EP2864641B1 - Turbocompressor - Google Patents

Turbocompressor Download PDF

Info

Publication number
EP2864641B1
EP2864641B1 EP13734691.2A EP13734691A EP2864641B1 EP 2864641 B1 EP2864641 B1 EP 2864641B1 EP 13734691 A EP13734691 A EP 13734691A EP 2864641 B1 EP2864641 B1 EP 2864641B1
Authority
EP
European Patent Office
Prior art keywords
bearing
compressor
shaft
turbocompressor
compressor wheel
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
EP13734691.2A
Other languages
German (de)
French (fr)
Other versions
EP2864641A1 (en
Inventor
Simon Klink
Alister Clay
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.)
Robert Bosch GmbH
Original Assignee
Robert Bosch GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Robert Bosch GmbH filed Critical Robert Bosch GmbH
Publication of EP2864641A1 publication Critical patent/EP2864641A1/en
Application granted granted Critical
Publication of EP2864641B1 publication Critical patent/EP2864641B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/04—Multi-stage pumps specially adapted to the production of a high vacuum, e.g. molecular pumps
    • F04D19/048—Multi-stage pumps specially adapted to the production of a high vacuum, e.g. molecular pumps comprising magnetic bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/051—Axial thrust balancing
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F04D29/058—Bearings magnetic; electromagnetic

Definitions

  • the invention relates to a turbocompressor with a first and a second compressor stage.
  • the compressor stages each have a compressor wheel, which is arranged on a common shaft.
  • the shaft is mounted without contact.
  • Turbo compressors of the type mentioned are known in the art. With the aid of multi-stage compressors, higher densities of a gaseous medium can be achieved at a given volume flow than with simple compressors.
  • magnetic bearings have a number of disadvantages. They are expensive to manufacture and expensive, since on the one hand they require many components, on the other hand, they have to be manufactured with the highest precision. Furthermore, they are difficult to adjust, so they are very expensive even in the assembly. Another disadvantage of magnetic bearings is that they require power to operate, and in the event of power failure, bearing damage can occur.
  • a concrete, prior art device of the type mentioned is a Danfoss Turbocor, which has a two-stage, semi-hermetic centrifugal compressor and non-contact magnetic bearing. Two impellers are arranged on a common shaft without gears.
  • the Danfoss Turbocor can operate over a speed range of 18,000 to 48,000 rpm. operate.
  • the two impellers are arranged approximately in an end quarter of an axially extending shaft.
  • the shaft is supported by three magnetic bearings, two of which are radial bearings and one is an axial bearing. Such storage is very expensive and consumes a lot of space.
  • JP 2001263291 A From the JP 2001263291 A is a rotor supporting structure of a high-speed compressor with axial and radial magnetic bearings known.
  • the WO 2003/040567 A1 discloses a two-stage, electrically driven compressor, wherein between the housings of the two compression stages, a motor is arranged.
  • the US 2012/051952 A1 shows a charging device for a power conversion device with two compressor wheels.
  • the discharge pressures applied to the compressor wheels during operation generate forces that are substantially balanced by the design of the compressor wheels.
  • the object of the invention is thus to provide a turbocompressor of the type mentioned, which has fewer components than conventional turbocompressors, compact builds, is easier to assemble and maintain, and has an improved axial stability.
  • a turbocompressor according to the invention has a first compressor stage, which is equipped with a first compressor wheel.
  • a compressor stage may be a centrifugal compressor, an axial compressor, a cross-flow compressor or other compressor of known type operating with rotating components.
  • the turbocompressor according to the invention has a second compressor stage, which is likewise equipped with a compressor wheel.
  • the second compressor stage is connected downstream of the first compressor stage, so that the output of the first compressor stage is flow-connected to the input of the second compressor stage.
  • the two compressor wheels of the first compressor stage and the second compressor stage are arranged on a common shaft.
  • the shaft is mounted without contact. It is provided that a non-contact bearing of the shaft between the first compressor and the second compressor is arranged.
  • the arrangement of the non-contact bearing between the two compressor wheels allows on the one hand that axial forces are reduced to the bearing, on the other hand it allows a shortening of the shaft, since the bearing of the shaft must be at least partially not provided outside the compressor stages.
  • the bearing has a radially projecting flange on the shaft side. the axially at least partially enclosed by housing-side bearing components.
  • the housing-side bearing components may be magnets, for example.
  • the non-contact bearing may be a magnetic bearing.
  • Magnetic bearings are well suited for the required speeds in turbocompressors.
  • the bearing between the first compressor and the second compressor is the only bearing for supporting the shaft.
  • the turbocompressor according to the invention can be designed so that the bearing has to absorb only small transverse or shear forces and low axial forces, as acting on the shaft forces of the two compressor wheels in opposite directions and each other compensate.
  • the first compressor and the second compressor are aligned with each other such that the respective inputs of the compressor stages are arranged on opposite sides of the shaft. This can be achieved in particular by the fact that the compressor wheels are arranged back to back on the shaft. Such an arrangement also favors a simple assembly or design of the turbocompressor according to the invention with few components.
  • the compressor wheels can also be formed integrally with the shaft.
  • the compressor wheels have substantially the same distance from the bearing. In this way, lateral forces pointing in the radial direction can be compensated for one another on the bearing, so that the bearing is largely shear-free.
  • the bearing may be formed as a combined, non-contact radial and thrust bearing. As a result, even greater stability of the bearing can be achieved even with changing operating states of the turbocompressor.
  • an electric drive and / or a generator can be integrated into the bearing.
  • the turbocompressor can be initially accelerated by means of an electric motor and electrical energy can be obtained from the turbocompressor, for example in order to allow a controlled deceleration of the turbocompressor in the event of a power failure without the non-contact bearing failing.
  • the shaft has a rotationally symmetrical arranged, at least one side open cavity in which a rotor is arranged integrally, wherein a stator protrudes into the cavity.
  • the stator can thus interact with the shaft without contact and it is a combination of non-contact bearing, which usually interacts with the outer sides of the shaft connected to the rotating part of the bearing, and electric motor in a compact design possible.
  • a tip is arranged on a rotation axis of the shaft and has a distance from the shaft of 0 to 5 mm, preferably from 0 to 1 mm.
  • the tip may be formed as a tip of a cone. With the help of such a tip can be an axial support of the non-contact bearing reach, which exerts only a force axially on the shaft, when the bearing is deflected out of the equilibrium position, as can happen, for example, with load changes of the flowing medium.
  • Such a tip can also be arranged on both sides of the shaft.
  • a shaft of a turbocompressor according to the invention described above can thus carry a bearing component of a non-contact bearing and two compressor wheels, which are arranged on the left and right of the bearing component.
  • the compressor wheels can be arranged back to back.
  • the shaft together with compressor wheels can have a symmetrical arrangement of compressor wheels and bearing component with respect to an axial center plane.
  • the bearing component has a radially protruding flange.
  • the shaft may have a cavity in which a rotor of an electric motor is arranged.
  • the compressor wheels and / or the bearing component may be formed integrally with the shaft.
  • Fig. 1 shows a schematic section through a turbocompressor 2.
  • the turbocompressor 2 according to the invention has a first compressor stage 4 and a second compressor stage 6.
  • the first compressor stage has a first compressor wheel 8 and a second compressor wheel 10.
  • the first compressor wheel 8 and the second compressor wheel 10 are formed integrally with a shaft 12.
  • the compressor wheels 8, 10 rotate about a common axis of rotation.
  • the common component with shaft 12, the first compressor wheel 8 and the second compressor wheel 10 is mounted by means of a magnetic bearing 14.
  • the magnetic bearing 14 has a shaft-side bearing part 16 and a housing-side bearing part 18. Between the two bearing parts is an air gap 20th
  • the first compressor stage 4 has an inlet 22, through which the gaseous medium to be compressed flows into the turbocompressor 2. The medium is accelerated through the first compressor wheel to the outside and then compressed in a diffuser 24 and discharged radially outward.
  • the first compressor stage is sealed by means of a wall 26 to the outside.
  • a media-leading channel is formed on the outside by means of the wall 26 and inside by the housing-side bearing part 18 of the magnetic bearing 14.
  • the precompressed air is fed via an output 28 of the first compressor stage to an input 30 of the second compressor stage and there accelerated a second time by means of the second compressor wheel 10 and compressed by means of a further diffuser 32.
  • Radially outward lying in the second compressor stage is also a channel with a wall 34 and the housing-side bearing member 18 is formed.
  • the compressed medium leaves the second compressor stage 6 through an outlet 36.
  • the magnetic bearing 14 according to the invention may be formed simultaneously as a motor, wherein the housing-side bearing member 18 then forms the stator and the shaft-side bearing member 16 in this case, a rotor.
  • Fig. 2 is the magnetic bearing 14 compared to the example according to Fig. 1 extended by a radially projecting flange 38, which is assigned to the shaft-side bearing member 16.
  • a groove 40 is provided for this purpose, within which the flange 38 is arranged. This embodiment additionally stabilizes the bearing 14 axially.
  • the non-contact magnetic bearing 14 is axially stabilized by a cone 42, which is arranged with its tip 44 of the shaft 12 assigned.
  • the tip 44 lies substantially on the axis of rotation of the shaft 12.
  • Tip 44 and shaft 12 are very closely spaced, preferably less than 1 mm. Shaft 12 and tip 44 thus come into abutment only when the shaft-compressor wheel unit is axially deflected.
  • the cone 42 with its tip 44 thus form an axial support for the compressor.
  • the bearing 14 is designed as a pure bearing.
  • a drive motor 46 for the two compressor stages 4, 6 is provided in the shaft 12.
  • the shaft 12 has for this purpose a coaxially arranged cavity 48, in the interior of which a rotor 50 is arranged.
  • Into the cavity 48 protrudes in likewise concentrically arranged shaft 52, on which a stator 54 is arranged.
  • the motor 46 may also serve as a generator.

Description

Die Erfindung betrifft einen Turboverdichter mit einer ersten und einer zweiten Verdichterstufe. Die Verdichterstufen weisen jeweils ein Verdichterrad auf, welches auf einer gemeinsamen Welle angeordnet ist. Die Welle ist dabei berührungsfrei gelagert.The invention relates to a turbocompressor with a first and a second compressor stage. The compressor stages each have a compressor wheel, which is arranged on a common shaft. The shaft is mounted without contact.

Turboverdichter der eingangs genannten Art sind im Stand der Technik bekannt. Mit Hilfe von mehrstufigen Verdichtern lassen sich höhere Verdichtungen eines gasförmigen Mediums bei vorgegebenem Volumenstrom erreichen als mit einfachen Verdichtern.Turbo compressors of the type mentioned are known in the art. With the aid of multi-stage compressors, higher densities of a gaseous medium can be achieved at a given volume flow than with simple compressors.

Es ist des Weiteren bekannt, die Verdichterräder der entsprechenden Verdichterstufen auf einer gemeinsamen Welle anzuordnen, um die Teilemenge zu reduzieren.It is also known to arrange the compressor wheels of the respective compressor stages on a common shaft to reduce the amount of parts.

Darüber hinaus ist bekannt, dass Verdichter für kleinere Volumenströme mit hohen Drehzahlen betrieben werden müssen. Derartige hohe Drehzahlen können jedoch Probleme bei der Lagerung der beweglichen Teile mit sich bringen, sodass teilweise auf aufwendige, hochdrehzahlfeste Lagerungen zurückgegriffen werden muss. Für derartige Anwendungen ist es bekannt, Magnetlager zu verwenden.In addition, it is known that compressors for smaller volume flows must be operated at high speeds. However, such high speeds can bring problems in the storage of the moving parts with it, so that sometimes has to resort to expensive, high-speed bearings. For such applications it is known to use magnetic bearings.

Magnetlager haben jedoch eine Reihe von Nachteilen. Sie sind aufwendig herzustellen und teuer, da sie einerseits viele Bauteile benötigen, andererseits mit höchster Präzision gefertigt werden müssen. Des Weiteren sind sie schwierig zu justieren, sodass sie auch in der Montage sehr aufwendig sind. Ein weiterer Nachteil von Magnetlagern ist, dass sie zum Betrieb Strom benötigen, und bei Stromausfällen Lagerschäden entstehen können.However, magnetic bearings have a number of disadvantages. They are expensive to manufacture and expensive, since on the one hand they require many components, on the other hand, they have to be manufactured with the highest precision. Furthermore, they are difficult to adjust, so they are very expensive even in the assembly. Another disadvantage of magnetic bearings is that they require power to operate, and in the event of power failure, bearing damage can occur.

Eine konkrete, vorbekannte Vorrichtung der eingangs genannten Art ist ein Danfoss-Turbocor, der einen zweistufigen, halbhermetischen Zentrifugalverdichter und berührungsfreie Magnetlager aufweist. Zwei Impeller sind auf einer gemeinsamen Welle ohne Getriebe angeordnet. Der Danfoss-Turbocor kann über einen Drehzahlbereich von 18 000 bis 48 000 U/min. betrieben werden. Die beiden Impeller sind in etwa in einem endseitigen Viertel einer sich axial lang erstreckenden Welle angeordnet. Die Welle ist mittels dreier Magnetlager gelagert, von denen zwei radiale Lager sind und eines ein axiales Lager ist. Eine derartige Lagerung ist sehr aufwendig und verbraucht viel Platz.A concrete, prior art device of the type mentioned is a Danfoss Turbocor, which has a two-stage, semi-hermetic centrifugal compressor and non-contact magnetic bearing. Two impellers are arranged on a common shaft without gears. The Danfoss Turbocor can operate over a speed range of 18,000 to 48,000 rpm. operate. The two impellers are arranged approximately in an end quarter of an axially extending shaft. The shaft is supported by three magnetic bearings, two of which are radial bearings and one is an axial bearing. Such storage is very expensive and consumes a lot of space.

Aus der JP 2001263291 A ist eine Rotor stützende Struktur eines hochdrehenden Kompressors mit axialen und radialen Magnetlagern bekannt.From the JP 2001263291 A is a rotor supporting structure of a high-speed compressor with axial and radial magnetic bearings known.

Die WO 2003/040567 A1 offenbart einen zweistufigen, elektrisch angetriebenen Kompressor, wobei zwischen den Gehäusen der beiden Verdichtungsstufen ein Motor angeordnet ist.The WO 2003/040567 A1 discloses a two-stage, electrically driven compressor, wherein between the housings of the two compression stages, a motor is arranged.

Die US 2012/051952 A1 zeigt eine Aufladeeinrichtung für eine Energieumwandlungseinrichtung mit zwei Verdichterrädern. Die im Betrieb an den Verdichterrädern anliegenden Austrittsdrücke generieren Kräfte, die durch die Gestaltung der Verdichterräder im Wesentlichen ausgeglichen sind.The US 2012/051952 A1 shows a charging device for a power conversion device with two compressor wheels. The discharge pressures applied to the compressor wheels during operation generate forces that are substantially balanced by the design of the compressor wheels.

Aufgabe der Erfindung ist es somit, einen Turboverdichter der eingangs genannten Art anzugeben, der weniger Bauteile als herkömmliche Turboverdichter aufweist, kompakter baut, einfacher zu montieren und zu warten ist, und der eine verbesserte axiale Stabilität aufweist.The object of the invention is thus to provide a turbocompressor of the type mentioned, which has fewer components than conventional turbocompressors, compact builds, is easier to assemble and maintain, and has an improved axial stability.

Die Aufgabe wird gelöst durch einen Turboverdichter nach Anspruch 1. Weitere Ausgestaltungen der Erfindung sind Gegenstand der Unteransprüche.The object is achieved by a turbocompressor according to claim 1. Further embodiments of the invention are the subject of the dependent claims.

Ein erfindungsgemäßer Turboverdichter weist eine erste Verdichterstufe auf, welche mit einem ersten Verdichterrad ausgestattet ist. Eine solche Verdichterstufe kann ein Radialverdichter, ein Axialverdichter, ein Querstromverdichter oder ein anderer Verdichter bekannten Typs sein, der mit rotierenden Bauteilen arbeitet.A turbocompressor according to the invention has a first compressor stage, which is equipped with a first compressor wheel. Such a compressor stage may be a centrifugal compressor, an axial compressor, a cross-flow compressor or other compressor of known type operating with rotating components.

Der erfindungsgemäße Turboverdichter weist eine zweite Verdichterstufe auf, die ebenfalls mit einem Verdichterrad ausgestattet ist. Auch hier kann aus den verschiedenen bekannten Grundprinzipien ausgewählt werden. Die zweite Verdichterstufe ist der ersten Verdichterstufe nachgeschaltet, sodass der Ausgang der ersten Verdichterstufe mit dem Eingang der zweiten Verdichterstufe strömungsverbunden ist.The turbocompressor according to the invention has a second compressor stage, which is likewise equipped with a compressor wheel. Here, too, can be selected from the various known basic principles. The second compressor stage is connected downstream of the first compressor stage, so that the output of the first compressor stage is flow-connected to the input of the second compressor stage.

Die beiden Verdichterräder der ersten Verdichterstufe und der zweiten Verdichterstufe sind auf einer gemeinsamen Welle angeordnet. Die Welle ist berührungsfrei gelagert. Dabei ist vorgesehen, dass ein berührungsfreies Lager der Welle zwischen dem ersten Verdichterrad und dem zweiten Verdichterrad angeordnet ist. Die Anordnung des berührungsfreien Lagers zwischen den beiden Verdichterrädern ermöglicht einerseits, dass axiale Kräfte auf das Lager verringert sind, andererseits ermöglicht es eine Verkürzung der Welle, da die Lagerung der Welle zumindest teilweise nicht außerhalb der Verdichterstufen vorgesehen sein muss.The two compressor wheels of the first compressor stage and the second compressor stage are arranged on a common shaft. The shaft is mounted without contact. It is provided that a non-contact bearing of the shaft between the first compressor and the second compressor is arranged. The arrangement of the non-contact bearing between the two compressor wheels allows on the one hand that axial forces are reduced to the bearing, on the other hand it allows a shortening of the shaft, since the bearing of the shaft must be at least partially not provided outside the compressor stages.

Erfindungsgemäß weist das Lager wellenseitig einen radial hervorstehenden Flansch auf. der axial zumindest teilweise von gehäuseseitigen Lagerkomponenten umschlossen ist. Die gehäuseseitigen Lagerkomponenten können beispielsweise Magneten sein.According to the invention, the bearing has a radially projecting flange on the shaft side. the axially at least partially enclosed by housing-side bearing components. The housing-side bearing components may be magnets, for example.

Gemäß einer ersten möglichen Ausgestaltung des erfindungsgemäßen Turboverdichters kann das berührungsfreie Lager ein Magnetlager sein. Magnetlager sind für die benötigten Drehzahlen in Turboverdichtern gut geeignet.According to a first possible embodiment of the turbocompressor according to the invention, the non-contact bearing may be a magnetic bearing. Magnetic bearings are well suited for the required speeds in turbocompressors.

Gemäß einer weiteren möglichen Ausgestaltung der Erfindung kann vorgesehen sein, dass das Lager zwischen dem ersten Verdichterrad und dem zweiten Verdichterrad das einzige Lager zur Lagerung der Welle ist. Dadurch, dass beiderseits des Lagers Verdichterräder angeordnet sind, kann der erfindungsgemäße Turboverdichter so ausgelegt werden, dass das Lager nur geringe Quer- bzw. Scherkräfte und geringe axiale Kräfte aufnehmen muss, da auf die Welle wirkende Kräfte der beiden Verdichterräder in entgegengesetzte Richtungen zeigen und gegenseitig kompensieren.According to another possible embodiment of the invention can be provided that the bearing between the first compressor and the second compressor is the only bearing for supporting the shaft. Characterized in that compressor wheels are arranged on both sides of the bearing, the turbocompressor according to the invention can be designed so that the bearing has to absorb only small transverse or shear forces and low axial forces, as acting on the shaft forces of the two compressor wheels in opposite directions and each other compensate.

Des Weiteren lässt sich hierdurch eine erhebliche Reduktion der Länge der die Verdichterräder tragenden Welle erreichen. Dies reduziert weiterhin die Trägheit des erfindungsgemäßen Turboverdichters und verringert damit zudem die benötigte Anlaufenergie.Furthermore, this can achieve a considerable reduction in the length of the shaft carrying the compressor wheels. This further reduces the inertia of the turbocompressor according to the invention and thus also reduces the required starting energy.

Gemäß einer weiteren möglichen Ausgestaltung der Erfindung kann vorgesehen sein, dass das erste Verdichterrad und das zweite Verdichterrad derart zueinander ausgerichtet sind, dass die jeweiligen Eingänge der Verdichterstufen auf gegenüberliegenden Seiten der Welle angeordnet sind. Dies kann insbesondere dadurch erreicht werden, dass die Verdichterräder Rücken an Rücken auf der Welle angeordnet sind. Eine derartige Anordnung begünstigt darüber hinaus eine einfache Montage bzw. Ausgestaltung des erfindungsgemäßen Turboverdichters mit wenigen Bauteilen.According to another possible embodiment of the invention can be provided that the first compressor and the second compressor are aligned with each other such that the respective inputs of the compressor stages are arranged on opposite sides of the shaft. This can be achieved in particular by the fact that the compressor wheels are arranged back to back on the shaft. Such an arrangement also favors a simple assembly or design of the turbocompressor according to the invention with few components.

Vorteilhafterweise können die Verdichterräder auch einstückig mit der Welle ausgebildet sein.Advantageously, the compressor wheels can also be formed integrally with the shaft.

Gemäß einer weiteren Ausgestaltung der Erfindung kann vorgesehen sein, dass die Verdichterräder im Wesentlichen denselben Abstand zum Lager aufweisen. Auf diese Weise lassen sich in radiale Richtung weisende Querkräfte auf das Lager gegenseitig kompensieren, sodass das Lager weitgehend scherkräftefrei ist.According to a further embodiment of the invention can be provided that the compressor wheels have substantially the same distance from the bearing. In this way, lateral forces pointing in the radial direction can be compensated for one another on the bearing, so that the bearing is largely shear-free.

Gemäß einer weiteren möglichen Ausgestaltung der Erfindung kann das Lager als kombiniertes, berührungsfreies Radial- und Axiallager ausgebildet sein. Hierdurch lässt sich eine noch höhere Stabilität des Lagers auch bei wechselnden Betriebszuständen des Turboverdichters erreichen.According to another possible embodiment of the invention, the bearing may be formed as a combined, non-contact radial and thrust bearing. As a result, even greater stability of the bearing can be achieved even with changing operating states of the turbocompressor.

Gemäß einer weiteren möglichen Ausgestaltung der Erfindung kann ein Elektroantrieb und/oder ein Generator in das Lager integriert sein. Auf diese Weise kann der Turboverdichter mittels eines Elektromotors anfänglich beschleunigt werden und es kann elektrische Energie aus dem Turboverdichter gewonnen werden, beispielsweise um bei einem Stromausfall ein kontrolliertes Abbremsen des Turboverdichters zu ermöglichen, ohne dass das berührungslose Lager versagt.According to another possible embodiment of the invention, an electric drive and / or a generator can be integrated into the bearing. In this way, the turbocompressor can be initially accelerated by means of an electric motor and electrical energy can be obtained from the turbocompressor, for example in order to allow a controlled deceleration of the turbocompressor in the event of a power failure without the non-contact bearing failing.

Gemäß einer weiteren möglichen Ausgestaltung der Erfindung kann vorgesehen sein, dass die Welle eine rotationssymmetrisch angeordneten, wenigstens einseitig offenen Hohlraum aufweist, in dem ein Rotor integriert angeordnet ist, wobei ein Stator in den Hohlraum hineinragt. Der Stator kann auf diese Weise berührungsfrei mit der Welle zusammenwirken und es ist eine Kombination von berührungslosem Lager, das üblicherweise mit den Außenseiten des mit der Welle verbundenen, drehenden Teils des Lagers wechselwirkt, und Elektromotor in kompakter Ausgestaltung möglich.According to another possible embodiment of the invention can be provided that the shaft has a rotationally symmetrical arranged, at least one side open cavity in which a rotor is arranged integrally, wherein a stator protrudes into the cavity. The stator can thus interact with the shaft without contact and it is a combination of non-contact bearing, which usually interacts with the outer sides of the shaft connected to the rotating part of the bearing, and electric motor in a compact design possible.

Gemäß einer weiteren möglichen Ausgestaltung der Erfindung kann vorgesehen sein, dass eine Spitze auf einer Rotationsachse der Welle angeordnet ist und einen Abstand zur Welle von 0 bis 5 mm, bevorzugt von 0 bis 1 mm aufweist. Die Spitze kann als Spitze eines Konus ausgebildet sein. Mit Hilfe einer derartigen Spitze lässt sich eine Axialabstützung des berührungsfreien Lagers erreichen, die nur dann axial eine Kraft auf die Welle ausübt, wenn das Lager aus der Gleichgewichtslage heraus ausgelenkt wird, wie dies beispielsweise bei Lastwechseln des strömenden Mediums geschehen kann. Eine derartige Spitze kann auch beiderseits der Welle angeordnet sein.According to another possible embodiment of the invention can be provided that a tip is arranged on a rotation axis of the shaft and has a distance from the shaft of 0 to 5 mm, preferably from 0 to 1 mm. The tip may be formed as a tip of a cone. With the help of such a tip can be an axial support of the non-contact bearing reach, which exerts only a force axially on the shaft, when the bearing is deflected out of the equilibrium position, as can happen, for example, with load changes of the flowing medium. Such a tip can also be arranged on both sides of the shaft.

Eine Welle eines Turboverdichters gemäß der zuvor beschriebenen Erfindung kann also eine Lagerkomponente eines berührungsfreien Lagers sowie zwei Verdichterräder tragen, die links und rechts des Lagerbestandteils angeordnet sind. Die Verdichterräder können Rücken an Rücken angeordnet sein. Die Welle nebst Verdichterrädern kann des Weiteren, bezogen auf eine axiale Mittelebene eine symmetrische Anordnung von Verdichterrädern und Lagerbestandteil aufweisen. Der Lagerbestandteil weist einen radial hervorstehenden Flansch auf. Des Weiteren kann die Welle einen Hohlraum aufweisen, in dem ein Rotor eines Elektromotors angeordnet ist. Die Verdichterräder und/oder der Lagerbestandteil können einstückig mit der Welle ausgebildet sein.A shaft of a turbocompressor according to the invention described above can thus carry a bearing component of a non-contact bearing and two compressor wheels, which are arranged on the left and right of the bearing component. The compressor wheels can be arranged back to back. Furthermore, the shaft together with compressor wheels can have a symmetrical arrangement of compressor wheels and bearing component with respect to an axial center plane. The bearing component has a radially protruding flange. Furthermore, the shaft may have a cavity in which a rotor of an electric motor is arranged. The compressor wheels and / or the bearing component may be formed integrally with the shaft.

Weitere Ziele, Vorteile, Merkmale und Anwendungsmöglichkeiten der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung eines Ausführungsbeispiels anhand der Zeichnung. Dabei bilden alle beschriebenen und/oder bildlich dargestellten Merkmale für sich oder in beliebiger sinnvoller Kombination den Gegenstand der vorliegenden Erfindung, auch unabhängig von ihrer Zusammenfassung in den Ansprüchen oder deren Rückbeziehung.Other objects, advantages, features and applications of the present invention will become apparent from the following description of an embodiment with reference to the drawings. All described and / or illustrated features alone or in any meaningful combination form the subject matter of the present invention, also independent of their summary in the claims or their dependency.

Die Erfindung wird anhand mehrerer Ausführungsbeispiele erläutert. Dabei zeigen schematisch:

Fig. 1
einen Schnitt durch einen zweistufigen Turboverdichter,
Fig. 2
einen Schnitt durch einen erfindungsgemäßen Turboverdichter gemäß einer Ausführungsform,
Fig. 3
einen Schnitt durch einen Turboverdichter gemäß einem nicht beanspruchten Beispiel, sowie
Fig. 4
einen Schnitt durch einen Turboverdichter gemäß einem nicht beanspruchten Beispiel.
The invention will be explained with reference to several embodiments. Here are shown schematically:
Fig. 1
a section through a two-stage turbocompressor,
Fig. 2
a section through a turbocompressor according to the invention according to an embodiment,
Fig. 3
a section through a turbocompressor according to a non-claimed example, as well
Fig. 4
a section through a turbocompressor according to a non-claimed example.

In den nachfolgenden Figuren werden gleiche oder gleich wirkende Bauteile zur einfacheren Lesbarkeit mit gleichen Bezugszeichen versehen.In the following figures, the same or equivalent components are provided with the same reference numerals for ease of reading.

Fig. 1 zeigt einen schematischen Schnitt durch einen Turboverdichter 2. Der erfindungsgemäße Turboverdichter 2 weist eine erste Verdichterstufe 4 und eine zweite Verdichterstufe 6 auf. Die erste Verdichterstufe weist ein erstes Verdichterrad 8 sowie ein zweites Verdichterrad 10 auf. Das erste Verdichterrad 8 und das zweite Verdichterrad 10 sind einstückig mit einer Welle 12 ausgebildet. Die Verdichterräder 8, 10 rotieren um eine gemeinsame Drehachse. Fig. 1 shows a schematic section through a turbocompressor 2. The turbocompressor 2 according to the invention has a first compressor stage 4 and a second compressor stage 6. The first compressor stage has a first compressor wheel 8 and a second compressor wheel 10. The first compressor wheel 8 and the second compressor wheel 10 are formed integrally with a shaft 12. The compressor wheels 8, 10 rotate about a common axis of rotation.

Das gemeinsame Bauteil mit Welle 12, erstem Verdichterrad 8 und zweitem Verdichterrad 10 ist mittels eines Magnetlagers 14 gelagert. Das Magnetlager 14 weist ein wellenseitiges Lagerteil 16 und ein gehäuseseitiges Lagerteil 18 auf. Zwischen den beiden Lagerteilen befindet sich ein Luftspalt 20.The common component with shaft 12, the first compressor wheel 8 and the second compressor wheel 10 is mounted by means of a magnetic bearing 14. The magnetic bearing 14 has a shaft-side bearing part 16 and a housing-side bearing part 18. Between the two bearing parts is an air gap 20th

Die erste Verdichterstufe 4 weist einen Eingang 22 auf, durch die das zu verdichtende gasförmige Medium in den Turboverdichter 2 einströmt. Das Medium wird durch das erste Verdichterrad nach außen beschleunigt und dann in einem Diffusor 24 verdichtet und radial nach außen abgeführt. Hierzu ist die erste Verdichterstufe mittels einer Wandung 26 nach außen abgedichtet. Ein Medien führender Kanal wird außen mittels der Wandung 26 und innen durch das gehäuseseitige Lagerteil 18 des Magnetlagers 14 gebildet.The first compressor stage 4 has an inlet 22, through which the gaseous medium to be compressed flows into the turbocompressor 2. The medium is accelerated through the first compressor wheel to the outside and then compressed in a diffuser 24 and discharged radially outward. For this purpose, the first compressor stage is sealed by means of a wall 26 to the outside. A media-leading channel is formed on the outside by means of the wall 26 and inside by the housing-side bearing part 18 of the magnetic bearing 14.

Die vorkomprimierte Luft wird über einen Ausgang 28 der ersten Verdichterstufe einem Eingang 30 der zweiten Verdichterstufe zugeführt und dort mittels des zweiten Verdichterrades 10 ein weiteres Mal beschleunigt und mittels eines weiteren Diffusors 32 verdichtet. Radial außen liegend in der zweiten Verdichterstufe ist ebenfalls ein Kanal mit einer Wandung 34 und dem gehäuseseitigen Lagerteil 18 gebildet. Das komprimierte Medium verlässt die zweite Verdichterstufe 6 durch einen Ausgang 36.The precompressed air is fed via an output 28 of the first compressor stage to an input 30 of the second compressor stage and there accelerated a second time by means of the second compressor wheel 10 and compressed by means of a further diffuser 32. Radially outward lying in the second compressor stage is also a channel with a wall 34 and the housing-side bearing member 18 is formed. The compressed medium leaves the second compressor stage 6 through an outlet 36.

Das erfindungsgemäße Magnetlager 14 kann gleichzeitig als Motor ausgebildet sein, wobei das gehäuseseitige Lagerteil 18 dann den Stator bildet und das wellenseitige Lagerteil 16 in diesem Fall einen Rotor.The magnetic bearing 14 according to the invention may be formed simultaneously as a motor, wherein the housing-side bearing member 18 then forms the stator and the shaft-side bearing member 16 in this case, a rotor.

Gemäß Fig. 2 ist das Magnetlager 14 gegenüber dem Beispiel gemäß Fig. 1 durch einen radial hervorstehenden Flansch 38 erweitert, der dem wellenseitigen Lagerteil 16 zuzuordnen ist. In dem gehäuseseitigen Lagerteil 18 ist hierzu eine Nut 40 vorgesehen, innerhalb derer der Flansch 38 angeordnet ist. Diese Ausgestaltung stabilisiert das Lager 14 zusätzlich axial.According to Fig. 2 is the magnetic bearing 14 compared to the example according to Fig. 1 extended by a radially projecting flange 38, which is assigned to the shaft-side bearing member 16. In the housing-side bearing part 18, a groove 40 is provided for this purpose, within which the flange 38 is arranged. This embodiment additionally stabilizes the bearing 14 axially.

In dem Beispiel gemäß Fig. 3 ist das berührungslose Magnetlager 14 axial durch einen Konus 42 stabilisiert, der mit seiner Spitze 44 der Welle 12 zugewiesen angeordnet ist. Die Spitze 44 liegt im Wesentlichen auf der Drehachse der Welle 12. Spitze 44 und Welle 12 sind sehr dicht zueinander beabstandet, bevorzugt weniger als 1 mm. Welle 12 und Spitze 44 kommen somit nur dann in Anlage, wenn die Welle-Verdichterrad-Einheit axial ausgelenkt wird. Der Konus 42 mit seiner Spitze 44 bilden somit eine axiale Abstützung für den Verdichter.In the example according to Fig. 3 the non-contact magnetic bearing 14 is axially stabilized by a cone 42, which is arranged with its tip 44 of the shaft 12 assigned. The tip 44 lies substantially on the axis of rotation of the shaft 12. Tip 44 and shaft 12 are very closely spaced, preferably less than 1 mm. Shaft 12 and tip 44 thus come into abutment only when the shaft-compressor wheel unit is axially deflected. The cone 42 with its tip 44 thus form an axial support for the compressor.

In dem Beispiel gemäß Fig. 4 ist das Lager 14 als reines Lager ausgebildet. Ein Antriebsmotor 46 für die beiden Verdichterstufen 4, 6 ist in der Welle 12 vorgesehen. Die Welle 12 weist dazu einen koaxial angeordneten Hohlraum 48 auf, in dessen Inneren ein Rotor 50 angeordnet ist. In den Hohlraum 48 ragt in ebenfalls konzentrisch angeordneter Schaft 52 ein, an dem ein Stator 54 angeordnet ist. Der Motor 46 kann auch als Generator dienen.In the example according to Fig. 4 the bearing 14 is designed as a pure bearing. A drive motor 46 for the two compressor stages 4, 6 is provided in the shaft 12. The shaft 12 has for this purpose a coaxially arranged cavity 48, in the interior of which a rotor 50 is arranged. Into the cavity 48 protrudes in likewise concentrically arranged shaft 52, on which a stator 54 is arranged. The motor 46 may also serve as a generator.

Claims (7)

  1. Turbocompressor having a first compressor stage (4), which has a first compressor wheel (8), and having a second compressor stage (6), which has a second compressor wheel (10), wherein the first compressor wheel (8) and the second compressor wheel (10) are arranged on a common shaft (12), wherein the shaft (12) is mounted in contactless fashion, wherein a contactless bearing (14) of the shaft (12) is arranged between the first compressor wheel (8) and the second compressor wheel (10),
    characterized in that the bearing (14) has, at the shaft side, a radially protruding flange (38) which is axially at least partially surrounded by housing-side bearing components (18, 40).
  2. Turbocompressor according to Claim 1,
    characterized in that the contactless bearing is a magnetic bearing (14).
  3. Turbocompressor according to Claim 1 or 2,
    characterized in that the shaft (12) is mounted only by means of the contactless bearing (14).
  4. Turbocompressor according to any of the preceding claims,
    characterized in that the first compressor wheel (8) and the second compressor wheel (10) are oriented such that the respective inputs (22, 30) of the compressor stages (4, 6) are arranged on opposite sides of the shaft (12).
  5. Turbocompressor according to Claim 4,
    characterized in that the compressor wheels (8, 10) have substantially the same spacing to the bearing (14) .
  6. Turbocompressor according to any of the preceding claims,
    characterized in that the bearing (14) is designed as a combined contactless radial and axial bearing.
  7. Turbocompressor according to any of the preceding claims,
    characterized in that an electric drive (46) and/or a generator is integrated into the bearing (14).
EP13734691.2A 2012-06-26 2013-06-25 Turbocompressor Active EP2864641B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012012540.2A DE102012012540A1 (en) 2012-06-26 2012-06-26 Turbo compressor
PCT/EP2013/063200 WO2014001286A1 (en) 2012-06-26 2013-06-25 Turbocompressor

Publications (2)

Publication Number Publication Date
EP2864641A1 EP2864641A1 (en) 2015-04-29
EP2864641B1 true EP2864641B1 (en) 2019-08-07

Family

ID=48748177

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13734691.2A Active EP2864641B1 (en) 2012-06-26 2013-06-25 Turbocompressor

Country Status (5)

Country Link
US (1) US20150219106A1 (en)
EP (1) EP2864641B1 (en)
CN (1) CN104379939A (en)
DE (1) DE102012012540A1 (en)
WO (1) WO2014001286A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014224283A1 (en) * 2014-11-27 2016-06-02 Robert Bosch Gmbh Compressor with a sealing channel
DE102014224285A1 (en) 2014-11-27 2016-06-02 Robert Bosch Gmbh Compressor with a sealing channel
DE102014224757A1 (en) 2014-12-03 2016-06-09 Robert Bosch Gmbh Compressor with a sealing channel
DE102017202658A1 (en) 2017-02-20 2018-08-23 Ford Global Technologies, Llc Compressor and motor vehicle

Family Cites Families (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2438426A (en) * 1939-12-19 1948-03-23 Power Jets Res & Dev Ltd Centrifugal compressor
US2944785A (en) * 1955-05-18 1960-07-12 Thompson Ramo Wooldridge Inc Impeller for turbine engine and the like
US2960825A (en) * 1955-10-19 1960-11-22 Thompson Ramo Wooldridge Inc Reexpansion gas turbine engine with differential compressor drive
US3210044A (en) * 1963-06-19 1965-10-05 Morita Mfg Closed type air turbine having air bearings
US3647324A (en) * 1969-12-18 1972-03-07 Edson Howard Rafferty Electrically driven pumps capable of use as heart pumps
DE2337226A1 (en) * 1973-07-21 1975-02-06 Maschf Augsburg Nuernberg Ag VACUUM PUMP WITH A RUNNER MOUNTED INSIDE THEIR HOUSING
JPS55145816A (en) * 1979-04-28 1980-11-13 Mitsubishi Precision Co Ltd Magnetically floatingly supported rotary wheel
US4688998A (en) * 1981-03-18 1987-08-25 Olsen Don B Magnetically suspended and rotated impellor pump apparatus and method
US5078741A (en) * 1986-10-12 1992-01-07 Life Extenders Corporation Magnetically suspended and rotated rotor
US4530639A (en) * 1984-02-06 1985-07-23 A/S Kongsberg Vapenfabrikk Dual-entry centrifugal compressor
US4884942A (en) * 1986-06-30 1989-12-05 Atlas Copco Aktiebolag Thrust monitoring and balancing apparatus
US4779614A (en) * 1987-04-09 1988-10-25 Nimbus Medical, Inc. Magnetically suspended rotor axial flow blood pump
US5112202A (en) * 1990-01-31 1992-05-12 Ntn Corporation Turbo pump with magnetically supported impeller
US5195877A (en) * 1990-10-05 1993-03-23 Kletschka Harold D Fluid pump with magnetically levitated impeller
US5470208A (en) * 1990-10-05 1995-11-28 Kletschka; Harold D. Fluid pump with magnetically levitated impeller
US5055005A (en) * 1990-10-05 1991-10-08 Kletschka Harold D Fluid pump with levitated impeller
IL109967A (en) * 1993-06-15 1997-07-13 Multistack Int Ltd Compressor
US5547350A (en) * 1994-12-15 1996-08-20 Dresser-Rand Company Modular shaftless compressor
US5924848A (en) * 1995-06-01 1999-07-20 Advanced Bionics, Inc. Blood pump having radial vanes with enclosed magnetic drive components
US5685700A (en) * 1995-06-01 1997-11-11 Advanced Bionics, Inc. Bearing and seal-free blood pump
US5893705A (en) * 1996-12-13 1999-04-13 General Electric Company Integrated motor and blower apparatus having two back-to-back coupled rotors
US5818131A (en) * 1997-05-13 1998-10-06 Zhang; Wei-Min Linear motor compressor and its application in cooling system
DE59710092D1 (en) * 1997-09-25 2003-06-18 Levitronix Llc Waltham Centrifugal pump and centrifugal pump arrangement
KR100273359B1 (en) * 1997-11-29 2001-01-15 구자홍 Turbo compressor
ES2215044T3 (en) * 1999-04-20 2004-10-01 Forschungszentrum Julich Gmbh ROTOR DEVICE.
EP1069313B1 (en) * 1999-07-16 2005-09-14 Man Turbo Ag Turbo compressor
US6227820B1 (en) * 1999-10-05 2001-05-08 Robert Jarvik Axial force null position magnetic bearing and rotary blood pumps which use them
TW429289B (en) * 1999-12-10 2001-04-11 Delta Electronics Inc Novel magnetic suspending bearing structure
US20010039369A1 (en) * 1999-12-14 2001-11-08 Terentiev Alexandre N. Blood pump system
JP2001263291A (en) * 2000-03-15 2001-09-26 Ishikawajima Harima Heavy Ind Co Ltd Rotation supporting structure of high speed motor driven compressor
DE50107173D1 (en) * 2000-06-26 2005-09-29 Draegerwerk Ag Gas delivery device for respiratory and anesthesia devices
KR100356506B1 (en) * 2000-09-27 2002-10-18 엘지전자 주식회사 Turbo compressor
AU2002307461A1 (en) * 2001-04-23 2002-11-05 Elliott Turbomachinery Co., Inc. Multi-stage centrifugal compressor
US6547539B2 (en) * 2001-05-21 2003-04-15 Advanced Bionics, Inc. Pump assembly with bearing and seal-free reusable impeller for fragile and aggressive fluids
NL1018212C2 (en) * 2001-06-05 2002-12-10 Siemens Demag Delaval Turbomac Compressor unit comprising a centrifugal compressor and an electric motor.
US20040247461A1 (en) * 2001-11-08 2004-12-09 Frank Pflueger Two stage electrically powered compressor
JP2005508482A (en) * 2001-11-08 2005-03-31 ボーグワーナー・インコーポレーテッド 2-stage electric compressor
CA2373905A1 (en) * 2002-02-28 2003-08-28 Ronald David Conry Twin centrifugal compressor
EP1391587B1 (en) * 2002-08-20 2010-06-02 Borgwarner, Inc. Turbocharger
US6861778B2 (en) * 2003-02-28 2005-03-01 Valentin M. Izraelev System for passive and stable suspension of a rotor in rotor/stator assemblies
US20050265834A1 (en) * 2004-05-28 2005-12-01 Harvatek Corporation Fan structure
US20070036662A1 (en) * 2005-08-05 2007-02-15 C.R.F Societa Consortilla Per Azioni Multistage motor-compressor for the compression of a fluid
US20110038737A1 (en) * 2007-11-01 2011-02-17 Ronald David Conry Multi-stage compressor
CN101149077B (en) * 2007-11-07 2010-09-29 南京航空航天大学 Permanent-magnetic biased axial radial magnetic bearing
DE102008050314A1 (en) * 2008-08-18 2010-02-25 Daimler Ag Compressor and method for operating a compressor and fuel cell device with a compressor
DE102010035725A1 (en) * 2010-08-28 2012-03-01 Daimler Ag Charging device for an energy conversion device

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP2864641A1 (en) 2015-04-29
DE102012012540A1 (en) 2014-01-02
US20150219106A1 (en) 2015-08-06
WO2014001286A1 (en) 2014-01-03
CN104379939A (en) 2015-02-25

Similar Documents

Publication Publication Date Title
DE102007032933B4 (en) turbomachinery
EP2864641B1 (en) Turbocompressor
EP2503104A2 (en) Turbo engine
EP3899284B1 (en) Side-channel compressor for a fuel cell system for conveying and/or compressing a gaseous medium
WO2001057402A1 (en) Friction vacuum pump
DE102011055599A1 (en) Pump for temperature circuit in vehicle, has housing with pump chamber, and rotatable blade wheel arranged in pump chamber for conveying fluid, where flow component is arranged on blade wheel for generating pressure field
WO2011092091A1 (en) Centrifugal pump
EP2643556A1 (en) Coupled outlet vane device/angular adjustment
DE102015207341A1 (en) Compressor and motor vehicle
EP1067290B1 (en) Vacuum pump
EP3657021A1 (en) Vacuum pump
DE112019000727T5 (en) Warehouse construction
EP2826958A1 (en) Rotor for a thermal flow engine
WO2013092982A1 (en) Compressor and compressor operation method
EP2148094B1 (en) Vacuum pump
DE102004037266A1 (en) Drive axle especially for land vehicles has electric motor and differential integrated into the electric motor rotor and two drive shafts with reduction drive gears
EP2565464B1 (en) Vacuum pump
WO2019057712A1 (en) Electric media gap machine for a compressor and/or turbine, and compressor and/or turbine
EP3051138A1 (en) Vacuum pump housing, vacuum pump and method for producing a vacuum pump housing
EP3835589A1 (en) Electric motor device with an electric motor and an integral fan device
WO2003031823A1 (en) Axially discharging friction vacuum pump
EP3196471A1 (en) Monolithic permanent magnet, permanent magnet bearing, vacuum pump and method for producing a monolithic permanent magnet
DE102015111049B4 (en) vacuum pump
EP2888481B1 (en) Vacuum pump
WO2022171442A1 (en) Electrically driven air supply device and kit for the production thereof

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: 20150126

AK Designated contracting states

Kind code of ref document: A1

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

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190122

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

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

Ref country code: AT

Ref legal event code: REF

Ref document number: 1164314

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190815

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502013013324

Country of ref document: DE

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: NL

Ref legal event code: MP

Effective date: 20190807

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: 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: 20190807

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: 20190807

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: 20191107

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: 20190807

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: 20191209

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: 20191107

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: 20190807

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: 20190807

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

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: 20191207

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: 20190807

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: 20191108

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: 20190807

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: 20190807

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: 20190807

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: 20190807

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: ROBERT BOSCH GMBH

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: 20190807

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: 20190807

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: 20190807

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: 20190807

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

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: 20200224

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: 20190807

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: 20190807

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: 20190807

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502013013324

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

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

PG2D Information on lapse in contracting state deleted

Ref country code: IS

26N No opposition filed

Effective date: 20200603

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: 20190807

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: 20190807

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: LU

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

Effective date: 20200625

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200630

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

Ref country code: CH

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

Effective date: 20200630

Ref country code: LI

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

Effective date: 20200630

Ref country code: IE

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

Effective date: 20200625

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: 20200630

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1164314

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200625

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: 20200625

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: 20190807

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: 20190807

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

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: 20190807

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

Ref country code: FR

Payment date: 20230619

Year of fee payment: 11

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

Ref country code: IT

Payment date: 20230630

Year of fee payment: 11

Ref country code: GB

Payment date: 20230622

Year of fee payment: 11

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

Ref country code: DE

Payment date: 20230817

Year of fee payment: 11