EP1642009B1 - Distributor for an exhaust gas turbine - Google Patents

Distributor for an exhaust gas turbine Download PDF

Info

Publication number
EP1642009B1
EP1642009B1 EP04731148A EP04731148A EP1642009B1 EP 1642009 B1 EP1642009 B1 EP 1642009B1 EP 04731148 A EP04731148 A EP 04731148A EP 04731148 A EP04731148 A EP 04731148A EP 1642009 B1 EP1642009 B1 EP 1642009B1
Authority
EP
European Patent Office
Prior art keywords
exhaust gas
bearing ring
support element
ring
distributor according
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
Application number
EP04731148A
Other languages
German (de)
French (fr)
Other versions
EP1642009A1 (en
Inventor
Hermann Burmester
Akihiro Ohkita
Yukio Takahashi
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=33482715&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1642009(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by IHI Charging Systems International GmbH filed Critical IHI Charging Systems International GmbH
Publication of EP1642009A1 publication Critical patent/EP1642009A1/en
Application granted granted Critical
Publication of EP1642009B1 publication Critical patent/EP1642009B1/en
Anticipated expiration legal-status Critical
Active legal-status Critical Current

Links

Images

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

Definitions

  • the invention relates to a distributor for an exhaust gas turbine according to the preamble of claim 1.
  • contour sleeve and bearing ring guide vanes are then provided radially outwardly to the blades, which are rotatably mounted in the bearing ring and can be adjusted by a mounted in the bearing housing adjusting mechanism.
  • the contour sleeve and bearing ring are screwed together by screws and are held by spacer ribs at a distance.
  • a flexible mounting ring holds and centers the bearing ring in the housing.
  • the mounting ring has a z-shaped cross-sectional profile, wherein a radially outwardly directed outer flange in the parting line between the Bearing housing and the spiral housing engages and is held simultaneously with the housing screws, while an inner, radially directed flange engages over the bearing ring on the outer circumference and is bolted to the bearing ring.
  • Between the inner and outer flange of the mounting ring has a relatively thin cylindrical portion through which the contour sleeve is held flexible with the diffuser so that it is in conjunction with the radial seal at the outlet of the exhaust gas turbine capable of thermally expanding, without the Clamp adjustment of the vanes.
  • the type of storage of the adjustment is complex in the production and installation.
  • the mounting ring has different wall thicknesses, so that its production is costly.
  • stator vane for a turbocharger in which a vane carrier plate, vanes, levers and an adjusting ring can be manufactured, transported and installed as a module, the components being captive after connecting vane axes and vane levers are connected to the vane support plate.
  • the invention is based on the object to store a collar for adjustable guide vanes of a gas turbine turbocharger in a simple manner and cost. It is achieved according to the invention by the features of claim 1. Further advantageous embodiments will be apparent from the dependent claims.
  • the annular support member is produced as a component with a constant wall thickness without cutting and / or machined.
  • it can be produced inexpensively with little effort, eg as Sheet metal part. It is also very easy.
  • its thermal expansions and deformations can be easily predetermined due to its simple configuration.
  • the bearing ring is captively connected via a rivet with the spacer element, with the contour sleeve and the support member and preferably forms with the guide vanes, which are adjustably mounted between the bearing ring and the contour sleeve, a mounting unit.
  • This is held in the housing of the exhaust gas turbine and centered by an outer, radially directed flange of the support member between a bearing housing and a volute casing of the exhaust gas turbine is clamped.
  • the spacer elements are sealing bolts on which rivet heads are formed on the front side. With these the spacer bolts are fastened on the one hand to the contour sleeve and on the other hand to the bearing ring. But it is also possible to connect the bearing ring, the contour sleeve and the support member, regardless of the spacer element with each other via a rivet connection, a screw connection, a welded connection or a press connection captive, so that they form a mounting unit.
  • the spacer can be made arbitrary in this case and e.g. be formed by a spacer rib on the contour sleeve and / or the bearing ring.
  • the support member is connected on the side facing away from the exhaust gas with the bearing ring, so that the inner flange is not directly exposed to the hot exhaust gases and the support member can be made of a low-cost material.
  • a retaining plate can be attached to the bearing ring, with molded brackets forms a receiving space for a collar for the vanes towards the support element.
  • Both the retaining ring and the adjusting ring as well as further parts of a control mechanism for the guide vanes can be added to the mounting unit by being captively connected to the bearing ring.
  • the compensation ring is arranged between the retaining plate and the support element and preferably fastened with the same fastening means as for this on the bearing ring.
  • the support member In order to reduce the thermal stresses in the suspension of the support member, it may also be appropriate to connect the support member on the exhaust side facing the bearing ring.
  • An exhaust gas turbine 10 of an exhaust gas turbocharger has a bearing housing 27, in which a shaft 14 of an impeller 13 is rotatably mounted about an axis of rotation 16. Via the shaft 14, the impeller 13 of the exhaust gas turbine 10 drives the impeller, not shown, of a compressor of the turbocharger.
  • the impeller 13 has blades 15, which exhaust gas via a radially outer guide 17 in the flow direction 35 is supplied.
  • the exhaust gas is passed through a turbine outlet 36 in an unillustrated exhaust system of an internal combustion engine.
  • the diffuser 17 essentially comprises a contoured sleeve 18 which forms a lateral boundary of the blades 15 with clearance and is held at a distance by spacer elements 20 in the form of spacer bolts to a bearing ring 22.
  • the spacer bolts 20 have rivet heads 21 on the front side, through which the contour sleeve 18 and the bearing ring 22 are pressed against stops of the spacer elements 20.
  • adjustable guide vanes 19 are rotatably mounted. They are adjusted by an adjusting mechanism 28 via a collar 39, lever 41 and the guide vanes 19 associated control shafts 29 in dependence on operating parameters.
  • the bearing ring 22 and the captive associated with him to a mounting unit components, in particular the contour sleeve 18, the vanes 19, the spacer elements 20, the bearing ring 22 and parts of the Stellmechnismus 28 are in the housing 11, 27 of the exhaust turbine 10 by an annular flexible support member 23 held and centered.
  • the support member 23 has a substantially z-shaped cross section with an outer radial flange 24 and an inner radial flange 25.
  • the support member 23 has a constant wall thickness and is suitably made of sheet metal. While the inner flange 25 is fixed to the bearing ring 22, the outer flange 24 is clamped between a mounting flange 30 of the bearing housing 27 and a mounting flange 31 of a spiral housing 11 by the two mounting flanges 30, 31 are held together by a clamping ring 32 in cross-section V-shaped ,
  • the spiral housing 11 has a spiral channel 12, the flow cross-section of which tapers from a tangential inlet, not shown, in a known manner over the circumference of the spiral housing 11.
  • the contour sleeve 18 is limited axially slidably inserted with its axially extending part and sealed at the outer periphery by a radial sealing ring 34 which is embedded in a groove 33.
  • the diffuser 17 can adjust to different thermal expansions during operation of the exhaust gas turbine 10, without causing tension of adjacent components, in particular the adjusting mechanism 28.
  • the spacer element 20 can simultaneously serve in the form of a spacer bolt, which has rivet heads 21 on the front side.
  • a retaining plate 37 can be attached to the bearing ring 22 by the spacer element 20.
  • the retaining plate 37 forms with its integrally formed brackets 38 to the support member 23 through an installation space for the adjusting ring 39th
  • a compensation ring 40 is provided between the retaining ring 37 and the support member 23. Since it behaves under the operating conditions similar to the retaining ring 37, its distance from the retaining ring 37 and its brackets 38 is constant, so that the set game is maintained during operation and thermal expansions and deformations do not affect the function of the actuating mechanism detrimental.

Description

Die Erfindung betrifft einen Leitapparat für eine Abgasturbine nach dem Oberbegriff des Anspruchs 1.The invention relates to a distributor for an exhaust gas turbine according to the preamble of claim 1.

Aus der US 2 860 827 A ist ein Turbolader mit einer Abgasturbine und einem Verdichter bekannt, wobei das Laufrad mit den Laufschaufeln der Abgasturbine über eine Antriebswelle das Laufrad eines Verdichters antreibt. Die Antriebswelle ist in einem Lagergehäuse gelagert, das Teil eines Turbinengehäuses ist. Die Laufschaufeln werden seitlich mit Spiel von einer Konturhülse begrenzt, die mit einem axial gerichteten Ende über einen radialen Dichtring dichtend in einen Austrittsquerschnitt eines Spiralgehäuses eingesetzt ist. Zwischen dem sich radial nach außen erstreckenden Teil der Konturhülse und einem Lagerring sind radial nach außen an die Laufschaufeln anschließend Leitschaufeln vorgesehen, die in dem Lagerring drehbar gelagert sind und durch einen im Lagergehäuse gelagerten Verstellmechanismus verstellt werden können. Die Konturhülse und Lagerring sind durch Schrauben miteinander verschraubt und werden durch Abstandsrippen auf Distanz gehalten.From US Pat. No. 2,860,827 A a turbocharger with an exhaust gas turbine and a compressor is known, wherein the impeller with the rotor blades of the exhaust gas turbine drives the impeller of a compressor via a drive shaft. The drive shaft is mounted in a bearing housing which is part of a turbine housing. The blades are laterally limited by play of a contour sleeve, which is inserted with an axially directed end sealingly via a radial sealing ring in an outlet cross-section of a spiral housing. Between the radially outwardly extending part of the contour sleeve and a bearing ring guide vanes are then provided radially outwardly to the blades, which are rotatably mounted in the bearing ring and can be adjusted by a mounted in the bearing housing adjusting mechanism. The contour sleeve and bearing ring are screwed together by screws and are held by spacer ribs at a distance.

Ein flexibler Montagering hält und zentriert den Lagerring im Gehäuse. Hierzu besitzt der Montagering ein z-förmiges Querschnittprofil, wobei ein radial nach außen gerichteter äußerer Flansch in die Trennfuge zwischen dem Lagergehäuse und dem Spiralgehäuse eingreift und mit den Gehäuseschrauben gleichzeitig gehalten wird, während ein innerer, radial gerichteter Flansch den Lagerring am äußeren Umfang übergreift und mit dem Lagerring verschraubt ist. Zwischen dem inneren und äußeren Flansch besitzt der Montagering einen relativ dünnen zylindrischen Teilabschnitt, durch den die Konturhülse mit dem Leitapparat flexibel gehalten wird, so dass sie in Verbindung mit der radialen Dichtung am Austritt der Abgasturbine in der Lage ist, sich thermisch auszudehnen, ohne die Verstelleinrichtung der Leitschaufeln zu verspannen. Die Art der Lagerung der Verstelleinrichtung ist aufwändig in der Herstellung und Montage. Ferner besitzt der Montagering unterschiedliche Wandstärken, so dass seine Herstellung kostspielig ist.A flexible mounting ring holds and centers the bearing ring in the housing. For this purpose, the mounting ring has a z-shaped cross-sectional profile, wherein a radially outwardly directed outer flange in the parting line between the Bearing housing and the spiral housing engages and is held simultaneously with the housing screws, while an inner, radially directed flange engages over the bearing ring on the outer circumference and is bolted to the bearing ring. Between the inner and outer flange of the mounting ring has a relatively thin cylindrical portion through which the contour sleeve is held flexible with the diffuser so that it is in conjunction with the radial seal at the outlet of the exhaust gas turbine capable of thermally expanding, without the Clamp adjustment of the vanes. The type of storage of the adjustment is complex in the production and installation. Furthermore, the mounting ring has different wall thicknesses, so that its production is costly.

Aus der EP 1 227 221 ist eine Leitschaufel für eine Stelleinrichtung für einen Turbolader bekannt, bei der eine Leitschaufelträgerplatte, Leitschaufeln, Hebel und ein Verstellring als ein Modul hergestellt, transportiert und eingebaut werden können, wobei die Einzelteile nach dem Verbinden von Leitschaufelachsen und Leitschaufelhebeln unverlierbar mit der Leitschaufelträgerplatte verbunden sind.From EP 1 227 221 a stator vane for a turbocharger is known in which a vane carrier plate, vanes, levers and an adjusting ring can be manufactured, transported and installed as a module, the components being captive after connecting vane axes and vane levers are connected to the vane support plate.

Der Erfindung liegt die Aufgabe zu Grunde, einen Stellring für verstellbare Leitschaufeln einer Gasturbine eines Turboladers auf einfache Weise und kostengünstig zu lagern. Sie wird gemäß der Erfindung durch die Merkmale des Anspruchs 1 gelöst. Weitere vorteilhafte Ausgestaltungen ergeben sich aus den Unteransprüchen.The invention is based on the object to store a collar for adjustable guide vanes of a gas turbine turbocharger in a simple manner and cost. It is achieved according to the invention by the features of claim 1. Further advantageous embodiments will be apparent from the dependent claims.

Nach der Erfindung ist das ringförmige Stützelement als ein Bauteil mit einer konstanten Wandstärke spanlos und/oder spanabhebend hergestellt. Dadurch kann es mit wenig Aufwand kostengünstig hergestellt werden, z.B. als Blechteil. Zudem ist es besonders leicht. Ferner können seine Wärmedehnungen und Verformungen auf Grund seiner einfachen Konfiguration leicht vorher bestimmt werden.According to the invention, the annular support member is produced as a component with a constant wall thickness without cutting and / or machined. As a result, it can be produced inexpensively with little effort, eg as Sheet metal part. It is also very easy. Furthermore, its thermal expansions and deformations can be easily predetermined due to its simple configuration.

Zweckmäßigerweise ist der Lagerring über eine Nietverbindung unverlierbar mit dem Distanzelement, mit der Konturhülse sowie dem Stützelement verbunden und bildet vorzugsweise mit den Leitschaufeln, die zwischen dem Lagerring und der Konturhülse verstellbar gelagert sind, eine Montageeinheit. Diese wird in dem Gehäuse der Abgasturbine gehalten und zentriert, indem ein äußerer, radial gerichteter Flansch des Stützelements zwischen einem Lagergehäuse und einem Spiralgehäuse der Abgasturbine eingespannt wird.Conveniently, the bearing ring is captively connected via a rivet with the spacer element, with the contour sleeve and the support member and preferably forms with the guide vanes, which are adjustably mounted between the bearing ring and the contour sleeve, a mounting unit. This is held in the housing of the exhaust gas turbine and centered by an outer, radially directed flange of the support member between a bearing housing and a volute casing of the exhaust gas turbine is clamped.

Gemäß einer Ausgestaltung der Erfindung wird vorgeschlagen, dass die Distanzelemente Dichtbolzen sind, an denen stirnseitig Nietköpfe angeformt sind. Mit diesen werden die Distanzbolzen einerseits an der Konturhülse und andererseits an dem Lagerring befestigt. Es ist aber auch möglich, den Lagerring, die Konturhülse sowie das Stützelement unabhängig von dem Distanzelement miteinander über eine Nietverbindung, eine Schraubenverbindung, eine Schweißverbindung oder eine Pressverbindung unverlierbar zu verbinden, damit sie eine Montageeinheit bilden. Das Distanzelement kann in diesem Fall beliebig ausgeführt werden und z.B. durch eine Abstandsrippe an der Konturhülse und/oder dem Lagerring gebildet werden.According to one embodiment of the invention it is proposed that the spacer elements are sealing bolts on which rivet heads are formed on the front side. With these the spacer bolts are fastened on the one hand to the contour sleeve and on the other hand to the bearing ring. But it is also possible to connect the bearing ring, the contour sleeve and the support member, regardless of the spacer element with each other via a rivet connection, a screw connection, a welded connection or a press connection captive, so that they form a mounting unit. The spacer can be made arbitrary in this case and e.g. be formed by a spacer rib on the contour sleeve and / or the bearing ring.

Zweckmäßigerweise wird das Stützelement auf der dem Abgas abgewandten Seite mit dem Lagerring verbunden, so dass der innere Flansch nicht unmittelbar den heißen Abgasen ausgesetzt ist und das Stützelement aus einem kostengünstigen Werkstoff hergestellt werden kann. Mit der gleichen Befestigung wie für das Stützelement kann ein Halteblech am Lagerring angebracht werden, das mit angeformten Haltewinkeln zum Stützelement hin einen Aufnahmeraum für einen Stellring für die Leitschaufeln bildet. Sowohl der Haltering als auch der Stellring sowie weitere Teile eines Stellmechanismus für die Leitschaufeln können zu der Montageeinheit hinzugefügt werden, indem sie mit dem Lagerring unverlierbar verbunden werden. Dadurch wird einerseits die Montage vereinfacht, zum anderen ergeben sich einfache, kurze Bauteile, deren Wärmedehnungen sehr gering sind. Dennoch kann es zweckmäßig sein, zum axialen Kalibrieren des Einbauraums des Stellrings einen Ausgleichsring zwischen dem Haltering und dem Stützelement bzw. dem Lagerring vorzusehen. Der Ausgleichsring ist zwischen dem Halteblech und dem Stützelement angeordnet und vorzugsweise mit den gleichen Befestigungsmitteln wie für dieses am Lagerring befestigt.Conveniently, the support member is connected on the side facing away from the exhaust gas with the bearing ring, so that the inner flange is not directly exposed to the hot exhaust gases and the support member can be made of a low-cost material. With the same attachment as for the support element, a retaining plate can be attached to the bearing ring, with molded brackets forms a receiving space for a collar for the vanes towards the support element. Both the retaining ring and the adjusting ring as well as further parts of a control mechanism for the guide vanes can be added to the mounting unit by being captively connected to the bearing ring. As a result, on the one hand, the assembly is simplified, on the other hand result in simple, short components whose thermal expansion is very low. Nevertheless, it may be expedient to provide a compensation ring between the retaining ring and the support element or the bearing ring for axial calibration of the installation space of the adjusting ring. The compensation ring is arranged between the retaining plate and the support element and preferably fastened with the same fastening means as for this on the bearing ring.

Um die Wärmespannungen in der Aufhängung des Stützelements zu verringern, kann es ferner zweckmäßig sein, das Stützelement auf der dem Abgas zugewandten Seite mit dem Lagerring zu verbinden.In order to reduce the thermal stresses in the suspension of the support member, it may also be appropriate to connect the support member on the exhaust side facing the bearing ring.

Weitere Vorteile ergeben sich aus der folgenden Zeichnungsbeschreibung. In der Zeichnung sind Ausführungsbeispiele der Erfindung dargestellt. Die Zeichnung, die Beschreibung und die Ansprüche enthalten zahlreiche Merkmale in Kombination. Der Fachmann wird die Merkmale zweckmäßigerweise auch einzeln betrachten und zu sinnvollen weiteren Kombinationen zusammenfassen.Further advantages emerge from the following description of the drawing. In the drawings, embodiments of the invention are shown. The drawing, the description and the claims contain numerous features in combination. The person skilled in the art will expediently also consider the features individually and combine them into meaningful further combinations.

Dabei zeigen:

Fig. 1
einen schematischen Längsschnitt durch eine Abgasturbine,
Fig. 2
einen Teillängsschnitt durch einen Leitapparat ohne Leitschaufeln und
Fig. 3
einen Teillängsschnitt im Bereich eines Stellrings für die Leitschaufeln.
Showing:
Fig. 1
a schematic longitudinal section through an exhaust gas turbine,
Fig. 2
a partial longitudinal section through a nozzle without vanes and
Fig. 3
a partial longitudinal section in the region of an adjusting ring for the vanes.

Eine Abgasturbine 10 eines Abgasturboladers besitzt ein Lagergehäuse 27, in dem eine Welle 14 eines Laufrads 13 um eine Rotationsachse 16 drehbar gelagert ist. Über die Welle 14 treibt das Laufrad 13 der Abgasturbine 10 das nicht dargestellte Laufrad eines Verdichters des Turboladers an. Das Laufrad 13 besitzt Laufschaufeln 15, denen Abgas über einen radial außen liegenden Leitapparat 17 in Strömungsrichtung 35 zugeführt wird. Das Abgas wird über einen Turbinenaustritt 36 in ein nicht dargestelltes Abgassystem einer Brennkraftmaschine geleitet.An exhaust gas turbine 10 of an exhaust gas turbocharger has a bearing housing 27, in which a shaft 14 of an impeller 13 is rotatably mounted about an axis of rotation 16. Via the shaft 14, the impeller 13 of the exhaust gas turbine 10 drives the impeller, not shown, of a compressor of the turbocharger. The impeller 13 has blades 15, which exhaust gas via a radially outer guide 17 in the flow direction 35 is supplied. The exhaust gas is passed through a turbine outlet 36 in an unillustrated exhaust system of an internal combustion engine.

Der Leitapparat 17 umfasst im Wesentlichen eine Konturhülse 18, die mit Spiel eine seitliche Begrenzung der Laufschaufeln 15 bildet und über Distanzelemente 20 in Form von Distanzbolzen zu einem Lagerring 22 auf Abstand gehalten wird. Die Distanzbolzen 20 weisen stirnseitig Nietköpfe 21 auf, durch die die Konturhülse 18 und der Lagering 22 gegen Anschläge der Distanzelemente 20 gedrückt werden. Zwischen dem radial nach außen gerichteten Teil der Konturhülse 18 und dem Lagerring 22 sind verstellbare Leitschaufeln 19 drehbar gelagert. Sie werden durch einen Verstellmechanismus 28 über einen Stellring 39, Stellhebel 41 und mit den Leitschaufeln 19 verbundenen Stellwellen 29 in Abhängigkeit von Betriebsparametern verstellt. Der Lagerring 22 und die mit ihm zu einer Montageeinheit unverlierbar verbundenen Komponenten, insbesondere die Konturhülse 18, die Leitschaufeln 19, die Distanzelemente 20, der Lagerring 22 und Teile des Stellmechnismus 28, werden im Gehäuse 11, 27 der Abgasturbine 10 durch ein ringförmiges flexibles Stützelement 23 gehalten und zentriert. Das Stützelement 23 hat einen im Wesentlichen z-förmigen Querschnitt mit einem äußeren radialen Flansch 24 und einem inneren radialen Flansch 25.The diffuser 17 essentially comprises a contoured sleeve 18 which forms a lateral boundary of the blades 15 with clearance and is held at a distance by spacer elements 20 in the form of spacer bolts to a bearing ring 22. The spacer bolts 20 have rivet heads 21 on the front side, through which the contour sleeve 18 and the bearing ring 22 are pressed against stops of the spacer elements 20. Between the radially outwardly directed part of the contour sleeve 18 and the bearing ring 22 adjustable guide vanes 19 are rotatably mounted. They are adjusted by an adjusting mechanism 28 via a collar 39, lever 41 and the guide vanes 19 associated control shafts 29 in dependence on operating parameters. The bearing ring 22 and the captive associated with him to a mounting unit components, in particular the contour sleeve 18, the vanes 19, the spacer elements 20, the bearing ring 22 and parts of the Stellmechnismus 28 are in the housing 11, 27 of the exhaust turbine 10 by an annular flexible support member 23 held and centered. The support member 23 has a substantially z-shaped cross section with an outer radial flange 24 and an inner radial flange 25.

Zwischen den beiden Flanschen 24, 25 befindet sich ein zylindrischer Teil 26, der auf Grund seiner Dimensionierung wesentlich zur Flexibilität des Stützelements 23 beiträgt. Das Stützelement 23 besitzt eine konstante Wandstärke und wird zweckmäßigerweise aus Blech gefertigt. Während der innere Flansch 25 am Lagerring 22 befestigt ist, wird der äußere Flansch 24 zwischen einem Befestigungsflansch 30 des Lagergehäuses 27 und einem Befestigungsflansch 31 eines Spiralgehäuses 11 verspannt, indem die beiden Befestigungsflansche 30, 31 durch einen im Querschnitt v-förmigen Spannring 32 zusammengehalten werden.Between the two flanges 24, 25 is a cylindrical part 26, which contributes substantially to the flexibility of the support member 23 due to its dimensions. The support member 23 has a constant wall thickness and is suitably made of sheet metal. While the inner flange 25 is fixed to the bearing ring 22, the outer flange 24 is clamped between a mounting flange 30 of the bearing housing 27 and a mounting flange 31 of a spiral housing 11 by the two mounting flanges 30, 31 are held together by a clamping ring 32 in cross-section V-shaped ,

Das Spiralgehäuse 11 besitzt einen Spiralkanal 12, dessen Strömungsquerschnitt sich von einem nicht dargestellten tangentialen Einlass in bekannter Weise über den Umfang des Spiralgehäuses 11 verjüngt. In das Spiralgehäuse 11 ist die Konturhülse 18 mit ihrem axial verlaufenden Teil begrenzt axial verschiebbar eingesetzt und an dessen äußerem Umfang durch einen radialen Dichtring 34 abgedichtet, der in einer Nut 33 eingebettet ist. Somit kann sich der Leitapparat 17 auf unterschiedliche Wärmedehnungen während des Betriebs der Abgasturbine 10 einstellen, ohne dass es zu Verspannungen benachbarter Bauteile, insbesondere des Verstellmechanismus 28 kommt.The spiral housing 11 has a spiral channel 12, the flow cross-section of which tapers from a tangential inlet, not shown, in a known manner over the circumference of the spiral housing 11. In the spiral housing 11, the contour sleeve 18 is limited axially slidably inserted with its axially extending part and sealed at the outer periphery by a radial sealing ring 34 which is embedded in a groove 33. Thus, the diffuser 17 can adjust to different thermal expansions during operation of the exhaust gas turbine 10, without causing tension of adjacent components, in particular the adjusting mechanism 28.

Während bei der Ausführung nach Fig. 1 das Stützelement 23 mit seinem inneren Flansch 25 den Lagerring 22 übergreift, und mit dem inneren Flansch 25 an dem Lagerring 22 befestigt ist, ist das Stützelement 23 nach Fig. 2 mit seinem inneren Flansch 25 an der dem Abgas abgewandten Seite des Lagerrings 22 befestigt und ist somit gegenüber den heißen Abgasen geschützt. Zum Befestigen des Stützelements 23 kann gleichzeitig das Distanzelement 20 in Form eines Distanzbolzens dienen, der stirnseitig Nietköpfe 21 aufweist. Ferner kann durch das Distanzelement 20 ein Halteblech 37 am Lagerring 22 befestigt werden.While in the embodiment of FIG. 1, the support member 23 with its inner flange 25, the bearing ring 22 engages over, and is secured to the inner flange 25 on the bearing ring 22, the support member 23 of FIG. 2 with its inner flange 25 at the Exhaust side facing away from the bearing ring 22 and is thus protected from the hot exhaust gases. For fixing the support element 23, the spacer element 20 can simultaneously serve in the form of a spacer bolt, which has rivet heads 21 on the front side. Furthermore, a retaining plate 37 can be attached to the bearing ring 22 by the spacer element 20.

Das Halteblech 37 bildet mit seinen angeformten Haltewinkeln 38 zum Stützelement 23 hin einen Einbauraum für den Stellring 39.The retaining plate 37 forms with its integrally formed brackets 38 to the support member 23 through an installation space for the adjusting ring 39th

Zur Kontrolle des notwendigen axialen Spiels für den Stellring 39 unter den wechselnd heißen Betriebsbedingungen der Abgasturbine 10 ist zwischen dem Haltering 37 und dem Stützelement 23 ein Ausgleichsring 40 vorgesehen. Da er sich unter den Betriebsbedingungen ähnlich verhält wie der Haltering 37, bleibt sein Abstand vom Haltering 37 bzw. seinen Haltewinkeln 38 konstant, so dass das eingestellte Spiel während des Betriebs erhalten bleibt und sich Wärmedehnungen und Verformungen nicht auf die Funktion des Stellmechanismus nachteilig auswirken.To control the necessary axial clearance for the adjusting ring 39 under the changing hot operating conditions of the exhaust gas turbine 10, a compensation ring 40 is provided between the retaining ring 37 and the support member 23. Since it behaves under the operating conditions similar to the retaining ring 37, its distance from the retaining ring 37 and its brackets 38 is constant, so that the set game is maintained during operation and thermal expansions and deformations do not affect the function of the actuating mechanism detrimental.

Claims (9)

  1. Distributor for an exhaust gas turbine of a turbocharger which has a bearing ring and a contoured casing which are held at a distance from one another by means of spacer elements and between which adjustable guide vanes are rotatably mounted, the contoured casing being inserted with a radial seal into a spiral housing in an axially displaceable manner and delimiting a lateral outer contour of a rotor with play, while the bearing ring is centered and mounted relative to a housing of the exhaust gas turbine by means of an annular flexible support element,
    characterized
    in that the support element (23) is manufactured in a non-cutting and/or a cutting manner as a component with a constant wall thickness.
  2. Distributor according to Claim 1,
    characterized
    in that the bearing ring (22) is captively connected to the spacer element (20), to the contoured casing (18) and to the support element (23) by means of a rivet connection, and thus forms an assembly unit.
  3. Distributor according to Claim 2,
    characterized
    in that the spacer element (20) is a spacer bolt on which rivet heads (21) are integrated on the end side.
  4. Distributor according to Claim 1,
    characterized
    in that the bearing ring (22) is captively connected independently of the spacer element (20) to the contoured casing (18) and the support element (23) by means of a rivet connection, a screw connection, a welded connection or an interference fit and thus forms an assembly unit.
  5. Distributor according to one of the preceding claims,
    characterized
    in that the support element (23) is connected to the support ring (22) on the side facing away from the exhaust gas.
  6. Distributor according to Claim 5,
    characterized
    in that an annular metal holding plate (37) is fastened to the bearing ring (22) on the side facing away from the exhaust gas, which holding plate forms, with integrally formed angle supports (38), a receiving space toward the support element (23) for a setting ring (39) for the guide vanes (19).
  7. Distributor according to Claim 6,
    characterized
    in that an equalization ring (40) is provided between the holding plate (37) and the support element (23).
  8. Distributor according to Claim 6 or 7,
    characterized
    in that all or some of its components (18, 20, 22, 23) including an adjusting device (28, 29, 37, 39, 40) are assembled to form an assembly of a design and are captively held together.
  9. Distributor according to one of Claims 1 to 4,
    characterized
    in that the support element (23) is fastened to the bearing ring (22) on the side facing the exhaust gas.
EP04731148A 2003-06-07 2004-05-05 Distributor for an exhaust gas turbine Active EP1642009B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10325985A DE10325985A1 (en) 2003-06-07 2003-06-07 Guide device for an exhaust gas turbine
PCT/EP2004/004758 WO2004109063A1 (en) 2003-06-07 2004-05-05 Distributor for an exhaust gas turbine

Publications (2)

Publication Number Publication Date
EP1642009A1 EP1642009A1 (en) 2006-04-05
EP1642009B1 true EP1642009B1 (en) 2006-10-18

Family

ID=33482715

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04731148A Active EP1642009B1 (en) 2003-06-07 2004-05-05 Distributor for an exhaust gas turbine

Country Status (5)

Country Link
US (1) US20110236197A1 (en)
EP (1) EP1642009B1 (en)
JP (1) JP4280936B2 (en)
DE (2) DE10325985A1 (en)
WO (1) WO2004109063A1 (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007040679A1 (en) 2007-08-29 2009-03-05 Bayerische Motoren Werke Aktiengesellschaft Guide vane device for turbine of turbo charger, comprises two spaced bolt over distance, where spaced bolts are projected on guide vane facing side from side wall with head in increased diameter
DE102008053079A1 (en) 2008-10-24 2010-04-29 Bayerische Motoren Werke Aktiengesellschaft Exhaust gas turbocharger for diesel internal-combustion engine of vehicle, has guiding device adjustable by adjusting device over coupling element, where coupling element is made of temperature-constant plastic
US7918023B2 (en) 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
US7980816B2 (en) 2007-08-27 2011-07-19 Honeywell International Inc. Retainer for a turbocharger
DE102013106063A1 (en) 2012-09-20 2014-03-20 Ihi Charging Systems International Gmbh Adjustable guide vane for turbine of turbocharger, has carrier ring that is formed from material with low expansion coefficient and high thermal conductivity to reduce first gap
DE102012109549A1 (en) 2012-10-08 2014-04-10 Ihi Charging Systems International Gmbh Adjustable distributor for an exhaust gas guide section of a turbine, and exhaust gas turbocharger
DE102012110329A1 (en) 2012-10-29 2014-04-30 Firma IHI Charging Systems International GmbH Adjustable nozzle for a turbine and method of making an adjustable nozzle
DE102018115448A1 (en) * 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh turbocharger
US11346249B2 (en) 2019-03-05 2022-05-31 Pratt & Whitney Canada Corp. Gas turbine engine with feed pipe for bearing housing
US11391179B2 (en) 2019-02-12 2022-07-19 Pratt & Whitney Canada Corp. Gas turbine engine with bearing support structure

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4275081B2 (en) * 2005-02-10 2009-06-10 三菱重工業株式会社 Scroll structure of variable displacement exhaust turbocharger and method of manufacturing the same
EP1945928B2 (en) 2005-10-18 2015-11-25 Honeywell International Inc. Turbocharger and variable-nozzle cartridge therefor
DE102007021448B4 (en) * 2006-05-18 2012-06-28 Man Diesel & Turbo Se Diaphragm for an exhaust gas turbocharger operated with heavy oil reciprocating internal combustion engine
US7559199B2 (en) 2006-09-22 2009-07-14 Honeywell International Inc. Variable-nozzle cartridge for a turbocharger
DE102007029004A1 (en) 2007-06-23 2008-12-24 Ihi Charging Systems International Gmbh Exhaust gas turbocharger for an internal combustion engine
JP2009144546A (en) * 2007-12-12 2009-07-02 Ihi Corp Turbocharger
DE102008000776B4 (en) * 2008-01-21 2022-04-14 BMTS Technology GmbH & Co. KG Turbine with variable turbine geometry, in particular for an exhaust gas turbocharger, and exhaust gas turbocharger
DE102008005658A1 (en) 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg loader
DE102008000860A1 (en) 2008-03-27 2009-10-01 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable guide vane device for exhaust gas-turbo charger of internal combustion engine of motor vehicle, has spacer formed of bolts, where diameter of bolts is designed smaller than clearance hole to create heat isolated free space
DE102008023552B4 (en) 2008-05-14 2018-12-20 BMTS Technology GmbH & Co. KG Exhaust gas turbocharger for a motor vehicle
JP5452991B2 (en) * 2008-07-10 2014-03-26 ボーグワーナー インコーポレーテッド Variable geometry vane ring assembly with stepped spacers
JP2010071142A (en) * 2008-09-17 2010-04-02 Ihi Corp Turbocharger
JP5101546B2 (en) 2009-02-26 2012-12-19 三菱重工業株式会社 Variable displacement exhaust turbocharger
JP5397144B2 (en) * 2009-10-14 2014-01-22 株式会社Ｉｈｉ Assembly method of variable nozzle unit
DE102009056875B4 (en) * 2009-12-03 2013-07-11 Bosch Mahle Turbo Systems Gmbh & Co. Kg Bearing housing, charging device and method for surface treatment of a bearing housing
GB201015679D0 (en) * 2010-09-20 2010-10-27 Cummins Ltd Variable geometry turbine
DE102012006711A1 (en) * 2012-01-18 2013-07-18 Ihi Charging Systems International Gmbh turbocharger
DE112013001366T5 (en) * 2012-04-03 2014-11-27 Borgwarner Inc. Holding system and method for vane ring unit
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
DE102013104905A1 (en) 2013-05-13 2014-11-13 Ihi Charging Systems International Gmbh Adjustable distributor for a turbine, turbine for an exhaust gas turbocharger and turbocharger
US9556880B2 (en) 2013-06-26 2017-01-31 Honeywell International Inc. Turbine exhaust seal
JP6204398B2 (en) * 2015-03-23 2017-09-27 カルソニックカンセイ株式会社 Turbine housing
WO2017078088A1 (en) * 2015-11-06 2017-05-11 カルソニックカンセイ株式会社 Turbine housing
CN106337697B (en) * 2016-09-13 2019-02-01 中国北方发动机研究所(天津) A kind of nozzle ring seal arrangement
US11015518B2 (en) 2017-03-16 2021-05-25 Mitsubishi Heavy Industries, Ltd. Variable nozzle device and variable-geometry type exhaust turbocharger
KR20220093987A (en) 2020-12-28 2022-07-05 한화에어로스페이스 주식회사 An exhaust duct assembly with an improved weld zone structure and aircraft including the same

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2860827A (en) * 1953-06-08 1958-11-18 Garrett Corp Turbosupercharger
US3101926A (en) * 1960-09-01 1963-08-27 Garrett Corp Variable area nozzle device
US4179247A (en) * 1977-01-14 1979-12-18 Wrr Industries, Inc. Turbocharger having variable area turbine nozzles
US4679984A (en) * 1985-12-11 1987-07-14 The Garrett Corporation Actuation system for variable nozzle turbine
US4804316A (en) * 1985-12-11 1989-02-14 Allied-Signal Inc. Suspension for the pivoting vane actuation mechanism of a variable nozzle turbocharger
US4907952A (en) * 1986-12-05 1990-03-13 Honda Giken Kogyo Kabushiki Kaisha Turbocharger
US5947681A (en) * 1997-03-17 1999-09-07 Alliedsignal Inc. Pressure balanced dual axle variable nozzle turbocharger
JP3771765B2 (en) * 2000-01-24 2006-04-26 三菱重工業株式会社 Variable turbocharger
JP3842943B2 (en) * 2000-01-24 2006-11-08 三菱重工業株式会社 Variable turbocharger
JP2001329851A (en) * 2000-05-19 2001-11-30 Mitsubishi Heavy Ind Ltd Variable nozzle mechanism for variable displacement turbine
DE10104176A1 (en) * 2001-01-24 2002-07-25 Mahle Gmbh Guide blade adjusting device for turbocharger ha adjusting ring with projecting noses for axial guidance of ring on blade carrier plate
US7946116B2 (en) * 2002-09-05 2011-05-24 Honeywell International, Inc. Turbocharger comprising a variable nozzle device

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7918023B2 (en) 2007-02-08 2011-04-05 Honeywell International Inc. Method for manufacturing a variable-vane mechanism for a turbocharger
US7980816B2 (en) 2007-08-27 2011-07-19 Honeywell International Inc. Retainer for a turbocharger
DE102007040679A1 (en) 2007-08-29 2009-03-05 Bayerische Motoren Werke Aktiengesellschaft Guide vane device for turbine of turbo charger, comprises two spaced bolt over distance, where spaced bolts are projected on guide vane facing side from side wall with head in increased diameter
DE102008053079A1 (en) 2008-10-24 2010-04-29 Bayerische Motoren Werke Aktiengesellschaft Exhaust gas turbocharger for diesel internal-combustion engine of vehicle, has guiding device adjustable by adjusting device over coupling element, where coupling element is made of temperature-constant plastic
DE102013106063A1 (en) 2012-09-20 2014-03-20 Ihi Charging Systems International Gmbh Adjustable guide vane for turbine of turbocharger, has carrier ring that is formed from material with low expansion coefficient and high thermal conductivity to reduce first gap
DE102013106063A8 (en) * 2012-09-20 2014-04-10 Ihi Charging Systems International Gmbh Adjustable nozzle for a turbine
DE102012109549A1 (en) 2012-10-08 2014-04-10 Ihi Charging Systems International Gmbh Adjustable distributor for an exhaust gas guide section of a turbine, and exhaust gas turbocharger
WO2014056574A1 (en) 2012-10-08 2014-04-17 Ihi Charging Systems International Gmbh Adjustable stator for an exhaust gas guiding section of a turbine, and turbocharger
DE102012109549B4 (en) 2012-10-08 2023-03-30 Ihi Charging Systems International Gmbh Adjustable diffuser for an exhaust gas duct section of a turbine, and exhaust gas turbocharger
DE102012110329A1 (en) 2012-10-29 2014-04-30 Firma IHI Charging Systems International GmbH Adjustable nozzle for a turbine and method of making an adjustable nozzle
WO2014067628A1 (en) 2012-10-29 2014-05-08 Ihi Charging Systems International Gmbh Adjustable diffuser for a radial turbine and assembly method related thereto
DE102018115448A1 (en) * 2018-06-27 2020-01-02 Ihi Charging Systems International Gmbh turbocharger
US11220957B2 (en) 2018-06-27 2022-01-11 Ihi Charging Systems International Gmbh Exhaust gas turbocharger
US11391179B2 (en) 2019-02-12 2022-07-19 Pratt & Whitney Canada Corp. Gas turbine engine with bearing support structure
US11346249B2 (en) 2019-03-05 2022-05-31 Pratt & Whitney Canada Corp. Gas turbine engine with feed pipe for bearing housing

Also Published As

Publication number Publication date
WO2004109063A1 (en) 2004-12-16
DE10325985A1 (en) 2004-12-23
DE502004001823D1 (en) 2006-11-30
JP2006527323A (en) 2006-11-30
US20110236197A1 (en) 2011-09-29
JP4280936B2 (en) 2009-06-17
EP1642009A1 (en) 2006-04-05

Similar Documents

Publication Publication Date Title
EP1642009B1 (en) Distributor for an exhaust gas turbine
DE10325649B4 (en) Exhaust gas turbine for an exhaust gas turbocharger
EP1460237B1 (en) Casing of a turbocharger
EP1736635B1 (en) Air transfer system between compressor and turbine of a gas turbine engine
DE10210866C1 (en) Guide blade segment fixing device for flow channel of aircraft gas turbine uses slot and hook fixing and pin fitting through latter
EP1334262B1 (en) Exhaust gas turbocharger for an internal combustion engine with variable turbine geometry
EP2161431B1 (en) Inlet nose cone for an aircraft gas turbine powerplant
WO2009092635A2 (en) Supercharger device
EP3440319B1 (en) Turbocharger for an internal combustion engine
WO2010003537A2 (en) Turbine housing for an exhaust gas turbocharger of an internal combustion engine
EP1860284A1 (en) Casings assembling
EP0806547A1 (en) Axial turbine for turbochargers
EP2112332B1 (en) Supporting ring for a guide vane assembly with an air-sealed channel
EP3252284B1 (en) Combustion engine comprising two exhaust gas turbochargers
DE102004031986B4 (en) Exhaust gas turbocharger for an internal combustion engine
DE102021211009A1 (en) Bearing housing of an exhaust gas turbocharger with heat shield, exhaust gas turbine assembly and exhaust gas turbocharger
EP1724443A1 (en) Nozzle ring
EP1840350B1 (en) Cladding device, in particular for exhaust gas pipes from power units
DE102019125823B4 (en) Turbine housing and exhaust gas turbocharger with pre-guide blades and an internal combustion engine with an exhaust gas turbocharger
DE102014109131A1 (en) turbocharger
DE102015224990A1 (en) Method for assembling a combustion chamber of a gas turbine engine
DE102013106063A1 (en) Adjustable guide vane for turbine of turbocharger, has carrier ring that is formed from material with low expansion coefficient and high thermal conductivity to reduce first gap
DE102012006710A1 (en) Supercharger for internal combustion engine i.e. reciprocating internal combustion engine, has supporting element fastened at bearing housing by attachment element that is partially held in housing that includes turbine
DE102010013706A1 (en) Method for manufacturing turbocharger housing, involves providing measurement section at spiral housing, where turbocharger housing with its two housing halves is formed as cast parts
WO2018137882A1 (en) Adjustable guide apparatus for an exhaust gas guide section of an exhaust gas turbocharger and exhaust gas guide section for an exhaust gas turbocharger

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: 20051125

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

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

Designated state(s): DE FR GB IT

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

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20061018

REF Corresponds to:

Ref document number: 502004001823

Country of ref document: DE

Date of ref document: 20061130

Kind code of ref document: P

ET Fr: translation filed
PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

26 Opposition filed

Opponent name: HONEYWELL TURBO TECHNOLOGIES

Effective date: 20070717

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

PLAY Examination report in opposition despatched + time limit

Free format text: ORIGINAL CODE: EPIDOSNORE2

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO

R26 Opposition filed (corrected)

Opponent name: HONEYWELL TURBO TECHNOLOGIES

Effective date: 20070717

PLBC Reply to examination report in opposition received

Free format text: ORIGINAL CODE: EPIDOSNORE3

PLCK Communication despatched that opposition was rejected

Free format text: ORIGINAL CODE: EPIDOSNREJ1

PLBN Opposition rejected

Free format text: ORIGINAL CODE: 0009273

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

Free format text: STATUS: OPPOSITION REJECTED

27O Opposition rejected

Effective date: 20130509

REG Reference to a national code

Ref country code: DE

Ref legal event code: R100

Ref document number: 502004001823

Country of ref document: DE

Effective date: 20130509

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

Ref country code: GB

Payment date: 20140520

Year of fee payment: 11

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

Ref country code: FR

Payment date: 20140516

Year of fee payment: 11

Ref country code: IT

Payment date: 20140527

Year of fee payment: 11

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

Effective date: 20150505

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 NON-PAYMENT OF DUE FEES

Effective date: 20150505

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20160129

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: 20150505

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

Ref country code: FR

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

Effective date: 20150601

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502004001823

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: 502004001823

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

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230530

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

Ref country code: DE

Payment date: 20230519

Year of fee payment: 20