EP2317081B1 - Variable geometry turbine and/or compressor - Google Patents

Variable geometry turbine and/or compressor Download PDF

Info

Publication number
EP2317081B1
EP2317081B1 EP10189179A EP10189179A EP2317081B1 EP 2317081 B1 EP2317081 B1 EP 2317081B1 EP 10189179 A EP10189179 A EP 10189179A EP 10189179 A EP10189179 A EP 10189179A EP 2317081 B1 EP2317081 B1 EP 2317081B1
Authority
EP
European Patent Office
Prior art keywords
blade bearing
bearing ring
ring
adjusting
guide rollers
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
EP10189179A
Other languages
German (de)
French (fr)
Other versions
EP2317081A3 (en
EP2317081A2 (en
Inventor
Anatolij Martens
Timo Tries
Florian Rentz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BMTS Technology GmbH and Co KG
Original Assignee
Bosch Mahle Turbo Systems GmbH and Co KG
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 Bosch Mahle Turbo Systems GmbH and Co KG filed Critical Bosch Mahle Turbo Systems GmbH and Co KG
Publication of EP2317081A2 publication Critical patent/EP2317081A2/en
Publication of EP2317081A3 publication Critical patent/EP2317081A3/en
Application granted granted Critical
Publication of EP2317081B1 publication Critical patent/EP2317081B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • 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
    • F05D2260/33—Retaining components in desired mutual position with a bayonet coupling
    • 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
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • the present invention relates to a variable turbine and / or compressor geometry with a vane ring and rotatably mounted therein or therein vanes according to the preamble of claim 1.
  • the invention also relates to a equipped with such a variable turbine and / or compressor geometry charging device and a method for mounting such a variable turbine and / or compressor geometry.
  • variable turbine and / or compressor geometry with a blade bearing ring and rotatably mounted guide vanes known.
  • the known variable turbine and / or compressor geometry in this case has an adjusting ring for adjusting the guide vanes, which is rotatably mounted on guide rollers on the blade bearing ring.
  • An axial fixation of the adjusting ring on the blade bearing ring takes place via the guide rollers, which in turn are arranged rotatably and fixedly in the axial direction on the blade bearing ring.
  • a disadvantage of the known variable turbine and / or compressor geometry is that the guide rollers are designed only as a plain bearing, whereby a comparatively high adjustment when adjusting the variable turbine and / or compressor geometry is overcome.
  • Other variable tubing and / or compressor geometry according to the prior art are known from the DE 10 2007 056 154 A1 or the DE 102 09 172 A1 known.
  • the present invention therefore deals with the problem of providing for a generic variable turbine and / or compressor geometry an improved or at least one alternative embodiment, which is characterized in particular by a simple assembly and a low resistance to working.
  • the present invention is based on the general idea of supporting a guide roller for guiding an adjusting ring on a blade bearing ring rotatably on the blade bearing ring and providing on at least one guide roller a captive securing device which rotatably fixes the guide roller on the blade bearing ring. Due to the rotatable mounting of the guide roller on the blade bearing ring, an adjusting resistor for adjusting the variable turbine and / or compressor geometry can be significantly reduced, since a rolling resistance is usually significantly lower than a comparable sliding resistance at non-rotatably arranged guide rollers.
  • the respectively associated guide roller can moreover be arranged captively on the blade bearing ring, in particular before or during assembly of the adjusting ring, whereby the assembly of the variable turbine and / or compressor geometry and the further assembly steps can be simplified as a whole.
  • it must not be provided on each guide roller an associated captive, but usually only on at least one or two, the other guide rollers are fixed after the assembly of the adjusting ring on this in the axial direction.
  • the adjusting ring on its inner circumference recesses, which are arranged in such a way to the guide rollers, that the adjusting ring in the axial direction on the blade bearing ring can be placed and fixed in the manner of a bayonet lock on this.
  • the vanes can still be mounted on the blade bearing ring and brought with their adjusting levers into engagement with the adjusting ring.
  • the mounting of the adjusting ring on the blade bearing ring in the manner of a bayonet closure can be configured by the invention provided on the inner circumference of the adjusting ring recesses and thus the assembly can be significantly simplified.
  • Fig. 1 has a variable turbine and / or compressor geometry 1 according to the invention a blade bearing ring 2, on which guide vanes 3 (see. Fig. 2 ) are rotatably mounted.
  • the guide vanes 3 pierce the bucket bearing ring 2 with a shovel journal 4 and engage with an adjusting lever 5 in associated adjusting recesses 6 on an adjusting ring 7.
  • the adjusting ring 7 is mounted on the blade bearing ring 2 via rotatable guide rollers 8.
  • At least one of the guide rollers 8 is assigned a captive securing device 9 designed in the manner of a notched nail, which fixes the guide roller 8 rotatably but firmly in the axial direction on the blade bearing ring 2. In the axial direction, of course, this means allowing a small, a twist permitting game.
  • the rotatable arrangement of the guide roller 8 on the blade bearing ring 2 a rotatably connected to the blade bearing ring 2 pin 10 is provided on which the respective associated guide roller 8 is rotatably mounted.
  • the pin 10 has a radial step 11, which is arranged in the installed state in alignment with the surface of the blade bearing ring 2.
  • the individual guide rollers 8 each have a circumferential recess 12, in which the adjusting ring 7 engages with its inner circumference and thereby guided both in the radial direction and in the axial direction.
  • the captive 9 ensures that the guide roller 8 is not unintentionally from the pin 10th slips off, wherein at the same time on the guide roller 8 provided circumferential recess 12 and the adjusting ring 7 can be fixed in the axial direction on the blade bearing ring 2.
  • the adjusting ring 7 has on its inner circumference recesses 13 which are arranged or positioned to the position of the guide rollers 8, that the adjusting ring 7 in the axial direction on the blade bearing ring 2 can be placed and fixed in the manner of a bayonet lock on this is.
  • the inventive variable turbine and / or compressor geometry 1 is also comparatively easy to assemble, in which first the individual guide rollers 8 are rotatably arranged on the blade bearing ring 2 via the associated pins 10. Subsequently, at least two of the guide rollers 8 are fixed in each case via an associated captive 9 on the blade bearing ring 2 in the axial direction, wherein the Axialfix ist can be done for example via a arranged on the captive 9 head 14.
  • the adjusting ring 7 can be positioned with its provided on the inner circumference recesses 13, 13 'to the guide rollers 8 so that it over in the axial direction the guide rollers 8 can be pushed. Subsequently, the adjusting ring 7 is rotated until the guide rollers 8 with not recessed inner peripheral portions 15 of the adjusting ring. 7 cooperate, so that it is connected in the manner of a bayonet closure with the blade bearing ring 2. Subsequently, the guide vanes 3 are still rotatably mounted on the blade bearing ring 2 via the blade journal 4, wherein the adjusting lever 5 are positioned so that they interact with VerstellausEnglish Institute 6 on the adjusting ring 7.
  • variable turbine and / or compressor geometry 1 In general, with the variable turbine and / or compressor geometry 1 according to the invention, an adjustment resistance for adjusting the guide vanes 3 of the variable turbine and / or compressor geometry 1 can be significantly reduced, since the guide rollers 8 are actually rotatably arranged on the blade bearing ring 2 and thereby not only as slide bearings act. At the same time, the assembly of the variable turbine and / or compressor geometry 1 can be simplified by the inventively provided recesses 13,13 '. Such a variable turbine and / or compressor geometry 1 is usually used in charging devices, in particular in exhaust gas turbochargers in internal combustion engines in motor vehicles.

Description

Die vorliegende Erfindung betrifft eine variable Turbinen- und/oder Verdichtergeometrie mit einem Schaufellagerring und drehbar daran bzw. darin gelagerten Leitschaufeln gemäß dem Oberbegriff des Anspruchs 1. Die Erfindung betrifft außerdem eine mit einer derartigen variablen Turbinen- und/oder Verdichtergeometrie ausgestattete Ladeeinrichtung sowie ein Verfahren zur Montage einer derartigen variablen Turbinen- und/oder Verdichtergeometrie.The present invention relates to a variable turbine and / or compressor geometry with a vane ring and rotatably mounted therein or therein vanes according to the preamble of claim 1. The invention also relates to a equipped with such a variable turbine and / or compressor geometry charging device and a method for mounting such a variable turbine and / or compressor geometry.

Aus der WO 2008/118833 ist eine gattungsgemäße variable Turbinen- und/oder Verdichtergeometrie mit einem Schaufellagerring und drehbar daran gelagerten Leitschaufeln bekannt. Die bekannte variable Turbinen- und/oder Verdichtergeometrie weist dabei einen Verstellring zum Verstellen der Leitschaufeln auf, der über Führungsrollen am Schaufellagerring drehbar gelagert ist. Eine Axialfixierung des Verstellrings am Schaufellagerring erfolgt dabei über die Führungsrollen, die ihrerseits drehbar und in Axialrichtung fest am Schaufellagerring angeordnet sind. Nachteilig bei der bekannten variablen Turbinen- und/oder Verdichtergeometrie ist dabei, dass die Führungsrollen lediglich als Gleitlager ausgebildet sind, wodurch ein vergleichsweise hoher Verstellwiderstand beim Verstellen der variablen Turbinen- und/oder Verdichtergeometrie zu überwinden ist. Weitere variable Tubinen-und/oder Verdichtergeometrie gemäß dem Stand der Technik sind aus der DE 10 2007 056 154 A1 bzw. der DE 102 09 172 A1 bekannt.From the WO 2008/118833 is a generic variable turbine and / or compressor geometry with a blade bearing ring and rotatably mounted guide vanes known. The known variable turbine and / or compressor geometry in this case has an adjusting ring for adjusting the guide vanes, which is rotatably mounted on guide rollers on the blade bearing ring. An axial fixation of the adjusting ring on the blade bearing ring takes place via the guide rollers, which in turn are arranged rotatably and fixedly in the axial direction on the blade bearing ring. A disadvantage of the known variable turbine and / or compressor geometry is that the guide rollers are designed only as a plain bearing, whereby a comparatively high adjustment when adjusting the variable turbine and / or compressor geometry is overcome. Other variable tubing and / or compressor geometry according to the prior art are known from the DE 10 2007 056 154 A1 or the DE 102 09 172 A1 known.

Die vorliegende Erfindung beschäftigt sich daher mit dem Problem, für eine gattungsgemäße variable Turbinen- und/oder Verdichtergeometrie eine verbesserte oder zumindest eine alternative Ausführungsform anzugeben, die sich insbesondere durch eine einfache Montage sowie einen geringen Arbeitswiderstand auszeichnet.The present invention therefore deals with the problem of providing for a generic variable turbine and / or compressor geometry an improved or at least one alternative embodiment, which is characterized in particular by a simple assembly and a low resistance to working.

Dieses Problem wird erfindungsgemäß durch die Gegenstände der unabhängigen Ansprüche gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.This problem is solved according to the invention by the subject matters of the independent claims. Advantageous embodiments are the subject of the dependent claims.

Die vorliegende Erfindung beruht auf dem allgemeinen Gedanken, eine Führungsrolle zum Führen eines Verstellrings an einem Schaufellagerring drehbar am Schaufellagerring zu lagern und an zumindest einer Führungsrolle eine Verliersicherung vorzusehen, die die Führungsrolle drehbar am Schaufellagerring fixiert. Durch die drehbare Lagerung der Führungsrolle am Schaufellagerring kann ein Verstellwiderstand zum Verstellen der variablen Turbinen- und/oder Verdichtergeometrie deutlich reduziert werden, da ein Rollwiderstand üblicherweise deutlich geringer ist als ein vergleichbarer Gleitwiderstand bei drehfest angeordneten Führungsrollen. Durch die zumindest eine Verliersicherung kann zudem die jeweils zugehörige Führungsrolle verliersicher am Schaufellagerring angeordnet werden und zwar insbesondere vor oder während der Montage des Verstellrings, wodurch die Montage der variablen Turbinen- und/oder Verdichtergeometrie und die weiteren Montageschritte insgesamt vereinfacht werden kann. Generell muss dabei nicht an jeder Führungsrolle eine zugehörige Verliersicherung vorgesehen sein, sondern üblicherweise lediglich an zumindest einer oder zwei, wobei die anderen Führungsrollen nach erfolgter Montage des Verstellringes über diesen in Axialrichtung fixiert sind.The present invention is based on the general idea of supporting a guide roller for guiding an adjusting ring on a blade bearing ring rotatably on the blade bearing ring and providing on at least one guide roller a captive securing device which rotatably fixes the guide roller on the blade bearing ring. Due to the rotatable mounting of the guide roller on the blade bearing ring, an adjusting resistor for adjusting the variable turbine and / or compressor geometry can be significantly reduced, since a rolling resistance is usually significantly lower than a comparable sliding resistance at non-rotatably arranged guide rollers. Due to the at least one captive securing device, the respectively associated guide roller can moreover be arranged captively on the blade bearing ring, in particular before or during assembly of the adjusting ring, whereby the assembly of the variable turbine and / or compressor geometry and the further assembly steps can be simplified as a whole. In general, it must not be provided on each guide roller an associated captive, but usually only on at least one or two, the other guide rollers are fixed after the assembly of the adjusting ring on this in the axial direction.

Bei einer vorteilhaften Weiterbildung der erfindungsgemäßen Lösung, weist der Verstellring an seinem Innenumfang Ausnehmungen auf, die derart zu den Führungsrollen angeordnet sind, dass der Verstellring in Axialrichtung auf den Schaufellagerring aufsetzbar und in der Art eines Bajonettverschlusses an diesem fixierbar ist. Dies ermöglicht es, die Führungsrollen samt der zugehörigen Verliersicherungen vor dem Verstellring am Schaufellagerring zu montieren, wobei der Verstellring anschließend mit seinen Ausnehmungen derart zu den Führungsrollen positioniert werden kann, dass er axial über diese geschoben und anschließend verdreht werden kann, die Führungsrollen mit nicht ausgenommenen Innenumfangsbereichen des Verstellrings zusammenwirken und dadurch der Verstellring sowohl in Axial- als auch in Radialrichtung geführt ist. Anschließend können noch die Leitschaufeln am Schaufellagerring montiert und mit ihren Verstellhebeln in Eingriff mit dem Verstellring gebracht werden. Generell kann durch die erfindungsgemäßen am Innenumfang des Verstellrings vorgesehenen Ausnehmungen die Montage des Verstellrings am Schaufellagerring in der Art eines Bajonettverschlusses ausgestaltet und dadurch die Montage deutlich vereinfacht werden.In an advantageous development of the solution according to the invention, the adjusting ring on its inner circumference recesses, which are arranged in such a way to the guide rollers, that the adjusting ring in the axial direction on the blade bearing ring can be placed and fixed in the manner of a bayonet lock on this. This makes it possible to mount the guide rollers together with the associated Verliersicherungen before the adjusting ring on the blade bearing ring, the adjusting ring then with its recesses so to the Guide rollers can be positioned so that it can be pushed axially over this and then rotated, the guide rollers cooperate with non-recessed inner peripheral portions of the adjusting ring and thereby the adjusting ring is guided in both the axial and radial directions. Subsequently, the vanes can still be mounted on the blade bearing ring and brought with their adjusting levers into engagement with the adjusting ring. In general, the mounting of the adjusting ring on the blade bearing ring in the manner of a bayonet closure can be configured by the invention provided on the inner circumference of the adjusting ring recesses and thus the assembly can be significantly simplified.

Weitere wichtige Merkmale und Vorteile der Erfindung ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the invention will become apparent from the dependent claims, from the drawings and from the associated figure description with reference to the drawings.

Bevorzugte Ausführungsbeispiele der Erfindung sind in den Zeichnungen dargestellt und werden in der nachfolgenden Beschreibung näher erläutert, wobei sich gleiche Bezugszeichen auf gleiche oder ähnliche oder funktional gleiche Bauteile beziehen.Preferred embodiments of the invention are illustrated in the drawings and will be described in more detail in the following description, wherein like reference numerals refer to the same or similar or functionally identical components.

Dabei zeigen, jeweils schematisch,

Fig. 1
eine erfindungsgemäße variable Turbinen- und/oder Verdichtergeometrie in einer Ansicht,
Fig. 2
eine Schnittdarstellung durch die variable Turbinen- und/oder Verdichtergeometrie entlang der Schnittebene II-II.
Show, in each case schematically,
Fig. 1
a variable turbine and / or compressor geometry according to the invention in a view,
Fig. 2
a sectional view through the variable turbine and / or compressor geometry along the section plane II-II.

Entsprechend der Fig. 1, weist eine erfindungsgemäße variable Turbinen- und/oder Verdichtergeometrie 1 einen Schaufellagerring 2 auf, an welchem Leitschaufeln 3 (vgl. insb. Fig. 2) drehbar gelagert sind. Die Leitschaufeln 3 durchstoßen dabei mit einem Schaufellagerzapfen 4 den Schaufellagerring 2 und greifen mit einem Verstellhebel 5 in zugehörige Verstellausnehmungen 6 an einem Verstellring 7 ein. Durch ein Verdrehen des Verstellrings 7 relativ zum Schaufellagerring 2 werden somit sämtliche Verstellhebel 5 und damit über die jeweiligen Schaufellagerzapfen 4 auch die zugehörigen Leitschaufeln 3 gleichmäßig verstellt. Um dabei einen Verstellwiderstand zum Verstellen der variablen Turbinen- und/oder Verdichtergeometrie 1 so gering wie möglich zu halten, ist der Verstellring 7 über drehbare Führungsrollen 8 am Schaufellagerring 2 gelagert. Zumindest einer der Führungsrollen 8 ist dabei eine in der Art eines Kerbnagels ausgebildete Verliersicherung 9 zugeordnet, die die Führungsrolle 8 drehbar aber in Axialrichtung fest am Schaufellagerring 2 fixiert. In Axialrichtung fest bedeutet hierbei selbstverständlich das Zulassen eines geringen, eine Verdrehung erlaubenden Spiels.According to the Fig. 1 , has a variable turbine and / or compressor geometry 1 according to the invention a blade bearing ring 2, on which guide vanes 3 (see. Fig. 2 ) are rotatably mounted. The guide vanes 3 pierce the bucket bearing ring 2 with a shovel journal 4 and engage with an adjusting lever 5 in associated adjusting recesses 6 on an adjusting ring 7. By rotating the adjusting ring 7 relative to the blade bearing ring 2 thus all the adjusting lever 5 and thus on the respective blade pivot 4 and the associated vanes 3 are adjusted uniformly. In order to keep an adjusting resistor for adjusting the variable turbine and / or compressor geometry 1 as small as possible, the adjusting ring 7 is mounted on the blade bearing ring 2 via rotatable guide rollers 8. In this case, at least one of the guide rollers 8 is assigned a captive securing device 9 designed in the manner of a notched nail, which fixes the guide roller 8 rotatably but firmly in the axial direction on the blade bearing ring 2. In the axial direction, of course, this means allowing a small, a twist permitting game.

Betrachtet man die Fig. 2, so kann man erkennen, dass zur drehbaren Anordnung der Führungsrolle 8 am Schaufellagerring 2 ein drehbar mit dem Schaufellagerring 2 verbundener Stift 10 vorgesehen ist, an welchem die jeweilige zugehörige Führungsrolle 8 drehbar gelagert ist. Dabei weist der Stift 10 eine radiale Stufe 11 auf, die im Einbauzustand fluchtend zur Oberfläche des Schaufellagerrings 2 angeordnet ist. Wie den Fig. 1 und 2 weiter zu entnehmen ist, weisen die einzelnen Führungsrollen 8 jeweils eine Umfangsausnehmung 12 auf, in welche der Verstellring 7 mit seinem Innenumfang eingreift und dadurch sowohl in Radialrichtung als auch in Axialrichtung geführt ist. Die Verliersicherung 9 gewährleistet dabei, dass die Führungsrolle 8 nicht ungewollt vom Stift 10 abrutscht, wobei über die an der Führungsrolle 8 vorgesehene Umfangsausnehmung 12 zugleich auch der Verstellring 7 in Axialrichtung am Schaufellagerring 2 fixiert werden kann.Looking at the Fig. 2 , it can be seen that the rotatable arrangement of the guide roller 8 on the blade bearing ring 2, a rotatably connected to the blade bearing ring 2 pin 10 is provided on which the respective associated guide roller 8 is rotatably mounted. In this case, the pin 10 has a radial step 11, which is arranged in the installed state in alignment with the surface of the blade bearing ring 2. Like that Fig. 1 and 2 can be seen further, the individual guide rollers 8 each have a circumferential recess 12, in which the adjusting ring 7 engages with its inner circumference and thereby guided both in the radial direction and in the axial direction. The captive 9 ensures that the guide roller 8 is not unintentionally from the pin 10th slips off, wherein at the same time on the guide roller 8 provided circumferential recess 12 and the adjusting ring 7 can be fixed in the axial direction on the blade bearing ring 2.

Betrachtet man die Fig. 1, so kann man erkennen, dass der Verstellring 7 an seinem Innenumfang Ausnehmungen 13 aufweist, die derart zur Lage der Führungsrollen 8 angeordnet bzw. positioniert sind, dass der Verstellring 7 in Axialrichtung auf den Schaufellagerring 2 aufsetzbar und in der Art eines Bajonettverschlusses an diesem fixierbar ist. Generell sind dabei bei der gemäß der Fig. 1 dargestellten variablen Turbinen- und/oder Verdichtergeometrie 1 insgesamt fünf Führungsrollen 8 vorgesehen, jedoch nur vier Ausnehmungen 13, wobei die Ausnehmung 13' zumindest so groß ausgebildet ist, dass bei einer fluchtenden Anordnung der übrigen Ausnehmungen 13 zu den jeweiligen Führungsrollen 8 ein axiales Aufschieben des Verstellrings 7 auf den Schaufellagerring 2 möglich ist.Looking at the Fig. 1 , it can be seen that the adjusting ring 7 has on its inner circumference recesses 13 which are arranged or positioned to the position of the guide rollers 8, that the adjusting ring 7 in the axial direction on the blade bearing ring 2 can be placed and fixed in the manner of a bayonet lock on this is. Generally are doing in accordance with the Fig. 1 shown a total of five guide rollers 8, but only four recesses 13, wherein the recess 13 'is at least so large that in an aligned arrangement of the remaining recesses 13 to the respective guide rollers 8, an axial sliding of the Adjusting ring 7 on the blade bearing ring 2 is possible.

Die erfindungsgemäße variable Turbinen- und/oder Verdichtergeometrie 1 ist dabei auch vergleichsweise einfach zu montieren, in dem zunächst die einzelnen Führungsrollen 8 über die zugehörigen Stifte 10 drehbar am Schaufellagerring 2 angeordnet werden. Anschließend werden zumindest zwei der Führungsrollen 8 über jeweils eine zugehörige Verliersicherung 9 am Schaufellagerring 2 in Axialrichtung fixiert, wobei die Axialfixierung beispielsweise über einen an der Verliersicherung 9 angeordneten Kopf 14 erfolgen kann. Sind die einzelnen Führungsrollen 8 am Schaufellagerring 2 montiert und zumindest zwei der Führungsrollen 8 zusätzlich mittels einer zugehörigen Verliersicherung 9 fixiert, kann der Verstellring 7 mit seinen am Innenumfang vorgesehenen Ausnehmungen 13, 13' derart zu den Führungsrollen 8 positioniert werden, dass er in Axialrichtung über die Führungsrollen 8 geschoben werden kann. Anschließend wird der Verstellring 7 solange verdreht, bis die Führungsrollen 8 mit nicht ausgenommenen Innenumfangsbereichen 15 des Verstellrings 7 zusammenwirken, so dass dieser in der Art eines Bajonettverschlusses mit dem Schaufellagering 2 verbunden ist. Anschließend werden noch die Leitschaufeln 3 über die Schaufellagerzapfen 4 drehbar am Schaufellagerring 2 montiert, wobei die Verstellhebel 5 derart positioniert werden, dass sie mit Verstellausnehmungen 6 am Verstellring 7 zusammenwirken.The inventive variable turbine and / or compressor geometry 1 is also comparatively easy to assemble, in which first the individual guide rollers 8 are rotatably arranged on the blade bearing ring 2 via the associated pins 10. Subsequently, at least two of the guide rollers 8 are fixed in each case via an associated captive 9 on the blade bearing ring 2 in the axial direction, wherein the Axialfixierung can be done for example via a arranged on the captive 9 head 14. If the individual guide rollers 8 mounted on the blade bearing ring 2 and at least two of the guide rollers 8 additionally fixed by means of an associated captive 9, the adjusting ring 7 can be positioned with its provided on the inner circumference recesses 13, 13 'to the guide rollers 8 so that it over in the axial direction the guide rollers 8 can be pushed. Subsequently, the adjusting ring 7 is rotated until the guide rollers 8 with not recessed inner peripheral portions 15 of the adjusting ring. 7 cooperate, so that it is connected in the manner of a bayonet closure with the blade bearing ring 2. Subsequently, the guide vanes 3 are still rotatably mounted on the blade bearing ring 2 via the blade journal 4, wherein the adjusting lever 5 are positioned so that they interact with Verstellausnehmungen 6 on the adjusting ring 7.

Generell kann mit der erfindungsgemäßen variablen Turbinen- und/oder Verdichtergeometrie 1 ein Verstellwiderstand zum Verstellen der Leitschaufeln 3 der variablen Turbinen- und/oder Verdichtergeometrie 1 deutlich reduziert werden, da die Führungsrollen 8 tatsächlich drehbar am Schaufellagering 2 angeordnet sind und dadurch nicht nur als Gleitlager fungieren. Zugleich kann durch die erfindungsgemäß vorgesehenen Ausnehmungen 13,13' die Montage der variablen Turbinen- und/oder Verdichtergeometrie 1 vereinfacht werden. Eingesetzt wird eine derartige variable Turbinen- und/oder Verdichtergeometrie 1 üblicherweise in Ladeeinrichtungen, insbesondere in Abgasturboladern bei Verbrennungsmotoren in Kraftfahrzeugen.In general, with the variable turbine and / or compressor geometry 1 according to the invention, an adjustment resistance for adjusting the guide vanes 3 of the variable turbine and / or compressor geometry 1 can be significantly reduced, since the guide rollers 8 are actually rotatably arranged on the blade bearing ring 2 and thereby not only as slide bearings act. At the same time, the assembly of the variable turbine and / or compressor geometry 1 can be simplified by the inventively provided recesses 13,13 '. Such a variable turbine and / or compressor geometry 1 is usually used in charging devices, in particular in exhaust gas turbochargers in internal combustion engines in motor vehicles.

Claims (7)

  1. A variable turbine and/or compressor geometry (1) having
    - a blade bearing ring (2) with guide blades (3) rotatably mounted thereon/therein,
    - an adjusting ring (7) for adjusting the guide blades (3), wherein the adjusting ring (7) is rotatably mounted on the blade bearing ring (2) via guide rollers (8),
    wherein
    - at least one of the guide rollers (8) is rotatably mounted on the blade bearing ring (2),
    - on at least one guide roller (8) a loss prevention device (9) is provided, which rotatably fixes the guide roller (8) on the blade bearing ring (2),
    characterized in that
    - the at least one loss prevention device (9) is designed as notched pin.
  2. The variable turbine and/or compressor geometry according to Claim 1,
    characterized in that
    the adjusting ring (7) on its inner circumference comprises recesses (13, 13') which are arranged to the guide rollers (8) in such a manner that the adjusting ring (7) can be fitted onto the blade bearing ring (2) in axial direction and fixed in the manner of a bayonet closure.
  3. The variable turbine and/or compressor geometry according to Claim 1 or 2,
    characterized in that
    for the rotatable arrangement of the guide roller (8) on the blade bearing ring (2) a pin (10) that is rotatably connected to the blade bearing ring (2) is provided, on which the respective guide roller (8) is rotatably mounted.
  4. The variable turbine and/or compressor geometry according to Claim 3,
    characterized in that
    the pin (10) has a radial step (11) which radially increases in size in the direction of the blade bearing ring (2) and against which in the installation state the guide roller (8) is able to bear.
  5. The variable turbine and/or compressor geometry according to any one of the Claims 1 to 4,
    characterized in that
    the loss prevention device (9) comprises a head (14) with which the associated guide roller (8) is fixed on the blade bearing ring (2) in axial direction.
  6. A charging device, in particular an exhaust gas turbocharger having a variable turbine and/or compressor geometry (1) according to any one of the preceding claims.
  7. A method for the assembly of a variable turbine and/or compressor geometry (1) according to any one of the Claims 1 to 5, wherein
    - the guide rollers (8) are rotatably arranged on the blade bearing ring (2) via pins (10),
    - at least two guide rollers (8) are fixed on the blade bearing ring (2) via a loss prevention device (9) each,
    - the adjusting ring (7) with its recesses (13, 13') provided on the inner circumference is positioned to the guide rollers (8) in such a manner that it can be pushed over the guide rollers (8) in axial direction,
    - the adjusting ring (7) is rotated until the guide rollers (8) interact with non-recessed inner circumferential regions (15) of the adjusting ring (7),
    - the guide blades (3) are mounted, wherein the adjusting levers (5) engage in the associated recesses (6).
EP10189179A 2009-10-31 2010-10-28 Variable geometry turbine and/or compressor Active EP2317081B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009051582 2009-10-31
DE102009052982A DE102009052982A1 (en) 2009-10-31 2009-11-12 Variable turbine and / or compressor geometry

Publications (3)

Publication Number Publication Date
EP2317081A2 EP2317081A2 (en) 2011-05-04
EP2317081A3 EP2317081A3 (en) 2012-04-04
EP2317081B1 true EP2317081B1 (en) 2012-12-05

Family

ID=43385722

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10189179A Active EP2317081B1 (en) 2009-10-31 2010-10-28 Variable geometry turbine and/or compressor

Country Status (2)

Country Link
EP (1) EP2317081B1 (en)
DE (1) DE102009052982A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013213530A1 (en) 2013-07-10 2015-01-15 Bosch Mahle Turbo Systems Gmbh & Co. Kg Method for fixing a guide roller for an adjusting ring of a variable turbine geometry

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9651053B2 (en) 2014-01-24 2017-05-16 Pratt & Whitney Canada Corp. Bleed valve
DE102018210085A1 (en) * 2018-06-21 2019-12-24 Continental Automotive Gmbh Compressor with directly driven variable iris and charging device

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10209172A1 (en) * 2002-03-01 2003-09-18 Daimler Chrysler Ag Exhaust gas turbocharger for combustion engine, has 2 bearing points on same side of feed channel in turbine housing; turbine blade contacts channel wall on opposite side without bearings
DE60226784D1 (en) * 2002-09-05 2008-07-03 Honeywell Int Inc TURBOCHARGER WITH ADJUSTABLE RODS
US7670107B2 (en) 2007-03-26 2010-03-02 Honeywell International Inc. Variable-vane assembly having fixed axial-radial guides and fixed radial-only guides for unison ring
DE102007056154A1 (en) * 2007-11-21 2009-05-28 Bosch Mahle Turbo Systems Gmbh & Co. Kg loader
DE102008007670B4 (en) * 2008-02-06 2021-01-07 BMTS Technology GmbH & Co. KG Control ring for VTG
DE102008014678B4 (en) * 2008-03-18 2014-08-14 Continental Automotive Gmbh Turbocharger with a variable turbine geometry VTG

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013213530A1 (en) 2013-07-10 2015-01-15 Bosch Mahle Turbo Systems Gmbh & Co. Kg Method for fixing a guide roller for an adjusting ring of a variable turbine geometry

Also Published As

Publication number Publication date
DE102009052982A1 (en) 2011-05-05
EP2317081A3 (en) 2012-04-04
EP2317081A2 (en) 2011-05-04

Similar Documents

Publication Publication Date Title
EP2018480B1 (en) Turbocharger
EP1662094B1 (en) Vane assembly for a turbocharger and turbocharger
EP2209969B1 (en) Supercharger device
DE102008014678B4 (en) Turbocharger with a variable turbine geometry VTG
EP1672178B1 (en) Boîtier de turbine d'un turbocompresseur d'échappement à géométrie variable de turbine
EP2002127B1 (en) Preswirl guide device
DE102008007670B4 (en) Control ring for VTG
DE112010004597B4 (en) Turbocharger with variable turbine geometry
DE112012002909T5 (en) turbocharger
EP1734231A1 (en) Turbocharger and nozzle mounting ring therefor
EP3333374B1 (en) Guiding vane adjustment with side-mounted actuation lever and corresponding assembly method
DE112013001527B4 (en) Exhaust gas turbocharger with variable turbine geometry
EP2592239B1 (en) Variable turbine geometry for a charging device and corresponding charging device
EP2317081B1 (en) Variable geometry turbine and/or compressor
EP3524781B1 (en) Connecting device for an adjustable vane of a gas turbine
WO2012045748A1 (en) Variable turbine and/or compressor geometry
EP1462616B1 (en) Assembly for the axial and radial fastening of a guide vane ring in a casing of a turbine engine
EP3106625B1 (en) Variable turbine or compressor geometry for an exhaust-gas turbocharger
EP2500526B1 (en) Adjustment ring of a charging device
DE102010004622B4 (en) Variable turbine and / or compressor geometry
DE102007052735B4 (en) Charging device
DE102004023211A1 (en) Supercharger for internal combustion engine used in motor vehicle, has bearing housing that has axial guide surface for guiding slide bearings, arranged at radial inner surface of adjustment ring, when blade ring carrier turns
EP1391585B1 (en) Turbocharger with variable geometry
DE102008049005A1 (en) Loading device, particularly exhaust-gas turbocharger for internal combustion engine of motor vehicle, has variable turbine geometry which has guide blades rotatably arranged in guide blade carrier
DE102004031986B4 (en) Exhaust gas turbocharger for an internal combustion engine

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

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/46 20060101ALI20120229BHEP

Ipc: F01D 17/16 20060101AFI20120229BHEP

17P Request for examination filed

Effective date: 20120512

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

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

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: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 587413

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121215

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010001803

Country of ref document: DE

Effective date: 20130131

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

Ref country code: HR

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: 20121205

Ref country code: FI

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: 20121205

Ref country code: ES

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: 20130316

Ref country code: LT

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: 20121205

Ref country code: SE

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: 20121205

Ref country code: NO

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: 20130305

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20121205

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: SI

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: 20121205

Ref country code: LV

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: 20121205

Ref country code: PL

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: 20121205

Ref country code: GR

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: 20130306

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

Ref country code: SK

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: 20121205

Ref country code: IS

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: 20130405

Ref country code: EE

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: 20121205

Ref country code: CZ

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: 20121205

Ref country code: RS

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: 20121205

Ref country code: BG

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: 20130305

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

Ref country code: NL

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: 20121205

Ref country code: PT

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: 20130405

Ref country code: RO

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: 20121205

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

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

Ref country code: DK

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: 20121205

26N No opposition filed

Effective date: 20130906

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

Ref country code: CY

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: 20121205

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: 20121205

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010001803

Country of ref document: DE

Effective date: 20130906

BERE Be: lapsed

Owner name: BOSCH MAHLE TURBO SYSTEMS G.M.B.H. & CO. KG

Effective date: 20131031

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

Ref country code: MC

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: 20121205

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: BE

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

Effective date: 20131031

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

Ref country code: IE

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

Effective date: 20131028

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

Ref country code: SM

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: 20121205

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: TR

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: 20121205

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

Ref country code: LI

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

Effective date: 20141031

Ref country code: MK

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: 20121205

Ref country code: LU

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

Effective date: 20131028

Ref country code: HU

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

Effective date: 20101028

Ref country code: CH

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

Effective date: 20141031

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

Ref country code: MT

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: 20121205

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 587413

Country of ref document: AT

Kind code of ref document: T

Effective date: 20151028

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

Ref country code: AT

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

Effective date: 20151028

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502010001803

Country of ref document: DE

Representative=s name: BRP RENAUD UND PARTNER MBB RECHTSANWAELTE PATE, DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 502010001803

Country of ref document: DE

Owner name: BMTS TECHNOLOGY GMBH & CO. KG, DE

Free format text: FORMER OWNER: BOSCH MAHLE TURBO SYSTEMS GMBH & CO. KG, 70376 STUTTGART, DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

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

Ref country code: AL

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: 20121205

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502010001803

Country of ref document: DE

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

Ref country code: FR

Payment date: 20221031

Year of fee payment: 13

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

Ref country code: GB

Payment date: 20221020

Year of fee payment: 13

Ref country code: DE

Payment date: 20221019

Year of fee payment: 13