EP1260677B2 - Axial turbine with containment - Google Patents
Axial turbine with containment Download PDFInfo
- Publication number
- EP1260677B2 EP1260677B2 EP02010986.4A EP02010986A EP1260677B2 EP 1260677 B2 EP1260677 B2 EP 1260677B2 EP 02010986 A EP02010986 A EP 02010986A EP 1260677 B2 EP1260677 B2 EP 1260677B2
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- EP
- European Patent Office
- Prior art keywords
- turbine
- housing
- turbine disk
- exhaust gas
- disk
- 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.)
- Expired - Lifetime
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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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
Definitions
- the invention relates to an axial turbine of an exhaust gas turbocharger with a turbine housing formed by a Turbinenzuströmgephaseuse with a gas outlet side wall and a Turbinenabströmgephaseuse with a gas inlet side wall, in which a shaft supported turbine disk is arranged with blades, the turbine disk to the outside of an exhaust gas diffuser to form a flow channel is limited and in which a burst protection is provided in the turbine housing in the axial region of the turbine disk.
- burst protection in the form of a burst protection ring as an integral part of the turbine exhaust casing or a turbine disk cover ring bolted to the diffuser, for example by means of a clamping ring, was a sufficient means to prevent broken blades from exiting the turbine casing.
- the outer wall of the exhaust diffuser is designed in the axial region of the turbine disk in the radial direction with an outer and an inner contour and between the outer and inner contour an annular support wall is provided, wherein the outer contour is designed in the form of an annular extension piece over
- the axial area of the turbine disk is designed such that a between the support wall and Inner contour of the exhaust diffuser arranged cover ring is provided for the turbine disk, and that Turbinenzuström- and Turbinenabströmgephaseuse are interconnected so that the gas inlet side wall of Turbinenabströmgephinuses in the radial direction over the median plane of the turbine disk, a three-stage burst protection is achieved in the axial turbine, which meets all requirements Fulfills.
- the fragments are first (1st stage) thrown against the cover ring on the support wall of the exhaust diffuser. If the fragments are so large that the covering ring and the supporting wall do not withstand the stresses, then part of the kinetic energy of the fragments is dissipated by their breakage.
- At least the cover ring is therefore made of a non-brittle material such as steel or a steel alloy, while the other parts of the axial turbine can continue to consist of castings in a known manner, so that this energy dissipation is optimized. Also for the same purpose the cover ring is fixed to the support wall supporting by means of flexible connecting elements on the exhaust diffuser.
- the fragments meet radially outward on the annular extension piece of the outer contour of the exhaust diffuser.
- This annular or cylindrical extension piece in that it is designed to be pulled over the axial region of the turbine disk, can absorb a substantial part of the kinetic energy of the fragments.
- the annular extension piece of the outer contour of the exhaust gas diffuser is reinforced by means of radially arranged ribs in a preferred manner.
- the remaining energy of the fragments is absorbed by the gas inlet side wall of the turbine exhaust housing, which is located in the radial direction just above the center plane of the turbine disk, wherein a solid flange connection between Turbinenzuströmgeophuse, diffuser outer wall and Turbinenabströmgephaseuse is preferably rigid.
- the exhaust gas turbocharger of the type on which the drawing is based comprises an axial turbine 1 which has a turbine housing composed of a turbine inlet housing 2 with a gas outlet side wall 3 and a turbine exhaust housing 4 with a gas inlet side wall 5.
- a turbine housing composed of a turbine inlet housing 2 with a gas outlet side wall 3 and a turbine exhaust housing 4 with a gas inlet side wall 5.
- turbine housing a supported by a shaft 6 turbine disk 7 with blades 8 is arranged.
- the blades 8 of the turbine disk 7 are bounded to the outside by an exhaust gas diffuser 9 and received by this in a flow channel 14.
- the outer wall 10 of the Abgasduffusors 9 is executed in the axial region of the turbine disk 7 in the radial direction with an outer 11 and an inner contour 12. Between the outer 11 and inner contour 12, a cylindrical or annular support wall 13 is formed, wherein the outer contour 11 is designed in the form of an annular or cylindrical extension piece, which is designed to be pulled over the axial region of the turbine disk 7.
- the flow channel 14 is formed, which receives the exhaust gases of a motor not shown here and continues in a known manner to the blades 8 of the turbine disk 7.
- Upstream in the flow channel 14 is an outer 15 and an inner ring 16 comprehensive nozzle ring inserted, which is connected by means of connecting elements 17 and flanges 18 on outer 15 and inner ring 16 with the Turbinenzuströmgephaseuse 2.
- Axial between the nozzle ring 15, 16 and the exhaust diffuser 9 is a cover ring 19 for the rotor blades 7 of the turbine disk 7 sealingly clamped the flow channel 14 on the inner contour 12 of the exhaust gas diffuser 9, such that the nozzle ring forms a gap 28 between its outer ring 15 and cover ring 19 as well as between its inner ring 16 and the turbine disk 7.
- Another gap 21 is left between the turbine disk 7 and the inner wall 22 of the exhaust gas diffuser 9 in a known manner.
- the cover ring 19 is fixed to the support wall 13 of the exhaust gas diffuser 9 by means of flexible connecting elements 27, for example. Expansion screws, fixed to the exhaust gas diffuser 9.
- Turbinenzuström- 2 and Turbinenabströmgenosuse 4 are connected to each other such that the gas inlet side wall 5 of the Turbinenabströmgenosuses 4 in the radial direction is exactly aligned above the center plane 23 of the turbine disk 7.
- the annular extension piece of the outer contour 11 of the exhaust gas diffuser 9 has at its end a circumferential, or a plurality of individual mounting flange / s 24, which is clamped in the connection of Turbinenzuström- 2 and Turbinenabströmgephaseuse 4 and screwed by means of rigid connecting elements 25 with these.
- annular extension piece of the outer contour 11 is reinforced by means of radially arranged ribs 26.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Description
Die Erfindung betrifft eine Axialturbine eines Abgasturboladers mit einem aus einem Turbinenzuströmgehäuse mit einer gasaustrittseitigen Wand und einem Turbinenabströmgehäuse mit einer gaseintrittseitigen Wand ausgebildeten Turbinengehäuse, in diesem eine von einer Welle getragene Turbinenscheibe mit Laufschaufeln angeordnet ist, die Turbinenscheibe nach aussen von einem Abgasdiffusor unter Ausbildung eines Strömungskanals begrenzt ist und bei der im Turbinengehäuse im axialen Bereich der Turbinenscheibe ein Berstschutz vorgesehen ist.The invention relates to an axial turbine of an exhaust gas turbocharger with a turbine housing formed by a Turbinenzuströmgehäuse with a gas outlet side wall and a Turbinenabströmgehäuse with a gas inlet side wall, in which a shaft supported turbine disk is arranged with blades, the turbine disk to the outside of an exhaust gas diffuser to form a flow channel is limited and in which a burst protection is provided in the turbine housing in the axial region of the turbine disk.
Um hohe Ladedrücke zu erreichen, drehen heutige Abgasturbolader mit sehr hohen Umfangsgeschwindigkeiten. Insbesondere bei grossen Abgasturboladern führt dies dazu, dass die Bruchstücke einer eventuell geborstenen Turbinenscheibe, bzw. einer Laufschaufel nur durch aufwendige konstruktive Massnahmen im Turbinengehäuse zurückgehalten werden können.To achieve high boost pressures today's turbocharger rotate at very high peripheral speeds. In particular, in the case of large exhaust-gas turbochargers, this leads to the fact that the fragments of a possibly burst turbine disk or of a rotor blade can only be retained in the turbine housing by complex design measures.
In der Vergangenheit war bereits im Turbinengehäuse ein sich axial im Bereich der Turbinenscheibe erstreckender Schutz- oder Berstring vorgesehen.In the past, a protective or Berstring was already provided in the turbine housing axially extending in the region of the turbine disk.
Der grundsätzliche Aufbau und die Wirkungsweise derartiger Axialturbinen für Abgasturbolader sind an sich bekannt und bedürfen daher im vorliegenden Zusammenhang keiner näheren Erläuterung mehr. So ist beispielsweise in der
Im Verlauf der Entwicklung von axial durchströmten Turbinen für Abgasturbolader ging jedoch der Trend von langen schmalen Laufschaufeln hin zu kurzen breiten, sogenannten "wide cord"-Schaufeln mit reduzierter Schaufelzahl. Dadurch werden die einzelnen Laufschaufeln schwerer und die Turbinenscheiben, die diese Schaufeln auch bei hohen Umfangsgeschwindigkeiten sicher halten müssen, breiter. Diese Massnahmen führen natürlich dazu, dass die rotierenden Massen grösser werden. In Verbindung mit den heute üblichen hohen Umfangsgeschwindigkeiten entstehen dadurch erheblich gesteigerte Zentrifugalkräfte, denen durch eine bessere Ausführung von Schutzmassnahmen Rechnung getragen werden muss.However, in the development of turbocharged axial flow turbines, there has been a trend from long narrow blades to short, wide blade blades with reduced blade numbers. This makes the individual blades heavier and the turbine disks that keep these blades safe even at high peripheral speeds need, wider. Of course, these measures will cause the rotating masses to get bigger. In conjunction with today's usual high peripheral speeds caused by significantly increased centrifugal forces, which must be taken into account by better execution of protective measures.
In der Vergangenheit war ein voran beschriebener Berstschutz in Form eines Berstschutzringes als ein integraler Bestandteil des Turbinenabströmgehäuses oder ein Abdeckring für die Turbinenscheibe, der beispielsweise mittels eines Klemmringes am Diffusor angeschraubt ist, ein ausreichendes Mittel, um gebrochene Laufschaufeln am Ausdringen aus dem Turbinengehäuse zu hindern.In the past, previously described burst protection in the form of a burst protection ring as an integral part of the turbine exhaust casing or a turbine disk cover ring bolted to the diffuser, for example by means of a clamping ring, was a sufficient means to prevent broken blades from exiting the turbine casing.
Durch die gestiegenen Anforderungen reicht die voran beschriebene Massnahme jedoch nicht mehr aus, um einen sicheren Berstschutz zu gewährleisten, der ein Durchschlagen der Aussenwand des Turbinengehäuses zuverlässig verhindert und eine Gefährdung von Personen oder eine Beschädigung benachbarter Maschinenteile ausschliesst.Due to the increased requirements, the measure described above, however, is no longer sufficient to ensure a safe burst protection, which reliably prevents a penetration of the outer wall of the turbine housing and excludes a risk to persons or damage adjacent machine parts.
Hiervon ausgehend ist es daher die Aufgabe der vorliegenden Erfindung, eine Axialturbine eingangs erwähnter Art mit einfachen und kostengünstigen Mitteln so weiterzubilden, dass das Austreten von Bruchstücken einer geborstenen Turbinenscheibe oder eines geborstenen Laufrades aus dem Turbinengehäuse auch bei extrem hohen Umfangsgeschwindigkeiten verhindert werden kann, ohne einen zusätzlichen Berstschutz ausserhalb des Turbinengehäuses vorsehen zu müssen.On this basis, it is therefore an object of the present invention to develop an axial turbine of the type mentioned with simple and inexpensive means so that the escape of fragments of a ruptured turbine disk or a ruptured impeller from the turbine housing can be prevented even at extremely high peripheral speeds, without a to provide additional burst protection outside the turbine housing.
Diese Aufgabe wird erfindungsgemäss durch die kennzeichnenden Merkmale des Patentanspruchs 1 gelöst.This object is achieved according to the invention by the characterizing features of claim 1.
Dadurch, dass die Aussenwand des Abgasdiffusors im axialen Bereich der Turbinenscheibe in radialer Richtung mit einer Aussen- und einer Innenkontur ausgeführt ist und zwischen der Aussen- und Innenkontur eine ringförmige Stützwandung vorgesehen ist, wobei die Aussenkontur in Form eines ringförmigen Verlängerungsstücks ausgeführt ist, das über den axialen Bereich der Turbinenscheibe gezogen ausgestaltet ist, dass ein zwischen Stützwandung und Innenkontur des Abgasdiffusors angeordneter Abdeckring für die Turbinenscheibe vorgesehen ist, und dass Turbinenzuström- und Turbinenabströmgehäuse derart miteinander verbunden sind, dass die gaseintrittseitige Wand des Turbinenabströmgehäuses in radialer Richtung über der Mittelebene der Turbinenscheibe steht, wird ein dreistufiger Berstschutz in der Axialturbine erreicht, der alle Anforderungen erfüllt.Characterized in that the outer wall of the exhaust diffuser is designed in the axial region of the turbine disk in the radial direction with an outer and an inner contour and between the outer and inner contour an annular support wall is provided, wherein the outer contour is designed in the form of an annular extension piece over The axial area of the turbine disk is designed such that a between the support wall and Inner contour of the exhaust diffuser arranged cover ring is provided for the turbine disk, and that Turbinenzuström- and Turbinenabströmgehäuse are interconnected so that the gas inlet side wall of Turbinenabströmgehäuses in the radial direction over the median plane of the turbine disk, a three-stage burst protection is achieved in the axial turbine, which meets all requirements Fulfills.
Im Falle eines Bruches der Turbinenscheibe oder einer Turbinenschaufel werden die Bruchstücke zuerst (1. Stufe) an den Abdeckring an der Stützwandung des Abgasdiffusors geschleudert. Sind die Bruchstücke so gross, dass Abdeckring und Stützwandung den Beanspruchungen nicht standhalten, so wird durch deren Bruch ein Teil der kinetischen Energie der Bruchstücke dissipiert.In the case of a breakage of the turbine disk or a turbine blade, the fragments are first (1st stage) thrown against the cover ring on the support wall of the exhaust diffuser. If the fragments are so large that the covering ring and the supporting wall do not withstand the stresses, then part of the kinetic energy of the fragments is dissipated by their breakage.
Zumindest ist der Abdeckring deshalb aus einem nicht spröden Material wie Stahl oder einer Stahllegierung gefertigt, während die anderen Teile der Axialturbine weiterhin in bekannter Weise aus Gussteilen bestehen können, so dass diese Energiedissipation optimiert ist. Auch zum gleichen Zweck ist der Abdeckring sich an der Stützwandung abstützend mittels flexibler Verbindungselemente am Abgasdiffusor fixiert.At least the cover ring is therefore made of a non-brittle material such as steel or a steel alloy, while the other parts of the axial turbine can continue to consist of castings in a known manner, so that this energy dissipation is optimized. Also for the same purpose the cover ring is fixed to the support wall supporting by means of flexible connecting elements on the exhaust diffuser.
In der zweiten Stufe treffen die Bruchstücke radial nach aussen auf das ringförmige Verlängerungsstück der Aussenkontur des Abgasdiffusors. Dieses ringförmige, bzw. zylinderförmige Verlängerungsstück kann dadurch, dass es über den axialen Bereich der Turbinenscheibe gezogen ausgestaltet ist, einen wesentlichen Teil der Bewegungsenergie der Bruchstücke aufnehmen. Dazu ist in bevorzugter Weise das ringförmige Verlängerungsstück der Aussenkontur des Abgasdiffusors mittels radial angeordneter Rippen verstärkt.In the second stage, the fragments meet radially outward on the annular extension piece of the outer contour of the exhaust diffuser. This annular or cylindrical extension piece, in that it is designed to be pulled over the axial region of the turbine disk, can absorb a substantial part of the kinetic energy of the fragments. For this purpose, the annular extension piece of the outer contour of the exhaust gas diffuser is reinforced by means of radially arranged ribs in a preferred manner.
In der dritten Stufe wird die restliche Energie der Bruchstücke durch die in radialer Richtung genau über der Mittelebene der Turbinenscheibe stehenden gaseintrittseitigen Wand des Turbinenabströmgehäuses aufgenommen, wobei eine massive Flanschverbindung zwischen Turbinenzuströmgehäuse, Diffusoraussenwand und Turbinenabströmgehäuse bevorzugt starr ausgeführt ist.In the third stage, the remaining energy of the fragments is absorbed by the gas inlet side wall of the turbine exhaust housing, which is located in the radial direction just above the center plane of the turbine disk, wherein a solid flange connection between Turbinenzuströmgehäuse, diffuser outer wall and Turbinenabströmgehäuse is preferably rigid.
Die Erfindung soll nachfolgend aus einer Beispielsbeschreibung anhand der Zeichnung näher erläutert werden.The invention will be explained in more detail below from an example description with reference to the drawing.
Die nachstehend beschriebene Zeichnung zeigt einen Teillängsschnitt durch eine erfindungsgemässe Axialturbine eines Abgasturboladers. Es sind dabei nur die für das Verständnis der Erfindung wesentlichen Element dargestellt und bezeichnet. Nicht dargestellt ist beispielsweise die Verdichterseite des Abgasturboladers. Die Strömungsrichtung des Abgases ist mittels Pfeilen angedeutet.The drawing described below shows a partial longitudinal section through an inventive axial turbine of an exhaust gas turbocharger. There are only shown and designated the essential element for the understanding of the invention. Not shown, for example, the compressor side of the exhaust gas turbocharger. The flow direction of the exhaust gas is indicated by arrows.
Der Abgasturbolader der in der Zeichnung zugrundeliegenden Art umfasst eine Axialturbine 1, die ein aus einem Turbinenzuströmgehäuse 2 mit einer gasaustrittseitigen Wand 3 und einem Turbinenabströmgehäuse 4 mit einer gaseintrittseitigen Wand 5 zusammengesetztes Turbinengehäuse besitzt. Im Turbinengehäuse ist eine von einer Welle 6 getragene Turbinenscheibe 7 mit Laufschaufeln 8 angeordnet.The exhaust gas turbocharger of the type on which the drawing is based comprises an axial turbine 1 which has a turbine housing composed of a
Die Laufschaufeln 8 der Turbinenscheibe 7 werden nach aussen von einem Abgasdiffusor 9 begrenzt und von diesem in einem Strömungskanal 14 aufgenommen. Die Aussenwand 10 des Abgasduffusors 9 ist im axialen Bereich der Turbinenscheibe 7 in radialer Richtung mit einer Aussen- 11 und einer Innenkontur 12 ausgeführt. Zwischen der Aussen- 11 und Innenkontur 12 ist eine zylindrische, bzw. ringförmige Stützwandung 13 angeformt, wobei die Aussenkontur 11 in Form eines ringförmigen, bzw. zylindrischen Verlängerungsstückes ausgeführt ist, das über den axialen Bereich der Turbinenscheibe 7 gezogen ausgestaltet ist.The
Zwischen der Turbinenscheibe 7 und dem Turbinengehäuse ist der Strömungskanal 14 ausgebildet, der die Abgase eines hier nicht dargestellten Motors aufnimmt und in bekannter Weise zu den Laufschaufeln 8 der Turbinenscheibe 7 weiterführt. Stromauf im Strömungskanal 14 ist ein einen Aussen- 15 und einen Innenring 16 umfassender Düsenring eingelegt, der mittels Verbindungselementen 17 und Flanschen 18 an Aussen- 15 und Innenring 16 mit dem Turbinenzuströmgehäuse 2 verbunden ist.Between the
Axial zwischen Düsenring 15, 16 und Abgasdiffusor 9 ist ein Abdeckring 19 für die Laufschaufeln 8 der Turbinenscheibe 7 den Strömungskanal 14 an der Innenkontur 12 des Abgasdiffusors 9 abdichtend eingespannt, derart dass der Düsenring sowohl zwischen seinem Aussenring 15 und Abdeckring 19 einen Spalt 28 als auch zwischen seinem Innenring 16 und der Turbinenscheibe 7 einen Spalt 20 ausbildet. Ein weiterer Spalt 21 ist zwischen Turbinenscheibe 7 und der Innenwand 22 des Abgasdiffusors 9 in bekannter Weise belassen.Axial between the
Der Abdeckring 19 ist sich an der Stützwandung 13 des Abgasdiffusors 9 abstützend mittels flexibler Verbindungselemente 27, bspw. Dehnschrauben, am Abgasdiffusor 9 fixiert.The
Das Turbinenzuström- 2 und Turbinenabströmgehäuse 4 sind derart miteinander verbunden, dass die gaseintrittseitige Wand 5 des Turbinenabströmgehäuses 4 in radialer Richtung genau fluchtend über der Mittelebene 23 der Turbinenscheibe 7 steht.The Turbinenzuström- 2 and Turbinenabströmgehäuse 4 are connected to each other such that the gas
Das ringförmige Verlängerungsstück der Aussenkontur 11 des Abgasdiffusors 9 weist endseitig einen umlaufenden, oder mehrere einzelne Befestigungsflansch/e 24 auf, der/die in die Verbindung von Turbinenzuström- 2 und Turbinenabströmgehäuse 4 eingeklemmt und mittels starrer Verbindungselemente 25 mit diesen verschraubt ist.The annular extension piece of the outer contour 11 of the exhaust gas diffuser 9 has at its end a circumferential, or a plurality of individual mounting flange /
Des weiteren ist das ringförmige Verlängerungsstück der Aussenkontur 11 mittels radial angeordneter Rippen 26 verstärkt.Furthermore, the annular extension piece of the outer contour 11 is reinforced by means of radially arranged
- 11
- Axialturbineaxial turbine
- 22
- TurbinenzuströmgehäuseTurbinenzuströmgehäuse
- 33
- Gasaustrittseitige WandGas outlet side wall
- 44
- TurbinenabströmgehäuseTurbinenabströmgehäuse
- 55
- Gaseintrittseitige WandGas inlet side wall
- 66
- Wellewave
- 77
- Turbinenscheibeturbine disk
- 88th
- Laufschaufelblade
- 99
- Abgasdiffusorexhaust diffuser
- 1010
- Aussenwandouter wall
- 1111
- Aussenkonturouter contour
- 1212
- Innenkonturinner contour
- 1313
- Stützwandungsupporting wall
- 1414
- Strömungskanalflow channel
- 1515
- Aussenring des DüsenringsOuter ring of the nozzle ring
- 1616
- Innenring des DüsenringsInner ring of the nozzle ring
- 1717
- Verbindungselementefasteners
- 1818
- Flanscheflanges
- 1919
- Abdeckringcover ring
- 2020
- Spaltgap
- 2121
- Spaltgap
- 2222
- Innenwand des AbgasdiffusorsInner wall of the exhaust diffuser
- 2323
- Mittelebenemidplane
- 2424
- Befestigungsflanschmounting flange
- 2525
- starres Verbindungselementrigid connection element
- 2626
- Rippenribs
- 2727
- flexibles Verbindungselementflexible connection element
- 2828
- Spaltgap
Claims (1)
- An axial turbine (1) of an exhaust-gas-driven turbo-charger comprising a turbine housing, which is formed by a turbine inflow housing (2) with a gas-outlet-side wall (3) and a turbine outflow housing (4) with a gas-inlet-side wall (5) and in which is disposed a turbine disk (7) carried by a shaft (6) and having rotating blades (8), wherein the turbine disk (7) is delimited in the outward direction by an exhaust gas diffuser (9) with the formation of a flow channel (14) and wherein in the turbine housing in the axial region of the turbine disk a rupture protection device is provided,
wherein the outer wall (10) of the exhaust gas diffuser (9) in the axial region of the turbine disk (7) is designed in the radial direction with an external contour (11) and an internal contour (12) and turbine inflow housing (2) and turbine outflow housing (4) are connected to one another in such a way that the gas-inlet-side wall (5) of the turbine outflow housing (4) is situated in the radial direction over the centre plane (23) of the turbine disk (7),
wherein an annular support wall (13) is provided between the external contour (11) and the internal contour (12), and
wherein the external contour (11) takes the form of an annular extension piece that is drawn over the axial region of the turbine disk (7),
wherein a cover ring (19) disposed between support wall (13) and internal contour (12) of the exhaust gas diffuser (9) is provided for the turbine disk (7) and rotating blades (8),
characterized in that
the cover ring (19) is fixed, so as to be supported against the support wall (13), by means of flexible connection elements (27) to the exhaust gas diffuser (9),
at least the cover ring (19) of the exhaust gas diffuser (9) is made of a non-brittle material such as steel or a steel alloy.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE2001125250 DE10125250C5 (en) | 2001-05-23 | 2001-05-23 | Axial turbine of an exhaust turbocharger with internal burst protection |
| DE10125250 | 2001-05-23 |
Publications (4)
| Publication Number | Publication Date |
|---|---|
| EP1260677A2 EP1260677A2 (en) | 2002-11-27 |
| EP1260677A3 EP1260677A3 (en) | 2005-02-09 |
| EP1260677B1 EP1260677B1 (en) | 2006-06-28 |
| EP1260677B2 true EP1260677B2 (en) | 2016-11-02 |
Family
ID=7685942
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP02010986.4A Expired - Lifetime EP1260677B2 (en) | 2001-05-23 | 2002-05-17 | Axial turbine with containment |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP1260677B2 (en) |
| JP (1) | JP4153722B2 (en) |
| DE (2) | DE10125250C5 (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006039064B4 (en) | 2006-08-19 | 2020-06-25 | Man Energy Solutions Se | Exhaust gas turbocharger for an internal combustion engine |
| CN101506476B (en) * | 2006-08-24 | 2011-09-14 | Abb涡轮***有限公司 | Turbine housing |
| DE102008061398A1 (en) | 2008-12-10 | 2010-06-17 | Man Diesel Se | Method for creating burst protection for flow machine, particularly exhaust gas turbocharger, involves wrapping machine housing of flow machine partially with metal or Kevlar netting |
| JP4905565B2 (en) * | 2010-02-04 | 2012-03-28 | トヨタ自動車株式会社 | Turbocharger and its wheel housing |
| JP5889266B2 (en) * | 2013-11-14 | 2016-03-22 | 三菱重工業株式会社 | Turbine |
| DE202014002981U1 (en) | 2014-04-08 | 2014-04-16 | Man Diesel & Turbo Se | Axial turbine for an exhaust gas turbocharger |
| DE202014002980U1 (en) | 2014-04-08 | 2014-04-16 | Man Diesel & Turbo Se | Axial turbine for an exhaust gas turbocharger |
| CN104454146A (en) * | 2014-10-27 | 2015-03-25 | 中国北车集团大连机车研究所有限公司 | Protection device for fracture of axial turbine of turbocharger |
| CN106368740B (en) * | 2016-11-14 | 2017-12-05 | 沈阳航空航天大学 | A kind of double wall outer ring structure of Gas Turbine |
| DE102017120543A1 (en) | 2017-09-06 | 2019-03-07 | Man Diesel & Turbo Se | Axial turbine of a turbocharger and turbocharger |
| DE102018105827A1 (en) * | 2018-03-14 | 2019-09-19 | Man Energy Solutions Se | Formwork of a turbocharger and turbocharger |
| CN109057877B (en) * | 2018-10-26 | 2023-11-28 | 中国船舶重工集团公司第七0三研究所 | Turbine stator structure for helium turbine |
| DE102018127719A1 (en) * | 2018-11-07 | 2020-05-07 | Man Energy Solutions Se | Compensation device for compensating thermal relative movements |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3462169D1 (en) * | 1983-06-29 | 1987-02-26 | Bbc Brown Boveri & Cie | Axial turbine for a turbo charger |
| DE19618313B4 (en) * | 1996-05-08 | 2005-07-21 | Abb Turbo Systems Ag | Axial turbine of an exhaust gas turbocharger |
| US6049523A (en) * | 1997-05-30 | 2000-04-11 | Lucent Technologies Inc. | System and method for achieving efficient coordination of protection switching |
-
2001
- 2001-05-23 DE DE2001125250 patent/DE10125250C5/en not_active Expired - Lifetime
-
2002
- 2002-05-17 DE DE50207358T patent/DE50207358D1/en not_active Expired - Lifetime
- 2002-05-17 JP JP2002142424A patent/JP4153722B2/en not_active Expired - Fee Related
- 2002-05-17 EP EP02010986.4A patent/EP1260677B2/en not_active Expired - Lifetime
Non-Patent Citations (2)
| Title |
|---|
| A. RIPPL, DR.-ING.: "Theoretical and experimental investigations for a new turbocharger generation", vol. 2, 2001, pages: 193 - 195-202 † |
| TCA turbocharges, The new generation Broschüre der MAN Diesel SE † |
Also Published As
| Publication number | Publication date |
|---|---|
| DE10125250C5 (en) | 2007-03-29 |
| EP1260677A2 (en) | 2002-11-27 |
| JP2003003804A (en) | 2003-01-08 |
| DE10125250C1 (en) | 2002-09-12 |
| JP4153722B2 (en) | 2008-09-24 |
| EP1260677A3 (en) | 2005-02-09 |
| DE50207358D1 (en) | 2006-08-10 |
| EP1260677B1 (en) | 2006-06-28 |
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