EP0119323A1 - Exhaust gas turbo charger for internal-combustion engines - Google Patents

Exhaust gas turbo charger for internal-combustion engines Download PDF

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Publication number
EP0119323A1
EP0119323A1 EP83113132A EP83113132A EP0119323A1 EP 0119323 A1 EP0119323 A1 EP 0119323A1 EP 83113132 A EP83113132 A EP 83113132A EP 83113132 A EP83113132 A EP 83113132A EP 0119323 A1 EP0119323 A1 EP 0119323A1
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EP
European Patent Office
Prior art keywords
exhaust gas
gas turbocharger
radially outer
outer spiral
turbocharger according
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.)
Granted
Application number
EP83113132A
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German (de)
French (fr)
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EP0119323B1 (en
Inventor
Wilfried Ing. Schneider (Grad.)
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Kloeckner Humboldt Deutz AG
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Kloeckner Humboldt Deutz AG
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Priority to AT83113132T priority Critical patent/ATE20120T1/en
Publication of EP0119323A1 publication Critical patent/EP0119323A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • F01D17/146—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by throttling the volute inlet of radial machines or engines

Definitions

  • the invention relates to an exhaust gas turbocharger for internal combustion engines with a turbine housing surrounding a turbine impeller, which is provided with an inlet and an outlet for the exhaust gases of the internal combustion engine and arranged on the inlet side essentially concentrically to the turbine impeller and having a radially inner spiral and at least one radially outer spiral. wherein the radially inner and the radially outer spiral form a common partition and the exhaust gas inlet cross section of the turbine housing can be changed by means of a control member.
  • Exhaust gas turbochargers of this type can be adapted to different operating ranges of the internal combustion engine, for example part-load or full-load operation, during operation by means of a change in the exhaust-gas inlet cross-section brought about by the control member and thus by influencing the exhaust-gas speed in the turbine housing.
  • the control member is preferably actuated as a function of the boost pressure or the speed of the internal combustion engine via suitable actuators.
  • the invention has for its object to improve an exhaust gas turbocharger for internal combustion engines of the type mentioned in such a way that effective structuring of the exhaust gas turbocharger to different operating areas of the internal combustion engine is possible with structurally simple means while largely avoiding the loss-intensive partial loading of the turbine impeller during operation.
  • the internal and the outer spiral are in flow connection through opening cross sections provided in the partition, arranged one behind the other in the flow direction of the exhaust gas, and extend essentially over the entire peripheral region of the turbine impeller.
  • the inventive design of the exhaust gas turbocharger makes it possible in an advantageous manner, regardless of the position of the control member and thus irrespective of the operating range of the internal combustion engine to apply the entire circumferential area of the turbine wheel evenly, the exhaust gas flowing through the radially outer spiral being assigned to the entire circumferential area of the turbine wheel even with the maximum released exhaust gas cross section, since on the one hand a partial volume flow emerges through the opening cross sections and the turbine wheel is acted upon directly and, on the other hand, the respectively emerging partial flow of the outer spiral also influences the flow of the radially inner spiral in the sense of a change in the inflow angle on the turbine impeller.
  • the opening cross sections are preferably provided in the flow direction of the exhaust gas with the same angular distance from one another in relation to the turbine impeller axis.
  • the partition wall can be designed according to fluidic and advantageous manufacturing aspects.
  • the partition consists of several individual wall segments, which are arranged radially offset in the flow direction of the exhaust gas to form the opening cross sections, and wherein the individual wall segments are preferably arranged such that a constant flow cross section is present between two opening cross sections arranged one behind the other.
  • the flow cross section of the radially outer spiral decreases in stages, the respective stage cross sections preferably being adapted to the respective branch flow rates in the sense of a largely constant flow velocity.
  • the turbine impeller is 1 and 2 denotes the turbine housing, which is provided with an inlet 3 and an outlet 4, which - not shown in more detail - can be connected to the exhaust pipe of an internal combustion engine.
  • the exhaust gas turbocharger further comprises a compressor 5 arranged coaxially to the turbine impeller 1, which, however, is of no particular importance with regard to the present invention.
  • the turbine housing 2 has a spiral 6, which is located radially on the inside of the turbine impeller 1, and a radially outer spiral 7, each of which adjoins the inlet 3.
  • the radially outer spiral 7 is controlled by a control element which is designed as a flap wing 8 in the exemplary embodiment according to FIG. 1 and as a rotary slide valve 15 in the exemplary embodiment according to FIG. 3.
  • the flap wing 8 according to FIG. 1 can be pivoted about a center of gravity axis 10 parallel to the turbine impeller axis 9.
  • the radially inner spiral 6 and the radially outer spiral 7 have a common partition 11, which consists of several individual wall segments 11a, 11b, 11c, 11d.
  • the E inzelwandsegmente lla to lld of the exhaust gas is in the flow direction 12 configured and arranged, the radially inner spiral 6 and the radially outer coil 7 by opening cross-sections 13a, 13b that 13c and 13d a urbinenlaufradachse to T 9-related equal angular distance from one another have, are in flow connection.
  • the flow cross-section of the radially outer spiral 7 increases in the flow direction 12 from the exhaust gas, wherein in each case is constant between two adjacent opening cross-sections of the flow cross-section of the radially äu- ß ere spiral.
  • the radially inner spiral 6 and the radially outer spiral 7 extend essentially over the entire circumferential area of the turbine impeller 1, so that uniform application of the entire circumferential area of the turbine impeller 1 is possible in all operating areas of the internal combustion engine.
  • the openings 13a to 13d when the control member 8, 15 is closed, cause only a slight disturbance in the amount of exhaust gas flowing through the radially inner spiral 6, so that the turbine impeller 1 is subjected to an essentially constant inflow angle distributed over the circumference.
  • a continuous enlargement of the inlet cross-section 3 and thus a continuous release of the flow cross-section of the radially outer spiral 7 in order to adapt the exhaust gas turbocharger characteristic to higher engine speeds results in a partial exhaust gas flow from the radially outer spiral 7 into the radial direction through the openings 13a to 13d internal spiral 6 arrives, the flow velocity of the exhaust gas in the radially outer spiral 7 remains approximately constant due to the cross-sectional constrictions, so that the flow in the radially inner spiral 6 is influenced in the sense of a change in the inflow angle of the turbine impeller 1, so that the respective Partial exhaust gas flow contributes to the uniform application of the turbine impeller 1 over the entire circumferential area in an advantageous manner.
  • FIG. 1 The partial longitudinal section along the section lines II-II in Fig. 1 illustrates the exhaust gas turbocharger designed according to the invention, wherein it is also indicated as possible according to the invention that the spirals 6 and 7 through a wall 14 extending in a plane perpendicular to the turbine impeller axis 9 in two channels can be subdivided, which is particularly important in multi-cylinder reciprocating internal combustion engines with shock charging.
  • the control member for changing the cross section of the inlet 3 is designed as a rotary valve 15.
  • a rotary valve has the advantage that on the one hand the adjusting forces of the control member can be kept low due to the minimized flow resistance and on the other hand influences of the control member on the inlet flow, e.g. B. swirls, etc., are significantly reduced. This can be of advantageous importance in the exhaust gas turbocharger designed according to the invention.

Abstract

A turbocharger for an internal combustion engine has a turbine casing including an inlet opening from which radially internally and radially external spiral paths extend. These spiral paths have a common partition, and the exhaust gas inlet cross-section of the turbine casing can be varied by a control element for the purpose of adapting the characteristic curve of the turbocharger to different operating ranges of the internal combustion engine. And, the spiral paths are in hydrodynamic communication through orifice areas provided in the partition, with such orifice areas being spaced an equal distance from one another in the direction of flow of the exhaust gas, and the spiral paths extend substantially over the entire peripheral area of the turbine wheel.

Description

Die Erfindung bezieht sich auf einen Abgasturbolader für Brennkraftmaschinen mit einem ein Turbinenlaufrad umgebendes Turbinengehäuse, das mit einem Einlaß und einem Auslaß für die Abgase der Brennkraftmaschine versehen ist und einlaßseitig im wesentlichen konzentrisch zum Turbinenlaufrad angeordnet eine radial innenliegende Spirale und zumindest eine radial äußere Spirale aufweist, wobei die radial innenliegende und die radial äußere Spirale eine gemeinsame Trennwand bilden und der Abgaseinlaßquerschnitt des Turbinengehäuses mittels eines Steuerorgans veränderbar ist.The invention relates to an exhaust gas turbocharger for internal combustion engines with a turbine housing surrounding a turbine impeller, which is provided with an inlet and an outlet for the exhaust gases of the internal combustion engine and arranged on the inlet side essentially concentrically to the turbine impeller and having a radially inner spiral and at least one radially outer spiral. wherein the radially inner and the radially outer spiral form a common partition and the exhaust gas inlet cross section of the turbine housing can be changed by means of a control member.

Abgasturbolader dieser Bauart können während des Betriebes durch eine mittels des Steuerorgans bewirkte Veränderung des Abgaseinlaßquerschnittes und somit durch eine Beeinflussung der Abgasgeschwindigkeit im Turbinengehäuse an unterschiedliche Betriebsbereiche der Brennkraftmaschine, beispielsweise Teillast- oder Vollastbetrieb, angepaßt werden. Hierbei wird das Steuerorgan bevorzugt in Abhängigkeit des Ladedruckes oder der Drehzahl der Brennkraftmaschine über geeignete Stellglieder betätigt.Exhaust gas turbochargers of this type can be adapted to different operating ranges of the internal combustion engine, for example part-load or full-load operation, during operation by means of a change in the exhaust-gas inlet cross-section brought about by the control member and thus by influencing the exhaust-gas speed in the turbine housing. In this case, the control member is preferably actuated as a function of the boost pressure or the speed of the internal combustion engine via suitable actuators.

Es ist aus der DE-OS 31 05 179 ein Abgasturbolader für Brennkraftmaschinen der gattungsgemäßen Bauart bekannt, bei dem insgesamt drei radial außerhalb der innenliegenden Spirale angeordnete Spiralen vorgesehen sind, die jeweils durch getrennte Steuerorgane einzeln freigebbar bzw. absperrbar sind und jeweils unterschiedliche Umfangsbereiche des Turbinenlaufrades beaufschlagen. Als besonders nachteilig ist neben dem erheblichen Bauaufwand bei diesem Abgasturbolader die bei unterschiedlichen Drehzahlen der Brennkraftmaschine bzw. bei unterschiedlichem Ladedruck jeweils stattfindende verlustintensive Teilbeaufschlagung des Turbinenrades anzusehen. Weiterhin ist der aufzubringende Regelaufwand für die drei getrennten Steuerorgane zur Angleichung der Abgasturboladercharakteristik an die jeweiligen Betriebsbereiche der Brennkraftmaschine erheblich.It is known from DE-OS 31 05 179 an exhaust gas turbocharger for internal combustion engines of the generic type, in which a total of three radially outside the internal spiral spirals are provided, each of which can be individually released or blocked by separate control members and each have different peripheral areas of the turbine impeller act upon. In addition to the considerable amount of construction work involved in this exhaust gas turbocharger, the loss-intensive partial loading of the turbine wheel which occurs at different engine speeds or at different boost pressure is particularly disadvantageous. Furthermore, the control effort to be applied for the three separate control elements for matching the exhaust gas turbocharger characteristics to the respective operating areas of the internal combustion engine is considerable.

Der Erfindung liegt die Aufgabe zugrunde, einen Abgasturbolader für Brennkraftmaschinen der eingangs genannten Bauart dahingehend zu verbessern, daß mit baulich einfachen Mitteln unter einer weitgehenden Vermeidung der verlustintensiven Teilbeaufschlagung des Turbinenlaufrades während des Betriebes eine wirksame Angleichung des Abgasturboladers an unterschiedliche Betriebsbereiche der Brennkraftmaschine möglich ist.The invention has for its object to improve an exhaust gas turbocharger for internal combustion engines of the type mentioned in such a way that effective structuring of the exhaust gas turbocharger to different operating areas of the internal combustion engine is possible with structurally simple means while largely avoiding the loss-intensive partial loading of the turbine impeller during operation.

Diese Aufgabe wird erfindungsgemäß dadurch gelöst, daß die innenliegende und die äußere Spirale durch in der Trennwand vorgesehene, in Strömungsrichtung des Abgases hintereinander angeordnete öffnungsquerschnitte in Strömungsverbindung stehen und sich im wesentlichen über den gesamten Umfangsbereich des Turbinenlaufrades erstrecken. Durch die erfindungsgemäße Gestaltung des Abgasturboladers ist es in vorteilhafter Weise möglich, unabhängig von der Stellung des Steuerorgans und somit unabhängig vom Betriebsbereich der Brennkraftmaschine jeweils den gesamten Umfangbereich des Turbinenrades gleichmäßig zu beaufschlagen, wobei selbst bei maximal freigegebenem Abgasquerschnitt das durch die radial äußere Spirale strömende Abgas dem gesamten Umfangsbereich des Turbinenrades zugeordnet ist, da einerseits jeweils ein Teilmengenstrom durch die öffnungsquerschnitte austritt und das Turbinenrad direkt beaufschlagt und andererseits der jeweils austretende Teilmengenstrom der äußeren Spirale auch die Strömung der radial innenliegenden Spirale im Sinne einer Veränderung des Anströmwinkels am Turbinenlaufrad beeinflußt. Hiermit ist mit baulich einfachen Mitteln und mit einem minimierten Regelaufwand über den gesamten Betriebsberei-ch der Brennkraftmaschine eine hinsichtlich des Gesamtwirkungsgrades optimierte Angleichung der Abgasturboladercharakteristik an unterschiedliche Betriebsbereiche der Brennkraftmaschine möglich.This object is achieved in that the internal and the outer spiral are in flow connection through opening cross sections provided in the partition, arranged one behind the other in the flow direction of the exhaust gas, and extend essentially over the entire peripheral region of the turbine impeller. The inventive design of the exhaust gas turbocharger makes it possible in an advantageous manner, regardless of the position of the control member and thus irrespective of the operating range of the internal combustion engine to apply the entire circumferential area of the turbine wheel evenly, the exhaust gas flowing through the radially outer spiral being assigned to the entire circumferential area of the turbine wheel even with the maximum released exhaust gas cross section, since on the one hand a partial volume flow emerges through the opening cross sections and the turbine wheel is acted upon directly and, on the other hand, the respectively emerging partial flow of the outer spiral also influences the flow of the radially inner spiral in the sense of a change in the inflow angle on the turbine impeller. With structurally simple means and with a minimal control effort over the entire operating range of the internal combustion engine, an adaptation of the exhaust gas turbocharger characteristic to different operating ranges of the internal combustion engine with regard to the overall efficiency is possible.

Bevorzugt sind die öffnungsquerschnitte hierbei in Strömungsrichtung des Abgases mit einem auf die Turbinenlaufradachse bezogenen gleichen Winkelabstand voneinander vorgesehen.The opening cross sections are preferably provided in the flow direction of the exhaust gas with the same angular distance from one another in relation to the turbine impeller axis.

Um insbesondere die Strömungsgeschwindigkeit des Abgases in der äußeren Spirale trotz der jeweils durch die öffnungsquerschnitte abgezweigten Teilmengenströme konstant zu halten, sieht eine Weiterbildung der Erfindung vor, daß der Strömungsquerschnitt der radial äußeren Spirale in Strömungsrichtung des Abgases abnimmt.In particular, in order to keep the flow velocity of the exhaust gas in the outer spiral constant despite the partial flow rates branched off by the opening cross sections, a further development of the invention provides that the flow cross section of the radially outer spiral decreases in the flow direction of the exhaust gas.

Die Gestaltung der Trennwand kann erfindungsgemäß nach strömungstechnischen und vorteilhaften fertigungstechnischen Gesichtspunkten erfolgen. So ist es beispielsweise erfindungsgemäß möglich, daß die Trennwand aus mehreren Einzelwandsegmenten besteht, die in Strömungsrichtung des Abgases unter Bildung der öffnungsquerschnitte radial versetzt angeordnet sind, und wobei bevorzugt die Einzelwandsegmente derart angeordnet sind, daß zwischen zwei hintereinander angeordneten öffnungsquerschnitten jeweils ein konstanter Strömungsquerschnitt vorhanden ist. Hierbei nimmt der Strömungsquerschnitt der radial äußeren Spirale in Stufen ab, wobei die jeweiligen Stufenquerschnitte bevorzugt an die jeweils abgezweigten Teilmengenströmen im Sinne einer weitgehend gleichbleibenden Strömungsgeschwindigkeit angepaßt sind.According to the invention, the partition wall can be designed according to fluidic and advantageous manufacturing aspects. For example, it is possible according to the invention that the partition consists of several individual wall segments, which are arranged radially offset in the flow direction of the exhaust gas to form the opening cross sections, and wherein the individual wall segments are preferably arranged such that a constant flow cross section is present between two opening cross sections arranged one behind the other. Here, the flow cross section of the radially outer spiral decreases in stages, the respective stage cross sections preferably being adapted to the respective branch flow rates in the sense of a largely constant flow velocity.

Weitere vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung sind in den Unteransprüchen angegeben.Further advantageous refinements and developments of the invention are specified in the subclaims.

Zur weiteren Erläuterung der Erfindung wird auf die Zeichnungen verwiesen, in denen jeweils Ausführungsbeispiele der Erfindung dargestellt sind. Es zeigen:

  • Fig. 1 einen Querschnitt durch ein erstes Ausführungsbeispiel eines erfindungsgemäß gestalteten Abgasturboladers;
  • Fig. 2 einen Teilschnitt nach der Schnittlinie II-II in Fig. 1 des erfindungsgemäß gestalteten Abgasturboladers;
  • Fig. 3 einen Querschnitt durch ein weiteres Ausführungsbeispiel eines erfindungsgemäß gestalteten Abgasturboladers.
To further explain the invention, reference is made to the drawings, in which exemplary embodiments of the invention are shown. Show it:
  • 1 shows a cross section through a first embodiment of an exhaust gas turbocharger designed according to the invention;
  • FIG. 2 shows a partial section along section line II-II in FIG. 1 of the exhaust gas turbocharger designed according to the invention;
  • Fig. 3 shows a cross section through a further embodiment of an exhaust gas turbocharger designed according to the invention.

In den in den Fig. l bis 3 dargestellten Ausführungsbeispielen des erfindungsgemäßen Abgasturboladers, wobei grundsätzlich gleichwirkende Teile mit gleichen Bezugsziffern versehen sind, ist mit 1 das Turbinenlaufrad und mit 2 das Turbinengehäuse bezeichnet, das mit einem Einlaß 3 und einem Auslaß 4 versehen ist, die - nicht näher dargestellt - an die Abgasleitung einer Brennkraftmaschine anschließbar sind. Der Abgasturbolader umfaßt weiterhin einen koaxial zum Turbinenlaufrad 1 angeordneten Verdichter 5, dem jedoch im Hinblick auf die vorliegende Erfindung keine besondere Bedeutung zukommt. Das Turbinengehäuse 2 weist eine zum Turbinenlaufrad 1 radial innenliegende Spirale 6 und eine radial äußere Spirale 7 auf, die sich jeweils an den Einlaß 3 anschließen. Die radial äußere Spirale 7 wird von einem Steuerorgan beherrscht, das in dem Ausführungsbeispiel nach Fig. 1 als Klappenflügel 8 und in dem Ausführungsbeispiel nach Fig. 3 als Drehschieber 15 ausgebildet ist. Zur Veränderung des Einlaßquerschnittes ist der Klappenflügel 8 nach Fig. 1 um eine zur Turbinenlaufradachse 9 parallele Schwerpunktachse 10 schwenkbar. Die radial innenliegende Spirale 6 und die radial äußere Spirale 7 haben eine gemeinsame Trennwand 11, die aus mehreren Einzelwandsegmenten lla, llb, llc, lld besteht. Die Einzelwandsegmente lla bis lld sind in Strömungsrichtung 12 des Abgases derart gestaltet und angeordnet, daß die radial innenliegende Spirale 6 und die radial äußere Spirale 7 durch öffnungsquerschnitte 13a, 13b, 13c und 13d, die einen auf die Turbinenlaufradachse 9 bezogenen gleichen Winkelabstand voneinander aufweisen, in Strömungsverbindung stehen. Der Strömungsquerschnitt der radial äußeren Spirale 7 nimmt in Strömungsrichtung 12 des Abgases ab, wobei jeweils zwischen zwei benachbarten öffnungsquerschnitten der Strömungsquerschnitt der radial äu- ßere Spirale 7 konstant ist. Die radial innenliegende Spirale 6 und die radial äußere Spirale 7 erstrecken sich im wesentlichen über den gesamten Umfangsbereich des Turbinenlaufrades 1, so daß eine gleichmäßige Beaufschlagung des gesamten Umfangsbereiches des Turbinenlaufrades 1 in allen Betriebsbereichen der Brennkraftmaschine möglich ist. Während des Betriebes des Abgasturboladers bewirken die Öffnungen 13a bis 13d bei geschlossenem Steuerorgan 8, 15 nur eine geringe Störung der durch die radial innenliegende Spirale 6 strömende Abgasmenge, so daß das Turbinenlaufrad 1 gleichmäßig über den Umfang verteilt mit einem im wesentlichen konstanten Anströmwinkel beaufschlagt wird. Eine kontinuierliche Vergrößerung des Einlaßquerschnittes 3 und somit eine kontinuierliche Freigabe des Strömungsquerschnittes der radial äußere Spirale 7 zur Angleichung der Abgasturboladercharakteristik an höhere Drehzahlen der Brennkraftmaschine hat zur Folge, daß durch die Öffnungen 13a bis 13d jeweils ein Teilabgasstrom von der radial äußere Spirale 7 in die radial innenliegende Spirale 6 gelangt, wobei die Strömungsgeschwindigkeit des Abgases in der radial äußere Spirale 7 durch die Querschnittsverengungen jeweils annähernd konstant bleibt, so daß die Strömung in der radial innenliegenden Spirale 6 im Sinne einer Veränderung des Anströmwinkels des Turbinenlaufrades 1 beeinflußt wird, so daß der jeweilige Teilabgasstrom zur gleichmäßigen Beaufschlagung des Turbinenlaufrades 1 über den gesamten Umfangsbereich in vorteilhafter Weise beiträgt.In the exemplary embodiments of the exhaust gas turbocharger according to the invention shown in FIGS. 1 to 3, parts with basically the same function being provided with the same reference numbers, the turbine impeller is 1 and 2 denotes the turbine housing, which is provided with an inlet 3 and an outlet 4, which - not shown in more detail - can be connected to the exhaust pipe of an internal combustion engine. The exhaust gas turbocharger further comprises a compressor 5 arranged coaxially to the turbine impeller 1, which, however, is of no particular importance with regard to the present invention. The turbine housing 2 has a spiral 6, which is located radially on the inside of the turbine impeller 1, and a radially outer spiral 7, each of which adjoins the inlet 3. The radially outer spiral 7 is controlled by a control element which is designed as a flap wing 8 in the exemplary embodiment according to FIG. 1 and as a rotary slide valve 15 in the exemplary embodiment according to FIG. 3. To change the inlet cross section, the flap wing 8 according to FIG. 1 can be pivoted about a center of gravity axis 10 parallel to the turbine impeller axis 9. The radially inner spiral 6 and the radially outer spiral 7 have a common partition 11, which consists of several individual wall segments 11a, 11b, 11c, 11d. The E inzelwandsegmente lla to lld of the exhaust gas is in the flow direction 12 configured and arranged, the radially inner spiral 6 and the radially outer coil 7 by opening cross-sections 13a, 13b that 13c and 13d a urbinenlaufradachse to T 9-related equal angular distance from one another have, are in flow connection. The flow cross-section of the radially outer spiral 7 increases in the flow direction 12 from the exhaust gas, wherein in each case is constant between two adjacent opening cross-sections of the flow cross-section of the radially äu- ß ere spiral. 7 The radially inner spiral 6 and the radially outer spiral 7 extend essentially over the entire circumferential area of the turbine impeller 1, so that uniform application of the entire circumferential area of the turbine impeller 1 is possible in all operating areas of the internal combustion engine. During operation of the exhaust gas turbocharger, the openings 13a to 13d, when the control member 8, 15 is closed, cause only a slight disturbance in the amount of exhaust gas flowing through the radially inner spiral 6, so that the turbine impeller 1 is subjected to an essentially constant inflow angle distributed over the circumference. A continuous enlargement of the inlet cross-section 3 and thus a continuous release of the flow cross-section of the radially outer spiral 7 in order to adapt the exhaust gas turbocharger characteristic to higher engine speeds results in a partial exhaust gas flow from the radially outer spiral 7 into the radial direction through the openings 13a to 13d internal spiral 6 arrives, the flow velocity of the exhaust gas in the radially outer spiral 7 remains approximately constant due to the cross-sectional constrictions, so that the flow in the radially inner spiral 6 is influenced in the sense of a change in the inflow angle of the turbine impeller 1, so that the respective Partial exhaust gas flow contributes to the uniform application of the turbine impeller 1 over the entire circumferential area in an advantageous manner.

Der Teillängsschnitt nach den Schnittlinien II-II in Fig. 1 verdeutlicht den erfindungsgemäß gestalteten Abgasturbolader, wobei es als erfindungsgemäß ebenfalls möglich angedeutet ist, daß die Spiralen 6 und 7 durch eine sich in einer senkrechten Ebene zur Turbinenlaufradachse 9 erstreckende Wand 14 in jeweils zwei Kanäle unterteilbar sind, was insbesondere bei mehrzylindrigen Hubkolbenbrennkraftmaschinen mit Stoßaufladung von Bedeutung ist.The partial longitudinal section along the section lines II-II in Fig. 1 illustrates the exhaust gas turbocharger designed according to the invention, wherein it is also indicated as possible according to the invention that the spirals 6 and 7 through a wall 14 extending in a plane perpendicular to the turbine impeller axis 9 in two channels can be subdivided, which is particularly important in multi-cylinder reciprocating internal combustion engines with shock charging.

In Fig. 3 ist das Steuerorgan zur Veränderung des Querschnittes des Einlasses 3 als Drehschieber 15 ausgebildet. Ein Drehschieber beinhaltet den Vorteil, daß einerseits die Verstellkräfte des Steuerorgans aufgrund der minimierten Strömungswiderstände gering gehalten werden können und andererseits Einflüsse des Steuerorgans auf die Einlaßströmung, z. B. Verwirbelungen etc., wesentlich verringert sind. Dieses kann bei dem erfindungsgemäß gestalteten Abgasturbolader von vorteilhafter Bedeutung sein.In Fig. 3, the control member for changing the cross section of the inlet 3 is designed as a rotary valve 15. A rotary valve has the advantage that on the one hand the adjusting forces of the control member can be kept low due to the minimized flow resistance and on the other hand influences of the control member on the inlet flow, e.g. B. swirls, etc., are significantly reduced. This can be of advantageous importance in the exhaust gas turbocharger designed according to the invention.

Claims (8)

1. Abgasturbolader für Brennkraftmaschinen mit einem ein Turbinenlaufrad (1) umgebendes Turbinengehäuse (2), das mit einem Einlaß (3) und einem Auslaß (4) für die Abgase der Brennkraftmaschine versehen ist und einlaßseitig im wesentlichen konzentrisch zum Turbinenlaufrad (1) angeordnet eine radial innenliegende Spirale (6) und zumindest eine radial äußere Spirale (7) aufweist, wobei die radial innenliegende und die radial äußere Spirale (6, 7) eine gemeinsame Trennwand (11) haben und der Abgaseinlaßquerschnitt des Turbinengehäuses (2) mittels eines Steuerorgans (8, 15) veränderbar ist,
dadurch gekennzeichnet, daß die innenliegende und die äußere Spirale (6, 7) durch in der Trennwand (11) vorgesehene, in Strömungsrichtung (12) des Abgases hintereinander angeordnete öffnungsquerschnitte (13a, 13b, 13c, 13d) in Strömungsverbindung stehen und sich im wesentlichen über den gesamten Umfangsbereich des Turbinenlaufrades (1) erstrecken.1. Exhaust gas turbocharger for internal combustion engines with a turbine impeller (1) surrounding the turbine housing (2), which is provided with an inlet (3) and an outlet (4) for the exhaust gases of the internal combustion engine and arranged on the inlet side essentially concentrically to the turbine impeller (1) has a radially inner spiral (6) and at least one radially outer spiral (7), the radially inner and the radially outer spiral (6, 7) having a common partition (11) and the exhaust gas inlet cross section of the turbine housing (2) by means of a control member ( 8, 15) is changeable,
characterized in that the inner and outer spirals (6, 7) are in flow connection and are essentially connected by opening cross sections (13a, 13b, 13c, 13d) provided in the partition (11) and arranged one behind the other in the flow direction (12) of the exhaust gas Extend over the entire circumferential area of the turbine impeller (1). 2. Abgasturbolader nach Anspruch 1, dadurch gekennzeichnet, daß die öffnungsquerschnitte (13a - 13d) in Strömungsrichtung (12) des Abgases mit einem auf die Turbinenlaufradachse (9) bezogenen gleichen Winkelabstand voneinander in der Trennwand (11) vorgesehen sind.2. Exhaust gas turbocharger according to claim 1, characterized in that the opening cross-sections (13a - 13d) are provided in the flow direction (12) of the exhaust gas with an equal angular distance from the turbine impeller axis (9) from one another in the partition (11). 3. Abgasturbolader nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß der Strömungsquerschnitt der radial äußeren Spirale (7) in Strömungsrichtung (12) des Abgases abnimmt.3. Exhaust gas turbocharger according to one of claims 1 or 2, characterized in that the flow cross section of the radially outer spiral (7) decreases in the flow direction (12) of the exhaust gas. 4. Abgasturbolader nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß die Trennwand (11) aus mehreren Einzelwandsegmenten (lla, llb, llc, lld) besteht, die in Strömungsrichtung (12) des Abgases unter Bildung der öffnungsquerschnitte (13a - 13d) radial versetzt angeordnet sind.4. Exhaust gas turbocharger according to one of the preceding claims, characterized in that the partition (11) consists of several individual wall segments (lla, llb, llc, lld) which radially in the flow direction (12) of the exhaust gas to form the opening cross sections (13a - 13d) are staggered. 5. Abgasturbolader nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß die radial äußere Spirale (7) jeweils zwischen zwei hintereinander angeordneten öffnungsquerschnitten (13a - 13d) einen konstanten Strömungsquerschnitt aufweist.5. Exhaust gas turbocharger according to one of the preceding claims, characterized in that the radially outer spiral (7) each between two successively arranged opening cross sections (13a - 13d) has a constant flow cross section. 6. Abgasturbolader nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß als Steuerorgan eine vorzugsweise um eine Schwerpunktsachse (10) drehbare Klappe (8) vorgesehen ist, die die radial äußere Spirale (7) beherrscht.6. Exhaust gas turbocharger according to one of claims 1 to 5, characterized in that the control member is preferably a rotatable about a center of gravity axis (10) flap (8) is provided which controls the radially outer spiral (7). 7. Abgasturbolader nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß als Steuerorgan ein Drehschieber (15) vorgesehen ist, der die radial äußere Spirale (7) beherrscht.7. Exhaust gas turbocharger according to one of claims 1 to 5, characterized in that a rotary slide valve (15) is provided as a control member, which controls the radially outer spiral (7). 8. Abgasturbolader nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß die Spiralen (6, 7) durch zumindest eine sich in einer senkrechten Ebene zur Turbinenlaufradachse (9) erstreckende Wand (14) unterteilbar sind.8. Exhaust gas turbocharger according to one of the preceding claims, characterized in that the spirals (6, 7) by at least one in a vertical plane to the turbine wheel axis (9) extending wall (14) can be divided.
EP83113132A 1983-01-24 1983-12-27 Exhaust gas turbo charger for internal-combustion engines Expired EP0119323B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT83113132T ATE20120T1 (en) 1983-01-24 1983-12-27 EXHAUST GAS TURBOCHARGER FOR COMBUSTION ENGINES.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3302186 1983-01-24
DE19833302186 DE3302186A1 (en) 1983-01-24 1983-01-24 EXHAUST TURBOCHARGER FOR INTERNAL COMBUSTION ENGINES

Publications (2)

Publication Number Publication Date
EP0119323A1 true EP0119323A1 (en) 1984-09-26
EP0119323B1 EP0119323B1 (en) 1986-05-28

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP83113132A Expired EP0119323B1 (en) 1983-01-24 1983-12-27 Exhaust gas turbo charger for internal-combustion engines

Country Status (5)

Country Link
US (1) US4565068A (en)
EP (1) EP0119323B1 (en)
JP (1) JPS59138727A (en)
AT (1) ATE20120T1 (en)
DE (2) DE3302186A1 (en)

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EP0212834A2 (en) * 1985-07-17 1987-03-04 Geoffrey Light Wilde Variable inlet for a radial turbine
EP0208248B1 (en) * 1985-07-03 1989-05-03 Hitachi, Ltd. Internal combustion engine with variable-capacity turbocharger
DE19717559C2 (en) * 1996-04-25 2002-02-07 Aisin Seiki turbocharger
EP3819486A1 (en) * 2019-11-08 2021-05-12 Volkswagen Ag Turbocharger for high performance engine concepts

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EP3819486A1 (en) * 2019-11-08 2021-05-12 Volkswagen Ag Turbocharger for high performance engine concepts

Also Published As

Publication number Publication date
US4565068A (en) 1986-01-21
EP0119323B1 (en) 1986-05-28
JPS59138727A (en) 1984-08-09
DE3363831D1 (en) 1986-07-03
DE3302186A1 (en) 1984-07-26
ATE20120T1 (en) 1986-06-15

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