EP2229508A1 - Control device for blade adjustment - Google Patents

Control device for blade adjustment

Info

Publication number
EP2229508A1
EP2229508A1 EP09701799A EP09701799A EP2229508A1 EP 2229508 A1 EP2229508 A1 EP 2229508A1 EP 09701799 A EP09701799 A EP 09701799A EP 09701799 A EP09701799 A EP 09701799A EP 2229508 A1 EP2229508 A1 EP 2229508A1
Authority
EP
European Patent Office
Prior art keywords
guide
vanes
exhaust gas
turbine
radius
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.)
Withdrawn
Application number
EP09701799A
Other languages
German (de)
French (fr)
Inventor
Matthias Jarusel
Peter Neuenschwander
Bent Phillipsen
Thorsten Bosse
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems 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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP09701799A priority Critical patent/EP2229508A1/en
Publication of EP2229508A1 publication Critical patent/EP2229508A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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 the field of turbomachines, in particular the turbocharger for supercharged internal combustion engines.
  • Exhaust gas turbochargers are used to increase the performance of internal combustion engines (reciprocating engines).
  • An exhaust gas turbocharger consists of an exhaust gas turbine in the exhaust gas stream of the internal combustion engine and a compressor in the intake tract of the internal combustion engine.
  • the turbine wheel of the exhaust gas turbine is set in rotation by the exhaust gas flow of the internal combustion engine and drives the impeller of the compressor via a shaft.
  • the compressor increases the pressure in the intake tract of the internal combustion engine, so that when sucking a larger amount of air enters the combustion chambers.
  • Exhaust gas turbines are also used as power turbines. In this case, they do not drive the compressor of an exhaust gas turbocharger via the shaft, but rather a generator or via a clutch another mechanical useful part.
  • the flow components of the turbocharger have been developed for reasons of economy for high specific flow rates (high mass flow compared to the geometric size).
  • the blades of the turbines of such turbomachinery can be exposed to high vibration excitations.
  • a very precise coordination of the guide device (nozzle ring) and the blade geometry should be made.
  • the guide blade vanes of the rotor blade are a periodic disturbance with frequency equal to number of vanes by number of revolutions. If this frequency coincides with natural frequencies of the blades, resonances can occur. The alternating voltages in these resonances can possibly lead to material damage. It is known that the resonant amplitudes increase with decreasing opening of the vanes. This can lead to the limitation of the permissible openings of the guide vanes. With the variable turbine geometry, it is important to have a large adjustment range of the vane opening. If the range of permissible vane openings has to be restricted by impermissible resonances, the benefits of the variable turbine geometry are reduced.
  • variable guide device is built in exhaust gas turbochargers for large engines usually as a separate module and the gas inlet and gas outlet housings of
  • the object of the invention is to optimize an adjustable guide device for a turbomachine, such as an exhaust gas turbine, such that the fastening means used for attachment to the adjacent housing can be mounted independently of the orientation of the guide device to the housing.
  • the idea of the invention consists in the displacement of the attachment for the cultivation of the guide device in the region radially outside the guide vanes, in particular radially outside the guide vane shafts.
  • the circumferential position of the vanes can be freely selected within the predetermined angle. There are no collisions between the vanes and the fasteners.
  • the vanes can be distributed both evenly and unevenly around the circumference.
  • the vanes are realized by uneven distribution of the guide vane receptacle in the relief ring, carrier ring and Nutenring.
  • FIG. 1 shows a section through an exhaust gas turbine with an adjustable guide device according to the prior art
  • Fig. 2 shows a section through an exhaust gas turbine with an inventively designed, adjustable guide.
  • Fig. 1 shows a detail of a conventional axial turbine of an exhaust gas turbocharger.
  • the turbine wheel 10 is arranged on the shaft 30 rotatably mounted in a bearing housing about the axis A.
  • Turbine wheel 10 includes a plurality of blades 11 which are distributed along the circumference at the radially outer edge of the turbine wheel.
  • the exhaust gas flow in the flow channel is indicated by arrows.
  • the blades of the turbine wheel are flowed in the axial direction.
  • an adjustable guide device upstream of the rotor blades 11 of the exhaust gas turbine, an adjustable guide device (adjustable turbine geometry) is arranged.
  • This adjustable guide device comprises a plurality of guide vanes 41, which each have a shaft 42.
  • Each of the guide vanes 41 is mounted in each case with its shaft 42 about the axis B rotatably in the housing.
  • the housing of the guide device essentially comprises a support ring 40, which encloses the flow channel in an annular manner. Towards the flow channel, the support ring 40 can still enclose a relief ring 45.
  • the shafts 42 of the vanes 41 are arranged in the support ring 40 in holes provided for this purpose. The holes extend, as the shafts 42 of the vanes 41, substantially in the radial direction.
  • the support ring is fastened with fastening means 50 on the gas outlet housing 20. As fasteners bolts or screws are used.
  • the adjustable guide device further comprises an adjusting ring 43 and per guide vane an adjusting lever 44.
  • the adjusting ring 43 is moved in the circumferential direction.
  • the adjustment levers 44 transmit the rotational movement to the shafts 42 of the vanes.
  • the fastening means are arranged radially outside the bearing points 46 of the guide blade shafts 42, or radially outside the free ends of the guide blade shafts.
  • the radius r 2 outside which the fastening means 50 are located is thus larger than the radius n within which the guide blade shafts are located.
  • the guide vanes 41 can be both uniformly and non-uniformly distributed along the circumference of the carrier ring, without thereby the fastening means 50 and the shafts 42 of the vanes intersect each other.
  • the non-uniform arrangement of the guide vanes 41 is realized by non-uniform distribution of the guide vane receptacle in the relief ring 45, carrier ring 40 and adjusting ring.
  • the support ring 40 can be positioned at any angle with respect to the gas outlet housing 20 even with irregularly distributed vanes, which allow distributed along the circumference arranged holes for the fasteners. The circumferential position of the guide vanes can thus be freely selected within the predetermined angle.
  • the gas inlet housing 21 can be connected radially within the adjusting lever 44 with separate fastening means with the support ring 40, as indicated in Fig. 2.

Abstract

The fastening for the attachment of the control device (40) to the gas outlet housing (20) is positioned in the region radially outside the guide blades (41, 42). The circumferential position of the guide blades may thereby be freely selected within the predefined angle. No collisions occur between the guide blades (41, 42) and the fastening means (50).

Description

LEITVORRICHTUNG FÜR SCHAUFELVERSTELLUNG LEAD DEVICE FOR SHAFT ADJUSTMENT
B E S C H R E I B U N GDESCRIPTION
Technisches GebietTechnical area
Die Erfindung bezieht sich auf das Gebiet der Strömungsmaschinen, insbesondere der Abgasturbolader für aufgeladene Brennkraftmaschinen.The invention relates to the field of turbomachines, in particular the turbocharger for supercharged internal combustion engines.
Sie betrifft die Befestigung einer Leitvorrichtung an einem Gehäuse einer solchen Strömungsmaschine befestigt wird.It relates to the attachment of a guide device to a housing of such a turbomachine is attached.
Stand der TechnikState of the art
Abgasturbolader werden zur Leistungssteigerung von Brennkraftmaschinen (Hubkolbenmotoren) eingesetzt. Ein Abgasturbolader besteht aus einer Abgasturbine im Abgasstrom der Brennkraftmaschine und einem Verdichter im Ansaugtrakt der Brennkraftmaschine. Das Turbinenrad der Abgasturbine wird vom Abgasstrom der Brennkraftmaschine in Rotation versetzt und treibt über eine Welle das Laufrad des Verdichters an. Der Verdichter erhöht den Druck im Ansaugtrakt der Brennkraftmaschine, so dass beim Ansaugen eine größere Menge Luft in die Brennkammern gelangt. Abgasturbinen werden auch als Nutzturbinen eingesetzt. In diesem Fall treiben sie über die Welle nicht den Verdichter eines Abgasturboladers an, sondern einen Generator oder über eine Kupplung ein anderes, mechanisches Nutzteil.Exhaust gas turbochargers are used to increase the performance of internal combustion engines (reciprocating engines). An exhaust gas turbocharger consists of an exhaust gas turbine in the exhaust gas stream of the internal combustion engine and a compressor in the intake tract of the internal combustion engine. The turbine wheel of the exhaust gas turbine is set in rotation by the exhaust gas flow of the internal combustion engine and drives the impeller of the compressor via a shaft. The compressor increases the pressure in the intake tract of the internal combustion engine, so that when sucking a larger amount of air enters the combustion chambers. Exhaust gas turbines are also used as power turbines. In this case, they do not drive the compressor of an exhaust gas turbocharger via the shaft, but rather a generator or via a clutch another mechanical useful part.
Die jüngste Entwicklung im Bereich moderner Hubkolbenmotoren wird von der Reduktion der Emissionen, der Kosten und des Brennstoffverbrauchs getrieben. DasThe recent development in the field of modern reciprocating engines is driven by the reduction of emissions, costs and fuel consumption. The
Aufladesystem des Motors trägt dabei massgeblich zur Erreichung derCharging system of the engine contributes significantly to the achievement of
Entwicklungsziele bei. In der Vergangenheit sind bei Grossmotoren überwiegendDevelopment goals. In the past, large engines are predominant
Abgasturbolader mit Turbinen- und Verdichterkomponenten mit festen Geometrien verwendet worden (Fix-Geometrien). Diese Geometrien sind für jeden einzelnen Motor ausgelegt und angepasst worden. Während dem Betrieb des Motors waren sie aber unveränderlich. Um zukünftig eine noch bessere Anpassung des Abgasturboladers an den Motor während dem Betrieb zu ermöglichen, steht der Einsatz von im Betrieb verstellbaren (oder variablen) Turbinengeometrien (VTG) vermehrt zur Diskussion. Dabei wird die Öffnung der Leitschaufeln der Leitvorrichtung der Abgasturbine durch eine Verdrehung der Leitschaufeln variiert. Die Verwendung von verstellbaren Turbinengeometrien ist bekannter Stand der Technik und insbesondere im Bereich der Kleinmotoren, wie sie etwa in Personenkraftwagen eingesetzt werden, weit verbreitet. Bei den Grossmotoren werden bereits heute bei Gasmotoren, die eine genaue Regelung des Brennstoff/Luft-Verhältnisses erfordern, variable Turbinengeometrien verwendet. In der Zukunft ist mit verbreitetem Einsatz von variablen Turbinengeometrien bei Grossmotoren zu rechnen.Exhaust gas turbocharger with turbine and compressor components with fixed geometries been used (fixed geometries). These geometries have been designed and adapted for each individual engine. During the operation of the engine but they were unchanging. In the future an even better adaptation of the exhaust gas turbocharger To enable the engine during operation, the use of adjustable in operation (or variable) turbine geometries (VTG) is increasingly up for discussion. In this case, the opening of the guide vanes of the guide device of the exhaust gas turbine is varied by a rotation of the guide vanes. The use of variable turbine geometries is well known in the art and particularly in the field of small engines, such as those used in passenger cars. In the case of large engines, variable turbine geometries are already being used today for gas engines which require precise regulation of the fuel / air ratio. In the future, widespread use of variable turbine geometries in large engines is to be expected.
Die Strömungskomponenten des Turboladers sind aus Gründen der Wirtschaftlichkeit für hohe spezifische Durchsätze entwickelt worden (hoher Massenstrom im Vergleich zur geometrischen Grosse). Die Laufschaufeln der Turbinen solcher Turbomaschinen können hohen Schwingungsanregungen ausgesetzt sein. Um ein sicheres Betriebsverhalten zu gewährleisten, sollte bei der Entwicklung der Turbine eine sehr genaue Abstimmung von Leitvorrichtung (Düsenring) und Laufschaufelgeometrie gemacht werden.The flow components of the turbocharger have been developed for reasons of economy for high specific flow rates (high mass flow compared to the geometric size). The blades of the turbines of such turbomachinery can be exposed to high vibration excitations. In order to ensure a safe operating behavior, during the development of the turbine, a very precise coordination of the guide device (nozzle ring) and the blade geometry should be made.
Insbesondere kann das Problem auftreten, dass die Leitschaufeln der Leitvorrichtung für die Laufschaufeln des Turbinenrades eine periodische Störung darstellen, mit Frequenz gleich Leitschaufelzahl mal Drehzahl. Stimmt diese Frequenz mit Eigenfrequenzen der Laufschaufeln überein, können Resonanzen entstehen. Die Wechselspannungen in diesen Resonanzen können allenfalls zu Materialschäden führen. Es ist bekannt, dass die Resonanzamplituden mit abnehmender Öffnung der Leitschaufeln ansteigen. Dies kann zur Begrenzung der zulässigen Öffnungen der Leitschaufeln führen. Bei der variablen Turbinengeometrie ist es wichtig, einen grossen Verstellbereich der Leitschaufelöffnung zu Verfügung zu haben. Falls der Bereich der zulässigen Leitschaufelöffnungen durch unzulässige Resonanzen eingeschränkt werden muss, reduziert sich der Nutzen der variablen Turbinengeometrie.In particular, there may be the problem that the guide blade vanes of the rotor blade are a periodic disturbance with frequency equal to number of vanes by number of revolutions. If this frequency coincides with natural frequencies of the blades, resonances can occur. The alternating voltages in these resonances can possibly lead to material damage. It is known that the resonant amplitudes increase with decreasing opening of the vanes. This can lead to the limitation of the permissible openings of the guide vanes. With the variable turbine geometry, it is important to have a large adjustment range of the vane opening. If the range of permissible vane openings has to be restricted by impermissible resonances, the benefits of the variable turbine geometry are reduced.
Aus "Theoretical and Experimental Analysis of the Reduction of Rotor Blade Vibration in Turbomachinery Through the use of Modified Stator Vane Spacing"; R. H. Kemp, M. H.From "Theoretical and Experimental Analysis of the Reduction of Rotor Blade Vibration in Turbomachinery Through the Use of Modified Stator Vane Spacing"; R.H. Kemp, M.H.
Hirschberg, W. C. Morgan. NACA Technical Note 4374, 1958 ist bekannt, dass eine ungleichmässige Verteilung der Umfangsposition der Leitschaufeln eine deutliche Reduktion der Resonanzamplituden bewirken kann. Die ungleichmässige Anordnung der Leitschaufeln wird heute bei vielen Turbomaschinen verwendet, um Resonanzamplituden zu reduzieren.Hirschberg, WC Morgan. NACA Technical Note 4374, 1958 it is known that an uneven distribution of the circumferential position of the vanes a significant Can cause reduction of the resonance amplitudes. The uneven arrangement of the vanes is used today in many turbomachines to reduce resonance amplitudes.
Die variable Leitvorrichtung (VTG) wird bei Abgasturboladern für Grossmotoren in der Regel als separates Modul gebaut und an den Gasein- und Gasaustrittsgehäusen derThe variable guide device (VTG) is built in exhaust gas turbochargers for large engines usually as a separate module and the gas inlet and gas outlet housings of
Abgasturbine befestigt, wie dies in der Fig.1 angedeutet ist. Das Gaseintrittsgehäuse und das Gasaustrittsgehäuse sind in der Regel für den Anbau an unterschiedlichenAttached exhaust gas turbine, as indicated in Figure 1. The gas inlet housing and the gas outlet housing are usually for attachment to different
Motoren in Stufen von bestimmten Winkeln, beispielsweise 15°, frei drehbar. Dies führt typischerweise zur Verwendung von über den Umfang gleichmässig verteilten Schrauben (bei Abschnitten von 15°, ergibt dies 24 Schrauben). Bei der Verwendung von ungleichmässig angeordneten Leitschaufeln werden Kollisionen zwischen denEngines in steps of certain angles, for example 15 °, freely rotatable. This typically results in the use of circumferentially evenly spaced screws (for 15 ° sections this gives 24 screws). When using unevenly arranged vanes collisions between the
Leitschaufeln und den Schrauben unvermeidlich.Guide vanes and the screws inevitable.
Kurze Darstellung der ErfindungBrief description of the invention
Die Aufgabe der Erfindung besteht darin, eine verstellbare Leitvorrichtung für eine Strömungsmaschine, etwa eine Abgasturbine, derart zu optimieren, dass die zur Befestigung am benachbarten Gehäuse verwendeten Befestigungsmittel unabhängig von der Ausrichtung der Leitvorrichtung zum Gehäuse angebracht werden können.The object of the invention is to optimize an adjustable guide device for a turbomachine, such as an exhaust gas turbine, such that the fastening means used for attachment to the adjacent housing can be mounted independently of the orientation of the guide device to the housing.
Die Erfindungsidee besteht in der Verlagerung der Befestigung für den Anbau der Leitvorrichtung in den Bereich radial ausserhalb der Leitschaufeln, insbesondere radial ausserhalb der Leitschaufel-Schäfte. Damit kann die Umfangsposition der Leitschaufeln innerhalb der vorgegebenen Winkel frei gewählt werden. Es entstehen keine Kollisionen zwischen den Leitschaufeln und den Befestigungsmitteln.The idea of the invention consists in the displacement of the attachment for the cultivation of the guide device in the region radially outside the guide vanes, in particular radially outside the guide vane shafts. Thus, the circumferential position of the vanes can be freely selected within the predetermined angle. There are no collisions between the vanes and the fasteners.
Die Leitschaufeln können sowohl gleichmässig wie ungleichmässig am Umfang verteilt werden. Für die ungleichmässige Anordnung werden die Leitschaufeln durch ungleichmässige Verteilung der Leitschaufelaufnahme im Entlastungsring, Trägerring und Nutenring verwirklicht. Kurze Beschreibung der ZeichnungenThe vanes can be distributed both evenly and unevenly around the circumference. For the non-uniform arrangement, the vanes are realized by uneven distribution of the guide vane receptacle in the relief ring, carrier ring and Nutenring. Brief description of the drawings
Nachfolgend wird eine Ausführungsform der Erfindung anhand von Zeichnungen detailliert erläutert. Hierbei zeigtHereinafter, an embodiment of the invention will be explained in detail with reference to drawings. This shows
Fig. 1 einen Schnitt durch eine Abgasturbine mit einer verstellbaren Leitvorrichtung gemäss dem Stand der Technik, und1 shows a section through an exhaust gas turbine with an adjustable guide device according to the prior art, and
Fig. 2 einen Schnitt durch eine Abgasturbine mit einer erfindungsgemäss ausgebildeten, verstellbaren Leitvorrichtung.Fig. 2 shows a section through an exhaust gas turbine with an inventively designed, adjustable guide.
Weg zur Ausführung der ErfindungWay to carry out the invention
Fig. 1 zeigt einen Ausschnitt einer herkömmlichen Axialturbine eines Abgasturboladers. Das Turbinenrad 10 ist auf der um die Achse A drehbar in einem Lagergehäuse gelagerten Welle 30 angeordnet. Das Turbinenrad 10 umfasst eine Vielzahl von Laufschaufeln 11 , welche am radial äusseren Rand des Turbinenrades entlang dem Umfang verteilt angeordnet sind. Die Abgasströmung in dem Strömungskanal ist mit Pfeilen angedeutet. Die Laufschaufeln des Turbinenrades werden in axialer Richtung angeströmt. Stromaufwärts der Laufschaufeln 11 der Abgasturbine ist eine verstellbare Leitvorrichtung (Verstellbare Turbinengeometrie) angeordnet. Diese verstellbare Leitvorrichtung umfasst eine Vielzahl von Leitschaufeln 41 , welche jeweils einen Schaft 42 aufweisen. Jede der Leitschaufeln 41 ist jeweils mit ihrem Schaft 42 um die Achse B drehbar im Gehäuse gelagert. Das Gehäuse der Leitvorrichtung umfasst im wesentlichen einen Tragring 40, welcher den Strömungskanal ringförmig umschliesst. Zum Strömungskanal hin kann der Tragring 40 noch einen Entlastungsring 45 umschliessen. Die Schäfte 42 der Leitschaufeln 41 sind im Tragring 40 in dafür vorgesehenen Bohrungen angeordnet. Die Bohrungen verlaufen, wie die Schäfte 42 der Leitschaufeln 41 , im wesentlichen in radialer Richtung. Der Tragring ist mit Befestigungsmitteln 50 am Gasaustrittsgehäuse 20 befestigt. Als Befestigungsmittel werden Bolzen oder Schrauben verwendet. Die verstellbare Leitvorrichtung umfasst weiter einen Verstellring 43 sowie pro Leitschaufel einen Verstellhebel 44. Zum Verstellen der Leitvorrichtung wird der Verstellring 43 in Umfangsrichtung bewegt. Die Verstellhebel 44 übertragen die Rotationsbewegung auf die Schäfte 42 der Leitschaufeln. Bei der erfindungsgemäss ausgeführten Leitvorrichtung nach Fig. 2 sind die Befestigungsmittel radial ausserhalb der Lagerstellen 46 der Leitschaufel-Schäfte 42, bzw. radial ausserhalb der freien Enden der Leitschaufel-Schäfte angeordnet. Der Radius r2, ausserhalb dessen sich die Befestigungsmittel 50 befinden ist somit grösser als der Radius n, innerhalb dessen sich die Leitschaufel-Schäfte befinden.Fig. 1 shows a detail of a conventional axial turbine of an exhaust gas turbocharger. The turbine wheel 10 is arranged on the shaft 30 rotatably mounted in a bearing housing about the axis A. Turbine wheel 10 includes a plurality of blades 11 which are distributed along the circumference at the radially outer edge of the turbine wheel. The exhaust gas flow in the flow channel is indicated by arrows. The blades of the turbine wheel are flowed in the axial direction. Upstream of the rotor blades 11 of the exhaust gas turbine, an adjustable guide device (adjustable turbine geometry) is arranged. This adjustable guide device comprises a plurality of guide vanes 41, which each have a shaft 42. Each of the guide vanes 41 is mounted in each case with its shaft 42 about the axis B rotatably in the housing. The housing of the guide device essentially comprises a support ring 40, which encloses the flow channel in an annular manner. Towards the flow channel, the support ring 40 can still enclose a relief ring 45. The shafts 42 of the vanes 41 are arranged in the support ring 40 in holes provided for this purpose. The holes extend, as the shafts 42 of the vanes 41, substantially in the radial direction. The support ring is fastened with fastening means 50 on the gas outlet housing 20. As fasteners bolts or screws are used. The adjustable guide device further comprises an adjusting ring 43 and per guide vane an adjusting lever 44. For adjusting the guide device, the adjusting ring 43 is moved in the circumferential direction. The adjustment levers 44 transmit the rotational movement to the shafts 42 of the vanes. 2, the fastening means are arranged radially outside the bearing points 46 of the guide blade shafts 42, or radially outside the free ends of the guide blade shafts. The radius r 2 outside which the fastening means 50 are located is thus larger than the radius n within which the guide blade shafts are located.
Damit können die Leitschaufeln 41 sowohl gleichmässig wie ungleichmässig entlang des Umfangs des Trägerrings verteilt werden, ohne dass dadurch die Befestigungsmittel 50 und die Schäfte 42 der Leitschaufeln einander kreuzen. Die ungleichmässige Anordnung der Leitschaufeln 41 wird durch ungleichmässige Verteilung der Leitschaufelaufnahme im Entlastungsring 45, Trägerring 40 und Verstellring verwirklicht. Der Trägerring 40 lässt sich auch bei unregelmässig verteilten Leitschaufeln in jedem Winkel bezüglich des Gasaustrittsgehäuses 20 positionieren, welcher die entlang dem Umfang verteilt angeordneter Bohrungen für die Befestigungsmittel zulassen. Die Umfangsposition der Leitschaufeln kann somit innerhalb der vorgegebenen Winkel frei gewählt werden.Thus, the guide vanes 41 can be both uniformly and non-uniformly distributed along the circumference of the carrier ring, without thereby the fastening means 50 and the shafts 42 of the vanes intersect each other. The non-uniform arrangement of the guide vanes 41 is realized by non-uniform distribution of the guide vane receptacle in the relief ring 45, carrier ring 40 and adjusting ring. The support ring 40 can be positioned at any angle with respect to the gas outlet housing 20 even with irregularly distributed vanes, which allow distributed along the circumference arranged holes for the fasteners. The circumferential position of the guide vanes can thus be freely selected within the predetermined angle.
Das Gaseintrittsgehäuse 21 kann radial innerhalb des Verstellhebels 44 mit separaten Befestigungsmitteln mit dem Trägerring 40 verbunden werden, wie in Fig. 2 angedeutet. The gas inlet housing 21 can be connected radially within the adjusting lever 44 with separate fastening means with the support ring 40, as indicated in Fig. 2.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
10 Turbinenrad10 turbine wheel
11 Laufschaufeln des Turbinerads11 blades of the turbine wheel
20 Gasaustrittsgehäuse der Abgasturbine20 gas outlet housing of the exhaust gas turbine
30 Welle des Abgasturboladers30 shaft of the exhaust gas turbocharger
40 Trägerring, Gehäuse der Leitvorrichtung40 carrier ring, housing of the guide
41 Leitschaufeln, verstellbar41 vanes, adjustable
42 Schaft der Leitschaufel42 stem of the vane
43 Verstellring43 adjusting ring
44 Verstellhebel44 adjusting lever
45 Entlastungsring45 relief ring
46 Lagerstellen zur Lagerung des Schaftes der Leitschaufel 50 Befestigungsmittel zur Befestigung des Trägerrings am46 bearing points for supporting the shaft of the vane 50 fastening means for fixing the carrier ring on
Turbinengehäuse π Aussenradius der Leitschaufel-Schäfte r2 Innenradius der Befestigungsmittel zur Befestigung desTurbine housing π Outer radius of the vane shafts r 2 Inner radius of the fastening means for fastening the
Trägerrings am TurbinengehäuseCarrier ring on the turbine housing
A Achse der Welle des AbgasturboladersA Axle of the shaft of the exhaust gas turbocharger
B Achse des Schaftes der Leitschaufel B axis of the stem of the vane

Claims

PAT E N TA N S P R Ü C H E PAT EN TA NSPR O CHE
1. Strömungsmaschine, umfassend ein Gehäuse (20) sowie eine ringförmig ausgebildete Leitvorrichtung mit drehbaren Leitschaufeln (40), welche entlang dem Umfang der Leitvorrichtung verteilt angeordnet und je mit einen radial verlaufenden Schaft (42) in einem Trägerring (40) der Leitvorrichtung gelagert sind, wobei der1. Turbomachine, comprising a housing (20) and an annular guide device with rotatable vanes (40) which are arranged distributed along the circumference of the guide and each with a radially extending shaft (42) in a support ring (40) of the guide are mounted , where the
Trägerring (40) Lagerstellen (46) zur Aufnahme der Leitschaufel-Schäften (42) und Befestigungsmittel (50) zum Befestigen des Trägerrings (40) an dem Gehäuse (20) umfasst, dadurch gekennzeichnet, dass die Lagerstellen (46) zur Aufnahme der Leitschaufel-Schäfte (42) radial innerhalb eines ersten Radius (n) angeordnet sind und die Befestigungsmittel (50) radial ausserhalb eines zweiten Radius (r2) angeordnet sind, und dass der Radius (n) kleiner ist als der zweite Radius (r2).Carrier ring (40) bearing points (46) for receiving the guide vane shafts (42) and fastening means (50) for attaching the carrier ring (40) on the housing (20), characterized in that the bearing points (46) for receiving the guide vane Shafts (42) are arranged radially within a first radius (s) and the fastening means (50) are arranged radially outside a second radius (r 2 ), and that the radius (n) is smaller than the second radius (r 2 ) ,
2. Strömungsmaschine nach Anspruch 1 , wobei die Leitschaufeln (40) entlang dem Umfang der Leitvorrichtung ungleichmässig verteilt, das heisst in unterschiedlichen Abständen zueinander, angeordnet sind. 2. Turbomachine according to claim 1, wherein the guide vanes (40) distributed unevenly along the circumference of the guide device, that is, at different distances from each other, are arranged.
3. Abgasturbolader, umfassend eine Abgasturbine, welche als Strömungsmaschine gemäss Anspruch 1 oder 2 ausgebildet ist. 3. Exhaust gas turbocharger, comprising an exhaust gas turbine, which is designed as a turbomachine according to claim 1 or 2.
EP09701799A 2008-01-15 2009-01-12 Control device for blade adjustment Withdrawn EP2229508A1 (en)

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EP09701799A EP2229508A1 (en) 2008-01-15 2009-01-12 Control device for blade adjustment

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EP08150265A EP2080871A1 (en) 2008-01-15 2008-01-15 Variable guide vane mechanism
EP09701799A EP2229508A1 (en) 2008-01-15 2009-01-12 Control device for blade adjustment
PCT/EP2009/050258 WO2009090149A1 (en) 2008-01-15 2009-01-12 Control device for blade adjustment

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EP09701799A Withdrawn EP2229508A1 (en) 2008-01-15 2009-01-12 Control device for blade adjustment

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Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2295732A1 (en) 2009-09-14 2011-03-16 Alstom Technology Ltd Axial turbine and method for discharging a flow from an axial turbine
IN2014DN07030A (en) * 2012-02-02 2015-04-10 Borgwarner Inc
US20140023502A1 (en) * 2012-07-20 2014-01-23 General Electric Company Variable vane assembly for turbine system
EP2781695A1 (en) * 2013-03-22 2014-09-24 ABB Turbo Systems AG Nozzle for an exhaust gas turbine
US9194249B2 (en) 2013-07-25 2015-11-24 Solar Turbines Incorporated Method for enhancing power of a gas turbine engine
GB201616108D0 (en) * 2016-09-22 2016-11-09 Rolls Royce Plc Gas turbine engine
WO2019217979A1 (en) 2018-05-09 2019-11-14 Gaffoor Feizal Alli Turbocharger

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3074689A (en) * 1960-06-06 1963-01-22 Chrysler Corp Adjustable nozzle ring support

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3542484A (en) * 1968-08-19 1970-11-24 Gen Motors Corp Variable vanes
US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US3817655A (en) * 1972-11-22 1974-06-18 Carrier Corp Stator blade mounting structure for turbomachines
US4003675A (en) * 1975-09-02 1977-01-18 Caterpillar Tractor Co. Actuating mechanism for gas turbine engine nozzles
US4497171A (en) * 1981-12-22 1985-02-05 The Garrett Corporation Combustion turbine engine
DE4213709A1 (en) 1992-04-25 1993-10-28 Asea Brown Boveri Turbine with axial flow
DE19618314A1 (en) * 1996-05-08 1997-11-13 Asea Brown Boveri Exhaust gas turbine of an exhaust gas turbocharger
DE10013335A1 (en) * 2000-03-17 2001-09-20 Abb Turbo Systems Ag Baden Conducting apparatus is for position alteration of conducting blades in turbocharger exhaust gas turbine has blades arranged axially symmetrically to the turbine axis in an exhaust gas flow channel and can be pivoted by a pivot device
JP2002303147A (en) * 2001-04-05 2002-10-18 Toyota Motor Corp Variable displacement turbo-charger
US7097420B2 (en) * 2004-04-14 2006-08-29 General Electric Company Methods and apparatus for assembling gas turbine engines
DE102004030798B4 (en) * 2004-06-25 2014-12-24 Volkswagen Ag Exhaust gas turbocharger for an internal combustion engine with variable turbine geometry
JP4247214B2 (en) * 2004-10-29 2009-04-02 三菱重工業株式会社 Exhaust turbine turbocharger
EP1669548A1 (en) * 2004-12-08 2006-06-14 ABB Turbo Systems AG Guide vane apparatus for a gas turbine engine
GB2426555A (en) * 2005-05-28 2006-11-29 Siemens Ind Turbomachinery Ltd Turbocharger air intake

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3074689A (en) * 1960-06-06 1963-01-22 Chrysler Corp Adjustable nozzle ring support

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CN101910566A (en) 2010-12-08
US20100278651A1 (en) 2010-11-04
WO2009090149A1 (en) 2009-07-23
KR101265927B1 (en) 2013-05-20
EP2080871A1 (en) 2009-07-22
KR20100095642A (en) 2010-08-31
JP5123400B2 (en) 2013-01-23
JP2011510207A (en) 2011-03-31
US8251647B2 (en) 2012-08-28

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