EP2167793B1 - Exhaust gas turbocharger for an internal combustion engine - Google Patents

Exhaust gas turbocharger for an internal combustion engine Download PDF

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Publication number
EP2167793B1
EP2167793B1 EP08773444A EP08773444A EP2167793B1 EP 2167793 B1 EP2167793 B1 EP 2167793B1 EP 08773444 A EP08773444 A EP 08773444A EP 08773444 A EP08773444 A EP 08773444A EP 2167793 B1 EP2167793 B1 EP 2167793B1
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EP
European Patent Office
Prior art keywords
exhaust gas
spacer element
gas turbocharger
turbocharger according
internal combustion
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.)
Not-in-force
Application number
EP08773444A
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German (de)
French (fr)
Other versions
EP2167793A2 (en
Inventor
Jan Ehrhard
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IHI Charging Systems International GmbH
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IHI Charging Systems International GmbH
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Publication date
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Publication of EP2167793A2 publication Critical patent/EP2167793A2/en
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Publication of EP2167793B1 publication Critical patent/EP2167793B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to an exhaust gas turbocharger for an internal combustion engine according to the preamble of claim 1.
  • a diffuser emerges in an exhaust gas guide section of an exhaust gas turbocharger for an internal combustion engine.
  • the distributor has a number of adjustable guide vanes which are positioned in an inflow passage in the exhaust guide section, upstream of a wheel chamber in the exhaust guide section, in which the turbine wheel is rotatably received.
  • the distributor has a bearing ring and a contour sleeve, wherein the bearing ring and the contour sleeve are fixed by means of spacer elements such that a certain, first distance between the bearing ring and the contour sleeve is present. Due to the positioning of the spacer elements in the inflow passage of the exhaust gas flow is opposite to a flow resistance, whereby efficiency losses of the exhaust gas turbocharger are brought about.
  • the published patent EP 1 394 364 A1 also discloses a nozzle for an exhaust gas turbocharger, having an exhaust gas guide portion, which has a spiral channel with a spiral tongue, wherein the nozzle assigned to spacer elements.
  • These spacers are aerodynamically designed such that in the inflow of the Abgasanströmung a contrary to the usual known in the prior art spacer elements reduced flow resistance due to the positioning of the spacer elements is realized. Nevertheless, efficiency losses are still due to the positioning of the spacer elements.
  • the invention is based on the object of bringing about a further reduction of efficiency losses, which occur due to the spacer elements positioned in the inflow channel, with the aid of simple measures.
  • the at least one spacer element has a lateral surface whose second distance from a longitudinal axis of the spacer element over a length of the spacer element and / or over a cross-sectional area of the spacer element is variable, wherein the spacer element is positioned in a region of a second wake of the spiral tongue.
  • the outer surface can thereby be designed such that a flow resistance formed on the basis of the spacer element can be reduced, and to increase the efficiency, the spacer element is positioned such that it is arranged in a region of a second caster.
  • a spiral tongue is formed in the exhaust gas guide section. In the region of the spiral tongue, the second wake of the exhaust gas flow is formed when flowing through the spiral channel.
  • the efficiency losses occurring due to the second caster are not or only slightly affected by the positioning of the spacer element in this area.
  • the increase in efficiency is due to the fact that the efficiency losses occurring through the spacer element are compensated by the positioning in the region of the second wake.
  • the cross-sectional area of the spacer element is drop-shaped, similar to a vane cross-sectional area, so that a particularly small flow resistance coefficient can be realized.
  • an embodiment of the spacer element has proven in which a chord length of the spacer element has at least twice the size of a largest profile thickness of the spacer element.
  • the spacer element is to be positioned such that a first wake initiated by the spacer element can be flowed through a channel formed by a first guide vane and a second guide vane adjacent to the first guide vane, without interaction with a boundary layer of the second vane.
  • a flow section which is formed downstream of a flow-around element, can be referred to as a wake.
  • the wake is a flow section formed on the blade trailing edge. This caster leads here to influence the flow in the channel formed between two vanes.
  • the distance between the bearing ring and the contour sleeve is secured over a circumference of the bearing ring.
  • the in Fig. 1 shown istiereströmbare exhaust gas guide portion 2 of an exhaust gas turbocharger 1 is provided in an exhaust tract of an internal combustion engine, not shown, in which it is a gasoline engine or a diesel engine, provided.
  • the exhaust gas turbocharger 1 further includes a non-illustrated throughflow fresh air guide portion and a bearing portion, not shown, which is arranged in a non-illustrated intake tract of the internal combustion engine.
  • the exhaust gas turbocharger 1 has a running gear 3, which is a not-shown compressor wheel for sucking and compressing combustion air, a turbine wheel 4 for expansion of exhaust gas and a compressor wheel with the turbine wheel 4 rotatably connecting shaft 5 with a Rotary axis 6 includes.
  • the shaft 5 is rotatably mounted in the bearing portion of the exhaust gas turbocharger 1, which is positioned between the air guide portion and the exhaust gas guide portion 2.
  • an inlet channel 7 is formed in the exhaust gas guide section 2.
  • the inlet channel 7 is used to condition the exhaust gas, which puts the turbine wheel 4 in a rotating motion during operation of the internal combustion engine.
  • the compressor wheel With the help of the shaft 5, the compressor wheel is also set in rotation, so that it sucks in combustion air and compressed.
  • a spiral channel 8 is arranged in the exhaust gas guide section 2, which serves to provide a rotationally symmetrical flow. Furthermore, the spiral channel 8 is formed as a connecting channel between the inlet channel 7 and an inflow channel 9, which is positioned downstream of the spiral channel 8. At the entry into the spiral channel 8, a spiral tongue 20 is configured in the exhaust gas guide section 2. Downstream of the inflow channel 9, a wheel chamber 10 is arranged in the exhaust gas guide section 2, in which the turbine wheel 4 is rotatably received. Downstream of the wheel chamber 10, the exhaust gas guide section 2 has an outlet channel 11 for the escape of the exhaust gas from the exhaust gas guide section 2.
  • a nozzle 12 is shown according to the prior art.
  • the nozzle 12, the turbine wheel 4 is formed annularly comprehensive and has a bearing ring 13 for receiving guide vanes 14, which are provided for flow conditioning.
  • the guide vanes 14 are rotatably mounted on the bearing ring 13.
  • the bearing ring 13 is positioned in the exhaust gas guide section 2 so that the guide vanes 14 are arranged in the inflow channel 9.
  • the bearing ring 13 is positioned opposite a contour sleeve 15, which is designed for flow conditioning and simplified assembly of the nozzle 12.
  • spacer elements 16 are positioned in the inflow channel 9.
  • spacers 16 according to the prior art are cylindrical.
  • Fig. 3 is shown in a plan view of the nozzle 12 of an exhaust gas turbocharger 1.
  • the spacer elements 16 have a longitudinal axis 17, a lateral surface 18, a length L and a cross-sectional area 19 (see FIG. Fig. 5 ).
  • the spacer elements 16 of the exhaust gas turbocharger 1 according to the invention gem.
  • Fig. 4 are designed aerodynamically, such that the lateral surface 18 has a second distance MA from the longitudinal axis 17, which is variable over the cross-sectional area 19.
  • a preferred cross-sectional area 19 of the spacer element 16 is realized, which has a drop-shaped shape similar to a guide blade cross-sectional area.
  • the cross-sectional area 19 is designed to be consistent along the longitudinal axis 17.
  • the lateral surface 18 could additionally or exclusively over the length L have a variable second distance MA, so that
  • the spacer element 16 has a symmetrical or asymmetrical, waisted or a bulbous contour.
  • a total of three spacer elements 16 are arranged at a third distance RD from the axis of rotation 6, which is greater than a fourth distance RL of the guide vanes 14 from the axis of rotation 6.
  • the spacer elements 16 are preferably formed sleeve-shaped. In a further embodiment, at least four spacer elements 16 are provided.
  • a chord length SL of the spacer element 16 in the exemplary embodiment has approximately four times the size of a largest profile thickness PD of the spacer element 16. To achieve an improvement in efficiency, the chord length SL should be at least twice the size of the profile thickness PD.
  • the spacers 16 are placed relative to the vanes 14 in a streamlined positioning.
  • the positioning is selected such that a first wake 21 initiated by the spacer element 16 can flow through a channel 22 formed by two guide vanes 14 arranged next to one another, ideally in the middle thereof.
  • Fig. 4 is positioned in a further embodiment for further increase in efficiency of one of the three spacer elements 16 in the region of a second wake 23, which is formed in the region of the spiral tongue 20.
  • the spacer elements 16 are mounted on the bearing ring 13. In a further embodiment, the spacer elements 16 are additionally mounted on the contour sleeve 15. In a further embodiment, the spacer elements 16 are mounted only on the contour sleeve 15. In addition to the function to bring about a constant distance between the bearing ring 13 and the contour sleeve 15, the spacer element 16 can also be assigned a carrier function, in the sense that the contour sleeve 15 is completely supported and positioned by the spacer element 16 or fixed radially and axially.
  • the spacer elements 16 are rotatably and / or translationally mounted.
  • the bearing ring 13 has for translational movement of the spacer element 16 has a groove-shaped, ideally arcuate opening in which the spacer element 16 is slidably mounted.
  • an adjusting device for adjusting the spacer element 16 is provided, which has a mechanical structure. The adjustment is dependent on operating variables of the internal combustion engine, with the aid of a control and control unit.

Abstract

In an exhaust gas turbocharger for an internal combustion engine, comprising a turbine rotor, which is rotatably housed in a rotor chamber through which exhaust gas coming from the internal combustion engine is conducted and wherein the flow around the turbine rotor is conditioned by means of a guide apparatus comprising a support ring with rotatably mounted guide vanes. For fixing a first distance (A) between the support ring and the contour sleeve, at least one spacer element with a longitudinal axis, an outer surface and a cross-sectional area is provided so as to have a streamlined shape forming in the exhaust gas flow only a relatively narrow wake line and the spacer element is so arranged that the wake line formed thereby extends essentially through a flow space between two adjacent guide vanes without disturbing the exhaust gas flow around these guide vanes.

Description

Die Erfindung betrifft einen Abgasturbolader für eine Brennkraftmaschine gemäß dem Oberbegriff des Anspruchs 1.The invention relates to an exhaust gas turbocharger for an internal combustion engine according to the preamble of claim 1.

Aus der Offenlegungsschrift DE 103 25 985 A1 geht ein Leitapparat in einem Abgasführungsabschnitt eines Abgasturboladers für eine Brennkraftmaschine hervor. Mit Hilfe des Leitapparates ist eine Anströmung des Turbinenrades von aus der Brennkraftmaschine austretender Abgase konditionierbar. Der Leitapparat weist hierzu eine Anzahl verstellbarer Leitschaufeln auf, welche in einem Anströmkanal im Abgasführungsabschnitt, stromauf einer Radkammer im Abgasführungsabschnitt, in welcher das Turbinenrad drehbar aufgenommen ist, positioniert sind. Der Leitapparat weist einen Lagerring und eine Konturhülse auf, wobei der Lagerring und die Konturhülse mit Hilfe von Distanzelementen derart fixiert sind, dass ein bestimmter, erster Abstand zwischen dem Lagerring und der Konturhülse vorliegt. Aufgrund der Positionierung der Distanzelemente im Anströmkanal ist der Abgasanströmung ein Strömungswiderstand entgegengesetzt, wodurch Wirkungsgradverluste des Abgasturboladers herbeigeführt werden.From the publication DE 103 25 985 A1 a diffuser emerges in an exhaust gas guide section of an exhaust gas turbocharger for an internal combustion engine. With the help of the diffuser, an oncoming flow of the turbine wheel can be conditioned by exiting from the internal combustion engine exhaust gases. For this purpose, the distributor has a number of adjustable guide vanes which are positioned in an inflow passage in the exhaust guide section, upstream of a wheel chamber in the exhaust guide section, in which the turbine wheel is rotatably received. The distributor has a bearing ring and a contour sleeve, wherein the bearing ring and the contour sleeve are fixed by means of spacer elements such that a certain, first distance between the bearing ring and the contour sleeve is present. Due to the positioning of the spacer elements in the inflow passage of the exhaust gas flow is opposite to a flow resistance, whereby efficiency losses of the exhaust gas turbocharger are brought about.

Der Offenlegungsschrift EP 1 394 364 A1 offenbart ebenfalls einen Leitapparat für einen Abgasturbolader, mit einem Abgasführungsabschnitt, welcher einen Spiralkanal mit einer Spiralzunge aufweist, wobei dem Leitapparat Distanzelemente zugeordnet sind. Diese Distanzelemente sind aerodynamisch derart ausgebildet, so dass im Anströmkanal der Abgasanströmung ein im Gegensatz zu den üblichen im Stand der Technik bekannten Distanzelementen verringerter Strömungswiderstand aufgrund der Positionierung der Distanzelemente realisiert ist. Dennoch liegen aufgrund der Positionierung der Distanzelemente weiterhin Wirkungsgradverluste vor. The published patent EP 1 394 364 A1 also discloses a nozzle for an exhaust gas turbocharger, having an exhaust gas guide portion, which has a spiral channel with a spiral tongue, wherein the nozzle assigned to spacer elements. These spacers are aerodynamically designed such that in the inflow of the Abgasanströmung a contrary to the usual known in the prior art spacer elements reduced flow resistance due to the positioning of the spacer elements is realized. Nevertheless, efficiency losses are still due to the positioning of the spacer elements.

Der Erfindung liegt die Aufgabe zu Grunde, eine weitere Reduzierung von Wirkungsgradverlusten, welche aufgrund der im Anströmkanal positionierten Distanzelemente auftreten, mit Hilfe einfacher Maßnahmen herbeizuführen.The invention is based on the object of bringing about a further reduction of efficiency losses, which occur due to the spacer elements positioned in the inflow channel, with the aid of simple measures.

Erfindungsgemäß weist das mindestens eine Distanzelement eine Mantelfläche auf, deren zweiter Abstand von einer Längsachse des Distanzelementes über eine Länge des Distanzelementes und/oder über eine Querschnittsfläche des Distanzelementes veränderlich ist, wobei das Distanzelement in einem Bereich eines zweiten Nachlaufs der Spiralzunge positioniert ist. Vorteilhafterweise ist dadurch die Mantelfläche so gestaltbar, dass ein aufgrund des Distanzelementes ausgebildeter Strömungswiderstand reduzierbar ist und zur Steigerung das Wirkungsgrades ist das Distanzelement so positioniert, dass es in einem Bereich eines zweiten Nachlaufs angeordnet ist. Am Eintritt in den Spiralkanal ist im Abgasführungsabschnitt eine Spiralzunge ausgebildet. Im Bereich der Spiralzunge ist bei Durchströmung des Spiralkanals der zweite Nachlauf der Abgasströmung ausgebildet. Die aufgrund des zweiten Nachlaufs auftretenden Wirkungsgradverluste werden nicht oder nur unwesentlich durch die Positionierung des Distanzelementes in diesem Bereich beeinträchtigt. Die Wirkungsgradsteigerung ist dadurch bedingt, dass die durch das Distanzelement auftretenden Wirkungsgradverluste durch die Positionierung im Bereich des zweiten Nachlaufs kompensiert werden.According to the invention, the at least one spacer element has a lateral surface whose second distance from a longitudinal axis of the spacer element over a length of the spacer element and / or over a cross-sectional area of the spacer element is variable, wherein the spacer element is positioned in a region of a second wake of the spiral tongue. Advantageously, the outer surface can thereby be designed such that a flow resistance formed on the basis of the spacer element can be reduced, and to increase the efficiency, the spacer element is positioned such that it is arranged in a region of a second caster. At entry into the spiral channel, a spiral tongue is formed in the exhaust gas guide section. In the region of the spiral tongue, the second wake of the exhaust gas flow is formed when flowing through the spiral channel. The efficiency losses occurring due to the second caster are not or only slightly affected by the positioning of the spacer element in this area. The increase in efficiency is due to the fact that the efficiency losses occurring through the spacer element are compensated by the positioning in the region of the second wake.

In einer weiteren Ausgestaltung ist die Querschnittsfläche des Distanzelementes tropfenförmig ausgebildet, ähnlich einer Leitschaufelquerschnittsfläche, sodass ein besonders kleiner Strömungswiderstandsbeiwert realisierbar ist.In a further embodiment, the cross-sectional area of the spacer element is drop-shaped, similar to a vane cross-sectional area, so that a particularly small flow resistance coefficient can be realized.

Als insbesondere vorteilhaft hat sich eine Ausgestaltung des Distanzelementes erwiesen, bei der eine Sehnenlänge des Distanzelementes mindestens die zweifache Größe einer größten Profildicke des Distanzelements aufweist.As particularly advantageous, an embodiment of the spacer element has proven in which a chord length of the spacer element has at least twice the size of a largest profile thickness of the spacer element.

Durch eine hülsenförmige Ausbildung des Distanzelementes sind Material und Gewicht vorteilhafterweise reduzierbar.By a sleeve-shaped design of the spacer element material and weight are advantageously reduced.

Mit Hilfe einer drehbaren und/oder translatorisch bewegbaren Lagerung des Distanzelementes ist ein kleinstmöglicher Strömungswiderstand in jedem Betriebspunkt des Abgasturboladers einzustellen. Damit ist in jedem Betriebspunkt des Abgasturboladers ein bestmöglicher Wirkungsgrad erzielbar.With the aid of a rotatable and / or translationally movable mounting of the spacer element is a smallest possible flow resistance in each operating point of the exhaust gas turbocharger set. Thus, the best possible efficiency can be achieved at each operating point of the exhaust gas turbocharger.

Zur weiteren Anhebung des Wirkungsgrades ist das Distanzelement so zu positionieren, dass ein vom Distanzelement initiierter erster Nachlauf durch einen von einer ersten Leitschaufel und einer neben der ersten Leitschaufel angeordneten zweiten Leitschaufel gebildeten Kanal strömbar ist, ohne eine Interaktion mit einer Grenzschicht der zweiten Leitschaufel. Als Nachlauf ist prinzipiell ein Strömungsabschnitt zu bezeichnen, welcher stromab eines umströmten Elementes ausgebildet ist. Bei schaufelförmigen Elementen, deren Schaufelspitzen mit einer Schaufelhinterkante in Richtung der Strömung angeordnet sind, ist der Nachlauf ein an der Schaufelhinterkante ausgebildeter Strömungsabschnitt. Dieser Nachlauf führt hier zur Beeinflussung der Strömung in dem zwischen zwei Leitschaufeln ausgebildeten Kanal. Beim Auftreffen des Nachlaufs auf die Grenzschicht einer Leitschaufel kommt es zu einer Aufdickung oder zu einem Abriss der Grenzschicht, wodurch ein Wirkungsgradverlust herbeigeführt wird. Mit Hilfe der geeigneten Positionierung des Distanzelementes kann dieses Abreißen vermieden werden, so dass eine Wirkungsgradsteigerung herbeiführbar ist.To further increase the efficiency, the spacer element is to be positioned such that a first wake initiated by the spacer element can be flowed through a channel formed by a first guide vane and a second guide vane adjacent to the first guide vane, without interaction with a boundary layer of the second vane. In principle, a flow section, which is formed downstream of a flow-around element, can be referred to as a wake. In the case of blade-shaped elements whose blade tips are arranged with a blade trailing edge in the direction of the flow, the wake is a flow section formed on the blade trailing edge. This caster leads here to influence the flow in the channel formed between two vanes. When hitting the caster On the boundary layer of a vane, there is a thickening or a demolition of the boundary layer, whereby a loss of efficiency is brought about. With the help of the appropriate positioning of the spacer element this tearing can be avoided, so that an increase in efficiency can be brought about.

Mit Hilfe von mindestens drei Distanzelementen, welche zwischen dem Lagerring und der Konturhülse angeordnet sind, ist der Abstand zwischen dem Lagerring und der Konturhülse über einen Umfang des Lagerrings gesichert.With the help of at least three spacer elements which are arranged between the bearing ring and the contour sleeve, the distance between the bearing ring and the contour sleeve is secured over a circumference of the bearing ring.

Weitere Vorteile und zweckmäßige Ausführungen sind den weiteren Ansprüchen, der Figurenbeschreibung und den Zeichnungen zu entnehmen. Es zeigen:

Fig. 1
In einem Schnitt ein Abgasführungsabschnitt eines Abgasturboladers mit einem Leitapparat gemäß dem Stand der Technik,
Fig. 2
in einer Draufsicht den Leitapparat gemäß Fig. 1,
Fig. 3
in einer Draufsicht den Leitapparat eines Abgasturboladers, mit Distanzelementen mit einer bevorzugten Mantelfläche und in einer ersten Positionierung,
Fig. 4
in einer Draufsicht den Leitapparat des erfindungsgemäßen Abgasturboladers , wobei die Distanzelemente in einer zweiten, bevorzugten Position angeordnet sind und
Fig. 5
in einer perspektivischen Darstellung ein Distanzelement des erfindungsgemäßen Abgasturboladers.
Further advantages and expedient embodiments can be taken from the further claims, the description of the figures and the drawings. Show it:
Fig. 1
In a section, an exhaust gas guide section of an exhaust gas turbocharger with a guide device according to the prior art,
Fig. 2
in a plan view of the distributor according to Fig. 1 .
Fig. 3
in a plan view of the distributor of an exhaust gas turbocharger, with spacer elements with a preferred lateral surface and in a first positioning,
Fig. 4
in a plan view of the nozzle of the exhaust gas turbocharger according to the invention, wherein the spacer elements are arranged in a second, preferred position and
Fig. 5
in a perspective view of a spacer element of the exhaust gas turbocharger according to the invention.

Der in Fig. 1 dargestellte durchströmbare Abgasführungsabschnitt 2 eines Abgasturboladers 1 ist in einem Abgastrakt einer nicht näher dargestellten Brennkraftmaschine, bei der es sich um einen Ottomotor oder einen Dieselmotor handelt, vorgesehen. Der Abgasturbolader 1 weist weiterhin einen nicht näher dargestellten durchströmbaren Frischluftführungsabschnitt und einen nicht näher dargestellten Lagerabschnitt auf, welcher in einem nicht näher dargestellten Ansaugtrakt der Brennkraftmaschine angeordnet ist.The in Fig. 1 shown durchströmbare exhaust gas guide portion 2 of an exhaust gas turbocharger 1 is provided in an exhaust tract of an internal combustion engine, not shown, in which it is a gasoline engine or a diesel engine, provided. The exhaust gas turbocharger 1 further includes a non-illustrated throughflow fresh air guide portion and a bearing portion, not shown, which is arranged in a non-illustrated intake tract of the internal combustion engine.

Der Abgasturbolader 1 weist ein Laufzeug 3 auf, welches ein nicht näher dargestelltes Verdichterrad zum Ansaugen und Verdichten von Verbrennungsluft, ein Turbinenrad 4 zur Expansion von Abgas sowie eine das Verdichterrad mit dem Turbinenrad 4 drehfest verbindende Welle 5 mit einer Drehachse 6 umfasst. Die Welle 5 ist im Lagerabschnitt des Abgasturboladers 1 drehbar gelagert, welcher zwischen dem Luftführungsabschnitt und dem Abgasführungsabschnitt 2 positioniert ist.The exhaust gas turbocharger 1 has a running gear 3, which is a not-shown compressor wheel for sucking and compressing combustion air, a turbine wheel 4 for expansion of exhaust gas and a compressor wheel with the turbine wheel 4 rotatably connecting shaft 5 with a Rotary axis 6 includes. The shaft 5 is rotatably mounted in the bearing portion of the exhaust gas turbocharger 1, which is positioned between the air guide portion and the exhaust gas guide portion 2.

Zur Einströmung des Abgases in den Abgasführungsabschnitt 2 ist ein Eintrittskanal 7 im Abgasführungsabschnitt 2 ausgebildet. Der Eintrittskanal 7 dient zur Konditionierung des Abgases, welches im Betrieb der Brennkraftmaschine das Turbinenrad 4 in eine rotierende Bewegung versetzt. Mit Hilfe der Welle 5 das Verdichterrad ebenfalls in Rotation versetzt wird, so dass es Verbrennungsluft ansaugt und verdichtet.For the inflow of the exhaust gas into the exhaust gas guide section 2, an inlet channel 7 is formed in the exhaust gas guide section 2. The inlet channel 7 is used to condition the exhaust gas, which puts the turbine wheel 4 in a rotating motion during operation of the internal combustion engine. With the help of the shaft 5, the compressor wheel is also set in rotation, so that it sucks in combustion air and compressed.

Stromab des Eintrittskanals 7 ist im Abgasführungsabschnitt 2 ein Spiralkanal 8 angeordnet, welcher zur Bereitstellung einer rotationssymmetrischen Strömung dient. Des Weiteren ist der Spiralkanal 8 als Verbindungskanal zwischen dem Eintrittskanal 7 und einem Zuströmkanal 9, welcher stromab des Spiralkanals 8 positioniert ist, ausgebildet. Am Eintritt in den Spiralkanal 8 ist im Abgasführungsabschnitt 2 eine Spiralzunge 20 ausgestaltet. Stromab des Zuströmkanals 9 ist eine Radkammer 10 im Abgasführungsabschnitt 2 angeordnet, in welcher das Turbinenrad 4 drehbar aufgenommen ist. Stromab der Radkammer 10 weist der Abgasführungsabschnitt 2 einen Austrittskanal 11 zum Entweichen des Abgases aus dem Abgasführungsabschnitt 2 auf.Downstream of the inlet channel 7, a spiral channel 8 is arranged in the exhaust gas guide section 2, which serves to provide a rotationally symmetrical flow. Furthermore, the spiral channel 8 is formed as a connecting channel between the inlet channel 7 and an inflow channel 9, which is positioned downstream of the spiral channel 8. At the entry into the spiral channel 8, a spiral tongue 20 is configured in the exhaust gas guide section 2. Downstream of the inflow channel 9, a wheel chamber 10 is arranged in the exhaust gas guide section 2, in which the turbine wheel 4 is rotatably received. Downstream of the wheel chamber 10, the exhaust gas guide section 2 has an outlet channel 11 for the escape of the exhaust gas from the exhaust gas guide section 2.

Damit sowohl bei niedrigen Lasten und niedrigen Drehzahlen der Brennkraftmaschine als auch bei hohen Lasten und hohen Drehzahlen der Brennkraftmaschine ein größtmöglicher Abgasturboladerwirkungsgrad erreichbar ist, ist das Abgas mit Hilfe eines verstellbar ausgebildeten Leitapparates 12 konditionierbar, welcher im Abgasführungsabschnitt 2 angeordnet ist.Thus, a maximum exhaust gas turbocharger efficiency can be achieved both at low loads and low speeds of the engine and at high loads and high speeds of the internal combustion engine, the exhaust gas with the aid of an adjustable trained Leitapparates 12 is conditioned, which is arranged in the exhaust gas guide section 2.

In Fig. 1 ist ein Leitapparat 12 gemäß dem Stand der Technik dargestellt. Der Leitapparat 12 ist das Turbinenrad 4 ringförmig umfassend ausgebildet und weist einen Lagerring 13 zur Aufnahme von Leitschaufeln 14 auf, welche zur Strömungskonditionierung vorgesehen sind. Die Leitschaufeln 14 sind auf dem Lagerring 13 drehbar gelagert.In Fig. 1 a nozzle 12 is shown according to the prior art. The nozzle 12, the turbine wheel 4 is formed annularly comprehensive and has a bearing ring 13 for receiving guide vanes 14, which are provided for flow conditioning. The guide vanes 14 are rotatably mounted on the bearing ring 13.

Der Lagerring 13 ist im Abgasführungsabschnitt 2 so positioniert, dass die Leitschaufeln 14 im Zuströmkanal 9 angeordnet sind. Dem Lagerring 13 gegenüberliegend positioniert ist eine Konturhülse 15, welche zur Strömungskonditionierung und zur vereinfachten Montage des Leitapparates 12 ausgebildet ist.The bearing ring 13 is positioned in the exhaust gas guide section 2 so that the guide vanes 14 are arranged in the inflow channel 9. The bearing ring 13 is positioned opposite a contour sleeve 15, which is designed for flow conditioning and simplified assembly of the nozzle 12.

Zur Fixierung eines ersten Abstandes A zwischen der Konturhülse 15 und dem Lagerring 13, welcher zur Vermeidung eines Verkantens der Leitschaufeln 14 bei Änderung ihrer Position notwendig ist, sind Distanzelemente 16 im Zuströmkanal 9 positioniert. Die in Fig. 2 dargestellten Distanzelemente 16 gemäß dem Stand der Technik sind zylindrisch ausgestaltet.For fixing a first distance A between the contour sleeve 15 and the bearing ring 13, which is necessary to avoid tilting of the guide vanes 14 when changing their position, spacer elements 16 are positioned in the inflow channel 9. In the Fig. 2 shown spacers 16 according to the prior art are cylindrical.

In Fig. 3 ist in einer Draufsicht der Leitapparat 12 eines Abgasturboladers 1 dargestellt. Die Distanzelemente 16 weisen eine Längsachse 17, eine Mantelfläche 18, eine Länge L und eine Querschnittsfläche 19 auf (s. Fig. 5). Die Distanzelemente 16 des erfindungsgemäßen Abgasturboladers 1 gem. Fig. 4 sind strömungsgünstig gestaltet, derart, dass die Mantelfläche 18 einen zweiten Abstand MA von der Längsachse 17 aufweist, der über die Querschnittsfläche 19 veränderlich ist.In Fig. 3 is shown in a plan view of the nozzle 12 of an exhaust gas turbocharger 1. The spacer elements 16 have a longitudinal axis 17, a lateral surface 18, a length L and a cross-sectional area 19 (see FIG. Fig. 5 ). The spacer elements 16 of the exhaust gas turbocharger 1 according to the invention gem. Fig. 4 are designed aerodynamically, such that the lateral surface 18 has a second distance MA from the longitudinal axis 17, which is variable over the cross-sectional area 19.

Es ist eine bevorzugte Querschnittsfläche 19 des Distanzelementes 16 realisiert, welche eine einer Leitschaufelquerschnittsfläche ähnliche, tropfenförmige Form aufweist. Die Querschnittsfläche 19 ist entlang der Längsachse 17 gleich bleibend ausgebildet. Ebenso könnte die Mantelfläche 18 zusätzlich oder ausschließlich über die Länge L einen veränderlichen zweiten Abstand MA aufweisen, so dass beispielsweise das Distanzelement 16 eine symmetrische oder asymmetrische, taillierte oder eine bauchige Kontur aufweist. Mit Hilfe des erfindungsgemäßen Abgasturboladers 1 ist neben einer Reduzierung der Wirkungsgradverluste des Abgasturboladers 1 eine gleichmäßige Anströmung der Leitschaufeln 14 gewährleistet. Daraus kann eine gleichmäßige Verteilung von Verstellmomenten der Leitschaufeln 14 resultieren, so dass eine Reduzierung des Verschleißes des Leitapparates 12 herbeiführbar ist.A preferred cross-sectional area 19 of the spacer element 16 is realized, which has a drop-shaped shape similar to a guide blade cross-sectional area. The cross-sectional area 19 is designed to be consistent along the longitudinal axis 17. Likewise, the lateral surface 18 could additionally or exclusively over the length L have a variable second distance MA, so that For example, the spacer element 16 has a symmetrical or asymmetrical, waisted or a bulbous contour. With the aid of the exhaust gas turbocharger 1 according to the invention a uniform flow of the guide vanes 14 is ensured in addition to a reduction in the efficiency losses of the exhaust gas turbocharger 1. This can result in a uniform distribution of adjusting moments of the guide vanes 14, so that a reduction in the wear of the nozzle 12 can be brought about.

Auf dem Lagerring 13 sind insgesamt drei Distanzelemente 16 in einem dritten Abstand RD von der Drehachse 6 angeordnet, welcher größer ist als ein vierter Abstand RL der Leitschaufeln 14 von der Drehachse 6. Die Distanzelemente 16 sind bevorzugt hülsenförmig ausgebildet. In einem weiteren Ausführungsbeispiel sind mindestens vier Distanzelemente 16 vorgesehen.On the bearing ring 13 a total of three spacer elements 16 are arranged at a third distance RD from the axis of rotation 6, which is greater than a fourth distance RL of the guide vanes 14 from the axis of rotation 6. The spacer elements 16 are preferably formed sleeve-shaped. In a further embodiment, at least four spacer elements 16 are provided.

Eine Sehnenlänge SL des Distanzelements 16 weist im Ausführungsbeispiel etwa die vierfache Größe einer größten Profildicke PD des Distanzelements 16 auf. Zur Herbeiführung einer Wirkungsgradverbesserung sollte die Sehnenlänge SL mindestens die doppelte Größe der Profildicke PD aufweisen.A chord length SL of the spacer element 16 in the exemplary embodiment has approximately four times the size of a largest profile thickness PD of the spacer element 16. To achieve an improvement in efficiency, the chord length SL should be at least twice the size of the profile thickness PD.

Die Distanzelemente 16 sind relativ zu den Leitschaufeln 14 in einer strömungsgünstigen Positionierung aufgestellt. Die Positionierung ist so gewählt, dass ein vom Distanzelement 16 initiierter erster Nachlauf 21 einen von zwei nebeneinander angeordneten Leitschaufeln 14 gebildeten Kanal 22, diesen idealerweise mittig durchströmen kann.The spacers 16 are placed relative to the vanes 14 in a streamlined positioning. The positioning is selected such that a first wake 21 initiated by the spacer element 16 can flow through a channel 22 formed by two guide vanes 14 arranged next to one another, ideally in the middle thereof.

Gemäß Fig. 4 ist in einem weiteren Ausführungsbeispiel zur weiteren Wirkungsgradsteigerung eines der insgesamt drei Distanzelemente 16 im Bereich eines zweiten Nachlaufs 23 positioniert, welcher im Bereich der Spiralzunge 20 ausgebildet ist.According to Fig. 4 is positioned in a further embodiment for further increase in efficiency of one of the three spacer elements 16 in the region of a second wake 23, which is formed in the region of the spiral tongue 20.

Im Ausführungsbeispiel sind die Distanzelemente 16 auf dem Lagerring 13 gelagert. In einem weiteren Ausführungsbeispiel sind die Distanzelemente 16 zusätzlich auf der Konturhülse 15 gelagert. In einem weiteren Ausführungsbeispiel sind die Distanzelemente 16 nur auf der Konturhülse 15 gelagert. Neben der Funktion einen konstanten Abstand zwischen dem Lagerring 13 und der Konturhülse 15 herbeizuführen, kann dem Distanzelement 16 auch eine Trägerfunktion zugeordnet werden, in dem Sinne, dass die Konturhülse 15 vollständig von dem Distanzelement 16 getragen und positioniert beziehungsweise radial und axial fixiert wird.In the exemplary embodiment, the spacer elements 16 are mounted on the bearing ring 13. In a further embodiment, the spacer elements 16 are additionally mounted on the contour sleeve 15. In a further embodiment, the spacer elements 16 are mounted only on the contour sleeve 15. In addition to the function to bring about a constant distance between the bearing ring 13 and the contour sleeve 15, the spacer element 16 can also be assigned a carrier function, in the sense that the contour sleeve 15 is completely supported and positioned by the spacer element 16 or fixed radially and axially.

In einem nicht näher dargestellten Ausführungsbeispiel sind die Distanzelemente 16 drehbar und/oder translatorisch bewegbar gelagert. Der Lagerring 13 weist zur translatorischen Bewegung des Distanzelementes 16 eine nutförmige, idealerweise bogenförmig ausgebildete Öffnung auf, in welcher das Distanzelement 16 verschiebbar gelagert ist. Zusätzlich ist eine Verstellvorrichtung zur Verstellung des Distanzelementes 16 vorzusehen, welche einen mechanischen Aufbau aufweist. Die Verstellung erfolgt abhängig von Betriebsgrößen der Brennkraftmaschine, mit Hilfe einer Regel- und Steuereinheit.In one embodiment, not shown, the spacer elements 16 are rotatably and / or translationally mounted. The bearing ring 13 has for translational movement of the spacer element 16 has a groove-shaped, ideally arcuate opening in which the spacer element 16 is slidably mounted. In addition, an adjusting device for adjusting the spacer element 16 is provided, which has a mechanical structure. The adjustment is dependent on operating variables of the internal combustion engine, with the aid of a control and control unit.

Claims (10)

  1. An exhaust gas turbocharger for an internal combustion engine, comprising an exhaust gas routing portion (2) which is arranged in an exhaust gas system of the internal combustion engine, and a turbine wheel (4) which is rotatably accommodated in a wheel chamber (10) of the exhaust gas routing portion (2) and which may be approached by the exhaust gas flowing from the internal combustion engine, wherein the incident flow of the turbine wheel (4) is conditionable by means of a guide vane mechanism (12), and wherein the guide vane mechanism (12) comprises a bearing ring (13) with rotatably supported guide vanes (14) and a contour sleeve (15), with at least one spacer element (16) with a longitudinal axis (17), a surface area (18) and a cross-sectional area (19) being provided for fixing a first distance (A) between the bearing ring (13) and the contour sleeve (15), wherein the exhaust gas routing portion (2) comprises a spiral channel (8) with a spiral tongue (20),
    characterised in that
    the surface area (18) comprises a second distance (MA) from the longitudinal axis (17), which is variable over the cross-sectional area (19) and/or the length (L) of the spacer element (16), with the spacer element (16) being positioned in a region of a second wake (23) of the spiral tongue (20).
  2. The exhaust gas turbocharger according to Claim 1,
    characterised in that
    the cross-sectional area (19) is formed drop-shaped.
  3. The exhaust gas turbocharger according to Claim 1 or 2,
    characterised in that
    a chord length (SL) of the spacer element (16) has at least twice the size of the maximum profile thickness (PD) of the spacer element (16).
  4. The exhaust gas turbocharger according to one of Claims 1 to 3,
    characterised in that
    the spacer element (16) is formed sleeve-shaped.
  5. The exhaust gas turbocharger according to one of Claims 1 to 4,
    characterised in that
    the spacer element (16) is supported rotatably and/or translatorily movable.
  6. The exhaust gas turbocharger according to one of Claims 1 to 5,
    characterised in that
    the spacer element (16) is positioned in such a manner that a first wake (21) which is initiated by the spacer element (16) may flow through a channel (22) which is formed by two guide vanes (14) arranged adjacent to one another.
  7. The exhaust gas turbocharger according to Claim 6,
    characterised in that
    the spacer element (16) is positioned in such a manner that a boundary layer of the guide vane (14) cannot be influenced.
  8. The exhaust gas turbocharger according to one of Claims 1 to 7,
    characterised in that
    at least three spacer elements (16) are arranged on the bearing ring (13) for fixing the distance (A) between the bearing ring (13) and the contour sleeve (15).
  9. The exhaust gas turbocharger according to one of Claims 1 to 8,
    characterised in that
    the spacer element (16) is movably supported on the contour sleeve (15).
  10. The exhaust gas turbocharger according to one of Claims 1 to 9,
    characterised in that
    the spacer element (16) is connected immovably with the contour sleeve (15).
EP08773444A 2007-06-23 2008-06-14 Exhaust gas turbocharger for an internal combustion engine Not-in-force EP2167793B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007029004A DE102007029004A1 (en) 2007-06-23 2007-06-23 Exhaust gas turbocharger for an internal combustion engine
PCT/EP2008/004807 WO2009000436A2 (en) 2007-06-23 2008-06-14 Exhaust gas turbocharger for an internal combustion engine

Publications (2)

Publication Number Publication Date
EP2167793A2 EP2167793A2 (en) 2010-03-31
EP2167793B1 true EP2167793B1 (en) 2012-04-18

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EP08773444A Not-in-force EP2167793B1 (en) 2007-06-23 2008-06-14 Exhaust gas turbocharger for an internal combustion engine

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US (1) US8418460B2 (en)
EP (1) EP2167793B1 (en)
JP (1) JP5733855B2 (en)
AT (1) ATE554271T1 (en)
DE (1) DE102007029004A1 (en)
WO (1) WO2009000436A2 (en)

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Publication number Publication date
ATE554271T1 (en) 2012-05-15
DE102007029004A1 (en) 2008-12-24
US20100154415A1 (en) 2010-06-24
WO2009000436A2 (en) 2008-12-31
EP2167793A2 (en) 2010-03-31
JP5733855B2 (en) 2015-06-10
US8418460B2 (en) 2013-04-16
JP2010530935A (en) 2010-09-16
WO2009000436A3 (en) 2009-02-12

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