EP1394364A1 - Turbocharger and annular guide conduit therefor - Google Patents

Turbocharger and annular guide conduit therefor Download PDF

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Publication number
EP1394364A1
EP1394364A1 EP02018296A EP02018296A EP1394364A1 EP 1394364 A1 EP1394364 A1 EP 1394364A1 EP 02018296 A EP02018296 A EP 02018296A EP 02018296 A EP02018296 A EP 02018296A EP 1394364 A1 EP1394364 A1 EP 1394364A1
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EP
European Patent Office
Prior art keywords
spacers
bearing ring
blade
turbocharger
ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02018296A
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German (de)
French (fr)
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EP1394364B1 (en
Inventor
Michael Stilgenbauer
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BorgWarner Inc
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BorgWarner Inc
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Filing date
Publication date
Application filed by BorgWarner Inc filed Critical BorgWarner Inc
Priority to EP02018296A priority Critical patent/EP1394364B1/en
Priority to DE50205993T priority patent/DE50205993D1/en
Priority to JP2003297285A priority patent/JP2004084667A/en
Priority to US10/649,477 priority patent/US7010915B2/en
Publication of EP1394364A1 publication Critical patent/EP1394364A1/en
Priority to US11/270,738 priority patent/US7533529B2/en
Application granted granted Critical
Publication of EP1394364B1 publication Critical patent/EP1394364B1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers

Definitions

  • the invention relates to a turbocharger in the turbine housing at least a turbine rotor is rotatably mounted, which the exhaust gas via a guide grid of variable turbine geometry is supplied.
  • variable turbine geometry is in the prior art, for example according to WO 01/96713, a wreath of nozzles of variable orientation forming vanes understood. Therefore, the guide grid has one axial boundary of a blade space forming blade bearing ring, on each of an associated shaft a plurality of adjustable around its shaft blades in the so limited vane space is stored around the turbine rotor, the exhaust over so the blades can be fed in an adjustable amount.
  • TG ring
  • the invention relates to such a trained Nozzle ring.
  • Turbocharger are within the present description also similar turbomachines, such as secondary air pumps, understood.
  • Such a turbocharger and such a blade bearing ring is for example from the EP-A-0 226 444 has become known.
  • the axial dimension of the blade space secured by spacer spacers, which screwed into the vane bearing ring must be used, which is of course a relatively complicated process.
  • the invention is based on the object, the production cost of a turbocharger or to reduce a vane bearing ring of the type mentioned, and this happens according to the invention characterized in that at least one of the two rings in the circumferential direction distributed spacers integrally formed, through which the axial distance between the two Rings is secure.
  • the spacers sit on one or the other ring or alternately on one or the other ring or in each case a half spacer the one ring is opposite to half a spacer of the other ring.
  • the spacers formed on the blade bearing ring in particular are poured, because the other ring is generally part of a larger one Section of the housing to which a spacer is more difficult to install.
  • the spacers are integrally formed so that installation costs be avoided.
  • the tolerance range can also be be reduced, so that this production brings greater accuracy.
  • one is constructively free, at best in the place of the cylindrical form of a Stiftes to choose an aerodynamically cheaper form.
  • This can preferably be done the spacers themselves have a blade shape, which shape is preferably approximately tangential is aligned.
  • a turbocharger 1 in a conventional manner a turbine housing part 2 and an associated compressor housing part 3 along an axis of rotation R are arranged.
  • the turbine housing part 2 is partially shown in section, so that a blade bearing ring 6 forming a radially outer guide grid, distributed over the circumference Guide vanes 7 about their the blade bearing ring 6 passing through pivot axes.
  • an actuating device 11 To control the movement or the position of the guide vanes 7 is an actuating device 11 provided. This can be of any nature in itself, but it is preferable if, in a conventional manner, it has a control housing 12 that controls the movement a ram member 14 attached to it controls its movement in known manner on a behind the blade bearing ring 6 (left behind in Fig. 1) the same adjusting ring 5 implement the same in a slight rotational movement.
  • This rotational movement are about the shafts 8
  • the vanes 7 in terms of their Rotary position relative to the turbine rotor 4 adjusted so that they are from an approximately tangential an extreme position in an approximately radially extending other extreme position adjustable are.
  • the exhaust gas supplied via the supply channel of an internal combustion engine more or less supplied to the turbine rotor 4, before it at the along the axis of rotation R extending axial neck 10 exits again.
  • These spacers 16 are better From Fig. 2 to see where a blade bearing ring 6 without the blades 7 stored in it you can see.
  • the spacers 16 are at regular angular intervals in the circumferential direction of the ring 6 is arranged around the rotation axis R, so that the distance to the bearing ring 15 (Fig. 1) over the entire circumference is the same size.
  • These spacers 16 are formed with the blade bearing ring 6 in one piece, preferably by a casting, in particular by investment casting, so that they with the ring 6 in the immediate shallleittagen stand. It is understood that other manufacturing processes for a one-piece part 6, 16 are conceivable, but a casting is preferred.
  • the spacers 16 could, of course, at different points of the radius of the Blade bearing ring 6 are arranged, but it is preferred if they are in the apparent Way are arranged on the peripheral edge of the ring 6. Otherwise they would have to namely be arranged in place of a corresponding vane, as shown in the US-A-4,659,295 has been proposed.
  • the spacers 16 each of a bore 18 for connecting bolt with the bearing ring 15th to enforce, so that the forces of the connection directly on the surfaces 17 of the spacers 16 act.
  • the spacers 16 in the frame the invention can obtain an aerodynamically favorable form and in particular even formed like a shovel.
  • this elongated shape is approximately in the tangential direction - relative to the Ring 6 - extends.
  • the invention is not limited to the illustrated embodiment is; For example, it can also be used for turbochargers with more than one turbine rotor 2 and / or compressor rotor 21 or with more than one feed channel 9 applied become. Moreover, it would be conceivable not to provide all spacers 16 with bores 18, in particular, if more than three spacers 16 should be provided, for example six. Instead of the blade bearing ring 6 together with the spacers 16 by To produce casting, the apparent from Fig. 2 surface, for example, could also obtained by extrusion, as for other fluid flowed through car components has already been proposed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)

Abstract

The device has a turbine housing with at least one exhaust gas feed channel and rotatable turbine rotor to which gas is fed via a control grating enclosing the rotor with variable turbine geometry. The grating has axially separate blade bearing rings (6) bounding a blade volume. At least one of the rings has distance holders (16) formed on it in one piece and distributed in the peripheral direction to maintain the axial separation of the rings. AN Independent claim is also included for the following: (a) a blade bearing ring for an inventive turbocharger.

Description

Gebiet der Erfindung:Field of the invention:

Die Erfindung bezieht sich auf einen Turbolader in dessen Turbinengehäuse mindestens ein Turbinenrotor drehbar gelagert ist, dem das Abgas über ein Leitgitter variabler Turbinengeometrie zugeführt wird. Unter variabler Turbinengeometrie wird im Stand der Technik, etwa nach der WO 01/96713, ein Kranz von zwischeneinander Düsen variabler Ausrichtung bildenden Leitschaufeln verstanden. Daher besitzt das Leitgitter einen die eine axiale Begrenzung eines Schaufelraumes bildenden Schaufellagerring, an dem jeweils an einer zugehörigen Welle eine Vielzahl von um ihre Welle verstellbaren Schaufeln in dem so begrenzten Schaufelraum rund um den Turbinenrotor gelagert ist, dem Abgas so über die Schaufeln in einstellbarer Menge zuführbar ist. Am axial dem Schaufellagerring gegenüberliegenden Ende des Schaufelraumes ist ein weiterer Ring (TG) zur axialen Begrenzung desselben vorgesehen. Ferner bezieht sich die Erfindung auf einen derart ausgebildeten Schaufellagerring. Unter "Turbolader" seien im Rahmen der vorliegenden Beschreibung auch ähnliche Strömungsmaschinen, wie etwa Sekundärluftpumpen, verstanden.The invention relates to a turbocharger in the turbine housing at least a turbine rotor is rotatably mounted, which the exhaust gas via a guide grid of variable turbine geometry is supplied. Under variable turbine geometry is in the prior art, for example according to WO 01/96713, a wreath of nozzles of variable orientation forming vanes understood. Therefore, the guide grid has one axial boundary of a blade space forming blade bearing ring, on each of an associated shaft a plurality of adjustable around its shaft blades in the so limited vane space is stored around the turbine rotor, the exhaust over so the blades can be fed in an adjustable amount. At the axially opposite the blade bearing ring End of the bucket space is another ring (TG) for axial limitation provided for. Furthermore, the invention relates to such a trained Nozzle ring. Under "turbocharger" are within the present description also similar turbomachines, such as secondary air pumps, understood.

Hintergrund der ErfindungBackground of the invention

Ein derartiger Turbolader und ein derartiger Schaufellagerring ist beispielsweise aus der EP-A-0 226 444 bekannt geworden. Dabei wird die axiale Dimension des Schaufelraumes durch abstandhaltende Distanzhülsen gesichert, welche in den Schaufellagerring eingeschraubt eingesetzt werden müssen, was natürlich ein relativ aufwendiger Vorgang ist. Dazu kommen noch die relativ hohen Kosten der Montage.Such a turbocharger and such a blade bearing ring is for example from the EP-A-0 226 444 has become known. In this case, the axial dimension of the blade space secured by spacer spacers, which screwed into the vane bearing ring must be used, which is of course a relatively complicated process. In addition, there are the relatively high costs of installation.

Kurzfassung der ErfindungSummary of the invention

Der Erfindung liegt die Aufgabe zugrunde, die Herstellungkosten eines Turboladers bzw. eines Schaufellagerringes der eingangs genannten Art zu verringern, und dies geschieht erfindungsgemäß dadurch, daß mindestens einer der beiden Ringe in Umfangsrichtung verteilt Abstandhalter einteilig angeformt aufweist, durch die der axiale Abstand der beiden Ringe sicherbar ist. Dadurch wird in überraschender Weise nicht nur die gestellte Aufgabe gelöst, sondern auch - wie aus der folgenden detaillierten Beschreibung der Zeichnungen hervorgeht - die Präzision und die Zuverlässigkeit im Betrieb erhöht.The invention is based on the object, the production cost of a turbocharger or to reduce a vane bearing ring of the type mentioned, and this happens according to the invention characterized in that at least one of the two rings in the circumferential direction distributed spacers integrally formed, through which the axial distance between the two Rings is secure. As a result, not only the asked is in a surprising way Task solved, but also - as from the following detailed description of the Drawings show - increased precision and reliability in operation.

An sich ist es gleichgültig, ob die Abstandhalter am einen oder am anderen Ring sitzen oder wechselweise am einen oder anderen Ring oder jeweils ein halber Abstandhalter des einen Ringes einem halben Abstandhalter des anderen Ringes gegenüberliegt. Allerdings ist es bevorzugt, wenn die Abstandhalter am Schaufellagerring angeformt, insbesondere gegossen, sind, denn der andere Ring wird im allgemeinen Teil eines größeren Abschnittes des Gehäuses sein, an dem ein Abstandhalter schwieriger anzubringen ist.In itself, it does not matter if the spacers sit on one or the other ring or alternately on one or the other ring or in each case a half spacer the one ring is opposite to half a spacer of the other ring. Indeed it is preferred if the spacers formed on the blade bearing ring, in particular are poured, because the other ring is generally part of a larger one Section of the housing to which a spacer is more difficult to install.

Erfindungsgemäß werden also die Abstandhalter einteilig angeformt, so daß Montagekosten vermieden werden. Bei Einsatz eines Feingußverfahrens kann auch der Toleranzbereich verringert werden, so daß diese Herstellung eine größere Genauigkeit bringt. Vor allem aber ist man auch konstruktiv frei, allenfalls an Stelle der zylindrischen Form eines Stiftes eine aerodynamisch günstigere Form zu wählen. Dies kann bevorzugt so erfolgen, daß die Abstandhalter selbst Schaufelform besitzen, welche Form bevorzugt etwa tangential ausgerichtet ist.According to the invention so the spacers are integrally formed so that installation costs be avoided. When using a precision casting process, the tolerance range can also be be reduced, so that this production brings greater accuracy. In front But in any case one is constructively free, at best in the place of the cylindrical form of a Stiftes to choose an aerodynamically cheaper form. This can preferably be done the spacers themselves have a blade shape, which shape is preferably approximately tangential is aligned.

Kurzbeschreibung der ZeichnungenBrief description of the drawings

Weitere Einzelheiten der Erfindung ergeben sich aus der nachfolgenden Beschreibung eines in der Zeichnung schematisch dargestellten, bevorzugten Ausführungsbeispieles.Further details of the invention will become apparent from the following description a schematically illustrated in the drawing, preferred embodiment.

Es zeigen:

Fig. 1
einen Turbolader in Perspektivansicht, teilweise im Schnitt, an dem die vorliegende Erfindung zur Anwendung kommt; und
Fig. 2
eine Perspektivansicht eines erfindungsgemäßen, in einen Turbolader nach Fig. 1 einzusetzenden Schaufellagerring.
Show it:
Fig. 1
a turbocharger in perspective view, partially in section, to which the present invention is applied; and
Fig. 2
a perspective view of a blade bearing ring according to the invention, to be used in a turbocharger according to Fig. 1.

Detaillierte Beschreibung der ZeichnungenDetailed description of the drawings

Gemäß Fig. 1 weist ein Turbolader 1 in üblicher Weise einen Turbinengehäuseteil 2 und einen damit verbundenen Kompressorgehäuseteil 3 auf, die entlang einer Rotationsachse R angeordnet sind. Der Turbinengehäuseteil 2 ist teilweise im Schnitt gezeigt, so daß darin ein Schaufellagerring 6 ein radial äußeres Leitgitter bildende, über den Umfang verteilte Leitschaufeln 7 um ihre den Schaufellagerring 6 durchsetzenden Schwenkachsen 8 verdreht, so daß sie zwischen einander Düsenquerschnitte bilden, die je nach der Lage der Leitschaufeln 7, nämlich radial (wie dargestellt) oder mehr tangential, größer oder kleiner sind und den in der Mitte an der Achse R gelegene Turbinenrotor 4 mehr oder weniger mit dem über einen Zufuhrkanal 9 zugeführten und über einen zentralen Stutzen 10 abgeführten Abgas eines Motors beaufschlagen, um über den Turbinenrotor 4 einen auf derselben Welle sitzenden Kompressorrotor 21 anzutreiben.1, a turbocharger 1 in a conventional manner a turbine housing part 2 and an associated compressor housing part 3 along an axis of rotation R are arranged. The turbine housing part 2 is partially shown in section, so that a blade bearing ring 6 forming a radially outer guide grid, distributed over the circumference Guide vanes 7 about their the blade bearing ring 6 passing through pivot axes. 8 twisted so that they form nozzle cross sections between each other, depending on the location the guide vanes 7, namely radially (as shown) or more tangentially, larger or are smaller and located in the middle on the axis R turbine rotor 4 more or less with the supplied via a supply channel 9 and a central port 10 applied exhaust gas of an engine to impose on the turbine rotor 4 a To drive on the same shaft compressor rotor 21 to drive.

Um die Bewegung bzw. die Lage der Leitschaufeln 7 zu steuern, ist eine Betätigungseinrichtung 11 vorgesehen. Diese kann an sich beliebiger Natur sein, doch ist es bevorzugt, wenn sie, in an sich herkömmlicher Weise, ein Steuergehäuse 12 aufweist, das die Steuerbewegung eines an ihr befestigten Stößelgliedes 14 steuert, dessen Bewegung in an sich bekannter Weise auf einen hinter dem Schaufellagerring 6 (links dahinter in Fig. 1) gelegenen Verstellring 5 in eine leichte Drehbewegung desselben umzusetzen. Durch diese Drehbewegung werden über die Wellen 8 die Leitschaufeln 7 hinsichtlich ihrer Drehlage relativ zum Turbinenrotor 4 so verstellt, daß sie aus einer etwa tangential verlaufenden einen Extremstellung in eine etwa radial verlaufende andere Extremlage verstellbar sind. Dadurch wird das über den Zufuhrkanal zugeführte Abgas eines Verbrennungsmotors mehr oder weniger dem Turbinenrotor 4 zugeführt, bevor es bei dem sich entlang der Drehachse R erstreckenden Axialstutzen 10 wieder austritt.To control the movement or the position of the guide vanes 7 is an actuating device 11 provided. This can be of any nature in itself, but it is preferable if, in a conventional manner, it has a control housing 12 that controls the movement a ram member 14 attached to it controls its movement in known manner on a behind the blade bearing ring 6 (left behind in Fig. 1) the same adjusting ring 5 implement the same in a slight rotational movement. By This rotational movement are about the shafts 8, the vanes 7 in terms of their Rotary position relative to the turbine rotor 4 adjusted so that they are from an approximately tangential an extreme position in an approximately radially extending other extreme position adjustable are. As a result, the exhaust gas supplied via the supply channel of an internal combustion engine more or less supplied to the turbine rotor 4, before it at the along the axis of rotation R extending axial neck 10 exits again.

Zwischen dem Schaufellagerring 6 und einem ringförmigen Teil 15 des Turbinengehäuseteiles 2 verbleibt ein relativ schmaler Raum 13 um den Schaufeln 7 eine freie Beweglichkeit zu gestatten. Natürlich darf dieser Schaufelraum 13 nicht wesentlich größer als die Breite der Schaufeln 7 sein, weil dann die Abgasenergie Leckverluste erleiden würde. Anderseits darf der Schaufelraum 13 aber auch nicht zu knapp bemessen sein, weil dann die Schaufeln 7 klemmen könnten. Dies ist auch deshalb besonders bedeutsam, weil ja durch die heißen Abgase mit einer gewissen Wärmedehnung des Materials gerechnet werden muß.Between the blade bearing ring 6 and an annular part 15 of the turbine housing part 2 remains a relatively narrow space 13 around the blades 7 a free mobility to allow. Of course, this blade chamber 13 may not be much larger than that Be the width of the blades 7, because then the exhaust energy would suffer leakage. On the other hand, the vane space 13 may not be too tight, because then the blades 7 could jam. This is especially important because yes calculated by the hot exhaust gases with a certain thermal expansion of the material must become.

Um daher diesen Schaufelraum 13 bzw. den Abstand des Schaufellagerringes 6 vom gegenüberliegenden Lagerring 15 zu sichern, trägt der Schaufellagerring 6 angeformte, mit ihm einstückig ausgebildete Abstandhalter 16. Diese Abstandhalter 16 sind besser aus Fig. 2 zu ersehen, wo ein Schaufellagerring 6 ohne die in ihm gelagerten Schaufeln 7 zu sehen ist.Therefore, this blade space 13 and the distance of the blade bearing ring 6 from to secure opposite bearing ring 15, carries the blade bearing ring 6 integrally formed, with him integrally formed spacers 16. These spacers 16 are better From Fig. 2 to see where a blade bearing ring 6 without the blades 7 stored in it you can see.

Wie ersichtlich, sind die Abstandhalter 16 in gleichmäßigen Winkelabständen in Umfangsrichtung des Ringes 6 rund um die Rotationsachse R angeordnet, so daß der Abstand zum Lagerring 15 (Fig. 1) über den gesamten Umfang gleich groß ist. Diese Abstandhalter 16 sind mit dem Schaufellagerring 6 in einem Stück ausgebildet, vorzugsweise durch einen Gießvorgang, insbesondere durch Feingießen, so daß sie mit dem Ring 6 in unmittelbarer Wärmeleitverbindung stehen. Es versteht sich, daß auch andere Herstellvorgänge für einen einstückigen Teil 6, 16 denkbar sind, doch ist ein Gießvorgang bevorzugt.As can be seen, the spacers 16 are at regular angular intervals in the circumferential direction of the ring 6 is arranged around the rotation axis R, so that the distance to the bearing ring 15 (Fig. 1) over the entire circumference is the same size. These spacers 16 are formed with the blade bearing ring 6 in one piece, preferably by a casting, in particular by investment casting, so that they with the ring 6 in the immediate Wärmeleitverbindung stand. It is understood that other manufacturing processes for a one-piece part 6, 16 are conceivable, but a casting is preferred.

Wenn daher heißes Abgas über den Zuführkanal 9 (oder mehrere Zuführkanäle) in den Schaufelraum 13 strömt, so verteilt sich diese Wärme relativ rasch über den Schaufellagerring 6 und dessen Abstandhalter 16, so daß an allen Orten im wesentlichen dieselbe Wärmedehnung erzielt und damit der Abstand zum Lagerring 15 mit Sicherheit über den Umfang des Schaufellagerringes 6 gleichmäßig sein wird. Wären die Abstandhalter etwa an in Bohrlöcher des Ringes 6 eingeschraubten Hülsen, also aus separaten Teilen, ausgebildet, so wäre einerseits der Wärmeübergang nicht so gut und anderseits könnten diese Hülsen schwerlich aus demselben (z.B. Guß-)Material bestehen, so daß auch die Dehnungskoëffizienten unterschiedlich wären. Dies alles wird - zur Erhöhung der Präzision und Verläßlichkeit im Betrieb - durch die Erfindung vermieden.Therefore, when hot exhaust gas via the supply channel 9 (or more feed channels) in the Bucket space 13 flows, this heat is distributed relatively quickly over the blade bearing ring 6 and its spacer 16, so that in all places substantially the same Thermal expansion achieved and thus the distance to the bearing ring 15 with certainty over the Scope of the blade bearing ring 6 will be uniform. If the spacers were about on sleeves screwed into boreholes of the ring 6, ie of separate parts, so on the one hand the heat transfer would not be so good and on the other hand could these sleeves are hardly made of the same (e.g., cast) material, so that the Strain coefficients would be different. All this will - to increase the precision and reliability in operation - avoided by the invention.

An sich könnten die Abstandhalter 16 natürlich an verschiedenen Stellen des Radius des Schaufellagerringes 6 angeordnet werden, doch ist es bevorzugt, wenn sie in der ersichtlichen Weise am Umfangsrand des Ringes 6 angeordnet sind. Andernfalls müßten sie nämlich an Stelle einer entsprechenden Leitschaufel angeordnet werden, wie dies in der US-A-4,659,295 vorgeschlagen worden ist.In itself, the spacers 16 could, of course, at different points of the radius of the Blade bearing ring 6 are arranged, but it is preferred if they are in the apparent Way are arranged on the peripheral edge of the ring 6. Otherwise they would have to namely be arranged in place of a corresponding vane, as shown in the US-A-4,659,295 has been proposed.

Ferner wurde bereits erwähnt, daß es möglich wäre, wenigstens einen Teil der Abstandhalter 16 am Lagerring 15 vorzusehen und gegen den Schaufellagerring 6 vorragen zu lassen, doch sind dort die Verhältnisse infolge der komplizierten Raumform des Turbinengehäuseteil 2 nicht so günstig wie bei der einfachen Form des Schaufellagerringes 6. Auch ist klar, daß es zwar an sich möglich wäre, nur zwei Abstandhalter 16 oder auch mehr als drei vorzusehen, daß aber mit genau drei Abstandhaltern 16 die Verbindungsebene zum Lagerring 15 (Fig. 1) geometrisch genau definiert ist. Es empfiehlt sich überdies, die diesem Lagerring 15 gegenüberliegenden und mit ihm in Verbindung tretenden Flächen 17 spanabhebend zu bearbeiten, beispielsweise durch Fräsen oder Drehen, um die axiale Länge aller Abstandhalter genau einzuhalten.Furthermore, it has already been mentioned that it would be possible to have at least a part of the spacers Provide 16 on the bearing ring 15 and protrude toward the blade bearing ring 6 let, but there are the conditions due to the complicated spatial shape of the turbine housing part 2 not so cheap as in the simple form of the blade bearing ring. 6 It is also clear that, although it would be possible per se, only two spacers 16 or provide more than three, but that with exactly three spacers 16, the connection level to the bearing ring 15 (Fig. 1) is geometrically defined precisely. It is also recommended the opposite of this bearing ring 15 and passing in conjunction with him To edit 17 surfaces machined, for example, by milling or turning to to strictly adhere to the axial length of all spacers.

Für diese zuletzt genannte Verbindung mit dem Lagerring 15 ist es vorteilhaft, die Abstandhalter 16 jeweils von einer Bohrung 18 für Verbindungsbolzen mit dem Lagerring 15 zu durchsetzen, so daß die Kräfte der Verbindung unmittelbar auf die Flächen 17 der Abstandhalter 16 wirken. Auch ist aus Fig. 2 ersichtlich, daß die Abstandhalter 16 im Rahmen der Erfindung eine aerodynamisch günstige Form erhalten können und insbesondere selbst schaufelartig ausgebildet werden. Im Falle einer aus aerodynamischen Gesichtspunkten gewählten länglichen Form, wie sie auch aus Fig. 2 zu ersehen ist, ist es vorteilhaft, wenn sich diese längliche Form etwa in tangentialer Richtung - bezogen auf den Ring 6 - erstreckt.For this latter connection with the bearing ring 15, it is advantageous, the spacers 16 each of a bore 18 for connecting bolt with the bearing ring 15th to enforce, so that the forces of the connection directly on the surfaces 17 of the spacers 16 act. It is also apparent from Fig. 2 that the spacers 16 in the frame the invention can obtain an aerodynamically favorable form and in particular even formed like a shovel. In the case of an aerodynamic point of view selected elongated shape, as can also be seen from Fig. 2, it is advantageous if this elongated shape is approximately in the tangential direction - relative to the Ring 6 - extends.

Ferner ist es vorteilhaft, wenn entlang des Umfangsrandes des jeweiligen Ringes 15 und/oder 6 und insbesondere des Schaufellagerringes 6 selbst, eine sich in axialer Richtung vom Schaufelraum 13 (bezogen auf Fig. 2 ist dies der Raum, der durch die axiale Länge L der Abstandhalter 16 bestimmt wird) zurückweichende Fläche 19 vorgesehen ist. Diese zurückweichende Fläche 19 ist im Beispiel der Fig. 2 bevorzugt konisch abgeschrägt, kann aber für gewisse Anwendungen gewünschtenfalls auch abgesetzt sein, etwa in Form einer Stufe mit abgerundetem Winkel. Dies hat sich für die aerodynamischen Verhältnisse innerhalb des Schaufelraumes 13 (Fig. 1) herausgestellt, welche Schaufeln 7 (Fig. 1) - wie erwähnt - an Verstellwellen sitzen, die jeweils eine Bohrung 20 aus einem in Umfangsrichtung des Schaufellagerringes 6 verlaufenden Kranz von Bohrungen 20 durchsetzen. Es versteht sich, daß eine solche vom Raum 13 zurückweichende Fläche auch am Ring 15 vorgesehen sein kann, obwohl sie bevorzugt nur am Schaufellagerring 6 vorgesehen ist.Furthermore, it is advantageous if along the peripheral edge of the respective ring 15th and / or 6 and in particular of the blade bearing ring 6 itself, one in the axial direction from the blade space 13 (referring to Fig. 2, this is the space defined by the axial Length L of the spacer 16 is determined) receding surface 19 is provided. This receding surface 19 is preferably tapered conically in the example of FIG. but may also be discontinued for certain applications if desired, in the form of a step with a rounded angle. This has become aerodynamic Conditions within the vane space 13 (Fig. 1) exposed, which Blades 7 (Fig. 1) - as mentioned - sitting on adjusting shafts, each having a bore 20th from a ring extending in the circumferential direction of the blade bearing ring 6 of holes 20 enforce. It is understood that such a receding from the space 13 Surface may also be provided on the ring 15, although they are preferred only on the blade bearing ring 6 is provided.

Aus den obigen Erläuterungen wird auch klar, daß durch die Erfindung die Herstellung der Abstandhalter mit dem Schaufellagering 6 ebenso vereinfacht wird, wie sein darauf folgender Einbau in den Turbinengehäuseteil 2. Überdies wird ein gleichmäßigerer und unmittelbarer Wärmeübergang zwischen Schaufellagerring 6 und Abstandhalter 16 erzielt. Dabei wird die Verläßlichkeit der präzisen Einhaltung des axialen Abstandes für den Schaufelraum 13 unter allen Betriebsbedingungen erhöht.From the above explanations it is also clear that the invention the spacer with the blade bearing ring 6 is simplified as well as being thereon following installation in the turbine housing part 2. Moreover, a more uniform and achieved direct heat transfer between the blade bearing ring 6 and spacer 16. The reliability of the precise adherence to the axial distance for the Bucket space 13 increased under all operating conditions.

Ferner versteht es sich, daß die Erfindung nicht auf die dargestellte Ausführung beschränkt ist; beispielsweise kann sie auch für Turbolader mit mehr als einem Turbinenrotor 2 und/oder Kompressorrotor 21 oder mit mehr als einem Zuführkanal 9 angewandt werden. Überdies wäre es denkbar, nicht alle Abstandhalter 16 mit Bohrungen 18 zu versehen, insbesondere, wenn etwa mehr als drei Abstandhalter 16 vorgesehen sein sollten, beispielsweise sechs. Statt den Schaufellagerring 6 samt den Abstandhaltern 16 durch Gießen herzustellen, könnte die aus Fig. 2 ersichtliche Oberfläche beispielsweise auch durch Fließpressen erhalten werden, wie dies für andere fluiddurchströmte Autobestandteile bereits vorgeschlagen worden ist.Furthermore, it should be understood that the invention is not limited to the illustrated embodiment is; For example, it can also be used for turbochargers with more than one turbine rotor 2 and / or compressor rotor 21 or with more than one feed channel 9 applied become. Moreover, it would be conceivable not to provide all spacers 16 with bores 18, in particular, if more than three spacers 16 should be provided, for example six. Instead of the blade bearing ring 6 together with the spacers 16 by To produce casting, the apparent from Fig. 2 surface, for example, could also obtained by extrusion, as for other fluid flowed through car components has already been proposed.

Claims (10)

Turbolader, der folgendes aufweist: ein Turbinengehäuse (2) mit mindestens einem Zufuhrkanal (9) für Abgas, in dem mindestens ein Turbinenrotor (4) drehbar gelagert ist, und dem das Abgas über ein den Turbinenrotor (4) radial außen umgebenden Leitgitter variabler Turbinengeometrie zuführbar ist, welches Leitgitter einen Schaufellagerring (6) aufweist, an dem jeweils an einer zugehörigen Welle (8) eine Vielzahl von um ihre Welle (8) verstellbaren Schaufeln (7) in einem begrenzten Schaufelraum (13) rund um den Turbinenrotor (4) gelagert ist, dem Abgas so über die Schaufeln (7) in einstellbarer Menge zuführbar ist, welcher Schaufellagerring (6) die eine axiale Begrenzung eines Schaufelraumes (13) bildet, und mit einem weiteren, dem Schaufellagerring (6) axial gegenüberliegenden Ring (15), der die andere axiale Begrenzung des Schaufelraumes (13) bildet, dadurch gekennzeichnet, daß
mindestens einer der beiden Ringe (6, 15) in Umfangsrichtung verteilt Abstandhalter (16) einteilig angeformt aufweist, durch die der axiale Abstand der beiden Ringe (6, 15) sicherbar ist.Turbocharger comprising: a turbine housing (2) with at least one supply channel (9) for exhaust gas, in which at least one turbine rotor (4) is rotatably mounted, and the exhaust gas via a the turbine rotor (4) radially outside surrounding Leitgitter variable turbine geometry is fed, which Leitgitter a vane bearing ring (6), on each of which an associated shaft (8) a plurality of about its shaft (8) adjustable blades (7) in a limited vane space (13) is mounted around the turbine rotor (4), the exhaust gas in an adjustable amount can be supplied via the blades (7), which blade bearing ring (6) which forms an axial boundary of a blade chamber (13), and with a further, the blade bearing ring (6) axially opposite ring (15) which forms the other axial boundary of the blade space (13), characterized in that
At least one of the two rings (6, 15) distributed in the circumferential direction spacers (16) integrally formed, through which the axial distance of the two rings (6, 15) is securable. Turbolader (1) nach Anspruch 1, dadurch gekennzeichnet, daß die Abstandhalter (16) am Schaufellagerring (6) angeformt sind.Turbocharger (1) according to claim 1, characterized in that the spacers (16) are integrally formed on the blade bearing ring (6). Turbolader (1) nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Abstandhalter (16) am gegossenen jeweiligen Ring (6 bzw. 15) mitgegossen sind.Turbocharger (1) according to claim 1 or 2, characterized in that the spacers (16) are also cast on the cast respective ring (6 or 15). Turbolader (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Abstandhalter (16) am Umfangsrand des jeweiligen Ringes (6 bzw. 15) angeordnet sind.Turbocharger (1) according to one of the preceding claims, characterized in that the spacers (16) are arranged on the peripheral edge of the respective ring (6 or 15). Turbolader (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß entlang des Umfangsrandes des jeweiligen Ringes (6 bzw. 15), insbesondere des Schaufellagerringes (6), eine sich in axialer Richtung vom Schaufelraum (13) zurückweichende Fläche (19) vorgesehen ist.Turbocharger (1) according to one of the preceding claims, characterized in that along the peripheral edge of the respective ring (6 or 15), in particular of the blade bearing ring (6), an area (19) which recedes in the axial direction from the blade space (13) is. Turbolader (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Abstandhalter (16) selbst eine längliche Form, bevorzugt Schaufelform, besitzen, welche Form zweckmäßig etwa tangential ausgerichtet ist.Turbocharger (1) according to one of the preceding claims, characterized in that the spacers (16) themselves have an elongate shape, preferably a blade shape, which shape is expediently oriented approximately tangentially. Turbolader (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß wenigstens ein Teil der Abstandhalter (16) jeweils von einer Bohrung (18) für Verbindungsbolzen mit einem jeweils benachbarten Lagerteil durchsetzt sind, insbesondere zur Verbindung mit dem axial gegenüberliegenden Lagerring (15).Turbocharger (1) according to one of the preceding claims, characterized in that at least a part of the spacers (16) are respectively penetrated by a bore (18) for connecting bolts with a respective adjacent bearing part, in particular for connection to the axially opposite bearing ring (15). , Schaufellagerring (6) für einen Turbolader (1) nach einem der vorhergehenden Ansprüche, mit über seine Fläche in Umfangsrichtung verteilten Bohrungen (20) für den Durchtritt der Wellen (8) von Leitschaufeln (7), dadurch gekennzeichnet, daß er in Umfangsrichtung verteilte axiale Abstandhalter (16), insbesondere mit einer aerodynamischen Schaufelform, einteilig angeformt aufweist, beispielsweise er in einem Gießverfahren, insbesondere einem Feingießverfahren, hergestellt und dabei die Abstandhalter (16) mitgegossen sind.Blade bearing ring (6) for a turbocharger (1) according to one of the preceding claims, with bores (20) distributed over its surface in the circumferential direction for the passage of the shafts (8) of guide vanes (7), characterized in that they have axial distributed in the circumferential direction Spacer (16), in particular with an aerodynamic blade shape, integrally formed, for example, it in a casting process, in particular a precision casting, manufactured while the spacers (16) are mitgegossen. Schaufellagerring (6) nach Anspruch 8, dadurch gekennzeichnet, daß entlang seines radialen Umfangsrandes eine sich in axialer Richtung Raum für die Schaufeln (7) zurückweichende Fläche (19) vorgesehen ist, an der vorzugsweise die Abstandhalter (16) angeordnet sind.Blade bearing ring (6) according to claim 8, characterized in that along its radial peripheral edge in the axial direction space for the blades (7) receding surface (19) is provided on which preferably the spacers (16) are arranged. Schaufellagerring (6) nach Anspruch 8 oder 9, dadurch gekennzeichnet, daß wenigstens ein Teil der Abstandhalter (16) jeweils von einer Bohrung (18) für Verbindungsbolzen mit einem jeweils benachbarten Lagerteil durchsetzt sind, insbesondere zur Verbindung mit dem axial gegenüberliegenden Ring (15).Blade bearing ring (6) according to claim 8 or 9, characterized in that at least a part of the spacers (16) are respectively penetrated by a bore (18) for connecting bolts with a respective adjacent bearing part, in particular for connection to the axially opposite ring (15). ,
EP02018296A 2002-08-26 2002-08-26 Turbocharger and annular guide conduit therefor Expired - Fee Related EP1394364B1 (en)

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EP02018296A EP1394364B1 (en) 2002-08-26 2002-08-26 Turbocharger and annular guide conduit therefor
DE50205993T DE50205993D1 (en) 2002-08-26 2002-08-26 Turbocharger and blade bearing ring for this
JP2003297285A JP2004084667A (en) 2002-08-26 2003-08-21 Turbocharger and its vane support ring
US10/649,477 US7010915B2 (en) 2002-08-26 2003-08-26 Turbocharger and vane support ring for it
US11/270,738 US7533529B2 (en) 2002-08-26 2005-11-09 Turbocharger and vane support ring for it

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US20050005603A1 (en) 2005-01-13
JP2004084667A (en) 2004-03-18
DE50205993D1 (en) 2006-05-04
US20060053787A1 (en) 2006-03-16
US7533529B2 (en) 2009-05-19
EP1394364B1 (en) 2006-03-08
US7010915B2 (en) 2006-03-14

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