EP0119323B1 - Turbosoufflante à gaz d'échappement pour moteurs à combustion interne - Google Patents

Turbosoufflante à gaz d'échappement pour moteurs à combustion interne Download PDF

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Publication number
EP0119323B1
EP0119323B1 EP83113132A EP83113132A EP0119323B1 EP 0119323 B1 EP0119323 B1 EP 0119323B1 EP 83113132 A EP83113132 A EP 83113132A EP 83113132 A EP83113132 A EP 83113132A EP 0119323 B1 EP0119323 B1 EP 0119323B1
Authority
EP
European Patent Office
Prior art keywords
exhaust gas
radially outer
flow
turbo supercharger
radially
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
Application number
EP83113132A
Other languages
German (de)
English (en)
Other versions
EP0119323A1 (fr
Inventor
Wilfried Ing. Schneider (Grad.)
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.)
Kloeckner Humboldt Deutz AG
Original Assignee
Kloeckner Humboldt Deutz 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 Kloeckner Humboldt Deutz AG filed Critical Kloeckner Humboldt Deutz AG
Priority to AT83113132T priority Critical patent/ATE20120T1/de
Publication of EP0119323A1 publication Critical patent/EP0119323A1/fr
Application granted granted Critical
Publication of EP0119323B1 publication Critical patent/EP0119323B1/fr
Expired 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
    • 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 inner 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. Due to the design of the exhaust gas turbocharger according to the invention, it is advantageously possible to apply the entire circumferential area of the turbine wheel evenly regardless of the position of the control member and thus regardless of the operating range of the internal combustion engine, the exhaust gas flowing through the radially outer spiral even with the maximum released exhaust gas cross section is assigned to the entire circumferential area of the turbine wheel, since on the one hand a partial flow flows through the opening cross-sections and acts directly on the turbine wheel and on the other hand the 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 minimized 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
  • 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 preferably the individual wall segments are 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.
  • 1 denotes the turbine impeller and 2 the turbine housing, which is provided with an inlet 3 and an outlet 4, which - Not shown in 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, which each connect to 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 a plurality of individual wall segments 11a, 11b, 11c, 11d.
  • the individual wall segments 11a to 11d are designed and arranged in the flow direction 12 of the exhaust gas in such a way that the radially inner spiral 6 and the radially outer spiral 7 through opening cross sections 13a, 13b, 13c and 13d, which have the same angular distance from one another in relation to the turbine impeller axis 9, be in flow communication.
  • the flow cross section of the radially outer spiral 7 decreases in the flow direction 12 of the exhaust gas, the flow cross section of the radially outer spiral 7 being constant between each two adjacent opening cross sections.
  • 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 element 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 a substantially 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 openings 13a to 13d comes radially inner spiral 6, 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 in the sense of a change in the incident angle of the turbine impeller 1 is influenced, 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 11-11 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 vertical plane 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Exhaust Gas After Treatment (AREA)

Claims (8)

1, Turbosoufflante à gaz d'échappement pour moteurs à combustion interne avec un carter de turbine (2) entourant une roue mobile de turbine (1) et qui est muni d'une entrée (3) et d'une sortie (4) pour les gaz d'échàppement du moteur à combustion interne, tandis qu'il comporte côté entrée, disposées en pratique concentriquement par rapport à la roue mobile de turbine (1), une spirale (6) placée radialement à l'intérieur et au moins une spirale (7) placée radialement à l'extérieur, cette spirale placée radialement à l'intérieur et cette spirale placée radialement à l'extérieur (6, 7) ayant une cloison de séparation commune (11), et la section transversale d'entrée des gaz d'échappement dans le carter de turbine (2) étant susceptible d'être modifiée au moyen d'un organe de commande (8, 15), turbosoufflante caractérisée en ce que la spirale intérieure et la spirale extérieure (6, 7) sont en communication par des ouvertures (13a, 13b, 13c, 13d) prévues dans la paroi de séparation (11) et disposées les unes derrière les autres dans le sens d'écoulement (12) des gaz d'échappement, ces spirales interne et externe s'étendant en pratique sur la totalité de la périphérie de la roue mobile de turbine (1).
2. Turbosoufflante à gaz d'échappement selon la revendication 1, caractérisée en ce que les ouvertures (13a à 13d) sont prévues dans la paroi de séparation (11) en étant décalées entre elles dans le sens d'écoulement (12) des gaz d'échappement d'un même angle par rapport à l'axe (9) de la roue mobile de turbines.
3. Turbosoufflante selon une des revendications 1 ou 2, caractérisée en ce que la section transversale d'écoulement de la spirale externe (7) décroît dans le sens d'écoulement (12) des gaz d'échappement.
4. Turbosoufflante selon une des précédentes revendications, caractérisée en ce que la paroi de séparation (11) est constituée de plusieurs segments individuels de parois (11a. 11b, 11c, 11 d) qui sont disposés dans le sens d'écoulement (12) des gaz d'échappement en étant décalés radialement pour ménager les ouvertures (13a à 13d).
5. Turbosoufflante à gaz d'échappement selon une des revendications précédentes, caractérisée en ce que la spirale extérieure (7) présente respectivement entre deux ouvertures successives (13a à 13d) une section transversale d'écoulement constante.
6. Turbosoufflante à gaz d'échappement selon une des revendications 1 à 5, caractérisée en ce qu'il est prévu comme organe de commande un clapet (8) susceptible de tourner, de préférence autour d'un axe (10) passant par son centre de gravité et qui contrôle la spirale extérieure (7).
7. Turbosoufflante à gaz d'échappement selon une des revendications 1 à 5, caractérisée en ce qu'il est prévu comme organe de commande, un registre tournant (15) qui contrôle la spirale extérieure (7).
8. Turbosoufflante à gaz d'échappement selon une des précédentes revendications, caractérisée en ce que les spirales (6, 7) sont susceptibles d'être subdivisées par au moins une paroi (14) s'étendant dans un plan perpendiculaire à l'axe (9) de la roue mobile de turbines.
EP83113132A 1983-01-24 1983-12-27 Turbosoufflante à gaz d'échappement pour moteurs à combustion interne Expired EP0119323B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT83113132T ATE20120T1 (de) 1983-01-24 1983-12-27 Abgasturbolader fuer brennkraftmaschinen.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3302186 1983-01-24
DE19833302186 DE3302186A1 (de) 1983-01-24 1983-01-24 Abgasturbolader fuer brennkraftmaschinen

Publications (2)

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

Family

ID=6189026

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83113132A Expired EP0119323B1 (fr) 1983-01-24 1983-12-27 Turbosoufflante à gaz d'échappement pour moteurs à combustion interne

Country Status (5)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9932843B2 (en) 2011-06-10 2018-04-03 Borgwarner Inc. Double flow turbine housing turbocharger

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DE10127916A1 (de) * 2001-06-08 2002-12-12 Daimler Chrysler Ag Abgasturbolader
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US6983596B2 (en) * 2001-11-02 2006-01-10 Borgwarner Inc. Controlled turbocharger with integrated bypass
JP2003184563A (ja) * 2001-12-14 2003-07-03 Aisin Seiki Co Ltd 可変容量ターボチャージャ
US7481056B2 (en) * 2006-03-30 2009-01-27 Blaylock Jimmy L Turbocharger with adjustable throat
DE102007017826B4 (de) * 2007-04-16 2010-11-04 Continental Automotive Gmbh Abgasturbolader
DE102007017775A1 (de) * 2007-04-16 2008-10-23 Continental Automotive Gmbh Abgasturbolader und Verfahren zu dessen Betreiben
US7694518B2 (en) * 2007-08-14 2010-04-13 Deere & Company Internal combustion engine system having a power turbine with a broad efficiency range
JP4875644B2 (ja) * 2008-02-29 2012-02-15 三菱重工業株式会社 タービンおよびこれを備えるターボチャージャ
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US9206732B2 (en) * 2010-02-26 2015-12-08 International Engine Intellectual Property Company, Llc Exhaust pulse energy divider
DE102010021928A1 (de) * 2010-05-28 2011-12-01 Daimler Ag Turbine für einen Abgasturbolader
US20130014497A1 (en) * 2011-07-15 2013-01-17 Gm Global Technology Operations Llc. Housing for an internal combustion engine
CN104956033A (zh) * 2012-12-20 2015-09-30 博格华纳公司 具有位于蜗壳中的分离叶片的涡轮机壳体
US9429162B2 (en) * 2013-02-01 2016-08-30 Honeywell International Inc. Axial turbine with sector-divided turbine housing
EP2770169B1 (fr) * 2013-02-20 2019-08-14 Ford Global Technologies, LLC Moteur à combustion interne chargé doté d'une turbine à deux flux et procédé de fonctionnement d'un tel moteur à combustion interne
JP6259520B2 (ja) * 2014-07-03 2018-01-10 三菱重工業株式会社 タービンケーシング、タービン、タービンケーシングを鋳造するための中子、及びタービンケーシングの製造方法
JP6222613B2 (ja) * 2014-08-27 2017-11-01 三菱重工業株式会社 開閉弁装置、及び回転機械
DE102019217316A1 (de) * 2019-11-08 2021-05-12 Volkswagen Aktiengesellschaft Abgasturbolader für Hochleistungsmotorkonzepte

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Publication number Priority date Publication date Assignee Title
US9932843B2 (en) 2011-06-10 2018-04-03 Borgwarner Inc. Double flow turbine housing turbocharger

Also Published As

Publication number Publication date
DE3302186A1 (de) 1984-07-26
ATE20120T1 (de) 1986-06-15
EP0119323A1 (fr) 1984-09-26
JPS59138727A (ja) 1984-08-09
US4565068A (en) 1986-01-21
DE3363831D1 (en) 1986-07-03

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