US20120237339A1 - Adjustable ring - Google Patents

Adjustable ring Download PDF

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Publication number
US20120237339A1
US20120237339A1 US13/420,796 US201213420796A US2012237339A1 US 20120237339 A1 US20120237339 A1 US 20120237339A1 US 201213420796 A US201213420796 A US 201213420796A US 2012237339 A1 US2012237339 A1 US 2012237339A1
Authority
US
United States
Prior art keywords
flanks
adjusting ring
blade
ring according
blade lever
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
US13/420,796
Other languages
English (en)
Inventor
Thomas Streich
Jochen Laubender
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.)
BMTS Technology GmbH and Co KG
Original Assignee
Individual
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 Individual filed Critical Individual
Assigned to BOSCH MAHLE TURBO SYSTEMS GMBH & CO. KG reassignment BOSCH MAHLE TURBO SYSTEMS GMBH & CO. KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LAUBENDER, JOCHEN, STREICH, THOMAS
Assigned to BOSCH MAHLE TURBO SYSTEMS GMBH & CO. KG reassignment BOSCH MAHLE TURBO SYSTEMS GMBH & CO. KG CORRECTIVE ASSIGNMENT TO CORRECT THE RECEIVING PARTY'S ADDRESS, PREVIOUSLY RECORDED ON REEL 027867 FRAME 0568. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT. Assignors: LAUBENDER, JOCHEN, STREICH, THOMAS
Publication of US20120237339A1 publication Critical patent/US20120237339A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/16—Two-dimensional parabolic
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the disclosure relates to an adjusting ring for a variable turbine and/or compressor geometry.
  • the disclosure additionally relates to a variable turbine and/or compressor geometry with such an adjusting ring.
  • the disclosure relates to a charging device, in particular an exhaust gas turbocharger, having a variable turbine and/or compressor geometry of the mentioned type.
  • variable turbine and/or compressor geometry is an established technique for the power control of a charging device, in particular of an exhaust gas turbocharger, with different gas throughputs. Therefore, an adjusting ring with recesses is provided, which substantially show two parallel lateral flanks, wherein the recesses receive blade lever heads of blade levers.
  • the blade lever heads are moved through a contact with the flanks of the recesses of the adjusting ring, which results in a rotation of guide blades arranged on a blade bearing ring, which are connected to the blade levers in a rotationally fixed manner via a blade mounting pin.
  • the cross section opened by the guide blades is reduced upon high power demand through the charging device and/or low propulsion gas throughput.
  • the cross section that is available through the guide blades is increased upon low power demand through the charging device and/or high drive gas throughput.
  • a gap between the blade lever heads and the corresponding flank can develop, which results in a sluggishness of the variable turbine and/or compressor geometry.
  • an incorrect transmission of an adjusting force via the flanks to the corresponding blade lever heads for the development of a friction takes place, which likewise contributes to the sluggishness of the variable turbine and/or compressor geometry.
  • the sluggishness in particular with load changes or changes of the power demand by the charging device, leads to a delayed reaction time or a hysteresis and thus a power reduction of the charging device.
  • Generic adjusting rings are known for example from DE 10 2007 022 356 A1 and DE 10 2004 023 209 A1.
  • the present disclosure therefore deals with the problem of stating an improved embodiment for an adjusting ring of the generic type, which in particular contributes to an elimination or at least reduction of the hysteresis behaviour of the variable turbine and/or compressor geometry.
  • the present disclosure is based on the general idea of configuring the flanks of at least one recess with an adjusting ring of a variable turbine and/or compressor geometry of a charging device, wherein the adjusting ring comprises recesses directed to the inside for mounting blade lever heads of blade levers and each mount comprises two flanks, in such a manner that the blade lever heads and at least one of the flanks of the associated recesses have a contact for any positions of the associated guide blade and thus of the blade lever heads.
  • the flanks are designed in such a manner that a transmission of an adjusting force via the flanks to the corresponding blade lever heads is optimised.
  • the disclosure thereby utilises the realisation that a gap between a blade lever head and the flank of the associated clearance of the adjusting ring is caused through the parallel arrangement of the flanks of a recess with certain positions of the adjusting ring and thus of the blade lever heads.
  • a friction caused through an unfavourable transmission of the adjusting force between blade lever head and flank is in particular caused through the parallel arrangement of the flanks as well, which make possible an optimal transmission of the adjusting force only with certain adjusting positions of the adjusting ring and thus with certain positions of the blade lever head.
  • at least one flank of at least one recess has a curved shape, in particular a parabolic shape, or both flanks of a recess have a predefined deviation from a parallel arrangement.
  • the curvature angle of the for example curved flanks can in particular have a dependency on a nominal diameter of the blade lever head.
  • the curved shape of the flank in this case serves in particular for the purpose of guaranteeing a contact between blade lever head and said flank for any positions of the guide blades and thus of the blade lever head.
  • these embodiments of the flank serve for the purpose of optimising an adjusting force transmitted by the flank onto the blade lever head in such a manner that the friction between flank and blade lever head is at least reduced.
  • flanks of a recess are designed in such a manner that they have a predefined deviation from a parallel arrangement. Accordingly, the flanks are configured in such a manner that they are for example arranged obliquely to one another. Such an arrangement, too, serves in particular for the purpose of guaranteeing a contact between blade lever head and the corresponding flank/flanks for any positions of the guide blades and thus of the blade lever head.
  • this embodiment of the flanks serves for the purpose of optimising an adjusting force transmitted to the blade lever head through the flank in such a manner that the friction between flank and blade lever head is at least minimised.
  • flanks of a recess which have a deviation from a parallel arrangement, are designed in such a manner that at least one of the flanks runs in a radial plane of the adjusting ring.
  • both flanks of a recess can also lie in a radial plane.
  • a further advantageous embodiment comprises flanks of at least one recess, which are arranged in mirror image to one another.
  • flanks which are mirrored to one another with respect to a radial plane of the adjusting ring running in their middle.
  • the flanks are thus designed in particular with curved shape of the respective flanks in such a manner that the make available the same, however mirrored, mount on both sides of the associated recess.
  • a base of the recess additionally to the already mentioned embodiments has a curved shape.
  • the base can be for example rounded off in order to prevent in particular a friction of the blade lever head with the base of the associated recess.
  • the adjusting ring is integrated in a variable turbine and/or compressor geometry.
  • the blade levers are connected by blade lever pins to a blade bearing ring, wherein guide blades are coupled to the blade lever pins in a rotationally fixed manner.
  • the flanks of the adjusting ring are designed in such a manner that the associated blade lever heads are supported substantially orthogonally on the associated flank independently of the position of the adjusting ring and thus of the guide blades.
  • This orthogonal support in this case serves in particular for the purpose of achieving an optimal transmission of the adjusting force to the blade lever heads and thus to the guide blades through the adjusting ring.
  • the rotation of the adjusting ring in a variable turbine and/or compressor geometry merely runs over a few angular degrees. Accordingly, the respective flanks according to the disclosure can be designed in such a manner that they merely ensure an optimised transmission of the adjusting force between adjusting ring and blade lever head and/or a contact between blade lever head and the associated flank merely in the relevant angular range.
  • FIG. 1-4 in each case a detail of an adjusting ring according to the disclosure.
  • an adjusting ring 1 comprises at least one recess 2 , wherein the recesses 2 comprise two lateral flanks 3 , 3 ′ and a base 4 .
  • both flanks 3 , 3 ′ of the shown recess 2 have a curved shape, wherein both flanks 3 , 3 ′ show an angular transition to the adjusting ring 1 .
  • this can also be round shaped.
  • one of the flanks 3 corresponds to the mirror image of the other flank 3 ′ with respect to a mirror plane 5 running in the middle of both flanks 3 , 3 ′, which forms a radial plane of the adjusting ring 1 at the same time.
  • the base 4 of the recess 2 likewise has a curved shape, wherein the curvature angle of the flanks 3 , 3 ′ and of the base 4 differ in that the base 4 has a greater curvature.
  • FIG. 2 shows an alternative embodiment of the flanks 3 , 3 ′ of the recess 2 having an angular transition to the adjusting ring 1 .
  • the flanks 3 , 3 ′ in this case are flat and have a predefined deviation from a parallel arrangement in such a manner that they exhibit an inclination to one another and contact one another in an acute base 4 .
  • the flanks 3 , 3 ′ are furthermore designed in such a way that one of the flanks 3 corresponds to the mirror image of the other flank 3 ′ with respect to the mirror plane 5 running in the middle of both flanks 3 .
  • FIG. 3 show a further embodiment of an adjusting ring 1 according to the disclosure, whose recess 2 comprises a flat flank 3 and a curved flank 3 ′, wherein both flanks 3 , 3 ′ have an angular transition to the adjusting ring.
  • the curved flank 3 ′ in this case touches the flat flank in the base 4 of the recess 2 , by which a curved base 4 of the recess 2 is formed.
  • the transition between the adjusting ring 1 and the recess 2 is rounded off.
  • the transition to a flank 3 has a different rounding than the transition to the other flank 3 ′.
  • the flanks 3 , 3 ′ in this case are each flat, while they deviate from a parallel arrangement in such a manner that they lie on radial planes 6 which pass through the centre point 7 of the adjusting ring 1 .
  • the flat flanks 3 , 3 ′ which lie on the planes 6 , meet in a curved and rounded-off base 4 of the associated recess 2 .
  • the flanks 3 , 3 ′ are embodied furthermore in such a manner that one of the flanks 3 ′ corresponds to the mirror image of the other flank 3 with respect to a mirror plane 5 running in the middle of both flanks 3 , 3 ′.
  • flanks 3 , 3 ′ serve for the purpose of improving a transmission of an adjusting force via the flanks 3 , 3 ′ to the associated blade lever heads through the shape of the flanks 3 , 3 ′.
  • This is effected in particular in that the flanks 3 , 3 ′ are designed such that their shape and arrangement ensure a substantially orthogonal support of the associated blade lever head, independently of the position of the corresponding guide blades and thus of the blade lever head.
  • the force introduction between the lever head and the adjusting ring 1 merely takes place in circumferential direction (tangentially) of the adjusting ring 1 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
US13/420,796 2011-03-15 2012-03-15 Adjustable ring Abandoned US20120237339A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011005556A DE102011005556A1 (de) 2011-03-15 2011-03-15 Verstellring
DE102011005556.8 2011-03-15

Publications (1)

Publication Number Publication Date
US20120237339A1 true US20120237339A1 (en) 2012-09-20

Family

ID=45655447

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/420,796 Abandoned US20120237339A1 (en) 2011-03-15 2012-03-15 Adjustable ring

Country Status (3)

Country Link
US (1) US20120237339A1 (de)
EP (1) EP2500526B1 (de)
DE (1) DE102011005556A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120243973A1 (en) * 2009-12-09 2012-09-27 Kierat Jaroslaw Adjusting device for a charger, in particularly an exhaust gas turbocharger
WO2019069678A1 (ja) * 2017-10-06 2019-04-11 株式会社Ihi 可変容量機構
JPWO2020225898A1 (de) * 2019-05-09 2020-11-12

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013000499A1 (de) 2013-01-12 2014-07-17 Daimler Ag Verstelleinrichtung für einen Abgasturbolader

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2164099A (en) * 1984-06-29 1986-03-12 Ishikawajima Harima Heavy Ind Variable capacity turbochargers
EP1520959A1 (de) * 2002-04-26 2005-04-06 BorgWarner Inc. Turbokompressor mit verstellbaren Leitschaufeln
US20080118349A1 (en) * 2004-11-08 2008-05-22 Dominique Petitjean Variable Geometry Compressor
JP2008215259A (ja) * 2007-03-06 2008-09-18 Toyota Motor Corp 可変ノズル式ターボチャージャ
US20110138805A1 (en) * 2009-12-15 2011-06-16 Honeywell International Inc. Conjugate curve profiles for vane arms, main-arms, and unison rings

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3933455B2 (ja) * 2001-11-30 2007-06-20 株式会社小松製作所 可変ターボ過給機
DE10316389B3 (de) * 2003-04-10 2004-01-22 Mtu Friedrichshafen Gmbh Leiteinrichtung für einen Abgasturbolader
DE102004023209A1 (de) 2004-05-11 2005-12-08 Volkswagen Ag Abgasturbolader für eine Brennkraftmaschine mit variabler Turbinengeometrie
DE102004043928A1 (de) * 2004-09-11 2006-04-13 Ihi Charging Systems International Gmbh Stelleinrichtung für Leitschaufeln eines Abgasturboladers
DE102006048514B3 (de) * 2005-12-01 2007-05-10 Mtu Friedrichshafen Gmbh Leiteinrichtung für einen VTG-Abgasturbolader
DE102007022356A1 (de) 2007-05-12 2008-11-13 Mahle International Gmbh Ladeeinrichtung
JP4307500B2 (ja) * 2007-09-21 2009-08-05 株式会社豊田自動織機 可変ノズル機構付きターボチャージャ
DE102009032452A1 (de) * 2009-07-09 2011-01-13 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
KR101144515B1 (ko) * 2009-10-27 2012-05-11 현대자동차주식회사 가변 지오메트리 터보차져의 노즐어셈블리

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2164099A (en) * 1984-06-29 1986-03-12 Ishikawajima Harima Heavy Ind Variable capacity turbochargers
EP1520959A1 (de) * 2002-04-26 2005-04-06 BorgWarner Inc. Turbokompressor mit verstellbaren Leitschaufeln
US20080118349A1 (en) * 2004-11-08 2008-05-22 Dominique Petitjean Variable Geometry Compressor
JP2008215259A (ja) * 2007-03-06 2008-09-18 Toyota Motor Corp 可変ノズル式ターボチャージャ
US20110138805A1 (en) * 2009-12-15 2011-06-16 Honeywell International Inc. Conjugate curve profiles for vane arms, main-arms, and unison rings

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
EP1520959 Machine Translation. Accessed EPO website on July 18, 2016. *
JP 2008-215259 Machine Translation. Accessed JPO website on July 18, 2016. *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120243973A1 (en) * 2009-12-09 2012-09-27 Kierat Jaroslaw Adjusting device for a charger, in particularly an exhaust gas turbocharger
US9022729B2 (en) * 2009-12-09 2015-05-05 Ihi Charging Systems International Gmbh Adjusting device for a charger, in particularly an exhaust gas turbocharger
WO2019069678A1 (ja) * 2017-10-06 2019-04-11 株式会社Ihi 可変容量機構
JPWO2020225898A1 (de) * 2019-05-09 2020-11-12
WO2020225898A1 (ja) * 2019-05-09 2020-11-12 三菱重工エンジン＆ターボチャージャ株式会社 可変容量型排気ターボ過給機
JP7217345B2 (ja) 2019-05-09 2023-02-02 三菱重工エンジン＆ターボチャージャ株式会社 可変容量型排気ターボ過給機

Also Published As

Publication number Publication date
EP2500526A1 (de) 2012-09-19
EP2500526B1 (de) 2015-04-08
DE102011005556A1 (de) 2012-09-20

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Legal Events

Date Code Title Description
AS Assignment

Owner name: BOSCH MAHLE TURBO SYSTEMS GMBH & CO. KG, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:STREICH, THOMAS;LAUBENDER, JOCHEN;REEL/FRAME:027867/0568

Effective date: 20120228

AS Assignment

Owner name: BOSCH MAHLE TURBO SYSTEMS GMBH & CO. KG, GERMANY

Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE RECEIVING PARTY'S ADDRESS, PREVIOUSLY RECORDED ON REEL 027867 FRAME 0568. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT;ASSIGNORS:STREICH, THOMAS;LAUBENDER, JOCHEN;REEL/FRAME:028123/0493

Effective date: 20120228

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION