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US20120269624A1 - Axial bearing arrangement for a shaft of a turbocharger - Google Patents

Axial bearing arrangement for a shaft of a turbocharger Download PDF

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Publication number
US20120269624A1
US20120269624A1 US13/509,636 US201013509636A US2012269624A1 US 20120269624 A1 US20120269624 A1 US 20120269624A1 US 201013509636 A US201013509636 A US 201013509636A US 2012269624 A1 US2012269624 A1 US 2012269624A1
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US
United States
Prior art keywords
turbocharger
axial bearing
axial
housing
bearing
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.)
Abandoned
Application number
US13/509,636
Other languages
English (en)
Inventor
Ralf Boening
Holger Faeth
Ralph Maurice Koempel
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.)
Continental Automotive GmbH
Original Assignee
Continental Automotive GmbH
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 Continental Automotive GmbH filed Critical Continental Automotive GmbH
Assigned to CONTINENTAL AUTOMOTIVE GMBH reassignment CONTINENTAL AUTOMOTIVE GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOENING, RALF, FAETH, HOLGER, KOEMPEL, RALPH-MAURICE
Publication of US20120269624A1 publication Critical patent/US20120269624A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
    • F16C35/02—Rigid support of bearing units; Housings, e.g. caps, covers in the case of sliding-contact 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/166—Sliding contact bearing
    • F01D25/168—Sliding contact bearing for axial load mainly
    • 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
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/051—Axial thrust balancing
    • F04D29/0513—Axial thrust balancing hydrostatic; hydrodynamic thrust bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F04D29/0563—Bearings cartridges
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
    • F16C17/047—Sliding-contact bearings for exclusively rotary movement for axial load only with fixed wedges to generate hydrodynamic 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/51—Magnetic
    • 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
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/52—Axial thrust bearings
    • 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 invention relates to an axial bearing arrangement for a shaft in a turbocharger, the housing or a section of the housing of the turbocharger preferably being divided in a longitudinal direction into at least two housing halves.
  • a turbocharger consists of an exhaust gas turbine in an exhaust gas mass flow, which turbine is connected via a shaft to a compressor in the intake duct.
  • the turbine wheel of the turbine is arranged in a turbine housing and the compressor wheel of the compressor in a compressor housing.
  • the shaft is in turn mounted in a bearing housing.
  • the turbine wheel is driven by the exhaust gas mass flow and in turn drives the compressor wheel.
  • the compressor compresses the aspirated air and conducts it to the internal combustion engine.
  • the shaft is supported in the bearing housing by means of a radial bearing arrangement.
  • turbocharger housing is divided in a longitudinal direction and not, as hitherto, transversely to its longitudinal axis, that is, in a transverse direction.
  • This new turbocharger housing is the subject matter of a further patent application.
  • turbocharger having a turbocharger housing with an axial bearing arrangement having the features of claim 1 .
  • a turbocharger is made available with a turbocharger housing wherein at least one section of the turbocharger housing is configured to be divided or subdivided in a longitudinal direction into at least two housing halves, wherein a shaft is mounted in the turbocharger housing and wherein at least one axial bearing arrangement is provided in order to support the shaft in the axial direction.
  • turbocharger has the advantage that the axial bearing arrangement can be fitted to the rotor assembly and the rotor assembly with the axial bearing arrangement can then be placed complete in the housing halves of the turbocharger housing divided in a longitudinal direction.
  • FIG. 1 is a view of a housing half of a turbocharger which is configured to be divided in a longitudinal direction into two housing halves, the shaft being provided in the turbocharger housing with a radial bearing arrangement and an axial bearing arrangement according to a first embodiment of the invention;
  • FIG. 2 is a sectional view of the turbocharger according to FIG. 1 ;
  • FIG. 3 is a sectional view through a turbocharger housing having an axial bearing arrangement according to a further variant of the first embodiment of the invention
  • FIG. 4 is a sectional view through a turbocharger housing having an axial bearing arrangement according to a second embodiment of the invention
  • FIG. 5 is a sectional view through a turbocharger housing divided in a longitudinal direction with an axial bearing arrangement according to a third embodiment of the invention
  • FIG. 6 is a sectional view through a turbocharger housing divided in a longitudinal direction with an axial bearing arrangement according to a fourth embodiment of the invention.
  • FIG. 7 is a sectional view through a turbocharger housing divided in a longitudinal direction with an axial bearing arrangement according to a fifth embodiment of the invention.
  • FIG. 1 shows a sectional view through a turbocharger 10 having a turbocharger housing 12 which is configured to be divided in a longitudinal direction into, for example, at least two housing halves 14 .
  • FIG. 1 shows a housing half 14 from the seal side.
  • the housing half 14 has a recess 15 or groove in which a sealing arrangement can be received for fastening the two housing halves in a sealed manner.
  • the recess 15 and the path of the recess 15 in which a sealing arrangement is provided in order to seal the housing halves 14
  • the sealing of the two housing halves is the subject matter of a separate patent application.
  • the turbocharger housing 12 comprises a bearing housing 18 , a turbine housing 20 and a compressor housing 22 , all three housings being, for example, combined to form one housing and being configured to be divided along the longitudinal direction into at least two housing halves 14 .
  • the whole turbocharger housing 12 as in FIG. 1 , or at least a section of the turbocharger housing 12 , may be configured to be divided in a longitudinal direction into at least two housing halves 14 .
  • turbocharger housing 12 is configured to be divided in a longitudinal direction, for example in a horizontal plane, the longitudinal axis 24 of the turbocharger housing 12 lying in this case in the horizontal plane.
  • the turbocharger housing 12 may be configured to be divided into at least two housing halves 14 in every plane in the longitudinal direction.
  • the longitudinal axis 24 does not need to lie in this parting plane or, for example, to intersect said parting plane, although it may do so.
  • the turbocharger housing 12 may optionally be configured to be additionally at least partially coolable and/or heatable. More precisely, in the example shown in FIG. 1 the turbocharger housing 12 has in the region of the turbine housing 20 and of the bearing housing 18 an additional fluid jacket 26 or temperature regulating jacket into which a fluid, for example water, can be conducted in order to regulate the temperature of, or to cool and/or heat this region of the turbocharger housing 12 , depending on the function and application.
  • a fluid for example water
  • the housing half 14 shown in FIG. 1 is fastened and sealed to the other, corresponding housing half (not shown).
  • at least one or a plurality of bores 28 are provided in order to screw and/or pin the two housing halves 14 to one another.
  • any other form of fastening which is suitable for connecting the two housing halves 14 to one another and making possible or itself providing a seal between the two housing halves 14 , may be provided.
  • a bead seal, an O-ring seal and/or an elastomeric seal for example, may be provided as a sealing device for sealing the two housing halves 14 .
  • the bead seal, or one of the other seals is placed in a suitable recess 15 in one or both of the housing halves 14 , while the other housing-half surfaces which are not sealed are, for example, in direct contact with one another.
  • a shaft 30 on which a turbine wheel 32 and a compressor wheel 34 are provided is mounted in the bearing housing section 18 of the turbocharger housing 12 .
  • the turbine wheel 32 is arranged in the turbine housing section 20 and the compressor wheel 34 in the compressor housing section 22 of the turbocharger housing 12 .
  • the shaft 30 has a radial bearing arrangement 36 and an axial bearing arrangement 38 , according to the first embodiment of the invention.
  • an axial bearing arrangement 38 comprising at least one or a plurality of axial bearings is used in order to absorb, for example, the axial thrust and to position axially the rotor assembly, or the turbine and compressor wheels 32 , 34 , in such a way as to achieve both relatively high efficiency through narrow flow gaps and to prevent damage.
  • an axial bearing can no longer be installed axially since the rotor disk 32 , 34 or rotor is inserted radially and axial access no longer exists.
  • an axial bearing was firmly screw-fastened axially in a closed bearing housing prior to assembly. The rotor assembly was then mounted afterwards with the bearing arrangement.
  • the axial bearing arrangement 38 is now also mounted on the rotor assembly, and the bearing surface is provided and machined with the housing half.
  • the axial bearing arrangement 38 comprises at least one axial bearing 40 , for example in the form of an axial bearing disk. As shown in FIG. 1 , this axial bearing 40 is fastened to the shaft 30 of the rotor assembly. In order to be fastened to the shaft 30 , the axial bearing arrangement 38 may be cramped, screwed, pressed and/or shrunk thereon, to mention only a few examples of fastening possibilities. This applies to all embodiments of the invention. In this case the axial bearing 40 may be bounded on one side by a step of the shaft, and optionally on the other side additionally by a bush element 42 or a sleeve.
  • the bush element 42 additionally has on its outer side at least one sealing device 44 for sealing the bearing housing section 18 with respect to the compressor housing section 22 .
  • the sealing device 44 in this case, two piston ring seals in corresponding grooves on the outside of the bush element 42 may, for example, be provided.
  • the shaft 30 is mounted by means of a radial bearing arrangement 36 .
  • the radial bearing arrangement 36 has on its outer side a sleeve element 46 consisting, for example, of metal, e.g. steel, or including same, and has a collar section 48 at each end.
  • at least one or both collar sections 48 of the sleeve element 46 are, for example, configured to be resilient, in order to be tensioned between two stops or receptacles 50 , or in this case projections of the turbocharger housing 12 , and to tension the bearing arrangement provided in the sleeve element 46 in the axial direction.
  • one or both collar sections 48 may be configured to be non-resilient or stiff, and may be placed between the two stops 50 .
  • one or both collar sections 48 may optionally be additionally fastened, for example by means of screws, to the associated receptacle 50 .
  • at least one resiliently-acting or stiff collar section may also be additionally screw-fastened and/or pinned to the respective associated receptacle 50 .
  • one or both collar sections 48 are, for example, connected integrally or as separate parts to the sleeve element 46 .
  • the separate collar section 48 may optionally be additionally fastened to the sleeve element 46 , for example locked and/or screwed thereto, after the sleeve element 46 has been inserted in the bore.
  • one or both collar sections 48 of the sleeve element 46 may also optionally project additionally from the oil chamber, both on the turbine side, as shown in FIG. 1 , and on the compressor side (not shown), and take over further functions, for example that of a heat shield.
  • One or both collar sections 48 may, however, remain within the oil chamber, like the collar section 48 on the compressor side in FIG. 1 .
  • the sleeve element 46 may now itself be configured, for example, as a radial sliding bearing arrangement (not shown) and form two sliding bearing sections.
  • the sleeve element 46 as shown in the embodiment in FIG. 1 , may also receive a sleeve 54 which includes the two sliding bearing sections 52 .
  • two radial bearings may, for example, be also provided as sliding bearings, which radial bearings optionally are additionally arranged in the sleeve element 46 and spaced from one another by means of a spacer sleeve (not shown).
  • the sleeve element 46 may also be configured on its inner side as a spacer sleeve with a stop for each sliding bearing (not shown).
  • a layer 56 consisting of at least one or a plurality of plies of an elastic, heat-resistant or temperature-resistant material may optionally be provided additionally on the inner and/or outer side of the sleeve element 46 , as shown in FIG. 1 .
  • the material consists, for example, of a polymer, an elastomer and/or a hard rubber.
  • the invention is not limited to these materials. In principle, any other suitable, heat-resistant or temperature-resistant, elastic material may be used.
  • the sleeve 54 is fitted to the shaft 30 , the shaft 30 having, for example, a step with a stop for the sleeve 54 .
  • the axial bearing arrangement 38 which forms a stop for the sleeve 54 or the radial bearing arrangement 36 in the axial direction, is provided at the other end of the sleeve 54 .
  • a sheet metal oil barrier 58 may additionally be arranged on the axial bearing arrangement 38 or the axial bearing disk 40 , the axial bearing disk 40 optionally having additionally a receptacle 60 for the sheet metal oil barrier 58 .
  • the shaft 30 can easily be placed, together with the sleeve 54 , the layer 56 made of an elastic material or material combinations, and the sleeve element 46 with the two collar sections 48 , in the housing halves 14 of the longitudinally divided turbocharger housing 12 .
  • FIG. 2 shows in addition a sectional view through the turbocharger housing 12 , both housing halves 14 , 16 being represented. In this case the seal between the two housing halves 14 , 16 is also indicated in highly simplified form.
  • FIG. 3 further shows a sectional side view through a turbocharger housing 12 with an axial bearing arrangement 38 according to a further variant of the first embodiment of the invention.
  • a portion of the bearing housing section 18 of both housing halves 14 , 16 is shown in a sectional view.
  • the shaft 30 is mounted in the housing 18 by means of a radial bearing arrangement 36 consisting, for example, of two sliding bearings 62 between which, for example, a spacer sleeve 64 is additionally arranged.
  • An axial bearing arrangement 38 comprising at least one axial bearing 40 , for example in the form of an axial bearing disk, is further provided.
  • the axial bearing disk 40 is in this case fastened to the shaft 30 of the rotor assembly, being, for example, cramped, pressed or shrunk thereon, to mention only a few examples of possibilities of fastening the axial bearing arrangement 38 to the rotor or to the shaft 30 .
  • the axial bearing 40 may be arranged in a hollow or recess of the turbocharger housing 12 , the recess having on one or both sides a boundary portion 66 for the axial bearing arrangement 38 .
  • the boundary portion 66 or projection may be formed integrally or may be fastened to the turbocharger housing 12 as a separate part. In this case the boundary portion 66 additionally opposes unwanted axial movement of the axial bearing 40 , and serves here as an axial boundary portion.
  • a bush element 42 which may additionally have sealing elements on its outer side, may optionally be additionally provided for sealing the bearing housing section with respect to the rotor housing section (not shown).
  • a disk element 79 which serves, for example, to spin off lubricant from the shaft 30 , may, for example, be additionally provided adjacent to the bush element 42 .
  • the first embodiment according to the invention in which the rotor assembly includes an axial bearing arrangement 38 mounted on the shaft 30 , has the advantage that it is no longer necessary to fasten an axial bearing arrangement 38 separately in the housing 12 .
  • the assembled rotor assembly can be placed directly therein.
  • the recess or boundary portion 66 on one or both sides of the axial bearing 40 opposes unwanted axial movement of the axial bearing 40 .
  • the axial bearing 40 does not need to be placed in a recess or to have one or two lateral boundary portions 66 , since the axial bearing 40 is itself fastened firmly to the shaft 30 .
  • FIG. 4 shows in addition a sectional view through both housing halves 14 , 16 of a longitudinally divided turbocharger housing 12 having an axial bearing arrangement 38 according to a second embodiment of the invention.
  • the axial bearing arrangement 38 also comprises at least one axial bearing 40 , for example in the form of an axial bearing disk.
  • the axial bearing 40 has at least one or two bracket elements 68 or projections with which the axial bearing 40 is screwed firmly to a housing half 16 .
  • the axial bearing arrangement 38 may have play between its opening 70 and the external circumference of the shaft 30 .
  • the advantage of the second embodiment according to the invention, in which the axial bearing arrangement 38 is fixed radially with bracket elements 68 , is that the axial bearing arrangement 38 can already be fitted to the rotor assembly and then fastened, for example screwed and/or pinned, in the housing half 16 perpendicularly to the main or longitudinal axis 24 . In this case one has very easy, unobstructed access with a screwdriver to the screwing location.
  • FIG. 5 shows a sectional side view through a turbocharger housing 12 with an axial bearing arrangement 38 according to a third embodiment of the invention.
  • a shaft 30 supported radially by means of two radial sliding bearings 62 is represented, it being possible for the radial sliding bearings optionally to be arranged additionally in an insert sleeve 54 , as shown in FIG. 5 .
  • a shaft step is, for example, provided on one or both sides of the radial bearing arrangement 36 , on which shaft step an additional bearing collar 72 serving to provide the bearing surfaces for the axial bearing is arranged.
  • the bearing collar 72 is configured, for example, as a rotary part or a rotationally symmetrical part.
  • the bearing collar 72 has in turn on its outer side a receptacle 74 , for example in the form of a step or a recess (not shown), for the axial bearing arrangement 38 .
  • the axial bearing arrangement 38 comprises at least one axial bearing 40 , for example in the form of an axial bearing disk. Play is provided between the axial bearing 40 and the bearing collar 72 , since the bearing collar 72 rotates with the shaft 30 while the axial bearing 40 is fixed.
  • the axial bearing 40 may be fastened, for example by means of one or more screws 76 and/or pins (not shown), to the insert sleeve 54 and/or to the housing 12 .
  • the bearing collar 72 is fastened in such a way that it rotates with the shaft 30 .
  • the bearing collar 72 is, for example, clamped to the shaft 30 by means of a shaft nut, in which case a clearance fit or transition fit may be provided between the shaft 30 and the bearing collar 72 .
  • the bearing collar 72 may also be fastened to the shaft 30 in any other way.
  • the axial bearing arrangement 38 may be fastened, for example, to a separately installed insert sleeve 54 , as shown in FIG. 5 , for example by means of the fastening methods and fastening means described previously.
  • a further disk element 79 which can be used to spin off lubricant such as oil from the shaft 30 , may be additionally provided adjacent to the bearing collar 72 .
  • an additional step or boundary portion which additionally opposes axial movement of the axial bearing arrangement, as in FIG. 3 , can be dispensed with in this case. In principle, however, such a boundary portion may be provided on one or both sides of the axial bearing 40 , depending on function and application.
  • the third embodiment according to the invention in which the axial bearing arrangement 38 is arranged on a bearing collar 72 or bearing core or is screwed to an insert sleeve 54 , has the advantage that the axial bearing arrangement 38 can be assembled outside the housing halves of the turbocharger housing 12 and then placed therein together with the rotor.
  • FIG. 6 further shows a sectional side view through a turbocharger housing 12 and its two housing halves 14 , 16 , with an axial bearing arrangement 38 according to a fourth embodiment of the invention.
  • the axial bearing arrangement 38 may be arranged, for example, directly on the rotor or the shaft 30 (not shown) or, as shown in FIG. 6 , on a bearing collar 72 .
  • the axial bearing arrangement 38 likewise comprises at least one axial bearing 40 , for example in the form of an axial bearing disk.
  • the axial bearing 40 may in this case be provided on the bearing block 72 as described earlier, for example in FIG. 5 , the bearing collar 72 serving to provide the bearing surfaces for the axial bearing.
  • the axial bearing 40 is fixed rigidly or via at least one spring element 78 , while the bearing collar 72 rotates with the shaft 30 .
  • the bearing collar 72 may also be omitted.
  • the shaft 30 provides the bearing surface for the axial bearing 40 (not shown).
  • At least one spring element 78 with which the axial bearing arrangement 38 is braced axially in the turbocharger housing 12 , is used according to the fourth embodiment according to the invention.
  • the axial bearing arrangement 38 is fitted in a receptacle 60 in the form, for example, of a recess or hollow in the bearing housing section 18 and braced in the receptacle 60 by means of the spring element 78 , so that unwanted movement of the axial bearing 40 in the axial direction is opposed.
  • the axial bearing arrangement 38 is pressed against an axial surface of the receptacle 60 by the at least one spring element 78 .
  • At least one oil barrier ring 79 which is also tensioned on the shaft 30 may additionally be provided, as shown in FIG. 6 , the oil barrier ring 79 spinning off the oil or lubricant.
  • a spring element (not shown), which is arranged, for example, on the shaft 30 in the receptacle 60 , may optionally be provided additionally in order to fix the axial bearing 40 additionally in the axial direction.
  • the fourth embodiment according to the invention has the advantage that the spring element 78 and the receptacle or groove allow the axial bearing arrangement 38 to be fitted onto the rotor. In this case screw-fixing processes are omitted.
  • FIG. 7 shows a sectional side view through a turbocharger housing 12 with an axial bearing arrangement 38 according to a fifth embodiment of the invention.
  • the axial bearing arrangement 38 also comprises at least one axial bearing 40 , for example in the form of an axial bearing disk.
  • the axial bearing 40 as described previously, may be arranged, for example, directly on the shaft 30 (not shown) or, for example, on a bearing collar 72 , as shown in FIG. 7 , and may form, for example, a clearance fit with the shaft 30 or with the bearing collar 72 .
  • the axial bearing 40 is fixed while the bearing collar 72 rotates with the shaft 30 .
  • the axial bearing 40 may be simply fitted into an associated receptacle 60 or, optionally, may additionally be clamped or fastened therein. In order to fasten the axial bearing 40 , it may optionally be fixed, for example in the housing 12 , on its outer circumference with at least one sealing device 44 , for example an O-ring or a piston ring seal, etc.
  • the receptacle 60 for receiving an axial bearing 40 in the turbocharger housing 12 is configured in the form of a recess or a groove, the receptacle 60 having a first receptacle section 80 in which the axial bearing disk 40 is received, and the first receptacle section 80 being configured in such a way that, or having a boundary portion such that, it opposes unwanted axial movement of the axial bearing 40 .
  • the first receptacle section 80 forms with the axial bearing 40 a clearance fit or a transition fit, for example.
  • a second receptacle section 82 of the receptacle 60 is configured in such a way that at least one disk element 79 , for example an oil barrier ring and/or a spring element, can be arranged in the receptacle 60 , for example on the shaft 30 , in order to oppose unwanted axial movement of the bearing collar 72 or of the axial bearing 40 .
  • the receptacle 60 is configured, for example, with a step, as shown in FIG. 7 , in order to form the first and second receptacle sections 80 , 82 .
  • the second receptacle section 82 forms, for example, an oil chamber or lubricant chamber in which an oil barrier ring 79 , by means of which oil or lubricant can be spun off, may be arranged.
  • the oil barrier ring 79 forms an axial bearing surface for the axial bearing 40 .
  • the fifth embodiment according to the invention has the advantage that the groove or the first receptacle section 80 allows the axial bearing arrangement 38 to be fitted to the rotor. In this case additional fastening processes, such as screw fixing processes, are likewise omitted.
  • the invention is not restricted to the aforedescribed embodiments.
  • the aforedescribed embodiments, especially individual features of the different embodiments, may be combined with one another.
  • any other radial bearing arrangement may be used to support the shaft 30 of the turbocharger.
  • the core of this invention is the axial bearing arrangement 38 .
  • any other axial bearing 40 can be used, for example an axial contactless bearing such as an axial magnetic bearing, an axial rolling bearing and/or an axial sliding bearing, etc., to mention only a few further examples of axial bearings 40 .

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
US13/509,636 2009-11-13 2010-11-04 Axial bearing arrangement for a shaft of a turbocharger Abandoned US20120269624A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102009053102.5 2009-11-13
DE102009053102A DE102009053102B4 (de) 2009-11-13 2009-11-13 Turbolader mit einer Axiallageranordnung für eine Welle des Turboladers
PCT/EP2010/066838 WO2011057949A1 (de) 2009-11-13 2010-11-04 Axiallageranordnung für eine welle eines turboladers

Publications (1)

Publication Number Publication Date
US20120269624A1 true US20120269624A1 (en) 2012-10-25

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Family Applications (1)

Application Number Title Priority Date Filing Date
US13/509,636 Abandoned US20120269624A1 (en) 2009-11-13 2010-11-04 Axial bearing arrangement for a shaft of a turbocharger

Country Status (4)

Country Link
US (1) US20120269624A1 (de)
CN (1) CN102667199B (de)
DE (1) DE102009053102B4 (de)
WO (1) WO2011057949A1 (de)

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US20140157750A1 (en) * 2011-07-28 2014-06-12 Nuovo Pignone S.P.A Turbo-compressor train with rolling bearings and related assembly method
CN105121793A (zh) * 2012-12-21 2015-12-02 诺沃皮尼奥内股份有限公司 用于轴向分离式涡轮机的密封装置
US20160047267A1 (en) * 2012-03-27 2016-02-18 Hamilton Sundstrand Corporation Ram air turbine pump leakage control
US20160186568A1 (en) * 2013-06-13 2016-06-30 Continental Automotive Gmbh Turbocharger With a Radial-Axial Turbine Wheel
US9909450B1 (en) * 2013-03-13 2018-03-06 Us Synthetic Corporation Turbine assembly including at least one superhard bearing
US20190048932A1 (en) * 2017-08-11 2019-02-14 Garrett Transportation I Inc. Turbocharger with gas and liquid flow paths
WO2019092929A1 (ja) * 2017-11-10 2019-05-16 三菱重工業株式会社 過給機
US20210025325A1 (en) * 2019-07-23 2021-01-28 Transportation Ip Holdings, Llc System for a combined turbine, compressor, shroud, and bearing case for a turbocharger
JP2022520937A (ja) * 2019-02-06 2022-04-04 エービービー スウィッツァーランド リミテッド シャフトシールシステム、シャフトシールシステムを備えたターボ機械、およびシャフトをシールする方法

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DE102014211945A1 (de) * 2014-04-29 2015-10-29 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader
GB201615491D0 (en) * 2016-09-13 2016-10-26 Delta Motorsport Ltd Improvements in or relating to gas turbine generators
DE102017212821A1 (de) * 2017-07-26 2019-01-31 Robert Bosch Gmbh Turbomaschine, insbesondere für ein Brennstoffzellensystem
DE102017212815A1 (de) * 2017-07-26 2019-01-31 Robert Bosch Gmbh Turbomaschine, insbesondere für ein Brennstoffzellensystem
DE102018100937A1 (de) * 2018-01-17 2019-07-18 Man Energy Solutions Se Verschalung eines Turboladers und Turbolader
DE102018130706A1 (de) * 2018-12-03 2020-06-04 Martin Berger Abgasturbolader mit einem hydrodynamischen Gleitlager oder hydrodynamisches Gleitlager
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Cited By (23)

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US20120288367A1 (en) * 2009-11-13 2012-11-15 Continental Automotive Gmbh Turbocharger housing and tool device for machining the turbocharger housing
US9133857B2 (en) * 2009-11-13 2015-09-15 Continental Automotive Gmbh Turbocharger housing and tool device for machining the turbocharger housing
US20140157750A1 (en) * 2011-07-28 2014-06-12 Nuovo Pignone S.P.A Turbo-compressor train with rolling bearings and related assembly method
US20160047267A1 (en) * 2012-03-27 2016-02-18 Hamilton Sundstrand Corporation Ram air turbine pump leakage control
US9719367B2 (en) * 2012-03-27 2017-08-01 Hamilton Sundstrand Corporation Ram air turbine pump leakage control
CN105121793A (zh) * 2012-12-21 2015-12-02 诺沃皮尼奥内股份有限公司 用于轴向分离式涡轮机的密封装置
US20150345503A1 (en) * 2012-12-21 2015-12-03 Nuovo Pignone Srl Sealing arrangement for axially split turbomachines
JP2016500422A (ja) * 2012-12-21 2016-01-12 ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． 軸方向分割形ターボ機械の密閉構造
CN105121793B (zh) * 2012-12-21 2018-12-25 诺沃皮尼奥内股份有限公司 用于轴向分离式涡轮机的密封装置
US9810233B2 (en) * 2012-12-21 2017-11-07 Nuovo Pignone Srl Sealing arrangement for axially split turbomachines
US9909450B1 (en) * 2013-03-13 2018-03-06 Us Synthetic Corporation Turbine assembly including at least one superhard bearing
US10408086B1 (en) 2013-03-13 2019-09-10 Us Synthetic Corporation Turbine assembly including at least one superhard bearing
US10968773B1 (en) 2013-03-13 2021-04-06 Us Synthetic Corporation Turbine assembly including at least one superhard bearing
US20160186568A1 (en) * 2013-06-13 2016-06-30 Continental Automotive Gmbh Turbocharger With a Radial-Axial Turbine Wheel
US10190415B2 (en) * 2013-06-13 2019-01-29 Continental Automotive Gmbh Turbocharger with a radial-axial turbine wheel
US20190048932A1 (en) * 2017-08-11 2019-02-14 Garrett Transportation I Inc. Turbocharger with gas and liquid flow paths
US10502263B2 (en) * 2017-08-11 2019-12-10 Garrett Transportation I Inc. Turbocharger with gas and liquid flow paths
WO2019092929A1 (ja) * 2017-11-10 2019-05-16 三菱重工業株式会社 過給機
JP2019090336A (ja) * 2017-11-10 2019-06-13 三菱重工業株式会社 過給機
JP2022520937A (ja) * 2019-02-06 2022-04-04 エービービー スウィッツァーランド リミテッド シャフトシールシステム、シャフトシールシステムを備えたターボ機械、およびシャフトをシールする方法
US20220106893A1 (en) * 2019-02-06 2022-04-07 Abb Switzerland Ltd. Shaft Seal System, Turbomachine with Shaft Seal System, and Method of Sealing a Shaft
US20210025325A1 (en) * 2019-07-23 2021-01-28 Transportation Ip Holdings, Llc System for a combined turbine, compressor, shroud, and bearing case for a turbocharger
US11761379B2 (en) * 2019-07-23 2023-09-19 Transportation Ip Holdings, Llc System for a combined turbine, compressor, shroud, and bearing case for a turbocharger

Also Published As

Publication number Publication date
DE102009053102A1 (de) 2011-05-19
CN102667199B (zh) 2015-04-01
CN102667199A (zh) 2012-09-12
DE102009053102B4 (de) 2013-03-28
WO2011057949A1 (de) 2011-05-19

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