WO2021084871A1 - 冷却構造体および過給機 - Google Patents

冷却構造体および過給機 Download PDF

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Publication number
WO2021084871A1
WO2021084871A1 PCT/JP2020/032067 JP2020032067W WO2021084871A1 WO 2021084871 A1 WO2021084871 A1 WO 2021084871A1 JP 2020032067 W JP2020032067 W JP 2020032067W WO 2021084871 A1 WO2021084871 A1 WO 2021084871A1
Authority
WO
WIPO (PCT)
Prior art keywords
diameter side
flow path
housing
outer diameter
lid member
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2020/032067
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
健一 瀬川
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
IHI Corp
Original Assignee
IHI Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by IHI Corp filed Critical IHI Corp
Priority to DE112020005348.2T priority Critical patent/DE112020005348T5/de
Priority to CN202080074124.8A priority patent/CN114585803B/zh
Priority to JP2021554108A priority patent/JP7315019B2/ja
Publication of WO2021084871A1 publication Critical patent/WO2021084871A1/ja
Priority to US17/656,969 priority patent/US11732606B2/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/046—Heating, heat insulation or cooling means
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/98—Lubrication
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the turbocharger includes a turbine housing, a bearing housing, and a compressor housing.
  • the turbine housing houses the turbine impeller.
  • the compressor housing houses the compressor impeller.
  • the turbine impeller and compressor impeller are connected by a shaft.
  • the bearing housing houses the shaft and the bearing. The bearing pivotally supports the shaft.
  • a cooling flow path and a lubricating oil passage are formed in the bearing housing. Coolant flows through the cooling flow path. The coolant cools the bearing housing. Lubricating oil flows through the lubricating oil passage. Lubricating oil is supplied to the bearing through the lubricating oil passage. Lubricating oil lubricates the bearing.
  • Patent Document 1 discloses a split type bearing housing.
  • the split bearing housing is the space between the bearing and the turbine impeller and is split by a split plane orthogonal to the axial direction of the shaft.
  • the split bearing housing includes a first bearing housing and a second bearing housing.
  • the first bearing housing is arranged on the compressor impeller side.
  • the second bearing housing is arranged on the turbine impeller side.
  • a first cooling flow path is formed in the first bearing housing.
  • a second cooling flow path is formed in the second bearing housing. When the first bearing housing and the second bearing housing are fastened, one cooling flow path is formed by the first cooling flow path and the second cooling flow path.
  • a shaft accommodating space for accommodating the shaft is formed in the space between the bearing and the turbine impeller.
  • a first shaft accommodating space is formed in the first bearing housing.
  • a second shaft accommodating space is formed in the second bearing housing. When the first bearing housing and the second bearing housing are fastened, one shaft accommodating space is formed by the first shaft accommodating space and the second shaft accommodating space.
  • An object of the present disclosure is to provide a cooling structure and a supercharger capable of reducing the mixing of lubricating oil and coolant.
  • the cooling structure includes a housing having an inner cylinder portion in which an insertion hole through which a shaft is inserted is formed, and a housing having an inner cylinder portion radially outside the inner cylinder portion. It is provided with a cooling flow path formed in the above, and a lid member arranged on the outer side of the housing in the radial direction with respect to the inner cylinder portion and arranged adjacent to the cooling flow path.
  • the lid member On the inner diameter side end formed on the inner diameter side of the lid member, which faces the housing in the radial direction, and on the outer diameter side end formed on the outer diameter side of the lid member, which faces the housing in the radial direction. It may be formed and provided with either one of the inner diameter side end portion and the outer diameter side end portion and an abutting surface that abuts in the axial direction of the shaft.
  • a sealing member arranged on either one may be provided.
  • a seal member arranged on the abutting surface may be provided.
  • the supercharger of the present disclosure includes the above cooling structure.
  • FIG. 1 is a schematic cross-sectional view of the turbocharger.
  • FIG. 2 is an extracted view of the alternate long and short dash line portion in FIG.
  • FIG. 3 is an extracted view of a broken line portion in FIG.
  • FIG. 4 is a diagram showing a state in which the abutting surface comes into contact with the inner diameter side end portion of the lid member.
  • FIG. 5 is a diagram showing a state in which the seal member is arranged on the outer diameter side facing surface.
  • FIG. 1 is a schematic cross-sectional view of the turbocharger TC.
  • the arrow L direction shown in FIG. 1 will be described as the left side of the turbocharger TC.
  • the arrow R direction shown in FIG. 1 will be described as the right side of the turbocharger TC.
  • the supercharger TC includes a supercharger main body 1.
  • the turbocharger main body 1 includes a bearing housing 3, a turbine housing 5, and a compressor housing 7.
  • a turbine housing 5 is connected to the left side of the bearing housing 3 by a fastening bolt 9.
  • a compressor housing 7 is connected to the right side of the bearing housing 3 by a fastening bolt 11.
  • a bearing hole 3a is formed in the bearing housing 3.
  • the bearing hole 3a penetrates the supercharger TC in the left-right direction.
  • a bearing 13 is arranged in the bearing hole 3a.
  • FIG. 1 shows a semi-floating bearing as an example of the bearing 13.
  • the bearing 13 may be another radial bearing such as a full floating bearing or a rolling bearing.
  • a shaft 15 is inserted through the bearing 13.
  • the shaft 15 is rotatably supported by the bearing 13.
  • a turbine impeller 17 is provided at the left end of the shaft 15.
  • the turbine impeller 17 is rotatably housed in the turbine housing 5.
  • a compressor impeller 19 is provided at the right end of the shaft 15.
  • the compressor impeller 19 is rotatably housed in the compressor housing 7.
  • the turbine impeller 17 and the compressor impeller 19 rotate integrally with the shaft 15.
  • An intake port 21 is formed in the compressor housing 7.
  • the intake port 21 opens on the right side of the turbocharger TC.
  • the intake port 21 is connected to an air cleaner (not shown).
  • a diffuser flow path 23 is formed between the bearing housing 3 and the compressor housing 7.
  • the diffuser flow path 23 boosts air.
  • the diffuser flow path 23 is formed in an annular shape from the inside to the outside in the radial direction (hereinafter, simply referred to as the radial direction) of the shaft 15 (compressor impeller 19).
  • the diffuser flow path 23 communicates with the intake port 21 via the compressor impeller 19 inside in the radial direction.
  • a compressor scroll flow path 25 is formed in the compressor housing 7.
  • the compressor scroll flow path 25 is formed in an annular shape.
  • the compressor scroll flow path 25 is located, for example, radially outside the compressor impeller 19.
  • the compressor scroll flow path 25 communicates with an engine intake port (not shown) and a diffuser flow path 23.
  • a seal plate 27 is arranged on the back side (left side in FIG. 1) of the compressor impeller 19.
  • the seal plate 27 has a disk shape.
  • the outer diameter of the seal plate 27 is larger than the maximum outer diameter of the compressor impeller 19.
  • the outer diameter of the seal plate 27 may be equal to the maximum outer diameter of the compressor impeller 19, or may be smaller than the maximum outer diameter of the compressor impeller 19.
  • a through hole is formed in the center of the seal plate 27 in the radial direction. The shaft 15 is inserted through the through hole.
  • a fitting hole 3b is formed on the surface of the bearing housing 3 on the compressor housing 7 side (right side in FIG. 1).
  • the seal plate 27 is fitted into the fitting hole 3b.
  • the seal plate 27 is provided with a bolt hole (not shown) radially outside the through hole.
  • the bolt holes penetrate in the rotation axis direction of the shaft 15 (hereinafter, simply referred to as the axial direction).
  • a screw hole (not shown) is formed in the fitting hole 3b at a position facing the bolt hole in the axial direction.
  • Fastening bolts (not shown) are inserted into the bolt holes. Fastening bolts are screwed into the screw holes.
  • the seal plate 27 is fastened to the bearing housing 3 by the fastening bolt.
  • the bearing 13 housed in the bearing hole 3a of the bearing housing 3 is lubricated with lubricating oil.
  • the seal plate 27 suppresses the lubricating oil after lubricating the bearing 13 from leaking from the bearing housing 3 to the compressor housing 7 side.
  • a heat shield plate 29 is arranged between the bearing housing 3 and the turbine housing 5.
  • the heat shield plate 29 has a disk shape.
  • the outer diameter of the heat shield plate 29 is larger than the maximum outer diameter of the turbine impeller 17.
  • a through hole is formed in the center of the heat shield plate 29 in the radial direction.
  • the shaft 15 is inserted through the through hole.
  • the heat shield plate 29 is arranged at a position axially opposed to the turbine impeller 17.
  • the heat shield plate 29 is arranged at a distance from the turbine impeller 17 in the axial direction.
  • the heat shield plate 29 blocks radiant heat from the turbine impeller 17 to the bearing housing 3 side. That is, the heat shield plate 29 suppresses the heat transfer of the exhaust gas to the bearing housing 3 side.
  • the heat shield plate 29 can suppress a temperature rise of the bearing 13 housed in the bearing hole 3a of the bearing housing 3. As a result, the bearing performance of the bearing 13 is maintained.
  • An exhaust port 31 is formed in the turbine housing 5.
  • the exhaust port 31 opens on the left side of the turbocharger TC.
  • the exhaust port 31 is connected to an exhaust gas purification device (not shown).
  • a gap 33 is formed between the bearing housing 3 and the turbine housing 5.
  • a flow passage x through which exhaust gas flows is formed in the gap 33.
  • the flow passage x is formed in an annular shape from the inside to the outside in the radial direction of the shaft 15.
  • a turbine scroll flow path 35 is formed in the turbine housing 5.
  • the turbine scroll flow path 35 is located, for example, radially outside the turbine impeller 17.
  • the flow passage x is located between the turbine impeller 17 and the turbine scroll flow path 35.
  • the flow passage x communicates the turbine scroll flow path 35 with the exhaust port 31 via the turbine impeller 17.
  • the turbine scroll flow path 35 communicates with a gas inlet (not shown). Exhaust gas discharged from an engine exhaust manifold (not shown) is guided to the gas inlet. The exhaust gas guided from the gas inflow port to the turbine scroll flow path 35 is guided to the exhaust port 31 via the flow path x and the blades of the turbine impeller 17. The exhaust gas guided to the exhaust port 31 rotates the turbine impeller 17 in the distribution process.
  • the rotational force of the turbine impeller 17 is transmitted to the compressor impeller 19 via the shaft 15. As described above, the air is boosted by the rotational force of the compressor impeller 19 and guided to the intake port of the engine.
  • the amount of rotation of the turbine impeller 17 becomes small. As the amount of rotation of the turbine impeller 17 decreases, the amount of rotation of the compressor impeller 19 also decreases. If the amount of rotation of the compressor impeller 19 becomes small, the pressure of the air supplied to the intake port of the engine may not be sufficiently increased.
  • variable capacitance mechanism 100 is arranged in the gap 33.
  • the variable capacitance mechanism 100 includes a shroud ring 101, a nozzle ring 103, a nozzle vane 105, a drive mechanism 107, and an actuator 109.
  • the shroud ring 101 is arranged on the side of the gap 33 that is separated from the bearing housing 3.
  • the shroud ring 101 has a main body portion 101a and a protruding portion 101b.
  • the main body 101a is formed in the shape of a thin plate ring.
  • the protruding portion 101b projects from the inner peripheral edge portion of the main body portion 101a toward the exhaust port 31 side.
  • a pin shaft hole 101c is formed in the main body 101a.
  • the pin shaft hole 101c penetrates the main body 101a in the axial direction.
  • a plurality of pin shaft holes 101c are formed at equal intervals in the circumferential direction of the main body 101a (only one is shown in FIG. 1). However, a plurality of pin shaft holes 101c may be formed at unequal intervals in the circumferential direction of the main body 101a.
  • the nozzle ring 103 is arranged on the side of the gap 33 close to the bearing housing 3.
  • the nozzle ring 103 is arranged so as to face the shroud ring 101 in the axial direction.
  • the nozzle ring 103 is arranged axially separated from the shroud ring 101.
  • a flow passage x is formed between the shroud ring 101 and the nozzle ring 103.
  • the nozzle ring 103 has a main body 103a.
  • the main body 103a is formed in the shape of a thin plate ring.
  • the main body 103a of the nozzle ring 103 has approximately the same diameter (outer diameter) as the main body 101a of the shroud ring 101.
  • a pin shaft hole 103b is formed in the main body 103a.
  • the pin shaft hole 103b penetrates the main body 103a in the axial direction.
  • a plurality of pin shaft holes 103b are formed at equal intervals in the circumferential direction of the main body 103a (only one is shown in FIG. 1). However, a plurality of pin shaft holes 103b may be formed at irregular intervals in the circumferential direction of the main body portion 103a.
  • the pin shaft hole 103b is arranged so as to face the pin shaft hole 101c in the axial direction.
  • the connecting pin 111 is inserted into the pin shaft holes 101c and 103b.
  • the shroud ring 101 is connected to the nozzle ring 103 by the connecting pin 111.
  • the connecting pin 111 keeps the facing distance between the shroud ring 101 and the nozzle ring 103 constant.
  • a blade shaft hole 101d is formed in the main body 101a of the shroud ring 101.
  • the blade shaft hole 101d is arranged radially inside the main body portion 101a with respect to the pin shaft hole 101c.
  • the blade shaft hole 101d penetrates the main body 101a in the axial direction.
  • a plurality of blade shaft holes 101d are formed at equal intervals in the circumferential direction of the main body 101a.
  • a blade shaft hole 103c is formed in the main body 103a of the nozzle ring 103.
  • the blade shaft hole 103c is arranged radially inside the main body portion 103a with respect to the pin shaft hole 103b.
  • the blade shaft hole 103c penetrates the main body 103a in the axial direction.
  • a plurality of blade shaft holes 103c are formed at equal intervals in the circumferential direction of the main body 103a (only one is shown in FIG. 1).
  • the blade shaft hole 103c is arranged so as to face the blade shaft hole 101d in the axial direction.
  • a blade shaft 105a is integrally formed on the nozzle vane 105.
  • the blade shaft 105a extends axially from the nozzle vane 105.
  • the blade shaft 105a is inserted into the blade shaft holes 101d and 103c.
  • the blade shaft 105a is rotatably supported by the blade shaft holes 101d and 103c.
  • the nozzle vane 105 is arranged between the main bodies 101a and 103a in a state where the blade shaft 105a is inserted into the blade shaft holes 101d and 103c. That is, the nozzle vane 105 is arranged in the flow passage x.
  • a plurality of nozzle vanes 105 are arranged in the flow passage x at intervals in the circumferential direction.
  • the plurality of nozzle vanes 105 are arranged at equal intervals in the rotational direction (circumferential direction) of the turbine impeller 17. However, the plurality of nozzle vanes 105 may be arranged at irregular intervals in the rotation direction of the turbine impeller 17.
  • the drive mechanism 107 is connected to the actuator 109 and the blade shaft 105a.
  • the actuator 109 is, for example, a pneumatic actuator.
  • the drive mechanism 107 converts the linear motion of the actuator 109 into a rotary motion.
  • the drive mechanism 107 rotates the blade shaft 105a by driving the actuator 109.
  • the nozzle vane 105 rotates integrally with the blade shaft 105a.
  • the intervals between the plurality of nozzle vanes 105 arranged in the flow passage x change.
  • the flow path cross-sectional area of the flow path x changes.
  • the flow velocity of the exhaust gas flowing through the flow passage x changes.
  • the variable capacitance mechanism 100 changes the interval (hereinafter, referred to as opening degree) of the plurality of nozzle vanes 105 according to the flow rate of the exhaust gas. For example, the variable capacitance mechanism 100 reduces the opening degree of the nozzle vane 105 and increases the flow velocity of the exhaust gas when the flow rate of the exhaust gas is small. As a result, the variable capacitance mechanism 100 can increase the amount of rotation of the turbine impeller 17 even when the flow rate of the exhaust gas is small. As a result, the variable capacitance mechanism 100 can increase the amount of rotation of the compressor impeller 19 even when the flow rate of the exhaust gas is small.
  • FIG. 2 is an extracted view of the alternate long and short dash line portion in FIG.
  • FIG. 3 is an extracted view of a broken line portion in FIG.
  • the bearing housing 3 includes a bearing structure BS.
  • the bearing structure BS includes an insertion hole 201, a bearing 13, and a lubricating oil passage 203.
  • the insertion hole 201 penetrates the bearing housing 3 from the left end to the right end in FIG.
  • the shaft 15 is inserted into the insertion hole 201.
  • the insertion hole 201 faces the shaft 15 in the radial direction.
  • a bearing hole 3a is formed in the central portion of the insertion hole 201.
  • the bearing hole 3a is a portion of the insertion hole 201 that faces the bearing 13 in the radial direction.
  • the bearing 13 is housed in the bearing hole 3a.
  • a groove 201a is formed in the insertion hole 201.
  • the groove 201a opens into the insertion hole 201.
  • the opening of the groove 201a is formed on the turbine impeller 17 side with respect to the bearing hole 3a.
  • the opening of the groove 201a is formed between the bearing 13 and the turbine impeller 17.
  • the groove 201a has a radial extending portion 201b and an axial extending portion 201c.
  • the radial extending portion 201b faces the shaft 15 in the radial direction and extends radially outward of the shaft 15.
  • the radial extending portion 201b extends in the circumferential direction of the shaft 15 and is formed in an annular shape.
  • the axial extending portion 201c extends in the axial direction of the shaft 15 from the outer peripheral edge portion of the radial extending portion 201b.
  • the groove 201a may be provided only with the radial extending portion 201b. That is, the groove 201a does not have to include the axially extending portion 201c.
  • a scattering space S1 is formed inside the groove 201a. The details of the scattering space S1 will be described later.
  • Lubricating oil is supplied to the lubricating oil passage 203.
  • the lubricating oil passage 203 opens (communicates) with the bearing hole 3a.
  • the lubricating oil passage 203 guides the lubricating oil to the bearing hole 3a.
  • the lubricating oil flows into the bearing hole 3a from the lubricating oil passage 203.
  • a bearing 13 is arranged in the bearing hole 3a.
  • the bearing 13 is formed in an annular shape.
  • a through hole 13a is formed in the bearing 13.
  • the through hole 13a extends in the radial direction from the inner peripheral surface to the outer peripheral surface of the bearing 13.
  • the through hole 13a faces the lubricating oil passage 203 in the radial direction.
  • the lubricating oil that has flowed into the bearing hole 3a flows into the space S2 between the inner peripheral surface of the bearing 13 and the shaft 15 through the through hole 13a.
  • the lubricating oil that has flowed into the space S2 moves in the axial direction of the shaft 15 (in the left and right directions in FIGS. 2 and 3).
  • a pair of bearing surfaces 13b, 13b are formed on the left and right sides of the space S2 in the bearing 13.
  • Lubricating oil is supplied between the pair of bearing surfaces 13b, 13b and the shaft 15.
  • the lubricating oil lubricates the pair of bearing surfaces 13b and 13b.
  • the shaft 15 is pivotally supported by the oil film pressure of the lubricating oil.
  • the pair of bearing surfaces 13b, 13b receive the radial load of the shaft 15.
  • the lubricating oil that lubricates the pair of bearing surfaces 13b, 13b moves in the axial direction of the shaft 15 in the direction away from the space S2. A part of the lubricating oil moves from the bearing 13 toward the turbine impeller 17. When the shaft 15 rotates, a part of the lubricating oil scatters in the radial direction of the shaft 15 as the shaft 15 rotates.
  • Lubricating oil scattered in the radial direction of the shaft 15 flows into the scattering space S1.
  • the lubricating oil that has flowed into the scattering space S1 falls vertically downward while moving in the scattering space S1 (groove 201a) in the rotational direction of the shaft 15.
  • the scattering space S1 By forming the scattering space S1, the amount of lubricating oil that moves to the turbine impeller 17 side is reduced as compared with the case where the scattering space S1 is not formed.
  • a protrusion 201d protruding inward in the radial direction is formed in the insertion hole 201.
  • the protrusion 201d is arranged on the turbine impeller 17 side with respect to the scattering space S1.
  • a large diameter portion 15a is formed on the shaft 15.
  • the large diameter portion 15a is larger than the diameter of the facing portion of the shaft 15 facing the pair of bearing surfaces 13b, 13b.
  • the large diameter portion 15a faces the protrusion 201d in the radial direction.
  • the amount of lubricating oil that moves to the turbine impeller 17 side is larger than that in the case where the protrusion 201d and the large diameter portion 15a are not arranged. It will be reduced.
  • a seal ring 205 is arranged on the turbine impeller 17 side of the protrusion 201d and the large diameter portion 15a.
  • the seal ring 205 is adjacent to the protrusion 201d and the large diameter portion 15a.
  • the seal ring 205 suppresses the lubricating oil from leaking to the turbine impeller 17 side from the gap between the protrusion 201d and the large diameter portion 15a.
  • the bearing housing 3 includes a cooling structure CS.
  • the cooling structure CS includes a main body (housing) 207 and a lid member 209.
  • the main body 207 forms a part of the bearing housing 3.
  • the lid member 209 forms a part of the bearing housing 3.
  • the bearing housing 3 is composed of the main body 207 and the lid member 209.
  • the main body 207 has an inner cylinder portion 207a in which the insertion hole 201 is formed.
  • a groove 201a (scattering space S1) is formed in the inner cylinder portion 207a.
  • a cooling flow path 211 is formed in the main body 207.
  • the cooling flow path 211 is formed radially outside the inner cylinder portion 207a.
  • the inner cylinder portion 207a is a portion of the main body 207 that is radially inside the cooling flow path 211.
  • a partition wall 207b is formed between the cooling flow path 211 and the groove 201a.
  • the cooling flow path 211 and the groove 201a are separated by a partition wall 207b.
  • the cooling flow path 211 extends in the circumferential direction of the shaft 15.
  • An opening 213 is formed in the main body 207 on the turbine housing 5 side of the cooling flow path 211.
  • the opening 213 opens to the outside of the main body 207.
  • the opening 213 is continuous with the cooling flow path 211.
  • Cooling liquid flows through the cooling flow path 211.
  • the coolant cools the bearing housing 3 (main body 207).
  • the temperature on the turbine impeller 17 side tends to be higher than that on the compressor impeller 19 side. Therefore, the cooling flow path 211 is formed on the turbine impeller 17 side of the main body 207.
  • the lid member 209 is formed in an annular shape.
  • the lid member 209 is arranged radially outside the inner cylinder portion 207a.
  • the lid member 209 is arranged in the opening 213.
  • the lid member 209 closes the opening 213. In other words, the lid member 209 covers the opening 213.
  • the lid member 209 is press-fitted into the opening 213. As a result, the lid member 209 is joined to the main body 207.
  • the present invention is not limited to this, and the lid member 209 may be fastened to the main body 207, welded, or adhered.
  • the lid member 209 When the lid member 209 is press-fitted into the opening 213, the lid member 209 is arranged adjacent to the cooling flow path 211.
  • the left side of the lid member 209 faces the external space (internal space of the turbine housing 5), and the right side of the lid member 209 faces the cooling flow path 211. That is, the lid member 209 forms a part of the cooling flow path 211.
  • the cooling flow path 211 is formed by two members, the main body 207 and the lid member 209.
  • a heat shield plate 29 is arranged on the left side of FIG. 2 from the lid member 209.
  • a nozzle ring 103 is arranged on the left side of FIG. 2 from the heat shield plate 29.
  • a spring washer SW is arranged between the lid member 209 and the heat shield plate 29.
  • the spring washer SW is connected to the lid member 209 and the heat shield plate 29.
  • the spring washer SW presses the heat shield plate 29 in a direction away from the lid member 209. By this pressing, the heat shield plate 29 comes into contact with the nozzle ring 103. That is, the heat shield plate 29 is pressed against the nozzle ring 103 by the spring washer SW.
  • the heat shield plate 29 is held between the nozzle ring 103 and the lid member 209 by the spring washer SW.
  • the lid member 209 includes an inner diameter side end portion 209a and an outer diameter side end portion 209b.
  • the inner diameter side end portion 209a is formed on the inner diameter side of the lid member 209.
  • the inner diameter side end portion 209a faces the main body 207 in the radial direction.
  • the outer diameter side end portion 209b is formed on the outer diameter side of the lid member 209.
  • the outer diameter side end portion 209b faces the main body 207 in the radial direction.
  • the opening 213 includes an inner diameter side facing surface 213a, an outer diameter side facing surface 213b, and an abutting surface 213c.
  • the inner diameter side facing surface 213a faces the inner diameter side end portion 209a of the lid member 209 in the radial direction.
  • the outer diameter side facing surface 213b faces the outer diameter side end portion 209b of the lid member 209 in the radial direction.
  • the abutting surface 213c faces the outer diameter side end portion 209b in the axial direction and comes into contact with the outer diameter side end portion 209b.
  • the abutting surface 213c abuts on the outer diameter side end portion 209b to determine the axial position of the lid member 209.
  • the inner diameter side facing surface 213a has a roughly cylindrical shape.
  • the inner diameter side facing surface 213a is located at a position where the inner peripheral surface on the inner diameter side of the cooling flow path 211 extends in the axial direction.
  • the inner diameter side facing surface 213a is flush with the inner peripheral surface of the cooling flow path 211 on the inner diameter side.
  • the abutting surface 213c has a roughly circular ring shape.
  • the abutting surface 213c is located at a position where the inner peripheral surface on the outer diameter side of the cooling flow path 211 extends in a direction orthogonal to the axial direction.
  • the inner diameter end of the abutting surface 213c is continuous with the inner peripheral surface on the outer diameter side of the cooling flow path 211.
  • the outer diameter side facing surface 213b has a substantially cylindrical shape.
  • the outer diameter side facing surface 213b is continuous with the outer diameter end of the abutting surface 213c.
  • the outer diameter side facing surface 213b is located at a position extending axially from the outer diameter end of the abutting surface 213c toward the turbine housing 5 side.
  • the lid member 209 is made of the same material as the main body 207. That is, the lid member 209 is made of a material having the same coefficient of linear expansion as that of the main body 207. However, the lid member 209 may have a coefficient of linear expansion different from that of the main body 207. For example, the lid member 209 may be made of a material having a coefficient of linear expansion larger than that of the main body 207. In that case, when the temperature of the bearing housing 3 rises, the lid member 209 expands more than the main body 207.
  • the outer diameter side facing surface 213b is pressed outward in the radial direction by the outer diameter side end portion 209b. Therefore, the coolant flowing through the cooling flow path 211 is less likely to leak from between the outer diameter side facing surface 213b and the outer diameter side end portion 209b.
  • the seal member 215 is arranged on the inner diameter side facing surface 213a.
  • the seal member 215 is, for example, a seal ring. The seal member 215 suppresses the cooling liquid from leaking to the turbine housing 5 side from between the inner diameter side facing surface 213a and the inner diameter side end portion 209a.
  • the seal member 217 is also arranged on the abutting surface 213c.
  • the seal member 217 is, for example, a seal ring.
  • the seal member 217 suppresses the cooling liquid from leaking to the turbine housing 5 side from between the abutting surface 213c and the outer diameter side end portion 209b.
  • the seal members 215 and 217 are not indispensable configurations.
  • the seal members 215 and 217 may not be arranged on the inner diameter side facing surface 213a and the abutting surface 213c.
  • the cooling flow path 211 is formed by two members, the main body 207 and the lid member 209. That is, the cooling flow path 211 is formed by two divided members.
  • a casting method in which a cooling flow path is formed by one member has been performed.
  • the cooling flow path was formed by one member by arranging a sand mold (core) in the mold at the time of casting the bearing housing.
  • a sand mold core
  • the shape of the cooling flow path and the cross-sectional area of the flow path are limited.
  • the cooling flow path has a complicated structure, it is difficult to remove the cast sand after forming the bearing housing by casting. Further, in the conventional casting method, when the cooling flow path is made into a complicated shape or the wall thickness forming the cooling flow path is thinly formed, the allowable dimensional tolerance range becomes small and the yield may deteriorate. was there.
  • the cooling flow path 211 is formed by two members, the main body 207 and the lid member 209. Before the lid member 209 is attached to the main body 207, the cooling flow path 211 is exposed to the outside of the main body 207 through the opening 213. Therefore, the cooling flow path 211 can be cut from the outside. Therefore, the cooling structure CS can relax the restrictions on the shape of the cooling flow path 211 and the cross-sectional area of the flow path.
  • the cooling flow path 211 may be formed by cutting instead of being formed by casting. Further, the cooling flow path 211 may be formed by casting (that is, formed by arranging a core in a mold) and then by cutting.
  • the cooling flow path 211 is formed of two members, a main body 207 and a lid member 209. Thereby, for example, by reducing the thickness of the lid member 209 in the axial direction, it becomes easy to bring the cooling flow path 211 closer to the seal ring 205 provided on the shaft 15. Further, by cutting the cooling flow path 211 in the axial direction and the radial direction, it becomes easy to bring the cooling flow path 211 closer to the seal ring 205. By bringing the cooling flow path 211 closer to the seal ring 205, it is possible to prevent the temperature of the seal ring 205 from becoming higher than the heat resistant temperature.
  • the cooling flow path 211 is exposed to the outside of the main body 207 through the opening 213 before the lid member 209 is attached to the main body 207. Therefore, even when the bearing housing 3 is formed by casting, it becomes easy to remove the cast sand from the cooling flow path 211. Further, the cooling flow path 211 can be formed by cutting by exposing it to the outside of the main body 207 through the opening 213. Therefore, in the cooling structure CS of the present embodiment, the range of dimensional tolerance at the time of casting can be increased, and the yield can be improved.
  • a lid member 209 adjacent to the cooling flow path 211 is arranged radially outside the inner cylinder portion 207a of the main body 207. Therefore, the dividing surface (joining surface) between the main body 207 and the lid member 209 is not exposed to the insertion hole 201 (groove 201a). That is, the dividing surface (joining surface) between the main body 207 and the lid member 209 does not communicate with the insertion hole 201 (groove 201a).
  • the dividing surface of the main body 207 and the lid member 209 communicates with the insertion hole 201 (groove 201a)
  • a part of the cooling liquid flowing through the cooling flow path 211 may flow into the scattering space S1 through the dividing surface. ..
  • the lubricating oil in the scattering space S1 may be mixed with the coolant and the lubricating oil may be diluted.
  • the lubricating oil is diluted, for example, when the turbocharger TC is mounted on a vehicle or a ship, it causes an engine failure.
  • the cooling structure CS of the present embodiment can suppress (reduce) the mixture of the coolant and the lubricating oil, the dilution of the lubricating oil, and the failure of the engine.
  • the cooling structure CS of the present embodiment includes an abutting surface 213c capable of axially contacting the outer diameter side end portion 209b of the lid member 209.
  • the abutting surface 213c can position the lid member 209 in the axial direction.
  • the abutting surface 213c may abut in the axial direction with the inner diameter side end portion 209a of the lid member 209.
  • FIG. 4 is a diagram showing a state in which the abutting surface 313c is in contact with the inner diameter side end portion 309a of the lid member 309.
  • the main body 307 is formed with a cooling flow path 211 and an opening 313.
  • the lid member 309 is press-fitted into the opening 313.
  • the opening 313 includes an inner diameter side facing surface 313a, an outer diameter side facing surface 313b, and an abutting surface 313c.
  • the inner diameter side facing surface 313a faces the inner diameter side end portion 309a of the lid member 309 in the radial direction.
  • the outer diameter side facing surface 313b faces the outer diameter side end portion 309b of the lid member 309 in the radial direction.
  • the abutting surface 313c faces the inner diameter side end portion 309a in the axial direction and abuts on the inner diameter side end portion 309a.
  • the abutting surface 313c abuts on the inner diameter side end portion 309a to determine the axial position of the lid member 309.
  • the abutting surfaces 213c and 313c may abut in the axial direction with either one of the inner diameter side end portion 309a and the outer diameter side end portion 209b.
  • the outer diameter side facing surface 313b has a roughly cylindrical shape.
  • the outer diameter side facing surface 313b is located at a position where the inner peripheral surface on the outer diameter side of the cooling flow path 211 extends in the axial direction.
  • the outer diameter side facing surface 313b is flush with the outer diameter side inner peripheral surface of the cooling flow path 211.
  • the abutting surface 313c has a roughly circular ring shape.
  • the abutting surface 313c is located at a position where the inner peripheral surface on the inner diameter side of the cooling flow path 211 extends in a direction orthogonal to the axial direction.
  • the outer diameter end of the abutting surface 313c is continuous with the inner peripheral surface on the inner diameter side of the cooling flow path 211.
  • the inner diameter side facing surface 313a has a substantially cylindrical shape.
  • the inner diameter side facing surface 313a is continuous with the inner diameter end of the abutting surface 313c.
  • the inner diameter side facing surface 313a is located at a position extending axially from the inner diameter end of the abutting surface 313c toward the turbine housing 5 side.
  • the lid member 309 is made of a material having a coefficient of linear expansion smaller than that of the main body 307, the main body 307 expands more than the lid member 309 as the temperature of the bearing housing 3 rises.
  • the inner diameter side end portion 309a is pressed outward in the radial direction by the inner diameter side facing surface 313a. Therefore, the cooling liquid flowing through the cooling flow path 211 is less likely to leak from between the inner diameter side facing surface 313a and the inner diameter side end portion 309a.
  • the seal member 315 is arranged on the outer diameter side facing surface 313b.
  • the seal member 315 is, for example, a seal ring.
  • the seal member 315 suppresses the coolant from leaking to the turbine housing 5 side from between the outer diameter side facing surface 313b and the outer diameter side end portion 309b.
  • the seal members 215 and 315 may be arranged on either the inner diameter side facing surface 213a or the outer diameter side facing surface 313b. As a result, even if the materials of the main bodies 207 and 307 and the lid members 209 and 309 are different, it is possible to prevent the coolant from leaking from the cooling flow path 211 to the turbine housing 5 side.
  • the seal members 215 and 315 are not limited to the seal ring.
  • the sealing members 215 and 315 may be, for example, a liquid gasket.
  • FIG. 5 is a diagram showing a state in which the seal member 415 is arranged on the outer diameter side facing surface 413b. As shown in FIG. 5, the main body 407 is formed with a cooling flow path 211 and an opening 413. A lid member 409 is screwed to the opening 413.
  • the opening 413 includes an inner diameter side facing surface 313a, an outer diameter side facing surface 413b, and an abutting surface 313c.
  • the inner diameter side facing surface 313a faces the inner diameter side end portion 309a of the lid member 409 in the radial direction.
  • the outer diameter side facing surface 413b faces the outer diameter side end portion 409b of the lid member 409 in the radial direction.
  • the abutting surface 313c faces the inner diameter side end portion 309a in the axial direction and abuts on the inner diameter side end portion 309a.
  • a female threaded portion FS with a thread on the inner circumference is formed on the outer diameter side facing surface 413b.
  • a male threaded portion MS having a thread on the outer circumference is formed on the outer diameter side end portion 409b.
  • a seal member 415 is arranged between the female screw portion FS and the male screw portion MS.
  • the sealing member 315 is, for example, a liquid gasket.
  • the seal member 415 suppresses the coolant from leaking to the turbine housing 5 side from between the female screw portion FS and the male screw portion MS.
  • the sealing member 217 is arranged on the abutting surface 213c (see FIGS. 2 and 3). As a result, the seal member 217 suppresses the cooling liquid from leaking to the turbine housing 5 side from between the abutting surface 213c and the outer diameter side end portion 209b.
  • the present invention is not limited to this, and the abutting surfaces 213c and 313c may not be formed on the main bodies 207, 307, and 407. Further, in the above embodiment, an example in which the seal members 215, 315, and 415 are arranged on the inner diameter side facing surfaces 213a, 313a or the outer diameter side facing surfaces 213b, 313b, and 413b has been described.
  • the present invention is not limited to this, and the seal members 215, 315, and 415 may not be arranged on the inner diameter side facing surfaces 213a, 313a or the outer diameter side facing surfaces 213b, 313b, and 413b.
  • the seal member 217 is arranged on the abutting surfaces 213c and 313c.
  • the present invention is not limited to this, and the seal member 217 may not be arranged on the abutting surfaces 213c and 313c.
  • the lid members 209, 309, 409 may be welded to the main body 207, 307, 407.
  • This disclosure can be used for the cooling structure CS and the turbocharger TC.
  • Shaft 201 Insertion hole 207: Main body (housing) 207a: Inner cylinder part 209: Lid member 209a: Inner diameter side end 209b: Outer diameter side end 211: Cooling flow path 213a: Inner diameter side facing surface 213b: Outer diameter Side facing surface 213c: Abutting surface 215: Seal member 217: Seal member 309a: Inner diameter side end 309b: Outer diameter side end 313a: Inner diameter side facing surface 313b: Outer diameter side facing surface 313c: Abutting surface 315: Seal Member CS: Cooling structure

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
PCT/JP2020/032067 2019-10-30 2020-08-25 冷却構造体および過給機 Ceased WO2021084871A1 (ja)

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DE112020005348.2T DE112020005348T5 (de) 2019-10-30 2020-08-25 Kühlstruktur und Turbolader
CN202080074124.8A CN114585803B (zh) 2019-10-30 2020-08-25 冷却结构体及增压器
JP2021554108A JP7315019B2 (ja) 2019-10-30 2020-08-25 冷却構造体および過給機
US17/656,969 US11732606B2 (en) 2019-10-30 2022-03-29 Cooling structure and turbocharger

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JP2019-196986 2019-10-30

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CN114585803A (zh) 2022-06-03
JP7315019B2 (ja) 2023-07-26
US20220220864A1 (en) 2022-07-14

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