DE4312077C1 - Exhaust gas turbocharger for IC engine - has at least one turbine and compressor, turbine having inflow and outflow sides, turbine wheel, housing with spirally-shaped flow channel and variable guide blade crown - Google Patents

Exhaust gas turbocharger for IC engine - has at least one turbine and compressor, turbine having inflow and outflow sides, turbine wheel, housing with spirally-shaped flow channel and variable guide blade crown

Info

Publication number
DE4312077C1
DE4312077C1 DE4312077A DE4312077A DE4312077C1 DE 4312077 C1 DE4312077 C1 DE 4312077C1 DE 4312077 A DE4312077 A DE 4312077A DE 4312077 A DE4312077 A DE 4312077A DE 4312077 C1 DE4312077 C1 DE 4312077C1
Authority
DE
Germany
Prior art keywords
turbine
chamber
compressor
exhaust gas
gas turbocharger
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
DE4312077A
Other languages
German (de)
Inventor
Erwin Schmidt
Gerhard Dr Ing Fraenkle
Siegfried Dipl Ing Sumser
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mercedes Benz Group AG
Original Assignee
Daimler Benz AG
Mercedes Benz AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Daimler Benz AG, Mercedes Benz AG filed Critical Daimler Benz AG
Priority to DE4312077A priority Critical patent/DE4312077C1/en
Application granted granted Critical
Publication of DE4312077C1 publication Critical patent/DE4312077C1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/04—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
    • F02B37/10—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump at least one pump being alternatively or simultaneously driven by exhaust and other drive, e.g. by pressurised fluid from a reservoir or an engine-driven pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/16—Control of the pumps by bypassing charging air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • F02B37/183—Arrangements of bypass valves or actuators therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F02B39/005—Cooling of pump drives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/02—EGR systems specially adapted for supercharged engines
    • F02M26/04—EGR systems specially adapted for supercharged engines with a single turbocharger
    • F02M26/05—High pressure loops, i.e. wherein recirculated exhaust gas is taken out from the exhaust system upstream of the turbine and reintroduced into the intake system downstream of the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/02—EGR systems specially adapted for supercharged engines
    • F02M26/09—Constructional details, e.g. structural combinations of EGR systems and supercharger systems; Arrangement of the EGR and supercharger systems with respect to the engine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/13—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories
    • F02M26/14—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories in relation to the exhaust system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/13—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories
    • F02M26/36—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories with means for adding fluids other than exhaust gas to the recirculation passage; with reformers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B3/00—Engines characterised by air compression and subsequent fuel addition
    • F02B3/06—Engines characterised by air compression and subsequent fuel addition with compression ignition
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Landscapes

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

Abstract

The compressor has a pressure side and a suction side and from the compressor pressure side a conduit is guided in a chamber in the turbine housing separate from the spirally shaped flow channel. From the chamber a connecting conduit issues, which is connected to the inflow side (8) of the turbine (3) and the flow connection between the pressure side (14) of the compressor (4) and the inflow side (8) of the turbine (3) is regulatable with a part of the variable guide blade crown (11). At least one part of the chamber is a constituent of the variable guide blade crown (11). With an axially displaceable, variable guide blade crown (11) the chamber is ring-shaped and an opening of the hole issuing in the chamber is displaced to a mouth of the connecting conduit leading from the chamber to the inflow side (8) of the turbine (3). USE/ADVANTAGE - Exhaust gas turbocharger which is simple and cost-favourable to produce, with which cooling of turbine components is possible using charging air.

Description

Die Erfindung betrifft einen Abgasturbolader für eine aufgela­ dene Brennkraftmaschine gemäß dem Oberbegriff des Patentan­ spruchs 1.The invention relates to an exhaust gas turbocharger for a dene internal combustion engine according to the preamble of the patent saying 1.

Aus der DE-OS 33 22 436 ist bereits ein Abgasturbolader der gattungsgemäßen Art bekannt.From DE-OS 33 22 436 is already an exhaust gas turbocharger generic type known.

Der Abgasturbolader umfaßt eine Turbine und einen Verdichter, wobei die Turbine ein Turbinengehäuse besitzt, in dem ein Spi­ ralkanal ausgebildet ist, der an ein Turbinenrad mündet. Im Mündungsbereich des Spiralkanales ist ein variabler Leitschau­ felkranz angeordnet, der in einer Turbinengehäusewand gelagert und mit einer Verstellmechanik verstellbar ist, wobei die Tur­ binengehäusewand Bestandteil einer zwischen Verdichter und Turbine angeordneten Kammer ist. Der Verdichter umfaßt ein Verdichtergehäuse, in dem ein um ein Verdichterrad geführter Radialdiffusor und ein Spiralkanal ausgebildet ist. Von dem Spiralkanal des Verdichters führt eine Leitung in die Kammer, in die somit, zwecks Kühlung des Leitschaufelkranzes, vom Spi­ ralkanal abgezweigte Ladeluft leitbar ist. Die in der Kammer befindliche Ladeluft ist über eine Ausströmöffnung unter Umge­ hung des Turbinenrades in ein Abgassystem leitbar.The exhaust gas turbocharger comprises a turbine and a compressor, wherein the turbine has a turbine housing in which a spi ralkkanal is formed, which opens onto a turbine wheel. in the The mouth area of the spiral channel is a variable guide arranged rim ring, which is stored in a turbine housing wall and is adjustable with an adjustment mechanism, the door Bin housing wall part of a between compressor and Turbine arranged chamber is. The compressor includes a Compressor housing, in which a led around a compressor wheel Radial diffuser and a spiral channel is formed. Of the The compressor's spiral channel leads a line into the chamber, into which, for the purpose of cooling the guide vane ring, from the spi ralkanal branched charge air is conductive. The one in the chamber charge air is via an outflow opening under vice The turbine wheel can be conducted into an exhaust system.

Ferner ist aus der DE-OS 28 55 687 eine aufgeladene Brenn­ kraftmaschine mit Abgasrückführung bekannt, bei der zwischen der turbineneinströmseitigen Abgasleitung und der verdichterdruckseitigen Ladeluftleitung eine separate, ventil­ gesteuerte Verbindungsleitung angeordnet ist.Furthermore, DE-OS 28 55 687 is a charged burner Engine known with exhaust gas recirculation, in which between the exhaust gas line on the turbine inlet side and the  a separate valve on the compressor pressure side of the charge air line controlled connecting line is arranged.

Zum allgemeinen Hintergrund wird noch auf die Druckschriften DE-OS 32 18 156, DE-OS 34 20 015, DE-PS 34 43 324, DE-PS 35 04 465, EP 0 302 082 und EP 0 377 712 verwiesen.The general background is still on the publications DE-OS 32 18 156, DE-OS 34 20 015, DE-PS 34 43 324, DE-PS 35 04 465, EP 0 302 082 and EP 0 377 712.

Ein Nachteil gattungsgemäßer Abgasturbolader besteht darin, daß die von der Druckseite des Verdichters des Abgasturboladers abgezweigte Ladeluft lediglich zur Kühlung von Turbinenbautei­ len verwendet wird und die in der komprimierten Ladeluft ent­ haltene Energie nicht weiter genutzt wird.A disadvantage of generic exhaust gas turbochargers is that from the pressure side of the compressor of the exhaust gas turbocharger branched charge air only for cooling turbine components len is used and ent in the compressed charge air held energy is no longer used.

Bei bekannten aufgeladenen Brennkraftmaschinen mit Abgasrück­ führung ist ein wesentlicher Nachteil darin zu sehen, daß für die Abgasrückführung eine separate Verbindungsleitung zwischen Abgasleitung und Ladeluftleitung mit eigener Regeleinrichtung benötigt wird.In known supercharged internal combustion engines with exhaust gas return leadership is a major disadvantage in the fact that for the exhaust gas recirculation has a separate connection line between Exhaust pipe and charge air pipe with its own control device is needed.

Der Erfindung liegt daher die Aufgabe zugrunde, einen gattungs­ gemäßen Abgasturbolader baulich einfach und kostengünstig der­ art auszubilden, daß mit diesem sowohl eine Kühlung von Tur­ binenbauteilen durch die Ladeluft als auch eine Abgasrückfüh­ rung realisierbar ist.The invention is therefore based on the object, a genus modern exhaust gas turbocharger structurally simple and inexpensive art to train that with this both a cooling of door line components through the charge air as well as an exhaust gas recirculation tion is feasible.

Die Aufgabe ist erfindungsgemäß durch die im Kennzeichen des Hauptanspruches gegebenen Merkmale gelöst.The object of the invention is characterized by the Main claim given characteristics solved.

Ein Vorteil der erfindungsgemäßen Anordnung des Abgasturbola­ ders besteht darin, daß durch die Strömungsverbindung zwischen Druckseite des Verdichters und Einströmseite der Turbine sowohl eine Kühlung von Turbinenteilen mit Ladeluft als auch eine Ab­ gasrückführung mit der selben Anordnung einfach und kostengün­ stig realisierbar ist. An advantage of the arrangement of the exhaust gas turbola according to the invention ders is that through the flow connection between Pressure side of the compressor and inflow side of the turbine both a cooling of turbine parts with charge air as well as an Ab gas recirculation with the same arrangement simple and inexpensive is always feasible.  

Ein weiterer Vorteil der Erfindung ist darin zu sehen, daß durch die Zuführung der abgezweigten, komprimierten Ladeluft in die Turbine die Ladeluftenergie zu deren Antrieb mitgenutzt wird.Another advantage of the invention is that by supplying the branched, compressed charge air into the turbine uses the charge air energy to drive it becomes.

Des weiteren wird durch die Ableitung von Ladeluft von der Druckseite des Verdichters ein effektiver Schutz vor Verdich­ terpumpen, gerade im Betrieb der Brennkraftmaschine im Vollastbereich bei niederen Drehzahlen, erreicht.Furthermore, the discharge of charge air from the Pressure side of the compressor an effective protection against compression terpumpen, especially in the operation of the internal combustion engine in the Full load range at low speeds, reached.

Durch die Ausgestaltung der Erfindung nach Anspruch 2 und 3 wird eine Kühlung des thermisch besonders stark beanspruchten variablen Leitschaufelkranzes und gleichzeitig ein Freiblasen mindestens eines Teils des Verstellsystems von Rußpartikeln ermöglicht.By designing the invention according to claims 2 and 3 is a cooling of the thermally particularly stressed variable guide vane ring and at the same time blowing free at least part of the adjustment system of soot particles enables.

Weitere Ausgestaltungen und Vorteile der Erfindung gehen aus den übrigen Unteransprüchen und der Beschreibung hervor.Further configurations and advantages of the invention go out the other subclaims and the description.

In den Zeichnungen ist die Erfindung anhand einer Prinzip­ zeichnung und zweier Ausführungsbeispiele näher erläutert. Es zeigen:In the drawings, the invention is based on a principle drawing and two embodiments explained. It demonstrate:

Fig. 1 eine prinzipiell bekannte Schemazeichnung einer aufgeladenen Brennkraftmaschine mit einem erfin­ dungsgemäßen Abgasturbolader, Fig. 1 shows a known principle schematic diagram of a supercharged internal combustion engine having an exhaust gas turbocharger OF INVENTION to the invention,

Fig. 2 in einem ersten Ausführungsbeispiel einen Radi­ alschnitt einer Turbine des erfindungsgemäßen Abgasturboladers mit einer in einen spiralför­ migen Strömungskanal mündenden Verbindungslei­ tung, Fig. 2 in a first embodiment of a Radi alschnitt a turbine of the turbocharger according to the invention with an opening into a flow channel-shaped spiralför Verbindungslei tung,

Fig. 3 einen Meridianteilschnitt von Fig. 2, Fig. 3 is a meridian sectional part of Fig. 2,

Fig. 4 in einem zweiten Ausführungsbeispiel einen Ra­ dialschnitt der Turbine des erfindungsgemäßen Abgasturboladers analog zu Fig. 2, jedoch mit einer direkt an ein Turbinenrad mündenden Ver­ bindungsleitung und Fig. 4 in a second embodiment, a Ra dial section of the turbine of the exhaust gas turbocharger according to the invention analogous to FIG. 2, but with a connection pipe leading directly to a turbine wheel and

Fig. 5 einen Meridianteilschnitt von Fig. 4. Fig. 5 is a meridian sectional part of Fig. 4.

Fig. 1 zeigt eine schematische Darstellung einer Brennkraftma­ schine 1 mit einem erfindungsgemäß ausgebildeten Abgasturbo­ lader 2 mit einer Turbine 3 und einem Verdichter 4, die mit einer gemeinsamen Welle 5 verbunden sind. Fig. 1 shows a schematic representation of an internal combustion engine 1 with an inventive exhaust gas turbocharger 2 with a turbine 3 and a compressor 4 , which are connected to a common shaft 5 .

Eine Abgasleitung 6 führt von einer Auslaßseite 7 der Brenn­ kraftmaschine 1 zu einer Einströmseite 8 der Turbine 3, deren Ausströmseite 9 über ein Abgasleitungsteil 10 mit einem nicht dargestellten Abgassystem der Brennkraftmaschine 1 verbunden ist. Die Turbine 3 besitzt an ihrer Einströmseite 8 einen in den Fig. 2 bis 5 näher dargestellten axial, verschieblichen Leitschaufelkranz 11.An exhaust pipe 6 leading from an outlet side 7 of the internal combustion engine 1 to an inflow side 8 of the turbine 3, the outflow side 9 is connected via an exhaust line part 10 with a not shown exhaust system of the internal combustion engine. 1 The turbine 3 has on its inflow side 8 an axially displaceable guide vane ring 11 shown in more detail in FIGS. 2 to 5.

Ein erster Teil 12 einer Ladeluftleitung 13 führt von einer Druckseite 14 des Verdichters 4 zu einem Ladeluftkühler 15, von dem ein zweiter Teil 16 der Ladeluftleitung 13 zu einer Ein­ laßseite 17 der Brennkraftmaschine 1 führt. Eine Saugseite 18 des Verdichters 4 ist über ein Abgasleitungsteil 19 in be­ kannter Weise mit einem nicht dargestellten Luftfilter verbun­ den.A first part 12 of a charge air line 13 leads from a pressure side 14 of the compressor 4 to a charge air cooler 15 , of which a second part 16 of the charge air line 13 leads to an inlet side 17 of the internal combustion engine 1 . A suction side 18 of the compressor 4 is verbun via an exhaust pipe part 19 in a known manner with an air filter, not shown.

Von der Druckseite 14 des Verdichters 4 führt eine Leitung 20 zur Einströmseite 8 der Turbine 3.A line 20 leads from the pressure side 14 of the compressor 4 to the inflow side 8 of the turbine 3 .

Die Regelung der Strömungsverbindung zwischen der Einlaßseite 8 der Turbine 3 und der Druckseite 14 des Verdichters 4 erfolgt durch die motorkennfeldgesteuerte Verschiebung des Leitschau­ felkranzes 11, mit dem auch das Betriebsverhalten der Turbine 3 in prinzipiell bekannter Weise geregelt wird.The regulation of the flow connection between the inlet side 8 of the turbine 3 and the pressure side 14 of the compressor 4 is carried out by the engine map-controlled displacement of the guide ring 11 , with which the operating behavior of the turbine 3 is regulated in a manner known in principle.

Die Fig. 2 und 3 zeigen einen Radialschnitt und einen Meridi­ anteilschnitt der Turbine 3 des erfindungsgemäßen Abgasturbo­ laders 2 mit einem Turbinengehäuse 21, das einen spiralförmigen Strömungskanal 22 umfaßt, der an ein Turbinenrad 23 mündet. Im Mündungsbereich des Strömungskanales 22 befindet sich der va­ riable Leitschaufelkranz 11. Figs. 2 and 3 show a radial section and a Meridi share section of the turbine 3 of the exhaust turbo supercharger according to the invention 2 comprising a turbine housing 21 which includes a spiral flow channel 22, which leads to a turbine wheel 23rd The variable guide vane ring 11 is located in the mouth region of the flow channel 22 .

Die Leitung 20 von der Druckseite 14 des Verdichters 4 ist an einem Rohrstutzen 24 des Turbinengehäuses 21 mit einer Überwurfmutter 25 befestigt. Der Rohrstutzen 24 bildet das Ende einer Bohrung 26 im Turbinengehäuse 21, die in eine Öffnung 27 einer Kammer 28 einmündet. Die Kammer 28 ist eine pfannenför­ mige Ausnehmung in einer Büchse 29 des axialverschieblichen Leitschaufelkranzes 11.The line 20 from the pressure side 14 of the compressor 4 is fastened to a pipe socket 24 of the turbine housing 21 with a union nut 25 . The pipe socket 24 forms the end of a bore 26 in the turbine housing 21 , which opens into an opening 27 of a chamber 28 . The chamber 28 is a pfannenför shaped recess in a sleeve 29 of the axially displaceable guide vane ring 11 .

Von einer Ausmündung 30 der Kammer 28 führt eine Verbindungs­ leitung 31 zum spiralförmigen Strömungskanal 22 und mündet in diesen in einer Mündung 32 tangential ein.From a mouth 30 of the chamber 28 leads a connecting line 31 to the spiral flow channel 22 and opens into this in a mouth 32 tangentially.

Durch eine Verschiebung des Leitschaufelkranzes 11 nebst Büchse 29 nach rechts ist die Öffnung 27 bzw. die Ausmündung 30 der Kammer 28 verschließbar, wodurch die Strömungsverbindung zwi­ schen Druckseite 14 des Verdichters 4 und Einströmseite 8 der Turbine 3 unterbrochen ist.By moving the guide vane ring 11 and bushing 29 to the right, the opening 27 or the mouth 30 of the chamber 28 can be closed, as a result of which the flow connection between the pressure side 14 of the compressor 4 and the inflow side 8 of the turbine 3 is interrupted.

Die Fig. 4 und 5 zeigen in einer analogen Darstellung zu Fig. 2 und 3 einen Radialschnitt und einen Meridianteilschnitt der Turbine 3 des erfindungsgemäßen Abgasturboladers 2. Gleiche Bauteile der Fig. 1, 2 und 3 werden mit gleichen Bezugszeichen gekennzeichnet. FIGS. 4 and 5 show, in a representation analogous to FIGS. 2 and 3 is a radial section and a meridian part section of the turbine 3 of the exhaust gas turbocharger 2 of the invention. Identical components in FIGS. 1, 2 and 3 are identified by the same reference symbols.

Der Leitschaufelkranz 11 ist an seiner linken Stirnseite 33 mit einer Büchse 34 fest verbunden, die auf einem Teil ihres Um­ fangs einen Bremsspalt 35 besitzt, der gleichzeitig eine Kammer 38 bildet. Im Motorbremsbetrieb wird der variable Leitschau­ felkranz 11 so weit nach rechts verschoben, bis sich die Büchse 34 mit dem Bremsspalt 35 über dem Turbinenrad befindet.The guide vane ring 11 is fixedly connected on its left end face 33 to a sleeve 34 which, on part of its order, has a brake gap 35 which simultaneously forms a chamber 38 . In engine braking operation, the variable guide ring 11 is shifted to the right until the sleeve 34 with the brake gap 35 is located above the turbine wheel.

Die Bohrung 26 im Turbinengehäuse 21 mündet in den Bremsspalt 35, von dem eine Verbindungsleitung 36 ausmündet, die direkt an die Anströmseite von Leitschaufeln 37 des Turbinenrades 23 mündet. Die einander zugewandten Öffnungen der Bohrung 26 und der Verbindungsleitung 36 liegen einander kongruent gegenüber. Die Regelung der Strömungsverbindung zwischen der Druckseite 14 des Verdichters 4 und der Einströmseite 8 der Turbine 3 erfolgt durch axiale Verschiebung des Leitschaufelkranzes 11, in dem wahlweise die Kammer 38 (Bremsspalt 35) oder die Büchse 34 zwischen Bohrung 26 und Verbindungsleitung 36 geschoben wird.The bore 26 in the turbine housing 21 opens into the brake gap 35 , from which a connecting line 36 opens, which opens directly onto the upstream side of guide vanes 37 of the turbine wheel 23 . The mutually facing openings of the bore 26 and the connecting line 36 are congruently opposite one another. The flow connection between the pressure side 14 of the compressor 4 and the inflow side 8 of the turbine 3 is regulated by axially displacing the guide vane ring 11 , in which the chamber 38 (brake gap 35 ) or the sleeve 34 is pushed between the bore 26 and the connecting line 36 .

Die Betätigungsvorrichtung des axialverschieblichen Leitschau­ felkranzes 11, die nicht dargestellt ist, besteht in prinzi­ piell bekannter Weise aus einem motorkennfeldgesteuerten Regler nebst Stellglied.The actuating device of the axially displaceable guide ring 11 , which is not shown, consists in principle known manner from a map controlled controller and actuator.

Treibende Kraft der Ladeluftzuführung von der Druckseite 14 zur Einströmseite 8 bzw. der Abgasrückführung von der Einströmseite 8 der Turbine 3 zur Druckseite 14 des Verdichters 4 ist das Druckgefälle zwischen Druckseite 14 und Einströmseite 8.The driving force of the charge air supply from the pressure side 14 to the inflow side 8 or the exhaust gas recirculation from the inflow side 8 of the turbine 3 to the pressure side 14 of the compressor 4 is the pressure drop between the pressure side 14 and the inflow side 8 .

Der Betriebsmodus der Brennkraftmaschine 1 (mit/ohne Abgas­ rückführung, mit/ohne Kühlung von Teilen der Turbine 3 durch abgezweigte Ladeluft) wird je nach vorhandenem Druckgefälle zwischen Druckseite 14 und Einströmseite 8 eingestellt, in dem der Leitschaufelkranz 11 nebst Büchse 34 durch den motorkennfeldgesteuerten Regler in eine die Bohrung 26 ver­ schließende oder öffnende Position geschoben wird.The operating mode of the internal combustion engine 1 (with / without exhaust gas recirculation, with / without cooling of parts of the turbine 3 by means of branched charge air) is set depending on the pressure drop between the pressure side 14 and the inflow side 8 , in which the guide vane ring 11 and bushing 34 are controlled by the controller controlled by the engine map is pushed into a bore 26 ver closing or opening position.

Eine weitere Verbesserung der Kühlung des Leitschaufelkranzes und des Turbinengehäuses ist erreichbar, wenn statt der pfannen­ förmigen Kammer gemäß der Fig. 2 und 3 die Kammer ringartig am Umfang der Büchse geführt wird und die Einmündung der Bohrung und die Ausmündung der Verbindungsleitung etwa um 180° versetzt sind.A further improvement in the cooling of the guide vane ring and the turbine housing can be achieved if, instead of the pan-shaped chamber according to FIGS . 2 and 3, the chamber is guided in a ring on the circumference of the sleeve and the mouth of the bore and the mouth of the connecting line are offset by approximately 180 ° are.

Claims (5)

1. Abgasturbolader für eine aufgeladene Brennkraftmaschine, wobei der Abgasturbolader mindestens eine Turbine und einen Verdichter aufweist und die Turbine eine Einströmseite und eine Ausströmseite sowie ein Turbinenrad, ein Turbinengehäuse mit einem spiralförmigen Strömungskanal und einen variablen Leit­ schaufelkranz umfaßt und der Verdichter eine Druckseite und eine Saugseite besitzt und von der Druckseite des Verdichters eine Leitung in eine vom spiralförmigen Strömungskanal abge­ trennte Kammer im Turbinengehäuse geführt ist, dadurch gekennzeichnet, daß von der Kammer (28, 38) eine Verbindungsleitung (31, 36) ausmündet, die mit der Einströmseite (8) der Turbine (3) ver­ bunden ist und daß die Strömungsverbindung zwischen der Druck­ seite (14) des Verdichters (4) und der Einströmseite (8) der Turbine (3) mit einem Teil des variablen Leitschaufelkranzes (11) regelbar ist.1. Exhaust gas turbocharger for a supercharged internal combustion engine, the exhaust gas turbocharger having at least one turbine and a compressor and the turbine having an inflow side and an outflow side as well as a turbine wheel, a turbine housing with a spiral flow channel and a variable guide vane ring and the compressor comprising a pressure side and a suction side has and from the pressure side of the compressor a line is led into a chamber separated from the spiral flow channel in the turbine housing, characterized in that a connection line ( 31 , 36 ) opens out from the chamber ( 28 , 38 ) and connects to the inflow side ( 8 ) the turbine ( 3 ) is connected and that the flow connection between the pressure side ( 14 ) of the compressor ( 4 ) and the inflow side ( 8 ) of the turbine ( 3 ) with part of the variable guide vane ring ( 11 ) can be regulated. 2. Abgasturbolader nach Anspruch 1, dadurch gekennzeichnet, daß mindestens ein Teil der Kammer (28, 38) Bestandteil des va­ riablen Leitschaufelkranzes (11) ist.2. Exhaust gas turbocharger according to claim 1, characterized in that at least part of the chamber ( 28 , 38 ) is part of the variable vane ring ( 11 ). 3. Abgasturbolader nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß bei einem axialverschieblichen, variablen Leitschaufelkranz (11) die Kammer (28, 38) ringförmig ausgebildet ist und daß eine Öffnung (27) der in die Kammer (28, 38) mündenden Bohrung (26) versetzt zu einer Ausmündung (30) der von der Kammer (28, 38) zur Einströmseite (8) der Turbine (3) führenden Verbindungs­ leitung (31, 36) angeordnet ist.3. Exhaust gas turbocharger according to claim 1 or 2, characterized in that with an axially displaceable, variable guide vane ring ( 11 ), the chamber ( 28 , 38 ) is annular and that an opening ( 27 ) of the bore opening into the chamber ( 28 , 38 ) ( 26 ) offset to an opening ( 30 ) from the chamber ( 28 , 38 ) to the inflow side ( 8 ) of the turbine ( 3 ) leading connecting line ( 31 , 36 ) is arranged. 4. Abgasturbolader nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Verbindungsleitung (31, 36) zwischen Kammer (28, 38) und Einströmseite (8) der Turbine (3) in etwa tangential in einer Mündung (32) in den spiralförmigen Strömungskanal (22) einmün­ det.4. Exhaust gas turbocharger according to one of claims 1 to 3, characterized in that the connecting line ( 31 , 36 ) between the chamber ( 28 , 38 ) and the inflow side ( 8 ) of the turbine ( 3 ) approximately tangentially in a mouth ( 32 ) in the spiral flow channel ( 22 ) einmün det. 5. Abgasturbolader nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die Verbindungsleitung (31, 36) zwischen Kammer (28, 38) und Einströmseite (8) der Turbine (3) direkt an das Turbinenrad (23) mündet.5. Exhaust gas turbocharger according to one of claims 1 to 4, characterized in that the connecting line ( 31 , 36 ) between the chamber ( 28 , 38 ) and the inflow side ( 8 ) of the turbine ( 3 ) opens directly to the turbine wheel ( 23 ).
DE4312077A 1993-04-13 1993-04-13 Exhaust gas turbocharger for IC engine - has at least one turbine and compressor, turbine having inflow and outflow sides, turbine wheel, housing with spirally-shaped flow channel and variable guide blade crown Expired - Fee Related DE4312077C1 (en)

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WO1996032583A1 (en) * 1995-04-11 1996-10-17 Nederlandse Organisatie Voor Toegepast Natuurwetenschappelijk Onderzoek Tno Exhaust-gas recirculation system for an internal combustion engine
AT2540U1 (en) * 1997-12-16 1998-12-28 Avl List Gmbh INTERNAL COMBUSTION ENGINE WITH AT LEAST ONE COMPRESSOR FOR PRE-COMPRESSING THE INTAKE AIR
DE19808832A1 (en) * 1998-03-03 1999-09-09 Daimler Chrysler Ag Procedure for controlling charge air mass flow of IC engine charged up by exhaust turbocharger with adjustable geometry
US6026791A (en) * 1997-03-03 2000-02-22 Alliedsignal Inc. Exhaust gas recirculation valve with integral feedback proportional to volumetric flow
DE19913792A1 (en) * 1999-03-26 2000-10-05 Daimler Chrysler Ag Charged internal combustion engine operating process, involving overflow line being forced open at set pressure difference to return exhaust gas to charge air line
DE10232519A1 (en) * 2002-07-18 2004-01-29 Daimlerchrysler Ag Exhaust gas turbocharger for combustion engine has control grid in turbine inlet cross-section at distance from turbine wheel; compressed combustion air is fed into space between grid, turbine wheel
EP1617041A1 (en) * 2004-07-15 2006-01-18 ABB Turbo Systems AG Turbocharger with air cooled turbine disc
WO2008066632A1 (en) * 2006-11-30 2008-06-05 Caterpillar Inc. Method for modulating turbocharger braking
DE102008057728A1 (en) * 2008-11-17 2010-05-27 Bosch Mahle Turbo Systems Gmbh & Co. Kg Exhaust gas turbine for exhaust gas turbocharger in internal combustion engine of motor vehicle, has withdrawal area arranged in end area of spiral-shaped inlet section of housing, where end area is spaced from housing inlet
WO2010095983A1 (en) * 2009-02-19 2010-08-26 Volvo Lastvagnar Ab Method and apparatus for controlling turbine efficiency
DE102009018769A1 (en) * 2009-04-24 2010-11-04 Bosch Mahle Turbo Systems Gmbh & Co. Kg Exhaust-gas turbine i.e. exhaust gas turbocharger, for internal-combustion engine of motor vehicle, has withdrawals arranged about 60 degree and 180 degree along spiral-shaped inlet section with respect to rotation axis
DE102015203171A1 (en) * 2015-02-23 2016-08-25 Ford Global Technologies, Llc Exhaust-driven turbocharged internal combustion engine comprising a centrifugal compressor with arranged in the diffuser guide and method for operating such an internal combustion engine
GB2552482A (en) * 2016-07-25 2018-01-31 Jaguar Land Rover Ltd Direct injection of gas into a turbine volute
DE102017106164A1 (en) 2017-03-22 2018-09-27 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr turbocharger
CN114729596A (en) * 2019-12-26 2022-07-08 三菱重工发动机和增压器株式会社 Variable capacity turbocharger

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WO1996032583A1 (en) * 1995-04-11 1996-10-17 Nederlandse Organisatie Voor Toegepast Natuurwetenschappelijk Onderzoek Tno Exhaust-gas recirculation system for an internal combustion engine
US6026791A (en) * 1997-03-03 2000-02-22 Alliedsignal Inc. Exhaust gas recirculation valve with integral feedback proportional to volumetric flow
AT2540U1 (en) * 1997-12-16 1998-12-28 Avl List Gmbh INTERNAL COMBUSTION ENGINE WITH AT LEAST ONE COMPRESSOR FOR PRE-COMPRESSING THE INTAKE AIR
DE19808832A1 (en) * 1998-03-03 1999-09-09 Daimler Chrysler Ag Procedure for controlling charge air mass flow of IC engine charged up by exhaust turbocharger with adjustable geometry
DE19808832C2 (en) * 1998-03-03 2000-04-13 Daimler Chrysler Ag Method for regulating the charge air mass flow of a supercharged internal combustion engine
FR2794173A1 (en) * 1999-03-26 2000-12-01 Daimler Chrysler Ag METHOD FOR OPERATING A SUPERCHARGED INTERNAL COMBUSTION ENGINE
DE19913792A1 (en) * 1999-03-26 2000-10-05 Daimler Chrysler Ag Charged internal combustion engine operating process, involving overflow line being forced open at set pressure difference to return exhaust gas to charge air line
DE10232519A1 (en) * 2002-07-18 2004-01-29 Daimlerchrysler Ag Exhaust gas turbocharger for combustion engine has control grid in turbine inlet cross-section at distance from turbine wheel; compressed combustion air is fed into space between grid, turbine wheel
EP1617041A1 (en) * 2004-07-15 2006-01-18 ABB Turbo Systems AG Turbocharger with air cooled turbine disc
WO2006005199A1 (en) * 2004-07-15 2006-01-19 Abb Turbo Systems Ag Exhaust-gas turbine for a turbocharger comprising an air-cooled turbine disc
WO2008066632A1 (en) * 2006-11-30 2008-06-05 Caterpillar Inc. Method for modulating turbocharger braking
US7644584B2 (en) 2006-11-30 2010-01-12 Caterpillar Inc. Method for modulating turbocharger braking
DE102008057728A1 (en) * 2008-11-17 2010-05-27 Bosch Mahle Turbo Systems Gmbh & Co. Kg Exhaust gas turbine for exhaust gas turbocharger in internal combustion engine of motor vehicle, has withdrawal area arranged in end area of spiral-shaped inlet section of housing, where end area is spaced from housing inlet
US9945327B2 (en) * 2009-02-19 2018-04-17 Volvo Lastvagnar Ab Method and apparatus for controlling turbine efficiency
EP2399013A1 (en) * 2009-02-19 2011-12-28 Volvo Lastvagnar AB Method and apparatus for controlling turbine efficiency
US20120159947A1 (en) * 2009-02-19 2012-06-28 Volvo Lastvagnar Ab Method and apparatus for controlling turbine efficiency
US20140083096A1 (en) * 2009-02-19 2014-03-27 Volvo Lastvagnar Ab Method and apparatus for controlling turbine efficiency
EP2399013A4 (en) * 2009-02-19 2014-05-28 Volvo Lastvagnar Ab Method and apparatus for controlling turbine efficiency
WO2010095983A1 (en) * 2009-02-19 2010-08-26 Volvo Lastvagnar Ab Method and apparatus for controlling turbine efficiency
DE102009018769A1 (en) * 2009-04-24 2010-11-04 Bosch Mahle Turbo Systems Gmbh & Co. Kg Exhaust-gas turbine i.e. exhaust gas turbocharger, for internal-combustion engine of motor vehicle, has withdrawals arranged about 60 degree and 180 degree along spiral-shaped inlet section with respect to rotation axis
US10006356B2 (en) 2015-02-23 2018-06-26 Ford Global Technologies, Llc Exhaust gas-turbocharged internal combustion engine comprising a radial compressor with guide device arranged in the diffuser, and method for operating an internal combustion engine of said type
DE102015203171A1 (en) * 2015-02-23 2016-08-25 Ford Global Technologies, Llc Exhaust-driven turbocharged internal combustion engine comprising a centrifugal compressor with arranged in the diffuser guide and method for operating such an internal combustion engine
GB2552482A (en) * 2016-07-25 2018-01-31 Jaguar Land Rover Ltd Direct injection of gas into a turbine volute
DE102017106164A1 (en) 2017-03-22 2018-09-27 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr turbocharger
WO2018171833A1 (en) 2017-03-22 2018-09-27 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr Exhaust turbocharger
US11008982B2 (en) 2017-03-22 2021-05-18 Iav Gmbh Ingenieurgesellschaft Auto Und Verkehr Exhaust-gas turbocharger
CN114729596A (en) * 2019-12-26 2022-07-08 三菱重工发动机和增压器株式会社 Variable capacity turbocharger
CN114729596B (en) * 2019-12-26 2023-10-13 三菱重工发动机和增压器株式会社 Variable capacity turbocharger

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