EP1631736A1 - Turbine a gaz d'echappement pour turbocompresseur a gaz d'echappement - Google Patents

Turbine a gaz d'echappement pour turbocompresseur a gaz d'echappement

Info

Publication number
EP1631736A1
EP1631736A1 EP04729870A EP04729870A EP1631736A1 EP 1631736 A1 EP1631736 A1 EP 1631736A1 EP 04729870 A EP04729870 A EP 04729870A EP 04729870 A EP04729870 A EP 04729870A EP 1631736 A1 EP1631736 A1 EP 1631736A1
Authority
EP
European Patent Office
Prior art keywords
exhaust gas
gas turbine
turbine according
housing
base plate
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.)
Granted
Application number
EP04729870A
Other languages
German (de)
English (en)
Other versions
EP1631736B1 (fr
Inventor
Hermann Burmester
Akihiro Ohkita
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.)
IHI Charging Systems International GmbH
Original Assignee
IHI Charging Systems International GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by IHI Charging Systems International GmbH filed Critical IHI Charging Systems International GmbH
Publication of EP1631736A1 publication Critical patent/EP1631736A1/fr
Application granted granted Critical
Publication of EP1631736B1 publication Critical patent/EP1631736B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the invention relates to an exhaust gas turbine for an exhaust gas turbocharger according to the preamble of claim 1.
  • an exhaust gas turbine for an exhaust gas turbocharger in which a spiral housing made of sheet metal is firmly connected on the one hand to a contour sleeve and on the other hand is clamped to a central bearing housing of the turbine via an intermediate ring by means of a tensioning band.
  • the intermediate ring can be formed in one piece with the contour sleeve or form a separate component.
  • the spiral housing is composed of two sheet metal shells, one of which forms the channel wall of the spiral channel which faces the diffuser, while the other shell forms the channel wall of the spiral channel which faces outwards.
  • the shell facing outwards can be surrounded by another shell with an air gap for thermal insulation.
  • the volute casing is designed to be complicated and is therefore complex to manufacture and assemble. Furthermore, it has a considerable weight and, in particular, does not allow any compensation for different thermal expansions of the individual housing parts to one another without significant thermal stresses occurring. Such thermal stresses can lead to malfunctions and result in premature wear.
  • the adjustment mechanism for the guide vanes, a bearing ring for the guide vanes, the contour sleeve and the guide vanes themselves can form a preassembled unit. From DE 100 22 052 AI a turbine housing for an exhaust gas turbocharger is known in which the spiral housing is double-walled.
  • the inner wall, which forms the spiral channel adjoins an inlet flange via an inlet funnel that opens tangentially into the spiral housing.
  • the outer wall is welded to the inlet flange, while the inner wall has a sliding fit to the outer wall and the inlet flange, so that thermal expansions in the direction of the inlet funnel between the inner and outer walls do not generate any thermal stresses.
  • the invention is based on the object of designing an exhaust gas turbine with a double-shell turbine housing made of sheet metal in such a way that the parts are simple and light and generate the lowest possible stresses under the influence of heat. It is solved according to the invention by the features of claim 1. Further advantageous embodiments result from the subclaims.
  • the spiral housing and the outer shell are cup-shaped.
  • the outer shell can be made largely cylindrical, while the spiral housing forms a spiral channel in accordance with the requirements of the desired flow conditions, the flow cross section of which tapers towards a diffuser.
  • the spiral housing and the outer shell are delimited on the end face facing the diffuser by parts of the diffuser which comprises a contour sleeve, a bearing ring and an intermediate ring.
  • One in cross Section V-shaped clamping ring clamps the outer shell over the intermediate ring with a central bearing housing of the exhaust gas turbocharger, while the inner spiral housing connects to part of the guide apparatus, for example to the intermediate ring or the bearing ring, via at least one axially flexible element.
  • the spiral housing can expand in the axial and radial direction under the influence of heat without exerting any significant stresses on the adjacent parts of the diffuser or on the outer shell.
  • the resilient element can be formed in a simple manner by a corrugated tube-like part of the spiral housing which is molded directly onto the spiral housing during manufacture and expediently has a smaller wall thickness than the rest of the spiral housing.
  • the resilient element consists of a sliding seat which is provided between a part of the diffuser and the spiral housing.
  • an intermediate ring or the bearing ring of the guide apparatus expediently has a shoulder, against which a preferably cylindrical connection of the volute housing rests and forms a sliding seat. The difference in diameter between a cylindrical connection and the radial boundary of the spiral channel is bridged by a radially directed, integrally formed transition.
  • connection point in addition to the sliding seat with a heat-resistant sealing element, e.g. in the form of a bead that is molded onto the connection of the volute casing and rests on the shoulder.
  • the guide apparatus comprises a contour sleeve and a bearing ring for adjustable guide vanes, which by Spacer bolts are connected to one another and form a flow channel which adjoins a spiral channel formed by the spiral housing.
  • the bearing ring is fastened to an intermediate ring which is braced on an outward-pointing outer flange together with a flange of the outer shell by a tension ring with an adjacent housing part of the exhaust gas turbocharger.
  • the bearing ring or the bearing ring and the intermediate ring form the end boundary of the spiral channel, so that the number of components required, the cost of materials and the weight are very low.
  • the radially inner part of the volute casing is expediently connected to the contour sleeve via a base plate.
  • the base plate which can be molded directly onto the spiral housing or is sealed by a separate seal, also serves to seal the spiral housing from the contour sleeve. This can be done on the one hand in the axial direction or in the radial direction by a correspondingly acting clamping ring which presses the base plate in the corresponding radial or axial direction against the contour sleeve.
  • an additional seal can be provided between the base plate and the contour sleeve.
  • FIG. 1 shows a half longitudinal section through an exhaust gas turbine without an impeller
  • FIG. 2 shows a variant of FIG. 1
  • FIG. 3 shows an end view of an exhaust gas turbine according to FIG.
  • FIG. 4 is a view in the direction of an arrow IV in FIG.
  • the exhaust gas turbine 10 comprises a contour sleeve 13, which is connected via spacer bolts 14 to a bearing ring 17 for adjustable guide vanes, not shown.
  • the spacer bolts 14, of which several are distributed over the circumference, have stops 15, against which the contour sleeve 13 or the bearing ring 17 abut and are held at the end of the spacer bolt 14 by a rivet head 16.
  • a flow channel 30 is formed, which leads to a radially inner impeller, not shown, and in which the guide vanes are arranged distributed over the circumference.
  • the bearing ring 17 is fastened to an intermediate ring 18, which has an outer conical flange 19 by means of a clamping ring 24 with a V-shaped cross section in a known manner is clamped against a central bearing housing, not shown, of the exhaust gas turbine. 1, the intermediate ring 18 is directly attached to the bearing ring 17 with its inner radial flange 20, in the embodiment according to FIG.
  • the bearing ring 17 is connected via a support plate ring 25 to a flange contour 38 of the bearing housing 37 (only indicated), in that an inner flange 26 of the support plate ring 25 is fastened to the bearing ring 17, and an outer flange 27 of the support plate ring 25 is braced by the clamping ring 24 with a suitable flange contour 38 of the bearing housing 37.
  • the support plate ring 25 is resilient and thus compensates for thermal expansion between the diffuser 13, 14, 17 and the housing of the turbocharger.
  • the flow channel 30 is surrounded radially on the outside by a spiral channel 12 through which exhaust gas is supplied.
  • its flow cross section narrows continuously from a tangentially opening inlet funnel 41 to the flow channel 30, which results in a spiral shape of the spiral housing 11, which essentially forms the spiral channel 12.
  • the narrowing of the cross section of the spiral channel 12 is indicated by a number of dashed sections of the spiral housing which form an angle to one another and were rotated into the plane of the drawing in FIGS. 1 and 2.
  • An outer shell 21 surrounds the spiral housing 11 and forms an air gap 22 with it for thermal insulation.
  • the outer shell 21 need not have a spiral shape.
  • it is expediently designed as a cylindrical pot, the conical flange 23 of which faces the intermediate ring 18 and is braced together with the latter (FIG. 1) and possibly with the support plate ring 25 (FIG. 2) by the clamping ring 24.
  • the spiral housing 11 also has the shape of a pot with an annular cross section, the radially outer housing wall having at its free end facing the bearing ring 17 a connection 34, with which it on a shoulder 33 of the intermediate ring 18 (FIG. 1) o -
  • the bearing ring 17 (Fig. 2) abuts, and forms a sliding seat 32.
  • the sliding seat 32 is expediently sealed by an additional seal, for example in the form of a bead 36 at the connection 34 of the spiral housing 11.
  • Other heat-resistant sealing elements can also be provided.
  • the sliding seat 32 enables the volute casing 11, which becomes very hot during operation, to expand both radially and axially without generating thermal stresses on the diffuser 13, 17 or the outer formwork 21.
  • the connection 34 can follow the outer contour of the spiral housing 11 in a spiral shape, the shoulder 33 being able to be formed accordingly, in part by a groove in the end face of the intermediate ring 18 or the bearing ring 17.
  • the shoulder is expediently cylindrical as shown, so that a transition 35 bridges the distance between the connection 34 and the spiral cross-sectional contour of the spiral housing 11.
  • the radially inner, spiral-shaped housing wall of the spiral housing 11 ends at a base plate 28 which is adapted in its outer contour to the radially inner, spiral-shaped housing wall and is expediently connected thereto, for example by welding, as a result of which a seal between the spiral housing 11 and the base plate 28 is also achieved.
  • the base plate 28 can, however, also be cylindrical in the outer region, but then has a spiral groove 31 for receiving the radially inner housing wall of the spiral housing 11.
  • the base plate te 28 can also be integrally formed in one piece in the form of a flange on the spiral housing 11. In all embodiments of the base plate 28, it is sealingly connected to the contour sleeve 13.
  • the seal between the base plate 28 and the contour sleeve 13 can be made axially or radially by being pressed against the contour sleeve 13 by a clamping element 29 in the form of a clamping ring with spring tongues 39 and tool eyelets 40.
  • the seal shown causes an axial seal.
  • a radial seal is conceivable in which a clamping ring comprising the base plate 28 presses the base plate 28 against the contour sleeve 13.
  • heat-resistant sealing means can be inserted between the components 13, 28, 11.

Landscapes

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

Abstract

L'invention concerne se fonde sur une turbine à gaz d'échappement (10) pour turbocompresseur avec un carter en spirale (11) réalisé à base de tôle, qui entoure un distributeur (13, 17) et présente une trémie d'alimentation (41) débouchant de manière tangentielle. Une coque extérieure (21) en tôle entoure le carter en spirale (11) avec une fente d'air (22). Il est prévu, selon l'invention, que le carter en spirale (11) et la coque extérieure (21) soient conçus en forme de pot et que les faces avant tournées vers le distributeur (13, 17), soient délimitées par des parties dudit distributeur (13, 17), auxquelles se raccorde le carter en spirale (11) par l'intermédiaire d'au moins un élément (32) à déformation axiale.
EP04729870.8A 2003-06-06 2004-04-28 Turbine a gaz d'echappement pour turbocompresseur a gaz d'echappement Expired - Lifetime EP1631736B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10325649.0A DE10325649B4 (de) 2003-06-06 2003-06-06 Abgasturbine für einen Abgasturbolader
PCT/EP2004/004452 WO2004109062A1 (fr) 2003-06-06 2004-04-28 Turbine a gaz d'echappement pour turbocompresseur a gaz d'echappement

Publications (2)

Publication Number Publication Date
EP1631736A1 true EP1631736A1 (fr) 2006-03-08
EP1631736B1 EP1631736B1 (fr) 2015-07-29

Family

ID=33482616

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04729870.8A Expired - Lifetime EP1631736B1 (fr) 2003-06-06 2004-04-28 Turbine a gaz d'echappement pour turbocompresseur a gaz d'echappement

Country Status (5)

Country Link
US (1) US7371047B2 (fr)
EP (1) EP1631736B1 (fr)
JP (1) JP4269184B2 (fr)
DE (1) DE10325649B4 (fr)
WO (1) WO2004109062A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10436069B2 (en) 2017-01-30 2019-10-08 Garrett Transportation I Inc. Sheet metal turbine housing with biaxial volute configuration

Families Citing this family (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2003279321A1 (en) * 2003-10-24 2005-05-19 Honeywell International Inc. Turbocharger with a thin-walled turbine housing having a floating flange attachment to the centre housing
DE10352960B4 (de) * 2003-11-13 2006-06-14 Benteler Automobiltechnik Gmbh Gehäuseanordnung für den Turbolader einer Brennkraftmaschine
DE602005020701D1 (de) 2005-10-18 2010-05-27 Honeywell Int Inc Turbolader und patrone mit variabler düse dafür
DE102008005658A1 (de) 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
JP2010101271A (ja) 2008-10-24 2010-05-06 Mitsubishi Heavy Ind Ltd 可変容量タービン
DE102008059936A1 (de) * 2008-12-02 2010-06-24 Heinrich Gillet Gmbh Laufradgehäuse eines Abgasturboladers mit separater Gehäusewand
DE102009011379B4 (de) * 2009-03-05 2012-07-05 Benteler Automobiltechnik Gmbh Abgasbaugruppe
US9097121B2 (en) * 2009-10-30 2015-08-04 Borgwarner Inc. Turbine casing of an exhaust-gas turbocharger
DE102009054403A1 (de) 2009-11-24 2011-05-26 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader
DE102009058534A1 (de) 2009-12-16 2011-06-22 Bosch Mahle Turbo Systems GmbH & Co. KG, 70376 Abgasturbolader für eine Brennkraftmaschine
JP5357738B2 (ja) 2009-12-21 2013-12-04 三菱重工業株式会社 タービンハウジング
JP5769407B2 (ja) 2010-02-01 2015-08-26 三菱重工業株式会社 板金タービンハウジング
DE102010011375A1 (de) * 2010-03-12 2011-09-15 Bosch Mahle Turbo Systems Gmbh & Co. Kg Turbinen-/Verdichtergehäuse
JP5986767B2 (ja) * 2012-03-23 2016-09-06 三菱重工業株式会社 タービンハウジングアセンブリ
JP5984446B2 (ja) * 2012-03-23 2016-09-06 三菱重工業株式会社 タービンハウジングアセンブリおよびタービンハウジングアセンブリの製造方法
WO2013151802A1 (fr) * 2012-04-03 2013-10-10 Borgwarner Inc. Système de retenue et procédé pour un ensemble de grilles à aubes
KR102076117B1 (ko) * 2012-05-04 2020-02-11 보르그워너 인코퍼레이티드 가변 터빈 구조 베인 팩을 위한 베이오넷 스페이서 유지 시스템
DE102012009090A1 (de) * 2012-05-09 2013-11-14 Benteler Automobiltechnik Gmbh Anbindung eines doppelwandigen Turboladergehäuses
CN102828786B (zh) * 2012-09-12 2016-02-10 湖南天雁机械有限责任公司 可变截面涡轮增压器固定喷嘴环
WO2015083252A1 (fr) 2013-12-04 2015-06-11 三菱重工業株式会社 Logement de turbine en tôle métallique
JP6331736B2 (ja) 2014-06-13 2018-05-30 株式会社Ihi 可変ノズルユニット及び可変容量型過給機
CN104295326B (zh) * 2014-09-16 2017-02-08 萍乡德博科技股份有限公司 用于涡轮增压器可变截面喷嘴环上的定距套的铆接结构
JP6353769B2 (ja) * 2014-11-19 2018-07-04 アイシン高丘株式会社 タービンハウジング
JP6580122B2 (ja) * 2015-03-05 2019-09-25 三菱重工エンジン＆ターボチャージャ株式会社 ターボチャージャ
CN105221189B (zh) * 2015-10-28 2017-03-01 苏州诺迅汽车零部件有限公司 用于涡轮增压器可变截面喷嘴环上的定距套的铆接结构
EP3372801B1 (fr) * 2015-11-06 2019-10-23 Calsonic Kansei Corporation Carter de turbine
JP6641584B2 (ja) * 2016-03-30 2020-02-05 三菱重工エンジン＆ターボチャージャ株式会社 ターボチャージャー
US10472988B2 (en) 2017-01-30 2019-11-12 Garrett Transportation I Inc. Sheet metal turbine housing and related turbocharger systems
US10544703B2 (en) 2017-01-30 2020-01-28 Garrett Transportation I Inc. Sheet metal turbine housing with cast core
US10494955B2 (en) 2017-01-30 2019-12-03 Garrett Transportation I Inc. Sheet metal turbine housing with containment dampers
US11506086B2 (en) * 2017-03-31 2022-11-22 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine housing and turbo charger provided with same
US10690144B2 (en) 2017-06-27 2020-06-23 Garrett Transportation I Inc. Compressor housings and fabrication methods
CN110573711B (zh) * 2017-09-27 2022-04-05 三菱重工发动机和增压器株式会社 涡轮壳体以及具有该涡轮壳体的增压器
CN111512032B (zh) * 2017-12-26 2021-07-13 马瑞利株式会社 涡轮机壳体的制造方法
DE102018107304A1 (de) * 2018-03-27 2019-10-02 Man Energy Solutions Se Turbolader
US11136997B2 (en) * 2019-07-23 2021-10-05 Ford Global Technologies, Llc Methods and systems for a compressor housing
US11732729B2 (en) 2021-01-26 2023-08-22 Garrett Transportation I Inc Sheet metal turbine housing
US11781489B2 (en) 2021-11-11 2023-10-10 Progress Rail Locomotive Inc. Gear train joint
US11719129B2 (en) 2021-11-11 2023-08-08 Progress Rail Locomotive Inc. Compressor housing
US11519423B1 (en) 2021-11-11 2022-12-06 Progress Rail Locomotive Inc. Compressor joint
US11879348B2 (en) 2021-11-11 2024-01-23 Progress Rail Locomotive Inc. Bearing carrier
US11739763B2 (en) 2021-11-11 2023-08-29 Progress Rail Locomotive Inc. Impeller attach mechanism
US11614001B1 (en) 2021-11-11 2023-03-28 Progress Rail Locomotive Inc. Turbine containment

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES461142A1 (es) * 1976-09-04 1978-06-01 Mtu Friedrichshafen Gmbh Mejoras en turbo-cargadores de gas de escape para maquinas motrices de combustion.
JPS595809A (ja) * 1982-07-03 1984-01-12 Nissan Motor Co Ltd タ−ビンハウジング
DE19606003A1 (de) * 1996-02-17 1997-06-12 Daimler Benz Ag Schiebesitz-Rohrverbindung
EP0918140A1 (fr) * 1997-11-21 1999-05-26 Asea Brown Boveri AG Moteur à combustion interne suralimenté
DE29909018U1 (de) * 1999-05-26 2000-09-28 Heinrich Gillet GmbH & Co. KG, 67480 Edenkoben Turbinengehäuse für Abgasturbolader
BR0017293B1 (pt) * 2000-07-19 2008-11-18 turbocompressor de geometria variÁvel.
SE0003571D0 (sv) * 2000-10-02 2000-10-02 Turbec Ab Jointing method
DE10061846B4 (de) * 2000-12-12 2004-09-09 Daimlerchrysler Ag Abgasturbolader für eine Brennkraftmaschine
SE520577C2 (sv) * 2001-09-07 2003-07-29 Turbec Ab Ledning för en gasturbinenhet samt en metod för tillverkning av en ledning för en gasturbinenhet

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2004109062A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10436069B2 (en) 2017-01-30 2019-10-08 Garrett Transportation I Inc. Sheet metal turbine housing with biaxial volute configuration

Also Published As

Publication number Publication date
EP1631736B1 (fr) 2015-07-29
DE10325649A1 (de) 2004-12-23
JP2006527322A (ja) 2006-11-30
US7371047B2 (en) 2008-05-13
DE10325649B4 (de) 2014-10-23
US20060133931A1 (en) 2006-06-22
WO2004109062A1 (fr) 2004-12-16
JP4269184B2 (ja) 2009-05-27

Similar Documents

Publication Publication Date Title
EP1631736B1 (fr) Turbine a gaz d'echappement pour turbocompresseur a gaz d'echappement
EP1642009B1 (fr) Distributeur pour une turbine a gaz d'echappement
EP1460237B1 (fr) Carter pour une turbosoufflante
DE102004039477B4 (de) Turbinengehäuse für einen Abgasturbolader
DE19703033A1 (de) Abgasturbine eines Turboladers
EP2167793B1 (fr) Turbocompresseur a suralimentation de gaz d'échappement pour moteur à combustion interne
EP0485556B1 (fr) Couronne directrice d'une turbine d'un groupe propulseur a turbine a gas
EP3548705B1 (fr) Turbochargeur
WO2009092635A2 (fr) Système de chargement
EP1860284A1 (fr) Assemblage de carters
EP2173972B1 (fr) Rotor pour turbomachine à flux axial
EP2054587B1 (fr) Boîtier de turbine
DE102018115448A1 (de) Abgasturbolader
DE3839968A1 (de) Turbinengehaeuse eines abgasturboladers
DE102012103412A1 (de) Turbine für einen Abgasturbolader
EP1443182A2 (fr) Dispositif de refroidissement
EP2526263A2 (fr) Système de boîtier pour une turbomachine axiale
WO2005066463A1 (fr) Turbomachine comportant un support a aubes directrices et procede de montage d'aubes directrices sur un support a aubes directrices
EP3921576B1 (fr) Résonateur, procédé de fabrication d'un résonateur de ce type, et ensemble brûleur pourvu d'un résonateur de ce type
EP1138881B1 (fr) Boítier pour turbine de gaz axiale
DE3731901C2 (fr)
EP1724443A1 (fr) Couronne directrice
DE3220148C2 (de) Diffusor mit Leitgitter einer Gasturbine
DE3309812C2 (de) Äußeres Gehäuse für ein Gasturbinentriebwerk
DE102023201450A1 (de) Axialfolienlager

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20051118

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): DE FR GB IT

RIN1 Information on inventor provided before grant (corrected)

Inventor name: OHKITA, AKIHIRO

Inventor name: BURMESTER, HERMANN

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150325

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502004014977

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150729

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502004014977

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004014977

Country of ref document: DE

Representative=s name: HEEB-KELLER, ANNETTE, DIPL.-ING. DR.-ING., DE

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004014977

Country of ref document: DE

Representative=s name: HEEB-KELLER, ANNETTE, DR., DE

26N No opposition filed

Effective date: 20160502

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160428

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20161230

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160428

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160502

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004014977

Country of ref document: DE

Representative=s name: HEEB-KELLER, ANNETTE, DR., DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 502004014977

Country of ref document: DE

Owner name: IHI CHARGING SYSTEMS INTERNATIONAL GMBH, DE

Free format text: FORMER OWNER: IHI CHARGING SYSTEMS INTERNATIONAL GMBH, 69126 HEIDELBERG, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20210421

Year of fee payment: 18

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004014977

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20221103