WO2006018189A1 - Exhaust turbocharger for an internal combustion engine - Google Patents

Exhaust turbocharger for an internal combustion engine Download PDF

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Publication number
WO2006018189A1
WO2006018189A1 PCT/EP2005/008635 EP2005008635W WO2006018189A1 WO 2006018189 A1 WO2006018189 A1 WO 2006018189A1 EP 2005008635 W EP2005008635 W EP 2005008635W WO 2006018189 A1 WO2006018189 A1 WO 2006018189A1
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WO
WIPO (PCT)
Prior art keywords
turbine
turbine wheel
internal combustion
combustion engine
exhaust gas
Prior art date
Application number
PCT/EP2005/008635
Other languages
German (de)
French (fr)
Inventor
Wolfram Schmid
Siegfried Sumser
Original Assignee
Daimlerchrysler Ag
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Publication date
Application filed by Daimlerchrysler Ag filed Critical Daimlerchrysler Ag
Publication of WO2006018189A1 publication Critical patent/WO2006018189A1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape

Definitions

  • the invention relates to an exhaust gas turbocharger for an internal combustion engine according to the preamble of claim 1.
  • the guide grid comprises a plurality of guide vanes distributed over the circumference of the guide grid.
  • the turbine blades of the turbine wheel are formed in such a way that the first natural frequency of each turbine blade depending on the number of guide vanes and the maximum supercharger speed follows an inequality and does not exceed a certain limit. This ensures that the first natural frequency of each turbine blade has a sufficient distance to the excitation frequency, which is calculated by multiplying the number of blades on the guide grid and the maximum supercharger speed in engine braking operation.
  • the invention is based on the problem to provide an exhaust gas turbocharger with a guide grid or a free annular nozzle without guide grid and with a thin-bladed turbine wheel, which has a high rigidity and high strength.
  • Turbine wheel blading the so-called fundamental tone to put on the maximum operating speed of the exhaust gas turbocharger in engine braking mode. If the operation of the exhaust gas turbocharger in resonance to this natural frequency, this can damage due to vibration fractures both in the exit region of the blade on a
  • Turbinenradaustrittskante as well as in the inlet region at a turbine wheel leading edge.
  • Turbine wheel leading edge to a blade height of a vane of a guide grid or a nozzle height of a free annular nozzle in relation to each other said ratio is greater than 2.0.
  • a ratio of a rear wall diameter of the turbine wheel to the turbine wheel inlet diameter is within a certain range, whereby a relative movement of the turbine blades is made possible with a vibration excitation of the turbine blades to each other. Furthermore, due to the not drawn up to Turbinenradeintritt rear wall of the turbine wheel an advantageous effect on the damping properties of the turbine wheel.
  • the turbine wheel diameter in an optimized engine turbocharger system is advantageously in a certain size ratio to the displacement of the internal combustion engine.
  • a free Strömungsgueritess which is located in a transition from a spiral channel of the turbine to the turbine, results in a turbo braking factor, which at maximum braking power in engine braking operation of a multiplication of the free flow cross-section with the inlet diameter of the turbine wheel and division with the displacement calculated internal combustion engine, which is in particular less than 0.006, possibly even less than 0.003.
  • this optimized value of the turbo-braking factor it is ensured that with maximum achievable engine braking power, the thermal load on the internal combustion engine and the exhaust-gas turbocharger is comparatively low.
  • the high engine braking powers and associated thermal and mechanical loads occurring with these turbo-braking factors can be absorbed by the turbine wheel without damage.
  • FIG. 1 is a schematic representation of a detail of a turbine wheel and a vane of an exhaust gas turbocharger according to the invention
  • FIG. 2 is a schematic plan view of the turbine wheel of the exhaust gas turbocharger according to the invention.
  • Fig. 3 shows a turbine wheel of the exhaust gas turbocharger according to the invention
  • FIG. 4 shows a twin-flow turbine of the exhaust gas turbocharger according to the invention.
  • Fig. 1 is a schematic representation of a detail of a turbine wheel 1 of a turbine 14 shown in FIG. 4 of an exhaust gas turbocharger, not shown in an exhaust duct, not shown, of an internal combustion engine, not shown, which is for example a gasoline or a diesel engine, mapped ,
  • the turbine wheel 1 with a turbine wheel inlet diameter D ⁇ has a turbine hub 2.
  • a turbine hub 2 which forms a rotationally fixed connection with the turbine hub 2, the turbine wheel 1 is rotatably coupled with a compressor, not shown in a non-illustrated intake of the engine and is driven by the turbine 1.
  • the compressor compresses sucked combustion air, which is supplied via not shown inlet ducts of the internal combustion engine.
  • the turbine wheel 1 is delimited by a turbine housing 4.
  • turbine blades 3 projecting approximately radially from the turbine hub 2 are arranged at uniform intervals, with only one turbine blade 3 being illustrated by way of example in FIG.
  • the turbine hub 2 has at its larger diameter end a turbine rear wall 5 with a diameter D 3 .
  • a turbine wheel inlet edge 6 of the turbine blade 3 is located perpendicular to the turbine wheel rear wall 5 at a distance H from the diameter D 8 of the turbine wheel rear wall 5.
  • the guide grid 7 is adjustable, so that via the guide grid 7, a free flow cross section A ⁇ , which is in a transition from a spiral channel 15 shown in FIG. 4 of the turbine 14 is located on the turbine 1 is adjustable.
  • This free flow cross-section A ⁇ determines the velocity of a flow medium and thus an inlet velocity of the flow medium into the turbine wheel 1 and thus also the rate of occurrence on a turbine blade 3 of the turbine wheel 1.
  • An arrow 9 represents the flow direction of the flow medium.
  • FIG. 2 shows the schematic plan view of a turbine blade 3 of the turbine wheel 1 of the exhaust gas turbocharger according to the invention.
  • a tangent 10 of the turbine blade 3 encloses an angle with a plane of the turbine wheel rear wall 5, the so-called
  • Rake angle ⁇ is advantageously less than 50 °.
  • S ER true length of the turbine wheel inlet edge 6 runs. The rotation of the turbine wheel 1 takes place in the direction of rotation 12.
  • the true length S ER of the turbine wheel leading edge 6 has a value of at least one quarter of the turbine wheel diameter D ⁇ and is at least twice as large as the blade height h Le or, in the case of a free annular nozzle, the height of the free annular nozzle.
  • the greater the ratio of the true length of the turbine wheel inlet edge S ER to the blade height h Le the more a pressure peak of a flow of the flow medium is reduced to the turbine blade 3.
  • Turbine wheel blading is exceeded at a maximum speed of the exhaust gas turbocharger.
  • Advantageously, thereby thin turbine blades 3 are used, which are operable damage-free under very high loads.
  • a ratio DD of the diameter D 5 of Turbinenrad Wegwand 5 to the turbine wheel inlet diameter D ⁇ is set within a range of values, which has the value of 0.6 as the minimum ratio and the value 0, 95 as the maximum ratio.
  • Fig. 3 the turbine wheel 1 of the exhaust gas turbocharger is shown to further illustrate the exhaust gas turbocharger according to the invention.
  • the turbine 14 is formed as a double-flow asymmetric turbine.
  • the turbine may also be designed as a single-flow turbine or a symmetrical multi-flow turbine.
  • a sizing rule may be considered. This dimensioning rule supports the design of the free flow cross-section A ⁇ and the
  • Ingress diameter D ⁇ of the turbine wheel 1 as a function of a stroke volume of the internal combustion engine which can be calculated as the sum of the difference volumes between the smallest and largest volumes of the combustion chambers of the internal combustion engine, in particular a reciprocating internal combustion engine.
  • a braking braking factor TBF is determined according to the relationship during braking operation at maximum braking power of the internal combustion engine
  • TBF A ⁇ • - V H determined, which is to achieve high braking performance while maintaining allowable load limits less than 0.006, in particular less than 0.003.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)

Abstract

Disclosed is an exhaust turbocharger for an internal combustion engine comprising a compressor in the intake manifold and a turbine in the exhaust manifold thereof, the compressor being connected to the turbine via a torsion-proof shaft. The true length of the leading edge of the turbine wheel and the inlet diameter of the turbine wheel as well as the true length of the leading edge of the turbine wheel and the height of the guide vanes are at a specific proportion relative to each other, respectively, while being provided with a minimum value that assures stiffness and rigidity of the turbine wheel.

Description

Abgasturbolader für eine Brennkraftmaschine Exhaust gas turbocharger for an internal combustion engine
Die Erfindung betrifft einen Abgasturbolader für eine Brennkraftmaschine nach 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 gattungsgemäßen Druckschrift DE 102 12 032 Al geht ein Abgasturbolader mit einem Leitgitter hervor. Das Leitgitter umfasst eine Mehrzahl über den Umfang des Leitgitters verteilte Leitschaufeln. Die Turbinenschaufeln des Turbinenrades sind in der Weise ausgebildet, dass die erste Eigenfrequenz jeder Turbinenschaufel in Abhängigkeit der Anzahl der Leitschaufeln des Leitgitters und der maximalen Laderdrehzahl einer Ungleichung folgt und einen bestimmten Grenzwert nicht überschreitet. Damit ist sichergestellt, dass die erste Eigenfrequenz jeder Turbinenschaufel einen ausreichenden Abstand zur Anregungsfrequenz aufweist, welche durch Multiplikation der Schaufelanzahl am Leitgitter und der maximalen Laderdrehzahl im Motorbremsbetrieb berechnet wird. Dieser Abstand zwischen Eigenfrequenz und Anregungsfrequenz stellt sicher, dass bei maximaler Motorbremsleistung, bei der die thermodynamische Belastung des Turbinenrades ein Maximum erreicht, keine zusätzliche Schwingungsanregung der Turbinenschaufeln stattfindet. Die Bruchgefahr ist somit deutlich reduziert und damit die Lebensdauer des Turbinenrades erhöht. Der Erfindung liegt das Problem zugrunde, einen Abgasturbolader mit einem Leitgitter oder einer freien Ringdüse ohne Leitgitter und mit einem dünnschaufeligen Turbinenrad zu schaffen, welches eine hohe Steifigkeit und eine hohe Festigkeit aufweist.From the generic document DE 102 12 032 Al an exhaust gas turbocharger with a guide grid is apparent. The guide grid comprises a plurality of guide vanes distributed over the circumference of the guide grid. The turbine blades of the turbine wheel are formed in such a way that the first natural frequency of each turbine blade depending on the number of guide vanes and the maximum supercharger speed follows an inequality and does not exceed a certain limit. This ensures that the first natural frequency of each turbine blade has a sufficient distance to the excitation frequency, which is calculated by multiplying the number of blades on the guide grid and the maximum supercharger speed in engine braking operation. This distance between natural frequency and excitation frequency ensures that at maximum engine braking power at which the thermodynamic load of the turbine wheel reaches a maximum, no additional vibration excitation of the turbine blades takes place. The risk of breakage is thus significantly reduced and thus increases the service life of the turbine wheel. The invention is based on the problem to provide an exhaust gas turbocharger with a guide grid or a free annular nozzle without guide grid and with a thin-bladed turbine wheel, which has a high rigidity and high strength.
Dieses Problem wird erfindungsgemäß mit den Merkmalen des Anspruchs 1 gelöst. Die Unteransprüche enthalten zweckmäßige Weiterbildungen.This problem is solved according to the invention with the features of claim 1. The dependent claims contain expedient developments.
Grundsätzlich wird bei der Entwicklung der Abgasturbolader darauf geachtet eine erste Eigenfrequenz derBasically, care is taken in the development of the exhaust gas turbocharger a first natural frequency of
Turbinenradbeschaufelung, den sogenannten Grundton, über die maximale Betriebsdrehzahl des Abgasturboladers im Motorbremsbetrieb zu legen. Erfolgt der Betrieb des Abgasturboladers in Resonanz zu dieser Eigenfrequenz, kann dies zu Schäden durch Schwingungsbrüche sowohl im Austrittsbereich der Schaufel an einerTurbine wheel blading, the so-called fundamental tone to put on the maximum operating speed of the exhaust gas turbocharger in engine braking mode. If the operation of the exhaust gas turbocharger in resonance to this natural frequency, this can damage due to vibration fractures both in the exit region of the blade on a
Turbinenradaustrittskante als auch im Eintrittsbereich an einer Turbinenradeintrittskante führen. Zur Problemlösung wird vorgeschlagen, eine wahre Länge der Turbinenradeintrittskante zum Durchmesser eines Turbinenradeintritts in ein Verhältnis zueinander zu setzen, wobei das Verhältnis größer ist als 0,25. Des Weiteren wird die wahre Länge derTurbinenradaustrittskante as well as in the inlet region at a turbine wheel leading edge. To solve the problem, it is proposed to set a true length of the turbine wheel leading edge to the diameter of a turbine wheel inlet in a relationship to each other, wherein the ratio is greater than 0.25. Furthermore, the true length of the
Turbinenradeintrittskante zu einer Schaufelhöhe einer Leitschaufel eines Leitgitters oder einer Düsenhöhe einer freien Ringdüse in ein Verhältnis zueinander gesetzt, wobei dieses Verhältnis größer ist als 2,0. Mit Hilfe dieser Beziehungen ist sichergestellt, dass mindestens die erste Eigenfrequenz der Turbinenradbeschaufelung bei der maximalen Drehzahl des Abgasturboladers bei niederen Anregungsintensitäten überschritten wird. Dadurch sind dünnschaufelige Turbinenräder einsetzbar, die unter sehr hohen Belastungen schadensfrei betreibbar sind.Turbine wheel leading edge to a blade height of a vane of a guide grid or a nozzle height of a free annular nozzle in relation to each other, said ratio is greater than 2.0. With the help of these relationships it is ensured that at least the first natural frequency of the turbine wheel blading is exceeded at low maximum intensities at the maximum rotational speed of the exhaust gas turbocharger. Thereby are Thin-bladed turbine wheels can be used, which can be operated without damage under very high loads.
In einer weiterführenden Ausgestaltung nach Anspruch 2 liegt ein Verhältnis eines Rückwanddurchmessers des Turbinenrades zum Turbinenradeintrittsdurchmesser innerhalb eines bestimmten Bereiches, wodurch bei einer Schwingungsanregung der Turbinenschaufeln eine Relativbewegung der Turbinenradschaufeln zueinander ermöglicht wird. Des Weiteren ergibt sich aufgrund der nicht bis zum Turbinenradeintritt hochgezogenen Rückwand des Turbinenrades ein vorteilhafter Einfluss auf die Dämpfungseigenschaften des Turbinenrades.In a further embodiment according to claim 2, a ratio of a rear wall diameter of the turbine wheel to the turbine wheel inlet diameter is within a certain range, whereby a relative movement of the turbine blades is made possible with a vibration excitation of the turbine blades to each other. Furthermore, due to the not drawn up to Turbinenradeintritt rear wall of the turbine wheel an advantageous effect on the damping properties of the turbine wheel.
In einer weiterführenden Ausgestaltung nach Anspruch 3 steht der Turbinenraddurchmesser in einem optimierten Brennkraftmaschinen-Turboladersystem vorteilhaft in einem bestimmten Größenverhältnis zum Hubvolumen der Brennkraftmaschine. Unter zusätzlicher Berücksichtigung eines freien Strömungsguerschnitts, welcher sich in einem Übergang von einem Spiralkanal der Turbine auf das Turbinenrad befindet, ergibt sich ein Turbobremsfaktor, der sich bei maximaler Bremsleistung im Motorbremsbetrieb aus einer Multiplikation des freien Strömungsquerschnitts mit dem Eintrittsdurchmesser des Turbinenrades und Division mit dem Hubvolumen der Brennkraftmaschine errechnet, der insbesondere kleiner ist als 0,006, gegebenenfalls sogar kleiner ist als 0,003. Bei diesem optimierten Wert des Turbobremsfaktors ist sichergestellt, dass bei maximal erreichbarer Motorbremsleistung die thermische Belastung der Brennkraftmaschine und des Abgasturboladers vergleichsweise gering ist . Die bei diesen Turbobremsfaktoren auftretenden hohen Motorbremsleistungen und damit einhergehenden thermischen und mechanischen Belastungen können von dem Turbinenrad schadensfrei aufgenommen werden. Weitere Vorteile und zweckmäßige Ausführungen der Erfindung sind den Ansprüchen, der Figurenbeschreibung und den Zeichnungen zu entnehmen. Dabei zeigen:In a further embodiment according to claim 3, the turbine wheel diameter in an optimized engine turbocharger system is advantageously in a certain size ratio to the displacement of the internal combustion engine. With additional consideration of a free Strömungsguerschnitts, which is located in a transition from a spiral channel of the turbine to the turbine, results in a turbo braking factor, which at maximum braking power in engine braking operation of a multiplication of the free flow cross-section with the inlet diameter of the turbine wheel and division with the displacement calculated internal combustion engine, which is in particular less than 0.006, possibly even less than 0.003. With this optimized value of the turbo-braking factor, it is ensured that with maximum achievable engine braking power, the thermal load on the internal combustion engine and the exhaust-gas turbocharger is comparatively low. The high engine braking powers and associated thermal and mechanical loads occurring with these turbo-braking factors can be absorbed by the turbine wheel without damage. Further advantages and expedient embodiments of the invention can be taken from the claims, the description of the figures and the drawings. Showing:
Fig. 1 eine schematisierte Darstellung eines Ausschnitts eines Turbinenrades und einer Leitschaufel eines erfindungsgemäßen Abgasturboladers,1 is a schematic representation of a detail of a turbine wheel and a vane of an exhaust gas turbocharger according to the invention,
Fig. 2 eine schematisierte Draufsicht auf das Turbinenrad des erfindungsgemäßen Abgasturboladers,2 is a schematic plan view of the turbine wheel of the exhaust gas turbocharger according to the invention,
Fig. 3 ein Turbinenrad des erfindungsgemäßen Abgasturboladers undFig. 3 shows a turbine wheel of the exhaust gas turbocharger according to the invention and
Fig. 4 eine zweiflutige Turbine des erfindungsgemäßen Abgasturboladers.4 shows a twin-flow turbine of the exhaust gas turbocharger according to the invention.
In Fig. 1 ist eine schematisierte Darstellung eines Ausschnitts eines Turbinenrades 1 einer in Fig. 4 dargestellten Turbine 14 eines nicht näher dargestellten Abgasturboladers in einem nicht näher dargestellten Abgastrakt einer nicht näher dargestellten Brennkraftmaschine, welche zum Beispiel ein Otto- oder ein Dieselmotor ist, abgebildet.In Fig. 1 is a schematic representation of a detail of a turbine wheel 1 of a turbine 14 shown in FIG. 4 of an exhaust gas turbocharger, not shown in an exhaust duct, not shown, of an internal combustion engine, not shown, which is for example a gasoline or a diesel engine, mapped ,
Das Turbinenrad 1 mit einem Turbinenradeintrittsdurchmesser Dτ weist eine Turbinenradnabe 2 auf. Über eine nicht näher dargestellte Welle, welche mit der Turbinenradnabe 2 eine drehfeste Verbindung bildet, ist das Turbinenrad 1 mit einem nicht näher dargestellten Verdichter in einem nicht näher dargestellten Ansaugtrakt der Brennkraftmaschine drehfest gekoppelt und wird vom Turbinenrad 1 angetrieben. Der Verdichter komprimiert angesaugte Verbrennungsluft, welche über nicht näher dargestellte Einlasskanäle der Brennkraftmaschine zugeführt wird. Das Turbinenrad 1 wird von einem Turbinengehäuse 4 begrenzt.The turbine wheel 1 with a turbine wheel inlet diameter D τ has a turbine hub 2. About a shaft, not shown, which forms a rotationally fixed connection with the turbine hub 2, the turbine wheel 1 is rotatably coupled with a compressor, not shown in a non-illustrated intake of the engine and is driven by the turbine 1. The compressor compresses sucked combustion air, which is supplied via not shown inlet ducts of the internal combustion engine. The turbine wheel 1 is delimited by a turbine housing 4.
Um den Umfang der Turbinenradnabe 2 sind in gleichmäßigen Abständen etwa radial von der Turbinenradnabe 2 abstehende Turbinenschaufeln 3 angeordnet, wobei in Fig. 1 exemplarisch nur eine Turbinenschaufel 3 abgebildet ist.Around the circumference of the turbine hub 2, turbine blades 3 projecting approximately radially from the turbine hub 2 are arranged at uniform intervals, with only one turbine blade 3 being illustrated by way of example in FIG.
Die Turbinenradnabe 2 weist an ihrem durchmessergrößeren Ende eine Turbinenradrückwand 5 mit einem Durchmesser D3 auf. Eine Turbinenradeintrittskante 6 der Turbinenschaufel 3 befindet sich senkrecht zur Turbinenradrückwand 5 in einem Abstand H vom Durchmesser D8 der Turbinenradrückwand 5.The turbine hub 2 has at its larger diameter end a turbine rear wall 5 with a diameter D 3 . A turbine wheel inlet edge 6 of the turbine blade 3 is located perpendicular to the turbine wheel rear wall 5 at a distance H from the diameter D 8 of the turbine wheel rear wall 5.
Im Turbinengehäuse 4 ist stromauf derIn the turbine housing 4 is upstream of
Turbinenradeintrittskante G der Turbinenschaufel 3 ein Leitgitter 7 mit einer Schaufelhöhe hLe einer nicht näher dargestellten Leitschaufel und einer Leitgitteraustrittskante 8 angeordnet. Das Leitgitter 7 ist verstellbar, so dass über das Leitgitter 7 ein freier Strömungsquerschnitt Aτ, welcher sich in einem Übergang von einem in Fig. 4 dargestellten Spiralkanal 15 der Turbine 14 auf das Turbinenrad 1 befindet einstellbar ist. Dieser freie Strömungsquerschnitt Aτ bestimmt die Geschwindigkeit eines Strömungsmediums und damit eine Eintrittsgeschwindigkeit des Strömungsmediums in das Turbinenrad 1 und damit auch die Auftrittsgeschwindigkeit auf eine Turbinenschaufel 3 des Turbinenrades 1. Ein Pfeil 9 stellt die Strömungsrichtung des Strömungsmediums dar.Turbinenradeintrittskante G of the turbine blade 3, a guide grid 7 with a blade height h Le a guide vane, not shown, and a Leitgitteraustrittskante 8 arranged. The guide grid 7 is adjustable, so that via the guide grid 7, a free flow cross section A τ , which is in a transition from a spiral channel 15 shown in FIG. 4 of the turbine 14 is located on the turbine 1 is adjustable. This free flow cross-section A τ determines the velocity of a flow medium and thus an inlet velocity of the flow medium into the turbine wheel 1 and thus also the rate of occurrence on a turbine blade 3 of the turbine wheel 1. An arrow 9 represents the flow direction of the flow medium.
Über einen entsprechend angelegten Spiralkanal 15 mit einer freien Ringdüse, also ohne Leitgitter 7, ist eine analoge Wirkung in der Turbine 14 auf die Geschwindigkeit des Strömungsmediums erzielbar. Fig. 2 zeigt die schematische Draufsicht auf eine Turbinenschaufel 3 des Turbinenrads 1 des erfindungsgemäßen Abgasturboladers. Um eine schlagähnliche Beanspruchung der Turbinenschaufel 3 zu verringern, schließt eine Tangente 10 der Turbinenschaufel 3 mit einer Ebene der Turbinenradrückwand 5 einen Winkel, den so genanntenAn analogous effect in the turbine 14 on the velocity of the flow medium can be achieved by means of a suitably arranged spiral channel 15 with a free annular nozzle, that is to say without a guide grid 7. FIG. 2 shows the schematic plan view of a turbine blade 3 of the turbine wheel 1 of the exhaust gas turbocharger according to the invention. In order to reduce a shock-like stress on the turbine blade 3, a tangent 10 of the turbine blade 3 encloses an angle with a plane of the turbine wheel rear wall 5, the so-called
Rakewinkel γ ein. Dieser Rakewinkel γ ist vorteilhaft kleiner als 50°. Entlang der Tangente 10 der Turbinenschaufel 3 verläuft eine wahre Länge SER der Turbinenradeintrittskante 6. Die Rotation des Turbinenrades 1 erfolgt in Drehrichtung 12.Rake angle γ. This rake angle γ is advantageously less than 50 °. Along the tangent 10 of the turbine blade 3, a true length S ER of the turbine wheel inlet edge 6 runs. The rotation of the turbine wheel 1 takes place in the direction of rotation 12.
Die wahre Länge SER der Turbinenradeintrittskante 6 weist erfindungsgemäß einen Wert von mindestens einem Viertel des Turbinenraddurchmessers Dτ auf und ist mindestens doppelt so groß wie die Schaufelhöhe hLe oder bei einer freien Ringdüse die Höhe der freien Ringdüse. Je größer das Verhältnis der wahren Länge der Turbinenradeintrittskante SER zur Schaufelhδhe hLe ist, umso mehr wird eine Druckspitze einer Strömung des Strömungsmediums auf die Turbinenschaufel 3 abgebaut.According to the invention, the true length S ER of the turbine wheel leading edge 6 has a value of at least one quarter of the turbine wheel diameter Dτ and is at least twice as large as the blade height h Le or, in the case of a free annular nozzle, the height of the free annular nozzle. The greater the ratio of the true length of the turbine wheel inlet edge S ER to the blade height h Le , the more a pressure peak of a flow of the flow medium is reduced to the turbine blade 3.
Mit Hilfe dieser Beziehungen ist sichergestellt, dass mindestens die erste Eigenfrequenz einerWith the help of these relationships it is ensured that at least the first natural frequency of a
Turbinenradbeschaufelung bei einer maximalen Drehzahl des Abgasturboladers überschritten wird. Vorteilhafterweise sind dadurch dünne Turbinenschaufeln 3 einsetzbar, die unter sehr hohen Belastungen schadensfrei betreibbar sind.Turbine wheel blading is exceeded at a maximum speed of the exhaust gas turbocharger. Advantageously, thereby thin turbine blades 3 are used, which are operable damage-free under very high loads.
Um bei einer Schwingungsanregung der Turbinenschaufeln 3 infolge einer bestimmten Abgasturboladerdrehzahl eine Relativbewegung der Turbinenschaufeln 3 zueinander zu ermöglichen ist ein Verhältnis DD des Durchmessers D5 der Turbinenradrückwand 5 zu dem Turbineradeintrittsdurchmesser Dτ innerhalb eines Wertebereiches zu legen, der als minimales Verhältnis den Wert 0,6 und als maximales Verhältnis den Wert 0, 95 aufweist.In order to enable a relative movement of the turbine blades 3 to each other at a vibration excitation of the turbine blades 3 due to a certain exhaust gas turbocharger speed is a ratio DD of the diameter D 5 of Turbinenradrückwand 5 to the turbine wheel inlet diameter D τ to set within a range of values, which has the value of 0.6 as the minimum ratio and the value 0, 95 as the maximum ratio.
In Fig. 3 ist zur weiteren Veranschaulichung des erfindungsgemäßen Abgasturboladers das Turbinenrad 1 des Abgasturboladers dargestellt.In Fig. 3, the turbine wheel 1 of the exhaust gas turbocharger is shown to further illustrate the exhaust gas turbocharger according to the invention.
In Fig. 4 ist die Turbine 14 als eine zweiflutige asymmetrische Turbine ausgebildet . Alternativ zu der zweiflutigen asymmetrischen Bauweise der Turbine 14, kann die Turbine auch als eine einflutige Turbine oder eine symmetrische mehrflutige Turbine ausgebildet sein.In Fig. 4, the turbine 14 is formed as a double-flow asymmetric turbine. As an alternative to the twin-flow asymmetric design of the turbine 14, the turbine may also be designed as a single-flow turbine or a symmetrical multi-flow turbine.
Um die Turbinenradbelastung, insbesondere die thermische Belastung, im Motorbremsbetrieb unter Verwendung von Abgasturbinen mit variabler Turbinengeometrie nicht zu überschreiten, kann eine Dimensionierungsregel berücksichtigt werden. Diese Dimensionierungsregel unterstützt die Auslegung des freien Strömungsquerschnitts Aτ und desIn order not to exceed the turbine load, in particular the thermal load, during engine braking operation using variable turbine geometry exhaust gas turbines, a sizing rule may be considered. This dimensioning rule supports the design of the free flow cross-section A τ and the
Eintrittsdurchmessers Dτ des Turbinenrades 1 in Abhängigkeit eines Hubvolumens der Brennkraftmaschine, welches als Summe der Differenzvolumina zwischen kleinstem und größtem Volumen der Brennräume der Brennkraftmaschine, insbesondere eine Hubkolben-Brennkraftmaschine errechenbar ist. Entsprechend dieser Dimensionierungsregel wird im Bremsbetrieb bei maximaler Bremsleistung der Brennkraftmaschine ein Turbobremsfaktor TBF gemäß der BeziehungIngress diameter D τ of the turbine wheel 1 as a function of a stroke volume of the internal combustion engine, which can be calculated as the sum of the difference volumes between the smallest and largest volumes of the combustion chambers of the internal combustion engine, in particular a reciprocating internal combustion engine. In accordance with this dimensioning rule, a braking braking factor TBF is determined according to the relationship during braking operation at maximum braking power of the internal combustion engine
Dτ D τ
TBF = Aτ • — VH ermittelt, der zur Erreichung hoher Bremsleistungen bei gleichzeitiger Einhaltung zulässiger Belastungsgrenzen kleiner als 0,006, insbesondere kleiner als 0,003 ist. TBF = A τ • - V H determined, which is to achieve high braking performance while maintaining allowable load limits less than 0.006, in particular less than 0.003.

Claims

Patentansprüche claims
Abgasturbolader für eine Brennkraftmaschine, mit einem im Ansaugtrakt der Brennkraftmaschine angeordneten Verdichter und einer im Abgasstrang der Brennkraftmaschine angeordneten Turbine (14) , welche Turbinenschaufeln (3) und ein Leitgitter (7) mit Leitschaufeln mit einer Schaufelhöhe (hLe) oder eine freie Ringdüse ohne Leitschaufeln mit einer DüsenhöheExhaust gas turbocharger for an internal combustion engine, with a compressor arranged in the intake tract of the internal combustion engine and a turbine (14) arranged in the exhaust tract of the internal combustion engine, which turbine blades (3) and a guide grid (7) with guide vanes with a blade height (h Le ) or a free annular nozzle without Guide vanes with a nozzle height
(hLe) aufweist, wobei die Turbine (14) einen Turbinenradeintrittsdurchmesser (Dτ) sowie eine wahre Länge (SER) einer Turbinenradeintrittskante (6) besitzt, dadurch gekennzeichnet, dass die wahre Länge (SER) der Turbinenradeintrittskante(h Le ), wherein the turbine (14) has a turbine wheel inlet diameter (D τ ) and a true length (S ER ) of a turbine wheel leading edge (6), characterized in that the true length (S ER ) of the turbine wheel leading edge
(6) zu dem Turbinenradeintrittsdurchmesser (Dτ) der Turbine (14) ein Verhältnis SD gemäß der Beziehung g(6) to the turbine wheel inlet diameter ( Dτ ) of the turbine (14) a ratio SD according to the relationship g
SD = -5^- aufweist und Dτ SD = - 5 ^ - and D τ
SD größer ist als 0,25 und die wahre Länge (SER) der Turbinenradeintrittskante (6) mit der Schaufelhöhe (hLe) der Leitschaufei des Leitgitters (7) oder der Düsenhöhe (hLe) der freien Ringdüse ein Verhältnis Sh gemäß der Beziehung g Sh = -^- aufweist undSD is larger than 0.25, and the true length (S ER ) of the turbine wheel leading edge (6) having the blade height (h Le ) of the guide rail of the guide rail (7) or the nozzle height (h Le ) of the free ring nozzle is a ratio Sh according to the relationship g Sh = - ^ - has and
Sh größer ist als 2,0. Abgasturbolader für eine Brennkraftmaschine nach AnspruchSh is greater than 2.0. Exhaust gas turbocharger for an internal combustion engine according to claim
1, dadurch gekennzeichnet, dass ein Durchmesser (D8) der Turbinenradrückwand (5) des Turbinenrades (1) mit dem Turbinenradeintrittsdurchmesser (Dτ) ein Verhältnis DD gemäß der Beziehung1, characterized in that a diameter (D 8 ) of the turbine rear wall (5) of the turbine wheel (1) with the turbine wheel inlet diameter (D τ ) a ratio DD according to the relationship
Ds D s
DD = -s- Dτ bildet und DD in folgendem Wertebereich liegt: 0,6 < DD < 0,95DD = -s- D τ forms and DD lies in the following value range: 0.6 <DD <0.95
Abgasturbolader für eine Brennkraftmaschine nach AnspruchExhaust gas turbocharger for an internal combustion engine according to claim
1 oder 2, dadurch gekennzeichnet, dass im Bremsbetrieb bei maximaler Bremsleistung der1 or 2, characterized in that in braking mode at maximum braking power of
Brennkraftmaschine ein freier Strömungsquerschnitt (Aτ) , welcher sich in einem Übergang von einem Spiralkanal (15) der Turbine (14) auf das Turbinenrad (1) befindet, derInternal combustion engine, a free flow cross-section (A τ ), which is located in a transition from a spiral channel (15) of the turbine (14) on the turbine wheel (1), the
Turbinenradeintrittsdurchmesser (Dτ) und ein HubvolumenTurbine wheel inlet diameter (D τ ) and a stroke volume
(V11) der Brennkraftmaschine in folgender Beziehung zueinander stehen und einen Turbobremsfaktor TBF gemäß der Beziehung(V 11 ) of the internal combustion engine in the following relationship to each other and a turbo braking factor TBF according to the relationship
TBF = Aτ • -^TBF = A τ • - ^
bilden, wobei der Turbobremsfaktor TBF kleiner als 0,006 ist. form, wherein the turbobar factor TBF is less than 0.006.
PCT/EP2005/008635 2004-08-11 2005-08-09 Exhaust turbocharger for an internal combustion engine WO2006018189A1 (en)

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JP2012500357A (en) * 2008-08-21 2012-01-05 ダイムラー・アクチェンゲゼルシャフト Exhaust turbocharger for automobile internal combustion engine
WO2015119828A1 (en) * 2014-02-04 2015-08-13 Borgwarner Inc. Heat shield for mixed flow turbine wheel turbochargers
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