EP2112332A1 - Air-sealed supporting ring for a guide vane assembly - Google Patents
Air-sealed supporting ring for a guide vane assembly Download PDFInfo
- Publication number
- EP2112332A1 EP2112332A1 EP08154983A EP08154983A EP2112332A1 EP 2112332 A1 EP2112332 A1 EP 2112332A1 EP 08154983 A EP08154983 A EP 08154983A EP 08154983 A EP08154983 A EP 08154983A EP 2112332 A1 EP2112332 A1 EP 2112332A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sealing air
- air channel
- housing
- turbomachine
- guide
- 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.)
- Granted
Links
Images
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
- 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 are for each individual motor designed and adapted. During the operation of the engine but they were unchanging.
- adjustable turbine geometries TMG that are adjustable in operation is increasingly being discussed. 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.
- 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 sealing air channel of the carrier ring formed according to the invention can have such a large cross-section that the entire sealing 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 shows a section through the support ring of a radially flowed guide device, such as those used in radial or mixed flow turbines.
- the sealing air channel 46 is formed according to the invention 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.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Description
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.
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 are for each individual motor designed and adapted. During the operation of the engine but they were unchanging. In order to enable even better adaptation of the exhaust gas turbocharger to the engine during operation, the use of adjustable (or variable) turbine geometries (VTG) that are adjustable in operation is increasingly being discussed. 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.
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 sealing air channel of the carrier ring formed according to the invention can have such a large cross-section that the entire sealing 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.
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 erfindungsgemäss ausgebildeten Trägerring einer radial durchströmten Leitvorrichtung.
- 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 an inventively designed support ring of a radially flowed guide.
Bei der axial durchströmten Leitvorrichtung mit dem erfindungsgemäss ausgebildeten Träggering nach
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
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
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
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
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.
In den schematischen Darstellungen gemäss
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.
- 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 (13)
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 |
KR1020107022843A KR101244956B1 (en) | 2008-04-23 | 2009-04-23 | Carrier ring of a conducting device with sealing air channel |
JP2011505504A JP5021846B2 (en) | 2008-04-23 | 2009-04-23 | Support ring of guide device having shut-off air passage |
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 true EP2112332A1 (en) | 2009-10-28 |
EP2112332B1 EP2112332B1 (en) | 2012-08-15 |
Family
ID=40551991
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
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)
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 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1669548A1 (en) * | 2004-12-08 | 2006-06-14 | ABB Turbo Systems AG | Guide vane apparatus for a gas turbine engine |
US20070172347A1 (en) * | 2006-01-23 | 2007-07-26 | Abb Turbo Systems Ag | Adjustable guide device |
US20080075583A1 (en) | 2006-08-28 | 2008-03-27 | Abb Turbo Systems Ag | Sealing of variable guide vanes |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4214852A (en) * | 1978-04-20 | 1980-07-29 | General Electric Company | Variable turbine vane assembly |
DE69825959T2 (en) * | 1997-06-19 | 2005-09-08 | Mitsubishi Heavy Industries, Ltd. | DEVICE FOR SEALING GUIDING TUBE GUIDES |
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 |
EP1788199A3 (en) * | 2005-11-22 | 2011-02-23 | General Electric Company | Variable stator vane assembly with a wear resistant coating |
-
2008
- 2008-04-23 EP EP20080154983 patent/EP2112332B1/en active Active
-
2009
- 2009-04-23 WO PCT/EP2009/054857 patent/WO2009130262A1/en active Application Filing
- 2009-04-23 KR KR1020107022843A patent/KR101244956B1/en active IP Right Grant
- 2009-04-23 CN CN200980115076.6A patent/CN102016237B/en active Active
- 2009-04-23 JP JP2011505504A patent/JP5021846B2/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1669548A1 (en) * | 2004-12-08 | 2006-06-14 | ABB Turbo Systems AG | Guide vane apparatus for a gas turbine engine |
US20070172347A1 (en) * | 2006-01-23 | 2007-07-26 | Abb Turbo Systems Ag | Adjustable guide device |
US20080075583A1 (en) | 2006-08-28 | 2008-03-27 | Abb Turbo Systems Ag | Sealing of variable guide vanes |
Also Published As
Publication number | Publication date |
---|---|
CN102016237A (en) | 2011-04-13 |
JP2012500922A (en) | 2012-01-12 |
EP2112332B1 (en) | 2012-08-15 |
JP5021846B2 (en) | 2012-09-12 |
KR20100133430A (en) | 2010-12-21 |
KR101244956B1 (en) | 2013-03-18 |
WO2009130262A1 (en) | 2009-10-29 |
CN102016237B (en) | 2014-06-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2218878B1 (en) | Seal device of an exhaust gas turbocharger | |
DE4242494C1 (en) | Adjustable flow-guide for engine exhaust turbocharger - has axially-adjustable annular insert in sectors forming different kinds of guide grilles supplied simultaneously by spiral passages | |
DE102016002701A1 (en) | Turbocharger turbine assembly | |
EP1460237A1 (en) | Casing of a turbocharger | |
DE112011104298B4 (en) | Gas turbine engine with secondary air circuit | |
DE102008005405B4 (en) | Turbine, in particular for an exhaust gas turbocharger, as well as an exhaust gas turbocharger | |
EP2112332B1 (en) | Supporting ring for a guide vane assembly with an air-sealed channel | |
EP1530670A1 (en) | Recirculation structure for a turbocompressor | |
DE102018221812B4 (en) | Exhaust gas turbine with an exhaust gas guide device for an exhaust gas turbocharger and an exhaust gas turbocharger | |
DE19924228A1 (en) | Multi-flow, adjustable exhaust gas turbocharger | |
EP1706597A1 (en) | Gas turbine with axially displaceable rotor | |
DE4309636A1 (en) | Radially flow-through turbocharger turbine | |
WO2018050347A1 (en) | Turbocharger for an internal combustion engine | |
WO2010003537A2 (en) | Turbine housing for an exhaust gas turbocharger of an internal combustion engine | |
DE10223876A1 (en) | Compressor, for the turbo charger of an IC motor, has a covering ring at the compressor wheel, radially around the wheel paddles, to form tunnel air flow channels between the paddles between the ring and the hub | |
DE102016002722A1 (en) | Turbocharger turbine nozzle and safety structure | |
DE60217049T2 (en) | Ölluftseparatorplug | |
DE4309637A1 (en) | Radially flow-through turbocharger turbine | |
EP2080871A1 (en) | Variable guide vane mechanism | |
DE102020202967A1 (en) | Exhaust gas turbocharger with integral housing | |
EP2730744B1 (en) | Exhaust gas turbo charger | |
DE102015006288A1 (en) | Turbine for an exhaust gas turbocharger, in particular an internal combustion engine, and drive device for a motor vehicle | |
DE102010053497A1 (en) | Exhaust-gas turbocharger for internal combustion engine of motor vehicle, has rotor comprising shaft that is provided with ventilation channels with outlet opening for guiding air from retaining area into close area of sealing ring | |
DE102012022647A1 (en) | Exhaust gas turbocharger for lifting cylinder internal combustion engine of motor vehicle, has portion limited by spine in axial direction, where spine comprises blade elements partially arranged in portion for compressing blade | |
DE2154726A1 (en) | RADIAL IMPACTED EXHAUST TURBOCHARGER |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA MK RS |
|
17P | Request for examination filed |
Effective date: 20100414 |
|
AKX | Designation fees paid |
Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR |
|
17Q | First examination report despatched |
Effective date: 20100708 |
|
RTI1 | Title (correction) |
Free format text: SUPPORTING RING FOR A GUIDE VANE ASSEMBLY WITH AN AIR-SEALED CHANNEL |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT CZ DE GB PL |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 570961 Country of ref document: AT Kind code of ref document: T Effective date: 20120815 Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 502008007942 Country of ref document: DE Effective date: 20121011 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20120815 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20130516 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502008007942 Country of ref document: DE Effective date: 20130516 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 570961 Country of ref document: AT Kind code of ref document: T Effective date: 20130423 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20130423 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 502008007942 Country of ref document: DE Owner name: TURBO SYSTEMS SWITZERLAND LTD., CH Free format text: FORMER OWNER: ABB TURBO SYSTEMS AG, BADEN, CH Ref country code: DE Ref legal event code: R082 Ref document number: 502008007942 Country of ref document: DE Representative=s name: ZIMMERMANN & PARTNER PATENTANWAELTE MBB, DE Ref country code: DE Ref legal event code: R081 Ref document number: 502008007942 Country of ref document: DE Owner name: ABB SCHWEIZ AG, CH Free format text: FORMER OWNER: ABB TURBO SYSTEMS AG, BADEN, CH |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20210225 AND 20210303 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20210304 AND 20210310 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20220922 AND 20220928 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 502008007942 Country of ref document: DE Owner name: TURBO SYSTEMS SWITZERLAND LTD., CH Free format text: FORMER OWNER: ABB SCHWEIZ AG, BADEN, CH |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20230420 Year of fee payment: 16 Ref country code: CZ Payment date: 20230414 Year of fee payment: 16 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230419 Year of fee payment: 16 |