EP0814235A1 - Radial turbine for a turbocharger - Google Patents

Radial turbine for a turbocharger Download PDF

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Publication number
EP0814235A1
EP0814235A1 EP97106344A EP97106344A EP0814235A1 EP 0814235 A1 EP0814235 A1 EP 0814235A1 EP 97106344 A EP97106344 A EP 97106344A EP 97106344 A EP97106344 A EP 97106344A EP 0814235 A1 EP0814235 A1 EP 0814235A1
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EP
European Patent Office
Prior art keywords
ring
guide
turbine
control
channel
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Granted
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EP97106344A
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German (de)
French (fr)
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EP0814235B1 (en
Inventor
Wolfgang Dipl.-Ing. Heintze
Jürgen Dipl.-Ing. Nagel
Horst Dipl.-Ing. Buschmann
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Caterpillar Motoren GmbH and Co KG
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MaK Motoren GmbH and Co KG
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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
    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • 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

Definitions

  • the invention relates to a radial turbine for a turbocharger of a supercharged internal combustion engine with an adjustable turbine guide device which has at least two separate gas supply channels, which can be displaced into two different working positions in a guide cylinder formed by two control rings in a guide cylinder surrounding the turbine blade, and the turbine guide device consists of the guide ring with the two control rings, between which gas supply channels of different cross-sections are formed via a separating partition.
  • an exhaust gas turbocharger with a radial turbine in which an adjustable control ring is arranged for changing an effective cross section of the guide device for the exhaust gas flow supplied.
  • This comprises two feed channels with different cross sections, which are designed for full load and part load, wherein in each case one feed channel is switched on in order to produce a correspondingly effective cross section.
  • the invention has for its object to enable simple adjustment of the control rings with a self-holding for a generic arrangement with a turbine guide.
  • an adjustable guide ring with two gas guide channels for full and partial load of the turbine guide device by means of a compressed air reservoir and electrically controllable solenoid valves in a position for high boost pressure and thus strong torque and in a further position for an optimal, Ignition pressure-compatible and consumption-optimized full-load operation is adjustable.
  • the guide ring can remain in its assumed position in stable self-retention after completion of an adjustment process. After the desired position has been reached, the guide ring thus remains self-locking and, moreover, this state is supported by the pressures developed by the internal combustion engine on the air and exhaust side.
  • the increased area of the intermediate wall on which the exhaust gas pressure stands and due to the different throttling of the ring channels by a one-sided seal results in a resulting holding force that holds the guide ring securely in the position assigned by the control.
  • the guide ring essentially comprises two control rings which each terminate an annular channel with the turbine housing. These ring channels are connected to the compressed air reservoir and a boost pressure sensor.
  • the intermediate wall separating the gas guide channels of the guide ring is held in the two possible positions in a wall of the turbine housing in a seat, each of which results in a flush gas guide channel.
  • a mechanical lock consisting of a retaining pin, which is pneumatically actuated and ensures that the guide ring does not move uncontrolled from a set position due to vibrations of the internal combustion engine, is used for the starting process and for idling.
  • the position of the guide ring is preferably set by means of a memory-oriented control, by a control device via solenoid valves depending on parameters of the internal combustion engine. These parameters can be, for example, the speed of the internal combustion engine, the speed of the exhaust gas turbine, the pressure in the charge air receiver or the fuel injection pump, and a combination of these parameters is also possible.
  • An exhaust gas turbocharger 1 for an internal combustion engine 13 essentially comprises a compressor 3 with an exhaust gas turbine 2. Via a control device 18, the exhaust gas turbine 2 can be supplied with compressed air as a function of the load state of the internal combustion engine through a boost pressure sensor 14 and a compressed air reservoir 8.
  • the guide ring L can be shifted into two positions T and V, the T position standing for a high boost pressure and allowing a strong torque on the output flange of the internal combustion engine 13.
  • the V position stands for optimal, pressure-sensitive and consumption-optimized full-load operation.
  • the turbine guide device 4 can be adjusted to the two positions T and V by means of the compressed air reservoir 8 and electrically controllable solenoid valves 9 in the control device 18. Due to constructive measures on the guide device 4, the guide ring L can remain in the desired position in the self-holding position, without constant supply of compressed air from an external store.
  • the guide ring L is pushed into the position T via a pressure pulse from the external compressed air reservoir 8 into the ring channel 5a of the control ring S1.
  • a mechanical lock consisting of a holding pin 19 is actuated by means of a pneumatic cylinder 20 and the position T is locked.
  • the air supply from the memory 8 can be interrupted, since otherwise high air consumption would result.
  • the pressure in the charge air receiver 14 also increases.
  • the boost pressure generates in the ring channels 5a or 5b of the control rings S1 or S2 the force for the self-holding of the turbine guide device 4.
  • the safe self-holding is achieved in particular by the ring channel 5b being sealed more tightly with respect to the turbine-side gas supply channel 12 by means of piston ring-like sealing elements 16 than on that other side in the ring channel 5a.
  • This different throttling results in a higher pressure in the ring channel 5b, which holds the guide ring L in the position T.
  • a further increase in the holding force is achieved by an enlarged area of an intermediate wall 17 of the guide ring L, on which the Exhaust gas pressure in the inflow channel 12 of the turbine 2 presses.
  • the intermediate wall 17 is mounted in a seat which consists of an annular recess 32 and 33 in the walls 30, 31 of the turbine housing 7.
  • the switching criteria 15, which are stored in the memory 10 of the control, are overrun. These can be: speed of the charging device 1, speed of the internal combustion engine 13, impermissible boost pressure or the amount of fuel injected or a combination of these quantities.
  • the ring channel 5b is briefly vented via the solenoid valves 9 by the electrical switching signal triggered by the switching criteria.
  • the charge pressure in the ring channel 5a presses the guide ring L from the position T into the position V. Due to the changed effective guide ring area in the gas guide channel 11, the charge pressure changes to a desired level.
  • a pressure pulse with a narrow time limit is conducted from the higher pressure of the external memory 8 into the ring channel 5b and displaces the guide ring L against the boost pressure in the ring channel 5a.
  • the controller interrupts the air flow from the memory 8 after an adjustable time interval and switches back to the boost pressure connection in the ring channel 5b. With this configuration, the guide ring L remains stable in the desired position.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

The radial turbine is fitted to a turbocharger on a internal combustion engine, and has adjustable guide equipment with at least two separate gas supply channels. The latter can be moved to two different positions, using a guide ring which is formed by one of two control rings (S1,S2) inside a guide cylinder (F) which encloses the turbine blades. The guide equipment consists of the guide ring with the two control rings, and gas supply channels of different cross sections are formed between them by a separating wall (17). The wall has an end area which is larger than the annular channel area of the guide cylinder in the turbine casing (7). The first control ring (S1) has an annular seal (16) between the channel (5b) and the casing, so that a pressure difference from the other annular channel (5a) is created.

Description

Die Erfindung bezieht sich auf eine Radialturbine für einen Turbolader einer aufgeladenen Brennkraftmaschine mit einer verstellbaren Turbinenleiteinrichtung, die mindestens zwei voneinander getrennte Gaszuführkanäle aufweist, welche mittels eines aus zwei Steuerringen gebildeten Leitringes in einem die Turbinenschaufel umgebenden Führungszylinder, in zwei unterschiedliche Arbeitspositionen verschiebbar ist und die Turbinenleiteinrichtung aus dem Leitring mit den zwei Steuerringen besteht, zwischen denen Gaszuführkanäle verschiedenen Querschnitts über eine trennende Zwischenwand gebildet sind.The invention relates to a radial turbine for a turbocharger of a supercharged internal combustion engine with an adjustable turbine guide device which has at least two separate gas supply channels, which can be displaced into two different working positions in a guide cylinder formed by two control rings in a guide cylinder surrounding the turbine blade, and the turbine guide device consists of the guide ring with the two control rings, between which gas supply channels of different cross-sections are formed via a separating partition.

Aus der DE 42 15 301 Al ist ein Abgasturbolader mit einer Radialturbine bekannt, bei der zur Änderung eines wirksamen Querschnitts des Leitapparates für den zugeführten Abgasstrom ein verstellbarer Steuerring angeordnet ist. Dieser umfaßt zwei Zuführkanäle mit unterschiedlichen Querschnitten, die für Vollast und Teillast ausgelegt sind, wobei jeweils ein Zuführkanal eingeschaltet ist, um einen entsprechend wirksamen Querschnitt zu ergeben.From DE 42 15 301 Al an exhaust gas turbocharger with a radial turbine is known, in which an adjustable control ring is arranged for changing an effective cross section of the guide device for the exhaust gas flow supplied. This comprises two feed channels with different cross sections, which are designed for full load and part load, wherein in each case one feed channel is switched on in order to produce a correspondingly effective cross section.

Der Erfindung liegt die Aufgabe zugrunde, für eine gattungsgemäße Anordnung mit einer Turbinenleiteinrichtung eine einfache Verstellung der Steuerringe mit einer Selbsthaltung zu ermöglichen.The invention has for its object to enable simple adjustment of the control rings with a self-holding for a generic arrangement with a turbine guide.

Diese Aufgabe wird erfindungsgemäß durch die Merkmale des Anspruches 1 gelöst. Weitere vorteilhafte Ausgestaltungen sind durch die Merkmale der Unteransprüche gekennzeichnet.This object is achieved by the features of claim 1. Further advantageous configurations are characterized by the features of the subclaims.

Die mit der Erfindung hauptsächlich erzielten Vorteile bestehen darin, daß ein verstellbarer Leitring mit zwei Gasführungskanälen für Voll- und Teillast der Turbinenleiteinrichtung mittels eines Druckluftspeichers und elektrisch ansteuerbaren Magnetventilen in eine Stellung für hohen Ladedruck und damit starkem Drehmoment und in eine weitere Stellung für einen optimalen, zünddruckgerechten und verbrauchsoptimierten Vollastbetrieb verstellbar ist.The main advantages achieved by the invention are that an adjustable guide ring with two gas guide channels for full and partial load of the turbine guide device by means of a compressed air reservoir and electrically controllable solenoid valves in a position for high boost pressure and thus strong torque and in a further position for an optimal, Ignition pressure-compatible and consumption-optimized full-load operation is adjustable.

Durch eine entsprechende konstruktive Ausbildung mittels einer die Gasführungskanäle trennenden Zwischenwand, kann der Leitring nach Abschluß eines Verstellvorganges in stabiler Selbsthaltung in seiner eingenommenen Stellung verbleiben. Nach einem Erreichen der gewünschten Position bleibt der Leitring somit in Selbsthaltung und zudem wird dieser Zustand noch durch die von der Brennkraftmaschine entwickelten Drücke luft- und abgasseitig unterstützt. Die vergrößerte Fläche der Zwischenwand auf die der Abgasdruck steht und durch die unterschiedliche Drosselung der Ringkanäle durch eine einseitige Abdichtung ergibt sich eine resultierende Haltekraft, die den Leitring sicher in der von der Steuerung zugewiesenen Position hält.By means of a corresponding constructive design by means of an intermediate wall separating the gas guiding channels, the guide ring can remain in its assumed position in stable self-retention after completion of an adjustment process. After the desired position has been reached, the guide ring thus remains self-locking and, moreover, this state is supported by the pressures developed by the internal combustion engine on the air and exhaust side. The increased area of the intermediate wall on which the exhaust gas pressure stands and due to the different throttling of the ring channels by a one-sided seal results in a resulting holding force that holds the guide ring securely in the position assigned by the control.

Der Leitring umfaßt im wesentlichen zwei Steuerringe, welche mit dem Turbinengehäuse jeweils einen Ringkanal abschließen. Diese Ringkanäle sind mit dem Druckluftspeicher und einem Ladedruckaufnehmer verbunden.The guide ring essentially comprises two control rings which each terminate an annular channel with the turbine housing. These ring channels are connected to the compressed air reservoir and a boost pressure sensor.

Die die Gasführungskanäle des Leitringes trennende Zwischenwand, ist jeweils in den zwei möglichen Stellungen in einer Wandung des Turbinengehäuses in einem Sitz gehalten, der jeweils einen bündigen Gasführungskanal ergibt.The intermediate wall separating the gas guide channels of the guide ring is held in the two possible positions in a wall of the turbine housing in a seat, each of which results in a flush gas guide channel.

Für den Anfahrvorgang sowie für den Leerlauf dient eine mechanische Sperre, bestehend aus einem Haltestift, welcher pneumatisch angesteuert wird und dafür sorgt, daß der Leitring nicht durch Vibrationen der Brennkraftmaschine unkontrolliert aus einer eingestellten Position wandert.A mechanical lock, consisting of a retaining pin, which is pneumatically actuated and ensures that the guide ring does not move uncontrolled from a set position due to vibrations of the internal combustion engine, is used for the starting process and for idling.

Die Position des Leitringes wird vorzugsweise mittels einer speicherorientierten Steuerung, durch eine Steuereinrichtung über Magnetventile in Abhängigkeit von Parametern der Brennkraftmaschine eingestellt. Diese Parameter können beispielsweise die Drehzahl der Brennkraftmaschine, die Drehzahl der Abgasturbine, der Druck im Ladeluftaufnehmer oder der Kraftstoffeinspritzpumpe sein, wobei auch eine Kombination dieser Parameter möglich ist.The position of the guide ring is preferably set by means of a memory-oriented control, by a control device via solenoid valves depending on parameters of the internal combustion engine. These parameters can be, for example, the speed of the internal combustion engine, the speed of the exhaust gas turbine, the pressure in the charge air receiver or the fuel injection pump, and a combination of these parameters is also possible.

Ein Ausführungsbeispiel der Erfindung ist in den Zeichnungen schematisch dargestellt und wird im folgenden näher beschrieben.An embodiment of the invention is shown schematically in the drawings and is described in more detail below.

Es zeigen:

Fig. 1
einen Längsschnitt durch einen Abgasturbolader mit einer Radialturbine und mit einem verstellbaren Leitring,
Fig. 2
einen vergrößerten Ausschnitt der Turbine mit dem verstellbaren Leitring und
Fig. 3
eine Steuerung mit Magnetventilen und Luftleitungen.
Show it:
Fig. 1
2 shows a longitudinal section through an exhaust gas turbocharger with a radial turbine and with an adjustable guide ring,
Fig. 2
an enlarged section of the turbine with the adjustable guide ring and
Fig. 3
a control with solenoid valves and air lines.

Ein Abgasturbolader 1 für eine Brennkraftmaschine 13 umfaßt im wesentlichen einen Verdichter 3 mit einer Abgasturbine 2. Über eine Steuerungseinrichtung 18 ist der Abgasturbine 2 durch einen Ladedruckaufnehmer 14 und einem Druckluftspeicher 8 Druckluft in Abhängigkeit vom Lastzustand der Brennkraftmaschine zuführbar.An exhaust gas turbocharger 1 for an internal combustion engine 13 essentially comprises a compressor 3 with an exhaust gas turbine 2. Via a control device 18, the exhaust gas turbine 2 can be supplied with compressed air as a function of the load state of the internal combustion engine through a boost pressure sensor 14 and a compressed air reservoir 8.

In der Abgasturbine 2 ist eine Turbinenleiteinrichtung 4 mit einem Leitring L, bestehend aus zwei Steuerringen Sl und S2 mit gebildeten Gasführungskanälen 11,12, unterschiedlichen Querschnitts angeordnet.A turbine guide device 4 with a guide ring L, consisting of two control rings S1 and S2 with formed gas guide channels 11, 12, of different cross-section, is arranged in the exhaust gas turbine 2.

Der Leitring L kann in zwei Stellungen T und V verschoben werden, wobei die T-Stellung für einen hohen Ladedruck steht und ein starkes Drehmoment am Abtriebsflansch der Brennkraftmaschine 13 erlaubt. Dagegen steht die V-Stellung für einen optimalen, zünddruckgerechten und verbrauchsoptimierten Vollastbetrieb.The guide ring L can be shifted into two positions T and V, the T position standing for a high boost pressure and allowing a strong torque on the output flange of the internal combustion engine 13. In contrast, the V position stands for optimal, pressure-sensitive and consumption-optimized full-load operation.

Die Turbinenleiteinrichtung 4 kann mittels des Druckluftspeichers 8 und elektrisch ansteuerbaren Magnetventilen 9 in der Steuerungseinrichtung 18 in die beiden Positionen T und V verstellt werden. Aufgrund konstruktiver Maßnahmen an der Leiteinrichtung 4 kann der Leitring L in der gewünschten Stellung in der Selbsthaltung verbleiben, ohne ständige Zuführung von Druckluft aus einem externen Speicher.The turbine guide device 4 can be adjusted to the two positions T and V by means of the compressed air reservoir 8 and electrically controllable solenoid valves 9 in the control device 18. Due to constructive measures on the guide device 4, the guide ring L can remain in the desired position in the self-holding position, without constant supply of compressed air from an external store.

Hierzu besteht auf der Turbinengehäuseseite 7 eine direkte Verbindung über eine Leitung 6 zum Ladeluftaufnehmer 14 der Brennkraftmaschine 13. Über einen Ringkanal 5a wirkt der Ladeluftdruck ständig auf den Leitring L. Auf der Lagerträgerseite 21 besteht eine Verbindung über eine Leitung 6a zwischen dem Ringkanal 5b und dem Ladeluftaufnehmer 14 nur über die Steuerungseinrichtung 18. In den Ringkanal 5a des Steuerringes S2 kann wahlweise Druckluft aus dem externen Druckluftspeicher 8, Ladeluft aus dem Ladeluftaufnehmer 14 oder durch Entlüftung der Druck entsprechend verändert werden. Auf dieser Seite erfolgt dann auch die Ein leitung des Schaltvorganges.For this purpose, there is a direct connection on the turbine housing side 7 via a line 6 to the charge air receiver 14 of the internal combustion engine 13. The charge air pressure constantly acts on the guide ring L via an annular duct 5a Connection via a line 6a between the ring channel 5b and the charge air sensor 14 only via the control device 18. In the ring channel 5a of the control ring S2, compressed air from the external compressed air reservoir 8, charge air from the charge air sensor 14 or by venting the pressure can be changed accordingly. On this page, the switching process is also initiated.

Ausgehend vom Start der Brennkraftmaschine 13, wird über einen Druckimpuls aus dem externen Druckluftspeicher 8 in den Ringkanal 5a des Steuerringes S1 der Leitring L in die Position T geschoben. Gleichzeitig wird mittels eines Pneumatikzylinders 20 eine mechanische Sperre, bestehend aus einem Haltestift 19, betätigt und die Position T verriegelt. Dadurch kann die Luftzufuhr aus dem Speicher 8 unterbrochen werden, da sich im anderen Fall ein hoher Luftverbrauch einstellen würde. Bei einer steigenden Leistung der Brennkraftmaschine 13 steigt auch der Druck im Ladeluftaufnehmer 14.Starting from the start of the internal combustion engine 13, the guide ring L is pushed into the position T via a pressure pulse from the external compressed air reservoir 8 into the ring channel 5a of the control ring S1. At the same time, a mechanical lock consisting of a holding pin 19 is actuated by means of a pneumatic cylinder 20 and the position T is locked. As a result, the air supply from the memory 8 can be interrupted, since otherwise high air consumption would result. As the output of the internal combustion engine 13 increases, the pressure in the charge air receiver 14 also increases.

Der Ladedruck erzeugt in den Ringkanälen 5a oder 5b der Steuerringe S1 oder S2 die Kraft für die Selbsthaltung der Turbinenleiteinrichtung 4. Die sichere Selbsthaltung wird insbesondere dadurch ereicht, daß der Ringkanal 5b mittels kolbenringartiger Dichtungselemente 16 gegenüber dem turbinenseitigen Gaszuführkanal 12 stärker abgedichtet wird als auf der anderen Seite im Ringkanal 5a.The boost pressure generates in the ring channels 5a or 5b of the control rings S1 or S2 the force for the self-holding of the turbine guide device 4. The safe self-holding is achieved in particular by the ring channel 5b being sealed more tightly with respect to the turbine-side gas supply channel 12 by means of piston ring-like sealing elements 16 than on that other side in the ring channel 5a.

Diese unterschiedliche Drosselung ergibt im Ringkanal 5b einen höheren Druck, der den Leitring L in der Position T hält. Eine weitere Verstärkung der Haltekraft wird durch eine vergrößerte Fläche einer Zwischenwand 17 des Leitringes L erreicht, auf die der Abgasdruck im Zuströmkanal 12 der Turbine 2 drückt. Die Zwischenwand 17 ist in einem Sitz gelagert, der aus einer Ringausnehmung 32 und 33 in den Wänden 30,31 des Turbinengehäuses 7 besteht.This different throttling results in a higher pressure in the ring channel 5b, which holds the guide ring L in the position T. A further increase in the holding force is achieved by an enlarged area of an intermediate wall 17 of the guide ring L, on which the Exhaust gas pressure in the inflow channel 12 of the turbine 2 presses. The intermediate wall 17 is mounted in a seat which consists of an annular recess 32 and 33 in the walls 30, 31 of the turbine housing 7.

Diese reduzierte Drosselung des Luftstromes im Ringkanal 5a führt zu einem thermischen Ausgleich der Leiteinrichtung 4, da die kühle Ladeluft den turbinenseitig heißeren Teil stärker kühlt. Dadurch entsteht kein thermischer Verzug, der zum Klemmen des Schiebesitzes im Führungszylinder F das Leitringes L führen könnte. Der Luftstrom dient gleichzeitig als Sperrluft gegen das Eindringen von Abgas in die Ringkanäle 5a und 5b und dient auch zur Vermeidung von Ablagerungen im Schiebespalt.This reduced throttling of the air flow in the annular duct 5a leads to a thermal compensation of the guide device 4, since the cool charge air cools the hotter part more strongly. As a result, there is no thermal distortion, which could lead to the guide ring L becoming jammed in the guide cylinder F. The air flow also serves as sealing air against the ingress of exhaust gas into the ring channels 5a and 5b and also serves to avoid deposits in the sliding gap.

Durch diese beiden Maßnahmen ergibt sich eine außerordentlich hohe Funktionssicherheit, auch beim Betrieb mit Rückstandskraftstoffen.These two measures result in extraordinarily high functional reliability, even when operating with residual fuels.

Bei weiter zunehmender Leistung werden die Schaltkriterien 15 überfahren, die im Speicher 10 der Steuerung abgelegt sind. Dieses können sein: Drehzahl der Aufladeeinrichtung 1, Drehzahl der Brennkraftmaschine 13, unzulässiger Ladedruck oder die eingespritzte Kraftstoffmenge oder eine Kombination dieser Größen.With further increasing power, the switching criteria 15, which are stored in the memory 10 of the control, are overrun. These can be: speed of the charging device 1, speed of the internal combustion engine 13, impermissible boost pressure or the amount of fuel injected or a combination of these quantities.

Durch das von den Schaltkriterien ausgelöste elektrische Schaltsignal wird der Ringkanal 5b über die Magnetventile 9 kurzzeitig entlüftet. Der anstehende Ladedruck im Ringkanal 5a drückt den Leitring L aus der Position T in die Position V. Aufgrund der veränderten wirksamen Leitringfläche im Gasführkanal 11 ändert sich der Ladedruck auf eine gewünschte Höhe.The ring channel 5b is briefly vented via the solenoid valves 9 by the electrical switching signal triggered by the switching criteria. The charge pressure in the ring channel 5a presses the guide ring L from the position T into the position V. Due to the changed effective guide ring area in the gas guide channel 11, the charge pressure changes to a desired level.

Beim Rückschalten von der Position V in die Position T wird ein zeitlich eng begrenzter Druckimpuls aus dem höheren Druck des externen Speichers 8 in den Ringkanal 5b geleitet und verschiebt den Leitring L gegen den Ladedruck im Ringkanal 5a. Die Steuerung unterbricht nach Ablauf eines einstellbaren Zeitintervalls den Luftstrom aus dem Speicher 8 und schaltet zurück auf die Ladedruckverbindung in den Ringkanal 5b. Durch diese Ausgestaltung verbleibt der Leitring L stabil in der gewünschten Position.When switching back from position V to position T, a pressure pulse with a narrow time limit is conducted from the higher pressure of the external memory 8 into the ring channel 5b and displaces the guide ring L against the boost pressure in the ring channel 5a. The controller interrupts the air flow from the memory 8 after an adjustable time interval and switches back to the boost pressure connection in the ring channel 5b. With this configuration, the guide ring L remains stable in the desired position.

Claims (6)

Radialturbine für einen Turbolader einer aufgeladenen Brennkraftmaschine mit einer verstellbaren Turbinenleiteinrichtung, die mindestens zwei voneinander getrennte Gaszuführkanäle aufweist, welche mittels eines aus zwei Steuerringen gebildeten Leitringes in einem die Turbinenschaufel umgebenden Führungszylinder, in zwei unterschiedliche Arbeitspositionen verschiebbar ist und die Turbinenleiteinrichtung aus dem Leitring mit den zwei Steuerringen besteht, zwischen denen Gaszuführkanäle verschiedenen Querschnitts über eine trennende Zwischenwand gebildet sind, dadurch gekennzeichnet, daß die Zwischenwand (17) stirnflächenmäßig größer ausgeführt ist als die Ringkanalfläche des den Leitring (L) aufnehmenden Führungszylinders (F) im Turbinengehäuse (7) und im ersten Steuerring (S1) eine Ringabdichtung (16) des Ringkanals (5b) zu dem Turbinengehäuse (7) derart aufweist, daß ein Druckunterschied zum weiteren Ringkanal (5a) des zweiten Steuerrings (S2) herstellbar ist.Radial turbine for a turbocharger of a supercharged internal combustion engine with an adjustable turbine guide device which has at least two separate gas supply channels, which can be displaced into two different working positions by means of a guide ring formed from two control rings in a guide cylinder surrounding the turbine blade, and the turbine guide device from the guide ring with the two There are control rings, between which gas supply ducts of different cross-sections are formed via a dividing partition, characterized in that the end wall (17) is larger in terms of face area than the ring duct surface of the guide cylinder (F) receiving the guide ring (L) in the turbine housing (7) and in the first Control ring (S1) has a ring seal (16) of the ring channel (5b) to the turbine housing (7) such that a pressure difference to the further ring channel (5a) of the second control ring (S2) can be produced. Radialturbine nach Anspruch 1, dadurch gekennzeichnet, daß der Ringkanal (5b) des Steuerringes (S1) über eine Leitung (6a) mit einem Druckluftspeicher (8) oder einen Ladeluftaufnehmer (14) verbindbar ist, wobei der weitere Ringkanal (5a) des Steuerringes (S2) über eine Leitung (6) mit dem Ladeluftaufnehmer (14) der Brennkraftmaschine (13) direkt verbunden ist.Radial turbine according to Claim 1, characterized in that the ring channel (5b) of the control ring (S1) can be connected via a line (6a) to a compressed air reservoir (8) or a charge air receiver (14), the further ring channel (5a) of the control ring ( S2) is connected via a line (6) to the charge air receiver (14) of the internal combustion engine (13). Radialturbine nach den Ansprüchen 1 oder 2, dadurch gekennzeichnet, daß die Zwischenwand (17) im Leitring (L) einen Sitz jeweils in einer Ausnehmung (32 oder 33) der gegenüberstehenden Wände (30,31) des Turbinengehäuses aufweist.Radial turbine according to claims 1 or 2, characterized in that the intermediate wall (17) in the guide ring (L) has a seat in each case in a recess (32 or 33) of the opposing walls (30, 31) of the turbine housing. Radialturbine nach den Ansprüchen 1, 2 oder 3, dadurch gekennzeichnet, daß auf der druckgesteuerten Seite des Ringkanals (5b) über einen von der Steuerungseinrichtung (10) angesteuerten Pneumatikzylinder (20) eine mechanische Sperre vorgesehen ist, die aus einem Haltestift (19) besteht, der zur Lagefixierung des Leitringes (L) festsetzbar ist.Radial turbine according to claims 1, 2 or 3, characterized in that a mechanical lock is provided on the pressure-controlled side of the ring channel (5b) via a pneumatic cylinder (20) controlled by the control device (10), said mechanical lock consisting of a retaining pin (19) , which can be fixed to fix the guide ring (L). Radialturbine nach einem oder mehreren der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Position des Leitringes (L) mittels einer speicherorientierten Steuerung der Einrichtung (18) über Magnetventile (9) in Abhängigkeit von Parametern, wie der Drehzahl der Brennkraftmaschine (13), der Drehzahl der Abgasturbine (2), dem Druck im Ladeluftaufnehmer (14) oder der Kraftstoffeinspritzmenge, oder eine Kombination dieser Parameter einstellbar ist.Radial turbine according to one or more of the preceding claims, characterized in that the position of the guide ring (L) by means of a memory-oriented control of the device (18) via solenoid valves (9) depending on parameters such as the speed of the internal combustion engine (13), the speed the exhaust gas turbine (2), the pressure in the charge air sensor (14) or the fuel injection quantity, or a combination of these parameters is adjustable. Verfahren zur Durchführung von Schaltvorgängen des Leitringes der Turbinenleiteinrichtung in die aktive und passive Arbeitsposition nach Anspruch 1, gekennzeichnet durch folgende Steuervorgänge: - der anstehende Ladedruck aus dem Ladedruckaufnehmer (14) wird in den Ringkanal (5a) des Steuerringes (S2) geleitet und verschiebt im Führungszylinder (F) den Leitring (L) aus der Arbeitsposition (V) in die Arbeitsposition (T) mit dem wirksamen Gasführungskanal (11), wobei die wirksame Leitringfläche im Gasführungskanal (11) den Ladedruck verändert; - bei einem Zurückschalten von der Arbeitsposition (T) in die Arbeitsposition (U) wird ein zeitlich begrenzter Druckimpuls aus dem Speicher (8) in den Ringkanal (5b) des Steuerringes (S1) geleitet; - der Leitring (L) wird gegen den in den Ringkanal eingeführten Ladedruck aus dem Ladedruckaufnehmer (14) im Führungszylinder (F) verschoben und der Abgasstrom durchströmt den Gasführungskanal (12). Method for performing switching operations of the guide ring of the turbine guide device in the active and passive working position according to claim 1, characterized by the following control processes: - The upcoming boost pressure from the boost pressure sensor (14) is passed into the ring channel (5a) of the control ring (S2) and moves the guide ring (L) in the guide cylinder (F) from the working position (V) to the working position (T) with the effective one Gas guide channel (11), wherein the effective guide ring surface in the gas duct (11) changes the boost pressure; - When switching back from the working position (T) to the working position (U), a time-limited pressure pulse from the memory (8) is passed into the ring channel (5b) of the control ring (S1); - The guide ring (L) is displaced against the charge pressure introduced into the ring channel from the charge pressure sensor (14) in the guide cylinder (F) and the exhaust gas flow flows through the gas guide channel (12).
EP97106344A 1996-06-13 1997-04-17 Radial turbine for a turbocharger Expired - Lifetime EP0814235B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19623558 1996-06-13
DE19623558A DE19623558C1 (en) 1996-06-13 1996-06-13 Radial turbine for turbocharger on internal combustion engine

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EP0814235A1 true EP0814235A1 (en) 1997-12-29
EP0814235B1 EP0814235B1 (en) 2000-03-01

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19623558C1 (en) * 1996-06-13 1997-04-10 Mak Maschinenbau Krupp Radial turbine for turbocharger on internal combustion engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR667306A (en) * 1928-02-02 1929-10-15 Rateau Soc Device for adjusting the operating conditions of centrifugal machines
US3426964A (en) * 1966-10-11 1969-02-11 Dresser Ind Compressor apparatus
EP0034915A1 (en) * 1980-02-22 1981-09-02 Holset Engineering Company Limited Radially inward flow turbine
US4802817A (en) * 1987-12-23 1989-02-07 Sundstrand Corporation Centrifugal pump with self-regulating impeller discharge shutter
DE4215301A1 (en) * 1992-05-09 1993-11-11 Mak Maschinenbau Krupp Exhaust gas turbocharger with a radial turbine
DE19623558C1 (en) * 1996-06-13 1997-04-10 Mak Maschinenbau Krupp Radial turbine for turbocharger on internal combustion engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR667306A (en) * 1928-02-02 1929-10-15 Rateau Soc Device for adjusting the operating conditions of centrifugal machines
US3426964A (en) * 1966-10-11 1969-02-11 Dresser Ind Compressor apparatus
EP0034915A1 (en) * 1980-02-22 1981-09-02 Holset Engineering Company Limited Radially inward flow turbine
US4802817A (en) * 1987-12-23 1989-02-07 Sundstrand Corporation Centrifugal pump with self-regulating impeller discharge shutter
DE4215301A1 (en) * 1992-05-09 1993-11-11 Mak Maschinenbau Krupp Exhaust gas turbocharger with a radial turbine
DE19623558C1 (en) * 1996-06-13 1997-04-10 Mak Maschinenbau Krupp Radial turbine for turbocharger on internal combustion engine

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DE59701159D1 (en) 2000-04-06
DE19623558C1 (en) 1997-04-10

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