EP2054587B1 - Turbine housing - Google Patents

Turbine housing Download PDF

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Publication number
EP2054587B1
EP2054587B1 EP07802890A EP07802890A EP2054587B1 EP 2054587 B1 EP2054587 B1 EP 2054587B1 EP 07802890 A EP07802890 A EP 07802890A EP 07802890 A EP07802890 A EP 07802890A EP 2054587 B1 EP2054587 B1 EP 2054587B1
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EP
European Patent Office
Prior art keywords
casing
diffuser
insert
turbine
housing
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.)
Revoked
Application number
EP07802890A
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German (de)
French (fr)
Other versions
EP2054587A2 (en
Inventor
Matthias Jarusel
Marco Di Pietro
Markus Städeli
Peter Neuenschwander
Bent Phillipsen
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
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ABB Turbo Systems AG
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Application filed by ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Priority to EP07802890A priority Critical patent/EP2054587B1/en
Publication of EP2054587A2 publication Critical patent/EP2054587A2/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • 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
    • F05D2250/70—Shape

Definitions

  • the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.
  • It relates to the housing of an axial turbine of an exhaust gas turbocharger.
  • 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.
  • the turbine side is configured according to the requirements of the internal combustion engine.
  • turbine blades with different blade heights can be provided, for example, for a given turbine size, that is to say a specific turbine wheel size and a corresponding turbine housing.
  • shorter or longer blades are mounted on the blade carrier.
  • turbine blades with deviating blade height are to be retrofitted into an existing exhaust gas turbine later.
  • the housing parts in the immediate vicinity of the rotor blades that is to say in particular the outer wall of the diffuser, must also be adapted. This can be cumbersome in conventional exhaust gas turbines, especially when larger housing parts, which may have a considerable weight, must be replaced on an exhaust gas turbocharger.
  • Gas outlet housing of axial turbines such as out DE 101 37 899 C1
  • they are designed as a collecting space which has an approximately semicircular cross-section on one side and a round or rectangular flange for connection to an outflow line on the opposite side.
  • the diffuser which extends virtually axially following the blade ring of the turbine wheel and undergoes a radial deflection in the region of the mouth into the collecting space.
  • the flow is controlled in conventional Abströmgephaseen only in the region of the diffuser due to precisely matched diffuser geometries. When the flow leaves the diffuser into the plenum, the flow goes its uncontrolled course.
  • the object of the invention is to improve the outflow of an axial turbine with simple means fluidically.
  • the housing in the outflow region, from the diffuser to the gas outlet housing is designed as a component with a combined inner and outer flow channel.
  • the integration of the diffuser in the gas outlet housing a housing is created, which is aerodynamically optimized and ensures maximum flow delay with minimal pressure loss.
  • the combined inner and outer flow channel is delimited by the gas outlet housing and a diffuser wall, wherein the point of intersection between the gas outlet housing and the diffuser wall according to the invention is along the circumference at different radii. This results in two, varying in the circumferential direction partial flow channels, which are responsible for the desired flow optimization.
  • the diffuser has a replaceable insert in the area radially outside the rotor blades, which can be exchanged for another insert with other geometric dimensions as needed and depending on the selected turbine blade height.
  • Fig. 1 shows the outflow area of an axial turbine.
  • the housing 1 in the outflow region essentially comprises the turbine-near diffuser, which is delimited by an inner diffuser wall 12 and an outer diffuser wall 11, and the outer gas outlet housing 10, which accommodates the inner flow 13 emerging from the inner region of the diffuser and as an outer flow 14 leads to the outlet flange of the gas outlet housing.
  • the task of the housing in the outflow area of the turbine is to delay the flow velocity of the exhaust gas without losing much pressure.
  • the gas outlet housing 10 is integrally formed with the diffuser housing. This results in an aerodynamically optimal transition from the inner flow region 13 to the outer flow region 14.
  • the region of the intersection between the gas outlet housing 10 and the outer wall 11 of the diffuser is T-shaped. The point of intersection T travels along the circumference of the diffuser wall, so that the outer flow channel has an unequal cross-section.
  • the gas outlet housing with integrated diffuser optionally contains an insert piece 15, which is arranged in the region radially outside the turbine blades 3.
  • Fig. 2 shows this area in an enlarged view. If a new blade height is provided in an axial turbine with a given housing size, ie a given integrated diffuser and gas outlet housing, the insert 15 can be exchanged to compensate for the distance between the blade tips and the housing. This can be easily, and especially without great logistical and assembly-technical effort to realize several turbine configurations with one and the same turbine size.
  • the differing housing parts are only the small inserts. It does not need to be replaced large diffusers or even replaced whole gas outlet housing.
  • the insert 15 can be, as in the Fig. 2 , shown secured between the diffuser outer wall and, for example, the nozzle ring 4 or the gas inlet housing 2. Alternatively, the insert can be attached to any housing piece, for example by means of screws. In Fig. 2 is indicated how for different lengths blades with appropriately offset blade tips 32, the inner contour of the different inserts is moved radially inward.
  • the outer fastening ring of the nozzle ring 4 is arranged upstream of the insert 15 in the flow direction.
  • the inner diameter of the outer mounting ring of the nozzle ring is smaller than the inner diameter of the inner contour of the insert 15. The difference is advantageously 0.3 to 3 times the distance between the blade tips and the inner contour of the insert.
  • the insert may optionally be arranged between two housing parts such that it has a certain range of motion in the radial direction. Thus, thermal stresses in the insert can be prevented. It should be noted that the insert remains centered by the adjacent housing pieces with respect to the turbine axis. This can advantageously be achieved by providing a centering seat at the exit end of the insert 16. Radially outside the turbine blades, the insert can expand freely in the radial direction, provided that a gap 17 is provided between the insert and the radially outside the insert piece arranged housing part.
  • the wall thickness of the insert is small compared to the adjacent housing parts. As a result, thermal tensions can be prevented during rapid temperature changes. Further, the difference in the thermal expansion of the insert and the turbine runner can be kept small.
  • the transition between insert 15 and the outer diffuser wall 11 may be formed flat or provided with a positive or negative step.
  • the insert may be provided prior to installation in the integrated housing with the desired inner diameter, which results from the selected turbine blade lengths. If the blade length has to be adjusted during operation, the insert piece can be correspondingly replaced by another insert piece, which has a larger or smaller inner diameter. For a given turbine size, all insert pieces have the same outside mass, only the inside diameter varies.

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 das Gehäuse einer Axialturbine eines Abgasturboladers.It relates to the housing of an axial turbine of an exhaust gas turbocharger.

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.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.

Bei der Auslegung eines Abgasturboladers für eine bestimmte Anwendung wird unter anderem die Turbinenseite den Anforderungen der Brennkraftmaschine entsprechend konfiguriert. Dabei können beispielsweise für eine gegebene Turbinengrösse, also eine bestimmte Turbinenradgrösse und ein entsprechendes Turbinengehäuse, Turbinenschaufeln mit unterschiedlichen Schaufelhöhen vorgesehen werden. Je nach Anwendung werden kürzere oder längere Schaufeln auf dem Schaufelträger montiert.When designing an exhaust gas turbocharger for a particular application, among other things, the turbine side is configured according to the requirements of the internal combustion engine. In this case, turbine blades with different blade heights can be provided, for example, for a given turbine size, that is to say a specific turbine wheel size and a corresponding turbine housing. Depending on the application, shorter or longer blades are mounted on the blade carrier.

Um auf eine sich ändernde Anwendung zu reagieren, sollen auch später Turbinenschaufeln mit abweichender Schaufelhöhe in eine bestehende Abgasturbine nachgerüstet werden können.In order to react to a changing application, turbine blades with deviating blade height are to be retrofitted into an existing exhaust gas turbine later.

Natürlich müssen durch die sich ändernden Schaufelhöhen auch die Gehäuseteile in unmittelbarer Umgebung der Laufschaufeln, also insbesondere die Diffusoraussenwand, angepasst werden. Dies kann bei herkömmlichen Abgasturbinen umständlich sein, insbesondere wenn grössere Gehäuseteile, welche ein erhebliches Gewicht aufweisen können, auf einem Abgasturbolader ersetzt werden müssen.Of course, due to the changing blade heights, the housing parts in the immediate vicinity of the rotor blades, that is to say in particular the outer wall of the diffuser, must also be adapted. This can be cumbersome in conventional exhaust gas turbines, especially when larger housing parts, which may have a considerable weight, must be replaced on an exhaust gas turbocharger.

Gasaustrittsgehäuse von Axialturbinen, wie etwa aus DE 101 37 899 C1 bekannt, sind in der Regel als ein Sammelraum ausgebildet, welcher auf der einen Seite einen in etwa halbkreisförmigen Querschnitt aufweist, und auf der gegenüberliegenden Seite einen runden oder rechteckigen Flansch zum Verbinden mit einer Abströmleitung umfasst. In den Sammelraum hinein ragt der Diffusor, welcher im Anschluss an den Schaufelkranz des Turbinenrades praktisch axial verläuft und im Bereich der Mündung in den Sammelraum eine radiale Umlenkung erfährt. Die Strömung ist bei herkömmlichen Abströmgehäusen nur im Bereich des Diffusors aufgrund genau abgestimmter Diffusorgeometrien kontrolliert. Wenn die Strömung den Diffusor in den Sammelraum verlässt, dann geht die Strömung ihren unkontrollierten Lauf.Gas outlet housing of axial turbines, such as out DE 101 37 899 C1 As is generally known, they are designed as a collecting space which has an approximately semicircular cross-section on one side and a round or rectangular flange for connection to an outflow line on the opposite side. Into the collecting space projects into the diffuser, which extends virtually axially following the blade ring of the turbine wheel and undergoes a radial deflection in the region of the mouth into the collecting space. The flow is controlled in conventional Abströmgehäusen only in the region of the diffuser due to precisely matched diffuser geometries. When the flow leaves the diffuser into the plenum, the flow goes its uncontrolled course.

Kurze Darstellung der ErfindungBrief description of the invention

Aufgabe der Erfindung besteht darin, den Abströmbereich einer Axialturbine mit einfachen Mitteln strömungstechnisch zu verbessern.The object of the invention is to improve the outflow of an axial turbine with simple means fluidically.

Erfindungsgemäss wird dies dadurch erreicht, dass bei einer Axialturbine das Gehäuse im Abströmbereich, vom Diffusor bis zum Gasaustrittsgehäuse als ein Bauteil mit einem kombinierten inneren und äusseren Strömungskanal ausgebildet ist. Durch die Integration des Diffusors in das Gasaustrittsgehäuse wird ein Gehäuse geschaffen, welches aerodynamisch optimiert ist und eine maximale Strömungsverzögerung bei minimalem Druckverlust gewährleistet.According to the invention, this is achieved in that, in the case of an axial turbine, the housing in the outflow region, from the diffuser to the gas outlet housing, is designed as a component with a combined inner and outer flow channel. The integration of the diffuser in the gas outlet housing a housing is created, which is aerodynamically optimized and ensures maximum flow delay with minimal pressure loss.

Der kombinierte innere und äussere Strömungskanal wird durch das Gasaustrittsgehäuse und eine Diffusorwand begrenzt, wobei sich der Schnittpunkt zwischen Gasaustrittsgehäuse und Diffusorwand erfindungsgemäss entlang dem Umfang auf unterschiedlichen Radien befindet. Dadurch ergeben sich zwei, in Umfangsrichtung variierende Teil-Strömungskanäle, welche für die gewünschte Strömungsoptimierung verantwortlich sind.The combined inner and outer flow channel is delimited by the gas outlet housing and a diffuser wall, wherein the point of intersection between the gas outlet housing and the diffuser wall according to the invention is along the circumference at different radii. This results in two, varying in the circumferential direction partial flow channels, which are responsible for the desired flow optimization.

Optional weist der Diffusor im Bereich radial ausserhalb der Laufschaufeln ein austauschbares Einsatzstück auf, welches bei Bedarf und in Abhängigkeit der gewählten Turbinenschaufelhöhe gegen ein anderes Einsatzstück mit anderen geometrischen Abmessungen ausgetauscht werden kann.Optionally, the diffuser has a replaceable insert in the area radially outside the rotor blades, which can be exchanged for another insert with other geometric dimensions as needed and depending on the selected turbine blade height.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Im folgenden ist anhand der Figuren die erfindungsgemässe Vorrichtung schematisch dargestellt und näher erläutert.In the following, the device according to the invention is shown schematically and explained in more detail with reference to the figures.

In allen Figuren sind gleichwirkende Elemente mit gleichen Bezugszeichen versehen:

Fig. 1
zeigt einen Schnitt durch den Abströmbereich einer Axialturbine mit erfindungsgemäss integriertem Diffusor und Gasaustrittsgehäuse, und
Fig. 2
zeigt einen vergrösserten Ausschnitt eines austauschbaren Einsatzstücks, welches im Bereich radial ausserhalb der Turbinenschaufeln im Diffusor angeordnet ist.
In all figures, the same elements are provided with the same reference numerals:
Fig. 1
shows a section through the outflow of an axial turbine with inventively integrated diffuser and gas outlet housing, and
Fig. 2
shows an enlarged section of a replaceable insert, which is arranged in the region radially outside the turbine blades in the diffuser.

Weg zur Ausführung der ErfindungWay to carry out the invention

Fig. 1 zeigt den Abströmbereich einer Axialturbine. Das Gehäuse 1 im Abströmbereich umfasst im wesentlichen den turbinennahen Diffusor, welcher von einer inneren Diffusorwand 12 und einer äusseren Diffusorwand 11 begrenzt ist, und das äussere Gasaustrittsgehäuse 10, welches die aus dem inneren Bereich des Diffusors austretende innere Strömung 13 aufnimmt und als äussere Strömung 14 zum Austrittsflansch des Gasaustrittsgehäuses führt. Aufgabe des Gehäuses im Abströmbereich der Turbine ist das Verzögern der Strömungsgeschwindigkeit des Abgases, ohne dabei viel Druck zu verlieren. Fig. 1 shows the outflow area of an axial turbine. The housing 1 in the outflow region essentially comprises the turbine-near diffuser, which is delimited by an inner diffuser wall 12 and an outer diffuser wall 11, and the outer gas outlet housing 10, which accommodates the inner flow 13 emerging from the inner region of the diffuser and as an outer flow 14 leads to the outlet flange of the gas outlet housing. The task of the housing in the outflow area of the turbine is to delay the flow velocity of the exhaust gas without losing much pressure.

Das Gasaustrittsgehäuse 10 ist mit dem Diffusorgehäuse einteilig ausgebildet. Dadurch ergibt sich ein aerodynamisch optimaler Übergang vom inneren Strömungsbereich 13 zum äusseren Strömungsbereich 14. Der Bereich des Schnittpunktes zwischen dem Gasaustrittsgehäuse 10 und der äusseren Wand 11 des Diffusors ist T-förmig. Der Schnittpunkt T wandert über den Umfang verteilt der Diffusorwand entlang, so dass der äussere Strömungskanal einen ungleichen Querschnitt aufweist.The gas outlet housing 10 is integrally formed with the diffuser housing. This results in an aerodynamically optimal transition from the inner flow region 13 to the outer flow region 14. The region of the intersection between the gas outlet housing 10 and the outer wall 11 of the diffuser is T-shaped. The point of intersection T travels along the circumference of the diffuser wall, so that the outer flow channel has an unequal cross-section.

Das Gasaustrittsgehäuse mit integriertem Diffusor enthält optional ein Einsatzstück 15, welches im Bereich radial ausserhalb der Turbinenschaufeln 3 angeordnet ist. Fig. 2 zeigt diesen Bereich in einer vergrösserten Darstellung. Wird bei einer Axialturbine mit gegebener Gehäusegrösse, also gegebenem integriertem Diffusor und Gasaustrittsgehäuse, eine neue Laufschaufelhöhe vorgesehen, kann zum Ausgleich des Abstandes zwischen den Schaufelspitzen und dem Gehäuse das Einsatzstück 15 ausgetauscht werden. Damit lassen sich auf einfache Weise, und insbesondere ohne grossen logistischen und montagetechnischem Aufwand, mehrere Turbinenkonfigurationen mit ein und derselben Turbinengrösse realisieren. Die sich unterscheidenden Gehäuseteile sind lediglich die kleinen Einsatzstücke. Es brauchen keine grossen Diffusoren ausgetauscht oder gar ganze Gasaustrittsgehäuse ersetzt zu werden.The gas outlet housing with integrated diffuser optionally contains an insert piece 15, which is arranged in the region radially outside the turbine blades 3. Fig. 2 shows this area in an enlarged view. If a new blade height is provided in an axial turbine with a given housing size, ie a given integrated diffuser and gas outlet housing, the insert 15 can be exchanged to compensate for the distance between the blade tips and the housing. This can be easily, and especially without great logistical and assembly-technical effort to realize several turbine configurations with one and the same turbine size. The differing housing parts are only the small inserts. It does not need to be replaced large diffusers or even replaced whole gas outlet housing.

Das Einsatzstück 15 lässt sich, wie in der Fig. 2. dargestellt zwischen der Diffusoraussenwand und beispielsweise dem Düsenring 4 oder dem Gaseintrittsgehäuse 2 befestigen. Alternativ kann das Einsatzstück an einem beliebigen Gehäusestück befestigt werden, beispielsweise mittels Schrauben. In Fig. 2 ist angedeutet, wie für unterschiedlich lange Schaufeln mit entsprechend versetzten Schaufelspitzen 32 die Innenkontur der unterschiedlichen Einsatzstücke gegen radial innen verschoben ist.The insert 15 can be, as in the Fig. 2 , shown secured between the diffuser outer wall and, for example, the nozzle ring 4 or the gas inlet housing 2. Alternatively, the insert can be attached to any housing piece, for example by means of screws. In Fig. 2 is indicated how for different lengths blades with appropriately offset blade tips 32, the inner contour of the different inserts is moved radially inward.

Der äussere Befestigungsring des Düsenrings 4 ist in Strömungsrichtung vor dem Einsatzstück 15 angeordnet. Vorteilhafterweise ist der innere Durchmesser des äusseren Befestigungsrings des Düsenrings kleiner als der innere Durchmesser der Innenkontur des Einsatzstücks 15. Die Differenz beträgt vorteilhafterweise das 0.3 bis 3 Fache des Abstandes zwischen den Schaufelspitzen und der Innenkontur des Einsatzstücks.The outer fastening ring of the nozzle ring 4 is arranged upstream of the insert 15 in the flow direction. Advantageously, the inner diameter of the outer mounting ring of the nozzle ring is smaller than the inner diameter of the inner contour of the insert 15. The difference is advantageously 0.3 to 3 times the distance between the blade tips and the inner contour of the insert.

Das Einsatzstück kann optional derart zwischen zwei Gehäuseteilen angeordnet sein, dass es in radialer Richtung einen gewissen Bewegungsspielraum aufweist. Damit können thermische Spannungen im Einsatzstück verhindert werden. Dabei ist zu achten, dass das Einsatzstück durch die angrenzenden Gehäusestücke bezüglich der Turbinenachse zentriert bleibt. Dies kann mit Vorteil dadurch erreicht werden, dass am austrittsseitigen Ende des Einsatzstücks 16 ein Zentriersitz vorhanden ist. Radial ausserhalb der Turbinenschaufeln kann das Einsatzstück sich in radialer Richtung frei ausdehnen, sofern ein Spalt 17 zwischen dem Einsatzstück und dem radial ausserhalb des Einsatzstücks angeordneten Gehäuseteil vorgesehen ist.The insert may optionally be arranged between two housing parts such that it has a certain range of motion in the radial direction. Thus, thermal stresses in the insert can be prevented. It should be noted that the insert remains centered by the adjacent housing pieces with respect to the turbine axis. This can advantageously be achieved by providing a centering seat at the exit end of the insert 16. Radially outside the turbine blades, the insert can expand freely in the radial direction, provided that a gap 17 is provided between the insert and the radially outside the insert piece arranged housing part.

Die Wandstärke des Einsatzstücks ist im Vergleich zu den benachbarten Gehäuseteilen klein. Dadurch können bei schnellen Temperaturwechseln thermische Spannungen verhinderte werden. Weiter kann der Unterschied der thermische Dehnung des Einsatzstückes und das Turbinenlaufrad klein gehalten werden.The wall thickness of the insert is small compared to the adjacent housing parts. As a result, thermal tensions can be prevented during rapid temperature changes. Further, the difference in the thermal expansion of the insert and the turbine runner can be kept small.

Der Übergang zwischen Einsatzstück 15 und der äusseren Diffusorwand 11 kann flach oder aber mit einer positiven oder negativen Stufe versehen ausgebildet sein.The transition between insert 15 and the outer diffuser wall 11 may be formed flat or provided with a positive or negative step.

Bei der Herstellung oder Wartung einer derart ausgebildeten Axialturbine, kann das Einsatzstück vor dem Einbau in das integrierte Gehäuse mit dem gewünschten Innendurchmesser versehen werden, welcher sich aufgrund der gewählten Turbineschaufellängen ergibt. Muss im Betrieb die Schaufellänge angepasst werden, kann entsprechend das Einsatzstück durch ein anderes Einsatzstück ersetzt werden, welches einen grösseren oder kleineren Innendurchmesser aufweist. Für eine gegebene Turbinengrösse weisen alle Einsatzstücke die gleichen Aussenmasse auf, es variiert lediglich der Innendurchmesser.In the manufacture or maintenance of such a designed axial turbine, the insert may be provided prior to installation in the integrated housing with the desired inner diameter, which results from the selected turbine blade lengths. If the blade length has to be adjusted during operation, the insert piece can be correspondingly replaced by another insert piece, which has a larger or smaller inner diameter. For a given turbine size, all insert pieces have the same outside mass, only the inside diameter varies.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Gehäuse im AbströmbereichHousing in the outflow area
1010
GasaustrittsgehäuseGas outlet casing
1111
Äussere DiffusorwandOuter diffuser wall
1212
Innere DiffusorwandInner diffuser wall
1313
Innerer StrömungskanalInner flow channel
1414
Äusserer StrömungskanalOuter flow channel
1515
Einsatzstückinsert
1616
Austrittsseitiges Ende des EinsatzstücksOutlet end of the insert
1717
Radialer Spalt zwischen Gasaustrittsgehäuse und EinsatzstückRadial gap between gas outlet housing and insert
22
GaseintrittsgehäuseGas inlet casing
33
Turbinenradturbine
3131
Laufschaufelnblades
3232
Schaufelspitzenblade tips
3333
Abstand zwischen Schaufelspitzen und GehäuseDistance between blade tips and housing
44
Düsenringnozzle ring

Claims (4)

  1. Casing of an axial turbine, comprising a diffuser and a gas outlet casing, the diffuser projecting into a collecting space delimited by the gas inlet casing, characterized in that the diffuser and the gas outlet casing are produced as an integrated one-piece casing part.
  2. Casing according to Claim 1, the gas outlet casing (10) meeting the diffuser wall (11) at an intersection point (T), and the position of the intersection point (T) on the diffuser wall varying in the circumferential direction.
  3. Casing according to either one of Claims 1 and 2, the integrated casing comprising, in a region radially outside the moving blades (31) of the axial turbine, an insert piece (15) which is inserted as a separate structural part into the integrated casing.
  4. Casing according to Claim 3, a radial gap (17) being provided between the insert piece (15) and the casing part arranged radially outside, and the insert piece (15) having at the end (16) located on the gas-outlet side a centring seat, via which the said insert piece is centred on the casing part arranged radially outside.
EP07802890A 2006-08-24 2007-08-24 Turbine housing Revoked EP2054587B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07802890A EP2054587B1 (en) 2006-08-24 2007-08-24 Turbine housing

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP06405366 2006-08-24
EP06405365 2006-08-24
PCT/EP2007/058849 WO2008023068A2 (en) 2006-08-24 2007-08-24 Turbine housing
EP07802890A EP2054587B1 (en) 2006-08-24 2007-08-24 Turbine housing

Publications (2)

Publication Number Publication Date
EP2054587A2 EP2054587A2 (en) 2009-05-06
EP2054587B1 true EP2054587B1 (en) 2009-12-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP07802890A Revoked EP2054587B1 (en) 2006-08-24 2007-08-24 Turbine housing

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EP (1) EP2054587B1 (en)
JP (1) JP2010501774A (en)
KR (1) KR101055231B1 (en)
CN (1) CN101506476B (en)
DE (1) DE502007002221D1 (en)
WO (1) WO2008023068A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019101602A1 (en) * 2019-01-23 2020-07-23 Man Energy Solutions Se Fluid machine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2685054B1 (en) * 2012-07-09 2020-11-25 ABB Schweiz AG Diffuser of an exhaust gas turbine
JP5889266B2 (en) * 2013-11-14 2016-03-22 三菱重工業株式会社 Turbine
JP6731359B2 (en) * 2017-02-14 2020-07-29 三菱日立パワーシステムズ株式会社 Exhaust casing and steam turbine including the same
DE102017124467A1 (en) 2017-10-19 2019-04-25 Abb Turbo Systems Ag Diffuser arrangement of an exhaust gas turbine
CN109098780A (en) * 2018-05-24 2018-12-28 中车大连机车研究所有限公司 A kind of turbocharger combustion gas exhaust gas intake and exhaust shell
SE543851C2 (en) * 2019-12-12 2021-08-10 Scania Cv Ab Exhaust additive dosing system comprising a turbocharger
CN112524383B (en) * 2020-11-17 2022-04-19 中国航发四川燃气涡轮研究院 Axial expansion self-compensating device for aircraft engine turbine part tester

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB815475A (en) * 1954-09-10 1959-06-24 Henschel & Sohn Ges Mit Beschr Improvements in gas turbines with a small built-in heat exchanger
DD267079A1 (en) 1987-12-23 1989-04-19 Bergmann Borsig Veb EXTRACTOR HOUSING WITH RADIAL EXTRACTION FOR FLOW MACHINES
JP3547522B2 (en) * 1995-05-17 2004-07-28 新潟原動機株式会社 Exhaust turbine supercharger cleaning equipment
US6168375B1 (en) * 1998-10-01 2001-01-02 Alliedsignal Inc. Spring-loaded vaned diffuser
DE10125250C5 (en) * 2001-05-23 2007-03-29 Man Diesel Se Axial turbine of an exhaust turbocharger with internal burst protection
DE10137899C1 (en) * 2001-08-02 2003-04-03 Man B & W Diesel Ag Axial turbine for exhaust gas turbocharger of diesel engine has gas outlet channel acting as diffuser for surrounding collection space communicating with exit flow line
EP1574681A1 (en) * 2004-03-11 2005-09-14 Ford Global Technologies, LLC Exhaust turbine with down-pipe diffuser

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019101602A1 (en) * 2019-01-23 2020-07-23 Man Energy Solutions Se Fluid machine

Also Published As

Publication number Publication date
KR101055231B1 (en) 2011-08-09
KR20090035599A (en) 2009-04-09
EP2054587A2 (en) 2009-05-06
WO2008023068A3 (en) 2008-06-19
WO2008023068A2 (en) 2008-02-28
CN101506476B (en) 2011-09-14
CN101506476A (en) 2009-08-12
DE502007002221D1 (en) 2010-01-14
JP2010501774A (en) 2010-01-21

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