WO2004027218A1 - Turbocompresseur possedant un dispositif de buse variable - Google Patents

Turbocompresseur possedant un dispositif de buse variable Download PDF

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Publication number
WO2004027218A1
WO2004027218A1 PCT/IB2002/003835 IB0203835W WO2004027218A1 WO 2004027218 A1 WO2004027218 A1 WO 2004027218A1 IB 0203835 W IB0203835 W IB 0203835W WO 2004027218 A1 WO2004027218 A1 WO 2004027218A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbocharger
nozzle
floating insert
housing
insert
Prior art date
Application number
PCT/IB2002/003835
Other languages
English (en)
Inventor
Giorgio Figura
Original Assignee
Honeywell International Inc.
Lavez, Alexis
Erbs, Eric
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 Honeywell International Inc., Lavez, Alexis, Erbs, Eric filed Critical Honeywell International Inc.
Priority to AU2002334286A priority Critical patent/AU2002334286A1/en
Priority to EP02807832.7A priority patent/EP1540142B1/fr
Priority to JP2004537343A priority patent/JP2006504021A/ja
Priority to EP16196537.1A priority patent/EP3150806A1/fr
Priority to PCT/IB2002/003835 priority patent/WO2004027218A1/fr
Priority to US10/528,642 priority patent/US20060062663A1/en
Publication of WO2004027218A1 publication Critical patent/WO2004027218A1/fr

Links

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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a turbocharger with a variable nozzle device for regulating the flow of exhaust gas driving a turbine.
  • turbochargers comprising a turbine for driving a compressor impeller or the like
  • Such a control is possible by arranging a plurality of vanes in a circular manner between a nozzle ring and the exhaust housing of the turbocharger.
  • the vanes form a plurality of nozzle passages, wherein by arranging the vanes in a pivotable manner, it becomes possible to vary the throat area of the nozzle passages.
  • turbocharger arrangement comprising a vane area formed between a nozzle ring and a ring member which is axially slidable with respect to the vanes.
  • turbocharger defined in claim 1.
  • Preferable embodiments of this turbocharger are set forth in the subclaims.
  • the turbocharger comprises vanes interposed in a nozzle between a nozzle element and a floating insert supported axially slidably on the exhaust housing or turbine housing.
  • a gap between the turbine housing and the nozzle element can be kept closed at any operational condition in order to increase the overall turbine efficiency of the turbocharger and the regulation thereof, while at the same time, the risk of vane sticking is avoided.
  • the floating insert can be urged against the vanes in said nozzle by a difference in the pressure in the exhaust gas inlet and the nozzle and/or by a biasing member supported on the exhaust housing.
  • biasing member a spring washer can be used which is placed preferably in a recess formed in the gas outlet or shroud portion of the turbine housing.
  • the biasing member can also be interposed in a recess formed in the floating insert.
  • the floating insert is formed preferably of a sheet metal and has a C-shaped cross-section with the open portion facing the turbine housing.
  • the space or recess formed between the insert and the turbine housing is communicated to the exhaust gas inlet of said exhaust housing preferably by cut-out portions in the insert.
  • variable nozzle device For mounting the variable nozzle device, its nozzle element carrying a vane pivoting mechanism is preferably clamped between a step portion of an inner periphery of the turbine and a discshaped member supported on the center housing.
  • the nozzle ring is abutted against the turbine housing by means of spacer elements passing through the floating insert and thus serving also as guiding means for guiding the movement of the floating insert.
  • a spacer element is arranged on the nozzle ring for limiting the displacement of the insert towards the vanes.
  • a piston ring can be provided between the floating insert and a gas outlet portion of the turbine housing.
  • Fig. 1 is a cross-sectional view of a part of an exhaust gas turbocharger according to a first embodiment of the invention
  • Fig. 2 is an enlarged cross-sectional view of the turbocharger shown in Fig. 1;
  • Fig. 3 is a cross-sectional view of a part of an exhaust gas turbocharger according to a second embodiment of the invention.
  • Fig. 4 is an enlarged cross-sectional view of the floating insert arrangement in the second embodiment shown in Fig. 3;
  • Fig. 5a and Fig. 5b are front and side views of the elastic spring washer used in each of the embodiments shown in Figs. 1 to 4;
  • Fig. 6 is a cross-sectional view of a part of an exhaust gas turbocharger according to a third embodiment of the invention.
  • Fig. 7a and Fig. 7b are front and cross-sectional views of a first embodiment of the floating insert used in the turbocharger according to the invention.
  • Fig. 8a and Fig. 8b are front and cross-sectional views of a second embodiment of the floating insert used in the turbocharger according to the invention.
  • Fig. 9a and Fig. 9b are front and cross-sectional views of a third embodiment of the floating insert used in the turbocharger according to the invention
  • Fig. 10 is a cross-sectional view of a fourth embodiment of the turbocharger according to the invention.
  • FIG. 11a and Fig. lib are front and cross-sectional views of the floating insert used in the fourth embodiment of the turbocharger shown in Fig. 10;
  • Fig. 12 is a cross-sectional view of a fifth embodiment of the .0 turbocharger according to the invention.
  • Fig. 1 shows a part of a turbocharger including a center housing 1 supporting a shaft 3 on which a turbine wheel 5 is mounted such that it extends within an exhaust or turbine housing 7 L5 mounted on a flange member 9 of the center housing 1 by means of fastening bolts not particularly shown in Fig. 1.
  • the exhaust housing 7 forms a generally scroll-shaped volute 11 receiving exhaust gas from an internal ⁇ 0 combustion engine. From the scroll-shaped volute 11 the exhaust gas is directed through an annular vane area forming a nozzle 13 into a turbine shroud 15 forming a portion of the turbine housing and encompassing the turbine wheel 5.
  • the nozzle 13 is formed between a ring-shaped insert 17 supported on a first
  • the nozzle ring 21 is fitted inside a second flange portion of the turbine housing by means of which the turbine housing is mounted to the center housing 1.
  • the flange portion of the turbine housing has an inner stepped opening engaging with the 0 nozzle ring 21 and urging the nozzle ring toward an elastic disc shroud 23 supported on the center housing 1 so that the nozzle ring becomes positioned in an axial direction of the turbocharger.
  • vanes 27 are associated with vane pins rotatably supported in the nozzle ring, wherein at the end of each vane pin facing the center housing 1, there is attached a vane arm 29
  • the vane arm 29 is attached to the vane pin preferably by welding, so that the length of the vane pin which is axially slidable within the nozzle ring exceeds the thickness of the nozzle ring 21 thus enabling a slight axial movement of the vanes 27 forth and back in the nozzle.
  • a unison ring 31 formed in its inner periphery.
  • the unison ring 31 is supported by means of its inner periphery on at least three rollers 33 spaced from each other in a circumferential direction, said rollers being rotatably mounted on dowels 35 secured radially
  • the rollers 33 include a peripheral groove for receiving the inner periphery of the unison ring 31.
  • the dowels 35 are secured at ⁇ 0 their two ends in holes of the flange member 9 and the nozzle ring 21 in order to prevent the nozzle ring from rotating.
  • the prevention from rotation can be achieved also by separate means with all dowels being secured only in holes of the nozzle ring, or by only one dowel extending in both the 5 flange member and the nozzle ring with the rest of the dowels extending only in holes of the nozzle ring.
  • the dowels serve as a radial support for the rollers which can rotate and slide axially on the dowels for following a rotation and/or axial distortion of the unison ring 0 under minimum friction or resistance.
  • an actuating system is used which is not particularly shown in the Figures.
  • a bell crank system described in the document US-A-4 804 316 can 5 be used.
  • the ring-shaped insert 17 is provided at its outer peripheral portion with at least one dowel pin 37 slidingly accommodated in a corresponding hole of the exhaust housing 7.
  • a circumferential recess 5 is formed in order to accommodate a piston ring 39.
  • the thickness of the insert ring 17 can be dimensioned such that there remains a small clearance between the insert ring and the
  • a spacer element 145 extending between a nozzle ring 121 and a first gas outlet portion 119 of the turbine housing 107 is arranged.
  • the spacer element 145 serves as an axial support for the nozzle ring 121 which is urged against the first portion 119 5 of the turbine housing 107 by the elastic disk shroud 123.
  • a ring-shaped insert according to one of the embodiments shown in Figs. 7a to 9b can be used in the turbocharger of the second embodiment.
  • radially cut-out portions 149 by means of which the insert 117 is slidably engaged with the 5 spacer elements 145 and prevented from rotating are provided in the periphery of the ring-shaped insert.
  • L0 is provided with axially cut-out portions 147 providing a communication of the circumferential recess 141 with the volute 111. Due to this communication, the pressure between the insert and the turbine housing becomes higher than the dynamic flow pressure within the nozzle 113 so that the pressure difference
  • L5 creates an additional force urging the insert 117 toward the vanes forming the nozzle passages.
  • the spacer elements 145 extend with their ends in both the turbine housing 107 and the nozzle ring .0 121 so that the provision of a locking element similar to the locking pin 26 used in the first embodiment shown in Fig. 2 is not necessary.
  • the third embodiment of the turbocharger according to the _5 invention shown in Fig. 6 differs from the second embodiment shown in Fig. 3 mainly in that the former spacer element 145 is replaced by a sleeve spacer 245 penetrated by a bolt 251.
  • the sleeve spacer 245 has an axial length longer than the sum of the axial thickness of the vanes 227 and the axial thickness of the 30 ring-shaped insert 217, so that a very flat elastic spring washer (not shown in Fig. 6) can be placed in the space between the ring-shaped insert 217 and the gas outlet portion 219 of the exhaust housing 207.
  • the turbocharger according to the fourth embodiment shown in Fig. 10 is almost the same as the turbocharger shown in Fig. 6, with the exception that the ring-shaped insert 317 has an L- shaped cross-section which, in co-operation with the gas outlet portion 319 of the turbine housing, forms a circumferential space 341 containing an elastic spring washer 343.
  • the piston ring 339 used in the fourth embodiment is accommodated within a recess formed in a portion of the turbine housing facing the inner periphery of the insert ring 317.
  • a substantial advantage of the invention is that the outer wall of the nozzle can be constituted by a relative small separate element which is not only exchangeable separately from the turbine housing, which as such integrally forms the volute and the outlet shroud encompassing the turbine, but is also flexibly adjustable towards the vanes, thus providing a limited clearance to the vanes and avoiding sticking hindering movement of the vanes.
  • the turbocharger according to a fifth embodiment is shown in Fig. 12.
  • the floating insert is designated with the reference sign 517.
  • the floating insert 517 is in the form of a shroud having a flange 518.
  • the flange 518 is interposed between the exhaust housing 507 and the center housing 51.
  • At least one hole is formed in the flange 518 coinciding with a corresponding hole in the center housing 51.
  • a locking pin 537 is passed through both holes so as to prevent the floating insert 517 from rotating relative to the center and exhaust housings 51, 507.
  • the flange 518 is fitted in an inner recess 541 formed in the exhaust housing 507.
  • the axial width of the flange 518 is smaller than the axial width of the inner recess 541 such that also a spring member 543 can be accommodated within the recess 541.
  • the spring member 543 axially urges the floating insert 517 towards the vanes 527.
  • the floating insert 517 is formed with a wall 516 which abuts against the vanes 527. Thereby, the vanes 527 are sandwiched between the floating insert 517 and the nozzle ring 521 by means of the spring member 543 in a floating manner in order to keep a constant nozzle width.
  • Such a construction provides a variable nozzle device which is not only arranged in a floating manner between the center housing 51 and the exhaust housing 507 but which also incorporates a nozzle ring 521 and the floating insert 517 being axially movable for floating with respect to each other, thus enabling a widening of the nozzle and therefore more efficiently avoiding sticking and binding of the vanes 527.
  • This embodiment advantageously facilitates the axial guiding of the floating insert 517 and reduces the component parts thereof.
  • the fifth embodiment may be modified as follows.
  • a modification of such a floating arrangement of the variable nozzle device can use the center housing design mentioned above, where the center housing is provided with an inner recess, with the floating insert 517 being accommodated in an axially movable manner within said recess.
  • the locking pin 537 may be attached to the exhaust housing.
  • the inner recess in the exhaust housing may be provided with an irregular inner shape matching an outer shape of the floating insert so as to prevent the floating insert from rotating relative to the exhaust housing.
  • the spring member 543 may be omitted.
  • an elastic disk shroud similar to the elastic disk shrouds 23, 123 of the preceding embodiments is used to urge the vanes 527 against the floating insert 517 via the nozzle ring 521.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Abstract

Un turbocompresseur comprend une zone d'ailettes formée entre un élément de buse (21) et un insert flottant (17) supporté sur le carter d'échappement (7), cet insert flottant (17) étant poussé contre les ailettes (27) situées dans la zone d'ailettes par un élément poussant (43). Grâce à cet agencement on améliore l'efficacité de la turbine et on évite, dans une grande mesure, le risque de collage des ailettes.
PCT/IB2002/003835 2002-09-18 2002-09-18 Turbocompresseur possedant un dispositif de buse variable WO2004027218A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
AU2002334286A AU2002334286A1 (en) 2002-09-18 2002-09-18 Turbocharger having variable nozzle device
EP02807832.7A EP1540142B1 (fr) 2002-09-18 2002-09-18 Turbocompresseur possedant un dispositif de buse variable
JP2004537343A JP2006504021A (ja) 2002-09-18 2002-09-18 可変ノズルデバイスを備えるターボ過給器
EP16196537.1A EP3150806A1 (fr) 2002-09-18 2002-09-18 Turbocompresseur avec dispositif de tuyère variable
PCT/IB2002/003835 WO2004027218A1 (fr) 2002-09-18 2002-09-18 Turbocompresseur possedant un dispositif de buse variable
US10/528,642 US20060062663A1 (en) 2002-09-18 2002-09-18 Turbocharger having variable nozzle device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2002/003835 WO2004027218A1 (fr) 2002-09-18 2002-09-18 Turbocompresseur possedant un dispositif de buse variable

Publications (1)

Publication Number Publication Date
WO2004027218A1 true WO2004027218A1 (fr) 2004-04-01

Family

ID=32012133

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2002/003835 WO2004027218A1 (fr) 2002-09-18 2002-09-18 Turbocompresseur possedant un dispositif de buse variable

Country Status (5)

Country Link
US (1) US20060062663A1 (fr)
EP (2) EP3150806A1 (fr)
JP (1) JP2006504021A (fr)
AU (1) AU2002334286A1 (fr)
WO (1) WO2004027218A1 (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1672177A1 (fr) * 2004-12-14 2006-06-21 BorgWarner Inc. Turbocompresseur
EP1707755A1 (fr) * 2005-03-08 2006-10-04 Dr.Ing. h.c.F. Porsche Aktiengesellschaft Carter de turbine d'un turbocompresseur avec une turbine à géométrie variable
DE102008039508A1 (de) 2008-08-23 2010-02-25 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
US8915704B2 (en) 2011-06-15 2014-12-23 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing ring
WO2013072294A3 (fr) * 2011-11-14 2014-12-31 Continental Automotive Gmbh Turbocompresseur à gaz d'échappement présentant une géométrie de turbine variable et une rondelle ressort d'étanchéité
US8967955B2 (en) 2011-09-26 2015-03-03 Honeywell International Inc. Turbocharger with variable nozzle having labyrinth seal for vanes
US8967956B2 (en) 2011-09-26 2015-03-03 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing arrangement
US8985943B2 (en) 2011-09-30 2015-03-24 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing arrangement
US9011089B2 (en) 2012-05-11 2015-04-21 Honeywell International Inc. Expansion seal
US9353637B2 (en) 2012-05-11 2016-05-31 Honeywell International Inc. Turbine exhaust housing
US9556880B2 (en) 2013-06-26 2017-01-31 Honeywell International Inc. Turbine exhaust seal
US9765687B2 (en) 2014-04-29 2017-09-19 Honeywell International Inc. Turbocharger with variable-vane turbine nozzle having a gas pressure-responsive vane clearance control member
US10087774B2 (en) 2014-09-29 2018-10-02 Honeywell International Inc. Turbocharger variable-vane cartridge with nozzle ring and pipe secured by two-piece self-centering spacers

Families Citing this family (19)

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Publication number Priority date Publication date Assignee Title
AU2002334286A1 (en) 2002-09-18 2004-04-08 Erbs, Eric Turbocharger having variable nozzle device
DE102004038748A1 (de) * 2004-08-10 2006-02-23 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine
JP4545068B2 (ja) * 2005-08-25 2010-09-15 三菱重工業株式会社 可変容量型排気ターボ過給機及び可変ノズル機構構成部材の製造方法
WO2007104535A1 (fr) * 2006-03-14 2007-09-20 Borgwarner Inc. Turbocompresseur
US7559199B2 (en) * 2006-09-22 2009-07-14 Honeywell International Inc. Variable-nozzle cartridge for a turbocharger
US7918023B2 (en) * 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
CN101663466A (zh) * 2007-06-26 2010-03-03 博格华纳公司 可变几何形状的涡轮增压器
DE102008000776B4 (de) * 2008-01-21 2022-04-14 BMTS Technology GmbH & Co. KG Turbine mit varialber Turbinengeometrie, insbesondere für einen Abgasturbolader, sowie Abgasturbolader
DE102008005404A1 (de) * 2008-01-21 2009-07-23 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbolader
DE102008005405B4 (de) * 2008-01-21 2021-03-04 BMTS Technology GmbH & Co. KG Turbine, insbesondere für einen Abgasturbolader, sowie Abgasturbolader
DE102008000852A1 (de) * 2008-03-27 2009-10-01 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader für ein Kraftfahrzeug
DE102008029080B4 (de) * 2008-06-19 2022-04-21 BMTS Technology GmbH & Co. KG Abgasturbolader für ein Kraftfahrzeug
US8267647B2 (en) * 2008-07-09 2012-09-18 Borgwarner Inc. Variable geometry turbocharger lower vane ring retaining system
JP5452991B2 (ja) * 2008-07-10 2014-03-26 ボーグワーナー インコーポレーテッド 段付きスペーサを有する可変ジオメトリのベーンリング組立体
DE102009058411A1 (de) * 2009-12-16 2011-06-22 BorgWarner Inc., Mich. Abgasturbolader
DE102011005151A1 (de) 2011-03-04 2012-09-06 Bayerische Motoren Werke Aktiengesellschaft Abgasturbolader für eine Brennkraftmaschine
JP5193346B2 (ja) * 2011-09-28 2013-05-08 三菱重工業株式会社 可変ノズル機構を備えた可変容量型排気ターボ過給機
CN105452738A (zh) * 2013-06-04 2016-03-30 大金工业株式会社 密封机构及涡轮冷冻机
EP3388686B1 (fr) * 2016-01-20 2020-07-15 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Machine rotative à aubes de stator

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EP1120546A2 (fr) * 2000-01-24 2001-08-01 Mitsubishi Heavy Industries, Ltd. Turbine avec capacité variable
WO2001096713A1 (fr) 2000-06-15 2001-12-20 Daimlerchrysler Ag Turbocompresseur pour moteur a combustion interne

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Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006170200A (ja) * 2004-12-14 2006-06-29 Borgwarner Inc ターボ過給機
US7600969B2 (en) 2004-12-14 2009-10-13 Borgwarner Inc. Turbocharger
KR101149083B1 (ko) * 2004-12-14 2012-05-25 보르그워너 인코퍼레이티드 터보차저
EP1672177A1 (fr) * 2004-12-14 2006-06-21 BorgWarner Inc. Turbocompresseur
EP1707755A1 (fr) * 2005-03-08 2006-10-04 Dr.Ing. h.c.F. Porsche Aktiengesellschaft Carter de turbine d'un turbocompresseur avec une turbine à géométrie variable
US7431560B2 (en) 2005-03-08 2008-10-07 Dr. Ing. H.C.F. Porsche Aktiengesellschaft Turbine housing of an exhaust gas turbocharger with adjustable turbine geometry
DE102008039508A1 (de) 2008-08-23 2010-02-25 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
US8915704B2 (en) 2011-06-15 2014-12-23 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing ring
US8967955B2 (en) 2011-09-26 2015-03-03 Honeywell International Inc. Turbocharger with variable nozzle having labyrinth seal for vanes
US8967956B2 (en) 2011-09-26 2015-03-03 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing arrangement
US8985943B2 (en) 2011-09-30 2015-03-24 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing arrangement
WO2013072294A3 (fr) * 2011-11-14 2014-12-31 Continental Automotive Gmbh Turbocompresseur à gaz d'échappement présentant une géométrie de turbine variable et une rondelle ressort d'étanchéité
US9011089B2 (en) 2012-05-11 2015-04-21 Honeywell International Inc. Expansion seal
US9353637B2 (en) 2012-05-11 2016-05-31 Honeywell International Inc. Turbine exhaust housing
US9556880B2 (en) 2013-06-26 2017-01-31 Honeywell International Inc. Turbine exhaust seal
US9765687B2 (en) 2014-04-29 2017-09-19 Honeywell International Inc. Turbocharger with variable-vane turbine nozzle having a gas pressure-responsive vane clearance control member
US10087774B2 (en) 2014-09-29 2018-10-02 Honeywell International Inc. Turbocharger variable-vane cartridge with nozzle ring and pipe secured by two-piece self-centering spacers

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AU2002334286A8 (en) 2004-04-08
EP1540142B1 (fr) 2016-11-09
US20060062663A1 (en) 2006-03-23
AU2002334286A1 (en) 2004-04-08
EP1540142A1 (fr) 2005-06-15
EP3150806A1 (fr) 2017-04-05
JP2006504021A (ja) 2006-02-02

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