EP3073064B1 - Turbocharger - Google Patents

Turbocharger Download PDF

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Publication number
EP3073064B1
EP3073064B1 EP16165283.9A EP16165283A EP3073064B1 EP 3073064 B1 EP3073064 B1 EP 3073064B1 EP 16165283 A EP16165283 A EP 16165283A EP 3073064 B1 EP3073064 B1 EP 3073064B1
Authority
EP
European Patent Office
Prior art keywords
vane
stop
guide
turbocharger
lever
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.)
Expired - Fee Related
Application number
EP16165283.9A
Other languages
German (de)
French (fr)
Other versions
EP3073064A1 (en
Inventor
Ralf Böning
Dietmar Metz
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.)
BorgWarner Inc
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BorgWarner Inc
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Filing date
Publication date
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Publication of EP3073064A1 publication Critical patent/EP3073064A1/en
Application granted granted Critical
Publication of EP3073064B1 publication Critical patent/EP3073064B1/en
Expired - Fee Related legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/04—Multi-stage pumps specially adapted to the production of a high vacuum, e.g. molecular pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a turbocharger according to the preamble of claim 1.
  • Such a turbocharger is from the EP 1 564 380 A1 known.
  • this document proposes a stop which is integrally connected to the adjusting ring.
  • the projection of the stop of the known turbocharger limits the end positions by contact with mounting rings of the adjusting lever on the blades, which also makes precise adjustment of the end positions difficult, since the mounting rings of these blade adjustment levers are subject to manufacturing tolerances and on the other hand, due to the positioning (division) inaccuracies arise.
  • turbocharger specified in the preamble of claim 1, which allows a simplification of the assembly of the guide grid or diffuser, at least a simple and accurate adjustment of the minimum flow through the diffuser should be possible alone.
  • the stop with which at least one setting of the minimum flow through the nozzle cross-sections formed by the vanes is possible, is formed as a separate component which is fixable in the guide grid, it is possible after mounting the guide grid this stop in a simple way and way to rework the exact setting of the required stop position, since it is not integrally connected to the guide grid. If the need for a readjustment of one of the two end positions of the guide grid, it can be either simply selected and mounted a suitable fitment for the desired end position or adapted the intended stop member by reworking the projection and then mounted in the guide grille. Thus, it is possible to make a precise end position targeted, which is problematic in the generic turbocharger due to the integral formation of the stop.
  • the entire diffuser can be completely pre-assembled as a cartridge and the minimum flow can be adjusted before it is then inserted into the turbine housing.
  • the adjustment of the minimum flow is thus independent of turbine housing and other components of the turbocharger, such as e.g. the bearing housing. Also, the nozzle position between the bearing and turbine housing no longer has any influence on the minimum flow setting. Also, the wear of the adjusting lever and its engagement with the adjusting ring does not affect the minimum flow rate.
  • a guide grid is defined as each independently tradable objects.
  • FIG. 1 an inventive turbocharger 1 is shown, which has a turbine housing 2 and a compressor housing 3 connected thereto via a bearing housing 19.
  • the housings 2, 3 and 19 are arranged along a rotation axis R.
  • the turbine housing 2 is shown partially in section to illustrate the arrangement of a vane ring 6 as part of a radially outer baffle 18 having a plurality of circumferentially spaced vanes 7 with pivot shafts 8.
  • nozzle cross-sections are formed, which are larger or smaller depending on the position of the guide vanes 7 and the turbine rotor 4 mounted in the middle on the axis of rotation R more or less with the supplied via a feed channel 9 and discharged via a central port 10 exhaust gas of an engine, to drive over the turbine rotor 4 a seated on the same shaft compressor rotor 17.
  • an actuating device 11 is provided.
  • This can be designed to be arbitrary, but a preferred embodiment, a control housing 12, which controls the control movement of a ram member 14 attached to her to implement the movement thereof to a located behind the blade bearing ring 6 adjusting 5 in a slight rotational movement of the same.
  • a clearance 13 for the vanes 7 is formed between the vane ring 6 and an annular part 15 of the turbine housing 2.
  • the blade bearing ring 6 has integrally formed spacers 16.
  • three spacers 16 are arranged at an angular distance of 120 ° in each case on the circumference of the blade bearing ring 6. In principle, it is However, it is possible to provide more or less such spacers 16.
  • Fig. 2 is a partial perspective view of the guide grid 18 shown on an enlarged scale.
  • a blade lever 20 is shown having at one end a mounting ring 21 with a recess 22 in which one end of the blade shaft 8 is fixed.
  • a lever head 23 of the blade lever 20 is disposed in an engagement recess 24 of the adjusting ring 5 and thus is engaged with the adjusting ring 5 in engagement.
  • FIG. 2 the arrangement of a stop 25 in the form of a separate component.
  • the stop 25 has a stop body 26, which has been fixed in the illustrated embodiment on the blade bearing ring 6.
  • the stopper body 6 has a radially outwardly projecting projection 27, which engages in a groove 31 of the adjusting ring 5.
  • the groove 31 of the adjusting ring 5 is bounded by two stop cams 29 and 30.
  • the stop cams 29 and 30 have inwardly into the groove 31 facing abutment abutment surfaces which can engage with the corresponding adjacent surface of the projection 27.
  • a stop position on the stop cam 29 for adjusting the minimum flow through the nozzle cross sections of the guide grid 18 is shown.
  • a stop web 28 is arranged at the upper end of a side facing the stop cam 29 side surface 34 which extends at right angles to the side surface 34.
  • This stop bar 28 can be reworked for exact position adjustment in case of need, should In the course of the assembly of the guide grid 18 it turns out that the exact position can not yet be set.
  • the stop 25 can then be separated from the blade bearing ring 6 and be reworked in a precision device by removing a suitable portion of the stop web 28.
  • Fig. 3 an embodiment of the guide grid 18 according to the invention is shown.
  • all parts that are those of Fig. 2 provided with the same reference numerals, so that reference can be made in terms of training and function to the above description.
  • the stop 25 of the second embodiment is provided with an adjusting plate 32.
  • the adjusting plate 32 has a fixing plate 35 which can be fixed to the stopper body 26, such as by a Fixierclip 36.
  • Fixierclip 36 any other types of mounting options for the adjusting plate 32 on the stopper body 26 are conceivable.
  • the adjusting plate 32 is provided in this embodiment with a stop plate 33 which extends parallel to the side surface 34 of the projection 27 and to this one Fig. 3 apparent distance, so as to be able to define the exact stop position.
  • the stop position can be effected by the replacement of the adjusting plate 32, so that in this embodiment, an exact adjustment, in particular the minimum flow, in a simple and cost-effective manner is possible.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Description

Die Erfindung betrifft einen Turbolader gemäß dem Oberbegriff des Anspruches 1.The invention relates to a turbocharger according to the preamble of claim 1.

Ein derartiger Turbolader ist aus der EP 1 564 380 A1 bekannt. Zur Vermeidung einer Schwächung des Verstellringes schlägt diese Druckschrift einen Anschlag vor, der einteilig mit dem Verstellring verbunden ist.Such a turbocharger is from the EP 1 564 380 A1 known. To avoid weakening the adjusting ring this document proposes a stop which is integrally connected to the adjusting ring.

Durch die einteilige Ausbildung des Anschlages am Verstellring ist es jedoch bei dem bekannten Turbolader, wenn überhaupt, nur unter relativ hohem Aufwand möglich, den Vorsprung des Anschlages nach der Montage des Leitgitters nachzubearbeiten, wenn beispielsweise eine Korrektur der Endlagen des Leitgitters vorgenommen werden soll bzw. muss. Ferner begrenzt der Vorsprung des Anschlages des bekannten Turboladers die Endstellungen durch Anlage an Befestigungsringen der Verstellhebel an den Schaufeln, was eine genaue Einstellung der Endlagen ebenfalls erschwert, da die Befestigungsringe dieser Schaufelverstellhebel zum einem Fertigungstoleranzen unterliegen und zum anderen infolge der Positionierung (Teilung) Ungenauigkeiten entstehen.Due to the one-piece design of the stop on the adjusting ring, it is possible in the known turbocharger, if at all, only relatively expensive to rework the projection of the stop after mounting the guide grid, for example, if a correction of the end positions of the guide grid should be made or got to. Furthermore, the projection of the stop of the known turbocharger limits the end positions by contact with mounting rings of the adjusting lever on the blades, which also makes precise adjustment of the end positions difficult, since the mounting rings of these blade adjustment levers are subject to manufacturing tolerances and on the other hand, due to the positioning (division) inaccuracies arise.

Es ist daher Aufgabe der vorliegenden Erfindung, einen Turbolader der im Oberbegriff des Anspruches 1 angegebenen Art zu schaffen, der eine Vereinfachung der Montage des Leitgitters bzw. Leitapparates ermöglicht, wobei zumindest eine einfache und genaue Einstellung des Minimaldurchflusses mittels des Leitapparates allein möglich sein soll.It is therefore an object of the present invention to provide a turbocharger specified in the preamble of claim 1, which allows a simplification of the assembly of the guide grid or diffuser, at least a simple and accurate adjustment of the minimum flow through the diffuser should be possible alone.

Die Lösung dieser Aufgabe erfolgt durch die Merkmale des Anspruchs 1.The solution of this object is achieved by the features of claim 1.

Dadurch, dass der Anschlag, mit dem zumindest eine Einstellung des Minimaldurchflusses durch die von den Leitschaufeln gebildeten Düsenquerschnitte möglich ist, als ein separates Bauteil ausgebildet ist, das im Leitgitter fixierbar ist, ist es möglich, nach der Montage des Leitgitters diesen Anschlag auf einfache Art und Weise zur exakten Einstellung der geforderten Anschlagposition nachzubearbeiten, da er nicht einstückig mit dem Leitgitter verbunden ist. Ergibt sich die Notwendigkeit einer Nachjustierung einer der beiden Endstellungen des Leitgitters, kann somit entweder auf einfache Art und Weise ein für die gewünschte Endstellung passendes Anschlagteil ausgewählt und montiert werden oder das vorgesehene Anschlagteil durch Nachbearbeitung des Vorsprunges angepasst und dann im Leitgitter montiert werden. Somit ist es möglich, eine genaue Endlagenstellung gezielt vorzunehmen, was beim gattungsgemäßen Turbolader aufgrund der einstückigen Ausbildung des Anschlages problematisch ist.The fact that the stop, with which at least one setting of the minimum flow through the nozzle cross-sections formed by the vanes is possible, is formed as a separate component which is fixable in the guide grid, it is possible after mounting the guide grid this stop in a simple way and way to rework the exact setting of the required stop position, since it is not integrally connected to the guide grid. If the need for a readjustment of one of the two end positions of the guide grid, it can be either simply selected and mounted a suitable fitment for the desired end position or adapted the intended stop member by reworking the projection and then mounted in the guide grille. Thus, it is possible to make a precise end position targeted, which is problematic in the generic turbocharger due to the integral formation of the stop.

Ferner ergibt sich der Vorteil, dass der gesamte Leitapparat als Kartusche komplett vormontiert und der Minimaldurchfluss eingestellt werden kann bevor er dann in das Turbinengehäuse eingelegt wird.Furthermore, there is the advantage that the entire diffuser can be completely pre-assembled as a cartridge and the minimum flow can be adjusted before it is then inserted into the turbine housing.

Die Einstellung des Minimaldurchflusses erfolgt somit unabhängig von Turbinengehäuse und anderen Komponenten des Turboladers, wie z.B. dem Lagergehäuse. Auch hat die Stutzenstellung zwischen Lager- und Turbinengehäuse keinen Einfluß mehr auf die Minimaldurchflusseinstellung. Ebenfalls wirkt sich der Verschleiß des Verstellhebels und dessen Eingriff am Verstellring nicht auf die Minimaldurchflussmenge aus.The adjustment of the minimum flow is thus independent of turbine housing and other components of the turbocharger, such as e.g. the bearing housing. Also, the nozzle position between the bearing and turbine housing no longer has any influence on the minimum flow setting. Also, the wear of the adjusting lever and its engagement with the adjusting ring does not affect the minimum flow rate.

Weiterhin ist es denkbar, direkt beim Schweißen die Schaufelwellen mit den Schaufelhebeln in der für die Minimalflusseinstellung erforderlichen Postion zu verbinden und dadurch auf einen nachfolgenden Einstellprozess zu verzichten. Auf diese Weise wird das Risiko und die Möglichkeit einer Minimalflussveränderung ausgeschlossen.Furthermore, it is conceivable to connect the blade shafts to the blade levers in the position required for the minimum flow adjustment directly during welding and thereby to dispense with a subsequent adjustment process. This eliminates the risk and possibility of a minimal flow change.

Die Unteransprüche 2 und 3 haben vorteilhafte Weiterbildungen der Erfindung zum Inhalt.The dependent claims 2 and 3 have advantageous developments of the invention to the content.

In den Ansprüchen 4 bis 6 ist ein Leitgitter als jeweils selbstständig handelbares Objekte definiert.In the claims 4 to 6, a guide grid is defined as each independently tradable objects.

Weitere Einzelheiten, Vorteile und Merkmale der Erfindung ergeben sich aus nachfolgender Beschreibung eines Ausführungsbeispiels anhand der Zeichnung. Es zeigt:

Fig. 1
eine geschnittene perspektivische Darstellung des grundsätzlichen Aufbaues eines erfindungsgemäßen Turboladers;
Fig. 2
eine perspektivische Darstellung einer nicht zum Gegenstand der Erfindung gehörenden Ausführungsform eines Leitgitters;
Fig. 3
eine der Fig. 2 entsprechende perspektivische Darstellung einer Ausführungsform des erfindungsgemäßen Leitgitters.
Further details, advantages and features of the invention will become apparent from the following description of an embodiment with reference to the drawing. It shows:
Fig. 1
a sectional perspective view of the basic structure of a turbocharger according to the invention;
Fig. 2
a perspective view of a not belonging to the subject invention embodiment of a guide grid;
Fig. 3
one of the Fig. 2 corresponding perspective view of an embodiment of the guide grid according to the invention.

In Fig. 1 ist ein erfindungsgemäßer Turbolader 1 dargestellt, der ein Turbinengehäuse 2 und ein damit über ein Lagergehäuse 19 verbundenes Kompressorgehäuse 3 aufweist. Die Gehäuse 2, 3 und 19 sind entlang einer Rotationsachse R angeordnet. Das Turbinengehäuse 2 ist teilweise im Schnitt gezeigt, um die Anordnung eines Schaufellagerrings 6 als Teil eines radial äußeren Leitgitters 18 zu verdeutlichen, das eine Mehrzahl von über den Umfang verteilten Leitschaufeln 7 mit Schwenkachsen bzw. Schaufelwellen 8 aufweist. Hierdurch werden Düsenquerschnitte gebildet, die je nach der Lage der Leitschaufeln 7 größer oder kleiner sind und den in der Mitte an der Rotationsachse R gelagerten Turbinenrotor 4 mehr oder weniger mit dem über einen Zuführkanal 9 zugeführten und über einen Zentralstutzen 10 abgeführten Abgas eines Motors beaufschlagen, um über den Turbinenrotor 4 einen auf der selben Welle sitzenden Verdichterrotor 17 anzutreiben.In Fig. 1 an inventive turbocharger 1 is shown, which has a turbine housing 2 and a compressor housing 3 connected thereto via a bearing housing 19. The housings 2, 3 and 19 are arranged along a rotation axis R. The turbine housing 2 is shown partially in section to illustrate the arrangement of a vane ring 6 as part of a radially outer baffle 18 having a plurality of circumferentially spaced vanes 7 with pivot shafts 8. As a result, nozzle cross-sections are formed, which are larger or smaller depending on the position of the guide vanes 7 and the turbine rotor 4 mounted in the middle on the axis of rotation R more or less with the supplied via a feed channel 9 and discharged via a central port 10 exhaust gas of an engine, to drive over the turbine rotor 4 a seated on the same shaft compressor rotor 17.

Um die Bewegung bzw. die Lage der Leitschaufeln 7 zu steuern, ist eine Betätigungseinrichtung 11 vorgesehen. Diese kann an sich beliebig ausgebildet sein, jedoch weist eine bevorzugte Ausführungsform ein Steuergehäuse 12 auf, das die Steuerbewegung eines an ihr befestigten Stößelgliedes 14 steuert, um dessen Bewegung auf einen hinter dem Schaufellagerring 6 gelegenen Verstellring 5 in eine leichte Drehbewegung desselben umzusetzen. Zwischen dem Schaufellagerring 6 und einem ringförmigen Teil 15 des Turbinengehäuses 2 wird ein Freiraum 13 für die Leitschaufeln 7 gebildet. Um diesen Freiraum 13 sichern zu können, weist der Schaufellagerring 6 einstückig geformte Abstandshalter 16 auf. Im Beispielsfalle sind drei Abstandshalter 16 in einem Winkelabstand von jeweils 120° am Umfang des Schaufellagerrings 6 angeordnet. Vom Prinzip her ist es jedoch möglich, mehr oder weniger derartige Abstandshalter 16 vorzusehen.In order to control the movement or the position of the guide vanes 7, an actuating device 11 is provided. This can be designed to be arbitrary, but a preferred embodiment, a control housing 12, which controls the control movement of a ram member 14 attached to her to implement the movement thereof to a located behind the blade bearing ring 6 adjusting 5 in a slight rotational movement of the same. Between the vane ring 6 and an annular part 15 of the turbine housing 2, a clearance 13 for the vanes 7 is formed. In order to be able to secure this clearance 13, the blade bearing ring 6 has integrally formed spacers 16. In the example case, three spacers 16 are arranged at an angular distance of 120 ° in each case on the circumference of the blade bearing ring 6. In principle, it is However, it is possible to provide more or less such spacers 16.

In Fig. 2 ist eine perspektivische Teilansicht des Leitgitters 18 in vergrößertem Maßstab dargestellt.In Fig. 2 is a partial perspective view of the guide grid 18 shown on an enlarged scale.

Repräsentativ für sämtliche Schaufelhebel dieses Leitgitters 18 ist ein Schaufelhebel 20 dargestellt, der an einem Ende einen Befestigungsring 21 mit einer Ausnehmung 22 aufweist, in der ein Ende der Schaufelwelle 8 fixiert ist.Representative of all blade lever this Leitgitters 18 a blade lever 20 is shown having at one end a mounting ring 21 with a recess 22 in which one end of the blade shaft 8 is fixed.

Ein Hebelkopf 23 des Schaufelhebels 20 ist in einer Eingriffsausnehmung 24 des Verstellrings 5 angeordnet und steht somit mit dem Verstellring 5 in Eingriff.A lever head 23 of the blade lever 20 is disposed in an engagement recess 24 of the adjusting ring 5 and thus is engaged with the adjusting ring 5 in engagement.

Ferner verdeutlicht Fig. 2 die Anordnung eines Anschlages 25 in Form eines separaten Bauteils. Der Anschlag 25 weist einen Anschlagkörper 26 auf, der bei der dargestellten Ausführungsform am Schaufellagerring 6 fixiert worden ist. Der Anschlagkörper 6 weist einen radial nach außen ragenden Vorsprung 27 auf, der in eine Nut 31 des Verstellringes 5 eingreift. Die Nut 31 des Verstellringes 5 wird von zwei Anschlagnocken 29 und 30 begrenzt. Die Anschlagnocken 29 und 30 weisen nach innen in die Nut 31 weisende Anschlaggegenflächen auf, die mit der entsprechenden benachbarten Fläche des Vorsprunges 27 in Eingriff treten können. Im Fall der Darstellung der Fig. 2 ist eine Anschlagstellung am Anschlagnocken 29 zur Einstellung des Minimaldurchflusses durch die Düsenquerschnitte des Leitgitters 18 gezeigt.Further clarified Fig. 2 the arrangement of a stop 25 in the form of a separate component. The stop 25 has a stop body 26, which has been fixed in the illustrated embodiment on the blade bearing ring 6. The stopper body 6 has a radially outwardly projecting projection 27, which engages in a groove 31 of the adjusting ring 5. The groove 31 of the adjusting ring 5 is bounded by two stop cams 29 and 30. The stop cams 29 and 30 have inwardly into the groove 31 facing abutment abutment surfaces which can engage with the corresponding adjacent surface of the projection 27. In the case of the representation of Fig. 2 a stop position on the stop cam 29 for adjusting the minimum flow through the nozzle cross sections of the guide grid 18 is shown.

Wie Fig. 2 ferner verdeutlicht, ist am oberen Ende einer auf den Anschlagnocken 29 weisenden Seitenfläche 34 ein Anschlagsteg 28 angeordnet, der sich im rechten Winkel zur Seitenfläche 34 erstreckt. Dieser Anschlagsteg 28 kann zur genauen Lageeinstellung im Bedarfsfalle nachbearbeitet werden, sollte sich im Zuge der Montage des Leitgitters 18 herausstellen, dass die genaue Position noch nicht eingestellt werden kann. Zu diesem Zwecke kann dann der Anschlag 25 vom Schaufellagerring 6 getrennt werden und in einem Präzisionsgerät durch Abtragen eines geeigneten Anteils des Anschlagsteges 28 nachbearbeitet werden.As Fig. 2 also clarified, a stop web 28 is arranged at the upper end of a side facing the stop cam 29 side surface 34 which extends at right angles to the side surface 34. This stop bar 28 can be reworked for exact position adjustment in case of need, should In the course of the assembly of the guide grid 18 it turns out that the exact position can not yet be set. For this purpose, the stop 25 can then be separated from the blade bearing ring 6 and be reworked in a precision device by removing a suitable portion of the stop web 28.

In Fig. 3 ist eine Ausführungsform des erfindungsgemäßen Leitgitters 18 dargestellt. Bei dieser Ausführungsform sind sämtliche Teile, die denjenigen der Fig. 2 entsprechen, mit denselben Bezugsziffern versehen, so dass hinsichtlich Ausbildung und Funktion auf die voranstehende Beschreibung verwiesen werden kann.In Fig. 3 an embodiment of the guide grid 18 according to the invention is shown. In this embodiment, all parts that are those of Fig. 2 provided with the same reference numerals, so that reference can be made in terms of training and function to the above description.

Im Gegensatz zur Anbringung eines Anschlagsteges 28 ist der Anschlag 25 der zweiten Ausführungsform mit einem Einstellblech 32 versehen. Das Einstellblech 32 weist eine Fixierplatte 35 auf, die am Anschlagkörper 26 festgelegt werden kann, wie beispielsweise durch einen Fixierclip 36. Natürlich sind auch jedwede andere Arten von Befestigungsmöglichkeiten für das Einstellblech 32 am Anschlagkörper 26 denkbar.In contrast to the attachment of a stop web 28, the stop 25 of the second embodiment is provided with an adjusting plate 32. The adjusting plate 32 has a fixing plate 35 which can be fixed to the stopper body 26, such as by a Fixierclip 36. Of course, any other types of mounting options for the adjusting plate 32 on the stopper body 26 are conceivable.

Anstelle des Anschlagsteges 28 ist bei dieser Ausführungsform das Einstellblech 32 mit einer Anschlagplatte 33 versehen, die parallel zur Seitenfläche 34 des Vorsprunges 27 verläuft und zu dieser einen aus Fig. 3 ersichtlichen Abstand einnimmt, um so die genaue Anschlagposition definieren zu können.Instead of the stop web 28, the adjusting plate 32 is provided in this embodiment with a stop plate 33 which extends parallel to the side surface 34 of the projection 27 and to this one Fig. 3 apparent distance, so as to be able to define the exact stop position.

Durch diese Ausführungsform kann mithin die Anschlagposition durch das Austauschen des Einstellbleches 32 bewirkt werden, so dass auch bei dieser Ausführungsform eine exakte Einstellung, insbesondere des Minimaldurchflusses, auf einfache und kostengünstige Art und Weise möglich ist.By this embodiment, therefore, the stop position can be effected by the replacement of the adjusting plate 32, so that in this embodiment, an exact adjustment, in particular the minimum flow, in a simple and cost-effective manner is possible.

Zur Ergänzung der Offenbarung wird explizit auf die zeichnerische Darstellung der Erfindung in den Fig. 1 bis 3 verwiesen.To supplement the disclosure is explicitly to the drawings of the invention in the Fig. 1 to 3 directed.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Turboladerturbocharger
22
Turbinengehäuseturbine housing
33
Kompressorgehäusecompressor housing
44
Turbinenrotorturbine rotor
55
Verstellringadjusting
66
SchaufellagerringNozzle ring
77
Leitschaufelnvanes
88th
Schaufelwellepaddle shaft
99
Zuführkanalfeed
1010
AxialstutzenAxialstutzen
1111
Betätigungseinrichtungactuator
1212
Steuergehäusecontrol housing
1313
Freiraum für Leitschaufeln 7Free space for vanes 7
1414
Stößelgliedplunger member
1515
Ringförmiger Teil des Turbinengehäuses 2Annular part of the turbine housing 2
1616
Abstandshalter/DistanznockenSpacer / spacer cams
1717
Kompressorrotorcompressor rotor
1818
Leitgitter/LeitapparatGuide baffle / diffuser
1919
Lagergehäusebearing housing
2020
Schaufelhebelvane levers
2121
Befestigungsringfixing ring
2222
Ausnehmungrecess
2323
Hebelkopflever head
2424
Eingriffsausnehmungenengagement recesses
2525
Anschlagattack
2626
Anschlagkörperstop body
2727
Vorsprunghead Start
2828
Anschlagstegstop web
29, 3029, 30
Anschlagnockenstop cams
3131
Nutgroove
3232
Einstellblechadjusting plate
3333
Anschlagplattestop plate
3434
Seitenflächenfaces
3535
Fixierplattefixing
3636
Fixierclipfixing clip

Claims (6)

  1. Turbocharger (1) with variable turbine geometry (VTG)
    - with a turbine housing (2) with a feed passage(9) for exhaust gases;
    - with a turbine rotor (4), which is rotatably mounted in the turbine housing (2); and
    - with a guide vane cascade (18),
    • which encloses the turbine rotor (4) radially on the outside,
    • which has a vane bearing ring (6),
    • which has a multiplicity of guide vanes (7), which have in each case a vane shaft (8) which is mounted in the vane bearing ring (6),
    • which has an adjusting ring (5) which is in functional communication with the guide vanes (7) via associated vane levers (20) which are fastened by one of their ends on the vane shafts (8), wherein each vane lever (20) on the other end has a lever head (23) which can be brought into engagement with an associated engagement recess (24) of the adjusting ring (5), and
    • which has a stop (25) at least for adjustment of the minimum throughflow through the nozzle cross sections which are formed by the guide vanes (7),
    • the stop (25) being formed as a separate component which can be fixed in the guide vane cascade (18),
    characterized in that
    • the stop (25) can be fixed on the vane bearing ring (6) and has a projection (27) which engages in a slot (31) of the adjusting ring (5), and
    • the stop (25) is provided with an adjustment plate (32) having a stop plate (33) which extends parallel to a side face (34) of the projection (27) and is spaced apart from the side face (34).
  2. Turbocharger according to Claim 1, characterized in that the adjustment plate (32) is formed as an exchangeable component which is variable in its dimensions and can be fixed on the stop (25).
  3. Turbocharger according to Claim 1 or 2, characterized in that the minimum throughflow is adjusted by means of the positioning of vane shaft (8) to vane lever (20).
  4. Guide vane cascade (18) for a turbocharger (1) with variable turbine geometry (VTG), which encloses a turbine rotor (4) of the turbocharger (1) radially on the outside and has the following parts:
    • a vane bearing ring (6),
    • a multiplicity of guide vanes (7), which have in each case a vane shaft (8) which is mounted in the vane bearing ring (6),
    • an adjusting ring (5) which is in functional communication with the guide vanes (7) via associated vane levers (20) which are fastened by one of their ends on the vane shafts (8), wherein each vane lever (20) on the other end has a lever head (23) which can be brought into engagement with an associated engagement recess (24) of the adjusting ring (5), and
    • a stop (25) at least for adjustment of the minimum throughflow through the nozzle cross sections which are formed by the guide vanes (7),
    • the stop (25) being formed as a separate component which can be fixed in the guide vane cascade (18),
    characterized in that
    • the stop (25) can be fixed on the vane bearing ring (6) and has a projection (27) which engages in a slot (31) of the adjusting ring (5), and
    • the stop (25) is provided with an adjustment plate (32) having a stop plate (33) which extends parallel to a side face (34) of the projection (27) and is spaced apart from the side face (34).
  5. Guide vane cascade according to Claim 4, characterized in that the adjustment plate (32) is formed as an exchangeable component which is variable in its dimensions and can be fixed on the stop (25).
  6. Guide vane cascade according to Claim 4 or 5, characterized in that the minimum throughflow is adjusted by means of the positioning of vane shaft (8) to vane lever (20).
EP16165283.9A 2006-05-19 2007-05-16 Turbocharger Expired - Fee Related EP3073064B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006023923 2006-05-19
EP07725312.8A EP2018480B1 (en) 2006-05-19 2007-05-16 Turbocharger

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP07725312.8A Division EP2018480B1 (en) 2006-05-19 2007-05-16 Turbocharger
EP07725312.8A Division-Into EP2018480B1 (en) 2006-05-19 2007-05-16 Turbocharger

Publications (2)

Publication Number Publication Date
EP3073064A1 EP3073064A1 (en) 2016-09-28
EP3073064B1 true EP3073064B1 (en) 2017-09-20

Family

ID=38353448

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Application Number Title Priority Date Filing Date
EP07725312.8A Expired - Fee Related EP2018480B1 (en) 2006-05-19 2007-05-16 Turbocharger
EP16165283.9A Expired - Fee Related EP3073064B1 (en) 2006-05-19 2007-05-16 Turbocharger

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07725312.8A Expired - Fee Related EP2018480B1 (en) 2006-05-19 2007-05-16 Turbocharger

Country Status (7)

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US (1) US8328520B2 (en)
EP (2) EP2018480B1 (en)
JP (1) JP2009537727A (en)
KR (1) KR101400878B1 (en)
CN (1) CN101438062A (en)
BR (1) BRPI0709404B1 (en)
WO (1) WO2007134787A1 (en)

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Also Published As

Publication number Publication date
BRPI0709404A2 (en) 2011-07-12
BRPI0709404B1 (en) 2019-08-06
EP2018480B1 (en) 2016-06-15
US20100014961A1 (en) 2010-01-21
CN101438062A (en) 2009-05-20
EP3073064A1 (en) 2016-09-28
EP2018480A1 (en) 2009-01-28
US8328520B2 (en) 2012-12-11
JP2009537727A (en) 2009-10-29
WO2007134787A1 (en) 2007-11-29
KR101400878B1 (en) 2014-05-29
KR20090010199A (en) 2009-01-29

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