USRE47973E1 - Turbocharger - Google Patents

Turbocharger Download PDF

Info

Publication number
USRE47973E1
USRE47973E1 US15/831,660 US201215831660A USRE47973E US RE47973 E1 USRE47973 E1 US RE47973E1 US 201215831660 A US201215831660 A US 201215831660A US RE47973 E USRE47973 E US RE47973E
Authority
US
United States
Prior art keywords
blade
base wall
lever head
adjusting ring
stop
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.)
Active, expires
Application number
US15/831,660
Inventor
Thomas Ramb
Dietmar Metz
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.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
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 BorgWarner Inc filed Critical BorgWarner Inc
Priority to US15/831,660 priority Critical patent/USRE47973E1/en
Assigned to BORGWARNER INC. reassignment BORGWARNER INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: RAMB, THOMAS, METZ, DIETMAR
Application granted granted Critical
Publication of USRE47973E1 publication Critical patent/USRE47973E1/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12Control of the pumps
    • F02B37/24Control of the pumps by using pumps or turbines with adjustable guide vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00Application
    • F05D2220/40Application in turbochargers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/50Kinematic linkage, i.e. transmission of position
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/60Fluid transfer
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00Road transport of goods or passengers
    • Y02T10/10Internal combustion engine [ICE] based vehicles
    • Y02T10/12Improving ICE efficiencies
    • Y02T10/144

Definitions

  • the invention relates to an exhaust-gas turbocharger.
  • a turbocharger of said type is known from EP 1 564 380 A1.
  • a stop be provided which is integrally connected to the adjusting ring and which is composed of a web, the width of which may be varied or which may be provided with an adjustable headless screw.
  • Said design duly yields, to a certain extent, the facility of an adjustable stop, but a stop constructed in this way would barely be feasible in practice because the spatial conditions would impede the insertion of a headless screw, which would moreover necessitate the provision of an internal thread in the integral stop part, and furthermore a locking facility for the headless screw would have to be provided in order to be able fix the position which has been set. This involves a high level of outlay owing to the extremely restricted spatial conditions in reality, and is therefore undesirable.
  • turbocharger which turbocharger permits a simplification of the assembly of the guide grate or guide apparatus, wherein at least a simple and precise setting of the minimum throughflow should be possible by means of the guide apparatus alone.
  • the guide blade position in the cartridge or the guide grate is realized by means of an inner stop between the adjusting ring and the blade lever or blade lever head. It is thereby possible for in each case one stop to be provided for the smallest blade position and preferably the largest blade position, without the need for additional components.
  • FIG. 1 shows a sectional perspective illustration of the basic design of a turbocharger according to the invention
  • FIG. 2 shows a plan view of the guide grate according to the invention
  • FIGS. 3-5 show detail views of the guide grate in different guide blade positions.
  • FIG. 1 illustrates a turbocharger 1 according to the invention which has a turbine housing 2 and a compressor housing 3 which is connected to said turbine housing via a bearing housing 19 .
  • the housings 2 , 3 and 19 are arranged along an axis of rotation R.
  • the turbine housing 2 is shown partially in section in order to illustrate the arrangement of a blade bearing ring 6 as part of a radially outer guide grate 18 which has a multiplicity of guide blades 7 which are distributed over the circumference and which have pivot shafts or blade shafts 8 .
  • nozzle cross sections are formed which, depending on the position of the guide blades 7 , become larger or smaller and supply a greater or lesser amount of the exhaust gas of an engine, which is supplied via a supply duct 9 and discharged via a central connecting piece 10 , to the turbine wheel 4 which is mounted in the center on the axis of rotation R, in order, by means of the turbine wheel 4 , to drive a compressor wheel 17 which is seated on the same shaft.
  • an actuating device 11 is provided.
  • Said actuating device may be of any desired form, but a preferred embodiment has a control housing 12 which controls the control movement of a plunger rod 14 fastened thereto in order to transmit the movement thereof to an adjusting ring 5 situated behind the blade bearing ring 6 , said movement being converted into a slight rotational movement of said adjusting ring.
  • a free space 13 for the guide blades 7 .
  • the blade bearing ring 6 has integrally formed spacers 16 .
  • three spacers 16 are arranged on the circumference of the blade bearing ring 6 at angular intervals of in each case 120°. It is however possible in principle for more or fewer such spacers 16 to be provided.
  • FIG. 2 shows a plan view of the guide grate 18 according to the invention, the blade bearing ring 6 , the guide blades 7 with the blade shafts 8 thereof, the adjusting ring 5 and the blade levers 20 with the lever heads 23 thereof, wherein in each case two blade levers 20 with lever heads 23 have been illustrated by way of example and representatively of all other arrangements.
  • the detail denoted in FIG. 2 by the letter “X” is reproduced in FIGS. 3 to 5 in different guide blade positions in each case. Accordingly, in each case only one cutout of the guide grate 18 is illustrated.
  • FIG. 3 shows an intermediate position ST M of the guide blades 7 .
  • FIG. 3 shows that the substantially semi-circular lever head 23 has a wall surface 27 which points toward a base surface 26 of the engagement recess 24 .
  • the intermediate blade position ST M shown in FIG. 3 there is play S between said wall surface 27 and the base wall 26 , as can be seen in detail from the illustration of FIG. 3 .
  • FIG. 4 shows the closed position ST G of the guide blades 7 .
  • the blade lever 20 pivots with its lever head 23 through an angle ⁇ , which may be approximately 25°, to the left.
  • which may be approximately 25°
  • the play S decreases to a value 0, as indicated in FIG. 4 .
  • the wall surface 27 bears against a first support point 25 of the base wall 26 , such that the support point 25 forms the stop (in this case the minimum stop).
  • FIG. 5 which shows the open blade position ST O , the blade lever 20 pivots about the central point M 8 of the blade shaft 8 through an angle ⁇ to the right, and contact occurs at a second support point 28 which is likewise situated on the base wall 26 and with which the wall surface 27 makes contact in said position as a maximum stop.
  • the two support points 25 and 28 are arranged symmetrically with respect to a radius line R which runs through the central point M 8 of the blade shaft 8 and which extends from the central point M 18 of the guide grate 18 .
  • the radius line R corresponds to the longitudinal central line of the blade lever 20 .
  • each blade lever has its end stop at the inner stop with respect to the adjusting ring at a maximum but also equal angle deflection.
  • the operating principle is the same both for the minimum stop and also for the maximum stop.
  • both end positions have the advantage that the guide blades come to rest in a very precise end position.
  • the solution according to the invention yields, for the minimum stop, a very precise, uniform duct formation with a correspondingly precise throughput characteristic value, which in turn is important for diesel engines.
  • the design according to the invention yields the advantage that at least one component, and therefore a number of machining processes on the blade bearing ring, and the associated assembly of such an additional component, can be eliminated. This yields not only a simplification of the design for the same technical effectiveness but also a cost advantage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Abstract

A turbocharger (1) with variable turbine geometry (VTG) having a guide grate (18) which surrounds a turbine wheel (4) radially at the outside, which has an adjusting ring (5) operatively connected to the guide blades (7) via associated blade levers (20) which are fastened to blade shafts (8) at one of the ends thereof. Each blade lever (20) has a lever head (23) which can be placed in engagement with an associated engagement recess (24), which has a base wall (26), of the adjusting ring (5), and which has a stop (25) at least for setting the minimum throughflow through the nozzle cross sections formed by the guide blades (7). The stop is a first support point (25) on the base wall (26), wherein, in the minimum throughflow position, the lever head (23) makes contact, via a wall surface (27) facing toward the base wall (26), with said first support point.

Description

The invention relates to an exhaust-gas turbocharger.
A turbocharger of said type is known from EP 1 564 380 A1. To prevent weakening of the adjusting ring, said document proposes that a stop be provided which is integrally connected to the adjusting ring and which is composed of a web, the width of which may be varied or which may be provided with an adjustable headless screw. Said design duly yields, to a certain extent, the facility of an adjustable stop, but a stop constructed in this way would barely be feasible in practice because the spatial conditions would impede the insertion of a headless screw, which would moreover necessitate the provision of an internal thread in the integral stop part, and furthermore a locking facility for the headless screw would have to be provided in order to be able fix the position which has been set. This involves a high level of outlay owing to the extremely restricted spatial conditions in reality, and is therefore undesirable.
However, in the known turbocharger, as a result of the integral formation of the stop on the adjusting ring, it is possible only with relatively high outlay, if at all, to rework the projection of the stop after the assembly of the guide grate, for example if a correction of the end positions of the guide grate must be performed.
It is therefore an object of the present invention to provide a turbocharger, which turbocharger permits a simplification of the assembly of the guide grate or guide apparatus, wherein at least a simple and precise setting of the minimum throughflow should be possible by means of the guide apparatus alone.
According to the invention, it is consequently possible for the guide blade position in the cartridge or the guide grate to be realized by means of an inner stop between the adjusting ring and the blade lever or blade lever head. It is thereby possible for in each case one stop to be provided for the smallest blade position and preferably the largest blade position, without the need for additional components.
Further details, features and advantages of the invention will emerge from the following description of an exemplary embodiment on the basis of the drawing, in which:
FIG. 1 shows a sectional perspective illustration of the basic design of a turbocharger according to the invention,
FIG. 2 shows a plan view of the guide grate according to the invention, and
FIGS. 3-5 show detail views of the guide grate in different guide blade positions.
FIG. 1 illustrates a turbocharger 1 according to the invention which has a turbine housing 2 and a compressor housing 3 which is connected to said turbine housing via a bearing housing 19. The housings 2, 3 and 19 are arranged along an axis of rotation R. The turbine housing 2 is shown partially in section in order to illustrate the arrangement of a blade bearing ring 6 as part of a radially outer guide grate 18 which has a multiplicity of guide blades 7 which are distributed over the circumference and which have pivot shafts or blade shafts 8. In this way, nozzle cross sections are formed which, depending on the position of the guide blades 7, become larger or smaller and supply a greater or lesser amount of the exhaust gas of an engine, which is supplied via a supply duct 9 and discharged via a central connecting piece 10, to the turbine wheel 4 which is mounted in the center on the axis of rotation R, in order, by means of the turbine wheel 4, to drive a compressor wheel 17 which is seated on the same shaft.
To control the movement or the position of the guide blades 7, an actuating device 11 is provided. Said actuating device may be of any desired form, but a preferred embodiment has a control housing 12 which controls the control movement of a plunger rod 14 fastened thereto in order to transmit the movement thereof to an adjusting ring 5 situated behind the blade bearing ring 6, said movement being converted into a slight rotational movement of said adjusting ring. Between the blade bearing ring 6 and an annular part 15 of the turbine housing 2 there is formed a free space 13 for the guide blades 7. To be able to safeguard said free space 13, the blade bearing ring 6 has integrally formed spacers 16. In the example, three spacers 16 are arranged on the circumference of the blade bearing ring 6 at angular intervals of in each case 120°. It is however possible in principle for more or fewer such spacers 16 to be provided.
FIG. 2 shows a plan view of the guide grate 18 according to the invention, the blade bearing ring 6, the guide blades 7 with the blade shafts 8 thereof, the adjusting ring 5 and the blade levers 20 with the lever heads 23 thereof, wherein in each case two blade levers 20 with lever heads 23 have been illustrated by way of example and representatively of all other arrangements. The detail denoted in FIG. 2 by the letter “X” is reproduced in FIGS. 3 to 5 in different guide blade positions in each case. Accordingly, in each case only one cutout of the guide grate 18 is illustrated.
FIG. 3 shows an intermediate position STM of the guide blades 7. FIG. 3 shows that the substantially semi-circular lever head 23 has a wall surface 27 which points toward a base surface 26 of the engagement recess 24. In the intermediate blade position STM shown in FIG. 3, there is play S between said wall surface 27 and the base wall 26, as can be seen in detail from the illustration of FIG. 3.
By contrast, FIG. 4 shows the closed position STG of the guide blades 7. Here, in the illustration selected in FIG. 4, the blade lever 20 pivots with its lever head 23 through an angle α, which may be approximately 25°, to the left. In said position, the play S decreases to a value 0, as indicated in FIG. 4. In said position, the wall surface 27 bears against a first support point 25 of the base wall 26, such that the support point 25 forms the stop (in this case the minimum stop).
In FIG. 5, which shows the open blade position STO, the blade lever 20 pivots about the central point M8 of the blade shaft 8 through an angle β to the right, and contact occurs at a second support point 28 which is likewise situated on the base wall 26 and with which the wall surface 27 makes contact in said position as a maximum stop.
The two support points 25 and 28 are arranged symmetrically with respect to a radius line R which runs through the central point M8 of the blade shaft 8 and which extends from the central point M18 of the guide grate 18. In the intermediate blade position illustrated in FIG. 3, the radius line R corresponds to the longitudinal central line of the blade lever 20.
Said arrangement yields in particular the advantage that a defined stop can be formed both for the minimum position and also for the maximum position without the need for additional components to be manufactured and assembled. Each blade lever has its end stop at the inner stop with respect to the adjusting ring at a maximum but also equal angle deflection. As explained on the basis of FIGS. 3 to 5, the operating principle is the same both for the minimum stop and also for the maximum stop. Here, both end positions have the advantage that the guide blades come to rest in a very precise end position.
For the maximum stop, this means a very precise inner circle at the blade ends, which is important in particular for variable turbine geometry exhaust-gas turbochargers which are used for spark-ignition engines.
The solution according to the invention yields, for the minimum stop, a very precise, uniform duct formation with a correspondingly precise throughput characteristic value, which in turn is important for diesel engines.
Furthermore, as stated, the design according to the invention yields the advantage that at least one component, and therefore a number of machining processes on the blade bearing ring, and the associated assembly of such an additional component, can be eliminated. This yields not only a simplification of the design for the same technical effectiveness but also a cost advantage.
In addition to the above written disclosure of the invention, reference is hereby explicitly made to the diagrammatic disclosure thereof in FIGS. 1 to 5.
LIST OF REFERENCE SYMBOLS
  • 1 Turbocharger
  • 2 Turbine housing
  • 3 Compressor housing
  • 4 Turbine wheel
  • 5 Adjusting ring
  • 6 Blade bearing ring
  • 7 Guide blades
  • 8 Blade shaft
  • 8H Blade shaft assigned to the lever head 23
  • 9 Supply duct
  • 10 Axial connecting piece
  • 11 Actuating device
  • 12 Control housing
  • 13 Free space for guide blades 7
  • 14 Plunger element
  • 15 Annular part of the turbine housing 2
  • 16 Spacer/Spacer cam
  • 17 Compressor wheel
  • 18 Guide grate/Guide apparatus (VTG)
  • 19 Bearing housing
  • 20 Blade lever
  • 21 Fastening ring
  • 22 Recess
  • 23 Lever head
  • 24 Engagement recesses
  • 25, 28 Stop (support point)
  • 26 Base wall
  • 27 Wall surface
  • R Radius lines
  • M8 Central point of the blade shaft
  • M18 Central point of the guide grate

Claims (5)

The invention claimed is:
1. A turbocharger (1) with variable turbine geometry (VTG) having
a turbine housing (2) with a supply duct (9) for exhaust gases;
a turbine wheel (4) which is mounted rotatably in the turbine housing (2); and
a guide grate (18)
which surrounds the turbine wheel (4) radially at the outside,
which has a blade bearing ring (6),
which has a multiplicity of guide blades (7) which have in each case one blade shaft (8) mounted in the blade bearing ring (6),
which has an a rotatable adjusting ring (5) operatively connected to the guide blades (7) via associated blade levers (20) which are fastened to the blade shafts (8) at one of the ends thereof, wherein each blade lever (20) has, at the other end, a lever head (23) which can be placed in engagement with an associated engagement recess (24), in the adjusting ring (5), which engagement recess (24) has a base wall (26), of the adjusting ring (5), and
which has a minimum stop (25) at least for setting the minimum throughflow through the nozzle cross sections formed by the guide blades (7),
wherein the minimum stop is a minimum stop support point (25) on the base wall (26) of the engagement recess, wherein, in the minimum throughflow position, the lever head (23) makes contact, via a lever head wall surface (27) facing toward the base wall (26), with said minimum stop support point (25) so that the adjusting ring (5) is stopped from further rotating past the minimum stop by the contact between lever head wall surface (27) of the lever head (23) and the base wall (26) of the engagement recess of the adjusting ring (5).
2. The turbocharger as claimed in claim 1 wherein a further stop in the form of a second support point (28) on the base wall (26) is provided, wherein in a maximum throughflow position, the lever head (23) makes contact, via the wall surface (27) facing toward the base wall (26), with said second support point.
3. The turbocharger as claimed in claim 2, wherein the first and second support points (25, 28) are arranged symmetrically with respect to a radius line (R) running through a central point (M8) of the blade shaft (8H) which is assigned to the lever head (23).
4. The turbocharger as claimed in claim 1, wherein, in an intermediate blade position (STM), there is play (S) between the base wall (26) and the wall surface (27), which points toward said base wall (26), of the lever head (23).
5. A turbocharger (1) with variable turbine geometry (VTG) having
a turbine housing (2) with a supply duct (9) for exhaust gases;
a turbine wheel (4) which is mounted rotatably in the turbine housing (2); and
a guide grate (18)
which surrounds the turbine wheel (4) radially at the outside,
which has a blade bearing ring (6),
which has a multiplicity of guide blades (7) which have in each case one blade shaft (8) mounted in the blade bearing ring (6),
which has a rotatable adjusting ring (5) operatively connected to the guide blades (7) via associated blade levers (20) which are fastened to the blade shafts (8) at one of the ends thereof, wherein each blade lever (20) has, at the other end, a lever head (23) in engagement with an associated engagement recess (24) in the adjusting ring (5), which engagement recess (24) has a base wall (26), of the adjusting ring (5), and
which has a maximum stop at least for setting the maximum throughflow through the nozzle cross sections formed by the guide blades (7),
wherein the maximum stop is a maximum stop support point (28) on the base wall (26) of the engagement recess, wherein, in the maximum throughflow position, the lever head (23) makes contact, via a lever head wall surface (27) facing toward the base wall (26), with said maximum stop support point (28) so that the adjusting ring (5) is stopped from further rotating past the maximum stop by the contact between lever head wall surface (27) of the lever head (23) and the base wall (26) of the engagement recess of the adjusting ring (5).
US15/831,660 2011-08-08 2012-07-24 Turbocharger Active 2033-12-22 USRE47973E1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US15/831,660 USRE47973E1 (en) 2011-08-08 2012-07-24 Turbocharger

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
DE102011109733 2011-08-08
DE102011109733 2011-08-08
PCT/US2012/047944 WO2013022597A1 (en) 2011-08-08 2012-07-24 Turbocharger
US14/235,538 US9506371B2 (en) 2011-08-08 2012-07-24 Turbocharger
US15/831,660 USRE47973E1 (en) 2011-08-08 2012-07-24 Turbocharger

Publications (1)

Publication Number Publication Date
USRE47973E1 true USRE47973E1 (en) 2020-05-05

Family

ID=47668797

Family Applications (2)

Application Number Title Priority Date Filing Date
US14/235,538 Ceased US9506371B2 (en) 2011-08-08 2012-07-24 Turbocharger
US15/831,660 Active 2033-12-22 USRE47973E1 (en) 2011-08-08 2012-07-24 Turbocharger

Family Applications Before (1)

Application Number Title Priority Date Filing Date
US14/235,538 Ceased US9506371B2 (en) 2011-08-08 2012-07-24 Turbocharger

Country Status (6)

Country Link
US (2) US9506371B2 (en)
JP (2) JP6072795B2 (en)
KR (2) KR101967791B1 (en)
CN (2) CN103635671B (en)
DE (1) DE112012002896T5 (en)
WO (1) WO2013022597A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9506371B2 (en) * 2011-08-08 2016-11-29 Borgwarner Inc. Turbocharger
US9739166B1 (en) * 2016-08-31 2017-08-22 Borgwarner Inc. VTG internal by-pass

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4741666A (en) * 1985-12-23 1988-05-03 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Variable displacement turbocharger
US6736595B2 (en) * 2001-02-27 2004-05-18 Mitsubishi Heavy Industries, Ltd. Adjustable nozzle mechanism for variable capacity turbine and its production method
US6907733B2 (en) * 2001-11-30 2005-06-21 Komatsu Ltd. Variable turbocharger
US20080031728A1 (en) * 2006-08-07 2008-02-07 Lorrain Sausse Vane assembly and method of assembling a vane assembly for a variable-nozzle turbocharger
US7886536B2 (en) * 2004-11-30 2011-02-15 Borgwarner Inc. Exhaust-gas turbocharger, regulating device for an exhaust-gas turbocharger and vane lever for a regulating device
US20110182717A1 (en) * 2006-03-30 2011-07-28 Borgwarner Inc. Turbocharger
US8328520B2 (en) * 2006-05-19 2012-12-11 Borgwarner Inc. Turbocharger with separately formed vane lever stops
US20130180106A1 (en) * 2010-09-27 2013-07-18 Borgwarner Inc. Method for manufacturing a turbocharger
US8545173B2 (en) * 2008-02-12 2013-10-01 Honeywell International, Inc. Process for calibrating a variable-nozzle assembly of a turbocharger and a variable-nozzle assembly facilitating such process
US8668443B2 (en) * 2010-01-08 2014-03-11 Honeywell International Inc. Variable-vane assembly having unison ring guided radially by rollers and fixed members, and restrained axially by one or more fixed axial stops
US8992166B2 (en) * 2009-11-27 2015-03-31 Borgwarner Inc. Turbocharger

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH1037754A (en) * 1996-07-24 1998-02-10 Toyota Motor Corp Variable nozzle turbocharger
JP3473469B2 (en) * 1998-12-28 2003-12-02 トヨタ自動車株式会社 Turbocharger with variable nozzle vanes
JP3764653B2 (en) * 2001-02-27 2006-04-12 三菱重工業株式会社 NOZZLE OPENING REGULATION DEVICE FOR VARIABLE NOZZLE MECHANISM AND ITS MANUFACTURING METHOD
JP3809361B2 (en) * 2001-10-22 2006-08-16 トヨタ自動車株式会社 Actuator control device
EP1564380A1 (en) * 2004-02-17 2005-08-17 BorgWarner Inc. Turbine unit comprising a variable guide vane system and a unison ring
JP4976427B2 (en) * 2006-02-16 2012-07-18 ボーグワーナー インコーポレーテッド Turbocharger with adjustable guide blade, blade lever and adjustment ring for it
JP2008215259A (en) * 2007-03-06 2008-09-18 Toyota Motor Corp Variable nozzle type turbocharger
JP5107223B2 (en) * 2008-12-26 2012-12-26 三菱重工業株式会社 Variable nozzle mechanism and variable displacement exhaust turbocharger
CN201794624U (en) * 2010-03-26 2011-04-13 萍乡市德博科技发展有限公司 Compact-disc-shaped driving pneumatic-blade variable-section nozzle ring component with pulleys
US9506371B2 (en) * 2011-08-08 2016-11-29 Borgwarner Inc. Turbocharger

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4741666A (en) * 1985-12-23 1988-05-03 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Variable displacement turbocharger
US6736595B2 (en) * 2001-02-27 2004-05-18 Mitsubishi Heavy Industries, Ltd. Adjustable nozzle mechanism for variable capacity turbine and its production method
US6907733B2 (en) * 2001-11-30 2005-06-21 Komatsu Ltd. Variable turbocharger
US7886536B2 (en) * 2004-11-30 2011-02-15 Borgwarner Inc. Exhaust-gas turbocharger, regulating device for an exhaust-gas turbocharger and vane lever for a regulating device
US20110182717A1 (en) * 2006-03-30 2011-07-28 Borgwarner Inc. Turbocharger
US8328520B2 (en) * 2006-05-19 2012-12-11 Borgwarner Inc. Turbocharger with separately formed vane lever stops
US20080031728A1 (en) * 2006-08-07 2008-02-07 Lorrain Sausse Vane assembly and method of assembling a vane assembly for a variable-nozzle turbocharger
US8545173B2 (en) * 2008-02-12 2013-10-01 Honeywell International, Inc. Process for calibrating a variable-nozzle assembly of a turbocharger and a variable-nozzle assembly facilitating such process
US8992166B2 (en) * 2009-11-27 2015-03-31 Borgwarner Inc. Turbocharger
US8668443B2 (en) * 2010-01-08 2014-03-11 Honeywell International Inc. Variable-vane assembly having unison ring guided radially by rollers and fixed members, and restrained axially by one or more fixed axial stops
US20130180106A1 (en) * 2010-09-27 2013-07-18 Borgwarner Inc. Method for manufacturing a turbocharger

Also Published As

Publication number Publication date
WO2013022597A1 (en) 2013-02-14
JP6072795B2 (en) 2017-02-01
KR20140050678A (en) 2014-04-29
US9506371B2 (en) 2016-11-29
JP2014525532A (en) 2014-09-29
JP2017096289A (en) 2017-06-01
CN103635671B (en) 2016-01-20
KR101967791B1 (en) 2019-04-10
CN103635671A (en) 2014-03-12
JP6518646B2 (en) 2019-05-22
DE112012002896T5 (en) 2014-04-03
CN105484809A (en) 2016-04-13
US20140154055A1 (en) 2014-06-05
KR101895894B1 (en) 2018-09-07
CN105484809B (en) 2017-05-31
KR20180100448A (en) 2018-09-10

Similar Documents

Publication Publication Date Title
US8186944B2 (en) Turbocharger comprising adjustable guide blades, blade lever and adjusting ring therefor
US8328520B2 (en) Turbocharger with separately formed vane lever stops
JP5941917B2 (en) Manufacturing method of turbocharger
US9896957B2 (en) Exhaust-gas turbocharger
US20070231125A1 (en) Preswirl guide device
US10927699B2 (en) Variable-pitch blade control ring for a turbomachine
US9494045B2 (en) Exhaust-gas turbocharger
KR20160062034A (en) Actuating mechanism and gear driven adjustment ring for a variable geometry turbocharger
JP4812597B2 (en) Turbocharger
US8992166B2 (en) Turbocharger
US9453426B2 (en) Stator vane adjusting device of a gas turbine
USRE47973E1 (en) Turbocharger
US9988975B2 (en) Exhaust-gas turbocharger
US10648359B2 (en) System for controlling variable-setting blades for a turbine engine
US10066498B2 (en) Exhaust gas turbocharger with turbine

Legal Events

Date Code Title Description
FEPP Fee payment procedure

Free format text: ENTITY STATUS SET TO UNDISCOUNTED (ORIGINAL EVENT CODE: BIG.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

AS Assignment

Owner name: BORGWARNER INC., MICHIGAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:RAMB, THOMAS;METZ, DIETMAR;SIGNING DATES FROM 20120731 TO 20120814;REEL/FRAME:051628/0812

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 4

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 8