EP1394364B1 - Turbocharger and annular guide conduit therefor - Google Patents
Turbocharger and annular guide conduit therefor Download PDFInfo
- Publication number
- EP1394364B1 EP1394364B1 EP02018296A EP02018296A EP1394364B1 EP 1394364 B1 EP1394364 B1 EP 1394364B1 EP 02018296 A EP02018296 A EP 02018296A EP 02018296 A EP02018296 A EP 02018296A EP 1394364 B1 EP1394364 B1 EP 1394364B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- spacers
- turbocharger
- annular guide
- guide conduit
- 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.)
- Expired - Lifetime
Links
- 125000006850 spacer group Chemical group 0.000 claims description 38
- 238000005266 casting Methods 0.000 claims description 4
- 238000005495 investment casting Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 4
- 230000002349 favourable effect Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000004323 axial length Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
Images
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
- 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 whose turbine housing at least one turbine rotor is rotatably mounted, to which the exhaust gas is fed via a guide grid of variable turbine geometry.
- Variable turbine geometry is understood in the prior art, for example according to WO 01/96713, to be a ring of vanes forming variable orientation nozzles. Therefore, the guide grid has an axial boundary of a blade space forming blade bearing ring, on each of which an associated shaft a plurality of adjustable around its shaft blades is mounted in the so-limited blade space around the turbine rotor, the exhaust so over the blades in an adjustable amount can be fed.
- a further ring a further ring (TG) is provided for axially limiting it.
- the invention relates to such a trained blade bearing ring.
- turbomachines such as secondary air pumps.
- Such a turbocharger and such a blade bearing ring has become known, for example, from EP-A-0 226 444 or DE-A-3 516 738.
- the axial dimension of the blade space is secured by spacer spacers, which must be inserted screwed into the blade bearing ring, which of course is a relatively complex operation.
- the invention has for its object to reduce the production cost of a turbocharger or a blade bearing ring of the type mentioned, and this is done according to the invention in that at least one of the two rings circumferentially distributed spacers integrally formed by 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 each half a spacer the one ring is opposite to half a spacer of the other ring.
- the spacers are formed on the vane bearing ring, in particular cast, because the other ring will generally be part of a larger portion of the housing to which a spacer is more difficult to attach.
- the spacers are integrally formed so that installation costs are avoided.
- the tolerance range can be reduced, so that this production brings greater accuracy.
- a turbocharger 1 in a conventional manner a turbine housing part 2 and an associated compressor housing part 3, which are arranged along an axis of rotation R.
- the turbine housing part 2 is partially shown in section, so that therein a vane ring 6 a radially outer vane forming, circumferentially distributed vanes 7 rotated about their the vane ring 6 passing through pivot axes 8 so that they form between each nozzle cross-sections, depending on the location the guide vanes 7, namely radially (as shown) or more tangential, larger or smaller and located in the middle of the axis R turbine rotor 4 more or less with the supplied via a supply channel 9 and a central port Apply 10 discharged exhaust gas of a motor to drive via the turbine rotor 4 a seated on the same shaft compressor rotor 21.
- an actuating device 11 is provided. This may be of any nature in itself, but it is preferred if it has, in a conventional manner, a control housing 12 which controls the control movement of a ram member 14 attached to its movement in a conventional manner to a behind the blade bearing ring 6 (left behind in Fig. 1) located adjusting ring 5 implement the same in a slight rotational movement.
- the guide vanes 7 are adjusted relative to the turbine rotor 4 with respect to their rotational position via the shafts 8 in such a way that they can be adjusted from an approximately tangentially extending one extreme position into an approximately radially extending other extreme position.
- the exhaust gas supplied via the supply channel of an internal combustion engine is supplied more or less to the turbine rotor 4, before it exits again at the axial connection piece 10 extending along the axis of rotation R.
- this blade space 13 may not be much larger than the width of the blades 7, because then the exhaust gas energy would suffer leakage.
- the blade chamber 13 may not be too tight, because then the blades 7 could jam. This is also particularly significant, because yes must be expected by the hot exhaust gases with a certain thermal expansion of the material.
- the spacers 16 are arranged at uniform angular intervals in the circumferential direction of the ring 6 around the axis of rotation R, so that the distance to the bearing ring 15 (FIG. 1) over the entire circumference is the same.
- 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 are in direct thermal conduction with the ring 6. 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 be arranged at different locations of the radius of the blade bearing ring 6, but it is preferred if they are arranged in the apparent manner at the peripheral edge of the ring 6. Otherwise, they would have to be placed in place of a corresponding vane, as proposed in US-A-4,659,295.
- the spacers 16 can receive an aerodynamically favorable shape in the context of the invention and in particular themselves are formed like a shovel. In the case of an elongated shape chosen from an aerodynamic point of view, as can also be seen from FIG. 2, it is advantageous if this elongate shape extends approximately tangentially with respect to the ring 6.
- receding surface 19 is provided along the peripheral edge of the respective ring 15 and / or 6 and in particular of the blade bearing ring 6 itself, in the axial direction of the blade chamber 13 (based on Fig. 2, this is the space through the axial length L of Spacer 16 is determined).
- This receding surface 19 is preferably tapered in the example of FIG. 2, but may also be discontinued for certain applications, for example in the form of a step with a rounded angle. This has been found for the aerodynamic conditions within the blade space 13 (FIG. 1), which blades 7 (FIG. 1) - as mentioned - sit on adjusting shafts, each having a bore 20 extending from a circumferential direction of the blade bearing ring 6 ring 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 it is preferably provided only on the blade bearing ring 6.
- the invention is not limited to the illustrated embodiment; For example, it can also be applied to turbochargers with more than one turbine rotor 2 and / or compressor rotor 21 or with more than one feed channel 9. Moreover, it would be conceivable not to provide all the spacers 16 with bores 18, in particular if, for example, more than three spacers 16 should be provided, for example six.
- the apparent from Fig. 2 surface could, for example, also are obtained by extrusion, as has already been proposed for other fluid-flow car components.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Description
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 whose turbine housing at least one turbine rotor is rotatably mounted, to which the exhaust gas is fed via a guide grid of variable turbine geometry. Variable turbine geometry is understood in the prior art, for example according to WO 01/96713, to be a ring of vanes forming variable orientation nozzles. Therefore, the guide grid has an axial boundary of a blade space forming blade bearing ring, on each of which an associated shaft a plurality of adjustable around its shaft blades is mounted in the so-limited blade space around the turbine rotor, the exhaust so over the blades in an adjustable amount can be fed. At the end of the blade space opposite the blade bearing ring, a further ring (TG) is provided for axially limiting it. Furthermore, the invention relates to such a trained blade bearing ring. In the context of the present description, "turbocharger" is also understood as meaning similar turbomachines, such as secondary air pumps.
Ein derartiger Turbolader und ein derartiger Schaufellagerring ist beispielsweise aus der EP-A-0 226 444, bzw der DE-A-3 516 738, 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 has become known, for example, from EP-A-0 226 444 or DE-A-3 516 738. The axial dimension of the blade space is secured by spacer spacers, which must be inserted screwed into the blade bearing ring, which of course is a relatively complex operation. In addition, there are the relatively high costs of installation.
Der Erfindung liegt die Aufgabe zugrunde, die Herstellungkosten eines Turboladers bzw. eines Schaufellagerringes der eingangs genannten Art zu verringem, 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 has for its object to reduce the production cost of a turbocharger or a blade bearing ring of the type mentioned, and this is done according to the invention in that at least one of the two rings circumferentially distributed spacers integrally formed by the axial distance between the two rings is secure. As a result, not only the stated object is surprisingly achieved, but also - as is apparent from the following detailed description of the drawings - the precision and reliability increases during 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 whether the spacers sit on one or the other ring or alternately on one or the other ring or each half a spacer the one ring is opposite to half a spacer of the other ring. However, it is preferred if the spacers are formed on the vane bearing ring, in particular cast, because the other ring will generally be part of a larger portion of the housing to which a spacer is more difficult to attach.
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 are avoided. When using a precision casting method and the tolerance range can be reduced, so that this production brings greater accuracy. Above all, one is also constructive free, if necessary to choose an aerodynamically more favorable shape instead of the cylindrical shape of a pin. This can preferably be done so that the spacers themselves have a blade shape, which shape is preferably oriented approximately tangentially.
Weitere Einzelheiten der Erfindung ergeben sich aus der nachfolgenden Beschreibung eines in der Zeichnung schematisch dargestellten, bevorzugten Ausführungsbeispieles. 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.
- 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.
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
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.In order to control the movement or the position of the guide vanes 7, an
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
Um daher diesen Schaufelraum 13 bzw. den Abstand des Schaufellagerringes 6 vom gegenüberliegenden Lagerring 15 zu sichem, 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
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
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 Dehnungskëffizienten unterschiedlich wären. Dies alles wird - zur Erhöhung der Präzision und Verläßlichkeit im Betrieb - durch die Erfindung vermieden.Therefore, when hot exhaust gas flows via the supply channel 9 (or more feed channels) into the
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
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 provide at least a portion of the
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
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
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 production of the spacers with the
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 Abstandhaltetn 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; For example, it can also be applied to turbochargers with more than one
Claims (10)
- Turbocharger which comprises the following:a turbine housing (2) having at least one feed channel (9) for exhaust gas, in which at least one turbine rotor (4) is rotatably mounted, and to which the exhaust gas can be fed via a rotary vane system of variable turbine geometry which surrounds the turbine rotor (4) radially on the outside, which rotary vane system hasan annular guide conduit (6) on which, in each case on an associated shaft (8), a multiplicity of blades (7) adjustable around their shaft (8) is mounted in a limited blade space (13) around the turbine rotor (4), and to which exhaust gas can be fed via the blades (7) in an adjustable amount, which annular guide conduit (6) forms an axial limit of a blade space (13), and havinga further ring (15) which is axially opposite the annular guide conduit (6) and forms the other axial limit of the blade space (13),
characterized in that
at least one of the two rings (6, 15) has one-part spacers (16) formed on it and distributed in the circumferential direction, by means of which spacers the axial spacing of the two rings (6, 15) can be secured. - Turbocharger (1) according to Claim 1, characterized in that the spacers (16) are formed on the annular guide conduit.
- Turbocharger (1) according to Claim 1 or 2, characterized in that the spacers (16) are also cast on the respective cast ring (6 or 15).
- Turbocharger (1) according to any of the preceding Claims, characterized in that the spacers (16) are arranged on the circumferential edge of the respective rings (6 or 15).
- Turbocharger (1) according to any of the preceding Claims, characterized in that a surface (19) receding from the blade space (13) in the axial direction is provided along the circumferential edge of the respective ring (6 or 15), in particular of the annular guide conduit.
- Turbocharger (1) according to any of the preceding Claims, characterized in that the spacers (16) themselves have an elongated shape, preferably a blade shape, which shape is expediently oriented approximately tangentially.
- Turbocharger (1) according to any of the preceding Claims, characterized in that in each case a hole (18) for connecting pins having a bearing part adjacent in each case, in particular for connection to the axially opposite bearing ring (15), passes through at least some of the spacers (16).
- Annular guide conduit (6) for a turbocharger (1) according to any of the preceding Claims, comprising holes (20) distributed over its surface in the circumferential direction for the passage of the shafts (8) of guide vanes (7), characterized in that it has, moulded on in one part, axial spacers (16) distributed in the circumferential direction, in particular having an aerodynamic blade shape, for example which is produced in a casting process, in particular a precision casting process, and the spacers (16) are also cast.
- Annular guide conduit (6) according to Claim 8, characterized in that a surface (19) receding in the axial direction from the space for the blades (7) is provided along the radial circumferential edge of said annular guide conduit, on which surface the spacers (16) are preferably arranged.
- Annular guide conduit (6) according to Claim 8 or 9, characterized in that in each case a hole (18) for connecting pins having a bearing part adjacent in each case, in particular for connection to the axially opposite ring (15), passes through at least some of the spacers (16).
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP02018296A EP1394364B1 (en) | 2002-08-26 | 2002-08-26 | Turbocharger and annular guide conduit therefor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1394364A1 EP1394364A1 (en) | 2004-03-03 |
| EP1394364B1 true EP1394364B1 (en) | 2006-03-08 |
Family
ID=31197805
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP02018296A Expired - Lifetime EP1394364B1 (en) | 2002-08-26 | 2002-08-26 | Turbocharger and annular guide conduit therefor |
Country Status (4)
| Country | Link |
|---|---|
| US (2) | US7010915B2 (en) |
| EP (1) | EP1394364B1 (en) |
| JP (1) | JP2004084667A (en) |
| DE (1) | DE50205993D1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008014680A1 (en) | 2008-03-18 | 2010-09-23 | Continental Automotive Gmbh | Leitgitteranordnung an exhaust gas turbocharger, exhaust gas turbocharger and method for producing a Leitgitteranordnung |
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| US20040205966A1 (en) * | 2001-08-03 | 2004-10-21 | Shinjiroh Ohishi | Method of manufacturing turbine frame of vgs type turbo charger, turbine frame manufactured by the method, exhaust gas guide assembly of vgs type turbo charger using the turbine frame and vgs type turbo charger incorporating the exhaust gas guide assembly |
| EP1577503B1 (en) * | 2004-03-08 | 2006-07-19 | BorgWarner Inc. | Turbo machine, stator vanes and assembly ring |
| DE102004062564B4 (en) * | 2004-12-24 | 2008-08-07 | Mahle Ventiltrieb Gmbh | Blade bearing ring of a turbocharger of a motor vehicle internal combustion engine |
| DE102005012048A1 (en) * | 2005-03-08 | 2006-09-14 | Dr.Ing.H.C. F. Porsche Ag | Turbine housing of an exhaust gas turbocharger with adjustable turbine geometry |
| EP1790830B1 (en) * | 2005-11-25 | 2019-03-27 | BorgWarner, Inc. | Turbocharger guide vane and turbocharger |
| JP4847842B2 (en) * | 2006-10-25 | 2011-12-28 | アイシン高丘株式会社 | Turbine housing |
| DE102007029004A1 (en) | 2007-06-23 | 2008-12-24 | Ihi Charging Systems International Gmbh | Exhaust gas turbocharger for an internal combustion engine |
| DE112010004594T5 (en) * | 2009-11-27 | 2013-01-24 | Borgwarner Inc. | Turbocharger with variable turbine geometry |
| CN103492688B (en) * | 2011-05-10 | 2016-02-10 | 博格华纳公司 | There is the turbosupercharger of variable turbine geometry |
| KR20150102045A (en) | 2012-12-28 | 2015-09-04 | 보르그워너 인코퍼레이티드 | Asymmetric actuator pivot shaft bushing for vtg turbocharger |
| US9873515B2 (en) * | 2014-08-13 | 2018-01-23 | Hamilton Sundstrand Corporation | Turbine nozzle with relief cut |
| US10227889B2 (en) * | 2015-02-05 | 2019-03-12 | Garrett Transportation I Inc. | Variable geometry nozzle for partitioned volute |
| US9810238B2 (en) | 2015-03-09 | 2017-11-07 | Caterpillar Inc. | Turbocharger with turbine shroud |
| US9777747B2 (en) | 2015-03-09 | 2017-10-03 | Caterpillar Inc. | Turbocharger with dual-use mounting holes |
| US9822700B2 (en) | 2015-03-09 | 2017-11-21 | Caterpillar Inc. | Turbocharger with oil containment arrangement |
| US9683520B2 (en) | 2015-03-09 | 2017-06-20 | Caterpillar Inc. | Turbocharger and method |
| US9650913B2 (en) | 2015-03-09 | 2017-05-16 | Caterpillar Inc. | Turbocharger turbine containment structure |
| US10066639B2 (en) | 2015-03-09 | 2018-09-04 | Caterpillar Inc. | Compressor assembly having a vaneless space |
| US9903225B2 (en) | 2015-03-09 | 2018-02-27 | Caterpillar Inc. | Turbocharger with low carbon steel shaft |
| US9890788B2 (en) | 2015-03-09 | 2018-02-13 | Caterpillar Inc. | Turbocharger and method |
| US9638138B2 (en) | 2015-03-09 | 2017-05-02 | Caterpillar Inc. | Turbocharger and method |
| US10006341B2 (en) | 2015-03-09 | 2018-06-26 | Caterpillar Inc. | Compressor assembly having a diffuser ring with tabs |
| US9732633B2 (en) | 2015-03-09 | 2017-08-15 | Caterpillar Inc. | Turbocharger turbine assembly |
| US9752536B2 (en) | 2015-03-09 | 2017-09-05 | Caterpillar Inc. | Turbocharger and method |
| US9915172B2 (en) | 2015-03-09 | 2018-03-13 | Caterpillar Inc. | Turbocharger with bearing piloted compressor wheel |
| US9739238B2 (en) | 2015-03-09 | 2017-08-22 | Caterpillar Inc. | Turbocharger and method |
| US9879594B2 (en) | 2015-03-09 | 2018-01-30 | Caterpillar Inc. | Turbocharger turbine nozzle and containment structure |
| USD777212S1 (en) | 2015-06-20 | 2017-01-24 | General Electric Company | Nozzle ring |
| JP6908472B2 (en) * | 2017-08-31 | 2021-07-28 | 三菱重工コンプレッサ株式会社 | Centrifugal compressor |
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| EP1536103B1 (en) * | 2003-11-28 | 2013-09-04 | BorgWarner, Inc. | Turbo machine having inlet guide vanes and attachment arrangement therefor |
| DE102004057864A1 (en) * | 2004-11-30 | 2006-06-01 | Borgwarner Inc.(N.D.Ges.D.Staates Delaware), Auburn Hills | Exhaust gas turbocharger, distributor for an exhaust gas turbocharger and blade lever for a distributor |
-
2002
- 2002-08-26 DE DE50205993T patent/DE50205993D1/en not_active Expired - Lifetime
- 2002-08-26 EP EP02018296A patent/EP1394364B1/en not_active Expired - Lifetime
-
2003
- 2003-08-21 JP JP2003297285A patent/JP2004084667A/en active Pending
- 2003-08-26 US US10/649,477 patent/US7010915B2/en not_active Expired - Lifetime
-
2005
- 2005-11-09 US US11/270,738 patent/US7533529B2/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008014680A1 (en) | 2008-03-18 | 2010-09-23 | Continental Automotive Gmbh | Leitgitteranordnung an exhaust gas turbocharger, exhaust gas turbocharger and method for producing a Leitgitteranordnung |
Also Published As
| Publication number | Publication date |
|---|---|
| US20050005603A1 (en) | 2005-01-13 |
| EP1394364A1 (en) | 2004-03-03 |
| US20060053787A1 (en) | 2006-03-16 |
| JP2004084667A (en) | 2004-03-18 |
| DE50205993D1 (en) | 2006-05-04 |
| US7010915B2 (en) | 2006-03-14 |
| US7533529B2 (en) | 2009-05-19 |
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