EP1890011A1 - Axial flow turbine with slotted shroud - Google Patents

Axial flow turbine with slotted shroud Download PDF

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Publication number
EP1890011A1
EP1890011A1 EP06405335A EP06405335A EP1890011A1 EP 1890011 A1 EP1890011 A1 EP 1890011A1 EP 06405335 A EP06405335 A EP 06405335A EP 06405335 A EP06405335 A EP 06405335A EP 1890011 A1 EP1890011 A1 EP 1890011A1
Authority
EP
European Patent Office
Prior art keywords
turbine
ring
blades
segments
exhaust gas
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP06405335A
Other languages
German (de)
French (fr)
Inventor
Josef Bättig
Karl-Heinz Rohne
Matthias Richner
William Gizzi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP06405335A priority Critical patent/EP1890011A1/en
Priority to PCT/EP2007/058202 priority patent/WO2008017681A1/en
Publication of EP1890011A1 publication Critical patent/EP1890011A1/en
Withdrawn legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous

Definitions

  • the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.
  • the axial turbine comprises a turbine wheel with blades and a cover ring radially surrounding the blades.
  • Exhaust gas turbochargers are used to increase the performance of internal combustion engines, in particular reciprocating engines.
  • an exhaust gas turbocharger usually has a centrifugal compressor and a radial or axial turbine. From a certain size it makes sense to use axial turbines for the drive of the compressor. So that the exhaust gas can not bypass the blades of the axial turbine, they are surrounded by a housing part radially outward. This housing part thus limits the flow channel radially outward in the region of the rotor blades.
  • This housing part may be formed as an integral part of a diffuser arranged downstream of the rotor blades, as an integral part of a radially outer housing wall of a nozzle ring arranged upstream of the rotor blades, or as a separate cover ring.
  • the exhaust gas is heavily contaminated with soot, ash and other pollutants. These are deposited over time on certain components of the exhaust gas turbine, in particular on the blades, the cover ring, the guide vanes of the nozzle ring and the diffuser, and reduce the efficiency of the exhaust gas turbine, which reduces the overall performance of the internal combustion engine. For this reason, the soiled components of the exhaust gas turbine must be cleaned at regular intervals. Usually, the Exhaust gas turbine washed with water. To minimize the burden on the contaminated components, turbocharger manufacturers dictate that the load on the internal combustion engine be reduced during the wash cycle. As a result, the temperature of the affected components is already slightly reduced before the washing process, resulting in smaller loads.
  • CH 35 11 42 discloses an axial turbine having a turbine wheel with blades and a cover ring radially surrounding the blades, wherein the cover ring is divided into a plurality of separate segments.
  • the object of the present invention is to improve the exhaust gas turbine of an exhaust gas turbocharger such that it also withstands cleaning operations under full load without signs of wear on the components of the exhaust gas turbine.
  • the cover ring is radially divided outside the rotor blades of the turbine wheel through slots in a plurality of annular segments which are separated from one another in the circumferential direction.
  • the segments according to the invention are connected via thin ribs to a circumferential ring, which is not influenced by the washing process.
  • the cover ring loses its tangential relationship as a ring.
  • the cover pulls in a sudden cooling, as occurs during cleaning of the exhaust gas turbine, no longer together in the radial direction.
  • this means that the cover ring maintains the diameter of the hot state during the cleaning process and only the slots between the individual segments are larger.
  • a strip of the rotor blades of the turbine wheel can be prevented at the housing parts arranged radially outside.
  • the segments are connected in both axial directions via ribs, each with a circumferential ring.
  • the effect of the expanding slots can be enhanced with rapid cooling, since no temperature gradient in the axial direction results in the area radially outside the blades of the turbine wheel during the cleaning process.
  • the slots are advantageously as small as possible, ie in the microscopic range formed.
  • Fig. 1 shows a section through the axis of an axial turbine of an exhaust gas turbocharger according to the prior art.
  • the turbine wheel 10 rotatably mounted in a housing includes a hub 11 and a plurality of blades 12 disposed thereon.
  • the exhaust flow needed to drive the turbine is transmitted through a flow channel from the gas inlet housing 42 via the nozzle ring 20 to the blades of the turbine wheel and further through the diffuser 31 led to the gas outlet housing 41.
  • the nozzle ring 20 comprises an inner wall 21 and an outer wall 22 and vanes 23 arranged therebetween.
  • the walls of the nozzle ring as well as the diffuser are housing parts which delimit the flow channel of the exhaust gas.
  • the flow channel in the region of the rotor blades is delimited by a cover ring radially enclosing the rotor blades.
  • This housing part can, as in FIG. 1, be formed as an integral part of the diffuser 31 arranged downstream of the rotor blades.
  • the cover ring may be formed as an integral part of the radially outer housing wall 22 of the nozzle ring or as an independent component.
  • FIG. 2 shows a section through the axis of an axial turbine of an exhaust-gas turbocharger with a cover ring 5 designed according to the invention, which delimits the flow channel in the area radially outside the rotor blades 12 of the turbine wheel.
  • the cover ring is shown enlarged in Fig. 3 again.
  • the cover ring comprises a plurality of segments 51 which are separated from one another by slits 57 along the circumference and at least one circumferential one Ring 54 and 55, respectively.
  • the segments are arranged directly radially outside the rotor blades. In this area, the cover ring thus loses its tangential relationship.
  • the cover ring therefore does not contract even in the case of a sudden cooling in the radial direction. Only the slots 57 between the individual segments are larger. As a result, a strip of the turbine can be prevented.
  • the segments 51 are connected via ribs 52 and 53, respectively, to the encircling rings 54 and 55, respectively.
  • the cover ring 5 is advantageously fastened to the diffuser 31 or the gas outlet housing 41, or, as indicated in FIG. 2, clamped between the two parts.
  • the cover ring can be screwed tightly by means of fastening holes 6 arranged in the holes 56.
  • the peripheral rings are advantageously separated by at least one housing part of the flow channel in the region of the blades, so that no cold water can reach the rings during the cleaning process. Thus, the rings undergo no cooling during the cleaning of the exhaust gas turbine and thus do not contract thermally.
  • FIG. 4 shows a first embodiment of the cover ring 5 according to the invention with a ring 55 arranged on the outlet side, on which the segments 51 are fastened in each case via ribs 53.
  • FIG. 5 shows a second embodiment of the cover ring 5 according to the invention with a ring 54 arranged on the inlet side and an outlet-side ring 55 on which the segments 51 are respectively fastened via ribs 52 and 53.
  • the rings 54 and 55 are set back with respect to the radially inner surface of the segments in the radial direction, so that they do not come in the installed state directly in contact with the flow or the cleaning liquid.
  • the ribs 52 and 53 are made as thin as possible to the heat conduction or temperature compensation between the segments 51 and the rings 54, respectively. 55 to minimize the washing.
  • the slots 57 between the individual segments 51 are formed as thin as possible. Since the temperature of the segments in operation is likely to be higher than the temperature during manufacture, the slots formed during manufacture close during operation due to the expansion of the segments along the circumference.
  • the slot width should, at least during operation of the exhaust gas turbine, be in the microscopic range of a few micrometers.
  • the inventive exhaust gas turbine can be used instead of driving a compressor as a power turbine, about to drive an electric generator or a mechanical machine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

Axial turbine comprises a covering ring (5) divided into segments (51) by slots running along the periphery, in which each segment is connected to peripheral rings (54, 55) via ribs (52, 53). An independent claim is also included for an exhaust gas turbocharger with the above axial turbine. Preferred Features: The slots in the covering ring run in the axial direction so that the segments are completely separated from each other in the peripheral direction. One of the peripheral rings is spaced from the covering ring in the axial direction.

Description

Technisches GebietTechnical area

Die Erfindung bezieht sich auf das Gebiet der Abgasturbolader für aufgeladene Brennkraftmaschinen.The invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.

Sie betrifft die Axialturbine eines Abgasturboladers, wobei die Axialturbine ein Turbinenrad mit Laufschaufeln und einen die Laufschaufeln radial umgebenden Abdeckring umfasst.It relates to the axial turbine of an exhaust gas turbocharger, wherein the axial turbine comprises a turbine wheel with blades and a cover ring radially surrounding the blades.

Stand der TechnikState of the art

Abgasturbolader werden zur Leistungssteigerung von Brennkraftmaschinen, insbesondere Hubkolbenmotoren, eingesetzt. Dabei besitzt ein Abgasturbolader üblicherweise einen Radialverdichter und eine Radial- oder Axialturbine. Ab einer bestimmten Grösse ist es sinnvoll Axialturbinen für den Antrieb des Verdichters einzusetzen. Damit das Abgas die Laufschaufeln der Axialturbine nicht umgehen kann, werden diese von einem Gehäuseteil radial aussen umschlossen. Dieses Gehäuseteil begrenzt somit im Bereich der Laufschaufeln den Strömungskanal radial nach Aussen. Dieses Gehäuseteil kann als integraler Bestandteil eines stromab der Laufschaufeln angeordneten Diffusors, als integraler Bestandteil einer radial äusseren Gehäusewand eines stromauf der Laufschaufeln angeordneten Düsenrings oder als separater Abdeckring ausgebildet sein.Exhaust gas turbochargers are used to increase the performance of internal combustion engines, in particular reciprocating engines. In this case, an exhaust gas turbocharger usually has a centrifugal compressor and a radial or axial turbine. From a certain size it makes sense to use axial turbines for the drive of the compressor. So that the exhaust gas can not bypass the blades of the axial turbine, they are surrounded by a housing part radially outward. This housing part thus limits the flow channel radially outward in the region of the rotor blades. This housing part may be formed as an integral part of a diffuser arranged downstream of the rotor blades, as an integral part of a radially outer housing wall of a nozzle ring arranged upstream of the rotor blades, or as a separate cover ring.

Je nach verwendetem Treibstoff, vor allem bei Schweröl (Heavy Fuel Oil, HFO), ist das Abgas stark mit Russ, Asche und anderen Schadstoffen verschmutzt. Diese lagern sich mit der Zeit auf gewissen Bauteilen der Abgasturbine, insbesondere auf den Laufschaufeln, dem Abdeckring, den Leitschaufeln des Düsenrings sowie dem Diffusor, ab und mindern den Wirkungsgrad der Abgasturbine, was insgesamt die Leistung der Brennkraftmaschine reduziert. Aus diesem Grund müssen die verschmutzten Bauteile der Abgasturbine in regelmässigen Abständen gereinigt werden. Üblicherweise wird die Abgasturbine mit Wasser gewaschen. Um die Belastungen für die verschmutzten Bauteil gering zu halten, wird von Turboladerherstellern vorgeschrieben, die Last der Brennkraftmaschine während des Waschvorgangs zu reduzieren. Dadurch wird die Temperatur der betroffenen Bauteile schon vor dem Waschvorgang etwas reduziert was zu kleineren Belastungen führt.Depending on the fuel used, especially in heavy fuel oil (HFO), the exhaust gas is heavily contaminated with soot, ash and other pollutants. These are deposited over time on certain components of the exhaust gas turbine, in particular on the blades, the cover ring, the guide vanes of the nozzle ring and the diffuser, and reduce the efficiency of the exhaust gas turbine, which reduces the overall performance of the internal combustion engine. For this reason, the soiled components of the exhaust gas turbine must be cleaned at regular intervals. Usually, the Exhaust gas turbine washed with water. To minimize the burden on the contaminated components, turbocharger manufacturers dictate that the load on the internal combustion engine be reduced during the wash cycle. As a result, the temperature of the affected components is already slightly reduced before the washing process, resulting in smaller loads.

Da die Betreiber der Brennkraftmaschinen immer weniger gewillt sind die Last der Brennkraftmaschine während des Reinigungsvorgangs zu reduzieren, triff das kühle Wasser auf die sehr heissen Bauteile. Da das Turbinenrad eine massive Scheibe jedoch der Abdeckring im Vergleich dazu nur ein dünnes Rohr ist, kühlt der Abdeckring viel schneller ab als das Turbinenrad. Das führt dazu, dass sich dieser schneller in radialer Richtung zusammenzieht. Aufgrund der engen Toleranzen zwischen den radial äussersten Spitzen der Laufschaufeln des Turbinenrades und dem angrenzenden Abdeckring kommt es deshalb häufig vor, dass die Laufschaufeln des Turbinenrades während des Waschvorgangs am Abdeckring streifen. Dies führt zu Abnutzung sowohl am Abdeckring als auch an den Spitzen der Laufschaufeln, was wiederum den Wirkungsgrad der Turbine mindert und insgesamt die Leistung der Brennkraftmaschine reduziert.Since the operators of the internal combustion engines are less willing to reduce the load of the internal combustion engine during the cleaning process, meet the cool water on the very hot components. Since the turbine wheel is a massive disk, however, the cover ring is only a thin tube compared to that, the cover ring cools much faster than the turbine wheel. This causes it to contract faster in the radial direction. Because of the tight tolerances between the radially outermost tips of the blades of the turbine wheel and the adjacent cover ring, it is therefore often the case that the blades of the turbine wheel during the washing process on the cover ring. This leads to wear both on the cover ring and on the tips of the blades, which in turn reduces the efficiency of the turbine and overall reduces the performance of the internal combustion engine.

CH 35 11 42 offenbart eine Axialturbine mit einem Turbinenrad mit Laufschaufeln und einem die Laufschaufeln radial umgebenden Abdeckring, wobei der Abdeckring in mehrere voneinander getrennte Segmente unterteilt ist. CH 35 11 42 discloses an axial turbine having a turbine wheel with blades and a cover ring radially surrounding the blades, wherein the cover ring is divided into a plurality of separate segments.

Kurze Darstellung der ErfindungBrief description of the invention

Die Aufgabe der vorliegenden Erfindung besteht darin, die Abgasturbine eines Abgasturboladers derart zu verbessern, dass sie auch Reinigungsvorgängen unter Volllast ohne Abnutzungserscheinungen an den Bauteilen der Abgasturbine standhält.The object of the present invention is to improve the exhaust gas turbine of an exhaust gas turbocharger such that it also withstands cleaning operations under full load without signs of wear on the components of the exhaust gas turbine.

Dies wird erfindungsgemäss erreicht, indem der Abdeckring radial ausserhalb der Laufschaufeln des Turbinenrades durch Schlitze in mehrere, in Umfangsrichtung voneinander getrennte Ringsegmente aufgeteilt ist. Damit die einzelnen Segmente trotz der Schlitze einen Zusammenhang haben, sind die Segmente erfindungsgemäss über dünne Rippen mit einem Umlaufenden Ring verbunden, der vom Waschvorgang nicht beeinflusst wird.This is achieved according to the invention in that the cover ring is radially divided outside the rotor blades of the turbine wheel through slots in a plurality of annular segments which are separated from one another in the circumferential direction. In order for the individual segments to have a connection despite the slots, the segments according to the invention are connected via thin ribs to a circumferential ring, which is not influenced by the washing process.

Der Abdeckring verliert dank der Segmentierung seinen tangentialen Zusammenhang als Ring. Damit zieht sich der Abdeckring bei einer schlagartigen Abkühlung, wie sie beim Reinigen der Abgasturbine vorkommt, nicht mehr in radialer Richtung zusammen. Konkret bedeutet dies, dass der Abdeckring den Durchmesser des heissen Zustandes während des Reinigungsvorgangs beibehält und lediglich die Schlitze zwischen den einzelnen Segmenten grösser werden. Dadurch kann ein Streifen der Laufschaufeln des Turbinenrades an den radial ausserhalb angeordneten Gehäuseteilen verhindert werden.Thanks to the segmentation, the cover ring loses its tangential relationship as a ring. Thus, the cover pulls in a sudden cooling, as occurs during cleaning of the exhaust gas turbine, no longer together in the radial direction. Specifically, this means that the cover ring maintains the diameter of the hot state during the cleaning process and only the slots between the individual segments are larger. As a result, a strip of the rotor blades of the turbine wheel can be prevented at the housing parts arranged radially outside.

Vorteilhafterweise sind die Segmente in beiden axialen Richtungen über Rippen mit jeweils einem umlaufenden Ring verbunden. Dadurch kann der Effekt der sich aufspreizenden Schlitze bei raschem Abkühlen verstärkt werden, da sich in dem Bereich radial ausserhalb der Laufschaufeln des Turbinenrades während des Reinigungsvorgangs kein Temperaturgradient in axialer Richtung ergibt.Advantageously, the segments are connected in both axial directions via ribs, each with a circumferential ring. As a result, the effect of the expanding slots can be enhanced with rapid cooling, since no temperature gradient in the axial direction results in the area radially outside the blades of the turbine wheel during the cleaning process.

Erfindungsgemäss können sich somit Segmente, die sich nicht stark abkühlen, weniger stark schrumpfen als solche, die stark abkühlen. Bei einem Waschvorgang können sich die einzelnen Segmente individuell in Umfangsrichtung zusammenziehen, ohne dass eine grosse und ungleichmässige Durchmesserreduktion der Abdeckringzone erfolgt. Durch die Segmentierung wird der Einfluss der lokalen Schrumpfzonen auf den Umfang bzw. Durchmesser aufgehoben.Thus, according to the invention, segments which do not cool strongly may shrink less than those which cool strongly. In a washing process, the individual segments can contract individually in the circumferential direction, without a large and uneven diameter reduction of the Abdeckringzone occurs. The segmentation eliminates the influence of the local shrinkage zones on the circumference or diameter.

Um den Wirkungsgrad der Turbine im normalen Betrieb durch die Schlitze zwischen den Segmenten nicht zu beeinträchtigen, sind die Schlitze vorteilhafterweise möglichst klein, also im mikroskopischen Bereich, ausgebildet.In order not to impair the efficiency of the turbine during normal operation through the slots between the segments, the slots are advantageously as small as possible, ie in the microscopic range formed.

Weitere Vorteile ergeben sich aus den abhängigen Ansprüchen.Further advantages emerge from the dependent claims.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Folgend sind anhand der Zeichnungen Ausführungsformen des Abgasturboladers mit erfindungsgemäss ausgeführten Turbinenabdeckringen beschrieben. Hierbei zeigt

Fig. 1
ein Schnittbild einer Abgasturbine gemäss dem Stand der Technik, mit einem im Diffusor integrierten Abdeckring über den Laufschaufeln der Turbine,
Fig. 2
ein Schnittbild einer Abgasturbine mit einem erfindungsgemäss ausgebildeten Abdeckring,
Fig. 3
einen vergrössert dargestellten Ausschnitt des Abdeckrings nach Fig. 2,
Fig. 4
eine isometrische Darstellung einer ersten Ausführungsform des erfindungsgemäss ausgebildeten Abdeckrings, und
Fig. 5
eine isometrische Darstellung einer zweiten Ausführungsform des erfindungsgemäss ausgebildeten Abdeckrings.
Embodiments of the exhaust gas turbocharger with turbine exhaust rings according to the invention are described below with reference to the drawings. This shows
Fig. 1
a sectional view of an exhaust gas turbine according to the prior art, with a built-in diffuser cover over the blades of the turbine,
Fig. 2
a sectional view of an exhaust gas turbine with an inventively designed cover ring,
Fig. 3
an enlarged detail of the cover ring according to FIG. 2,
Fig. 4
an isometric view of a first embodiment of the present invention formed cover, and
Fig. 5
an isometric view of a second embodiment of the present invention formed cover ring.

Weg zur Ausführung der ErfindungWay to carry out the invention

Fig. 1 zeigt einen Schnitt durch die Achse einer Axialturbine eines Abgasturboladers gemäss dem Stand der Technik. Das drehbar in einem Gehäuse gelagerte Turbinenrad 10 umfasst eine Nabe 11 und darauf angeordnet eine Vielzahl von Laufschaufeln 12. Die für den Antrieb der Turbine benötigte Abgasströmung wird durch einen Strömungskanal vom Gaseintrittsgehäuse 42 über den Düsenring 20 auf die Laufschaufeln des Turbinenrades und weiter über den Diffusor 31 zum Gasaustrittsgehäuse 41 geführt. Der Düsenring 20 umfasst eine Innenwand 21 und eine Aussenwand 22 sowie dazwischen angeordnete Leitschaufeln 23. Die Wände des Düsenrings wie auch der Diffusor sind Gehäuseteile, welche den Strömungskanal des Abgases begrenzen.Fig. 1 shows a section through the axis of an axial turbine of an exhaust gas turbocharger according to the prior art. The turbine wheel 10 rotatably mounted in a housing includes a hub 11 and a plurality of blades 12 disposed thereon. The exhaust flow needed to drive the turbine is transmitted through a flow channel from the gas inlet housing 42 via the nozzle ring 20 to the blades of the turbine wheel and further through the diffuser 31 led to the gas outlet housing 41. The nozzle ring 20 comprises an inner wall 21 and an outer wall 22 and vanes 23 arranged therebetween. The walls of the nozzle ring as well as the diffuser are housing parts which delimit the flow channel of the exhaust gas.

Damit das Abgas den Laufschaufeln des Turbinenrades nicht ausweichen kann, wird der Strömungskanal im Bereich der Laufschaufeln von einem die Laufschaufeln radial umschliessenden Abdeckring begrenzt. Dieses Gehäuseteil kann, wie in der Fig. 1, als integraler Bestandteil des stromab der Laufschaufeln angeordneten Diffusors 31 ausgebildet sein. Alternativ kann der Abdeckring als integraler Bestandteil der radial äusseren Gehäusewand 22 des Düsenrings oder als eigenständiges Bauteil ausgebildet sein.So that the exhaust gas can not escape the blades of the turbine wheel, the flow channel in the region of the rotor blades is delimited by a cover ring radially enclosing the rotor blades. This housing part can, as in FIG. 1, be formed as an integral part of the diffuser 31 arranged downstream of the rotor blades. Alternatively, the cover ring may be formed as an integral part of the radially outer housing wall 22 of the nozzle ring or as an independent component.

Fig. 2 zeigt einen Schnitt durch die Achse einer Axialturbine eines Abgasturboladers mit einem erfindungsgemäss ausgebildeten Abdeckring 5, welcher den Strömungskanal im Bereich radial ausserhalb der Laufschaufeln 12 des Turbinenrades begrenzt. Der Abdeckring ist in Fig. 3 nochmals vergrössert dargestellt.2 shows a section through the axis of an axial turbine of an exhaust-gas turbocharger with a cover ring 5 designed according to the invention, which delimits the flow channel in the area radially outside the rotor blades 12 of the turbine wheel. The cover ring is shown enlarged in Fig. 3 again.

Fig. 4 und 5 zeigen isometrische Darstellungen zweier Ausführungsformen des erfindungsgemäss ausgebildeten Abdeckrings.4 and 5 show isometric views of two embodiments of the present invention formed cover ring.

Der Abdeckring umfasst erfindungsgemäss mehrere, entlang dem Umfang durch Schlitze 57 voneinander getrennte Segmente 51 sowie zumindest einen umlaufenden Ring 54 bzw. 55. Die Segmente sind unmittelbar radial ausserhalb der Laufschaufeln angeordnet. In diesem Bereich verliert der Abdeckring somit seinen tangentialen Zusammenhang. Beim Reinigen der Abgasturbinen zieht sich der Abdeckring dadurch auch bei einer schlagartigen Abkühlung in radialer Richtung nicht zusammen. Lediglich die Schlitze 57 zwischen den einzelnen Segmenten werden grösser. Dadurch kann ein Streifen der Turbine verhindert werden. Auch bezüglich der unterschiedlichen Abkühlung entlang dem Umfang des Abdeckrings ergeben sich Vorteile: Segmente, die sich nicht stark abkühlen, schrumpfen weniger stark, solche, die stark abkühlen, schrumpfen stärker in Umfangsrichtung.According to the invention, the cover ring comprises a plurality of segments 51 which are separated from one another by slits 57 along the circumference and at least one circumferential one Ring 54 and 55, respectively. The segments are arranged directly radially outside the rotor blades. In this area, the cover ring thus loses its tangential relationship. When cleaning the exhaust gas turbine, the cover ring therefore does not contract even in the case of a sudden cooling in the radial direction. Only the slots 57 between the individual segments are larger. As a result, a strip of the turbine can be prevented. There are also advantages with regard to the different cooling along the circumference of the cover ring: Segments which do not cool off greatly shrink less, and those which cool strongly shrink more strongly in the circumferential direction.

Damit die einzelnen Segmente trotz der Schlitze einen Zusammenhang haben sind die Segmente 51 über Rippen 52 bzw. 53 mit den umlaufenden Ringen 54 bzw. 55 verbunden. Der Abdeckring 5 wird vorteilhafterweise an dem Diffusor 31 oder dem Gasaustrittsgehäuse 41 festgemacht, oder wie in der Fig. 2 angedeutet, zwischen den beiden Teilen festgeklemmt. Zusätzlich kann der Abdeckring mittels in dafür vorgesehenen Bohrungen 56 angeordneten Befestigungsmitteln 6 festgeschraubt werden.In order for the individual segments to have a connection despite the slots, the segments 51 are connected via ribs 52 and 53, respectively, to the encircling rings 54 and 55, respectively. The cover ring 5 is advantageously fastened to the diffuser 31 or the gas outlet housing 41, or, as indicated in FIG. 2, clamped between the two parts. In addition, the cover ring can be screwed tightly by means of fastening holes 6 arranged in the holes 56.

Die umlaufenden Ringe sind vorteilhafterweise durch mindestens ein Gehäuseteil vom Strömungskanal im Bereich der Laufschaufeln getrennt, so dass beim Reinigungsvorgang kein kaltes Wasser an die Ringe gelangen kann. Somit erfahren die Ringe keine Abkühlung bei der Reinigung der Abgasturbine und ziehen sich damit auch nicht thermisch bedingt zusammen.The peripheral rings are advantageously separated by at least one housing part of the flow channel in the region of the blades, so that no cold water can reach the rings during the cleaning process. Thus, the rings undergo no cooling during the cleaning of the exhaust gas turbine and thus do not contract thermally.

Fig. 4 zeigt eine erste Ausführungsform des erfindungsgemässen Abdeckrings 5 mit einem austrittsseitig angeordneten Ring 55, an welchem jeweils über Rippen 53 die Segmente 51 befestigt sind.FIG. 4 shows a first embodiment of the cover ring 5 according to the invention with a ring 55 arranged on the outlet side, on which the segments 51 are fastened in each case via ribs 53.

Fig. 5 zeigt eine zweite Ausführungsform des erfindungsgemässen Abdeckrings 5 mit einem eintrittsseitig angeordneten Ring 54 und einem austrittsseitigen Ring 55, an welchen jeweils über Rippen 52 bzw. 53 die Segmente 51 befestigt sind. Die Ringe 54 und 55 sind bezüglich der radial inneren Oberfläche der Segmente in radialer Richtung zurückversetzt, damit sie im eingebauten Zustand nicht direkt in Berührung mit der Strömung bzw. der Reinigungsflüssigkeit kommen.FIG. 5 shows a second embodiment of the cover ring 5 according to the invention with a ring 54 arranged on the inlet side and an outlet-side ring 55 on which the segments 51 are respectively fastened via ribs 52 and 53. The rings 54 and 55 are set back with respect to the radially inner surface of the segments in the radial direction, so that they do not come in the installed state directly in contact with the flow or the cleaning liquid.

Die Rippen 52 bzw. 53 werden möglichst dünn ausgeführt um die Wärmeleitung bzw. den Temperaturausgleich zwischen den Segmenten 51 und den Ringen 54 resp. 55 beim Waschen möglichst gering zu halten.The ribs 52 and 53 are made as thin as possible to the heat conduction or temperature compensation between the segments 51 and the rings 54, respectively. 55 to minimize the washing.

Um den Wirkungsgrad der Abgasturbine im normalen Betrieb durch den segmentierten Abdeckring nicht zu beeinträchtigen, sind die Schlitze 57 zwischen den einzelnen Segmenten 51 so dünn wie möglich auszubilden. Da die Temperatur der Segmente im Betrieb gegenüber der Temperatur bei der Herstellung in der Regel höher sein dürfte, schliessen sich die bei der Herstellung entstehenden Schlitze im Betrieb aufgrund der Ausdehnung der Segmente entlang dem Umfang. Die Schlitzbreite sollte, zumindest im Betrieb der Abgasturbine, im mikroskopischen Bereich von einigen wenigen Mikrometern liegen.In order not to affect the efficiency of the exhaust gas turbine in normal operation by the segmented cover ring, the slots 57 between the individual segments 51 are formed as thin as possible. Since the temperature of the segments in operation is likely to be higher than the temperature during manufacture, the slots formed during manufacture close during operation due to the expansion of the segments along the circumference. The slot width should, at least during operation of the exhaust gas turbine, be in the microscopic range of a few micrometers.

Die erfindungsgemässe Abgasturbine kann anstatt zum Antreiben eines Verdichters auch als Nutzturbine eingesetzt werden, etwa um einen Elektro-Generator oder eine mechanische Maschine anzutreiben.The inventive exhaust gas turbine can be used instead of driving a compressor as a power turbine, about to drive an electric generator or a mechanical machine.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

1010
Turbinenradturbine
1111
Turbinenradnabeturbine hub
1212
Laufschaufeln des TurbinenradesBlades of the turbine wheel
2020
Düsenringnozzle ring
2121
Innenwand des DüsenringsInner wall of the nozzle ring
2222
Aussenwand des DüsenringsOuter wall of the nozzle ring
2323
Leitschaufeln des DüsenringsGuide vanes of the nozzle ring
3131
Diffusordiffuser
4141
GasaustrittsgehäuseGas outlet casing
4242
GaseintrittsgehäuseGas inlet casing
55
AbdeckringFlange
5151
Segmente des AbdeckringsSegments of the cover ring
5252
Eintrittsseitige RippeEntrance side rib
5353
Austrittsseitige RippeOutlet rib
5454
Eintrittsseitiger, umlaufender RingEntry-side, circumferential ring
5555
Austrittsseitiger, umlaufender RingOutlet-side, circumferential ring
5656
Bohrungdrilling
5757
Schlitzslot
66
Befestigungsmittel, SchraubeFastener, screw

Claims (5)

Axialturbine, umfassend ein Turbinenrad (11) mit Laufschaufeln (12) und einem die Laufschaufeln radial umgebenden Abdeckring (5), wobei der Abdeckring (5) in mehrere, durch Schlitze (57) entlang dem Umfang voneinander getrennte Segmente (51) unterteilt ist, dadurch gekennzeichnet, dass jedes Segment (51) über eine Rippe (52, 53) mit einem umlaufenden Ring (54, 55) verbunden ist.Axial turbine comprising a turbine wheel (11) with blades (12) and a cover ring (5) radially surrounding the blades, the cover ring (5) being divided into a plurality of segments (51) separated by slots (57) along the circumference, characterized in that each segment (51) is connected by a rib (52, 53) to a circumferential ring (54, 55). Axialturbine gemäss Anspruch 1, dadurch gekennzeichnet, dass jedes Segment (51) über je zwei Rippen (52, 53) mit zwei umlaufenden Ringen (54, 55) verbunden ist.Axial turbine according to claim 1, characterized in that each segment (51) via two respective ribs (52, 53) with two circumferential rings (54, 55) is connected. Axialturbine gemäss einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass der umlaufende Ring (54, 55) durch ein Bauteil (22, 31), welches den Kanal der Strömung auf die Laufschaufeln (12) des Turbinenrades begrenzt, vom Innern dieses Strömungskanals abgeschirmt ist.Axial turbine according to one of claims 1 or 2, characterized in that the peripheral ring (54, 55) by a component (22, 31) which limits the channel of the flow on the blades (12) of the turbine wheel, shielded from the interior of this flow channel is. Axialturbine gemäss einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Schlitze (57) eine Schlitzdicke im mikroskopischen Bereich von einigen wenigen Mikrometern aufweisen.Axial turbine according to one of claims 1 to 3, characterized in that the slots (57) have a slot thickness in the microscopic range of a few micrometers. Abgasturbolader, gekennzeichnet durch eine Axialturbine gemäss einem der vorangehenden Ansprüche.Exhaust gas turbocharger, characterized by an axial turbine according to one of the preceding claims.
EP06405335A 2006-08-07 2006-08-07 Axial flow turbine with slotted shroud Withdrawn EP1890011A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06405335A EP1890011A1 (en) 2006-08-07 2006-08-07 Axial flow turbine with slotted shroud
PCT/EP2007/058202 WO2008017681A1 (en) 2006-08-07 2007-08-07 Axial turbine with slotted cover ring

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06405335A EP1890011A1 (en) 2006-08-07 2006-08-07 Axial flow turbine with slotted shroud

Publications (1)

Publication Number Publication Date
EP1890011A1 true EP1890011A1 (en) 2008-02-20

Family

ID=37622331

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06405335A Withdrawn EP1890011A1 (en) 2006-08-07 2006-08-07 Axial flow turbine with slotted shroud

Country Status (2)

Country Link
EP (1) EP1890011A1 (en)
WO (1) WO2008017681A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045167A1 (en) 2009-09-30 2011-04-07 Man Diesel & Turbo Se Turbine i.e. axial turbine, for use in exhaust-gas turbocharger to turbocharge large diesel engine, has diffuser divided into two segments in circumferential direction, where side of each segment is extended in radial direction

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB869908A (en) * 1958-03-25 1961-06-07 Zd Y V I Plzen A packing device for the rotor blades of turbines
US3286459A (en) * 1963-12-31 1966-11-22 Gen Motors Corp Turbine inlet screen assembly
US3730640A (en) * 1971-06-28 1973-05-01 United Aircraft Corp Seal ring for gas turbine
DE2820189A1 (en) * 1978-05-09 1979-11-22 Teves Gmbh Alfred Thermally compensated brake drum - has inwardly inclined brake surface which deflects to bend outwardly on warming
GB2076067A (en) * 1980-05-16 1981-11-25 Mtu Muenchen Gmbh Axial-flow compressor or turbine outer casing
JPH05288080A (en) * 1992-04-10 1993-11-02 Yanmar Diesel Engine Co Ltd Gas turbine engine
US5593276A (en) * 1995-06-06 1997-01-14 General Electric Company Turbine shroud hanger
EP1475515A2 (en) * 2003-05-06 2004-11-10 General Electric Company Apparatus for controlling rotor blade tip clearances in a gas turbine engine
EP1580404A2 (en) * 2004-03-26 2005-09-28 Rolls-Royce Deutschland Ltd & Co KG Arrangement for self adjusting the tip clearance in a two or multiple stage turbine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6896483B2 (en) * 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
US6877952B2 (en) * 2002-09-09 2005-04-12 Florida Turbine Technologies, Inc Passive clearance control

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB869908A (en) * 1958-03-25 1961-06-07 Zd Y V I Plzen A packing device for the rotor blades of turbines
US3286459A (en) * 1963-12-31 1966-11-22 Gen Motors Corp Turbine inlet screen assembly
US3730640A (en) * 1971-06-28 1973-05-01 United Aircraft Corp Seal ring for gas turbine
DE2820189A1 (en) * 1978-05-09 1979-11-22 Teves Gmbh Alfred Thermally compensated brake drum - has inwardly inclined brake surface which deflects to bend outwardly on warming
GB2076067A (en) * 1980-05-16 1981-11-25 Mtu Muenchen Gmbh Axial-flow compressor or turbine outer casing
JPH05288080A (en) * 1992-04-10 1993-11-02 Yanmar Diesel Engine Co Ltd Gas turbine engine
US5593276A (en) * 1995-06-06 1997-01-14 General Electric Company Turbine shroud hanger
EP1475515A2 (en) * 2003-05-06 2004-11-10 General Electric Company Apparatus for controlling rotor blade tip clearances in a gas turbine engine
EP1580404A2 (en) * 2004-03-26 2005-09-28 Rolls-Royce Deutschland Ltd & Co KG Arrangement for self adjusting the tip clearance in a two or multiple stage turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045167A1 (en) 2009-09-30 2011-04-07 Man Diesel & Turbo Se Turbine i.e. axial turbine, for use in exhaust-gas turbocharger to turbocharge large diesel engine, has diffuser divided into two segments in circumferential direction, where side of each segment is extended in radial direction

Also Published As

Publication number Publication date
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