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EP3548705B1 - Turbocharger - Google Patents

Turbocharger Download PDF

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Publication number
EP3548705B1
EP3548705B1 EP17768032.9A EP17768032A EP3548705B1 EP 3548705 B1 EP3548705 B1 EP 3548705B1 EP 17768032 A EP17768032 A EP 17768032A EP 3548705 B1 EP3548705 B1 EP 3548705B1
Authority
EP
European Patent Office
Prior art keywords
flange
turbine
housing
bearing housing
nozzle ring
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
EP17768032.9A
Other languages
German (de)
French (fr)
Other versions
EP3548705A1 (en
Inventor
Björn Hossbach
Tobias Weisbrod
Paul Schorer
Lukas BOZEK
Jan REZANINA
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.)
Everllence SE
Original Assignee
MAN Energy Solutions SE
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Publication date
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Publication of EP3548705A1 publication Critical patent/EP3548705A1/en
Application granted granted Critical
Publication of EP3548705B1 publication Critical patent/EP3548705B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to a turbocharger.
  • a turbocharger has a turbine in which a first medium is expanded. Furthermore, a turbocharger has a compressor in which a second medium is compressed using the energy obtained in the turbine when the first medium is expanded.
  • the turbine of the turbocharger has a turbine housing and a turbine rotor.
  • the compressor of the turbocharger has a compressor housing and a compressor rotor.
  • a bearing housing is positioned between the turbine housing of the turbine and the compressor housing of the compressor, the bearing housing being connected on the one hand to the turbine housing and on the other hand to the compressor housing.
  • a shaft via which the turbine rotor is coupled to the compressor rotor is mounted in the bearing housing.
  • the turbine housing of the turbine namely a so-called turbine inflow housing
  • the bearing housing are connected to one another via a fastening device, which is preferably designed as a clamping claw.
  • a fastening device preferably designed as a clamping claw
  • Such a fastening device is mounted with a first section of the same on a flange of the turbine housing via fastening means and covers a flange of the bearing housing at least in sections with a second section.
  • the assembly or assembly of the bearing housing and the turbine housing is braced by means of such a fastening device, in particular with clamping of a flange of a nozzle ring and possibly a flange of a heat shield between the flange of the turbine housing and the flange of the bearing housing.
  • the turbine housing is filled with the first medium to be expanded, in particular with exhaust gas to be expanded.
  • the turbine inflow housing of the turbine housing directs the exhaust gas towards the turbine rotor.
  • In the turbine inflow housing there is an overpressure in relation to the environment, which is reduced in the turbine while generating energy during the expansion of the first medium. Leakage can occur in the area of the connection point between the turbine housing or the turbine inflow housing and the bearing housing, so that the first medium to be expanded in the turbine can reach the environment via the connection area between the turbine housing and the bearing housing. This is a disadvantage.
  • the tension between the turbine housing or the turbine inflow housing and the bearing housing is increased in practice, in particular by means of higher tightening torques for the fastening means by which the fastening device, which is preferably designed as a clamping claw, is mounted on the turbine housing.
  • This also increases a clamping force between the fastening device and the bearing housing. A contact point between the bearing housing and the fastening device is exposed to high relative movements as a result of the different thermal expansions of the bearing housing and turbine housing or turbine inflow housing.
  • DE 102 97 203 T5 discloses a turbocharger having a compressor, a turbine and a bearing housing.
  • a flange is disclosed in the area of the turbine which is formed at one end of a piston of the turbine. This flange has slots to receive guide vanes.
  • the piston is a sliding piston and can therefore be moved in a sliding manner. The relative position of the flange changes depending on the movement of the piston.
  • the present invention is based on the object of creating a turbocharger with a novel flange connection.
  • a turbocharger according to claim 1. Thereafter, between the flange of the bearing housing and the flange of the turbine housing, between the flange of the bearing housing and the flange of the heat shield, which has a recess, a spring element is positioned in the recess of the flange of the heat shield, which the flange of the heat shield axially against the Flange of the nozzle ring and so presses the flange of the nozzle ring axially against the flange of the turbine housing.
  • This also enables a particularly advantageous sealing of the connection point between the turbine housing or the turbine inflow housing and the bearing housing. The risk is reduced that the medium to be expanded in the turbine gets into the environment via the connection area between the turbine housing and the bearing housing.
  • the invention relates to a turbocharger.
  • a turbocharger has a turbine for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger has a compressor for compressing a second medium, in particular charge air, to be precise using the energy obtained in the turbine when the first medium is expanded.
  • the turbine has a turbine housing and a turbine rotor.
  • the compressor has a compressor housing and a compressor rotor. The compressor rotor is coupled to the turbine rotor via a shaft that is journalled in a bearing housing, the bearing housing being positioned between the turbine housing and the compressor housing and being connected to both the turbine housing and the compressor housing.
  • the invention now relates to such details of a turbocharger which connect the turbine housing of a turbine, which is preferably designed as a radial turbine and bearing housings of a turbocharger relate to.
  • a turbocharger which connect the turbine housing of a turbine, which is preferably designed as a radial turbine and bearing housings of a turbocharger relate to.
  • Figs. 1 to 3 different examples of turbochargers described, wherein Figs. 1 to 3 each show corresponding sections from a turbocharger in the area of the connection between the turbine housing and the bearing housing.
  • FIG. 1 An example of a turbocharger not according to the invention is shown Fig. 1 , where in Fig. 1 the connection point between a turbine housing, namely a turbine inflow housing 1 of the turbine housing, and a bearing housing 2 of the exhaust gas turbocharger is shown. Also shows Fig. 1 a nozzle ring 3, a heat shield 4 and a so-called insert 11.
  • the turbine inflow housing 1 is connected to the bearing housing 2 via a fastening device 5 in such a way that the fastening device 5 is mounted on a flange 6 of the turbine inflow housing 1 with a first section 7, namely via several fastening means 8, and that the fastening device 5 with a second section 9 covers a flange 10 of the bearing housing 2 at least in sections.
  • the fastening device 5 is also referred to as a clamping claw and clamps the turbine inflow housing 1 and bearing housing 2 together.
  • the fastening device 5 can be segmented as seen in the circumferential direction.
  • each fastening means 8 comprises a threaded screw 8a screwed into the flange 6 of the turbine inflow housing 1 and a nut 8b engaging the other end of the threaded screw 8a, whereby by tightening the nuts 8b, a defined pretensioning force is exerted on the turbine inflow housing 1 and on the fastening device 5 Bearing housing 10 can be applied.
  • nozzle ring 3 of the turbine is installed in such a way that a flange 13 of the nozzle ring 3 is based on a Flow channel 24 of the turbine, in the region of which the nozzle ring 3 is arranged, is positioned on a side of the flow channel 24 opposite the flange 6 of the turbine inflow housing 1 and thus the flange 10 of the bearing housing 2.
  • the flange 13 of the nozzle ring 3 can be attached to a section 14 of the turbine inflow housing 1, which, like the flange 13 of the nozzle ring 3, is on the opposite side in relation to the flow channel 24 in the bracing area between the flanges 6, 10 of the turbine inflow housing 1 and bearing housing 2 of the flow channel 24 is positioned.
  • the flange 13 of the nozzle ring 3 engages at least in sections in a recess 15 of this section 14 of the turbine inflow housing 1, the flange 13 of the nozzle ring 3 seen in the radial direction with one end at a boundary of this recess 15 of the section 14 of the turbine inflow housing 1 and at one end opposite end on the insert 11 is supported.
  • an elastic spring element 16 is received, which presses against the flange 13 of the nozzle ring 3 in the axial direction.
  • FIG. 2 Another example of a turbocharger not according to the invention is shown Fig. 2 . Also in Fig. 2 the flange 13 of the nozzle ring 3 is positioned on a side of the flow channel 24 of the turbine opposite the bracing area of the flanges 6, 10 of the turbine inflow housing 1 and bearing housing 2.
  • Fig. 2 differs from the example of Fig. 1 by the fact that in Fig. 2 the flange 13 of the nozzle ring 3 is mounted on the section 14 of the bearing housing 1 via a fastening device designed as a feather key 17, which is received in a corresponding recess 18 of the section 14 of the bearing housing 1. Also in Fig. 2 the flange 13 of the nozzle ring 3 protrudes at least in sections into the recess 18 of the section 4 of the turbine inflow housing 1.
  • FIG. 2 Another difference of the example of the Fig. 2 compared to the example of Fig. 1 is that in Fig. 2 the flange 12 of the heat shield 4 is not clamped between the flanges 6, 10 of the turbine inflow housing 1 and the bearing housing 2. Rather, comes in Fig. 2 the flange 10 of the bearing housing 2 directly on the flange 6 of the turbine inflow housing 1 to the plant.
  • a sealing element 19 can also be positioned, which can be a preferably metallic sealing ring in the form of an O-ring or C-ring.
  • the sealing element 19 can also be made of graphite.
  • the sealing element 19 is in a recess 20 of the flange 6 of the turbine inflow housing 1 and seals, in particular in the axial direction, between sealing surfaces of the flanges 6, 10 of the turbine inflow housing 1 and the bearing housing 2 that lie against one another.
  • the nozzle ring 3 is also possible to design the nozzle ring 3 as an integral part of the insert 11. In this case, the nozzle ring 3 does not have to be attached separately to the turbine inflow housing 1. Rather, the insert 11, which provides the nozzle ring 3 as an integral assembly, then takes over the reception of the same in the turbine.
  • Fig. 3 shows an embodiment of a turbocharger according to the invention.
  • the flange 13 of the nozzle ring 3 and the flange 12 of the heat shield 4 both clamped between the flange 10 of the bearing housing 2 and the flange 6 of the turbine inflow housing 1, namely via the clamping device applied via the fastening device 5 Clamping force.
  • a spring element 22 is positioned between the flange 10 of the bearing housing 2 and the flange 6 of the turbine housing 1 and presses the flange 13 of the nozzle ring 3 axially against the flange 6 of the turbine inflow housing 1.
  • this spring element 22 between the flange 10 of the bearing housing 2 and the Flange 12 of the heat shield 4 is arranged so that the spring element 22 presses the flange 12 of the heat shield 4 against the flange 13 of the nozzle ring 3 and thus the flange 13 of the nozzle ring 3 against the flange 6 of the turbine inflow housing 1.
  • the spring element 22 is supported on the one hand on the flange 10 of the bearing housing 2 and on the other hand on the flange 12 of the heat shield 4. As already stated, the spring element 22 presses the flange 13 of the nozzle ring 3 in the axial direction against the flange 6 of the turbine inflow housing 1, whereby, even if these assemblies are subject to different thermal expansion during operation, a good sealing effect is always achieved in the connection area between the bearing housing 2 and the turbine inflow housing 1 is guaranteed, so that there is no risk of exhaust gas flowing out into the environment via this connection area.
  • clamping devices such as clamping claws
  • the flange of the bearing housing is screwed directly to the turbine inflow housing. This results in a clear sealing surface between flange 10 and flange 6, over which the entire force flow of the fastening elements 8 runs.
  • the heat shield and nozzle ring can then be clamped via a spring element 22.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft einen Turbolader.The invention relates to a turbocharger.

Aus der DE 10 2013 002 605 A1 ist der grundsätzliche Aufbau eines Turboladers bekannt. Ein Turbolader verfügt über eine Turbine, in der ein erstes Medium entspannt wird. Ferner verfügt ein Turbolader über einen Verdichter, in dem ein zweites Medium verdichtet wird, und zwar unter Nutzung der in der Turbine bei der Entspannung des ersten Mediums gewonnenen Energie. Die Turbine des Turboladers verfügt über ein Turbinengehäuse sowie einen Turbinenrotor. Der Verdichter des Turboladers verfügt über ein Verdichtergehäuse sowie einen Verdichterrotor. Zwischen dem Turbinengehäuse der Turbine und dem Verdichtergehäuse des Verdichters ist ein Lagergehäuse positioniert, wobei das Lagergehäuse einerseits mit dem Turbinengehäuse und andererseits mit dem Verdichtergehäuse verbunden ist. Im Lagergehäuse ist eine Welle gelagert, über die der Turbinenrotor mit dem Verdichterrotor gekoppelt ist.From the DE 10 2013 002 605 A1 the basic structure of a turbocharger is known. A turbocharger has a turbine in which a first medium is expanded. Furthermore, a turbocharger has a compressor in which a second medium is compressed using the energy obtained in the turbine when the first medium is expanded. The turbine of the turbocharger has a turbine housing and a turbine rotor. The compressor of the turbocharger has a compressor housing and a compressor rotor. A bearing housing is positioned between the turbine housing of the turbine and the compressor housing of the compressor, the bearing housing being connected on the one hand to the turbine housing and on the other hand to the compressor housing. A shaft via which the turbine rotor is coupled to the compressor rotor is mounted in the bearing housing.

Aus der Praxis ist es bekannt, dass das Turbinengehäuse der Turbine, nämlich ein sogenanntes Turbinenzuströmgehäuse, sowie das Lagergehäuse über eine vorzugsweise als Spannpratze ausgebildete Befestigungseinrichtung miteinander verbunden sind. Eine derartige, vorzugsweise als Spannpratze ausgebildete Befestigungseinrichtung ist mit einem ersten Abschnitt derselben an einem Flansch des Turbinengehäuses über Befestigungsmittel montiert und überdeckt mit einem zweiten Abschnitt einen Flansch des Lagergehäuses zumindest abschnittsweise. Über eine derartige Befestigungseinrichtung wird der Verband bzw. Verbund aus Lagergehäuse und Turbinengehäuse verspannt, insbesondere unter Klemmen eines Flanschs eines Düsenrings und gegebenenfalls eines Flanschs eines Hitzeschildes zwischen dem Flansch des Turbinengehäuses und dem Flansch des Lagergehäuses.It is known from practice that the turbine housing of the turbine, namely a so-called turbine inflow housing, and the bearing housing are connected to one another via a fastening device, which is preferably designed as a clamping claw. Such a fastening device, preferably designed as a clamping claw, is mounted with a first section of the same on a flange of the turbine housing via fastening means and covers a flange of the bearing housing at least in sections with a second section. The assembly or assembly of the bearing housing and the turbine housing is braced by means of such a fastening device, in particular with clamping of a flange of a nozzle ring and possibly a flange of a heat shield between the flange of the turbine housing and the flange of the bearing housing.

Das Turbinengehäuse ist mit dem zu entspannenden ersten Medium gefüllt, insbesondere mit zu entspannendem Abgas. Das Turbinenzuströmgehäuse des Turbinengehäuses leitet das Abgas in Richtung auf den Turbinenrotor. Im Turbinenzuströmgehäuse besteht ein Überdruck gegenüber der Umgebung, der in der Turbine unter Gewinnung von Energie bei der Entspannung des ersten Mediums abgebaut wird. Im Bereich der Verbindungsstelle von Turbinengehäuse bzw. Turbinenzuströmgehäuse und Lagergehäuse kann es zu einer Leckage kommen, sodass das erste, in der Turbine zu entspannende Medium über den Verbindungsbereich zwischen Turbinengehäuse und Lagergehäuse in die Umgebung gelangen kann. Dies ist von Nachteil.The turbine housing is filled with the first medium to be expanded, in particular with exhaust gas to be expanded. The turbine inflow housing of the turbine housing directs the exhaust gas towards the turbine rotor. In the turbine inflow housing there is an overpressure in relation to the environment, which is reduced in the turbine while generating energy during the expansion of the first medium. Leakage can occur in the area of the connection point between the turbine housing or the turbine inflow housing and the bearing housing, so that the first medium to be expanded in the turbine can reach the environment via the connection area between the turbine housing and the bearing housing. This is a disadvantage.

Um einer derartigen Leckage des in der Turbine zu entspannenden ersten Mediums entgegenzuwirken, wird in der Praxis die Verspannung zwischen Turbinengehäuse bzw. Turbinenzuströmgehäuse und Lagergehäuse erhöht, insbesondere über höhere Anzugsmomente für die Befestigungsmittel, über welche die vorzugsweise als Spannpratze ausgebildete Befestigungseinrichtung am Turbinengehäuse montiert ist. Hierdurch erhöht sich auch eine Klemmkraft zwischen der Befestigungseinrichtung und dem Lagergehäuse. Eine Kontaktstelle zwischen dem Lagergehäuse und der Befestigungseinrichtung ist infolge der unterschiedlichen thermischen Ausdehnungen von Lagergehäuse und Turbinengehäuse bzw. Turbinenzuströmgehäuse hohen Relativbewegungen ausgesetzt. In Verbindung mit einem hohen Kontaktdruck bzw. einer hohen Vorspannung bzw. einer hohen Klemmkraft zwischen dem Lagergehäuse und der Befestigungseinrichtung kann es dann in Folge eines sogenannten Grabeffekts zu einem Verschleiß an der Befestigungseinrichtung und/oder am Lagergehäuse kommen. Hierdurch kann dann eine Leckage des in der Turbine zu entspannenden ersten Mediums in die Umgebung verursacht werden.In order to counteract such a leakage of the first medium to be expanded in the turbine, the tension between the turbine housing or the turbine inflow housing and the bearing housing is increased in practice, in particular by means of higher tightening torques for the fastening means by which the fastening device, which is preferably designed as a clamping claw, is mounted on the turbine housing. This also increases a clamping force between the fastening device and the bearing housing. A contact point between the bearing housing and the fastening device is exposed to high relative movements as a result of the different thermal expansions of the bearing housing and turbine housing or turbine inflow housing. In connection with a high contact pressure or a high preload or a high clamping force between the bearing housing and the fastening device, wear on the fastening device and / or on the bearing housing can then occur as a result of a so-called digging effect. This can then cause the first medium to be expanded in the turbine to leak into the environment.

DE 102 97 203 T5 offenbart einen Turbolader mit einem Verdichter, einer Turbine und einem Lagergehäuse. Es ist ein Flansch im Bereich der Turbine offenbart, der an einem Ende eines Kolbens der Turbine ausgebildet ist. Dieser Flansch weist Schlitze auf, um Leitschaufeln aufzunehmen. Der Kolben ist ein gleitender Kolben, derselbe ist demnach gleitend bewegbar. Abhängig von der Bewegung des Kolbens ändert sich die Relativposition des Flansches. DE 102 97 203 T5 discloses a turbocharger having a compressor, a turbine and a bearing housing. A flange is disclosed in the area of the turbine which is formed at one end of a piston of the turbine. This flange has slots to receive guide vanes. The piston is a sliding piston and can therefore be moved in a sliding manner. The relative position of the flange changes depending on the movement of the piston.

DE 10 2009 024 151 A1 offenbart ein Turbinengehäuse eines Abgasturboladers. DE 10 2009 024 151 A1 discloses a turbine housing of an exhaust gas turbocharger.

Aus EP 2 960 460 A1 , JP S61 85503 A und US 2015/1025275 A1 ist weiterer Stand der Technik bekannt.Out EP 2 960 460 A1 , JP S61 85503 A and US 2015/1025275 A1 further prior art is known.

Hiervon ausgehend liegt der vorliegenden Erfindung die Aufgabe zugrunde, einen Turbolader mit einer neuartigen Flanschverbindung zu schaffen.Proceeding from this, the present invention is based on the object of creating a turbocharger with a novel flange connection.

Diese Aufgabe wird durch einen Turbolader nach Anspruch 1 gelöst. Hiernach ist zwischen dem Flansch des Lagergehäuses und dem Flansch des Turbinengehäuses, und zwar zwischen dem Flansch des Lagergehäuses und dem Flansch des Hitzeschilds, der eine Ausnehmung aufweist, in der Ausnehmung des Flanschs des Hitzeschilds ein Federelement positioniert, welches den Flansch des Hitzeschilds axial gegen den Flansch des Düsenrings und so den Flansch des Düsenrings axial gegen den Flansch des Turbinengehäuses drückt. Auch hiermit ist eine besonders vorteilhafte Abdichtung der Verbindungsstelle von Turbinengehäuse bzw. Turbinenzuströmgehäuse und Lagergehäuse möglich. Es wird die Gefahr reduziert, dass in der Turbine zu entspannende Medium über den Verbindungsbereich zwischen Turbinengehäuse und Lagergehäuse in die Umgebung gelangt.This object is achieved by a turbocharger according to claim 1. Thereafter, between the flange of the bearing housing and the flange of the turbine housing, between the flange of the bearing housing and the flange of the heat shield, which has a recess, a spring element is positioned in the recess of the flange of the heat shield, which the flange of the heat shield axially against the Flange of the nozzle ring and so presses the flange of the nozzle ring axially against the flange of the turbine housing. This also enables a particularly advantageous sealing of the connection point between the turbine housing or the turbine inflow housing and the bearing housing. The risk is reduced that the medium to be expanded in the turbine gets into the environment via the connection area between the turbine housing and the bearing housing.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus dem Unteranspruch und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1:
einen ausschnittsweisen Querschnitt durch einen nicht erfindungsgemäßen Turbolader im Bereich einer Verbindung eines Turbinengehäuses mit einem Lagergehäuse;
Fig. 2:
einen ausschnittsweisen Querschnitt durch einen nicht erfindungsgemäßen Turbolader im Bereich einer Verbindung eines Turbinengehäuses mit einem Lagergehäuse; und
Fig. 3:
einen ausschnittsweisen Querschnitt durch einen erfindungsgemäßen Turbolader im Bereich einer Verbindung eines Turbinengehäuses mit einem Lagergehäuse.
Preferred developments of the invention emerge from the dependent claim and the following description. Embodiments of the invention are explained in more detail with reference to the drawing, without being restricted to this. It shows:
Fig. 1:
a partial cross-section through a turbocharger not according to the invention in the area of a connection between a turbine housing and a bearing housing;
Fig. 2:
a partial cross-section through a turbocharger not according to the invention in the area of a connection between a turbine housing and a bearing housing; and
Fig. 3:
a partial cross-section through a turbocharger according to the invention in the area of a connection between a turbine housing and a bearing housing.

Die Erfindung betrifft einen Turbolader.The invention relates to a turbocharger.

Ein Turbolader verfügt über eine Turbine zur Entspannung eines ersten Mediums, insbesondere zur Entspannung von Abgas einer Brennkraftmaschine. Ferner verfügt ein Turbolader über einen Verdichter zur Verdichtung eines zweiten Mediums, insbesondere von Ladeluft, und zwar unter Nutzung von in der Turbine bei der Entspannung des ersten Mediums gewonnener Energie. Die Turbine verfügt dabei über ein Turbinengehäuse und einen Turbinenrotor. Der Verdichter verfügt über ein Verdichtergehäuse und einen Verdichterrotor. Der Verdichterrotor ist mit dem Turbinenrotor über eine Welle gekoppelt, die in einem Lagergehäuse gelagert ist, wobei das Lagergehäuse zwischen dem Turbinengehäuse und dem Verdichtergehäuse positioniert und sowohl mit dem Turbinengehäuse und dem Verdichtergehäuse verbunden ist. Dieser grundsätzliche Aufbau eines Turboladers ist dem hier angesprochenen Fachmann geläufig.A turbocharger has a turbine for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger has a compressor for compressing a second medium, in particular charge air, to be precise using the energy obtained in the turbine when the first medium is expanded. The turbine has a turbine housing and a turbine rotor. The compressor has a compressor housing and a compressor rotor. The compressor rotor is coupled to the turbine rotor via a shaft that is journalled in a bearing housing, the bearing housing being positioned between the turbine housing and the compressor housing and being connected to both the turbine housing and the compressor housing. This basic structure of a turbocharger is familiar to the person skilled in the art addressed here.

Die Erfindung betrifft nun solche Details eines Turboladers, die die Verbindung von Turbinengehäuse einer vorzugsweise als Radialturbine ausgebildeten Turbine und Lagergehäuse eines Turboladers betreffen. Nachfolgend werden unter Bezugnahme auf Fig. 1 bis 3 unterschiedliche Beispiele von Turboladern beschrieben, wobei Fig. 1 bis 3 jeweils entsprechende Ausschnitte aus einem Turbolader im Bereich der Verbindung des Turbinengehäuses mit dem Lagergehäuse zeigen.The invention now relates to such details of a turbocharger which connect the turbine housing of a turbine, which is preferably designed as a radial turbine and bearing housings of a turbocharger relate to. In the following, with reference to Figs. 1 to 3 different examples of turbochargers described, wherein Figs. 1 to 3 each show corresponding sections from a turbocharger in the area of the connection between the turbine housing and the bearing housing.

Ein nicht erfindungsgemäßes Beispiel eines Turboladers zeigt Fig. 1, wobei in Fig. 1 die Verbindungsstelle zwischen einem Turbinengehäuse, nämlich einem Turbinenzuströmgehäuse 1 des Turbinengehäuses, und einem Lagergehäuse 2 des Abgasturboladers gezeigt ist. Ferner zeigt Fig. 1 einen Düsenring 3, einen Hitzeschild 4 und ein sogenanntes Einsatzstück 11.An example of a turbocharger not according to the invention is shown Fig. 1 , where in Fig. 1 the connection point between a turbine housing, namely a turbine inflow housing 1 of the turbine housing, and a bearing housing 2 of the exhaust gas turbocharger is shown. Also shows Fig. 1 a nozzle ring 3, a heat shield 4 and a so-called insert 11.

Das Turbinenzuströmgehäuse 1 ist mit dem Lagergehäuse 2 über eine Befestigungseinrichtung 5 derart verbunden, dass die Befestigungseinrichtung 5 an einem Flansch 6 des Turbinenzuströmgehäuses 1 mit einem ersten Abschnitt 7 montiert ist, und zwar über mehrere Befestigungsmittel 8, und dass die Befestigungseinrichtung 5 mit einem zweiten Abschnitt 9 einen Flansch 10 des Lagergehäuses 2 zumindest abschnittsweise überdeckt. Die Befestigungseinrichtung 5 wird auch als Spannpratze bezeichnet und verspannt das Turbinenzuströmgehäuse 1 und Lagergehäuse 2 miteinander. Die Befestigungseinrichtung 5 kann in Umfangsrichtung gesehen segmentiert sein.The turbine inflow housing 1 is connected to the bearing housing 2 via a fastening device 5 in such a way that the fastening device 5 is mounted on a flange 6 of the turbine inflow housing 1 with a first section 7, namely via several fastening means 8, and that the fastening device 5 with a second section 9 covers a flange 10 of the bearing housing 2 at least in sections. The fastening device 5 is also referred to as a clamping claw and clamps the turbine inflow housing 1 and bearing housing 2 together. The fastening device 5 can be segmented as seen in the circumferential direction.

Im in Fig. 1 und 2 gezeigten Beispiel umfasst jedes Befestigungsmittel 8 eine in den Flansch 6 des Turbinenzuströmgehäuses 1 eingeschraubte Gewindeschraube 8a sowie eine an dem anderen Ende der Gewindeschraube 8a angreifende Mutter 8b, wobei durch Anziehen der Muttern 8b eine definierte Vorspannkraft über die Befestigungseinrichtung 5 auf das Turbinenzuströmgehäuse 1 und auf das Lagergehäuse 10 aufgebracht werden kann.In the in Fig. 1 and 2 As shown in the example, each fastening means 8 comprises a threaded screw 8a screwed into the flange 6 of the turbine inflow housing 1 and a nut 8b engaging the other end of the threaded screw 8a, whereby by tightening the nuts 8b, a defined pretensioning force is exerted on the turbine inflow housing 1 and on the fastening device 5 Bearing housing 10 can be applied.

Bei dem in Fig. 1 gezeigten Beispiel eines Abgasturboladers ist der Düsenring 3 der Turbine derart verbaut, dass ein Flansch 13 des Düsenrings 3 bezogen auf einen Strömungskanal 24 der Turbine, im Bereich dessen der Düsenring 3 angeordnet ist, auf einer dem Flansch 6 des Turbinenzuströmgehäuses 1 und damit dem Flansch 10 des Lagergehäuses 2 gegenüberliegenden Seite des Strömungskanals 24 positioniert ist.The in Fig. 1 The example of an exhaust gas turbocharger shown, the nozzle ring 3 of the turbine is installed in such a way that a flange 13 of the nozzle ring 3 is based on a Flow channel 24 of the turbine, in the region of which the nozzle ring 3 is arranged, is positioned on a side of the flow channel 24 opposite the flange 6 of the turbine inflow housing 1 and thus the flange 10 of the bearing housing 2.

So ist im Beispiel der Fig. 1 zwischen dem über die Befestigungseinrichtung 5 verspannten Flansch 10 des Turbinenzuströmgehäuses 1 und dem Flansch 10 des Lagergehäuses 2 ausschließlich ein Flansch 12 des Hitzeschildess 4 geklemmt. Der Flansch 13 des Düsenrings 3 hingegen ist nicht mehr in diesem Verspannbereich von Lagergehäuse 1 und Turbinenzuströmgehäuse 2 zwischen den Flanschen 6, 10 derselben geklemmt, wodurch die Anzahl der Bauteile im Spannverband reduziert und eine klar definierte Dichtstelle im Spannverband geschaffen wird. Hierdurch kann die Gefahr reduziert werden, dass Abgas über den Verbindungsbereich zwischen den Flanschen 6, 10 von Turbinenzuströmgehäuse 1 und Lagergehäuse 2 in die Umgebung gelangt.So in the example is the Fig. 1 Only one flange 12 of the heat shield 4 is clamped between the flange 10 of the turbine inflow housing 1, which is braced by the fastening device 5, and the flange 10 of the bearing housing 2. The flange 13 of the nozzle ring 3, on the other hand, is no longer clamped in this bracing area of the bearing housing 1 and turbine inflow casing 2 between the flanges 6, 10 of the same, which reduces the number of components in the clamping association and creates a clearly defined sealing point in the clamping association. This can reduce the risk that exhaust gas will get into the environment via the connection area between the flanges 6, 10 of the turbine inflow housing 1 and the bearing housing 2.

Der Flansch 13 des Düsenrings 3 kann an einem Abschnitt 14 des Turbinenzuströmgehäuses 1 befestigt sein, der ebenso wie der Flansch 13 des Düsenrings 3, bezogen auf den Strömungskanal 24 auf der im Verspannbereich zwischen den Flanschen 6, 10 von Turbinenzuströmgehäuse 1 und Lagergehäuse 2 gegenüberliegenden Seite des Strömungskanals 24 positioniert ist.The flange 13 of the nozzle ring 3 can be attached to a section 14 of the turbine inflow housing 1, which, like the flange 13 of the nozzle ring 3, is on the opposite side in relation to the flow channel 24 in the bracing area between the flanges 6, 10 of the turbine inflow housing 1 and bearing housing 2 of the flow channel 24 is positioned.

Im Beispiel der Fig. 1 greift der Flansch 13 des Düsenrings 3 zumindest abschnittsweise in eine Ausnehmung 15 dieses Abschnitts 14 des Turbinenzuströmgehäuses 1 ein, wobei sich der Flansch 13 des Düsenrings 3 in Radialrichtung gesehen mit einem Ende an einer Begrenzung dieser Ausnehmung 15 des Abschnitts 14 des Turbinenzuströmgehäuses 1 und an einem gegenüberliegenden Ende am Einsatzstück 11 abstützt. In die Ausnehmung 15 des Abschnitts 14 des Turbinenzuströmgehäuses 1, an welchem der Flansch 13 des Düsenrings 3 abgestützt ist, ist ein elastisches Federelement 16 aufgenommen, welches gegen den Flansch 13 des Düsenrings 3 in Axialrichtung drückt. Dabei drückt dieses elastische Federelement 16 derart gegen den Flansch 13 des Düsenrings 3, dass der Düsenring 3 von dem Federelement 16 in Richtung auf den Verbindungsbereich der Flansche 6, 10 von Turbinenzuströmgehäuse 1 und Lagergehäuse 2 gedrückt wird. Im Beispiel der Fig. 1 drückt der Düsenring 3 gegen den Flansch 12 des Hitzeschilds 4.In the example of the Fig. 1 the flange 13 of the nozzle ring 3 engages at least in sections in a recess 15 of this section 14 of the turbine inflow housing 1, the flange 13 of the nozzle ring 3 seen in the radial direction with one end at a boundary of this recess 15 of the section 14 of the turbine inflow housing 1 and at one end opposite end on the insert 11 is supported. In the recess 15 of the section 14 of the turbine inflow housing 1, on which the flange 13 of the nozzle ring 3 is supported, an elastic spring element 16 is received, which presses against the flange 13 of the nozzle ring 3 in the axial direction. This pushes the elastic Spring element 16 against flange 13 of nozzle ring 3 in such a way that nozzle ring 3 is pressed by spring element 16 in the direction of the connecting area of flanges 6, 10 of turbine inflow housing 1 and bearing housing 2. In the example of the Fig. 1 the nozzle ring 3 presses against the flange 12 of the heat shield 4.

Ein weiteres nicht erfindungsgemäßes Beispiel eines Turboladers zeigt Fig. 2. Auch in Fig. 2 ist der Flansch 13 des Düsenrings 3 an einer dem Verspannbereich der Flansche 6, 10 von Turbinenzuströmgehäuse 1 und Lagergehäuse 2 gegenüberliegenden Seite des Strömungskanals 24 der Turbine positioniert.Another example of a turbocharger not according to the invention is shown Fig. 2 . Also in Fig. 2 the flange 13 of the nozzle ring 3 is positioned on a side of the flow channel 24 of the turbine opposite the bracing area of the flanges 6, 10 of the turbine inflow housing 1 and bearing housing 2.

Das Beispiel der Fig. 2 unterscheidet sich vom Beispiel der Fig. 1 dadurch, dass in Fig. 2 der Flansch 13 des Düsenrings 3 an dem Abschnitt 14 des Lagergehäuses 1 über eine als Passfeder 17 ausgebildete Befestigungseinrichtung montiert ist, die in einer entsprechenden Ausnehmung 18 des Abschnitts 14 des Lagergehäuses 1 aufgenommen ist. Auch in Fig. 2 ragt der Flansch 13 des Düsenrings 3 zumindest abschnittsweise in die Ausnehmung 18 des Abschnitts 4 des Turbinenzuströmgehäuses 1 hinein.The example of Fig. 2 differs from the example of Fig. 1 by the fact that in Fig. 2 the flange 13 of the nozzle ring 3 is mounted on the section 14 of the bearing housing 1 via a fastening device designed as a feather key 17, which is received in a corresponding recess 18 of the section 14 of the bearing housing 1. Also in Fig. 2 the flange 13 of the nozzle ring 3 protrudes at least in sections into the recess 18 of the section 4 of the turbine inflow housing 1.

Ein weiterer Unterschied des Beispiels der Fig. 2 gegenüber dem Beispiel der Fig. 1 besteht darin, dass in Fig. 2 der Flansch 12 des Hitzeschildes 4 nicht zwischen den Flanschen 6, 10 von Turbinenzuströmgehäuse 1 und Lagergehäuse 2 geklemmt ist. Vielmehr kommt in Fig. 2 der Flansch 10 des Lagergehäuses 2 unmittelbar am Flansch 6 des Turbinenzuströmgehäuses 1 zur Anlage.Another difference of the example of the Fig. 2 compared to the example of Fig. 1 is that in Fig. 2 the flange 12 of the heat shield 4 is not clamped between the flanges 6, 10 of the turbine inflow housing 1 and the bearing housing 2. Rather, comes in Fig. 2 the flange 10 of the bearing housing 2 directly on the flange 6 of the turbine inflow housing 1 to the plant.

In diesem Dichtbereich zwischen dem Flansch 10 des Lagergehäuses 2 und dem Flansch 6 des Turbinenzuströmgehäuses 1 kann zusätzlich ein Dichtelement 19 positioniert werden, bei welchem es sich um einen vorzugsweise metallischen Dichtring in Form eines O-Rings oder C-Rings handeln kann. Das Dichtelement 19 kann auch aus Grafit gefertigt sein. In Fig. 2 ist das Dichtelement 19 in einer Ausnehmung 20 des Flanschs 6 des Turbinenzuströmgehäuses 1 aufgenommen und dichtet insbesondere in Axialrichtung zwischen Dichtflächen der aneinanderliegenden Flansche 6, 10 von Turbinenzuströmgehäuse 1 und Lagergehäuse 2.In this sealing area between the flange 10 of the bearing housing 2 and the flange 6 of the turbine inflow housing 1, a sealing element 19 can also be positioned, which can be a preferably metallic sealing ring in the form of an O-ring or C-ring. The sealing element 19 can also be made of graphite. In Fig. 2 the sealing element 19 is in a recess 20 of the flange 6 of the turbine inflow housing 1 and seals, in particular in the axial direction, between sealing surfaces of the flanges 6, 10 of the turbine inflow housing 1 and the bearing housing 2 that lie against one another.

Im Beispiel der Fig. 2 greift der Flansch 12 des Hitzeschildes 4 am Flansch 10 des Lagergehäuses 2 an, ist jedoch, wie bereits ausgeführt, nicht zwischen dem Flansch 10 des Lagergehäuses 2 und dem Flansch 6 des Turbinenzuströmgehäuses 1 geklemmt. Vielmehr greift der Flansch 12 des Hitzeschildes 4 in Fig. 2 über eine Verdrehsicherung 21 am Flansch 10 des Lagergehäuses 2 an. In Fig. 2 ist die Anzahl der Bauteile im Spannverband zwischen Lagergehäuse 2 und Turbinenzuströmgehäuse 1 weiter reduziert.In the example of the Fig. 2 If the flange 12 of the heat shield 4 engages the flange 10 of the bearing housing 2, however, as already stated, it is not clamped between the flange 10 of the bearing housing 2 and the flange 6 of the turbine inflow housing 1. Rather, the flange 12 of the heat shield 4 engages in Fig. 2 A rotation lock 21 on the flange 10 of the bearing housing 2. In Fig. 2 the number of components in the clamping connection between bearing housing 2 and turbine inflow housing 1 is further reduced.

Es ist ebenfalls möglich, den Düsenring 3 als integralen Bestandteil des Einsatzstücks 11 auszubilden. In diesem Fall muss dann der Düsenring 3 nicht gesondert am Turbinenzuströmgehäuse 1 befestigt werden. Vielmehr übernimmt dann das Einsatzstück 11, welches den Düsenring 3 als integrale Baugruppe bereitstellt, die Aufnahme desselben in der Turbine.It is also possible to design the nozzle ring 3 as an integral part of the insert 11. In this case, the nozzle ring 3 does not have to be attached separately to the turbine inflow housing 1. Rather, the insert 11, which provides the nozzle ring 3 as an integral assembly, then takes over the reception of the same in the turbine.

Fig. 3 zeigt ein Ausführungsbeispiel eines Turboladers nach der Erfindung. In Fig. 3 sind, wie im Stand der Technik üblich, der Flansch 13 des Düsenrings 3 und der Flansch 12 des Hitzeschildes 4 beide zwischen dem Flansch 10 des Lagergehäuses 2 und dem Flansch 6 des Turbinenzuströmgehäuses 1 geklemmt, nämlich über die über die Befestigungseinrichtung 5 auf diesen Spannverband aufgebrachte Klemmkraft. Fig. 3 shows an embodiment of a turbocharger according to the invention. In Fig. 3 are, as is usual in the prior art, the flange 13 of the nozzle ring 3 and the flange 12 of the heat shield 4 both clamped between the flange 10 of the bearing housing 2 and the flange 6 of the turbine inflow housing 1, namely via the clamping device applied via the fastening device 5 Clamping force.

Nach der Erfindung ist vorgesehen, zwischen dem Flansch 10 des Lagergehäuses 2 und dem Flansch 6 des Turbinengehäuses 1 ein Federelement 22 zu positionieren, welches den Flansch 13 des Düsenrings 3 axial gegen den Flansch 6 des Turbinenzuströmgehäuses 1 drückt. Im Ausführungsbeispiel der Fig. 3 ist dieses Federelement 22 zwischen dem Flansch 10 des Lagergehäuses 2 und dem Flansch 12 des Hitzeschildes 4 angeordnet, sodass das Federelement 22 den Flansch 12 des Hitzeschildes 4 gegen den Flansch 13 des Düsenrings 3 und so den Flansch 13 des Düsenrings 3 gegen den Flansch 6 des Turbinenzuströmgehäuses 1 drückt.According to the invention, a spring element 22 is positioned between the flange 10 of the bearing housing 2 and the flange 6 of the turbine housing 1 and presses the flange 13 of the nozzle ring 3 axially against the flange 6 of the turbine inflow housing 1. In the embodiment of Fig. 3 is this spring element 22 between the flange 10 of the bearing housing 2 and the Flange 12 of the heat shield 4 is arranged so that the spring element 22 presses the flange 12 of the heat shield 4 against the flange 13 of the nozzle ring 3 and thus the flange 13 of the nozzle ring 3 against the flange 6 of the turbine inflow housing 1.

Dabei stützt sich das Federelement 22 einerseits am Flansch 10 des Lagergehäuses 2 und andererseits am Flansch 12 des Hitzeschilds 4 ab. Wie bereits ausgeführt, drückt das Federelement 22 den Flansch 13 des Düsenrings 3 in Axialrichtung gegen den Flansch 6 des Turbinenzuströmgehäuses 1, wodurch selbst dann, wenn diese Baugruppen im Betrieb einer unterschiedlichen thermischen Ausdehnung unterliegen, stets eine gute Dichtwirkung im Verbindungsbereich von Lagergehäuse 2 und Turbinenzuströmgehäuse 1 gewährleistet wird, sodass keine Gefahr besteht, dass Abgas über diesen Verbindungsbereich nach außen in die Umgebung strömt.The spring element 22 is supported on the one hand on the flange 10 of the bearing housing 2 and on the other hand on the flange 12 of the heat shield 4. As already stated, the spring element 22 presses the flange 13 of the nozzle ring 3 in the axial direction against the flange 6 of the turbine inflow housing 1, whereby, even if these assemblies are subject to different thermal expansion during operation, a good sealing effect is always achieved in the connection area between the bearing housing 2 and the turbine inflow housing 1 is guaranteed, so that there is no risk of exhaust gas flowing out into the environment via this connection area.

Nach der der Erfindung kann zudem auf spezielle Spannvorrichtungen, wie Spannpratzen, verzichtet werden. Der Flansch des Lagergehäuses wird direkt mit dem Turbinenzuströmgehäuse verschraubt. Dadurch ergibt sich eine eindeutige Dichtfläche zwischen Flansch 10 und Flansch 6, über diese verläuft der gesamte Kraftfluss der Befestigungselemente 8. Die Klemmung von Hitzeschild und Düsenring kann dann über ein Federelement 22 erfolgen.According to the invention, special clamping devices, such as clamping claws, can also be dispensed with. The flange of the bearing housing is screwed directly to the turbine inflow housing. This results in a clear sealing surface between flange 10 and flange 6, over which the entire force flow of the fastening elements 8 runs. The heat shield and nozzle ring can then be clamped via a spring element 22.

BezugszeichenlisteList of reference symbols

11
TurbinenzuströmgehäuseTurbine inlet casing
22
LagergehäuseBearing housing
33
DüsenringNozzle ring
44th
HitzeschildHeat shield
55
BefestigungseinrichtungFastening device
66th
Flanschflange
77th
Abschnittsection
88th
BefestigungsmittelFasteners
8a8a
Schraubescrew
8b8b
Muttermother
99
Abschnittsection
1010
Flanschflange
1111
EinsatzstückInsert
1212th
Flanschflange
1313th
DichtbereichSealing area
1414th
Abschnittsection
1515th
AusnehmungRecess
1616
FederelementSpring element
1717th
PassfederAdjusting spring
1818th
AusnehmungRecess
1919th
DichtelementSealing element
2020th
AusnehmungRecess
2121
VerdrehsicherungAnti-twist device
2222nd
FederelementSpring element
2424
StrömungskanalFlow channel

Claims (2)

  1. A turbocharger,
    having a turbine for expanding a first medium,
    having a compressor for compressing a second medium utilising energy extracted in the turbine during the expansion of the first medium,
    wherein the turbine comprises a turbine housing (1) with a flange (6) and a turbine rotor,
    wherein the compressor comprises a compressor housing and a compressor rotor that is coupled to the turbine rotor via a shaft,
    having a bearing housing (2), in which the shaft is mounted, wherein the bearing housing (2) comprises a flange (10),
    having a fastening device (5) which comprises a first section (7) and a second section (9),
    wherein the turbine housing (1) and the compressor housing are each connected to the bearing housing (2) arranged between the same,
    wherein the turbine housing (1) and the bearing housing (2) are connected via the fastening device (5) in such a manner that the fastening device is mounted with the first section (7) on the flange (6) of the turbine housing (1) and with the second section (9) overlaps the flange (10) of the bearing housing (2) at least in sections,
    having a nozzle ring (3) comprising a flange (13),
    having a heat shield (14) comprising a flange (12),
    wherein between the flange (6) of the turbine housing (1) and the flange (10) of the bearing housing (2) the flange (13) of the nozzle ring (3) and the flange (12) of the heat shield (14) are clamped,
    characterized in that
    between the flange (10) of the bearing housing (2) and the flange (6) of the turbine housing (1), namely between the flange (10) of the bearing housing (2) and the flange (12) of the heat shield (4), which comprises a recess, a spring element (22) is positioned in the recess of the flange (12) of the heat shield (4), which axially presses the flange (12) of the heat shield (14) against the flange (13) of the nozzle ring (3) and thus axially presses the flange (13) of the nozzle ring (3) against the flange (6) of the turbine housing (1).
  2. The turbocharger according to Claim 1, characterized in that the spring element (22) supports itself on the one side on the flange (12) of the heat shield (4) and on the other side on the flange (10) of the bearing housing (2).
EP17768032.9A 2016-12-01 2017-08-31 Turbocharger Active EP3548705B1 (en)

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KR20190086568A (en) 2019-07-22
CN110023589A (en) 2019-07-16
WO2018099619A1 (en) 2018-06-07

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