EP2112332B1 - Supporting ring for a guide vane assembly with an air-sealed channel - Google Patents

Supporting ring for a guide vane assembly with an air-sealed channel Download PDF

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Publication number
EP2112332B1
EP2112332B1 EP20080154983 EP08154983A EP2112332B1 EP 2112332 B1 EP2112332 B1 EP 2112332B1 EP 20080154983 EP20080154983 EP 20080154983 EP 08154983 A EP08154983 A EP 08154983A EP 2112332 B1 EP2112332 B1 EP 2112332B1
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EP
European Patent Office
Prior art keywords
air
supporting ring
sealed channel
turbomachine
vane assembly
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.)
Active
Application number
EP20080154983
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German (de)
French (fr)
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EP2112332A1 (en
Inventor
Peter Neuenschwander
Matthias Jarusel
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Accelleron Industries AG
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ABB Turbo Systems AG
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Filing date
Publication date
Application filed by ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP20080154983 priority Critical patent/EP2112332B1/en
Priority to JP2011505504A priority patent/JP5021846B2/en
Priority to KR1020107022843A priority patent/KR101244956B1/en
Priority to CN200980115076.6A priority patent/CN102016237B/en
Priority to PCT/EP2009/054857 priority patent/WO2009130262A1/en
Publication of EP2112332A1 publication Critical patent/EP2112332A1/en
Application granted granted Critical
Publication of EP2112332B1 publication Critical patent/EP2112332B1/en
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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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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 guide devices for turbomachines, in particular for turbines of turbochargers for supercharged internal combustion engines.
  • It relates to a support ring of a guide device with adjustable guide vanes, guide devices with such a support ring, as well as flow machines with such guide devices with such a support ring.
  • 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.
  • turbochargers with turbine and compressor components with fixed geometries have been used predominantly for large engines (fixed geometries). These geometries have been designed and adapted for each individual engine. During the operation of the engine, however, they were invariable. 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.
  • variable turbine geometries are well known in the art and particularly in the field of small engines, such as those used in passenger cars.
  • variable turbine geometries are already being used today for gas engines which require precise regulation of the fuel / air ratio.
  • widespread use of variable turbine geometries in large engines is to be expected.
  • the guide In order to prevent the exhaust gases of the internal combustion engine in the bearing points of the guide vanes of the guide in exhaust gas turbochargers with variable turbine geometry and to exclude the leakage of exhaust gases into the environment, the guide must be supplied with air purge.
  • the sealing air is guided in an inside of the cross-sectional profile of the bearing housing ring - hereinafter referred to as a support ring - the guide device arranged annular channel.
  • a support ring - the guide device arranged annular channel.
  • the cross section of the sealing air duct is relatively small due to the limited space inside the profile of the support ring. In order to achieve a uniform supply of sealing air, the air must therefore be supplied in several places. For this purpose, other special pipes are needed outside the guide.
  • US20080075583 discloses a guide device of a turbine which has rotatably mounted guide vanes in the turbine housing. Between the turbine housing and the rotatably mounted in the turbine housing Leitschaufelschaft a sealing sleeve is arranged. An additional axial compression spring ensures that the sealing sleeve is pressed continuously against a guide blade counter contour and thereby an axial gap and the leakage flow through the bearing point of the Leitschaufel textilefte be prevented. Further, a barrier air supply is disclosed, which introduces sealing air in the region between the guide vane bearing point and the flow channel of the turbine.
  • the object of the invention is to provide a cost-effective to manufacture support ring of a guide device of a turbomachine.
  • this is achieved with a support ring, wherein the barrier air channel for preventing the ingress of gases from the flow channel into the bearing points of the guide vanes of the guide device as an outward opening and extending in the circumferential direction groove or channel is formed.
  • the groove is embedded in an axial end face of the carrier ring.
  • the groove is embedded in a radially outer side or inner side of the shell. If the barrier air duct designed as an open channel in the support ring, the support ring can thereby be poured without a core for the sealing air duct.
  • the embedded in an axial end face or a shell side of the carrier ring sealing air channel is sealed according to the invention on its open side by the gas outlet housing and / or another housing part, such as the cover.
  • the barrier air channel of the carrier ring formed according to the invention can have such a large cross-section that the entire barrier air can be supplied only at one point along the circumference. This makes it possible to save the distribution pipes and requires a smaller number of mechanical processing of the support ring. Further advantages emerge from the dependent claims.
  • Fig. 1 shows a conventional exhaust gas turbocharger with exhaust gas turbine 20 and compressor 10, and disposed therebetween bearing housing 50.
  • the exhaust gas turbine 20 includes a gas inlet housing 21 through which the hot exhaust gas flows to the turbine and this drives before the exhaust gas is supplied through the gas outlet housing 22 of the exhaust system.
  • the turbine wheel is arranged at one end of a shaft rotatable about the axis A, which is rotatably mounted in the bearing housing 50.
  • the compressor wheel At the other end of the shaft is the compressor wheel, which compresses air drawn in through the air inlet housing 11, which air is subsequently collected in the air outlet housing 21 and fed to the combustion chambers of the internal combustion engine.
  • the turbine is an axial flowed axial turbine.
  • Fig. 2 shows a section of an axial turbine of a conventional exhaust gas turbocharger.
  • the turbine wheel 25 is arranged on the shaft 30 which is rotatable about the axis A in the bearing housing 50.
  • the turbine wheel 25 includes a plurality of blades 26, which are distributed along the circumference of the radially outer edge of the turbine wheel.
  • the exhaust gas flow in the flow channel from the gas inlet housing 21 to the gas outlet housing 22 is indicated in the figures in each case by arrows. The blades of the turbine wheel are flowed in the axial direction.
  • an adjustable guide (adjustable turbine geometry) is arranged upstream of the rotor blades 26 of the exhaust turbine.
  • 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 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 cover ring 45.
  • the shafts 42 of the guide vanes 41 are arranged in the support ring 40 in holes provided and stored. These bearings run, as the shafts 42 of the vanes 41, substantially in the radial direction.
  • the support ring 40 is usually fastened with fastening means on the gas outlet housing 22 and / or on the gas inlet housing 21. As fasteners bolts, screws or tabs are used.
  • the adjustable guide device further comprises an adjusting ring 43 and per guide vane an adjusting lever 44, which are guided through openings 49 in the support ring to the shaft 42. To adjust the guide 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.
  • a barrier air channel 46 is arranged in the support ring 40. The sealing air is fed at one or more points in the annular inside the profile carrier ring 40 extending sealing air channel 46 and flows through the openings for the shafts of the vanes in the flow channel.
  • the openings 48 for receiving and supporting the shafts 42 of the guide vanes 41 are in turn supplied with sealing air via a sealing air channel 46.
  • the sealing air channel 46 is sealed with sealing elements 47, so that no blocking air can escape in this direction along the shank of the guide vanes.
  • the barrier air channel 46 is designed as a groove let into the axial end face of the carrier ring 40, as well as the schematic representations of the axially flow-through guide device 4 and FIG. 5 can be removed.
  • the sealing air channel 46 When installed, the sealing air channel 46 is bounded by the adjacent to the axial end face housing part 22. This results in the recessed as a groove in the support ring 40 sealing air channel 46 in the installed state, an annular cavity. To increase the cross section of the sealing air channel, a groove 23 opening in the axial direction can be introduced on the side of the housing.
  • the sealing air channel is composed of the carrier ring-side sealing air channel 46 and the housing-side groove 23.
  • the contact surfaces between the carrier ring and the adjacent housing parts may be flat, inclined or stepped in the region of the sealing air channel.
  • the groove 23 widening the sealing air channel can extend on the side of the housing into the region of the cover ring 45.
  • the cross section can be further enlarged.
  • the sealing air channel can be sealed by sealing elements 47 arranged radially inside and / or outside the sealing air channel. This makes it possible to prevent the sealing air fed into the barrier air channel 46 with excess pressure from escaping through the connection between the gas outlet housing 22 and the carrier ring 40.
  • the groove which forms the sealing air channel 46 can also be embedded on the end face of the carrier ring 40 facing the gas inlet housing 21.
  • the grooves forming the sealing air channel in the carrier ring and / or in the adjacent housing may be formed as annular groove segments, that is to say they may be divided along the circumference into a plurality of sections.
  • Each barrier air duct segment can be supplied individually with external air from the outside.
  • Fig. 6 relates to an example of a guide, which is not part of the invention.
  • the figure shows a section through the support ring of a radially flowed guide device, as used for example in radial or mixed flow turbine.
  • the sealing air channel 46 is formed by a radially outwardly or radially inwardly opening groove in the support ring.
  • This groove forming the barrier air channel 46 is thus embedded in a lateral surface of the carrier ring 40.
  • the limitation of the groove to the annular cavity is effected by an adjacent housing part, in the case of an exhaust gas turbine this would be about the gas inlet housing 21.
  • a circumferential groove 23 can be inserted to expand the sealing air channel 46 in the adjacent housing part.

Description

Technisches GebietTechnical area

Die Erfindung bezieht sich auf das Gebiet der Leitvorrichtungen für Strömungsmaschinen, insbesondere für Turbinen von Abgasturboladern für aufgeladene Brennkraftmaschinen.The invention relates to the field of guide devices for turbomachines, in particular for turbines of turbochargers for supercharged internal combustion engines.

Sie betrifft einen Trägerring einer Leitvorrichtung mit verstellbaren Leitschaufeln, Leitvorrichtungen mit einem solchen Trägerring, sowie Strömungsmaschinen mit solchen Leitvorrichtungen mit einem solchen Trägerring.It relates to a support ring of a guide device with adjustable guide vanes, guide devices with such a support ring, as well as flow machines with such guide devices with such a support ring.

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. Das Aufladesystem des Motors trägt dabei massgeblich zur Erreichung der Entwicklungsziele bei. In der Vergangenheit sind bei Grossmotoren überwiegend 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.The recent development in the field of modern reciprocating engines is driven by the reduction of emissions, costs and fuel consumption. The engine's charging system contributes significantly to achieving the development goals. In the past, turbochargers with turbine and compressor components with fixed geometries have been used predominantly for large engines (fixed geometries). These geometries have been designed and adapted for each individual engine. During the operation of the engine, however, they were invariable. 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 adjustable 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.

Um bei Abgasturboladern mit variabler Turbinengeometrie das Eintreten von Abgasen des Verbrennungsmotors in die Lagerstellen der Leitschaufeln der Leitvorrichtung zu verhindern und um die Leckage von Abgasen in die Umgebung auszuschliessen, muss die Leitvorrichtung mit Sperrluft versorgt werden.In order to prevent the exhaust gases of the internal combustion engine in the bearing points of the guide vanes of the guide in exhaust gas turbochargers with variable turbine geometry and to exclude the leakage of exhaust gases into the environment, the guide must be supplied with air purge.

Bei herkömmlichen Leitvorrichtungen wird die Sperrluft in einen im Innern des Querschnittprofils des tragenden Gehäuserings - nachfolgend als Tragring bezeichnet - der Leitvorrichtung angeordneten Ringkanal geführt. Beim Giessen des Tragringes ist wegen dieses Ringkanals ein Gusskern nötig, was den Giessprozess verteuert. Zudem ist der Querschnitt des Sperrluftkanals aufgrund der beschränkten Platzverhältnisse im Innern des Profils des Tragrings vergleichsweise klein. Um eine gleichmässige Versorgung mit Sperrluft zu erreichen muss die Luft daher an mehreren Stellen zugeführt werden. Dafür sind ausserhalb der Leitvorrichtung weitere spezielle Rohre nötig.In conventional guide devices, the sealing air is guided in an inside of the cross-sectional profile of the bearing housing ring - hereinafter referred to as a support ring - the guide device arranged annular channel. When casting the support ring, a cast core is necessary because of this annular channel, which makes the casting process more expensive. In addition, the cross section of the sealing air duct is relatively small due to the limited space inside the profile of the support ring. In order to achieve a uniform supply of sealing air, the air must therefore be supplied in several places. For this purpose, other special pipes are needed outside the guide.

US20080075583 offenbart eine Leitvorrichtung einer Turbine, welche im Turbinengehäuse drehbar gelagerte Leitschaufel aufweist. Zwischen dem Turbinengehäuse und dem drehbar im Turbinengehäuse gelagerten Leitschaufelschaft ist eine Dichthülse angeordnet. Eine zusätzliche axiale Druckfeder sorgt dafür, dass die Dichthülse kontinuierlich an eine Leitschaufel-Gegenkontur gepresst wird und dadurch ein axialer Spalt sowie die Leckage-Strömung durch die Lagerstelle der Leitschaufelschäfte unterbunden werden. Weiter ist eine Sperrluftversorgung offenbart, welche Sperrluft in den Bereich zwischen der Leitschaufellagerstelle und dem Strömungskanal der Turbine einbringt. US20080075583 discloses a guide device of a turbine which has rotatably mounted guide vanes in the turbine housing. Between the turbine housing and the rotatably mounted in the turbine housing Leitschaufelschaft a sealing sleeve is arranged. An additional axial compression spring ensures that the sealing sleeve is pressed continuously against a guide blade counter contour and thereby an axial gap and the leakage flow through the bearing point of the Leitschaufelschäfte be prevented. Further, a barrier air supply is disclosed, which introduces sealing air in the region between the guide vane bearing point and the flow channel of the turbine.

Kurze Darstellung der ErfindungBrief description of the invention

Die Aufgabe der Erfindung besteht darin, einen kostengünstig herzustellenden Tragring einer Leitvorrichtung einer Strömungsmaschine zu schaffen.The object of the invention is to provide a cost-effective to manufacture support ring of a guide device of a turbomachine.

Erfindungsgemäss wird dies mit einem Tragring erreicht, bei welchem der Sperrluftkanal zur Verhindern des Eindringens von Gasen aus dem Strömungskanal in die Lagerstellen der Leitschaufeln der Leitvorrichtung als eine sich nach aussen hin öffnende und sich in Umfangsrichtung erstreckende Nut oder Rinne ausgebildet ist. Bei einem Trägerring für eine axial durchströmte Leitvorrichtung, ist die Nut dabei in eine axiale Stirnseite des Trägerrings eingelassen. Bei einer radial durchströmten Leitvorrichtung ist die Nut dabei in eine radial aussen- oder innenliegende Mantelseite eingelassen. Wird der Sperrluftkanal als offene Rinne im Tragring gestaltet, kann der Tragring dadurch ohne Kern für den Sperrluftkanal gegossen werden.According to the invention this is achieved with a support ring, wherein the barrier air channel for preventing the ingress of gases from the flow channel into the bearing points of the guide vanes of the guide device as an outward opening and extending in the circumferential direction groove or channel is formed. In a carrier ring for an axially flowed guide device, the groove is embedded in an axial end face of the carrier ring. In a guide device through which the radial flow passes, the groove is embedded in a radially outer side or inner side of the shell. If the barrier air duct designed as an open channel in the support ring, the support ring can thereby be poured without a core for the sealing air duct.

Der in eine axiale Stirnseite oder eine Mantelseite des Trägerrings eingelassenen Sperrluftkanal wird erfindungsgemäss auf seiner offenen Seite durch das Gasaustrittsgehäuse und/ oder ein anderes Gehäuseteil, beispielsweise den Abdeckring, gedichtet.The embedded in an axial end face or a shell side of the carrier ring sealing air channel is sealed according to the invention on its open side by the gas outlet housing and / or another housing part, such as the cover.

Der Sperrluftkanal des erfindungsgemäss ausgebildeten Trägerrings kann dank der Anordnung am äusseren Bereich des Querschnittprofils einen so grossen Querschnitt aufweisen, dass die gesamte Sperrluft entlang dem Umfang lediglich an einer Stelle zugeführt werden kann. Dies ermöglicht die Einsparung der Verteilrohre und erfordert eine kleinere Anzahl mechanischer Bearbeitungen des Tragringes.
Weitere Vorteile ergeben sich aus den abhängigen Ansprüchen.Thanks to the arrangement at the outer region of the cross-sectional profile, the barrier air channel of the carrier ring formed according to the invention can have such a large cross-section that the entire barrier air can be supplied only at one point along the circumference. This makes it possible to save the distribution pipes and requires a smaller number of mechanical processing of the support ring.
Further advantages emerge from the dependent claims.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Nachfolgend wird eine Ausführungsform der Erfindung anhand von Zeichnungen detailliert erläutert. Hierbei zeigt

Fig.1
eine Gesamtansicht eines Abgasturboladers gemäss dem Stand der Technik,
Fig. 2
einen Schnitt durch eine Abgasturbine mit einer verstellbaren, axial durchströmten Leitvorrichtung gemäss dem Stand der Technik,
Fig. 3
einen Schnitt durch eine Abgasturbine mit einer verstellbaren, axial durchströmten Leitvorrichtung mit einem erfindungsgemäss ausgebildeten Trägerring,
Fig. 4
einen Ansicht in axialer Richtung auf einen erfindungsgemäss ausgebildeten Trägerring gemäss Fig. 3,
Fig. 5.
einen entlang V-V geführten Schnitt durch den Trägerring nach Fig. 4, und
Fig. 6
einen Schnitt durch einen ausgebildeten Trägerring einer radial durchströmten Leitvorrichtung.
Hereinafter, an embodiment of the invention will be explained in detail with reference to drawings. This shows
Fig.1
an overall view of an exhaust gas turbocharger according to the prior art,
Fig. 2
a section through an exhaust gas turbine with an adjustable, axially flow-through guide device according to the prior art,
Fig. 3
a section through an exhaust gas turbine with an adjustable, axially flowed through guide device with a carrier ring according to the invention,
Fig. 4
a view in the axial direction of a carrier ring according to the invention formed according to Fig. 3 .
Fig. 5.
a guided along VV section through the support ring after Fig. 4 , and
Fig. 6
a section through a trained carrier ring of a radially flowed guide.

Weg zur Ausführung der ErfindungWay to carry out the invention

Fig. 1 zeigt einen herkömmlichen Abgasturbolader mit Abgasturbine 20 und Verdichter 10, sowie dazwischen angeordnetem Lagergehäuse 50. Die Abgasturbine 20 umfasst ein Gaseintrittsgehäuse 21, durch welches das heisse Abgas auf das Turbinenrad strömt und dieses antreibt, bevor das Abgas durch das Gasaustrittsgehäuse 22 der Auspuffanlage zugeführt wird. Das Turbinenrad ist an einem Ende einer um die Achse A rotierbaren Welle angeordnet, welche im Lagergehäuse 50 drehbar gelagert ist. Am anderen Ende der Welle befindet sich das Verdichterrad, welches durch das Lufteintrittsgehäuse 11 angesaugte Luft verdichtet, welche anschliessend in dem Luftaustrittsgehäuse 21 gesammelt und den Brennkammern des Verbrennungsmotors zugeführt wird. In der dargestellten Ausführungsform handelt es sich bei der Turbine um eine axial angeströmte Axialturbine. Alternativ könnte das Abgas in streng radialer oder zur Radialen leicht geneigten Richtung auf das Turbinenrad geführt werden, wobei in diesem Fall von einer Radial, bzw. Mixed-Flow Turbine gesprochen wird.
Fig. 2 zeigt einen Ausschnitt einer Axialturbine eines herkömmlichen Abgasturboladers. Das Turbinenrad 25 ist auf der um die Achse A drehbar in dem Lagergehäuse 50 gelagerten Welle 30 angeordnet. Das Turbinenrad 25 umfasst eine Vielzahl von Laufschaufeln 26, welche am radial äusseren Rand des Turbinenrades entlang dessen Umfang verteilt angeordnet sind. Die Abgasströmung in dem Strömungskanal vom Gaseintrittsgehäuse 21 bis zum Gasaustrittsgehäuse 22 ist in den Figuren jeweils mit Pfeilen angedeutet. Die Laufschaufeln des Turbinenrades werden in axialer Richtung angeströmt. Stromaufwärts der Laufschaufeln 26 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 einen Tragring 40, welcher den Strömungskanal ringförmig umschliesst. Zum Strömungskanal hin kann der Tragring 40 noch einen Abdeckring 45 umschliessen. Die Schäfte 42 der Leitschaufeln 41 sind im Tragring 40 in dafür vorgesehenen Bohrungen angeordnet und gelagert. Diese Lagerstellen verlaufen, wie die Schäfte 42 der Leitschaufeln 41, im wesentlichen in radialer Richtung. Der Tragring 40 ist in der Regel mit Befestigungsmitteln am Gasaustrittsgehäuse 22 und/ oder am Gaseintrittsgehäuse 21 befestigt. Als Befestigungsmittel werden Bolzen, Schrauben oder Laschen verwendet. Die verstellbare Leitvorrichtung umfasst weiter einen Verstellring 43 sowie pro Leitschaufel einen Verstellhebel 44, welcher durch Öffnungen 49 im Trägerring zum Schaft 42 geführt sind. Zum Verstellen der Leitvorrichtung wird der Verstellring 43 in Umfangsrichtung bewegt. Die Verstellhebel 44 übertragen die Rotationsbewegung auf die Schäfte 42 der Leitschaufeln. Um das Eintreten von Abgasen in die Lagerstellen der Leitschaufeln 41 zu verhindern und um die Leckage von Abgasen in die Umgebung auszuschliessen ist im Trägerring 40 ein Sperrluftkanal 46 angeordnet. Die Sperrluft wird dabei an einer oder mehreren Stellen in den ringförmig im Innern des Profils Trägerrings 40 verlaufenden Sperrluftkanal 46 eingespeist und strömt durch die Öffnungen für die Schäfte der Leitschaufeln in den Strömungskanal. Fig. 1 shows a conventional exhaust gas turbocharger with exhaust gas turbine 20 and compressor 10, and disposed therebetween bearing housing 50. The exhaust gas turbine 20 includes a gas inlet housing 21 through which the hot exhaust gas flows to the turbine and this drives before the exhaust gas is supplied through the gas outlet housing 22 of the exhaust system. The turbine wheel is arranged at one end of a shaft rotatable about the axis A, which is rotatably mounted in the bearing housing 50. At the other end of the shaft is the compressor wheel, which compresses air drawn in through the air inlet housing 11, which air is subsequently collected in the air outlet housing 21 and fed to the combustion chambers of the internal combustion engine. In the illustrated embodiment, the turbine is an axial flowed axial turbine. Alternatively, the exhaust gas could be directed onto the turbine wheel in a direction which is strictly radial or slightly inclined to the radial direction, in which case a radial or mixed-flow turbine is used.
Fig. 2 shows a section of an axial turbine of a conventional exhaust gas turbocharger. The turbine wheel 25 is arranged on the shaft 30 which is rotatable about the axis A in the bearing housing 50. The turbine wheel 25 includes a plurality of blades 26, which are distributed along the circumference of the radially outer edge of the turbine wheel. The exhaust gas flow in the flow channel from the gas inlet housing 21 to the gas outlet housing 22 is indicated in the figures in each case by arrows. The blades of the turbine wheel are flowed in the axial direction. Upstream of the rotor blades 26 of the exhaust turbine, an adjustable guide (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 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 cover ring 45. The shafts 42 of the guide vanes 41 are arranged in the support ring 40 in holes provided and stored. These bearings run, as the shafts 42 of the vanes 41, substantially in the radial direction. The support ring 40 is usually fastened with fastening means on the gas outlet housing 22 and / or on the gas inlet housing 21. As fasteners bolts, screws or tabs are used. The adjustable guide device further comprises an adjusting ring 43 and per guide vane an adjusting lever 44, which are guided through openings 49 in the support ring to the shaft 42. To adjust the guide 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. In order to prevent the entry of exhaust gases into the bearing points of the guide vanes 41 and to exclude the leakage of exhaust gases into the environment a barrier air channel 46 is arranged in the support ring 40. The sealing air is fed at one or more points in the annular inside the profile carrier ring 40 extending sealing air channel 46 and flows through the openings for the shafts of the vanes in the flow channel.

Bei der axial durchströmten Leitvorrichtung mit dem erfindungsgemäss ausgebildeten Träggering nach Fig. 3 werden die Öffnungen 48 zur Aufnahme und Lagerung der Schäfte 42 der Leitschaufeln 41 wiederum über einen Sperrluftkanal 46 mit Sperrluft versorgt. Gegenüber der Öffnung 49 zur Durchführung des Verstellhebels 44 ist der Sperrluftkanal 46 mit Dichtelementen 47 abgedichtet, so dass in diese Richtung entlang dem Schaft der Leitschaufeln keine Sperrluft entweichen kann. Der Sperrluftkanal 46 ist erfindungsgemäss als eine in die axiale Stirnseite des Trägerrings 40 eingelassene Nut ausgebildet, wie auch den schematischen Darstellungen der axial durchströmten Leitvorrichtung gemäss Fig. 4 und Fig. 5 entnommen werden kann.In the case of the axially flow-through guide device with the carrier ring designed according to the invention Fig. 3 For example, the openings 48 for receiving and supporting the shafts 42 of the guide vanes 41 are in turn supplied with sealing air via a sealing air channel 46. Opposite the opening 49 for the passage of the adjusting lever 44, the sealing air channel 46 is sealed with sealing elements 47, so that no blocking air can escape in this direction along the shank of the guide vanes. According to the invention, the barrier air channel 46 is designed as a groove let into the axial end face of the carrier ring 40, as well as the schematic representations of the axially flow-through guide device 4 and FIG. 5 can be removed.

Im eingebauten Zustand wird der Sperrluftkanal 46 durch das an die axiale Stirnseite angrenzenden Gehäuseteil 22 begrenzt. Somit ergibt sich für den als Nut in den Trägerring 40 eingelassenen Sperrluftkanal 46 im eingebauten Zustand ein ringförmiger Hohlraum. Zur Vergrösserung des Querschnitts des Sperrluftkanals kann auf der Gehäuseseite eine sich in axialer Richtung öffnende Nut 23 eingelassen sein. In diesem Fall setzt sich der Sperrluftkanal aus dem trägerringseitigen Sperrluftkanal 46 und der gehäuseseitigen Nut 23 zusammen.When installed, the sealing air channel 46 is bounded by the adjacent to the axial end face housing part 22. This results in the recessed as a groove in the support ring 40 sealing air channel 46 in the installed state, an annular cavity. To increase the cross section of the sealing air channel, a groove 23 opening in the axial direction can be introduced on the side of the housing. In this case, the sealing air channel is composed of the carrier ring-side sealing air channel 46 and the housing-side groove 23.

Die Kontaktflächen zwischen dem Trägerring und den angrenzenden Gehäuseteilen können im Bereich des Sperrluftkanals flach, schräg oder gestuft ausgebildet sein.The contact surfaces between the carrier ring and the adjacent housing parts may be flat, inclined or stepped in the region of the sealing air channel.

Optional kann sich die den Sperrluftkanal erweiternde Nut 23 auf der Gehäuseseite bis in den Bereich des Abdeckrings 45 erstrecken. Dadurch lässt sich der Querschnitt weiter vergrössern.Optionally, the groove 23 widening the sealing air channel can extend on the side of the housing into the region of the cover ring 45. As a result, the cross section can be further enlarged.

Optional kann der Sperrluftkanal durch radial inner- und/ oder ausserhalb des Sperrluftkanals angeordnete Dichtungselemente 47 abgedichtet werden. Damit lässt sich verhindern, dass die mit Überdruck in den Sperrluftkanal 46 eingespeiste Sperrluft durch die Verbindung zwischen Gasaustrittsgehäuse 22 und Trägerring 40 entweicht.Optionally, the sealing air channel can be sealed by sealing elements 47 arranged radially inside and / or outside the sealing air channel. This makes it possible to prevent the sealing air fed into the barrier air channel 46 with excess pressure from escaping through the connection between the gas outlet housing 22 and the carrier ring 40.

Optional kann die Nut, welche den Sperrluftkanal 46 bildet auch auf der der Gaseintrittsgehäuse 21 zugewandten Stirnseite des Trägerrings 40 eingelassen sein.Optionally, the groove which forms the sealing air channel 46 can also be embedded on the end face of the carrier ring 40 facing the gas inlet housing 21.

Optional können die den Sperrluftkanal bildenden Nuten im Trägerring und/ oder im angrenzenden Gehäuse als Ringnutsegmente ausgebildet, also entlang dem Umfang in mehrere Abschnitte unterteilt sein. Jedes Sperrluftkanalsegment kann dabei einzeln von aussen mit Sperrluft versorgt werden.Optionally, the grooves forming the sealing air channel in the carrier ring and / or in the adjacent housing may be formed as annular groove segments, that is to say they may be divided along the circumference into a plurality of sections. Each barrier air duct segment can be supplied individually with external air from the outside.

Fig. 6 betrifft ein Beispiel einer Leitvorrichtung, die jedoch nicht Teil der Erfindung ist. Die Figur zeigt einen Schnitt durch den Trägerring einer radial durchströmten Leitvorrichtung, wie sie etwa in Radial- oder Mixedflow Turbinen eingesetzt werden. In diesem Fall ist der Sperrluftkanal 46 durch eine sich nach radial aussen oder nach radial innen öffnende Nut in den Trägerring gebildet. Diese den Sperrluftkanal 46 bildende Nut ist somit in eine Mantelfläche des Trägerrings 40 eingelassen. Die Begrenzung der Nut zum Ringhohlraum erfolgt durch ein benachbartes Gehäuseteil, im Falle einer Abgasturbine wäre dies etwa das Gaseintrittsgehäuse 21. Wiederum kann zur Erweiterung des Sperrluftkanals 46 in das benachbarte Gehäuseteil eine umlaufende Nut 23 eingelassen sein. Fig. 6 relates to an example of a guide, which is not part of the invention. The figure shows a section through the support ring of a radially flowed guide device, as used for example in radial or mixed flow turbine. In this case, the sealing air channel 46 is formed by a radially outwardly or radially inwardly opening groove in the support ring. This groove forming the barrier air channel 46 is thus embedded in a lateral surface of the carrier ring 40. The limitation of the groove to the annular cavity is effected by an adjacent housing part, in the case of an exhaust gas turbine this would be about the gas inlet housing 21. Again, a circumferential groove 23 can be inserted to expand the sealing air channel 46 in the adjacent housing part.

In den schematischen Darstellungen gemäss Fig. 4, Fig. 5 und Fig. 6 ist der Verstellhebel zum Verstellen der Leitschaufeln nicht eingezeichnet.In the schematic representations according to FIGS. 4, 5 and 6 the adjusting lever for adjusting the guide vanes is not shown.

Die im Detail beschriebenen Ausführungsbeispiele zeigen die Leitvorrichtung mit dem erfindungsgemäss ausgebildeten Träggering als verstellbare Leitvorrichtung einer Abgasturbine. Alle Merkmale soll jedoch auch für die allgemeine Anwendung in einer beliebigen Strömungsmaschine, insbesondere einem Verdichter, Geltung haben.The embodiments described in detail show the guide device with the carrier ring according to the invention designed as an adjustable guide device of an exhaust gas turbine. However, all features should also apply to the general application in any turbomachine, in particular a compressor, validity.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

1010
Verdichtercompressor
1111
Lufteintrittsgehäuse des VerdichtersAir intake housing of the compressor
1212
Luftaustrittsgehäuse des VerdichtersAir outlet housing of the compressor
2020
Abgasturbineexhaust turbine
2121
Gaseintrittsgehäuse der AbgasturbineGas inlet housing of the exhaust gas turbine
2222
Gasaustrittsgehäuse der AbgasturbineGas outlet housing of the exhaust gas turbine
2323
Nut im Gehäuse der AbgasturbineGroove in the housing of the exhaust gas turbine
2525
Turbinenradturbine
2626
Laufschaufeln des TurbineradsBlades of the turbine wheel
3030
Welle des AbgasturboladersShaft of the exhaust gas turbocharger
4040
Trägerring der LeitvorrichtungCarrier ring of the guide
4141
Leitschaufeln, verstellbarGuide vanes, adjustable
4242
Schaft der LeitschaufelShaft of the vane
4343
Verstellringadjusting
4444
Verstellhebeladjusting
4545
Abdeckringcover ring
4646
Sperrluftkanal im TrägerringBarrier air channel in the carrier ring
4747
Dichtungselementesealing elements
4848
Öffnung zur Aufnahme und Lagerung des Schaftes der LeitschaufelOpening for receiving and supporting the stem of the vane
4949
Öffnung zur Durchführung des VerstellhebelsOpening for the passage of the adjusting lever
5050
Lagergehäuse zur Lagerung der Welle des AbgasturboladersBearing housing for supporting the shaft of the exhaust gas turbocharger
AA
Achse der Welle des AbgasturboladersAxle of the shaft of the exhaust gas turbocharger
BB
Achse des Schaftes der LeitschaufelAxle of the shaft of the vane

Claims (9)

  1. Supporting ring (40) for a guide vane assembly of an axial turbine with adjustable guide vanes (41), the supporting ring surrounding a flow duct annularly, and the supporting ring comprising orifices (48) for the reception and rotatable mounting of shanks (42) of the guide vanes arranged in the flow duct, and an air-sealed channel (46) for feeding sealing air into the guide vane assembly, and the air-sealed channel (46) issuing into the orifices (48) for the reception and rotatable mounting of the vane shanks (42), characterized in that the air-sealed channel (46) is introduced as an outwardly opening and circumferentially extending groove into an outer side of the supporting ring (40), so that the sealing air flows out of the groove introduced into the supporting ring, through the orifices (48) in the supporting ring (40) for the reception and rotatable mounting of the vane shanks (42), into the flow duct.
  2. Supporting ring according to Claim 1, the air-sealed channel (46) being subdivided along the circumference into a plurality of annular groove segments.
  3. Guide vane assembly with a supporting ring according to either one of Claims 1 and 2, the guide vane assembly having adjustable guide vanes, and the guide vanes (41) having in each case a shank (42) which is rotatably mounted in each case in an orifice (48) of the supporting ring (40).
  4. Guide vane assembly with adjustable guide vanes (41) according to Claim 3, the air-sealed channel (46) being introduced as an axially opening and circumferentially extending groove into an axial end face of the supporting ring (40).
  5. Turbomachine, comprising a casing (22) and a guide vane assembly according to Claim 4, the supporting ring (40) lying, with the end face having the air-sealed channel (46), on the casing (22) of the turbomachine, in such a way that the casing (22) delimits the air-sealed channel (46) in the axial direction.
  6. Turbomachine according to Claim 6, a circumferentially extending groove (23) opened in the axial direction and towards the air-sealed channel (46) in the supporting ring (40) being introduced into the casing (22) in the region of the axial delimitation of the air-sealed channel (46).
  7. Turbomachine according to either one of Claims 5 and 6, sealing elements (47) being arranged in the transitional region between the supporting ring (40) and the casing of the turbomachine for the purpose of sealing off the air-sealed channel (46).
  8. Turbomachine according to one of Claims 5 to 7, the turbomachine being an exhaust gas turbine.
  9. Exhaust gas turbocharger, comprising a turbomachine according to Claim 8.
EP20080154983 2008-04-23 2008-04-23 Supporting ring for a guide vane assembly with an air-sealed channel Active EP2112332B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP20080154983 EP2112332B1 (en) 2008-04-23 2008-04-23 Supporting ring for a guide vane assembly with an air-sealed channel
JP2011505504A JP5021846B2 (en) 2008-04-23 2009-04-23 Support ring of guide device having shut-off air passage
KR1020107022843A KR101244956B1 (en) 2008-04-23 2009-04-23 Carrier ring of a conducting device with sealing air channel
CN200980115076.6A CN102016237B (en) 2008-04-23 2009-04-23 Carrier ring of a conducting device with sealing air channel
PCT/EP2009/054857 WO2009130262A1 (en) 2008-04-23 2009-04-23 Carrier ring of a conducting device with sealing air channel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20080154983 EP2112332B1 (en) 2008-04-23 2008-04-23 Supporting ring for a guide vane assembly with an air-sealed channel

Publications (2)

Publication Number Publication Date
EP2112332A1 EP2112332A1 (en) 2009-10-28
EP2112332B1 true EP2112332B1 (en) 2012-08-15

Family

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EP20080154983 Active EP2112332B1 (en) 2008-04-23 2008-04-23 Supporting ring for a guide vane assembly with an air-sealed channel

Country Status (5)

Country Link
EP (1) EP2112332B1 (en)
JP (1) JP5021846B2 (en)
KR (1) KR101244956B1 (en)
CN (1) CN102016237B (en)
WO (1) WO2009130262A1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT511072B1 (en) * 2011-06-22 2012-09-15 Avl List Gmbh INTERNAL COMBUSTION ENGINE WITH AT LEAST ONE CYLINDER
US9228447B2 (en) 2012-02-14 2016-01-05 United Technologies Corporation Adjustable blade outer air seal apparatus
DE102012211950A1 (en) * 2012-07-09 2014-05-08 Abb Turbo Systems Ag exhaust turbine
FR3051840B1 (en) * 2016-05-31 2020-01-10 Safran Aircraft Engines INTERMEDIATE CRANKCASE OF TURBOMACHINE, EQUIPPED WITH A SEALING PART WITH ARM / CRANK INTERFACE
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

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly
EP0919700B1 (en) * 1997-06-19 2004-09-01 Mitsubishi Heavy Industries, Ltd. Device for sealing gas turbine stator blades
DE10225679A1 (en) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Bearing ring for mounting of blade roots of variable stator blades in HP compressor of gas turbine, is divided into individual segments with box section construction and with free ends bevelled in relation to circumferential direction
DE10253693B4 (en) * 2002-11-18 2005-12-01 Borgwarner Turbo Systems Gmbh turbocharger
EP1669548A1 (en) * 2004-12-08 2006-06-14 ABB Turbo Systems AG Guide vane apparatus for a gas turbine engine
EP1788199A3 (en) * 2005-11-22 2011-02-23 General Electric Company Variable stator vane assembly with a wear resistant coating
EP1811134A1 (en) * 2006-01-23 2007-07-25 ABB Turbo Systems AG Variable guiding device
EP1895106A1 (en) 2006-08-28 2008-03-05 ABB Turbo Systems AG Sealing of variable guide vanes

Also Published As

Publication number Publication date
WO2009130262A1 (en) 2009-10-29
KR20100133430A (en) 2010-12-21
JP5021846B2 (en) 2012-09-12
JP2012500922A (en) 2012-01-12
CN102016237B (en) 2014-06-04
CN102016237A (en) 2011-04-13
KR101244956B1 (en) 2013-03-18
EP2112332A1 (en) 2009-10-28

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