end of the outlet side of the compressor-side oil supply hole extends along the outer periphery of the compressor-side floating bearing and opens toward the outer periphery of the compressor-side floating bearing A compressor side oiling groove is formed. For this reason, it is possible to increase the pressure receiving area of the oil supply pressure of the oil supplied to the compressor side floating bearing in the compressor side oil supply groove. Therefore, the amount of oil supplied to the compressor-side floating bearing can be increased, and seizure of the compressor-side floating bearing can be reduced.
- the turbine side oil supply passage includes a turbine side oil supply hole extending toward the turbine side floating bearing, and an outlet side of the turbine side oil supply hole And a turbine-side oil supply groove extending along the outer periphery of the turbine-side floating bearing and opening toward the outer periphery of the turbine-side floating bearing.
- the opening area of the compressor-side oil supply groove is configured to be larger than the opening area of the turbine-side oil supply groove.
- the turbine-side oil supply passage has the turbine-side floating at the turbine-side oil supply hole extending toward the turbine-side floating bearing and the outlet side end of the turbine side oil supply hole Since the turbine side oil supply groove extending along the outer periphery of the bearing and opening toward the outer periphery of the turbine side floating bearing is included, the turbine housing can be manufactured simply by adding the turbine side oil supply groove. The amount of oil supplied to the side floating bearing can be increased, and the rotating shaft rotating at high speed can be cooled more effectively.
- the compressor-side floating bearing is compared to the case where the opening area of the compressor-side oiling groove is the same as the opening area of the turbine-side oiling groove.
- the amount of oil supplied to the engine can be increased, and seizing of the compressor side floating bearing can be reduced.
- the turbocharger is disposed between the compressor-side floating bearing on the rotating shaft and the turbine-side floating bearing, in the axial direction
- the sleeve further includes a sleeve having one end in contact with the other axial end of the first floating bearing, and the other axial end in contact with one axial end of the second floating bearing. Then, at the axial center of the sleeve, a discharge port for discharging the oil, which is supplied to the compressor-side floating bearing and the turbine-side floating bearing and flows between the rotating shaft and the sleeve, is formed. Furthermore, the inner diameter of the open end on the compressor-side floating bearing side of the sleeve is configured to be larger than the inner diameter of the open end on the turbine-side floating bearing side.
- these bearings are in the direction in which they approach each other in the axial direction of the rotation shaft It can be positioned.
- the oil flowing out from the sleeve side of the compressor side floating bearing can be smoothed. It can flow to an outlet formed at the axial center of the sleeve. For this reason, it is possible to prevent an increase in pressure loss of oil flowing from the compressor side floating bearing to the sleeve side. Therefore, the flow of oil supplied to the compressor-side floating bearing and moved to the sleeve side can be smoothed. Therefore, the amount of oil supplied to the compressor-side floating bearing can be increased, and the possibility of the compressor-side floating bearing burning can be reduced.
- the inner diameter of the axially central portion of the sleeve is configured to be larger than the inner diameter of the open end portions on both axial sides of the sleeve .
- the volume of the space inside the axially central portion of the sleeve can be increased. Since oil flows out from the compressor-side floating bearing and turbine-side floating bearing into the space into the space, if the inner diameter of the axially central portion of the sleeve is the same as or smaller than the inner diameter of the open end of the sleeve on both axial sides. As a result, oil may be retained in the space.
- the volume of the space increases, and the oil flowing between the rotary shaft and the sleeve It is possible to prevent the possibility of staying in the space. Therefore, an increase in pressure loss of oil flowing from the compressor side floating bearing and the turbine side floating bearing to the sleeve side can be prevented, and the flow of oil supplied to the compressor side floating bearing and moved to the sleeve side can be smoothed. Can. Therefore, the amount of oil supplied to the compressor-side floating bearing can be increased, and the possibility of the compressor-side floating bearing burning can be reduced.
- the turbo shaft is mounted on the rotating shaft, and the turbine side floating bearing side end portion of the compressor side floating bearing is And a first C-shaped retaining ring in contact therewith.
- the second C-type snap ring mounted on the rotary shaft and in contact with the compressor-side floating bearing side end of the turbine-side floating bearing, and the first C-type snap ring have joint portions of the first C-type snap ring in the housing. It is mounted on the rotating shaft in a position facing the oil outlet.
- the second C-type snap ring is configured to be mounted on the rotation shaft with the joint portion of the second C-type snap ring facing in a direction other than the oil outlet of the housing.
- the joint portion of the first C-type snap ring is mounted on the rotating shaft in a posture facing the oil discharge outlet of the housing, the oil flowing out from the compressor-side floating bearing in the absence of the first C-type snap ring is drained A gap is provided in the middle of the path flowing to the outlet. For this reason, it is possible to prevent an increase in pressure loss of oil flowing from the compressor side floating bearing to the first C type snap ring side, and the oil flow supplied to the compressor side floating bearing and moving to the first C type snap ring side It can be smooth. Therefore, the amount of oil supplied to the compressor-side floating bearing can be increased, and the possibility of the compressor-side floating bearing burning can be reduced.
- the second C-type snap ring is mounted on the rotation shaft with the abutment of the second C-type snap ring facing in a direction other than the oil discharge outlet of the housing, so the second C-type snap ring does not exist.
- the joint portion of the second C-type snap ring is provided at a position where the oil flowing out from the turbine-side floating bearing is out of the path flowing to the oil discharge outlet. For this reason, since the pressure loss of the oil flowing from the turbine side floating bearing to the second C-type snap ring side increases, the flow rate of the oil flowing to the drain oil outlet can be reduced.
- the bearing housing includes a compressor-side bearing support that supports the compressor-side floating bearing, and a turbine-side bearing that supports the turbine-side floating bearing. And a supporting portion. And, inside the bearing housing, oil discharged from the first C-type snap ring side of the compressor-side floating bearing between the compressor-side bearing support and the turbine-side bearing support, and the second C of the turbine-side floating bearing A discharge space is formed to discharge the oil flowing out from the mold retaining ring side to the oil discharge outlet of the housing. Furthermore, at the end on the discharge outlet side of the discharge space side in the compressor side bearing support portion, a notch surface portion extending from the inner circumferential surface to the outer circumferential surface of the compressor side bearing support portion is formed Configured to
- the discharge space side is directed from the inner peripheral surface to the outer peripheral surface of the compressor side bearing support portion. Since the notch surface portion extending to the end is formed, the oil flowing out from the first C-shaped retaining ring side of the compressor-side floating bearing is a cut that extends to the discharge space side when moving from the discharge space to the discharge outlet side By flowing through the notched surface, the flow of oil can be made smoother. Therefore, there is no possibility that oil may stay in the discharge space, the amount of oil supplied to the compressor-side floating bearing can be increased, and the possibility of the compressor-side floating bearing burning can be further reduced.
- turbocharger In the turbocharger concerning one embodiment of the present invention, it is a sectional side elevation showing the section which met in the direction of an axis of the axis of rotation. It is a perspective view of the floating bearing concerning one embodiment of the present invention. It is an important section sectional view showing an oil supply passage which supplies oil to a floating bearing which supports a rotating shaft of a turbocharger concerning one embodiment of the present invention. It is an important section sectional view showing an oil supply passage which supplies oil to a floating bearing which supports a rotating shaft of a turbocharger concerning one embodiment of the present invention.
- FIG. 4A It is a figure showing the section of the floating bearing of the turbocharger shown in Drawing 4A, and the figure (a) is the sectional view in the direction view orthogonal to the axis of rotation of the compressor side floating bearing, and the figure (b) Is a cross-sectional view in a direction perpendicular to the rotation axis of the turbine-side floating bearing. It is an important section sectional view which arranged a sleeve between two floating bearings which support a rotating shaft of a turbocharger concerning one embodiment of the present invention. It is principal part sectional drawing which attached the C-type snap ring which positions two floating bearings which support the rotating shaft of the turbocharger concerning one Embodiment of this invention to the rotating shaft.
- FIG. 6C is a view showing a C-shaped retaining ring of the turbocharger shown in FIG. 6A
- FIG. 6A is a side view of a first C-type retaining ring for positioning the compressor-side floating bearing
- FIG. FIG. 6 is a side view of a second C-type snap ring for positioning a turbine-side floating bearing. It is principal part sectional drawing in which the notch surface part was formed in the bearing support part which supports the compressor side floating bearing of the turbocharger concerning one Embodiment of this invention.
- a representation representing a relative or absolute arrangement such as “in a direction”, “along a direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial” is strictly Not only does it represent such an arrangement, but also represents a state of relative displacement with an angle or distance that allows the same function to be obtained.
- expressions representing shapes such as quadrilateral shapes and cylindrical shapes not only represent shapes such as rectangular shapes and cylindrical shapes in a geometrically strict sense, but also uneven portions and chamfers within the range where the same effect can be obtained.
- the shape including a part etc. shall also be expressed.
- FIG. 1 is a side cross-sectional view showing a cross section along an axial direction of a rotation axis of a turbocharger according to an embodiment of the present invention.
- a turbocharger according to an embodiment of the present invention is, for example, a turbocharger mounted on an automobile engine or the like, although not particularly limited.
- the turbocharger 1 includes a turbine housing 10 for accommodating a turbine impeller 11 provided on one end side of the rotation shaft 2, and a compressor impeller provided on the other end side of the rotation shaft 2. 21 and a compressor-side floating bearing 31 and a turbine-side floating bearing 33 for rotatably supporting the rotation shaft 2, and a thrust plate 35 for supporting the thrust force (axial force) of the rotation shaft 2. It consists of three housings of the bearing housing 30 to accommodate.
- a spiral turbine scroll channel 12 is formed on the outer peripheral portion of the turbine housing 10.
- a turbine impeller 11 is disposed at a central portion of the turbine scroll passage 12.
- the turbine impeller 11 includes a frusto-conical turbine hub 11A in which the head of a conical body is cut off in a plane parallel to the bottom, and a plurality of turbine blades 11B provided radially projecting from the circumferential surface of the turbine hub 11A.
- the turbine hub 11A of the turbine impeller 11 is joined to one end of the rotating shaft 2 by welding, for example.
- the exhaust gas flowing through the turbine scroll passage 12 and acting on the turbine impeller 11 is discharged from the exhaust gas discharge passage 13 extending along the axial direction of the rotating shaft 2 to the outside of the turbine housing 10.
- a spiral compressor scroll passage 22 is formed on the outer peripheral portion of the compressor housing 20.
- the compressor impeller 21 is disposed at a central portion of the compressor scroll channel 22.
- the compressor impeller 21 comprises a frusto-conical compressor hub 21A in which the head of a cone is cut off in a plane parallel to the bottom surface, and a plurality of compressor blades 21B provided radially projecting from the circumferential surface of the compressor hub 21A. Become.
- a fitting insertion hole (not shown) into which the other end side of the rotary shaft 2 is inserted is formed.
- the compressor impeller 21 is fixed to the other end of the rotary shaft 2 by tightening a nut 23 from the tip of the compressor hub 21A after the one end side of the rotary shaft 2 is inserted into this insertion hole. Then, the air flows through the intake air introduction flow passage 24 extending along the axial direction of the rotation shaft 2, and the intake air compressed by the compressor impeller 21 extends through the diffuser flow passage 25 extending along the direction orthogonal to the rotation shaft 2. It is introduced into the compressor scroll channel 22 and supplied to an engine (not shown).
- the bearing housing 30 is disposed between the turbine housing 10 and the compressor housing 20, with one end connected to the compressor housing 20 and the other end connected to the turbine housing 10.
- the diffuser channel 25 described above is defined between the bearing housing 30 and the compressor housing 20.
- a projecting wall portion 30B that protrudes from the inner peripheral wall surface 30a of the bearing housing 30 is formed inside the bearing housing 30.
- the compressor-side bearing support 37 and the turbine-side bearing support 39 for accommodating the compressor-side floating bearing 31 and the turbine-side floating bearing 33 described above are formed on the tip end side of the projecting wall 30B.
- the compressor side bearing support portion 37 and the turbine side bearing support portion 39 are provided at intervals in the axial direction of the rotating shaft 2.
- the compressor side bearing support portion 37 is provided with a compressor side through hole 37 a penetrating in the axial direction of the rotary shaft 2.
- the central axis of the compressor side through hole 37 a is formed coaxially with the central axis of the rotating shaft 2.
- the compressor side floating bearing 31 is attached to the compressor side through hole 37a.
- the compressor-side floating bearing 31 is disposed such that the compressor-side end thereof is located on the same plane as the compressor-side end of the compressor-side through hole 37 a.
- the compressor through hole 37 a on the turbine side bearing support 39 side of the compressor side floating bearing 31 with respect to the turbine side end forms a discharge flow path through which the oil discharged from the compressor side floating bearing 31 flows.
- the turbine side bearing support portion 39 is formed similarly to the compressor side bearing support portion 37, and is provided with a turbine side through hole 39 a penetrating in the axial direction of the rotation shaft 2.
- the central axis of the turbine side through hole 39 a is formed coaxially with the central axis of the rotating shaft 2.
- the turbine side floating bearing 33 is attached to the turbine side through hole 39a.
- the turbine side floating bearing 33 is disposed such that the turbine side end thereof is located on the same plane as the turbine side end of the turbine side through hole 39a.
- the turbine side through hole 39 a of the compressor side bearing support portion 37 from the compressor side end of the turbine side floating bearing 33 serves as a discharge flow path through which the oil discharged from the turbine side floating bearing 33 flows.
- the compressor-side floating bearing 31 and the turbine-side floating bearing 33 have the same shape, so the compressor-side floating bearing 31 will be described, and the turbine-side floating bearing 33 will be given the same reference numerals for the same aspect and the description will be omitted. Do.
- FIG. 2 is a perspective view of a floating bearing according to an embodiment of the present invention.
- the compressor-side floating bearing 31 includes a peripheral wall portion 32 formed in a cylindrical shape with a predetermined thickness.
- the peripheral wall portion 32 is formed with a plurality of oil supply holes 32 a penetrating in the central axis direction of the peripheral wall portion 32.
- a plurality of fuel holes 32 a are formed at intervals in the circumferential direction at an axially intermediate portion of the peripheral wall portion 32. In the illustrated embodiment, six fueling holes 32a are formed, but the number of the fueling holes 32a is not limited to this.
- the compressor-side floating bearing 31 is inserted into the compressor-side through hole 37 a and the rotary shaft 2 is inserted into the inner peripheral surface 32 b of the peripheral wall portion 32.
- a gap (not shown) filled with oil is formed between the outer peripheral surface of the peripheral wall portion 32 and the inner peripheral surface 32b of the peripheral wall portion 32 and between the outer peripheral surface 32c of the peripheral wall portion 32 and the inner surface of the compressor side through hole 37a. Therefore, the compressor-side floating bearing 31 floats from the compressor-side bearing support 37 and the rotary shaft 2 through the oil.
- the turbine side floating bearing 33 is inserted into the turbine side through hole 39a and the rotary shaft 2 is inserted into the inner circumferential surface 32b of the peripheral wall portion 32 like the compressor side floating bearing 31.
- a gap (not shown) filled with oil is formed between the outer peripheral surface of the outer peripheral surface 2 and the inner peripheral surface 32b of the peripheral wall portion 32 and between the outer peripheral surface 32c of the peripheral wall portion 32 and the inner surface of the turbine side through hole 39a. Therefore, the turbine-side floating bearing 33 floats from the turbine-side bearing support 39 and the rotating shaft 2 through the oil.
- FIG. 3 is a cross-sectional view of an oil supply passage for supplying oil to a floating bearing that supports a rotating shaft of a turbocharger according to an embodiment of the present invention.
- FIG. 4A is a sectional view of an essential part showing an oil supply passage for supplying oil to a floating bearing that supports a rotating shaft of a turbocharger according to an embodiment of the present invention.
- FIG. 5 is a cross-sectional view of an essential part in which a sleeve is disposed between two floating bearings that support a rotating shaft of a turbocharger according to an embodiment of the present invention.
- FIG. 4A is a sectional view of an essential part showing an oil supply passage for supplying oil to a floating bearing that supports a rotating shaft of a turbocharger according to an embodiment of the present invention.
- FIG. 5 is a cross-sectional view of an essential part in which a sleeve is disposed between two floating bearings that support a rotating shaft of a turbocharger according to an embodiment of
- FIG. 6A is a sectional view of an essential part in which a C-shaped snap ring for positioning two floating bearings for supporting a rotating shaft of a turbocharger according to one embodiment of the present invention is mounted on the rotating shaft.
- FIG. 7 is a cross-sectional view of an essential part in which a notched surface part is formed in a bearing support part that supports a compressor-side floating bearing of a turbocharger according to an embodiment of the present invention.
- the turbocharger 1 As shown in FIG. 3, FIG. 4A, FIG. 4B, FIG. 5, FIG. 6A, and FIG. 7, the turbocharger 1 according to at least one embodiment of the present invention
- An oil introduction passage 41 for introducing oil (lubricating oil) supplied to the turbine-side floating bearing 33 and the thrust plate 35 is formed.
- one end of the oil introduction passage 41 opens at the upper end of the bearing housing 30, and the other end extends in the bearing housing 30 in the direction of the rotational axis, and the tip is floating on the turbine side It extends to a position closer to the compressor side floating bearing 31 side than the bearing 33. Therefore, the oil introduction passage 41 is disposed at a position close to the compressor-side floating bearing 31 in the axial direction of the rotary shaft 2.
- a compressor-side oil supply hole 42 extending toward the compressor-side floating bearing 31 is formed at the tip of the oil introduction passage 41 in the projecting wall portion 30B.
- the compressor side oil supply hole 42 is in communication with the oil introduction passage 41, and is in communication with the compressor side through hole 37 a so as to face the outer peripheral surface of the compressor side floating bearing 31. Therefore, the compressor side oil supply hole 42 becomes a compressor side oil supply passage 43 capable of supplying oil to the compressor side floating bearing 31 side.
- the cross-sectional shape of the compressor-side oil supply hole 42 is formed in a circular shape that facilitates processing.
- a turbine-side oil supply hole 45 extending toward the turbine-side floating bearing 33 is formed at the tip of the oil introduction passage 41 in the projecting wall portion 30B on the turbine-side bearing support 39 side.
- the turbine side oil supply hole 45 is in communication with the oil introduction passage 41, and is in communication with the turbine side through hole 39 a so as to face the outer peripheral surface 32 c of the turbine side floating bearing 33. Therefore, the turbine side oil supply hole 45 becomes a turbine side oil supply passage 46 capable of supplying oil to the turbine side floating bearing 33 side.
- the cross-sectional shape of the turbine side oil supply hole 45 is formed in the circular shape which is easy to process.
- the ratio of the oil supply pressure of the oil at the outlet 43 a of the compressor side oil supply passage 43 to the oil supply pressure of the oil at the outlet 46 a of the turbine side oil supply passage 46 is larger than 1.0 and smaller than 1.5. Is configured as.
- the oil supply pressure Pc of the oil at the outlet 43 a of the compressor side oil supply passage 43 is greater than 1.0 and less than 1.1 with respect to the oil supply pressure Pt of the oil at the outlet 46 a of the turbine side oil supply passage 46. It is good to be configured.
- the oil amount of oil flowing through the compressor side oiling passage 43 can be increased. Therefore, the amount of oil flowing to the compressor-side floating bearing 31 can be increased, and the possibility of the compressor-side floating bearing 31 burning can be reduced.
- the compressor-side oil supply passage 43 at least includes a compressor-side oil supply hole 42 extending toward the compressor-side floating bearing 31 as shown in FIG. 3, and the turbine-side oil supply passage 46 is on the turbine side
- the compressor-side oil supply hole 42 includes at least a turbine-side oil supply hole 45 extending toward the floating bearing 33 so that the cross-sectional area Sc of the compressor-side oil supply hole 42 is larger than the cross-sectional area St of the turbine-side oil supply hole 45 It is formed.
- the cross-sectional areas of the compressor side oil supply hole 42 and the turbine side oil supply hole 45 are made the same, the viscosity of the oil flowing through the compressor side oil supply hole 42 is lowered due to the influence of the heat transfer of the exhaust gas. Becomes high and pressure loss becomes large. Therefore, the oil supply to the compressor-side floating bearing 31 is reduced, and the compressor-side floating bearing 31 may be burned. Therefore, the cross-sectional area Sc of the compressor-side oil supply hole 42 is formed larger than the cross-sectional area St of the turbine-side oil supply hole 45.
- the flow path length of the compressor-side oil supply hole 42 is shorter than the flow path length of the turbine-side oil supply hole 45, as shown in FIGS. 3, 4A, 5, 6A, and 7. Is configured.
- the flow path length of the compressor side oil supply hole 42 is made shorter than the flow path length of the turbine side oil supply hole 45, thereby reducing the pressure loss of the oil flowing through the compressor side oil supply hole 42. be able to.
- the amount of oil supplied from the outlet 43a of the compressor-side oil supply passage 43 to the compressor-side floating bearing 31 can be increased, and the possibility of the compressor-side floating bearing 31 burning can be reduced.
- the cross-sectional area of the compressor-side fuel hole 42 and the cross-sectional area of the turbine-side fuel hole 45 are the same.
- the cross-sectional area 42 is smaller than the cross-sectional area of the turbine side oil supply hole 45, and the flow path length of the compressor side oil supply hole 42 is shorter than the flow path length of the turbine side oil supply hole 45, the outlet of the turbine side oil supply passage 46
- the ratio of the oil supply pressure of the oil at the outlet 43a of the compressor side oil supply passage 43 to the oil supply pressure of the oil at 46a is larger than 1.0 and smaller than 1.5. included.
- FIG. 4B is a view showing a cross section of the compressor side floating bearing 31 and the turbine side floating bearing 33 of the turbocharger 1 shown in FIG. 4A.
- FIG. 4A shows the rotation shaft 2 of the compressor side floating bearing 31.
- 6B is a cross-sectional view in a direction orthogonal to the rotation axis 2 of the turbine-side floating bearing 33. As shown in FIG.
- the compressor-side oil supply passage 43 includes a compressor-side oil supply hole 42 extending toward the compressor-side floating bearing 31.
- the compressor-side oil supply groove 44 extends along the outer periphery of the compressor-side floating bearing 31 and opens toward the outer periphery of the compressor-side floating bearing 31 at the end of the outlet side of the compressor-side oil supply hole 42 It is.
- the turbine side oil supply passage 46 extends along the outer periphery of the turbine side floating bearing 33 at the turbine side oil supply hole 45 extending toward the turbine side floating bearing 33 and the end of the turbine side oil supply hole 45 on the outlet side. And extending along the outer periphery of the turbine-side floating bearing 33.
- the opening area of the compressor-side oiling groove 44 is larger than the opening area of the turbine-side oiling groove 47.
- the opening area of the compressor-side oil supply groove 44 is a value calculated by multiplying the length Lc in the rotational axis direction of the compressor-side oil supply groove 44 by the circumferential length L ⁇ c along the outer periphery of the compressor-side floating bearing 31.
- the opening area of the turbine side oil supply groove 47 is a value calculated by multiplying the rotational axis direction length Lt of the turbine side oil supply groove 47 by the circumferential length L ⁇ t along the outer periphery of the turbine side floating bearing 33.
- the axial length Lc of the compressor side oil supply groove 44 is larger than the rotational axis direction length Lt of the turbine side oil supply groove 47, and the circumferential length L ⁇ c along the outer periphery of the compressor side floating bearing 31. Is larger than the circumferential length L ⁇ t along the outer periphery of the turbine-side floating bearing 33.
- the compressor-side oil supply passage 43 is formed by forming the compressor-side oil supply groove 44 opening toward the outer periphery of the compressor-side floating bearing 31 at the outlet end of the compressor-side oil supply hole 42.
- the pressure receiving area of the oil supply pressure of the oil supplied to the compressor-side floating bearing 31 at the outlet 43a can be increased. Therefore, the amount of oil supplied to the compressor-side floating bearing 31 can be increased, and seizure of the compressor-side floating bearing 31 can be reduced.
- the opening area of the compressor-side oiling groove 44 is larger than the opening area of the turbine-side oiling groove 47, the opening area of the compressor-side oiling groove 44 is the same as the opening area of the turbine-side oiling groove 47. The amount of oil supplied to the compressor-side floating bearing 31 can be increased, and seizure of the compressor-side floating bearing 31 can be reduced.
- the compressor side oil supply groove 44 and the turbine side oil supply groove 47 are provided at the outlet side end portions of the compressor side oil supply hole 42 and the turbine side oil supply hole 45, respectively.
- the compressor side oil supply groove 44 may be provided only at the outlet side end portion 42.
- the cross-sectional area of the compressor-side fuel hole 42 and the cross-sectional area of the turbine-side fuel hole 45 are the same.
- the cross-sectional area of the compressor-side fuel hole 42 is the turbine-side fuel hole
- the compressor side oil supply passage What is comprised so that the ratio of the oil supply pressure of the oil at the outlet 43a of 43 is smaller than 1.0 and smaller than 1.5 is also included in the invention according to claim 5.
- FIG. 5 is a cross-sectional view of an essential part in which the sleeve 50 is disposed between the two compressor side floating bearings 31 and the turbine side floating bearing 33 supporting the rotating shaft 2 of the turbocharger 1 according to an embodiment of the present invention.
- one end in the axial direction between the compressor-side floating bearing 31 and the turbine-side floating bearing 33 in the rotating shaft 2 is the axial direction of the compressor-side floating bearing 31.
- a sleeve 50 is further provided in contact with the other end, and the other axial end is in contact with one axial end of the turbine-side floating bearing 33.
- the sleeve 50 is formed in a cylindrical shape, and a through hole 50 a through which the rotation shaft 2 can be inserted is formed inside thereof.
- a discharge port 51 is formed at the axial central portion of the sleeve 50.
- the discharge port 51 is supplied to the compressor-side floating bearing 31 and the turbine-side floating bearing 33 and discharges the oil flowing between the rotary shaft 2 and the sleeve 50.
- the inner diameter ⁇ c of the open end of the sleeve 50 on the compressor side floating bearing 31 side is configured to be larger than the inner diameter ⁇ t of the open end on the turbine side floating bearing 33 side.
- the inner diameter ⁇ s of the axially central portion of the sleeve 50 is configured to be larger than the inner diameters ⁇ c and ⁇ t of the open end portions on both axial sides of the sleeve 50.
- these bearings are in the direction in which they approach each other in the axial direction of the rotary shaft 2. It can be positioned.
- the inner diameter ⁇ c of the open end of the sleeve 50 on the compressor side floating bearing 31 side is larger than the inner diameter ⁇ t of the open end on the turbine side floating bearing 33 side, from the sleeve 50 side of the compressor side floating bearing 31
- the oil to be discharged can be smoothly flowed to the discharge port 51 formed at the axial center of the sleeve 50. For this reason, it is possible to prevent an increase in pressure loss of oil flowing from the compressor side floating bearing 31 to the sleeve 50 side, and smooth the flow of oil supplied to the compressor side floating bearing 31 and moving to the sleeve 50 side. Can.
- the amount of oil supplied to the compressor-side floating bearing 31 can be increased, and the possibility of the compressor-side floating bearing 31 burning can be reduced.
- the inner diameter ⁇ s of the axially central portion of the sleeve 50 is larger than the inner diameters ⁇ c and ⁇ t of the open ends on both axial sides of the sleeve 50, the volume of the space 52 inside the axially central portion of the sleeve 50 is increased. be able to.
- oil flows out from the compressor-side floating bearing 31 and the turbine-side floating bearing 33 to the space 52, so that the inner diameter ⁇ s of the axial center of the sleeve 50 is the open end of the sleeve 50 on both sides in the axial direction. If the diameter is the same as or smaller than the inner diameters ⁇ c and ⁇ t, oil may be retained in the space 52.
- FIG. 6B is a view showing the first C-shaped retaining ring 61 and the second C-type retaining ring 62 of the turbocharger shown in FIG. 6A
- FIG. 6A (a) is a first C-type for positioning the compressor-side floating bearing 31
- FIG. 6A (b) is a side view of the second C-shaped snap ring 62 for positioning the turbine-side floating bearing 33.
- FIG. FIG. 7 is a cross-sectional view of an essential part of the compressor-side bearing support 37 for supporting the compressor-side floating bearing 31 of the turbocharger 1 according to an embodiment of the present invention, in which a notch surface 37b is formed.
- the rotation shaft 2 is provided on the turbine side floating bearing 33 end of the compressor side floating bearing 31.
- a first C-shaped snap ring 61 in contact and a second C-type snap ring 62 in contact with the compressor-side floating bearing 31 end of the turbine-side floating bearing 33 are further mounted.
- the first C-shaped retaining ring 61 is mounted on the rotary shaft 2 with the joint 61a of the first C-shaped retaining ring 61 facing the oil outlet 30c (see FIG. 1) of the bearing housing 30 (FIG.
- the second C-type snap ring 62 is mounted on the rotary shaft with the joint 62a of the second C-type snap ring 62 facing in a direction other than the oil outlet 30c of the bearing housing 30 (see FIG. 6B (b)). In the illustrated embodiment, it is mounted on the rotating shaft in an upward facing position.
- the compressor-side floating bearing 31 and the turbine-side floating bearing 33 are axially aligned with the rotary shaft 2 by the first C-type snap ring 61 and the second C-type snap ring 62 mounted on the rotary shaft 2. Positioning in the direction of approaching each other.
- the joint portion 61a of the first C-shaped snap ring 61 is mounted on the rotary shaft 2 in a posture facing the oil outlet 30c of the bearing housing 30, the compressor-side floating bearing in the absence of the first C-shaped snap ring 61 A joint 61a is provided in the middle of the path through which the oil flowing out from 31 flows to the oil outlet 30c. Therefore, it is possible to prevent an increase in pressure loss of oil flowing from the compressor side floating bearing 31 to the first C-shaped retaining ring 61 side, and supplied to the compressor side floating bearing 31 to move to the first C-type retaining ring 61 side The flow of oil can be smoothed. Thus, the amount of oil supplied to the compressor-side floating bearing 31 can be increased, and the possibility of the compressor-side floating bearing 31 burning can be reduced.
- the second C-type snap ring 62 is mounted on the rotary shaft 2 in a posture in which the joint 62a of the second C-type snap ring 62 faces in a direction other than the oil outlet 30c of the bearing housing 30,
- the joint portion 62a of the second C-type snap ring 62 is provided at a position where the oil flowing out from the turbine-side floating bearing 33 in the case where the snap ring 62 does not exist is deviated from the path to the oil outlet 30c.
- the pressure loss of the oil flowing from the turbine side floating bearing 33 toward the second C-type snap ring 62 increases, so the flow rate of the oil flowing to the oil outlet 30c can be reduced.
- FIG. 7 it flows out from the side of the first C-type snap ring 61 of the compressor-side floating bearing 31 between the compressor-side bearing support 37 and the turbine-side bearing support 39.
- a discharge space 48 is formed for discharging the oil and the oil flowing out from the side of the second C-type snap ring 62 of the floating bearing 33 on the turbine side to a drain oil outlet 30c (see FIG. 1) of the bearing housing 30.
- the compressor-side bearing support portion 37 extends from the inner peripheral surface 37c of the compressor-side bearing support portion 37 toward the outer-peripheral surface 37d at the end portion on the exhaust oil outlet 30c side of the discharge space 48 side.
- the notch surface 37b is formed.
- the notch surface portion 37b is formed at the end portion on the discharge outlet side of the discharge space 48 side of the compressor side bearing support portion 37, the first C-shaped retaining ring of the compressor side floating bearing 31
- the oil flowing out from the side 61 moves from the discharge space 48 to the drained oil outlet 30c side, it flows through the notched surface portion 37b extending to the discharge space 48 side, it is possible to make the flow of oil smoother. Therefore, there is no possibility that oil may stay in the discharge space 48, and the possibility of the compressor-side floating bearing 31 burning can be further reduced.
- turbocharger 1 was a supercharger
- turbocharger of the present invention is not limited to this.
- the turbocharger according to the present invention may be, for example, an electric compressor whose rotation shaft is rotated by a motor or a mechanical supercharger whose rotation shaft is rotated by power transmitted from a crankshaft or the like.
Abstract
Description
回転軸と、
前記回転軸の一端側に設けられるコンプレッサと、
前記回転軸の他端側に設けられるタービンと、
前記回転軸を回転自在に支持するコンプレッサ側フローティングベアリングと、
前記回転軸を回転自在に支持するタービン側フローティングベアリングであって、前記コンプレッサ側フローティングベアリングに対して前記回転軸の軸方向に間隔を有して配置され、前記コンプレッサ側フローティングベアリングよりも前記回転軸の軸方向において前記タービン側に配置されるタービン側フローティングベアリングと、
前記コンプレッサ側フローティングベアリング及び前記タービン側フローティングベアリングを収容するとともに、前記タービン側フローティングベアリングに供給するオイルが流れるタービン側給油通路と、前記コンプレッサ側フローティングベアリングに供給するオイルが流れるコンプレッサ側給油通路とが内部に形成されるベアリングハウジングと、を備え、
前記タービン側給油通路の出口におけるオイルの給油圧に対する前記コンプレッサ側給油通路の出口におけるオイルの給油圧の比が1.0より大きく1.5より小さくなるように構成されている。
コンプレッサ側給油通路は、コンプレッサ側フローティングベアリングに向かって延在するコンプレッサ側給油孔を少なくとも含み、タービン側給油通路は、タービン側フローティングベアリングに向かって延在するタービン側給油孔を少なくとも含んでいる。そして、コンプレッサ側給油通孔の断面積が、タービン側給油孔の断面積よりも大きくなるように構成されている。
3 回転軸
10 タービンハウジング
11 タービンインペラ
11A タービンハブ
11B タービン翼
12 タービンスクロール流路
13 排出流路
20 コンプレッサハウジング
21 コンプレッサインペラ
21A コンプレッサハブ
21B コンプレッサ翼
22 コンプレッサスクロール流路
23 ナット
24 吸気導入流路
25 ディフューザ流路
30 軸受ハウジング
30a 内周壁面
30B 突出壁部
30c 排油出口
31 コンプレッサ側フローティングベアリング
32 周壁部
32a 給油孔
32b 内周面
32c 外周面
33 タービン側フローティングベアリング
35 スラストプレート
37 コンプレッサベアリング支持部
37a コンプレッサ側貫通孔
37b 切欠き面部
37c 内周面
37d 外周面
39 タービン側ベアリング支持部
39a タービン側貫通孔
41 オイル導入路
42 コンプレッサ側給油孔
43 コンプレッサ側給油通路
43a コンプレッサ側給油通路の出口
44 コンプレッサ側給油溝
45 タービン側給油孔
46 タービン側給油通路
46a タービン側給油通路の出口
47 タービン側給油溝
48 排出空間
50 スリーブ
51 排出口
52 空間部
61 第1C型止め輪
61A,62A 合口部
62 第2C型止め輪
Claims (9)
- 回転軸と、
前記回転軸の一端側に設けられるコンプレッサと、
前記回転軸の他端側に設けられるタービンと、
前記回転軸を回転自在に支持するコンプレッサ側フローティングベアリングと、
前記回転軸を回転自在に支持するタービン側フローティングベアリングであって、前記コンプレッサ側フローティングベアリングに対して前記回転軸の軸方向に間隔を有して配置され、前記コンプレッサ側フローティングベアリングよりも前記回転軸の軸方向において前記タービン側に配置されるタービン側フローティングベアリングと、
前記コンプレッサ側フローティングベアリング及び前記タービン側フローティングベアリングを収容するとともに、前記タービン側フローティングベアリングに供給するオイルが流れるタービン側給油通路と、前記コンプレッサ側フローティングベアリングに供給するオイルが流れるコンプレッサ側給油通路とが内部に形成されるベアリングハウジングと、を備え、
前記タービン側給油通路の出口におけるオイルの給油圧に対する前記コンプレッサ側給油通路の出口におけるオイルの給油圧の比が1.0より大きく1.5より小さくなるように構成されている
ことを特徴とするターボチャージャ。 - 前記コンプレッサ側給油通路は、前記コンプレッサ側フローティングベアリングに向かって延在するコンプレッサ側給油孔を少なくとも含み、
前記タービン側給油通路は、前記タービン側フローティングベアリングに向かって延在するタービン側給油孔を少なくとも含み、
前記コンプレッサ側給油通孔の断面積が、前記タービン側給油孔の断面積よりも大きくなるように構成されている
ことを特徴とする請求項1に記載のターボチャージャ。 - 前記ベアリングハウジングは、一端部が前記ベアリングハウジングの外面に開口し他端側が前記回転軸側へ延在して前記コンプレッサ側給油通路及び前記タービン側給油通路に連通するオイル導入路を含み、
前記オイル導入路は、前記回転軸の軸方向において、前記タービン側フローティングベアリングよりも前記コンプレッサ側フローティングベアリング側に接近した位置に配設され、
前記コンプレッサ側給油孔の流路長は、前記タービン側給油孔の流路長よりも短い
ことを特徴とする請求項1又は2に記載のターボチャージャ。 - 前記コンプレッサ側給油通路は、前記コンプレッサ側フローティングベアリングに向かって延在するコンプレッサ側給油孔と、前記コンプレッサ側給油孔の出口側の端部において、前記コンプレッサ側フローティングベアリングの外周に沿って延在するとともに、前記コンプレッサ側フローティングベアリングの外周に向かって開口するコンプレッサ側給油溝と、を含む
ことを特徴とする請求項1から3のいずれかに記載のターボチャージャ。 - 前記タービン側給油通路は、前記タービン側フローティングベアリングに向かって延在するタービン側給油孔と、前記タービン側給油孔の出口側の端部において、前記タービン側フローティングベアリングの外周に沿って延在するとともに、前記タービン側フローティングベアリングの外周に向かって開口するタービン側給油溝と、を含み、
前記コンプレッサ側給油溝の開口面積は、前記タービン側給油溝の開口面積よりも大きい
ことを特徴とする請求項4に記載のターボチャージャ。 - 前記回転軸における前記コンプレッサ側フローティングベアリングと、前記タービン側フローティングベアリングとの間に配置され、軸方向の一端部が前記第コンプレッサ側フローティングベアリングの軸方向の他端部に接触し、軸方向の他端部が前記第タービン側フローティングベアリングの軸方向の一端部に接触するスリーブをさらに備え、
前記スリーブの軸方向中央部には、前記コンプレッサ側フローティングベアリング及び前記タービン側フローティングベアリングに供給され、前記回転軸と前記スリーブとの間に流れ込んだオイルを排出する排出口が形成され、
前記スリーブの前記コンプレッサ側フローティングベアリング側の開口端部の内径は、前記タービン側フローティングベアリング側の開口端部の内径よりも大きい
ことを特徴とする請求項1から5のいずれかに記載のターボチャージャ。 - 前記スリーブの前記軸方向中央部の内径は、前記スリーブの軸方向両側の開口端部の内径よりも大きい
ことを特徴とする請求項6に記載のターボチャージャ。 - 前記回転軸に装着されて、前記コンプレッサ側フローティングベアリングの前記タービン側フローティングベアリング側端部に接触する第1C型止め輪と、をさらに備え、
前記回転軸に装着されて、前記タービン側フローティングベアリングの前記コンプレッサ側フローティングベアリング側端部に接触する第2C型止め輪と、
前記第1C型止め輪は、前記第1C型止め輪の合口部が、前記ハウジングの排油出口を向いた姿勢で前記回転軸に装着され、
前記第2C型止め輪は、前記第2C型止め輪の合口部が、前記ハウジングの排油出口以外の方向を向いた姿勢で前記回転軸に装着される
ことを特徴とする請求項1から5のいずれかに記載のターボチャージャ。 - 前記ベアリングハウジングは、前記コンプレッサ側フローティングベアリングを支持するコンプレッサ側ベアリング支持部と、前記タービン側フローティングベアリングを支持するタービン側ベアリング支持部と、を含み、
前記ベアリングハウジングの内部には、前記コンプレッサ側ベアリング支持部と前記タービン側ベアリング支持部との間に、前記コンプレッサ側フローティングベアリングの第1C型止め輪側から流出されるオイル、及び前記タービン側フローティングベアリングの第2C型止め輪側から流出されるオイルを、前記ハウジングの排油出口へ排出するための排出空間が形成され、
前記コンプレッサ側ベアリング支持部における前記排出空間側の排出出口側の端部には、前記コンプレッサ側ベアリング支持部の内周面から外周面に向かって前記排出空間側へ延在する切欠き面部が形成されている
ことを特徴とする請求項8に記載のターボチャージャ。
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CN201580074846.2A CN107208543B (zh) | 2015-09-14 | 2015-09-14 | 涡轮增压器 |
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PCT/JP2015/076005 WO2017046842A1 (ja) | 2015-09-14 | 2015-09-14 | ターボチャージャ |
EP15904031.0A EP3249193B1 (en) | 2015-09-14 | 2015-09-14 | Turbocharger |
CN201910292755.6A CN109882284B (zh) | 2015-09-14 | 2015-09-14 | 涡轮增压器 |
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Also Published As
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CN107208543A (zh) | 2017-09-26 |
EP3249193A4 (en) | 2018-08-01 |
EP3249193A1 (en) | 2017-11-29 |
CN109882284B (zh) | 2021-05-25 |
EP3249193B1 (en) | 2024-05-01 |
JPWO2017046842A1 (ja) | 2017-10-19 |
US20180003105A1 (en) | 2018-01-04 |
CN107208543B (zh) | 2020-03-31 |
US10526960B2 (en) | 2020-01-07 |
JP6368864B2 (ja) | 2018-08-01 |
CN109882284A (zh) | 2019-06-14 |
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