WO2006046891A1 - Turbo charger unit with bearings for a rotor shaft - Google Patents

Turbo charger unit with bearings for a rotor shaft Download PDF

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Publication number
WO2006046891A1
WO2006046891A1 PCT/SE2004/001572 SE2004001572W WO2006046891A1 WO 2006046891 A1 WO2006046891 A1 WO 2006046891A1 SE 2004001572 W SE2004001572 W SE 2004001572W WO 2006046891 A1 WO2006046891 A1 WO 2006046891A1
Authority
WO
WIPO (PCT)
Prior art keywords
shaft
turbocharger unit
ring
bearing
rotor shaft
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/SE2004/001572
Other languages
French (fr)
Inventor
Kent Giselmo
Jonas Augustinson
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.)
Volvo Truck Corp
Original Assignee
Volvo Lastvagnar AB
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 Volvo Lastvagnar AB filed Critical Volvo Lastvagnar AB
Priority to JP2007538852A priority Critical patent/JP2008518158A/en
Priority to US11/576,953 priority patent/US20070214785A1/en
Priority to BRPI0419157-9A priority patent/BRPI0419157A/en
Priority to PCT/SE2004/001572 priority patent/WO2006046891A1/en
Priority to EP04793872A priority patent/EP1807632A1/en
Priority to CNA2004800443038A priority patent/CN101166913A/en
Publication of WO2006046891A1 publication Critical patent/WO2006046891A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F16C25/00—Bearings for exclusively rotary movement adjustable for wear or play
    • F16C25/06—Ball or roller 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
    • 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
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/02—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows
    • F16C19/14—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load
    • F16C19/16—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls
    • F16C19/163—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls with angular contact
    • 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
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/54—Systems consisting of a plurality of bearings with rolling friction
    • F16C19/546—Systems with spaced apart rolling bearings including at least one angular contact bearing
    • F16C19/547—Systems with spaced apart rolling bearings including at least one angular contact bearing with two angular contact rolling bearings
    • F16C19/548—Systems with spaced apart rolling bearings including at least one angular contact bearing with two angular contact rolling bearings in O-arrangement
    • 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
    • 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 present invention relates to a shaft mounting for a rotor shaft belonging to a turbocharger unit, which rotor shaft at its one end supports a turbine wheel and at its other end supports a compressor wheel and is supported in a bearing housing by means of two axially spaced bearing elements, one of which forms an axial support via a shoulder on the shaft.
  • a turbocharger unit can operate at rotation speeds up to around 200,000 r.p.m.
  • the mounting of the rotor of a turbo unit consists either of slide bearings, ball bearings or a combination of the two.
  • Ball bearings produce the lowest power loss.
  • the ball bearing application generally consists of two angular contact bearings, facing each other in a so-called O- arrangement (back-to-back arrangement) .
  • the two bearings can have a common outer ring with two elongated, separate inner rings, but can also consist of two normal angular contact bearings fitted in an outer sleeve and with a spacer sleeve between the two inner rings.
  • the rotation speed of the rotor varies especially under transient conditions, which means that axial forces are generated on the rotor shaft since the load direction is dependent on an increase or decrease in the rotation speed. If axial play is present in the mounting of the rotor shaft, the bearing life is adversely affected and there is also a risk of damage to the bearings.
  • the inner rings of the ball bearings therefore need a certain external force to ensure that the desired inner pre-load of the bearings is attained.
  • This force must not be too large, however, since there is risk of deformation of the inner rings.
  • This force is usually obtained from the nut of the compressor,
  • the axial force must be sufficient to ensure that the compressor does not slip toward the shaft, since the drive torque of the compressor is transferred by friction between the axial surfaces of the compressor and surrounding parts. This high axial force can be unsuitably high, however, for the bearing inner rings.
  • One object of the invention is therefore to produce a shaft mounting for a turbocharger unit, which allows simple adjustment of a desired bearing pre-load without risk of deformation of bearing elements.
  • a shaft mounting which according to the invention is con figured for this purpose, for a rotation shaft belonging to a turbocharger unit, which rotation shaft at its one end supports a turbine wheel and at its otJner end supports a compressor wheel and is supported in a bearing housing by means of two axially spaced bearing elements, one of which forms an axial support via a shoulder on the shaft, and is characterized according to the invention in that a discharger ring is mounted on the shaft by means of a threaded joint in such a way that the ring forms an axial support acting in the opposite axial direction against the other bearing element.
  • FIG . 1 shows in diagrammatic representation a longitudinal section thorough a two-stage turbocharger unit
  • FIG. 2 shows on a larger scale a shaft mounting used in the turbocharger unit in fig. 1
  • FIG. 3 shows a section through a discharger ring used in the shaft mounting according to fig. 2.
  • the first stage of the turbocharger unit is constituted by a high-pressure turbo unit 10, which cooperates with a series-connected low-pressure turbo unit 11.
  • Exhaust gases are conducted from an internal combustion engine (not shown) , for example a diesel engine, via separate pipe lines and worm-shaped turbine inlets 12, 13, into the turbine wheel 14 of the high-pressure turbo unit, which turbine wheel is mounted on a common shaft 15 with a compressor wheel 16.
  • the exhaust gases are conducted onward via a pipe line 17 to the turbine wheel 18 of the low-pressure turbo unit 11, which mounted on a common shaft 19 with a compressor wheel 20.
  • the exhaust gases are then conducted onward via a pipe line 21 to the exhaust system of the engine.
  • Filtered inlet air to the engine is conducted to the compressor wheel 20 of the low-pressure turbo unit 11.
  • a pipe line (not shown) conducts the inlet air onward to the compressor wheel 16 of the high-pressure turbo unit 10, from which compressor wheel the pressurized inlet air is conducted to the inlet side of the engine.
  • the shaft 15 of the high-pressure turbine is supported by means of a shaft mounting 22 and the shaft 19 of the low-pressure compressor is supported by means of a shaft mounting 23, shown in greater detail in fig. 2.
  • the shaft mounting 23 consists of two angular contact bearings 24, 25, which are mounted with their outer rings 24a, 25a inside a cylindrical sleeve 26 which is mounted with a certain play in the turbine housing. Radially inwardly directed flanges 26a on the inner side of the sleeve 26 form axial lateral supports for the outer rings.
  • the shaft 19 is inserted through the inner rings 24b, 25b of the bearings 24, 25 from the right in fig. 2, in such a way that it rests with a radially projecting shoulder portion 19a against the inner ring 25b.
  • the turbine shaft 19 is provided with an externally threaded portion 19b, which cooperates with an internally "threaded discharger ring 28, shown in section in fig. 3.
  • the discharger ring 28 comprises an inner ring portion 28a, with internal thread 28b, and an L-shaped, radially directed flange portion 29.
  • the latter is provided with radially directed ducts 29a and 29b, which are intended to drain away oil from shaft seals 30.
  • Two axial bores 31 in the flange portion 29 allow the bearing inner rings 24b, 25b to be pre-loaded by the use of a tightening tool.
  • lock fluid is used when mounting the discharger ring on the shaft 19.
  • the shaft mounting according to the invention can also be applied to the high-pressure turbo unit shown in fig. 1. If the inner rings 24b, 25b of the ball bearings are configured so as to be laterally extended one toward the other, these can rest directly one against the other, in which case the sleeve 26 becomes superfluous.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Supercharger (AREA)
  • Support Of The Bearing (AREA)
  • Rolling Contact Bearings (AREA)

Abstract

The invention relates to a turbocharger unit (10, 11) having a shaft mounting for a rotor shaft (19). The latter support at its on end a turbine wheel and at its other end a compressor wheel. The shaft is supported in a bearing housing by means of two axially spaced bearing elements (24, 25), one of which forms an axial support via a shoulder (19a) on the shaft. A desired exact bearing pre-load is attainable if a discharger ring (28) is mounted on the shaft (19) by means of a threaded joint in such a way that the ring (28) forms an axial support acting in the opposite axial direction against the other bearing element (24, 25).

Description

C20174/KS, 05—11-16
Title
Turbocharger unit with shaft mounting for a rotor shaft
TECHNICAL FIELD:
The present invention relates to a shaft mounting for a rotor shaft belonging to a turbocharger unit, which rotor shaft at its one end supports a turbine wheel and at its other end supports a compressor wheel and is supported in a bearing housing by means of two axially spaced bearing elements, one of which forms an axial support via a shoulder on the shaft.
BACKGROUND:
A turbocharger unit can operate at rotation speeds up to around 200,000 r.p.m. The mounting of the rotor of a turbo unit consists either of slide bearings, ball bearings or a combination of the two. Ball bearings produce the lowest power loss. The ball bearing application generally consists of two angular contact bearings, facing each other in a so-called O- arrangement (back-to-back arrangement) . The two bearings can have a common outer ring with two elongated, separate inner rings, but can also consist of two normal angular contact bearings fitted in an outer sleeve and with a spacer sleeve between the two inner rings.
The rotation speed of the rotor varies especially under transient conditions, which means that axial forces are generated on the rotor shaft since the load direction is dependent on an increase or decrease in the rotation speed. If axial play is present in the mounting of the rotor shaft, the bearing life is adversely affected and there is also a risk of damage to the bearings.
The inner rings of the ball bearings therefore need a certain external force to ensure that the desired inner pre-load of the bearings is attained. This force must not be too large, however, since there is risk of deformation of the inner rings. This force is usually obtained from the nut of the compressor, The axial force must be sufficient to ensure that the compressor does not slip toward the shaft, since the drive torque of the compressor is transferred by friction between the axial surfaces of the compressor and surrounding parts. This high axial force can be unsuitably high, however, for the bearing inner rings.
SUMMARY OF THE INVENTION:
One object of the invention is therefore to produce a shaft mounting for a turbocharger unit, which allows simple adjustment of a desired bearing pre-load without risk of deformation of bearing elements.
A shaft mounting, which according to the invention is con figured for this purpose, for a rotation shaft belonging to a turbocharger unit, which rotation shaft at its one end supports a turbine wheel and at its otJner end supports a compressor wheel and is supported in a bearing housing by means of two axially spaced bearing elements, one of which forms an axial support via a shoulder on the shaft, and is characterized according to the invention in that a discharger ring is mounted on the shaft by means of a threaded joint in such a way that the ring forms an axial support acting in the opposite axial direction against the other bearing element.
Advantageous illustrative embodiments of the invention derive from the following independent patent claims.
BRIEF DESCRIPTION OF THE FIGURES:
The invention will be described in greater detail below with reference to illustrative embodiments shown in the appended drawings, in which: FIG . 1 shows in diagrammatic representation a longitudinal section thorough a two-stage turbocharger unit, FIG. 2 shows on a larger scale a shaft mounting used in the turbocharger unit in fig. 1, and FIG. 3 shows a section through a discharger ring used in the shaft mounting according to fig. 2.
DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS: The shaft mounting according to the invention is shown in fig. 1 applied to a two-stage turbocharger unit, but can also be used on a conventional single-stage turbo unit .
The first stage of the turbocharger unit is constituted by a high-pressure turbo unit 10, which cooperates with a series-connected low-pressure turbo unit 11. Exhaust gases are conducted from an internal combustion engine (not shown) , for example a diesel engine, via separate pipe lines and worm-shaped turbine inlets 12, 13, into the turbine wheel 14 of the high-pressure turbo unit, which turbine wheel is mounted on a common shaft 15 with a compressor wheel 16. The exhaust gases are conducted onward via a pipe line 17 to the turbine wheel 18 of the low-pressure turbo unit 11, which mounted on a common shaft 19 with a compressor wheel 20. The exhaust gases are then conducted onward via a pipe line 21 to the exhaust system of the engine.
Filtered inlet air to the engine is conducted to the compressor wheel 20 of the low-pressure turbo unit 11. A pipe line (not shown) conducts the inlet air onward to the compressor wheel 16 of the high-pressure turbo unit 10, from which compressor wheel the pressurized inlet air is conducted to the inlet side of the engine.
The shaft 15 of the high-pressure turbine is supported by means of a shaft mounting 22 and the shaft 19 of the low-pressure compressor is supported by means of a shaft mounting 23, shown in greater detail in fig. 2. The shaft mounting 23 consists of two angular contact bearings 24, 25, which are mounted with their outer rings 24a, 25a inside a cylindrical sleeve 26 which is mounted with a certain play in the turbine housing. Radially inwardly directed flanges 26a on the inner side of the sleeve 26 form axial lateral supports for the outer rings. The shaft 19 is inserted through the inner rings 24b, 25b of the bearings 24, 25 from the right in fig. 2, in such a way that it rests with a radially projecting shoulder portion 19a against the inner ring 25b. On the opposite side of the inner ring 25b rests a spacer sleeve 27, which also bears against the other inner ring 25a. The turbine shaft 19 is provided with an externally threaded portion 19b, which cooperates with an internally "threaded discharger ring 28, shown in section in fig. 3.
The discharger ring 28 comprises an inner ring portion 28a, with internal thread 28b, and an L-shaped, radially directed flange portion 29. The latter is provided with radially directed ducts 29a and 29b, which are intended to drain away oil from shaft seals 30. Two axial bores 31 in the flange portion 29 allow the bearing inner rings 24b, 25b to be pre-loaded by the use of a tightening tool. Expediently, lock fluid is used when mounting the discharger ring on the shaft 19.
The invention should not be deemed to be limited to the illustrative embodiment described above, but rather a number of further variants and modifications are conceivable within the scope of the subsequent patent claims. For example, the shaft mounting according to the invention can also be applied to the high-pressure turbo unit shown in fig. 1. If the inner rings 24b, 25b of the ball bearings are configured so as to be laterally extended one toward the other, these can rest directly one against the other, in which case the sleeve 26 becomes superfluous.

Claims

P20174/KS, 05-11-16CLAIMS
1. A turbocharger unit (10; 11) having a shaft mounting for a rotor shaft (15; 19), which rotor shaft at its one end supports a turbine wheel (14; 18) and at its other end supports a compressor wheel (16; 20) and is supported in a bearing housing by means of two axially spaced bearing elements (24, 25), one of which forms an axial support via a shoulder (19a) on the shaft, characterised in that a discharger ring (28) is mounted on the shaft (15; 19) by means of a threaded joint in such a way that the ring (28) forms an axial support, acting in the opposite axial direction against the other bearing element (24, 25) .
2. The turbocharger unit as claimed in claim 1, characterized in that the bearing elements (24, 25) bear axially one against the other via an intermediate spacer sleeve (27) .
3. The turbocharger unit as claimed in claim 1 or 2, characterized in that the discharger ring (28) is mounted on the shaft (15; 19) by torque traction to a specific tightening torque.
4. The turbocharger unit as claimed in any one of claim 1 to 3, characterized in that the threaded joint is mounted with lock fluid.
5. The turbocharger unit as claimed in any one of claims 1 to 4, characterized in that the bearing elements are constituted by ball bearings (24, 25) .
6. The turbocharger unit as claimed in claim 5, characterized in that the inner rings (24b, 25b) of the ball bearings (24, 25) are laterally extended and rest directly one against the other.
PCT/SE2004/001572 2004-10-28 2004-10-28 Turbo charger unit with bearings for a rotor shaft Ceased WO2006046891A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
JP2007538852A JP2008518158A (en) 2004-10-28 2004-10-28 Turbocharger unit with shaft attachment for rotor shaft
US11/576,953 US20070214785A1 (en) 2004-10-28 2004-10-28 Turbo Charger Unit With Bearings For A Rotor Shaft
BRPI0419157-9A BRPI0419157A (en) 2004-10-28 2004-10-28 turbocharger unit with brackets for one rotor shaft
PCT/SE2004/001572 WO2006046891A1 (en) 2004-10-28 2004-10-28 Turbo charger unit with bearings for a rotor shaft
EP04793872A EP1807632A1 (en) 2004-10-28 2004-10-28 Turbo charger unit with bearings for a rotor shaft
CNA2004800443038A CN101166913A (en) 2004-10-28 2004-10-28 Turbo charger unit with bearing for a rotor shaft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2004/001572 WO2006046891A1 (en) 2004-10-28 2004-10-28 Turbo charger unit with bearings for a rotor shaft

Publications (1)

Publication Number Publication Date
WO2006046891A1 true WO2006046891A1 (en) 2006-05-04

Family

ID=36228071

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2004/001572 Ceased WO2006046891A1 (en) 2004-10-28 2004-10-28 Turbo charger unit with bearings for a rotor shaft

Country Status (6)

Country Link
US (1) US20070214785A1 (en)
EP (1) EP1807632A1 (en)
JP (1) JP2008518158A (en)
CN (1) CN101166913A (en)
BR (1) BRPI0419157A (en)
WO (1) WO2006046891A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009133445A1 (en) * 2008-04-28 2009-11-05 Toyota Jidosha Kabushiki Kaisha Bearing device for supercharger
WO2014004245A1 (en) * 2012-06-25 2014-01-03 Borgwarner Inc. Exhaust-gas turbocharger
US9759093B2 (en) 2012-11-12 2017-09-12 Cummins Ltd. Turbomachine bearing assembly preloading arrangement
US11326473B2 (en) 2019-12-18 2022-05-10 Borgwarner Inc. Bearing assembly and turbocharger including the bearing assembly

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EP2396519B1 (en) * 2009-01-20 2017-07-12 Williams International Co., L.L.C. Turbocharger core with turbine nozzle cartridge
SE533565E (en) * 2009-03-11 2013-08-06 Scania Cv Abp Shaft device and method for storing a shaft
DE102009034012B4 (en) * 2009-07-21 2011-09-29 Aktiebolaget Skf Method and device for axially securing a machine element
DE102010019528A1 (en) * 2010-05-06 2011-11-10 Schaeffler Technologies Gmbh & Co. Kg Rolling bearing device and turbocharger with such a rolling bearing device
DE102013213023A1 (en) * 2013-07-03 2015-01-08 Continental Automotive Gmbh Rotor for a turbocharger device, turbocharger device with a rotor and shaft for such a rotor
DE102013218303A1 (en) * 2013-09-12 2015-03-12 Bosch Mahle Turbo Systems Gmbh & Co. Kg Exhaust gas turbocharger with turbine
CN104018897A (en) * 2014-06-24 2014-09-03 常州新瑞汽车配件制造有限公司 Split type high-speed rolling bearing body of turbocharger
CN110939515A (en) * 2019-11-29 2020-03-31 西安航天动力研究所 Method for expanding axial force adjusting capability of rotor shaft system
CN112648068B (en) * 2020-12-22 2022-04-05 潍柴动力股份有限公司 Supercharger state control method and device

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EP0339601A1 (en) * 1988-04-26 1989-11-02 Nissan Motor Co., Ltd. Bearing holding arrangement in supercharger
US4961654A (en) * 1989-04-10 1990-10-09 Aerojet-General Corporation Bearing assembly
US6283639B1 (en) * 1994-02-03 2001-09-04 John E. Rode Bearing assembly adjustable spacer and system for adjusting the same
US20030123768A1 (en) * 2001-10-16 2003-07-03 Woollenweber William E. Bearing system for high-speed rotating machinery

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009133445A1 (en) * 2008-04-28 2009-11-05 Toyota Jidosha Kabushiki Kaisha Bearing device for supercharger
WO2014004245A1 (en) * 2012-06-25 2014-01-03 Borgwarner Inc. Exhaust-gas turbocharger
US9759093B2 (en) 2012-11-12 2017-09-12 Cummins Ltd. Turbomachine bearing assembly preloading arrangement
US10655498B2 (en) 2012-11-12 2020-05-19 Cummins Ltd. Turbomachine bearing assembly preloading arrangement
US11326473B2 (en) 2019-12-18 2022-05-10 Borgwarner Inc. Bearing assembly and turbocharger including the bearing assembly

Also Published As

Publication number Publication date
US20070214785A1 (en) 2007-09-20
JP2008518158A (en) 2008-05-29
BRPI0419157A (en) 2007-12-11
CN101166913A (en) 2008-04-23
EP1807632A1 (en) 2007-07-18

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