EP2368018A1 - Exhaust gas turbocharger - Google Patents

Exhaust gas turbocharger

Info

Publication number
EP2368018A1
EP2368018A1 EP09768407A EP09768407A EP2368018A1 EP 2368018 A1 EP2368018 A1 EP 2368018A1 EP 09768407 A EP09768407 A EP 09768407A EP 09768407 A EP09768407 A EP 09768407A EP 2368018 A1 EP2368018 A1 EP 2368018A1
Authority
EP
European Patent Office
Prior art keywords
sealing element
bearing housing
exhaust gas
bearing
gas turbocharger
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.)
Withdrawn
Application number
EP09768407A
Other languages
German (de)
French (fr)
Inventor
Adrian Kopp
Christoph Häge
Martin Thiele
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP09768407A priority Critical patent/EP2368018A1/en
Publication of EP2368018A1 publication Critical patent/EP2368018A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • F01D25/186—Sealing means for sliding contact bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
    • F16J15/3404—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member and characterised by parts or details relating to lubrication, cooling or venting of the seal
    • F16J15/3408—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member and characterised by parts or details relating to lubrication, cooling or venting of the seal at least one ring having an uneven slipping surface
    • F16J15/3412—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member and characterised by parts or details relating to lubrication, cooling or venting of the seal at least one ring having an uneven slipping surface with cavities
    • F16J15/3416—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member and characterised by parts or details relating to lubrication, cooling or venting of the seal at least one ring having an uneven slipping surface with cavities with at least one continuous groove
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
    • F16J15/3436—Pressing means
    • F16J15/3452—Pressing means the pressing force resulting from the action of a spring
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/52—Kinematic linkage, i.e. transmission of position involving springs

Definitions

  • the invention relates to the field of supercharged internal combustion engines. It relates to a charging device for such an internal combustion engine.
  • exhaust gas turbochargers are used by default, with a turbine in the exhaust system of Verbrennungskraftmasch ine and m with a Verbrennungskraftmasch ine upstream compressor.
  • the exhaust gases of the internal combustion engine are thereby relaxed in the turbine and converted into rotational energy.
  • the obtained rotational energy is transmitted by means of a shaft to the compressor, which compresses the internal combustion engine supplied air.
  • An exhaust gas turbocharger is composed of a rotor, consisting of a shaft, a compressor wheel and a turbine wheel, of flow-guiding housing parts (compressor housing or turbine housing) and of the bearing housing.
  • the shaft is mounted in the bearing housing in one or more bearings, which are lubricated with a lubricant.
  • the shaft in the bearing housing has a seal in each case in the direction of the turbine and the compressor.
  • the sealing of the oil chamber in the bearing housing of the turbocharger towards the shaft on the side of the compressor can be done by means of one or more piston rings.
  • This piston ring has a slight preload and is clamped in the seat of the bearing housing. Because of the air mass flow that is compressed by the compressor and the pressure in the oil chamber of the bearing housing, during operation of the turbocharger, the piston ring is displaced in the direction of the turbine and thus loosened of the piston ring in the rotating counterpart towards the turbine. This grinding on the Kolbenringnute the self-adjusting gap between the piston ring and the rotating counterpart is reduced to the shaft and the sealing effect of this ieser Kolbenringabd improved direction. The grinding of the piston ring takes place until the piston ring is present at the circumferential stop edge in the seat of the bearing housing.
  • EP 1 130 220 A2 discloses a rotary seal for sealing a rotating component against a stationary housing by means of a piston ring, which is ground in the axial direction by rubbing against the rotating part.
  • a stop is provided on the housing, which limits the displaceability of the piston ring in the axial direction.
  • the pressure in the oil chamber of the bearing housing is approximately constant and by the connection of the oil chamber to the crankcase of the engine, which is vented, there is atmospheric pressure in the oil chamber of the exhaust gas turbocharger.
  • a higher pressure than in the oil chamber of the bearing housing, on the sealing element is a positive pressure difference, which is not critical with respect to a possible oil leakage.
  • the present invention has for its object to provide a sealing element for the sealing of the oil chamber in the bearing housing of the exhaust gas turbocharger to the shaft on the side of the compressor, which is not or only slightly influenced by the pressure fluctuations in the wheel back of the compressor. According to the invention, this is achieved with a sealing element which is held in its optimum position by means of an external force. This force can be applied by one or more resilient elements on the sealing element. Due to the external force, the pressure forces acting on the sealing element, depending on the direction of the pressure difference, either compensated or strengthened.
  • the sealing element is designed as a sealing ring which is slidably seated in a seat of the bearing housing. Between the shaft and the bearing housing, a gap is formed, in which the acted upon by the spring force sealing ring is arranged.
  • the sealing ring according to the invention is pushed by a force acting on a first end side resilient element, for example by a spring, by spring assemblies, by elastomers or by externally supplied, acting on the sealing ring compressed air in the direction of the turbine.
  • a force acting on a first end side resilient element for example by a spring, by spring assemblies, by elastomers or by externally supplied, acting on the sealing ring compressed air in the direction of the turbine.
  • the grinding in is optionally limited in the axial direction by taking place until the sealing ring abuts against a stop.
  • the stop can be executed as a positive boundary in the form of an axial stop or as a non-positive limitation in the form of a widening seat.
  • the effective area of the sealing ring in the direction of the wheel back of the compressor is advantageously smaller than the effective area of the sealing ring in the direction of the
  • the ring can be additionally sealed.
  • the sealing of the seat in the bearing housing to the ring takes place in this case with an elastic element which is arranged either in a groove in the seat of the ring or in a groove in the seat of the bearing housing.
  • the sealing ring in the seat of the bearing housing is optionally secured against rotation, by a non-positive or positive connection of the sealing ring with the bearing housing.
  • the inventive seal can be supplemented with a further sealing element, for example a conventional piston ring.
  • FIG. 4 shows an enlarged detail of the region of the seal of the compressor wheel with respect to the exhaust gas turbocharger shaft with the first embodiment of the inventive seal according to FIG. 2, supplemented with an additional sealing element.
  • Fig. 1 shows a conventional exhaust gas turbocharger with a turbine 8 and a compressor 7.
  • the impeller of the turbine is arranged in the turbine housing 80 and is flowed in the illustrated embodiment obliquely to the radial (mixed-flow turbine).
  • the impeller of the compressor is arranged in the compressor housing 70.
  • the two wheels are connected to each other via a common shaft 2.
  • the shaft is mounted in the bearing housing 5 in a plurality of bearings 3.
  • the bearing housing 5 comprises a cavity, which is henceforth referred to as the oil chamber 1.
  • the oil chamber 1 the lubricating oil is supplied to or removed from the bearings and circulates oil-soaked air.
  • the housing comprises two bearing housing parts.
  • a first bearing housing part 9 is arranged between the flow channel of the compressor and the oil chamber 1.
  • the second bearing housing part 5 is arranged between the flow channel of the turbine and the oil space.
  • a cavity which is henceforth referred to as Radenburgraum 6.
  • the cutout according to FIG. 2 shows the bearing housing 9 as well as a disk 10 arranged on the shaft and rotating with the shaft.
  • a gap is formed between the non-rotating bearing housing 9 and the rotating disk 10.
  • the sealing element is arranged in the form of a circumferential sealing ring 4.
  • the sealing of the gap by means of the sealing ring 4 takes place on the one hand on the inside of the sealing ring against a seat 92 on the bearing housing and on the other hand against a protruding edge 101 on the disc 10.
  • the edge 101 can also be used as an outer edge of the disc 10 or as a protruding or external edge may be formed on the shaft itself.
  • the sealing ring 4 on an end face 42, which together with the edge 101 forms a sealing interface. In the area of the sealing interface there will be a grinding in of the sealing ring 4 during operation, i. the edge 101 will abrade material in the sealing ring 4 and a circumferential groove is formed, as indicated in the figure.
  • the sealing ring 4 is acted upon by a spring force which presses the sealing ring in the direction of the edge 101.
  • the spring force is exerted on the sealing ring 4 by a spring 13 mounted in a circumferential bore 91 in the bearing housing 9.
  • a spring with a large diameter can, as indicated in the embodiment of FIG. 3, provide several small springs along the circumference of the sealing ring 4 for the spring force in the direction of the edge 101.
  • spring packs or elastomers can also be used, or a corresponding force can be exerted on the sealing ring by means of compressed air, which is supplied externally to this area.
  • the sealing ring 4 rad ial against the inside by means of an additional sealing element 12 relative to the seat 92 on the bearing housing 9 are sealed.
  • the additional sealing element 12 is guided in a groove 43 in the sealing ring 4 or in a groove in the bearing housing.
  • Ansch lay 1 1 may be provided.
  • a form-fitting axial stop is provided, for example in the form of a snap ring, which is guided in a circumferential groove in the seat 92 of the bearing housing 9.
  • a conical shape of the seat 92 ensures a frictional stop.
  • the sealing ring 4 is displaced in the direction of the edge 101 on the cone-shaped seat until it is frictionally present.
  • the sealing ring 4 depending on the pressure ratio in the gap on the two opposite sides additionally in the direction of the spring force, ie towards the edge 101 hin-, or against the direction of the spring force, ie pushed away from the edge 101.
  • the spring force it is possible to prevent the sealing ring 4 from detaching from the edge 101 in the region of the sealing interface in the latter case.
  • the shape and arrangement of the sealing ring 4 in the gap between the bearing housing 9 and the disc 10 has an influence on how much the pressure forces generated by the pressure gradient applied to the sealing ring press the sealing ring in one direction or the other. Since the positive pressure difference reaches a greater absolute amount is advantageously the effective area A of the sealing ring 4 in the direction of the compressor 7 to choose smaller than the effective area B of the sealing ring 4 in the direction of the oil chamber 1 of the bearing housing 5.
  • the sealing ring 4 can optionally against rotation be secured by a non-positive or positive connection of the sealing ring 4 with the bearing housing.
  • the inventive seal can be supplemented with an additional sealing element in the gap between the fixed housing parts and the rotating elements, such as one or more piston rings 14 between the bearing housing 9 and the compressor 7.
  • the gap undergoes a deflection wherein the piston ring is arranged before the deflection and the sealing ring after the deflection.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Supercharger (AREA)

Abstract

The seal of the compressor impeller (7) relative to the bearing housing (9) comprises an annular sealing element (4) that forms a seal boundary together with a shaft edge (10) and that is acted upon by a spring force in the direction of the shaft edge (10). The pressure forces that act on the sealing element are either compensated or enhanced by the external spring force, depending on the direction of the pressure difference. In this way, the seal of the oil chamber in the bearing housing of the exhaust gas turbocharger, said seal being in the direction of the shaft, is not affected by the pressure fluctuations in the impeller rear chamber of the compressor, or is only very slightly affected thereby.

Description

Abgasturbolader turbocharger
B E S C H R E I B U N GDESCRIPTION
Technisches GebietTechnical area
Die Erfindung bezieht sich auf das Gebiet der aufgeladenen Brennkraftmaschinen. Sie betrifft eine Aufladevorrichtung für eine solche Brennkraftmaschine.The invention relates to the field of supercharged internal combustion engines. It relates to a charging device for such an internal combustion engine.
Stand der TechnikState of the art
Für die Leistungssteigerung einer Brennkraftmaschine werden heutzutage standardmässig Abgasturbolader eingesetzt, mit einer Turbine im Abgastrakt der Verbrennungskraftmasch ine und m it einem der Verbrennungskraftmasch ine vorgelagerten Verdichter. Die Abgase der Brennkraftmaschine werden dabei in der Turbine entspannt und in Drehenergie ungewandelt. Die gewonnene Drehenergie wird mittels einer Welle auf den Verdichter übertragen, welcher die der Brennkraftmaschine zugeführte Luft verdichtet. Durch die Verwendung der Energie der Abgase zur Verdichtung der dem Verbrennungsprozess in der Brennkraftmaschine zugeführten Luft, können der Verbrennungsprozess und der Wirkungsgrad der Brennkraftmaschine optimiert werden.For the increase in performance of an internal combustion engine today exhaust gas turbochargers are used by default, with a turbine in the exhaust system of Verbrennungskraftmasch ine and m with a Verbrennungskraftmasch ine upstream compressor. The exhaust gases of the internal combustion engine are thereby relaxed in the turbine and converted into rotational energy. The obtained rotational energy is transmitted by means of a shaft to the compressor, which compresses the internal combustion engine supplied air. By using the energy of the exhaust gases to compress the air supplied to the combustion process in the internal combustion engine, the combustion process and the efficiency of the internal combustion engine can be optimized.
Ein Abgasturbolader setzt sich aus einem Rotor, bestehend aus einer Welle, einem Verdichterrad und einem Turbinenrad, aus strömungsführenden Gehäuseteilen (Verdichtergehäuse resp. Turbinengehäuse) und aus dem Lagergehäuse zusammen. Die Welle ist im Lagergehäuse in einem oder mehreren Lagern gelagert, welche mit einem Schmiermittel geschmiert werden. Um ein Austreten des Schmiermittels in Richtung Turbine oder Verdichter zu verhindern, weist die Welle im Lagergehäuse je eine Abdichtung Richtung Turbine und Verdichter auf.An exhaust gas turbocharger is composed of a rotor, consisting of a shaft, a compressor wheel and a turbine wheel, of flow-guiding housing parts (compressor housing or turbine housing) and of the bearing housing. The shaft is mounted in the bearing housing in one or more bearings, which are lubricated with a lubricant. In order to prevent the lubricant from escaping in the direction of the turbine or compressor, the shaft in the bearing housing has a seal in each case in the direction of the turbine and the compressor.
Die Abdichtung des Ölraumes im Lagergehäuse des Abgasturboladers hin zur Welle auf der Seite des Verdichters kann mittels eines oder mehreren Kolbenringen erfolgen.The sealing of the oil chamber in the bearing housing of the turbocharger towards the shaft on the side of the compressor can be done by means of one or more piston rings.
Nachfolgend wird der Einfachheit halber die Abdichtung mittels eines Kolbenringes beschrieben. Dieser Kolbenring weist eine leichte Vorspannung auf und ist im Sitz des Lagergehäuses g e kl em mt . D u rch d e n D ru c ku ntersch ied zwi sch en d em Luftmassenstrom, welcher durch den Verdichter verdichtet wird und dem Druck im Ölraum des Lagergehäuses, kommt es im Betrieb des Turboladers zu einer Verschiebung des Kolbenringes in Richtung Turbine und somit zu einem Einschleifen des Kolbenringes in der drehenden Gegenpartie in Richtung Turbine. Durch dieses Einschleifen an der Kolbenringnute wird der sich einstellende Spalt zwischen Kolbenring und der sich drehenden Gegenpartie auf der Welle reduziert und die Dichtwirkung d ieser Kolbenringabd ichtung verbessert. Das Einschleifen des Kolbenringes erfolgt so lange, bis der Kolbenring an der umlaufenden Anschlagkante im Sitz des Lagergehäuses ansteht.Hereinafter, the sake of simplicity, the seal by means of a piston ring described. This piston ring has a slight preload and is clamped in the seat of the bearing housing. Because of the air mass flow that is compressed by the compressor and the pressure in the oil chamber of the bearing housing, during operation of the turbocharger, the piston ring is displaced in the direction of the turbine and thus loosened of the piston ring in the rotating counterpart towards the turbine. This grinding on the Kolbenringnute the self-adjusting gap between the piston ring and the rotating counterpart is reduced to the shaft and the sealing effect of this ieser Kolbenringabd improved direction. The grinding of the piston ring takes place until the piston ring is present at the circumferential stop edge in the seat of the bearing housing.
EP 1 130 220 A2 offenbart eine Rotationsdichtung zum Abdichten eines rotierenden Bauteils gegen ein stehendes Gehäuse mittels eines Kolbenringes, welcher durch Reiben an dem rotierenden Teil in axialer Richtung eingeschliffen wird. Um das zu starke Abschleifen des Kolbenrings zu verhindern, ist am Gehäuse ein Anschlag vorgesehen, welcher die Verschiebbarkeit des Kolbenrings in axialer Richtung begrenzt.EP 1 130 220 A2 discloses a rotary seal for sealing a rotating component against a stationary housing by means of a piston ring, which is ground in the axial direction by rubbing against the rotating part. In order to prevent excessive grinding of the piston ring, a stop is provided on the housing, which limits the displaceability of the piston ring in the axial direction.
Der Druck im Ölraum des Lagergehäuses ist näherungsweise konstant und durch die Verbindung des Ölraumes zu dem Kurbelgehäuse des Motors, das entlüftet wird, herrscht im Ölraum des Abgasturboladers Atmosphärendruck. Bei Volllastbetrieb des Motors herrscht im Radrückraum des Verdichters ein höherer Druck als im Ölraum des Lagergehäuses, über dem Dichtelement liegt eine positive Druckdifferenz an, was bezüglich einer möglichen Ölleckage unkritisch ist.The pressure in the oil chamber of the bearing housing is approximately constant and by the connection of the oil chamber to the crankcase of the engine, which is vented, there is atmospheric pressure in the oil chamber of the exhaust gas turbocharger. In full-load operation of the engine prevails in the Radrückraum of the compressor, a higher pressure than in the oil chamber of the bearing housing, on the sealing element is a positive pressure difference, which is not critical with respect to a possible oil leakage.
Bei einem Unterdruck im Radrückraum des Verdichters liegt hingegen über dem Dichtelement eine negative Druckdifferenz an . Dies kann je nach Höhe des Unterdruckes zu einer Heranführung des Schmiermittels in den Radrückraum führen.At a negative pressure in the Radrückraum of the compressor, however, is on the sealing element to a negative pressure difference. This can lead depending on the amount of negative pressure to a pre-introduction of the lubricant in the Radrückraum.
Kurze Darstellung der ErfindungBrief description of the invention
Der vorliegenden Erfindung liegt die Aufgabe zugrunde, ein Dichtelement für die Abdichtung des Ölraumes im Lagergehäuse des Abgasturboladers hin zur Welle auf der Seite des Verdichters zu schaffen, welches von den Druckschwankungen im Radrückraum des Verdichters nicht oder nur wenig beeinflusst wird. Erfindungsgemäss wird dies mit einem Dichtelement erreicht, welches mittels einer äusseren Kraft in seiner optimalen Lage gehalten wird. Diese Kraft kann durch ein oder mehrere federnde Elemente auf das Dichtelement aufgebracht werden. Durch die äussere Kraft werden die Druckkräfte, die auf das Dichtelement wirken, abhängig von der Richtung der Druckdifferenz, entweder kompensiert oder verstärkt.The present invention has for its object to provide a sealing element for the sealing of the oil chamber in the bearing housing of the exhaust gas turbocharger to the shaft on the side of the compressor, which is not or only slightly influenced by the pressure fluctuations in the wheel back of the compressor. According to the invention, this is achieved with a sealing element which is held in its optimum position by means of an external force. This force can be applied by one or more resilient elements on the sealing element. Due to the external force, the pressure forces acting on the sealing element, depending on the direction of the pressure difference, either compensated or strengthened.
Das Dichtelement ist als ein Dichtring ausgebildet, der verschiebbar in einem Sitz des Lagergehäuses sitzt. Zwischen der Welle und dem Lagergehäuse ist ein Spalt ausgebildet, in welchem der mit der Federkraft beaufschlagte Dichtring angeordnet ist. Der Dichtring wird erfindungsgemäss durch ein auf eine erste Stirnseite wirkendes federndes Element, beispielsweise durch eine Feder, durch Federpakete, durch Elastomere oder durch extern zugeführte, auf den Dichtring wirkende Druckluft in Richtung Turbine geschoben. Mit der gegenüberliegenden Stirnseite liegt der Dichtring an einer Kante der Welle, oder einer Kante eines mit der Welle rotierenden Hilfsbauteils an, wodurch es im Betrieb zu einem Einschleifen des Dichtringes an dieser Kante kommt. Das Einschleifen ist optional in axiale Richtung begrenzt, indem es solange erfolgt, bis der Dichtring an einem Anschlag anliegt. Der Anschlag kann dabei als formschlüssige Begrenzung in der Form eines Axialanschlags oder als kraftschlüssige Begrenzung in form eines sich erweiternden Sitzes ausgeführt werden.The sealing element is designed as a sealing ring which is slidably seated in a seat of the bearing housing. Between the shaft and the bearing housing, a gap is formed, in which the acted upon by the spring force sealing ring is arranged. The sealing ring according to the invention is pushed by a force acting on a first end side resilient element, for example by a spring, by spring assemblies, by elastomers or by externally supplied, acting on the sealing ring compressed air in the direction of the turbine. With the opposite end face of the sealing ring is located on an edge of the shaft, or an edge of a rotating shaft with the auxiliary component, whereby it comes in operation to a grinding of the sealing ring at this edge. The grinding in is optionally limited in the axial direction by taking place until the sealing ring abuts against a stop. The stop can be executed as a positive boundary in the form of an axial stop or as a non-positive limitation in the form of a widening seat.
Bei Unterdruck im Bereich des Radrückraums bildet sich über dem Dichtring eine Druckdifferenz aus, welche den Dichtring mit einer Kraft beaufschlagt, wobei diese Kraft und die Federkraft in die gleiche Richtung wirken.At negative pressure in the region of the Radrückraums forms above the sealing ring from a pressure difference, which acts on the sealing ring with a force, said force and the spring force acting in the same direction.
Bei Volllastbetrieb des Motors herrscht im Radrückraum des Verdichters ein höherer Druck als im Ölraum des Lagergehäuses, über dem Dichtelement liegt folglich eine positive Druckdifferenz an, die der äusseren Kraft, die auf das Dichtelement wirkt, entgegenwirkt. Damit eine vollständige Kompensation der äusseren Kraft nicht auftreten kann, ist diese vorteilhafterweise grösser zu wählen als die Druckkraft, die durch die grösste im Betrieb zu erwartende positive Druckdifferenz auftritt.At full load operation of the engine prevails in the Radrückraum of the compressor, a higher pressure than in the oil chamber of the bearing housing, on the sealing element is therefore a positive pressure difference, which counteracts the external force acting on the sealing element. So that a complete compensation of the external force can not occur, this is advantageously greater to choose than the pressure force that occurs due to the largest expected during operation positive pressure difference.
Da d ie positive Druckdifferenz einen grosseren absoluten Betrag erreicht ist vorteilhafterweise die wirksame Fläche des Dichtringes in Richtung des Radrückraumes des Verdichters kleiner als die wirksame Fläche des Dichtringes in Richtung desSince the positive pressure difference reaches a greater absolute value, the effective area of the sealing ring in the direction of the wheel back of the compressor is advantageously smaller than the effective area of the sealing ring in the direction of the
Ölraumes des Lagergehäuses auszubilden. Durch eine derartige Optimierung des Flächenverhältnisses kann die Dichtwirkung des Dichtelementes zusätzlich verbessert werden.Form oil space of the bearing housing. Through such optimization of the Area ratio, the sealing effect of the sealing element can be further improved.
Zur besseren Dichtwirkung kann der Ring noch zusätzlich abgedichtet werden. Die Abdichtung des Sitzes im Lagergehäuse zu dem Ring erfolgt in diesem Fall mit einem elastischen Element, das entweder in einer Nut im Sitz des Ringes oder in einer Nut im Sitz des Lagergehäuses angeordnet ist.For better sealing effect, the ring can be additionally sealed. The sealing of the seat in the bearing housing to the ring takes place in this case with an elastic element which is arranged either in a groove in the seat of the ring or in a groove in the seat of the bearing housing.
Der Dichtring im Sitz des Lagergehäuses ist optional gegen Verdrehen gesichert, durch eine kraft- oder formschlüssige Verbindung des Dichtringes mit dem Lagergehäuse.The sealing ring in the seat of the bearing housing is optionally secured against rotation, by a non-positive or positive connection of the sealing ring with the bearing housing.
Die erfindungsgemässe Dichtung kann mit einem weiteren Dichtelement, beispielsweise einem herkömmlichen Kolbenring ergänzt werden.The inventive seal can be supplemented with a further sealing element, for example a conventional piston ring.
Kurze Beschreibung der ZeichnungenBrief description of the drawings
Nachfolge n d s i n d a n h a n d d e r Z e i c h n u n g e n Au sfü h ru n g sfo rm e n d e s erfindungsgemässen Abgasturboladers beschrieben. Hierbei zeigtThe succession of the exhaust gas turbocharger according to the invention is described in more detail in the accompanying text of the invention. This shows
Fig. 1 einen entlang der Abgasturboladerwelle geführten Schnitt durch einen Abgasturbolader gemäss dem Stand der Technik,1 shows a guided along the exhaust gas turbocharger section through an exhaust gas turbocharger according to the prior art,
Fig. 2 einen vergrössert dargestellten Ausschnitt des Bereichs der Abdichtung des Verdichterrades gegenüber der Abgasturboladerwelle mit einer ersten Ausführungsform der erfindungsgemässen Abdichtung,2 shows an enlarged detail of the region of the sealing of the compressor wheel with respect to the exhaust gas turbocharger shaft with a first embodiment of the inventive seal,
Fig. 3 einen vergrössert dargestellten Ausschnitt des Bereichs der Abdichtung des Verdichterrades gegenüber der Abgasturboladerwelle mit einer zweiten3 shows an enlarged detail of the region of the sealing of the compressor wheel with respect to the exhaust gas turbocharger shaft with a second
Ausführungsform der erfindungsgemässen Abdichtung,Embodiment of the inventive seal,
Fig. 4 einen vergrössert dargestellten Ausschnitt des Bereichs der Abdichtung des Verdichterrades gegenüber der Abgasturboladerwelle mit der ersten Ausführungsform der erfindungsgemässen Abdichtung nach Fig. 2, ergänzt mit einem zusätzlichen Dichtelement.4 shows an enlarged detail of the region of the seal of the compressor wheel with respect to the exhaust gas turbocharger shaft with the first embodiment of the inventive seal according to FIG. 2, supplemented with an additional sealing element.
Weg zur Ausführung der ErfindungWay to carry out the invention
Fig . 1 zeigt einen herkömmlichen Abgasturbolader mit einer Turbine 8 und einem Verdichter 7. Die Laufrad der Turbine ist im Turbinengehäuse 80 angeordnet und wird in der dargestellten Ausführungsform schräg zur Radialen angeströmt (Mixed-Flow Turbine). Das Laufrad des Verdichters ist im Verdichtergehäuse 70 angeordnet. Die beiden Laufräder sind über eine gemeinsame Welle 2 miteinander verbunden. Die Welle ist im Lagergehäuse 5 in mehreren Lagern 3 gelagert. Im Bereich der Lager 3 der Welle 2 umfasst das Lagergehäuse 5 einen Hohlraum, welcher fortan als Ölraum 1 bezeichnet wird. Im Ölraum 1 wird das Schmieröl den Lagern zu oder abgeführt und es zirkuliert ölgetränkte Luft. Das Gehäuse umfasst zwei Lagergehäuseteile. Ein erstes Lagergehäuseteil 9 ist zwischen dem Strömungskanal des Verdichters und dem Ölraum 1 angeordnet. Das zweite Lagergehäuseteil 5 ist zwischen dem Strömungskanal der Turbine und dem Ölraum angeordnet. Im Rücken des Laufrades des Verdichters 7 erstreckt sich zwischen dem Laufrad und dem Lagergehäuse 9 ein Hohlraum, welcher fortan als Radrückraum 6 bezeichnet wird.Fig. 1 shows a conventional exhaust gas turbocharger with a turbine 8 and a compressor 7. The impeller of the turbine is arranged in the turbine housing 80 and is flowed in the illustrated embodiment obliquely to the radial (mixed-flow turbine). The impeller of the compressor is arranged in the compressor housing 70. The two wheels are connected to each other via a common shaft 2. The shaft is mounted in the bearing housing 5 in a plurality of bearings 3. In the area of the bearing 3 of the shaft 2, the bearing housing 5 comprises a cavity, which is henceforth referred to as the oil chamber 1. In the oil chamber 1, the lubricating oil is supplied to or removed from the bearings and circulates oil-soaked air. The housing comprises two bearing housing parts. A first bearing housing part 9 is arranged between the flow channel of the compressor and the oil chamber 1. The second bearing housing part 5 is arranged between the flow channel of the turbine and the oil space. In the back of the impeller of the compressor 7 extends between the impeller and the bearing housing 9, a cavity, which is henceforth referred to as Radrückraum 6.
Die erfindungsgemässe Abdichtung des Radrückraums 6 gegenüber dem Ölraum 1 des Lagergehäuses wird nachfolgend anhand der Detaildarstellungen in den Fig. 2 bis 4 erläutert. Die Detaildarstellungen zeigen jeweils vergrössert den in Fig. 1 mit einem gestrichelten Rechteck markierten Bereich zwischen Radrückraum 6 und Lager 3.The inventive sealing of the Radrückraums 6 relative to the oil chamber 1 of the bearing housing will be explained below with reference to the detailed representations in FIGS. 2 to 4. The detailed views each show enlarged in FIG. 1 marked with a dashed rectangle area between Radrückraum 6 and 3 camp.
Der Ausschnitt gemäss Fig. 2 zeigt das Lagergehäuse 9 sowie eine auf der Welle angeordnete und mit der Welle mitdrehende Scheibe 10. Zwischen dem nicht rotierenden Lagergehäuse 9 und der rotierenden Scheibe 10 ist ein Spalt ausgebildet. Im Spalt ist das Dichtelement in Form eines umlaufenden Dichtringes 4 angeordnet. Die Abdichtung des Spaltes mittels des Dichtringes 4 erfolgt dabei einerseits auf der Innenseite des Dichtringes gegenüber einem Sitz 92 auf dem Lagergehäuse und andererseits gegenüber einer vorstehenden Kante 101 an der Scheibe 10. Die Kante 101 kann auch als eine aussenliegende Kante der Scheibe 10 oder aber als eine hervorstehende oder aussenliegende Kante an der Welle selber ausgebildet sein. Gegenüber der Kante 101 weist der Dichtring 4 eine Stirnseite 42 auf, welche mit der Kante 101 zusammen eine Dichtgrenzfläche bildet. Im Bereich der Dichtgrenzfläche wird es im Betrieb zu einem Einschleifen des Dichtrings 4 kommen, d.h. die Kante 101 wird im Dichtring 4 Material abschleifen und es wird eine umlaufende Nut geformt, wie in der Figur angedeutet.The cutout according to FIG. 2 shows the bearing housing 9 as well as a disk 10 arranged on the shaft and rotating with the shaft. A gap is formed between the non-rotating bearing housing 9 and the rotating disk 10. In the gap, the sealing element is arranged in the form of a circumferential sealing ring 4. The sealing of the gap by means of the sealing ring 4 takes place on the one hand on the inside of the sealing ring against a seat 92 on the bearing housing and on the other hand against a protruding edge 101 on the disc 10. The edge 101 can also be used as an outer edge of the disc 10 or as a protruding or external edge may be formed on the shaft itself. Opposite the edge 101, the sealing ring 4 on an end face 42, which together with the edge 101 forms a sealing interface. In the area of the sealing interface there will be a grinding in of the sealing ring 4 during operation, i. the edge 101 will abrade material in the sealing ring 4 and a circumferential groove is formed, as indicated in the figure.
Erfindungsgemäss ist der Dichtring 4 mit einer Federkraft beaufschlagt, welche den Dichtring in Richtung der Kante 101 drückt. In der dargestellten Ausführungsform wird die Federkraft auf den Dichtring 4 durch eine in einer umlaufenden Bohrung 91 im Lagergehäuse 9 gelagerten Feder 13 ausgeübt. Anstelle einer Feder mit einem grossen Durchmesser können, wie dies in der Ausführungsform nach Fig. 3 angedeutet ist, mehrere kleine Federn entlang des Umfangs des Dichtringes 4 für die Federkraft in Richtung der Kante 101 sorgen . Alternativ zu einfachen Federn können auch Federpakete oder Elastomere eingesetzt werden, oder es kann mittels Druckluft, welche von extern diesem Bereich zugeführt wird, eine entsprechende Kraft auf den Dichtring bewirkt werden.According to the invention, the sealing ring 4 is acted upon by a spring force which presses the sealing ring in the direction of the edge 101. In the illustrated embodiment is the spring force is exerted on the sealing ring 4 by a spring 13 mounted in a circumferential bore 91 in the bearing housing 9. Instead of a spring with a large diameter can, as indicated in the embodiment of FIG. 3, provide several small springs along the circumference of the sealing ring 4 for the spring force in the direction of the edge 101. As an alternative to simple springs, spring packs or elastomers can also be used, or a corresponding force can be exerted on the sealing ring by means of compressed air, which is supplied externally to this area.
Optional kann der Dichtring 4 rad ial gegen innen mittels eines zusätzlichen Dichtelements 12 gegenüber dem Sitz 92 auf dem Lagergehäuse 9 abgedichtet werden. Das zusätzliche Dichtelement 12 wird dabei in einer Nut 43 im Dichtring 4 oder in einer Nut im Lagergehäuse geführt.Optionally, the sealing ring 4 rad ial against the inside by means of an additional sealing element 12 relative to the seat 92 on the bearing housing 9 are sealed. The additional sealing element 12 is guided in a groove 43 in the sealing ring 4 or in a groove in the bearing housing.
Um die axiale Verschiebbarkeit des Dichtringes 4 auf dem Sitz 92 des Lagergehäuses 9 und damit den oben beschriebenen Einschleifprozess zu begrenzen, kann optional ein Ansch lag 1 1 vorgesehen sein . I n der Ausfüh ru ngsform nach F ig . 2 ist ein formschlüssiger Axialanschlag vorgesehen, etwa in Form eines Sprengringes, welcher in einer umlaufenden Nut im Sitz 92 des Lagergehäuses 9 geführt ist. In der Ausführungsform nach Fig. 3 hingegen sorgt eine konusförmige Form des Sitzes 92 für einen kraftschlüssigen Anschlag. Der Dichtring 4 wird in Richtung der Kante 101 auf den konusförmigen Sitz verschoben, bis er kraftschlüssig ansteht.In order to limit the axial displaceability of the sealing ring 4 on the seat 92 of the bearing housing 9 and thus the grinding process described above, optionally Ansch lay 1 1 may be provided. I n the Ausfüh rungsform F ig. 2, a form-fitting axial stop is provided, for example in the form of a snap ring, which is guided in a circumferential groove in the seat 92 of the bearing housing 9. In contrast, in the embodiment according to FIG. 3, a conical shape of the seat 92 ensures a frictional stop. The sealing ring 4 is displaced in the direction of the edge 101 on the cone-shaped seat until it is frictionally present.
Im Betrieb wird der Dichtring 4 je nach Druckverhältnis im Spalt auf den beiden gegenüberliegenden Seiten zusätzlich in Richtung der Federkraft, also zur Kante 101 hin-, oder aber entgegen der Richtung der Federkraft, also von der Kante 101 weggedrückt. Durch geeignete Wahl der Federkraftstärke kann verhindert werden, dass sich im letzteren Fall der Dichtring 4 im Bereich der Dichtgrenzfläche von der Kante 101 löst.In operation, the sealing ring 4, depending on the pressure ratio in the gap on the two opposite sides additionally in the direction of the spring force, ie towards the edge 101 hin-, or against the direction of the spring force, ie pushed away from the edge 101. By a suitable choice of the spring force, it is possible to prevent the sealing ring 4 from detaching from the edge 101 in the region of the sealing interface in the latter case.
Bei Volllastbetrieb des Motors herrscht im Radrückraum 6 des Verdichters 7 ein höherer Druck als im Ölraum 1 des Lagergehäuses 5. Über dem Dichtring 4 liegt eine positive Druckdifferenz an, welche der Federkraft entgegenwirkt. Eine entgegengesetzt wirkende, negative Druckdifferenz l iegt über dem Dichtelement an , wenn im Radrückraum 6 des Verdichters 7 ein Unterdruck gegenüber dem Ölraum 1 herrscht. Eine derartige, negative Druckdifferenz verstärkt die äussere Federkraft, die auf den Dichtring 4 einwirkt.In full-load operation of the engine prevails in the Radrückraum 6 of the compressor 7, a higher pressure than in the oil chamber 1 of the bearing housing 5. About the sealing ring 4 is a positive pressure difference, which counteracts the spring force. An oppositely acting negative pressure difference is applied via the sealing element when a negative pressure with respect to the oil chamber 1 prevails in the wheel back 6 of the compressor 7. Such a negative pressure difference amplifies the external spring force acting on the sealing ring 4.
Zusätzlich zur Federkraftstärke hat auch die Form und Anordnung des Dichtringes 4 im Spalt zwischen dem Lagergehäuse 9 und der Scheibe 10 einen Einfluss darauf, wie stark die von dem über dem Dichtring anliegenden Druckgefälle erzeugten Druckkräfte den Dichtring in die eine oder andere Richtung drücken. Da die positive Druckdifferenz einen grosseren absoluten Betrag erreicht ist vorteilhafterweise die wirksame Fläche A des Dichtringes 4 in Richtung des Verdichters 7 kleiner zu wählen als die wirksame Fläche B des Dichtringes 4 in Richtung des Ölraumes 1 des Lagergehäuses 5. Der Dichtring 4 kann optional gegen Verdrehen gesichert werden, durch eine kraft- oder formschlüssige Verbindung des Dichtringes 4 mit dem Lagergehäuse 9.In addition to the spring force, the shape and arrangement of the sealing ring 4 in the gap between the bearing housing 9 and the disc 10 has an influence on how much the pressure forces generated by the pressure gradient applied to the sealing ring press the sealing ring in one direction or the other. Since the positive pressure difference reaches a greater absolute amount is advantageously the effective area A of the sealing ring 4 in the direction of the compressor 7 to choose smaller than the effective area B of the sealing ring 4 in the direction of the oil chamber 1 of the bearing housing 5. The sealing ring 4 can optionally against rotation be secured by a non-positive or positive connection of the sealing ring 4 with the bearing housing. 9
Wie i n Fig.4 dargestellt, kann die erfindungsgemässe Abdichtung mit einem zusätzlichen Dichtelement im Spalt zwischen den feststehenden Gehäuseteilen und den rotierenden Elementen, etwa einem oder mehreren Kolbenringen 14 zwischen dem Lagergehäuse 9 und dem Verdichterrad 7, ergänzt werden. Die beiden dargestellten Dichtelemente, der Dichtring 4 und der Kolbenring 14, wirken beide in Richtung der Turbinenseite, im Spalt zwischen den feststehenden Gehäuseteilen und den rotierenden Elementen wirken sie jedoch in entgegengesetzter Richtung. Der Spalt erfährt eine Umlenkung wobei der Kolbenring vor der Umlenkung und der Dichtring nach der Umlenkung angeordnet ist. As shown in Figure 4, the inventive seal can be supplemented with an additional sealing element in the gap between the fixed housing parts and the rotating elements, such as one or more piston rings 14 between the bearing housing 9 and the compressor 7. The two illustrated sealing elements, the sealing ring 4 and the piston ring 14, both act in the direction of the turbine side, in the gap between the stationary housing parts and the rotating elements, however, they act in the opposite direction. The gap undergoes a deflection wherein the piston ring is arranged before the deflection and the sealing ring after the deflection.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
Ölraumeoil space
Wellewave
LagernTo store
Dichtringseal
Lagergehäusebearing housing
RadrückraumRadrückraum
Verdichtercompressor
Verdichtergehäusecompressor housing
Turbineturbine
Turbinengehäuseturbine housing
Lagergehäusebearing housing
Bohrung im LagergehäuseBore in the bearing housing
Sitz am LagergehäuseSeat on the bearing housing
Scheibedisc
Kanteedge
Anschlagattack
Dichtelement federnde(s) Element(e)Sealing element resilient element (s)
Kolbenringpiston ring
Stirnseiten des DichtringesEnd faces of the sealing ring
Nut im Dichtring Groove in the sealing ring

Claims

PAT E N TA N S P R Ü C H E PAT EN TA NSPR O CHE
1. Abgasturbolader, umfassend ein Lagergehäuse (5) mit einer zentralen Bohrung, mindestens ein in der Bohrung angeordnetes Lager (3), eine in der Bohrung angeordnete, in dem mindestens einen Lager gelagerte Welle (2), ein auf der Welle (2) angeordnetes Verdichterrad (7), wobei zwischen der Welle und dem Lagergehäuse ein Spalt ausgebildet ist, welcher sich vom Verdichterrad (7) in Richtung des Lagers (3) erstreckt, sowieAn exhaust gas turbocharger comprising a bearing housing (5) having a central bore, at least one bearing (3) disposed in the bore, a shaft (2) mounted in the bore and supported in the at least one bearing, one on the shaft (2). arranged compressor wheel (7), wherein between the shaft and the bearing housing, a gap is formed, which extends from the compressor wheel (7) in the direction of the bearing (3), and
Dichtmittel, welche sich in der Bohrung zwischen dem Verdichterrad (7) und dem Lager (3) befinden, wobei die Dichtmittel mindestens ein ringförmiges DichtelementSealing means, which are located in the bore between the compressor wheel (7) and the bearing (3), wherein the sealing means at least one annular sealing element
(4, 14) umfassen, welches Dichtelement (4, 14) mit einer mit der Welle rotierenden(4, 14), which sealing element (4, 14) with a rotating with the shaft
Kante (101 ) eine Dichtgrenzfläche bildet, wobei mindestens ein ringförmigesEdge (101) forms a sealing interface, wherein at least one annular
Dichtelement (4) parallel zur Wellenachse verschiebbar auf einem Sitz (92) desSealing element (4) displaceable parallel to the shaft axis on a seat (92) of the
Lagergehäuses (9) angeordnet und mit einer durch ein Federelement (13) bewirkten Federkraft in axialer Richtung zum Lager hin beaufschlagt ist, dadurch gekennzeichnet, dass das mit einer Federkraft beaufschlagte Dichtelement (4) derart ausgebildet und im Spalt zwischen der Welle und dem Lagergehäuse angeordnet ist, dass bei Unterdruck im Bereich des Verdichterrades (7) aufgrund einer über dem Dichtelement (4) anliegenden Druckdifferenz, das Dichtelement (4) mit einer Kraft beaufschlagt wird, deren axiale Komponente in die gleiche Richtung wirkt wie die Federkraft.Bearing housing (9) arranged and acted upon by a spring element (13) caused spring force in the axial direction to the bearing, characterized in that the acted upon by a spring force sealing element (4) is formed and arranged in the gap between the shaft and the bearing housing is that at a negative pressure in the region of the compressor wheel (7) due to a voltage across the sealing element (4) applied pressure difference, the sealing element (4) is acted upon with a force whose axial component acts in the same direction as the spring force.
2. Abgasturbolader nach Anspruch 1 , wobei der Spalt mindestens eine Umlenkung in entgegengesetzter Richtung erfährt, und das mit der Federkraft beaufschlagte Dichtelement (14) im in entgegengesetzter Richtung verlaufenden Spaltabschnitt angeordnet ist, so dass bei Unterdruck im Bereich des Verdichterrades (7) das Dichtelement aufgrund des Unterdrucks in axialer Richtung zum Lager hin gedrückt wird.2. Exhaust gas turbocharger according to claim 1, wherein the gap undergoes at least one deflection in the opposite direction, and the acted upon by the spring force sealing element (14) is arranged in the opposite direction extending gap portion, so that at negative pressure in the region of the compressor wheel (7), the sealing element is pressed towards the bearing due to the negative pressure in the axial direction.
3. Abgasturbolader nach einem der Ansprüche 1 bis 4, wobei es sich beim Federelement um eine Feder (13), oder ein Federpaket, oder ein Elastomer handelt. 3. Exhaust gas turbocharger according to one of claims 1 to 4, wherein it is the spring element to a spring (13), or a spring assembly, or an elastomer.
4. Abgasturbolader nach einem der Ansprüche 1 oder 2, wobei ein Anschlag (11 ) des Lagergehäuses die axiale Verschiebbarkeit des Dichtelements (4) begrenzt.4. Exhaust gas turbocharger according to one of claims 1 or 2, wherein a stop (11) of the bearing housing limits the axial displaceability of the sealing element (4).
5. Abgasturbolader nach einem der Ansprüche 1 oder 2, wobei das Dichtelement (4) zum Sitz (92) des Lagergehäuses (9) mittels eines elastischen Elements (13) abgedichtet ist.5. Exhaust gas turbocharger according to one of claims 1 or 2, wherein the sealing element (4) to the seat (92) of the bearing housing (9) by means of an elastic element (13) is sealed.
6. Abgasturbolader nach einem der Ansprüche 1 oder 2, wobei das Dichtelement (4) zu dem zum Verdichter führenden Spalt eine kleinere Angriffsfläche aufweist als zu dem zum Lager (3) führenden Spalt.6. Exhaust gas turbocharger according to one of claims 1 or 2, wherein the sealing element (4) to the gap leading to the compressor has a smaller attack surface than to the bearing (3) leading gap.
7. Abgasturbolader nach einem der Ansprüche 1 bis 6, wobei das Dichtelement (4) in Kombination mit einem oder mehreren Kolbenringen eingesetzt wird. 7. Exhaust gas turbocharger according to one of claims 1 to 6, wherein the sealing element (4) is used in combination with one or more piston rings.
EP09768407A 2008-12-23 2009-12-16 Exhaust gas turbocharger Withdrawn EP2368018A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09768407A EP2368018A1 (en) 2008-12-23 2009-12-16 Exhaust gas turbocharger

Applications Claiming Priority (3)

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EP08172733A EP2202386A1 (en) 2008-12-23 2008-12-23 Turbocharger
PCT/EP2009/067296 WO2010072635A1 (en) 2008-12-23 2009-12-16 Exhaust gas turbocharger
EP09768407A EP2368018A1 (en) 2008-12-23 2009-12-16 Exhaust gas turbocharger

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EP08172733A Withdrawn EP2202386A1 (en) 2008-12-23 2008-12-23 Turbocharger
EP09768407A Withdrawn EP2368018A1 (en) 2008-12-23 2009-12-16 Exhaust gas turbocharger

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Publication number Priority date Publication date Assignee Title
DE102010038524B4 (en) * 2010-07-28 2020-08-13 Man Energy Solutions Se Turbo engine
KR102209976B1 (en) * 2013-04-09 2021-02-02 에이비비 스위츠랜드 엘티디. Housing of a radial compressor
JP6111978B2 (en) * 2013-10-28 2017-04-12 トヨタ自動車株式会社 Exhaust turbine turbocharger
EP2949872A1 (en) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomachine with a seal for separating working fluid and coolant fluid of the turbomachine and use of the turbomachine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3652183A (en) * 1970-10-15 1972-03-28 John E Pottharst Jr Compressor
US3784213A (en) * 1972-06-20 1974-01-08 Innovatex Corp Rotary face seal assembly
CA1148188A (en) * 1980-03-10 1983-06-14 Herman C. Laham Face seal system
US4391450A (en) * 1982-08-30 1983-07-05 Electrochemical Technology Corp. Shaft seal resistant to electrokinetic corrosion
DE3921880A1 (en) * 1989-07-04 1991-01-17 Kloeckner Humboldt Deutz Ag Bearing sealing system for turbo-supercharger - has additional seal which is operational under negative pressure difference
GB2359863B (en) 2000-03-04 2003-03-26 Alstom Turbocharger
DE20307447U1 (en) * 2003-05-13 2003-08-28 Burgmann Automotive Gmbh Axial plain bearing arrangement, in particular for charge compressors of internal combustion engines

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010072635A1 *

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