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WO2008142044A2 - Turbine housing - Google Patents

Turbine housing Download PDF

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Publication number
WO2008142044A2
WO2008142044A2 PCT/EP2008/056106 EP2008056106W WO2008142044A2 WO 2008142044 A2 WO2008142044 A2 WO 2008142044A2 EP 2008056106 W EP2008056106 W EP 2008056106W WO 2008142044 A2 WO2008142044 A2 WO 2008142044A2
Authority
WO
WIPO (PCT)
Prior art keywords
housing
turbine
gas outlet
gas
opening
Prior art date
Application number
PCT/EP2008/056106
Other languages
German (de)
French (fr)
Other versions
WO2008142044A3 (en
Inventor
Balz Flury
Peter Schellenberger
Daniel Oeschger
Bent Phillipsen
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
Publication of WO2008142044A2 publication Critical patent/WO2008142044A2/en
Publication of WO2008142044A3 publication Critical patent/WO2008142044A3/en

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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
    • 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
    • F01D25/04—Antivibration arrangements
    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to the field of exhaust gas turbines, as used in exhaust gas turbochargers, to increase the performance of internal combustion engines (reciprocating engines), or in power turbines, for converting the energy contained in the exhaust gases of internal combustion engines into mechanical or electrical energy. It relates to the housing of such an exhaust gas turbine.
  • thermodynamically optimized flow channel shapes In order to prevent damage to the rotating components, the clearance between the rotating components and the stationary housing parts must be increased due to the different sizes, whereby the efficiency gained by the thermodynamically optimized flow channel shapes is at least partially lost again.
  • the object of the invention is to make the gas outlet housing of an exhaust gas turbine resistant to asymmetrical expansion. According to the invention this is achieved with at least one support element, which is arranged in the interior of the gas outlet housing.
  • a partition wall or a rib may be provided, which leads transversely through the flow channel.
  • the gas outlet housing is just as stable as if it had a symmetrical shape.
  • the support member may be provided as an axial connection between the bearing housing side flange and the gaseinthtts substantiveen flange. This leads to a further stiffening of the entire turbine housing.
  • the support element is designed as a partition wall, which has a larger radial extent with respect to a narrow rib, or if a plurality of ribs arranged radially one above the other are used, not only axial forces but also a very high moment can be absorbed.
  • the thus achieved, stronger stabilization means that the tilting of the gas outlet flange can be avoided.
  • the support of the turbine housing according to the invention the asymmetrical housing deformations are so greatly reduced that the efficiency achieved by the thermodynamically optimized flow channel shapes can be fully utilized.
  • the support element causes the natural frequency of the exhaust gas turbine, or the exhaust gas turbocharger or the power turbine increases. This in turn contributes to a much less problematic operating behavior.
  • FIG. 1 shows an isometric view of a partially cutaway turbine housing with a support according to the invention through a dividing wall, seen from the side of the bearing housing flange,
  • FIG. 2 is an isometric view of the axially cut turbine housing of FIG. 1, with the section taken through the bulkhead seen from the side of the bearing housing flange.
  • FIG. Fig. 3 is an isometric view of the axially cut turbine housing of Figure 1, wherein the section is guided through the partition wall, seen from the side of the Gaseintrittflansches, and
  • Fig. 4 is an isometric view of a partially cut turbine housing with a support according to the invention by a
  • Fig. 5 is an isometric view of an axially cut turbine housing of the prior art, with inserted diffuser ..
  • FIG. 5 shows a turbine casing 10, cut along the turbine axis, of an exhaust gas turbocharger or a useful turbine according to the prior art.
  • the flow direction of the hot, brought up by the engine exhaust gas is indicated by the thick, white arrows.
  • the gas thus enters through the gas inlet opening 23 in the gas inlet flange 13 into the interior of the turbine housing, is guided in the flow channel via the blades of the turbine wheel, not shown, collected radially in the asymmetrically designed collecting chamber 14 outside the diffuser and leaves the turbine housing then via the gas outlet opening 21 in the gas outlet flange 11.
  • the turbine wheel, not shown, is arranged on a shaft, which is guided through the shaft opening 22 in the bearing housing flange 12 and rotatably mounted in the bearing housing.
  • the compressor in the exhaust gas turbocharger arranged at the power turbine, the connecting element to the utility machine.
  • the diffuser is not shown in the outflow region radially outside the turbine blades.
  • the diffuser is mounted on the back of the gas inlet flange 13 during assembly of the exhaust gas turbine.
  • the holes used for this purpose are shown in the figures.
  • the flow guide on the side of the bearing housing flange 12. This backdrop is either also part of the turbine housing, or else the Bearing housing or it is attached as a separate component during assembly between the bearing housing and the bearing housing flange 12 of the turbine housing.
  • FIG. 1 shows an isometric view of the partially cutaway turbine housing 10 with a support according to the invention through a dividing wall 15, seen from the side of the bearing housing flange 12.
  • the hot exhaust gas is fed from behind through the gas inlet opening 13 in the gas inlet flange 13 into the turbine housing.
  • the supporting partition wall 15 extends in the radially outer region of the turbine housing, the gas outlet region in the axial direction of the Lagergepuruseflansch 12 across the flow channel towards the side of the gas inlet flange 13.
  • the supporting partition wall 15 has a stabilizing effect on the turbine housing when unequal expansion occurs due to the asymmetrical shape during heavy heating.
  • FIGS. 2 and 3 show isometric views of the turbine housing 10, wherein the turbine housing is cut open by the partition wall 15. It can be clearly seen in these illustrations that the partition wall 15 connects the bearing housing side with the gas inlet side, and thus acts as a stabilizer for the turbine housing in the gas outlet region.
  • FIG. 4 shows an isometric view of a turbine housing supported according to the invention in a second embodiment.
  • the gas outlet region is supported by a rib 16.
  • the rib extends transversely through the flow channel and also connects the bearing housing side with the gas inlet side of the turbine housing.
  • two or more ribs may be radially superposed to provide additional support.
  • a high torque can be absorbed thereby, whereby it can be prevented that the gas outlet flange can tip over.

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

Abstract

The support element is embodied as a separating wall (15), running transversely through the asymmetric flow channel. The turbine housing (10) is thus just as stable as it would be with a symmetrical shape.

Description

Turbinengehäuse turbine housing
B E S C H R E I B U N GDESCRIPTION
Technisches GebietTechnical area
Die Erfindung bezieht sich auf das Gebiet der Abgasturbinen, wie sie in Abgasturboladern, zur Leistungssteigerung von Brennkraftmaschinen (Hubkolbenmotoren), oder in Nutzturbinen, zum Umwandeln der in den Abgasen von Brennkraftmaschinen enthaltenen Energie in mechanische oder elektrische Energie, eingesetzt werden. Sie betrifft das Gehäuse einer solchen Abgasturbine.The invention relates to the field of exhaust gas turbines, as used in exhaust gas turbochargers, to increase the performance of internal combustion engines (reciprocating engines), or in power turbines, for converting the energy contained in the exhaust gases of internal combustion engines into mechanical or electrical energy. It relates to the housing of such an exhaust gas turbine.
Stand der Technik Bei modernen Brennkraftmaschinen wird es für Hersteller von Abgasturboladern immer schwieriger die für eine effiziente Nutzung der Brennkraftmaschine geforderten Wirkungsgrade des Abgasturboladers bereitzustellen. Eine Möglichkeit den Wirkungsgrad des Abgasturboladers zu verbessern, besteht darin, neue, thermodynamisch optimierte Strömungskanalformen auszulegen. Im Gasaustrittsgehäuse einer Abgasturbine können bei betriebsbedingter Erwärmung aufgrund der thermodynamisch optimierten, asymmetrischen Form der Strömungskanalführung asymmetrische Ausdehnungen des Gehäuses entstehen.PRIOR ART In modern internal combustion engines, it is increasingly difficult for manufacturers of exhaust gas turbochargers to provide the efficiencies of the exhaust gas turbocharger required for efficient use of the internal combustion engine. One way to improve the efficiency of the exhaust gas turbocharger is to design new, thermodynamically optimized flow channel shapes. In the gas outlet housing of an exhaust gas turbine asymmetric dimensions of the housing may arise during operational heating due to the thermodynamically optimized, asymmetric shape of the flow channel guide.
Um Schäden an den rotierenden Bauteilen zu verhindern, muss aufgrund der unterschiedlich grossen Ausdehnungen das Spiel zwischen den rotierenden Bauteilen und den feststehenden Gehäuseteilen erhöht werden, wodurch der durch die thermodynamisch optimierte Strömungskanalformen gewonnene Wirkungsgrad zumindest teilweise wieder verloren geht.In order to prevent damage to the rotating components, the clearance between the rotating components and the stationary housing parts must be increased due to the different sizes, whereby the efficiency gained by the thermodynamically optimized flow channel shapes is at least partially lost again.
Kurze Darstellung der ErfindungBrief description of the invention
Die Aufgabe der Erfindung liegt darin, das Gasaustrittsgehäuse einer Abgasturbine gegen unsymmetrische Ausdehnung resistent zu machen. Erfindungsgemäss wird dies mit mindestens einem Stützelement erreicht, welches im Innern des Gasaustrittsgehäuses angeordnet ist.The object of the invention is to make the gas outlet housing of an exhaust gas turbine resistant to asymmetrical expansion. According to the invention this is achieved with at least one support element, which is arranged in the interior of the gas outlet housing.
Als Stützelement kann eine Trennwand oder eine Rippe vorgesehen sein, welche quer durch den Strömungskanal führt. Damit wird das Gasaustrittsgehäuse genauso stabil, wie wenn es eine symmetrische Form aufweisen würde.As a support member, a partition wall or a rib may be provided, which leads transversely through the flow channel. Thus, the gas outlet housing is just as stable as if it had a symmetrical shape.
Optional kann das Stützelement als axiale Verbindung zwischen dem lagergehäuseseitigen Flansch und dem gaseinthttsseitigen Flansch vorgesehen sein. Dies führt zu einer weiteren Versteifung des gesamten Turbinengehäuses.Optionally, the support member may be provided as an axial connection between the bearing housing side flange and the gaseinthttsseitigen flange. This leads to a further stiffening of the entire turbine housing.
Wird das Stützelement als eine Trennwand ausgebildet, welche gegenüber einer schmalen Rippe eine grossere radialer Ausdehnung aufweist, oder werden mehrere, radial übereinander angeordnete Rippen eingesetzt, können nicht nur axiale Kräfte sondern auch ein sehr hohes Moment aufgenommen werden. Die so erzielte, stärkere Stabilisierung führt dazu, dass das Abkippen des Gasaustrittsflansches vermieden werden kann. Die asymmetrischen Gehäusedeformationen werden dank der erfindungsgemässen Abstützung des Turbinengehäuses so stark vermindert, dass der durch die thermodynamisch optimierten Strömungskanalformen gewonnene Wirkungsgrad vollumfänglich genutzt werden kann.If the support element is designed as a partition wall, which has a larger radial extent with respect to a narrow rib, or if a plurality of ribs arranged radially one above the other are used, not only axial forces but also a very high moment can be absorbed. The thus achieved, stronger stabilization means that the tilting of the gas outlet flange can be avoided. Thanks to the support of the turbine housing according to the invention, the asymmetrical housing deformations are so greatly reduced that the efficiency achieved by the thermodynamically optimized flow channel shapes can be fully utilized.
Zusätzlich führt das Stützelement dazu, dass sich die Eigenfrequenz der Abgasturbine, bzw. des Abgasturboladers oder der Nutzturbine erhöht. Dies wiederum trägt zu einem wesentlich unproblematischeren Betriebsverhalten bei.In addition, the support element causes the natural frequency of the exhaust gas turbine, or the exhaust gas turbocharger or the power turbine increases. This in turn contributes to a much less problematic operating behavior.
Kurze Beschreibung der ZeichnungenBrief description of the drawings
Nachfolgend sind anhand der Zeichnungen Ausführungsformen des erfindungsgemässen Turbinengehäuses beschrieben. Hierbei zeigt Fig. 1 eine isometrische Ansicht eines teilweise aufgeschnittenen Turbinengehäuses mit einer erfindungsgemässen Abstützung durch eine Trennwand, von der Seite des Lagergehäuseflansches her gesehen,Embodiments of the turbine housing according to the invention will now be described with reference to the drawings. 1 shows an isometric view of a partially cutaway turbine housing with a support according to the invention through a dividing wall, seen from the side of the bearing housing flange,
Fig. 2 eine isometrische Ansicht des axial geschnittenen Turbinengehäuses nach Fig. 1 , wobei der Schnitt durch die Trennwand geführt ist, von der Seite des Lagergehäuseflansches her gesehen, Fig. 3 eine isometrische Ansicht des axial geschnittenen Turbinengehäuses nach Fig. 1 , wobei der Schnitt durch die Trennwand geführt ist, von der Seite des Gaseintrittflansches her gesehen, undFIG. 2 is an isometric view of the axially cut turbine housing of FIG. 1, with the section taken through the bulkhead seen from the side of the bearing housing flange. FIG. Fig. 3 is an isometric view of the axially cut turbine housing of Figure 1, wherein the section is guided through the partition wall, seen from the side of the Gaseintrittflansches, and
Fig. 4 eine isometrische Ansicht eines teilweise aufgeschnittenen Turbinengehäuses mit einer erfindungsgemässen Abstützung durch eineFig. 4 is an isometric view of a partially cut turbine housing with a support according to the invention by a
Rippe, von der Seite des Lagergehäuseflansches her gesehen, undRib, seen from the side of the bearing housing flange, and
Fig. 5 eine isometrische Ansicht eines axial geschnittenen Turbinengehäuses nach dem Stand der Technik, mit eingesetztem Diffusor..Fig. 5 is an isometric view of an axially cut turbine housing of the prior art, with inserted diffuser ..
Weg zur Ausführung der Erfindung Fig. 5 zeigt ein entlang der Turbinenachse aufgeschnittenes Turbinengehäuse 10 eines Abgasturboladers bzw. einer Nutzturbine nach dem Stand der Technik. Die Strömungsrichtung des heissen, von der Brennkraftmaschine herangeführten Abgases ist mit den dicken, weissen Pfeilen angedeutet. Das Gas tritt demnach durch die Gaseintrittsöffnung 23 im Gaseintrittsflansch 13 in das Innere des Turbinengehäuses, wird im Strömungskanal über die nicht dargestellten Laufschaufeln des Turbinenrades geführt, im asymmetrisch ausgebildeten Sammelraum 14 radial ausserhalb des Diffusors aufgefangen und verlässt das Turbinengehäuse anschliessend über die Gasaustrittsöffnung 21 im Gasaustrittsflansch 11. Das nicht dargestellte Turbinenrad ist auf einer Welle angeordnet, welche durch die Wellenöffnung 22 im Lagergehäuseflansch 12 geführt und im Lagergehäuse drehbar gelagert ist. Am gegenüberliegenden Ende der Welle ist beim Abgasturbolader das Verdichterrad, bei der Nutzturbine das Verbindungselement zur Nutzmaschine angeordnet.FIG. 5 shows a turbine casing 10, cut along the turbine axis, of an exhaust gas turbocharger or a useful turbine according to the prior art. The flow direction of the hot, brought up by the engine exhaust gas is indicated by the thick, white arrows. The gas thus enters through the gas inlet opening 23 in the gas inlet flange 13 into the interior of the turbine housing, is guided in the flow channel via the blades of the turbine wheel, not shown, collected radially in the asymmetrically designed collecting chamber 14 outside the diffuser and leaves the turbine housing then via the gas outlet opening 21 in the gas outlet flange 11. The turbine wheel, not shown, is arranged on a shaft, which is guided through the shaft opening 22 in the bearing housing flange 12 and rotatably mounted in the bearing housing. At the opposite end of the shaft is the compressor in the exhaust gas turbocharger, arranged at the power turbine, the connecting element to the utility machine.
In den Figuren 1 bis 4, welche das erfindungsgemässe Turbinengehäuse in verschiedenen Schnitten und aus verschiedenen Richtungen sowie in zwei unterschiedlichen Ausführungsformen zeigen, ist der Diffusor im Abströmbereich radial ausserhalb der Turbinenschaufeln nicht dargestellt. Der Diffusor wird bei der Montage der Abgasturbine auf der Rückseite des Gaseintrittsflansches 13 befestigt. Die dafür verwendeten Bohrungen sind in den Figuren dargestellt. Ebenfalls nicht dargestellt ist die strömungsführende Kulisse auf der Seite des Lagergehäuseflansches 12. Diese Kulisse ist entweder ebenfalls Teil des Turbinengehäuses, oder aber des Lagergehäuses oder sie wird als separates Bauteil bei der Montage zwischen dem Lagergehäuse und dem Lagergehäuseflansch 12 des Turbinengehäuses befestigt.In the figures 1 to 4, which show the turbine housing according to the invention in different sections and from different directions as well as in two different embodiments, the diffuser is not shown in the outflow region radially outside the turbine blades. The diffuser is mounted on the back of the gas inlet flange 13 during assembly of the exhaust gas turbine. The holes used for this purpose are shown in the figures. Also not shown is the flow guide on the side of the bearing housing flange 12. This backdrop is either also part of the turbine housing, or else the Bearing housing or it is attached as a separate component during assembly between the bearing housing and the bearing housing flange 12 of the turbine housing.
Fig. 1 zeigt eine isometrische Ansicht des teilweise aufgeschnittenen Turbinengehäuses 10 mit einer erfindungsgemässen Abstützung durch eine Trennwand 15, von der Seite des Lagergehäuseflansches 12 her gesehen. Das heisse Abgas wird von hinten durch die Gaseintrittsöffnung 13 im Gaseintrittsflansch 13 ins Turbinengehäuse hineingeführt. Die stützende Trennwand 15 erstreckt sich im radial äusseren Bereich des Turbinengehäuses, dem Gasaustrittsbereich in axialer Richtung von dem Lagergehäuseflansch 12 quer durch den Strömungskanal hin zur Seite des Gaseintrittsflansches 13. Das im Bereich des Sammelraumes 14, welcher sich im montierten Zustand der Abgasturbine, radial ausserhalb des Diffusors erstreckt, ist das Turbinengehäuse wie eingangs ausgeführt asymmetrisch ausgebildet, um durch verbesserte thermodynamische Verhältnisse eine Wirkungsgradsteigerung zu bewirken. Die stützende Trennwand 15 wirkt stabilisierend für das Turbinengehäuse, wenn es bei starker Erwärmung aufgrund der asymmetrischen Form zu ungleichen Ausdehnungen kommt.1 shows an isometric view of the partially cutaway turbine housing 10 with a support according to the invention through a dividing wall 15, seen from the side of the bearing housing flange 12. The hot exhaust gas is fed from behind through the gas inlet opening 13 in the gas inlet flange 13 into the turbine housing. The supporting partition wall 15 extends in the radially outer region of the turbine housing, the gas outlet region in the axial direction of the Lagergehäuseflansch 12 across the flow channel towards the side of the gas inlet flange 13. In the region of the collecting chamber 14, which in the assembled state of the exhaust gas turbine, radially outside extends the turbine housing as described above asymmetrically to effect an increase in efficiency by improved thermodynamic conditions. The supporting partition wall 15 has a stabilizing effect on the turbine housing when unequal expansion occurs due to the asymmetrical shape during heavy heating.
Fig. 2 und Fig. 3 zeigen isometrische Ansichten des Turbinengehäuses 10, wobei das Turbinengehäuse jeweils durch die Trennwand 15 aufgeschnitten ist. Es ist in diesen Darstellungen deutlich zu sehen, dass die Trennwand 15 die Lagergehäuseseite mit der Gaseintrittsseite verbindet, und so für das Turbinengehäuse im Gasaustrittsbereich stabilisierend wirkt.FIGS. 2 and 3 show isometric views of the turbine housing 10, wherein the turbine housing is cut open by the partition wall 15. It can be clearly seen in these illustrations that the partition wall 15 connects the bearing housing side with the gas inlet side, and thus acts as a stabilizer for the turbine housing in the gas outlet region.
Fig. 4 zeigt eine isometrische Ansicht eines erfindungsgemäss gestützten Turbinengehäuses in einer zweiten Ausführungsform. Anstelle einer sich radial bis an die äussere Grenze des Gasaustrittsflansches erstreckenden Trennwand, ist der Gasaustrittsbereich mit einer Rippe 16 abgestützt. Die Rippe erstreckt sich quer durch den Strömungskanal und verbindet ebenfalls die Lagergehäuseseite mit der Gaseintrittsseite des Turbinengehäuses. Optional können zwei oder mehr Rippen radial übereinander angeordnet sein, um eine zusätzliche Abstützung zu erreichen. Insbesondere kann dadurch ein hohes Moment aufgenommen werden, wodurch verhindert werden kann, dass der Gasaustrittsflansch abkippen kann. Bezugszeichenliste Turbinengehäuse Gasaustrittsflansch Lagergehäuseflansch Gaseintrittsflansch Sammelraum Stützelement (Trennwand) Stützelement (Rippe) Gasaustrittsöffnung Wellenöffnung Gaseintrittsöffnung 4 shows an isometric view of a turbine housing supported according to the invention in a second embodiment. Instead of a radially extending to the outer boundary of the gas outlet flange dividing wall, the gas outlet region is supported by a rib 16. The rib extends transversely through the flow channel and also connects the bearing housing side with the gas inlet side of the turbine housing. Optionally, two or more ribs may be radially superposed to provide additional support. In particular, a high torque can be absorbed thereby, whereby it can be prevented that the gas outlet flange can tip over. Turbine housing Gas outlet flange Bearing flange Gas inlet flange Collecting chamber Support element (partition wall) Support element (rib) Gas outlet opening Shaft opening Gas inlet opening

Claims

PAT E N TA N S P R Ü C H E PAT EN TA NSPR O CHE
1. Gasaustrittsgehäuse einer Abgasturbine, mit einer ersten Wellenöffnung (22) zum Durchführen einer Welle der Abgasturbine, mit einer Gaseintrittsöffnung (23) zum Zuführen von Abgasen in das Gasaustrittsgehäuse, wobei die Wellenöffnung (22) und Gaseintrittsöffnung (23) koaxial zueinander angeordnet sind, und mit einerA gas outlet housing of an exhaust gas turbine, having a first shaft opening (22) for passing a shaft of the exhaust gas turbine, with a gas inlet opening (23) for supplying exhaust gases into the gas outlet housing, wherein the shaft opening (22) and gas inlet opening (23) are arranged coaxially to one another, and with one
Gasaustrittsöffnung (21 ) zum Abführen der Abgase aus dem Gasaustrittsgehäuse, wobei die Gasaustrittsöffnung (21 ) senkrecht zu der Wellenöffnung (22) und der Gaseintrittsöffnung (23) angeordnet ist und sich zwischen der Gaseintrittsöffnung (23) und der Gasaustrittsöffnung (21 ) ein Strömungskanal erstreckt, wobei der Strömungskanal zwischen der Gaseintrittsöffnung (23) und der GasaustrittsöffnungGas outlet opening (21) for discharging the exhaust gases from the gas outlet housing, wherein the gas outlet opening (21) perpendicular to the shaft opening (22) and the gas inlet opening (23) and between the gas inlet opening (23) and the gas outlet opening (21) extends a flow channel , wherein the flow channel between the gas inlet opening (23) and the gas outlet opening
(21 ) asymmetrisch ausgebildet ist, dadurch gekennzeichnet, dass im Strömungskanal ein in axialer Richtung verlaufendes Stützelement (15, 16) zur Stabilisierung des Gasaustrittsgehäuses angeordnet ist.(21) is formed asymmetrically, characterized in that in the flow channel extending in the axial direction of a support member (15, 16) is arranged for stabilizing the gas outlet housing.
2. Gasaustrittsgehäuse nach Anspruch 1 , wobei das Stützelement als eine Trennwand (15) oder eine Rippe (16) durch den Strömungskanal ausgebildet ist.2. Gas outlet housing according to claim 1, wherein the support element is formed as a partition wall (15) or a rib (16) through the flow channel.
3. Turbinengehäuse, umfassend ein Gasaustrittsgehäuse nach einem der Ansprüche 1 oder 2.3. Turbine housing, comprising a gas outlet housing according to one of claims 1 or 2.
4. Turbinengehäuse nach Anspruch 3, wobei das Turbinengehäuse einen die Wellenöffnung (22) umschliessenden Lagergehäuseflansch (12) und einen die Gaseintrittsöffnung (23) umschliessenden Gaseintrittsflansch (13) umfasst und das4. turbine housing according to claim 3, wherein the turbine housing comprises a shaft housing (22) enclosing Lagergehäuseflansch (12) and a gas inlet opening (23) enclosing Gaseintrittsflansch (13) and the
Stützelement (15, 16) den Gaseintrittsflansch (13) in axialer Richtung mit dem Lagergehäuseflansch (12) verbindet.Support member (15, 16) connects the gas inlet flange (13) in the axial direction with the bearing housing flange (12).
5. Abgasturbolader oder Nutzturbine, umfassend ein Turbinengehäuse nach einem der Ansprüche 3 oder 4. 5. Exhaust gas turbocharger or power turbine, comprising a turbine housing according to one of claims 3 or 4.
PCT/EP2008/056106 2007-05-18 2008-05-19 Turbine housing WO2008142044A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07108472.7 2007-05-18
EP07108472A EP1992789A1 (en) 2007-05-18 2007-05-18 Exhaust gas turbine casing comprising a support element

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WO2008142044A2 true WO2008142044A2 (en) 2008-11-27
WO2008142044A3 WO2008142044A3 (en) 2009-11-19

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140047813A1 (en) * 2012-08-17 2014-02-20 Solar Turbines Incorporated Exhaust collector with radial and circumferential flow breaks

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8109720B2 (en) * 2009-03-31 2012-02-07 General Electric Company Exhaust plenum for a turbine engine
WO2019194797A1 (en) * 2018-04-04 2019-10-10 Siemens Aktiengesellschaft Exhaust gas collector for a turbine

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1405090A (en) * 1917-08-24 1922-01-31 British Westinghouse Electric Semidouble-flow steam turbine
US2724545A (en) * 1949-12-05 1955-11-22 Tech Studien Ag Discharge casings for axial flow engines
US2840342A (en) * 1953-03-17 1958-06-24 David H Silvern Turbine exhaust
US3149470A (en) * 1962-08-29 1964-09-22 Gen Electric Low pressure turbine exhaust hood
US3221491A (en) * 1963-04-22 1965-12-07 Laval Turbine Turbine
US4326832A (en) * 1978-11-14 1982-04-27 Tokyo Shibaura Denki Kabushiki Kaisha Exhaust outer casing
DE3108288A1 (en) * 1981-03-05 1982-09-23 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8900 Augsburg CHARGED INTERNAL COMBUSTION ENGINE
EP0345700A1 (en) * 1988-06-07 1989-12-13 SKODA koncernovy podnik Turbo machine exhaust casing
DE4325457C1 (en) * 1993-07-29 1994-07-28 Man B & W Diesel Ag Outlet flow housing for axial turbine
EP1273760A1 (en) * 2000-05-10 2003-01-08 General Motors Corporation Turbocharger with nozzle ring coupling
WO2008012294A2 (en) * 2006-07-25 2008-01-31 Siemens Aktiengesellschaft A gas turbine arrangement

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1405090A (en) * 1917-08-24 1922-01-31 British Westinghouse Electric Semidouble-flow steam turbine
US2724545A (en) * 1949-12-05 1955-11-22 Tech Studien Ag Discharge casings for axial flow engines
US2840342A (en) * 1953-03-17 1958-06-24 David H Silvern Turbine exhaust
US3149470A (en) * 1962-08-29 1964-09-22 Gen Electric Low pressure turbine exhaust hood
US3221491A (en) * 1963-04-22 1965-12-07 Laval Turbine Turbine
US4326832A (en) * 1978-11-14 1982-04-27 Tokyo Shibaura Denki Kabushiki Kaisha Exhaust outer casing
DE3108288A1 (en) * 1981-03-05 1982-09-23 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8900 Augsburg CHARGED INTERNAL COMBUSTION ENGINE
EP0345700A1 (en) * 1988-06-07 1989-12-13 SKODA koncernovy podnik Turbo machine exhaust casing
DE4325457C1 (en) * 1993-07-29 1994-07-28 Man B & W Diesel Ag Outlet flow housing for axial turbine
EP1273760A1 (en) * 2000-05-10 2003-01-08 General Motors Corporation Turbocharger with nozzle ring coupling
WO2008012294A2 (en) * 2006-07-25 2008-01-31 Siemens Aktiengesellschaft A gas turbine arrangement

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140047813A1 (en) * 2012-08-17 2014-02-20 Solar Turbines Incorporated Exhaust collector with radial and circumferential flow breaks

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WO2008142044A3 (en) 2009-11-19

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