EP2243932B1 - Axial turbomachine with a guiding nozzle comprising a stage of variable guide vanes - Google Patents
Axial turbomachine with a guiding nozzle comprising a stage of variable guide vanes Download PDFInfo
- Publication number
- EP2243932B1 EP2243932B1 EP10152861.0A EP10152861A EP2243932B1 EP 2243932 B1 EP2243932 B1 EP 2243932B1 EP 10152861 A EP10152861 A EP 10152861A EP 2243932 B1 EP2243932 B1 EP 2243932B1
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- EP
- European Patent Office
- Prior art keywords
- guide
- hub
- guide blades
- blade
- guide blade
- 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.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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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
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
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- 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
Definitions
- the invention relates to an exhaust gas turbocharger turbine with a number of adjustable guide vanes comprehensive in the flow channel, which is bounded on the one hand by an inner hub and the other by an outer vane support, wherein the vanes are rotatably mounted on the one hand in radial bearing bores of the annular vane support and on the other hand with seal their head profile against the guide vane, and with their foot profile against the hub, so the vanes are mounted on one side.
- Adjustable, in particular turbine nozzles are known to be used in turbine and turbocharger construction to better adapt the turbine during operation to the respective operating state.
- For the given characteristic for example, of an exhaust gas turbocharger in connection with a piston engine of high specific power makes it difficult to provide the desired air supply for the entire operating range.
- By opening the turbine cross-section with increasing load according to a given characteristic then the pressure increase can be limited so that at full load the purge air pressure and so that also adjust the ignition pressure and fuel consumption of the normal designed engine.
- the efficiency of the turbine with an adjustable turbine nozzle in particular during operation away from the design point, be raised or lowered.
- adjustable turbine nozzles have a plurality of rotatable about an axis arranged vanes, which are articulated via levers and collars.
- adjustable turbine nozzles for axially and radially traversed turbines. While the radially flowed adjustable turbine nozzle can be relatively simple (see, for example DE 42 18 229 C1 ), the axially flowed through is much more expensive to realize, since in particular the hub and Zuströmgepurtur spherical, ie at least curved must be designed. This is necessary to produce a uniform radial gap at all blade positions toward the hub and inflator housing contours.
- a generic axial flow machine, in particular axial flow turbine shows the DE 42 13 709 A1 .
- the adjustable turbine nozzle offers the possibility of reducing the flow area in the turbine at partial engine load, thereby increasing the air pressure in front of the cylinder.
- the previously known axially flowed adjustable Turbinenleitapparat includes within the annular flow passage bounding walls on the one hand, the inner hub and on the other hand, the hub ring-shaped outer stator vane carrier, which is mounted in the Zuströmgephaseuse the turbine.
- vanes do not jam during "hot” operation, they usually need to be installed with adequate clearance.
- the resulting slit flows at the top and bottom of the vanes can interfere with the main flow in the duct.
- US 2,651,496A discloses a turbine having one of the compliant hub contour and compliant bearing of the vanes.
- the compliant hub contour is provided by an inner ring attached to a flange.
- the flange for the inner ring is connected to another flange by fastening screws.
- DE 42 13 716 A1 discloses a nozzle of an axial turbine with adjustable vanes.
- US 3,999,883 A and GB 878,988 A Further prior art is known.
- the invention has the object of developing an exhaust gas turbocharger such that the components of the diffuser are both smoothly actuated, and allow only small gap flows.
- both above-mentioned requirements should be combined in a new axial flow machine.
- the hub is designed at least in the sealing region of theticianprofiles the vanes with a resilient hub contour and the one-sided storage of the vanes in the vane support in the direction of the vanes is also designed resilient, the flow losses through gaps between the Leitschaufel- and Zuströmgepuruse- or hub contours are reduced and also stresses the components of the adjustable nozzle, caused by sealing elements and thermal expansion of the components are avoided.
- the resilient configuration of the bearing of the guide vanes in the guide vane carrier is achieved by means of a disc spring acting in the direction of the vane axes ensures that the head profile of a vane in each operating condition rests against the Zuströmgephaseusekontur, whereby kept the gap between these two components very low or completely avoided.
- the yielding hub contour is designed in the form of an inner ring fitted in the hub contour, which in the pretensioned state bears against the foot profiles of the guide vanes, this inner ring is always in contact with the guide blade contours.
- the inner ring is flanged to the hub such that it is movable in the radial direction of the inflow housing, that is to say in the direction of the guide blade axis, but is inserted into the hub contour in the axial direction of the inflow housing only with slight play.
- mass flow losses are avoided.
- the inner ring is provided for Monday with a slot, so that here also a thermal expansion is compensated.
- the slot is according to the invention arranged so that it lies between two vanes and is not swept by the blade contour during an adjustment process, so that the losses caused by the slot can be minimized.
- the fact that in addition the slot is covered by means of a sealing plate with respect to the hub interior on the inside, mass flow losses through the slot can be avoided.
- the inner contour of the annular guide carrier, the hub, as well as the head and foot profiles of the vanes are designed to improve the sealing effect according to spherical.
- the inventive design of the diffuser of a generic axial flow machine an increased friction between the components is accepted, jamming of the mechanism, caused by different thermal expansions of the components is effectively prevented.
- the material selection could be such that in the gray cast iron guide vanes made of a high temperature resistant material are stored in a ceramic vane carrier and sealed with their foot profiles against a likewise cast hub. At the same time, it is ensured that the gaps between the guide blade and the inlet housing or hub can be kept as low as possible, as a result of which the flow losses can be reduced to a minimum.
- FIG. 1 a partial longitudinal section through an exhaust gas turbocharger.
- An axial flow-through, annular channel 20 of an axial turbine is limited on the one hand by an inner hub 21 and on the other by an annular guide vane carrier 7 together with Zuströmgephaseuse 8.
- the vane support 7 is mounted in a manner not described in detail in the Zuströmgephase 8.
- the adjustable guide vanes 30 each comprise a guide blade 1, a blade pin 2 and a Schaufeldtehteller 3.
- the blade pin 2 is rotatably mounted in a radial bearing bore of the annular vane support 7 and fixed in a known manner, for example by means of a screwed cap nut or the like on the vane support 7.
- an articulated lever 5 is rotationally fixed by means of a key on the extended pin 2 of the guide vane 30.
- the articulated lever 5 is contacted with the blade journal 2 and the guide blade carrier 7 with the interposition of a plate spring 4, so that the articulation lever 5 is supported against the guide blade carrier 7.
- the plate spring 4 exerts on the blade journal 2 a Biasing force, by which the base profile 31, ie the lower contour of the Leitschaufeiblattes 1 is pressed against the outer surface of the hub 21, so the base profile 31 of the vane 30 is at the stop with the hub 21 and thus seals against the contour of the hub 21.
- the blade journal 2 in the bearing bore of the guide blade carrier 7 almost free of play, but still clamped against thermal expansion in the direction of the axis A of the vane 30 elastic and vibration damping.
- the blade turntable 3 seals the channel 20 against the bearing bore of the guide blade carrier 7.
- the articulated lever 5 is movable in a known manner via a collar 6 by means not shown actuating means.
- the housing contour of the hub 21 is designed at least partially spherical with the inclusion of a hollow or inner space 22.
- an inner ring 9 is fitted into the Nabekontur, which is supported in the prestressed state against the base profile 31 of the vane 30 and is secured by a flange 12 to the hub 21 so that it is in the direction of the axis
- the guide vane 30 is movable, it has only slight play in the contour of the hub 21, that is to say in the axial direction of the channel 20.
- the inner ring 9 itself is provided with a slot 10 which is arranged so that it lies between two guide vanes and is not swept by the blade contour during the adjustment process. In order to prevent mass flow losses through the slot 10, it is covered by the hollow or inner space 22 of the hub 21 seen with a sealing plate 11.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Die Erfindung betrifft eine Abgasturboladerturbine mit einem eine Reihe von verstellbaren Leitschaufeln umfassenden Leitapparat im Strömungskanal, der zum einen durch eine innere Nabe und zum anderen durch einen äußeren Leitschaufelträger begrenzt ist, wobei die Leitschaufeln einerseits in radialen Lagerbohrungen des ringförmigen Leitschaufelträgers drehbar gelagert sind und andererseits mit ihrem Kopfprofil gegen den Leitschaufelträger, sowie mit ihrem Fußprofil gegen die Nabe dichten, also die Leitschaufeln einseitig gelagert sind.The invention relates to an exhaust gas turbocharger turbine with a number of adjustable guide vanes comprehensive in the flow channel, which is bounded on the one hand by an inner hub and the other by an outer vane support, wherein the vanes are rotatably mounted on the one hand in radial bearing bores of the annular vane support and on the other hand with seal their head profile against the guide vane, and with their foot profile against the hub, so the vanes are mounted on one side.
Verstellbare, insbesondere Turbinenleitapparate werden bekanntlich im Turbinen- und Turboladerbau verwendet um die Turbine während des Betriebes besser an den jeweiligen Betriebszustand anpassen zu können. Denn die gegebene Charakteristik beispielsweise eines Abgasturboladers im Zusammenhang mit einer Kolbenmaschine hoher spezifischer Leistung macht es schwierig, für den gesamten Betriebsbereich das erwünschte Luftangebot zur Verfügung zu stellen. So kann durch Verstellen des Leitapparate-Querschnitts der Ladedruck und damit das Luftangebot für einen gegebenen Lastpunkt innerhalb gewisser Grenzen verändert werden, Durch Öffnen des Turbinenquerschnitts mit zunehmender Last nach einer vorgegebenen Charakteristik kann dann der Druckanstieg so begrenzt werden, dass sich bei Volllast der Spülluftdruck und damit auch der Zünddruck und Kraftstoffverbrauch des normal ausgelegten Motors einstellen.Adjustable, in particular turbine nozzles are known to be used in turbine and turbocharger construction to better adapt the turbine during operation to the respective operating state. For the given characteristic, for example, of an exhaust gas turbocharger in connection with a piston engine of high specific power makes it difficult to provide the desired air supply for the entire operating range. Thus, by adjusting the nozzle cross-section of the boost pressure and thus the air supply for a given load point can be changed within certain limits, By opening the turbine cross-section with increasing load according to a given characteristic then the pressure increase can be limited so that at full load the purge air pressure and so that also adjust the ignition pressure and fuel consumption of the normal designed engine.
So kann also der Wirkungsgrad der Turbine mit einem verstellbaren Turbinenleitapparat, insbesondere beim Betrieb abseits vom Auslegungspunkt, angehoben oder abgesenkt werden.Thus, the efficiency of the turbine with an adjustable turbine nozzle, in particular during operation away from the design point, be raised or lowered.
Üblicherweise haben verstellbare Turbinenleitapparate mehrere um eine Achse drehbar angeordnete Leitschaufeln, die über Hebel und Stellringe angelenkt werden.Typically, adjustable turbine nozzles have a plurality of rotatable about an axis arranged vanes, which are articulated via levers and collars.
Grundsätzlich muss zwischen verstellbaren Turbinenleitapparaten für axial und radial durchströmten Turbinen unterschieden werden. Während der radial durchströmte verstellbare Turbinenleitapparat relativ einfach aufgebaut werden kann (siehe beispielsweise
Eine gattungsbildende Axialströmungsmaschine, insbesondere axial durchströmte Turbine zeigt die
Der vorbekannte axial durchströmte verstellbare Turbinenleitapparat umfasst innerhalb der den ringförmigen Strömungskanal begrenzenden Wandungen zum einen die innere Nabe und zum anderen den die Nabe ringförmig umfassenden äußeren Leitschaufelträger, der im Zuströmgehäuse der Turbine eingehängt ist. Die eigentliche Verstellung der Leitschaufel erfolgt über ein Hebelgestänge und vorzugsweise automatisch in Funktion der Betriebsparameter wie Ladedruck, Drehzahl usw.The previously known axially flowed adjustable Turbinenleitapparat includes within the annular flow passage bounding walls on the one hand, the inner hub and on the other hand, the hub ring-shaped outer stator vane carrier, which is mounted in the Zuströmgehäuse the turbine. The actual adjustment of the vane via a lever linkage and preferably automatically in function of the operating parameters such as boost pressure, speed, etc.
Um die Strömungsverluste in einem axial durchströmten verstellbaren Turbinenleitapparat gering zu halten, müssen die Spalte zwischen den Leitschaufeln und dem Zuströmgehäuse, bzw. der Nabe so gering wie möglich gehalten werden. Zu diesem Zwecke sind bereits verschiedene Maßnahmen bekannt geworden, wie z. B. dass die Leitschaufeln einen im Leitschaufelträger gelagerten Drehzapfen, der mit einem Schaufeldrehteller, der gegenüber dem Zuströmgehäuse abgedichtet ist, aufweisen (siehe beispielsweise
Andererseits, damit die Leitschaufeln während des "heißen" Betriebes nicht klemmen, müssen sie in der Regel mit angemessenem Spiel eingebaut werden. Um eine leichte Verstellbarkeit auch bei Lastwechsel, also bei unterschiedlicher thermischer Ausdehnung der Komponenten des Leitapparates gewährleisten zu können, werden bisher ausreichend große Spalte in Kauf genommen, die jedoch, d. h. die daraus resultierenden Spaltströmungen am Kopf und am Fuß der Leitschaufeln sich sehr störend auf die Hauptströmung im Kanal auswirken können.On the other hand, so that the vanes do not jam during "hot" operation, they usually need to be installed with adequate clearance. In order to ensure easy adjustability even with load changes, so with different thermal expansion of the components of the diffuser, so far sufficiently large gaps are accepted, however, d. H. the resulting slit flows at the top and bottom of the vanes can interfere with the main flow in the duct.
Diese beiden Forderungen nach einerseits einer Minimierung der Spaltquerschnite und andererseits einer leichten Verstellbarkeit der Komponenten widersprechen sich, weshalb die in der Vergangenheit realisierten verstellbaren axial durchströmten Turbinenleitapparate entweder leichtgängig waren oder geringe Strömungsverluste aufwiesen.These two requirements for on the one hand a minimization of the Spaltquerschnite and on the other hand a slight adjustability of the components contradict each other, which is why the realized in the past adjustable axial flow turbine nozzles were either smooth or had low flow losses.
Der Erfindung liegt die Aufgabe zugrunde eine Abgasturboladerturbine derart weiterzubilden, dass die Komponenten des Leitapparates sowohl leichtgängig betätigbar sind, als auch nur geringe Spaltströmungen zulassen. Es sollen also beide oben genannten Forderungen in einer neuen Axialströmungsmaschine vereint werden.The invention has the object of developing an exhaust gas turbocharger such that the components of the diffuser are both smoothly actuated, and allow only small gap flows. Thus, both above-mentioned requirements should be combined in a new axial flow machine.
Die Lösung der Aufgabe wird erfindungsgemäß durch die kennzeichnenden Merkmale des Patentanspruchs 1 gelöst.The solution of the problem is achieved by the characterizing features of claim 1.
Dadurch dass die Nabe zumindest im Dichtbereich des Fußprofiles der Leitschaufeln mit einer nachgiebigen Nabenkontur ausgeführt ist und die einseitige Lagerung der Leitschaufeln im Leitschaufelträger in Richtung der Leitschaufelachsen ebenfalls nachgiebig ausgestaltet ist, können die Strömungsverluste durch Spalte zwischen den Leitschaufel- und der Zuströmgehäuse- bzw. Nabenkonturen reduziert werden und außerdem Verspannungen der Komponenten des verstellbaren Leitapparates, verursacht durch Dichtungselemente und durch thermische Ausdehnung der Komponenten vermieden werden.The fact that the hub is designed at least in the sealing region of the Fußprofiles the vanes with a resilient hub contour and the one-sided storage of the vanes in the vane support in the direction of the vanes is also designed resilient, the flow losses through gaps between the Leitschaufel- and Zuströmgehäuse- or hub contours are reduced and also stresses the components of the adjustable nozzle, caused by sealing elements and thermal expansion of the components are avoided.
Dadurch dass erfindungsgemäß die nachgiebige Ausgestaltung der Lagerung der Leitschaufeln im Leitschaufelträger mittels jeweils einer in Richtung der Leitschaufelachsen wirkenden Tellerfeder erreicht wird, ist gewährleistet, dass das Kopfprofil einer Leitschaufel in jedem Betriebszustand an der Zuströmgehäusekontur anliegt, wodurch der Spalt zwischen diesen beiden Komponenten sehr gering gehalten oder ganz vermieden werden kann.
Dadurch dass die nachgiebige Nabenkontur in Form eines in die Nabenkontur eingepassten Innenrings, der im vorgespannten Zustand sich gegen die Fußprofile der Leitschaufeln abstützt, ausgeführt ist, liegt dieser Innenring immer an den Leitschaufelkonturen an. Der Innenring ist derart an der Nabe angeflanscht, dass er in radialer Richtung des Zuströmgehäuses, also in Richtung der Leitschaufelachse beweglich ist, in axialer Richtung des Zuströmgehäuses jedoch nur mit geringem Spiel in die Nabenkontur eingesetzt ist. Durch diese Maßnahme werden wiederum Massenstromverluste vermieden.
Zudem ist der Innenring zur Montag mit einem Schlitz versehen, so dass auch hier eine thermische Ausdehnung ausgleichbar ist. Der Schlitz ist erfindungsgemäß so angeordnet, dass er zwischen zwei Leitschaufeln liegt und während eines Verstellvorganges nicht durch die Schaufelkontur überstrichen wird, so dass die durch den Schlitz verursachten Verluste minimiert werden können.
Dadurch dass zudem der Schlitz mittels eines Dichtbleches bezüglich des Nabeninnenraums an der Innenseite abgedeckt ist, sind Massenstromverluste durch den Schlitz vermeidbar.
Im bevorzugten Ausführungsbeispiel sind Innenkontur des ringförmigen Leitschaufelträgers, die Nabe, sowie die Kopf- und Fußprofile der Leitschaufeln zur Verbesserung der Dichtwirkung entsprechend kugelförmig ausgebildet.The fact that according to the invention the resilient configuration of the bearing of the guide vanes in the guide vane carrier is achieved by means of a disc spring acting in the direction of the vane axes ensures that the head profile of a vane in each operating condition rests against the Zuströmgehäusekontur, whereby kept the gap between these two components very low or completely avoided.
Due to the fact that the yielding hub contour is designed in the form of an inner ring fitted in the hub contour, which in the pretensioned state bears against the foot profiles of the guide vanes, this inner ring is always in contact with the guide blade contours. The inner ring is flanged to the hub such that it is movable in the radial direction of the inflow housing, that is to say in the direction of the guide blade axis, but is inserted into the hub contour in the axial direction of the inflow housing only with slight play. By this measure again mass flow losses are avoided.
In addition, the inner ring is provided for Monday with a slot, so that here also a thermal expansion is compensated. The slot is according to the invention arranged so that it lies between two vanes and is not swept by the blade contour during an adjustment process, so that the losses caused by the slot can be minimized.
The fact that in addition the slot is covered by means of a sealing plate with respect to the hub interior on the inside, mass flow losses through the slot can be avoided.
In the preferred embodiment, the inner contour of the annular guide carrier, the hub, as well as the head and foot profiles of the vanes are designed to improve the sealing effect according to spherical.
Durch die erfindungsgemäße Ausbildung des Leitapparates einer gattungsbildenden Axialströmungsmaschine wird zwar eine erhöhte Reibung zwischen den Komponenten in Kauf genommen, ein Verklemmen der Mechanik, hervorgerufen durch unterschiedliche thermische Ausdehnungen der Komponenten ist jedoch wirksam verhindert. Die Materialauswahl könnte so aussehen, dass im Graugussverfahren aus einem hochwarmfesten Material hergestellte Leitschaufeln in einem Keramik-Leitschaufelträger gelagert sind und mit ihren Fußprofilen gegen eine ebenfalls gegossene Nabe dichten. Gleichzeitig ist sichergestellt, dass die Spalte zwischen Leitschaufel und Zuströmgehäuse, bzw. Nabe so gering wie möglich gehalten werden können, wodurch die Strömungsverluste auf ein Minimum reduzierbar sind.Although the inventive design of the diffuser of a generic axial flow machine, an increased friction between the components is accepted, jamming of the mechanism, caused by different thermal expansions of the components is effectively prevented. The material selection could be such that in the gray cast iron guide vanes made of a high temperature resistant material are stored in a ceramic vane carrier and sealed with their foot profiles against a likewise cast hub. At the same time, it is ensured that the gaps between the guide blade and the inlet housing or hub can be kept as low as possible, as a result of which the flow losses can be reduced to a minimum.
Eine Ausführungsform der Erfindung wird anhand der Zeichnung näher erläutert. Es zeigt die einzige
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente, insbesondere die Ansicht des Verstellleitapparates gezeigt.Only the elements essential to the understanding of the invention, in particular the view of the adjusting device, are shown.
Ein axial durchströmter, ringförmiger Kanal 20 einer Axialturbine ist zum einen durch eine innere Nabe 21 und zum anderen durch einen ringförmigen Leitschaufelträger 7 mitsamt Zuströmgehäuse 8 begrenzt. Der Leitschaufelträger 7 ist auf nicht näher beschriebene Art im Zuströmgehäuse 8 eingehängt.An axial flow-through,
Die verstellbaren Leitschaufeln 30 umfassen jeweils ein Leitschaufelblatt 1, einen Schaufelzapfen 2 und einen Schaufeldtehteller 3. Der Schaufelzapfen 2 ist in einer radialen Lagerbohrung des ringförmigen Leitschaufelträgers 7 drehbar gelagert und in bekannter Weise beispielsweise mittels einer aufgeschraubten Kronmutter oder ähnlichem am Leitschaufelträger 7 festgelegt. An der Außenseite des Leitschaufelträgers 7 ist auf dem verlängerten Zapfen 2 der Leitschaufel 30 ein Anlenkhebel 5 mittels einer Passfeder drehfest aufgesetzt. Der Anlenkhebel 5 ist mit dem Schaufelzapfen 2 und dem Leitschaufelträger 7 unter Zwischenschaltung einer Tellerfeder 4 kontaktiert, so dass der Anlenkhebel 5 sich gegen den Leitschaufelträger 7 abstützt. Die Tellerfeder 4 übt auf den Schaufelzapfen 2 eine Vorspannkraft aus, durch die das Fußprofil 31, d. h. die untere Kontur des Leitschaufeiblattes 1 gegen die äußere Oberfläche der Nabe 21 gedrückt wird, also das Fußprofil 31 der Leitschaufel 30 am Anschlag mit der Nabe 21 ist und so gegen die Kontur der Nabe 21 abdichtet. Dadurch ist der Schaufelzapfen 2 in der Lagerbohrung des Leitschaufelträgers 7 nahezu spielfrei, aber dennoch gegen Wärmedehnung in Richtung der Achse A der Leitschaufel 30 elastisch und schwingungsdämpfend eingespannt. Der Schaufeldrehteller 3 dichtet den Kanal 20 gegen die Lagerbohrung des Leitschaufelträgers 7 ab.The adjustable guide vanes 30 each comprise a guide blade 1, a
Der Anlenkhebel 5 ist in bekannter Weise über einen Stellring 6 durch nicht weiter gezeigte Betätigungsmittel bewegbar.The articulated
Die Gehäusekontur der Nabe 21 ist zumindest teilweise kugelförmig unter Einschließung eines Hohl- oder Innenraums 22 gestaltet.The housing contour of the
Im Dichtbereich 23 des Fußprofils 31 der Leitschaufel 30 ist ein Innenring 9 in die Nabekontur eingepasst, der im vorgespannten Zustand sich gegen das Fußprofil 31 der Leitschaufel 30 abstützt und mittels eines Flansches 12 an der Nabe 21 so befestigt ist, dass er in Richtung der Achse A der Leitschaufel 30 zwar beweglich ist, jedoch in der Kontur der Nabe 21, also in axialer Richtung des Kanals 20 ein nur geringes Spiel aufweist. Dazu ist die Kontaktierung zwischen Flansch 12 und Innenring 9 beispielsweise lediglich verzahnt.In the
Der innenring 9 selbst ist mit einem Schlitz 10 versehen, der so angeordnet ist, dass er zwischen zwei Leitschaufeln liegt und beim Verstellvorgang nicht durch die Schaufelkontur überstrichen wird. Um Massenstromverluste durch den Schlitz 10 zu verhindern, ist er vom Hohl- bzw. Innenraum 22 der Nabe 21 her gesehen mit einem Dichtblech 11 abgedeckt.The
Die Erfindung wäre im übrigen bei Verdichtern sinngemäß anwendbar. Ferner soll der Einsatz bei Axialgebläsen mit eingeschlossen sein.The invention would otherwise apply mutatis mutandis to compressors. Furthermore, the use should be included in axial fans.
- 11
- Leitschaufelblattairfoil
- 22
- Schaufelzapfenbucket pins
- 33
- SchaufeldrehtellerScoop turntable
- 44
- TellerfederBelleville spring
- 55
- AnlenkhebelFeedback lever
- 66
- Stellringcollar
- 77
- Leitschaufelträgerguide vane
- 88th
- Zuströmgehäuseinflow housing
- 99
- Innenringinner ring
- 1010
- Schlitzslot
- 1111
- Dichtblechsealing plate
- 1212
- Flanschflange
- 2020
- Strömungskanalflow channel
- 2121
- Nabehub
- 2222
- Hohl- bzw. InnenraumHollow or interior
- 2323
- Dichtbereichsealing area
- 3030
- Leitschaufelvane
- 3131
- Fußprofil der LeitschaufelBase profile of the vane
- 3232
- Kopfprofil der LeitschaufelHead profile of the vane
- AA
- Leitschaufelachsevane shaft
Claims (3)
- An exhaust gas turbocharger turbine,
with a flow passage (20),
with a guide apparatus comprising a series of adjustable guide blades (30) in the flow passage (20),
wherein the flow passage (20) is delimited on the one hand by an inner hub (21) and on the other hand by an outer, annular guide blade carrier (7),
wherein the guide blades comprise a guide blade leaf (1) with a root profile (31) and a head profile (32), a blade tenon (2), a guide blade turntable (3) and a guide blade axis (A),
wherein the guide blades on the one hand in the region of their head profiles (32) are rotatably mounted in radial bearing bores of the annular guide blade carrier (7) and on the other hand seal the root profiles (31) of the guide blades against the hub (21),
wherein the hub (21) is embodied with a resilient hub contour at least in the sealing region (23) of the root profiles (31) of the guide blades (30), which is embodied in the form of an inner ring (9) provided with a slot (10) fitted into the hub contour, which in the preloaded state supports itself against the root profile (31) of the guide blades (30), and which by means of a flange (12) is attached to the hub (21) so that it is moveable in the direction of the guide blade axis (A) of the guide blades (30) but on the contour of the hub (21) only has little play in the axial direction of the flow passage (20), for the purpose of which a contacting between flange (12) and inner ring (9) is merely serrated, and
wherein the mounting of the guide blades (30) in the direction of the guide blade axes (A) is likewise configured resiliently (4),
characterized in that
the mounting of the guide blades (30) is configured resiliently (4) by means of a disc spring (4) acting in each case in the direction of the guide blade axes (A), and in that
the slot (10) of the inner ring (9) is arranged so that it is positioned between two guide blades (30) and is not swept during the adjusting movement of the guide blade (30). - The exhaust gas turbocharger turbine according to Claim 1, characterized in that the inner contour of the annular guide blade carrier (7), the hub (21), and the head and root profiles (31 and 32) of the guide blades (30) are formed suitably spherically for improving the sealing effect.
- The exhaust gas turbocharger turbine according to Claim 1, characterized in that the slot (10) is covered regarding the hub interior space (22) by means of a sealing plate (11).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10016745A DE10016745B4 (en) | 2000-04-04 | 2000-04-04 | Axial flow machine with a nozzle comprising a number of adjustable guide vanes |
| EP01108009A EP1143111B8 (en) | 2000-04-04 | 2001-03-29 | Axial turbomachine with variable guide vanes |
Related Parent Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01108009A Division EP1143111B8 (en) | 2000-04-04 | 2001-03-29 | Axial turbomachine with variable guide vanes |
| EP01108009.0 Division | 2001-03-29 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP2243932A2 EP2243932A2 (en) | 2010-10-27 |
| EP2243932A3 EP2243932A3 (en) | 2011-01-26 |
| EP2243932B1 true EP2243932B1 (en) | 2019-03-13 |
Family
ID=7637566
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01108009A Expired - Lifetime EP1143111B8 (en) | 2000-04-04 | 2001-03-29 | Axial turbomachine with variable guide vanes |
| EP10152861.0A Expired - Lifetime EP2243932B1 (en) | 2000-04-04 | 2001-03-29 | Axial turbomachine with a guiding nozzle comprising a stage of variable guide vanes |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01108009A Expired - Lifetime EP1143111B8 (en) | 2000-04-04 | 2001-03-29 | Axial turbomachine with variable guide vanes |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6547521B2 (en) |
| EP (2) | EP1143111B8 (en) |
| JP (1) | JP2001289004A (en) |
| KR (1) | KR100824894B1 (en) |
| CN (1) | CN1278019C (en) |
| DE (2) | DE10016745B4 (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005040574A1 (en) * | 2005-08-26 | 2007-03-15 | Rolls-Royce Deutschland Ltd & Co Kg | Gap control device for a gas turbine |
| CH698928B1 (en) * | 2006-05-18 | 2009-12-15 | Man Diesel Se | Guide apparatus for an axially flow turbine of an exhaust turbocharger. |
| DE102007021448B4 (en) * | 2006-05-18 | 2012-06-28 | Man Diesel & Turbo Se | Diaphragm for an exhaust gas turbocharger operated with heavy oil reciprocating internal combustion engine |
| US9890655B2 (en) | 2008-09-18 | 2018-02-13 | Siemens Aktiengesellschaft | Adjusting device for variable guide vanes and method of operation |
| US8668445B2 (en) * | 2010-10-15 | 2014-03-11 | General Electric Company | Variable turbine nozzle system |
| CN102606223B (en) * | 2011-01-24 | 2014-12-17 | 中国石油化工集团公司 | Flue gas turbine |
| DE102011119879A1 (en) * | 2011-12-01 | 2013-06-06 | Ihi Charging Systems International Gmbh | Fluid energy machine, in particular for an exhaust gas turbocharger of a motor vehicle |
| DE102016110269A1 (en) | 2016-06-03 | 2017-12-07 | Man Diesel & Turbo Se | Axial turbine of a turbocharger and turbocharger |
| DE102016114253A1 (en) | 2016-08-02 | 2018-02-08 | Man Diesel & Turbo Se | Axial turbine of a turbocharger and turbocharger |
| DE102018101527A1 (en) | 2018-01-24 | 2019-07-25 | Man Energy Solutions Se | axial flow |
| CN112989720B (en) * | 2021-03-04 | 2022-05-06 | 上海交通大学 | Method for realizing optimization of radial clearance of hub by using cantilever stator blades of axial-flow compressor |
Family Cites Families (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE514728A (en) * | 1951-10-10 | |||
| CH360074A (en) * | 1957-10-31 | 1962-02-15 | Maschf Augsburg Nuernberg Ag | Diffuser with adjustable blades during operation, especially for gas turbines |
| US3542484A (en) * | 1968-08-19 | 1970-11-24 | Gen Motors Corp | Variable vanes |
| FR2030895A5 (en) * | 1969-05-23 | 1970-11-13 | Motoren Turbinen Union | |
| US3999883A (en) * | 1975-07-02 | 1976-12-28 | General Motors Corporation | Variable turbomachine stator |
| DE2740192C2 (en) | 1977-09-07 | 1981-11-12 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Gap seal for an axially flow-around guide vane of a turbomachine that is adjustable about its longitudinal axis |
| DE2931766C2 (en) * | 1979-08-04 | 1982-08-05 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Sealing device for the free blade ends of an adjustable diffuser of a gas turbine |
| GB2210935B (en) * | 1987-10-10 | 1992-05-27 | Rolls Royce Plc | Variable stator vane assembly |
| GB8914577D0 (en) * | 1989-06-24 | 1989-08-16 | Ici Plc | Catalysts |
| DE4017861A1 (en) * | 1990-06-02 | 1991-12-05 | Mtu Muenchen Gmbh | CONDUCTING WREATH FOR A GAS TURBINE |
| DE4213709A1 (en) | 1992-04-25 | 1993-10-28 | Asea Brown Boveri | Turbine with axial flow |
| DE4213716A1 (en) * | 1992-04-25 | 1993-10-28 | Asea Brown Boveri | Turbine with direct axial flow - has guide blades, which are axially movable in adjusting axis |
| DE4218229C1 (en) | 1992-06-03 | 1993-03-04 | Man B & W Diesel Ag, 8900 Augsburg, De | Turbocharger with radial flow through impeller - has blade retaining recesses, into which blades are insertable after axial shift of adjuster |
| DE4237031C1 (en) | 1992-11-03 | 1994-02-10 | Mtu Muenchen Gmbh | Adjustable guide vane |
| US5672047A (en) * | 1995-04-12 | 1997-09-30 | Dresser-Rand Company | Adjustable stator vanes for turbomachinery |
| JPH09203371A (en) * | 1996-01-26 | 1997-08-05 | Hitachi Ltd | Hydraulic apparatus capable of coping with sediment abrasion |
| FR2775731B1 (en) * | 1998-03-05 | 2000-04-07 | Snecma | CIRCULAR STAGE OF BLADES AT INTERIOR ENDS JOINED BY A CONNECTING RING |
-
2000
- 2000-04-04 DE DE10016745A patent/DE10016745B4/en not_active Expired - Fee Related
-
2001
- 2001-03-29 DE DE50115388T patent/DE50115388D1/en not_active Expired - Lifetime
- 2001-03-29 EP EP01108009A patent/EP1143111B8/en not_active Expired - Lifetime
- 2001-03-29 EP EP10152861.0A patent/EP2243932B1/en not_active Expired - Lifetime
- 2001-03-30 JP JP2001100202A patent/JP2001289004A/en active Pending
- 2001-04-03 KR KR1020010017559A patent/KR100824894B1/en active IP Right Grant
- 2001-04-04 US US09/825,955 patent/US6547521B2/en not_active Expired - Lifetime
- 2001-04-04 CN CNB011124733A patent/CN1278019C/en not_active Expired - Lifetime
Non-Patent Citations (1)
| Title |
|---|
| None * |
Also Published As
| Publication number | Publication date |
|---|---|
| DE50115388D1 (en) | 2010-04-29 |
| CN1316582A (en) | 2001-10-10 |
| KR20010095249A (en) | 2001-11-03 |
| DE10016745A1 (en) | 2001-10-18 |
| EP1143111A2 (en) | 2001-10-10 |
| EP1143111A3 (en) | 2003-05-07 |
| JP2001289004A (en) | 2001-10-19 |
| US6547521B2 (en) | 2003-04-15 |
| DE10016745B4 (en) | 2005-05-19 |
| EP1143111B8 (en) | 2010-05-19 |
| US20010026758A1 (en) | 2001-10-04 |
| EP2243932A3 (en) | 2011-01-26 |
| KR100824894B1 (en) | 2008-04-23 |
| EP2243932A2 (en) | 2010-10-27 |
| EP1143111B1 (en) | 2010-03-17 |
| CN1278019C (en) | 2006-10-04 |
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