DE4014976C1 - Exhaust turbocharger with two-stage axial exhaust turbine - has duct section, adjacent to first turbine stage, as part of axially displaceable ring slider - Google Patents

Exhaust turbocharger with two-stage axial exhaust turbine - has duct section, adjacent to first turbine stage, as part of axially displaceable ring slider

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Publication number
DE4014976C1
DE4014976C1 DE19904014976 DE4014976A DE4014976C1 DE 4014976 C1 DE4014976 C1 DE 4014976C1 DE 19904014976 DE19904014976 DE 19904014976 DE 4014976 A DE4014976 A DE 4014976A DE 4014976 C1 DE4014976 C1 DE 4014976C1
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DE
Germany
Prior art keywords
turbine
stage
exhaust gas
stages
ring slide
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 - Lifetime
Application number
DE19904014976
Other languages
German (de)
Inventor
Hans 7990 Friedrichshafen De Sudmanns
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.)
Rolls Royce Solutions GmbH
Original Assignee
MTU Friedrichshafen GmbH
MTU Motoren und Turbinen Union Friedrichshafen GmbH
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 MTU Friedrichshafen GmbH, MTU Motoren und Turbinen Union Friedrichshafen GmbH filed Critical MTU Friedrichshafen GmbH
Priority to DE19904014976 priority Critical patent/DE4014976C1/en
Application granted granted Critical
Publication of DE4014976C1 publication Critical patent/DE4014976C1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/12—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines with repeated action on same blade ring
    • 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
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages

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

Abstract

The exhaust turbocharger has two stages of axial turbine blading radially adjacent for each other on a common runner. The stages work in counterflow, using a diversion duct between the first stage outlet and second stage inlet, and a device to charge the first stage only, or both in sequence. A duct section (15), adjoining the first stage (13), is part of an axially adjusting ring slider (18) to connect the two stages (13,14) in the first slide setting, while in its second setting it links the first stage (13) outlet via the duct to the exhaust (25). ADVANTAGE - Simple switching of the turbine stages.

Description

Die Erfindung bezieht sich auf einen Abgasturbolader mit zweistufiger Axial-Abgasturbine nach dem Oberbegriff von Patentanspruch 1. Der Zweck dieser Anordnung liegt darin, die Abgasturbine an das wechselnde Abgasangebot der zugeordneten Brennkraftmaschine anzupassen.The invention relates to an exhaust gas turbocharger two-stage axial exhaust gas turbine according to the generic term of Claim 1. The purpose of this arrangement is that Exhaust gas turbine to the changing exhaust gas supply of the assigned Adapt internal combustion engine.

Ein gattungsgemäßer Abgasturbolader ist aus der DE 39 32 721 C1 bekannt. Die Abschaltung und betriebssichere Ausblendung der Beaufschlagung der zweiten Turbinenstufe aus dem Abgasstrom ist bei dem bekannten Abgasturbolader nicht befriedigend gelöst.A generic exhaust gas turbocharger is from DE 39 32 721 C1 known. The shutdown and reliable hiding of the Actuation of the second turbine stage from the exhaust gas flow is not solved satisfactorily in the known exhaust gas turbocharger.

Aus der JP 61-11 403 (A) ist eine zweistufige Axial-Gasturbine bekannt, die einen Umlenkkanal mit Leitwänden zwischen den beiden Turbinenstufen aufweist. Einrichtungen, die eine Teilbeaufschlagung der Axial-Gasturbine bewirken könnten, sind nicht erkennbar.JP 61-11 403 (A) is a two-stage axial gas turbine known that a deflection channel with baffles between the has two turbine stages. Facilities that a Partial loading of the axial gas turbine could cause not visible.

Aus der US-PS 43 67 626 ist ein Abgasturbolader mit einer einstufigen Axial-Abgasturbine bekannt geworden, der turbineneintrittsseitig einen mit Druckgas verstellbaren Ringschieber zur Steuerung von Ladeluftbeimischungen zum Abgasstrom aufweist. Eine Teilbeaufschlagung oder Umgehung der Axial-Abgasturbine ist mit dieser bekannten Anordnung nicht zu realisieren. From US-PS 43 67 626 is an exhaust gas turbocharger with a single-stage axial exhaust gas turbine known on the turbine inlet side an adjustable with compressed gas Ring slide valve for controlling charge air admixtures for Has exhaust gas flow. Partial loading or bypassing the Axial exhaust gas turbine is not too with this known arrangement realize.  

Die Aufgabe der Erfindung besteht nun darin, eine Einrichtung zu schaffen, mit der eine gattungsgemäße, zweistufige Axial-Abgasturbine auf einfache Weise zwischen ein- und zweistufigem Betrieb umschaltbar ist.The object of the invention is now a device to create a generic, two-stage Axial exhaust gas turbine in a simple way between one and two-stage operation is switchable.

Diese Aufgabe wird erfindungsgemäß mit den kennzeichnenden Merkmalen von Anspruch 1 gelöst und mit den Merkmalen der Ansprüche 2 bis 4 weiter ausgestaltet.This object is achieved with the characteristic Features of claim 1 solved and with the features of Claims 2 to 4 further developed.

Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, daß sich ein sehr einfacher mechanischer Aufbau für die Steuerung der Stufenbeaufschlagung der Axial-Abgasturbine ergibt, daß sowohl bei einstufiger als auch bei zweistufiger Beaufschlagung der Axial-Abgasturbine eine optimale verlustarme Strömungsführung realisiert ist und daß die Anordnung betriebssicher arbeitet.The advantages achieved with the invention are in particular in that there is a very simple mechanical structure for the Control of the stage loading of the axial exhaust gas turbine shows that both one-stage and two-stage  Actuation of the axial exhaust gas turbine an optimal low-loss Flow guidance is realized and that the arrangement works reliably.

Ein Ausführungsbeispiel ist in der Zeichnung dargestellt und wird nachstehend näher beschrieben.An embodiment is shown in the drawing and is described in more detail below.

Ein nur teilweise dargestellter Abgasturbolader 11 enthält eine zweistufige Axial-Abgasturbine 12. Die Beschaufelungen der ersten Turbinenstufe 13 und der zweiten Turbinenstufe 14 der Axial-Abgasturbine 12 sind in radialer Richtung aneinander anschließend an einer gemeinsamen Laufradscheibe angeordnet. Die Beschaufelungen der ersten Turbinenstufe 13 und der zweiten Turbinenstufe 14 werden in entgegengesetzter Richtung nacheinander vom Abgas einer nicht dargestellten Brennkraftmaschine durchströmt. Zwischen beiden Turbinenstufen 13, 14 ist ein strömungsgünstig gestalteter torusartiger Umlenkkanal angeordnet, der aus einem axial verschiebbaren Kanalabschnitt 15 und einem feststehenden Kanalabschnitt 16 gebildet wird.An exhaust gas turbocharger 11 , which is only partially shown, contains a two-stage axial exhaust gas turbine 12 . The blades of the first turbine stage 13 and the second turbine stage 14 of the axial exhaust gas turbine 12 are arranged next to one another in the radial direction on a common impeller disk. The blades of the first turbine stage 13 and the second turbine stage 14 are successively flowed through in the opposite direction by the exhaust gas of an internal combustion engine, not shown. Arranged between the two turbine stages 13 , 14 is a toroidal deflection duct which is designed to be aerodynamically efficient and which is formed from an axially displaceable duct section 15 and a fixed duct section 16 .

Der verschiebbare Kanalabschnitt 15 ist Teil eines Ringschiebers 18, der abgedichtet in einem entsprechenden Zylinder 19 hin- und herbeweglich angeordnet ist.The displaceable channel section 15 is part of a ring slide 18 , which is arranged in a corresponding cylinder 19 so that it can move back and forth.

Der Zylinder 19 ergibt sich als ringförmiger Hohlraum zwischen dem Gehäuse 20 des Abgasturboladers 11 und einem Gehäuseeinsatz 21.The cylinder 19 results as an annular cavity between the housing 20 of the exhaust gas turbocharger 11 and a housing insert 21 .

Die Betätigung des Ringschiebers 18 erfolgt durch Druckgas, das über Leitungen 22, 23 in die zugeordneten Zylinderteilräume 24, 25 zuführbar ist.The ring slide 18 is actuated by compressed gas, which can be fed via lines 22 , 23 into the associated cylinder subspaces 24 , 25 .

In der oberen Hälfte der Zeichnung ist der Ringschieber 18 bei Druckgaszufuhr in den Zylinderteilraum 24 über die Leitung 22 in der bei Vollast der Brennkraftmaschine erforderlichen Stellung dargestellt. Dabei durchströmt das gesamte Abgas der Brennkraftmaschine zunächst die erste Turbinenstufe 13 der Abgasturbine 12 und erzeugt einen ersten Teil der Turbinenleistung. Anschließend erfolgt eine Umlenkung des Abgasstromes in den Kanalabschnitten 15 und 16 um 180°. Der Kanalabschnitt 15 ist mit Leitwänden 27 ausgestattet, die eine drallfreie Anströmung der vor der zweiten Turbinenstufe 14 angeordneten Düsen 28 bewirken. Beim Durchströmen der zweiten Turbinenstufe 14 erfolgt dann die Erzeugung des zweiten Teiles der Turbinenleistung. Das Abgas gelangt danach in den Auspuff 26.In the upper half of the drawing, the ring slide 18 is shown in the position required when the internal combustion engine is under full load when compressed gas is supplied to the partial cylinder space 24 via the line 22 . The entire exhaust gas of the internal combustion engine first flows through the first turbine stage 13 of the exhaust gas turbine 12 and generates a first part of the turbine output. The exhaust gas flow in the duct sections 15 and 16 is then deflected by 180 °. The duct section 15 is equipped with guide walls 27 , which bring about a swirl-free flow against the nozzles 28 arranged in front of the second turbine stage 14 . When flowing through the second turbine stage 14 , the second part of the turbine power is then generated. The exhaust gas then passes into the exhaust 26 .

Die untere Hälfte der Zeichnung zeigt die Stellung des Ringschiebers 18 bei Teillast oder Leerlauf der Brennkraftmaschine, wobei der Zylinderteilraum 25 über die Leitung 23 mit Druckgas beaufschlagt ist. Das Abgas durchströmt wiederum die erste Turbinenstufe 13 der Abgasturbine 12 und gelangt dann aber über den Kanalabschnitt 15 unter Umgehung der zweiten Turbinenstufe 14 in den Auspuffkanal 17 und in den Auspuff 26.The lower half of the drawing shows the position of the ring slide 18 at partial load or idling of the internal combustion engine, with the cylinder part space 25 being pressurized with compressed gas via the line 23 . The exhaust gas in turn flows through the first turbine stage 13 of the exhaust gas turbine 12 and then passes via the duct section 15 , bypassing the second turbine stage 14, into the exhaust duct 17 and into the exhaust 26 .

Claims (4)

1. Abgasturbolader mit zweistufiger Axial-Abgasturbine, bei der die Beschaufelung der beiden Turbinenstufen der Axial-Abgasturbine in radialer Richtung aneinander anschließend am gemeinsamen Laufrad angeordnet sind und die Turbinenstufen in entgegengesetzter Richtung durchströmt werden, wobei zwischen Schaufelaustritt der ersten Turbinenstufe und Schaufeleintritt der zweiten Turbinenstufe ein Umlenkkanal ausgebildet ist und eine Einrichtung die Beaufschlagung von erster Turbinenstufe allein oder beider Turbinenstufen aufeinanderfolgend steuert, dadurch gekennzeichnet, daß ein an die erste Turbinenstufe (13) anschließender Kanalabschnitt (15) als Teil eines axialverstellbaren Ringschiebers (18) ausgebildet ist, daß der Kanalabschnitt (15) in einer ersten Stellung des Ringschiebers (18) erste und zweite Turbinenstufe (13, 14) verbindet und daß in einer zweiten Stellung des Ringschiebers (18) der Kanalabschnitt (15) den Austritt der ersten Turbinenstufe (13) direkt mit dem Auspuff (26) verbindet.1. Exhaust gas turbocharger with a two-stage axial exhaust gas turbine, in which the blading of the two turbine stages of the axial exhaust gas turbine are arranged next to one another in the radial direction on the common impeller and the turbine stages are flowed through in the opposite direction, with the blade outlet of the first turbine stage and the blade inlet of the second turbine stage a deflection duct is formed and a device controls the application of the first turbine stage alone or both turbine stages in succession, characterized in that a duct section ( 15 ) adjoining the first turbine stage ( 13 ) is designed as part of an axially adjustable ring slide ( 18 ) such that the duct section ( 15 ) in a first position of the ring slide ( 18 ) connects the first and second turbine stages ( 13 , 14 ) and that in a second position of the ring slide ( 18 ) the channel section ( 15 ) directly exits the first turbine stage ( 13 ) t connects to the exhaust ( 26 ). 2. Abgasturbolader mit zweistufiger Axial-Abgasturbine nach Anspruch 1, dadurch gekennzeichnet, daß der Kanalabschnitt (15) Leitwände (27) aufweist.2. Exhaust gas turbocharger with two-stage axial exhaust gas turbine according to claim 1, characterized in that the channel section ( 15 ) has guide walls ( 27 ). 3. Abgasturbolader mit zweistufiger Axial-Abgasturbine nach Anspruch 1, dadurch gekennzeichnet, daß zur Verstellung des in einem ringförmigen Zylinder (19) angeordneten Ringschiebers (18) mittels Druckgas in die erste und zweite Stellung, erste und zweite ringförmige Zylinderteilräume (24, 25) zwischen Ringschieber (18), Gehäuse (20) und Gehäuseeinsatz (21) ausgebildet sind. 3. Exhaust gas turbocharger with two-stage axial exhaust gas turbine according to claim 1, characterized in that for adjusting the in an annular cylinder ( 19 ) arranged ring slide ( 18 ) by means of compressed gas in the first and second position, first and second annular partial cylinder spaces ( 24 , 25 ) are formed between the ring slide ( 18 ), housing ( 20 ) and housing insert ( 21 ). 4. Abgasturbolader mit zweistufiger Axial-Abgasturbine nach Anspruch 3, dadurch gekennzeichnet, daß eine erste Leitung (22) für den Druckgasanschluß des ersten Zylinderteilraums (24) im Gehäuse (20) und eine zweite Leitung (23) für den Druckgasanschluß des zweiten Zylinderteilraumes (25) im Gehäuse (20) und Gehäuseeinsatz (21) ausgebildet ist.4. Exhaust gas turbocharger with two-stage axial exhaust gas turbine according to claim 3, characterized in that a first line ( 22 ) for the compressed gas connection of the first cylinder part space ( 24 ) in the housing ( 20 ) and a second line ( 23 ) for the compressed gas connection of the second cylinder part space ( 25 ) is formed in the housing ( 20 ) and housing insert ( 21 ).
DE19904014976 1990-05-10 1990-05-10 Exhaust turbocharger with two-stage axial exhaust turbine - has duct section, adjacent to first turbine stage, as part of axially displaceable ring slider Expired - Lifetime DE4014976C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19904014976 DE4014976C1 (en) 1990-05-10 1990-05-10 Exhaust turbocharger with two-stage axial exhaust turbine - has duct section, adjacent to first turbine stage, as part of axially displaceable ring slider

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19904014976 DE4014976C1 (en) 1990-05-10 1990-05-10 Exhaust turbocharger with two-stage axial exhaust turbine - has duct section, adjacent to first turbine stage, as part of axially displaceable ring slider

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0985803A1 (en) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Turbine stage with radial inlet and axial outlet
DE102005032002A1 (en) * 2005-07-08 2007-01-18 Daimlerchrysler Ag Supercharger for internal combustion (IC) engine used in automobile, has turbine wheel having low and high pressure stages each consisting of turbine blades
DE102011080596A1 (en) * 2011-08-08 2013-02-14 Abb Turbo Systems Ag Arrangement for conducting an exhaust gas in an exhaust gas flowed axially

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4367626A (en) * 1979-07-16 1983-01-11 Schwartzman Everett H Turbocharger systems
DE3932721C1 (en) * 1989-09-30 1990-10-25 Mtu Friedrichshafen Gmbh Supercharged IC engine with turbo drive - has two-stage turbine with partial by=pass to control rotor speed
JPH06111403A (en) * 1992-09-28 1994-04-22 Japan Energy Corp Film formation for recording medium consisting of multilayered artificial lattice films of transition metal/ noble metal

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4367626A (en) * 1979-07-16 1983-01-11 Schwartzman Everett H Turbocharger systems
DE3932721C1 (en) * 1989-09-30 1990-10-25 Mtu Friedrichshafen Gmbh Supercharged IC engine with turbo drive - has two-stage turbine with partial by=pass to control rotor speed
JPH06111403A (en) * 1992-09-28 1994-04-22 Japan Energy Corp Film formation for recording medium consisting of multilayered artificial lattice films of transition metal/ noble metal

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0985803A1 (en) * 1998-09-10 2000-03-15 Asea Brown Boveri AG Turbine stage with radial inlet and axial outlet
DE102005032002A1 (en) * 2005-07-08 2007-01-18 Daimlerchrysler Ag Supercharger for internal combustion (IC) engine used in automobile, has turbine wheel having low and high pressure stages each consisting of turbine blades
DE102011080596A1 (en) * 2011-08-08 2013-02-14 Abb Turbo Systems Ag Arrangement for conducting an exhaust gas in an exhaust gas flowed axially
WO2013020991A1 (en) 2011-08-08 2013-02-14 Abb Turbo Systems Ag Arrangement for routing an exhaust gas in an axial-flow exhaust gas turbine

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