EP1631736A1 - Exhaust gas turbine for an exhaust gas turbocharger - Google Patents

Exhaust gas turbine for an exhaust gas turbocharger

Info

Publication number
EP1631736A1
EP1631736A1 EP04729870A EP04729870A EP1631736A1 EP 1631736 A1 EP1631736 A1 EP 1631736A1 EP 04729870 A EP04729870 A EP 04729870A EP 04729870 A EP04729870 A EP 04729870A EP 1631736 A1 EP1631736 A1 EP 1631736A1
Authority
EP
European Patent Office
Prior art keywords
exhaust gas
gas turbine
turbine according
housing
base plate
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
EP04729870A
Other languages
German (de)
French (fr)
Other versions
EP1631736B1 (en
Inventor
Hermann Burmester
Akihiro Ohkita
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.)
IHI Charging Systems International GmbH
Original Assignee
IHI Charging Systems International GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by IHI Charging Systems International GmbH filed Critical IHI Charging Systems International GmbH
Publication of EP1631736A1 publication Critical patent/EP1631736A1/en
Application granted granted Critical
Publication of EP1631736B1 publication Critical patent/EP1631736B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the invention relates to an exhaust gas turbine for an exhaust gas turbocharger according to the preamble of claim 1.
  • an exhaust gas turbine for an exhaust gas turbocharger in which a spiral housing made of sheet metal is firmly connected on the one hand to a contour sleeve and on the other hand is clamped to a central bearing housing of the turbine via an intermediate ring by means of a tensioning band.
  • the intermediate ring can be formed in one piece with the contour sleeve or form a separate component.
  • the spiral housing is composed of two sheet metal shells, one of which forms the channel wall of the spiral channel which faces the diffuser, while the other shell forms the channel wall of the spiral channel which faces outwards.
  • the shell facing outwards can be surrounded by another shell with an air gap for thermal insulation.
  • the volute casing is designed to be complicated and is therefore complex to manufacture and assemble. Furthermore, it has a considerable weight and, in particular, does not allow any compensation for different thermal expansions of the individual housing parts to one another without significant thermal stresses occurring. Such thermal stresses can lead to malfunctions and result in premature wear.
  • the adjustment mechanism for the guide vanes, a bearing ring for the guide vanes, the contour sleeve and the guide vanes themselves can form a preassembled unit. From DE 100 22 052 AI a turbine housing for an exhaust gas turbocharger is known in which the spiral housing is double-walled.
  • the inner wall, which forms the spiral channel adjoins an inlet flange via an inlet funnel that opens tangentially into the spiral housing.
  • the outer wall is welded to the inlet flange, while the inner wall has a sliding fit to the outer wall and the inlet flange, so that thermal expansions in the direction of the inlet funnel between the inner and outer walls do not generate any thermal stresses.
  • the invention is based on the object of designing an exhaust gas turbine with a double-shell turbine housing made of sheet metal in such a way that the parts are simple and light and generate the lowest possible stresses under the influence of heat. It is solved according to the invention by the features of claim 1. Further advantageous embodiments result from the subclaims.
  • the spiral housing and the outer shell are cup-shaped.
  • the outer shell can be made largely cylindrical, while the spiral housing forms a spiral channel in accordance with the requirements of the desired flow conditions, the flow cross section of which tapers towards a diffuser.
  • the spiral housing and the outer shell are delimited on the end face facing the diffuser by parts of the diffuser which comprises a contour sleeve, a bearing ring and an intermediate ring.
  • One in cross Section V-shaped clamping ring clamps the outer shell over the intermediate ring with a central bearing housing of the exhaust gas turbocharger, while the inner spiral housing connects to part of the guide apparatus, for example to the intermediate ring or the bearing ring, via at least one axially flexible element.
  • the spiral housing can expand in the axial and radial direction under the influence of heat without exerting any significant stresses on the adjacent parts of the diffuser or on the outer shell.
  • the resilient element can be formed in a simple manner by a corrugated tube-like part of the spiral housing which is molded directly onto the spiral housing during manufacture and expediently has a smaller wall thickness than the rest of the spiral housing.
  • the resilient element consists of a sliding seat which is provided between a part of the diffuser and the spiral housing.
  • an intermediate ring or the bearing ring of the guide apparatus expediently has a shoulder, against which a preferably cylindrical connection of the volute housing rests and forms a sliding seat. The difference in diameter between a cylindrical connection and the radial boundary of the spiral channel is bridged by a radially directed, integrally formed transition.
  • connection point in addition to the sliding seat with a heat-resistant sealing element, e.g. in the form of a bead that is molded onto the connection of the volute casing and rests on the shoulder.
  • the guide apparatus comprises a contour sleeve and a bearing ring for adjustable guide vanes, which by Spacer bolts are connected to one another and form a flow channel which adjoins a spiral channel formed by the spiral housing.
  • the bearing ring is fastened to an intermediate ring which is braced on an outward-pointing outer flange together with a flange of the outer shell by a tension ring with an adjacent housing part of the exhaust gas turbocharger.
  • the bearing ring or the bearing ring and the intermediate ring form the end boundary of the spiral channel, so that the number of components required, the cost of materials and the weight are very low.
  • the radially inner part of the volute casing is expediently connected to the contour sleeve via a base plate.
  • the base plate which can be molded directly onto the spiral housing or is sealed by a separate seal, also serves to seal the spiral housing from the contour sleeve. This can be done on the one hand in the axial direction or in the radial direction by a correspondingly acting clamping ring which presses the base plate in the corresponding radial or axial direction against the contour sleeve.
  • an additional seal can be provided between the base plate and the contour sleeve.
  • FIG. 1 shows a half longitudinal section through an exhaust gas turbine without an impeller
  • FIG. 2 shows a variant of FIG. 1
  • FIG. 3 shows an end view of an exhaust gas turbine according to FIG.
  • FIG. 4 is a view in the direction of an arrow IV in FIG.
  • the exhaust gas turbine 10 comprises a contour sleeve 13, which is connected via spacer bolts 14 to a bearing ring 17 for adjustable guide vanes, not shown.
  • the spacer bolts 14, of which several are distributed over the circumference, have stops 15, against which the contour sleeve 13 or the bearing ring 17 abut and are held at the end of the spacer bolt 14 by a rivet head 16.
  • a flow channel 30 is formed, which leads to a radially inner impeller, not shown, and in which the guide vanes are arranged distributed over the circumference.
  • the bearing ring 17 is fastened to an intermediate ring 18, which has an outer conical flange 19 by means of a clamping ring 24 with a V-shaped cross section in a known manner is clamped against a central bearing housing, not shown, of the exhaust gas turbine. 1, the intermediate ring 18 is directly attached to the bearing ring 17 with its inner radial flange 20, in the embodiment according to FIG.
  • the bearing ring 17 is connected via a support plate ring 25 to a flange contour 38 of the bearing housing 37 (only indicated), in that an inner flange 26 of the support plate ring 25 is fastened to the bearing ring 17, and an outer flange 27 of the support plate ring 25 is braced by the clamping ring 24 with a suitable flange contour 38 of the bearing housing 37.
  • the support plate ring 25 is resilient and thus compensates for thermal expansion between the diffuser 13, 14, 17 and the housing of the turbocharger.
  • the flow channel 30 is surrounded radially on the outside by a spiral channel 12 through which exhaust gas is supplied.
  • its flow cross section narrows continuously from a tangentially opening inlet funnel 41 to the flow channel 30, which results in a spiral shape of the spiral housing 11, which essentially forms the spiral channel 12.
  • the narrowing of the cross section of the spiral channel 12 is indicated by a number of dashed sections of the spiral housing which form an angle to one another and were rotated into the plane of the drawing in FIGS. 1 and 2.
  • An outer shell 21 surrounds the spiral housing 11 and forms an air gap 22 with it for thermal insulation.
  • the outer shell 21 need not have a spiral shape.
  • it is expediently designed as a cylindrical pot, the conical flange 23 of which faces the intermediate ring 18 and is braced together with the latter (FIG. 1) and possibly with the support plate ring 25 (FIG. 2) by the clamping ring 24.
  • the spiral housing 11 also has the shape of a pot with an annular cross section, the radially outer housing wall having at its free end facing the bearing ring 17 a connection 34, with which it on a shoulder 33 of the intermediate ring 18 (FIG. 1) o -
  • the bearing ring 17 (Fig. 2) abuts, and forms a sliding seat 32.
  • the sliding seat 32 is expediently sealed by an additional seal, for example in the form of a bead 36 at the connection 34 of the spiral housing 11.
  • Other heat-resistant sealing elements can also be provided.
  • the sliding seat 32 enables the volute casing 11, which becomes very hot during operation, to expand both radially and axially without generating thermal stresses on the diffuser 13, 17 or the outer formwork 21.
  • the connection 34 can follow the outer contour of the spiral housing 11 in a spiral shape, the shoulder 33 being able to be formed accordingly, in part by a groove in the end face of the intermediate ring 18 or the bearing ring 17.
  • the shoulder is expediently cylindrical as shown, so that a transition 35 bridges the distance between the connection 34 and the spiral cross-sectional contour of the spiral housing 11.
  • the radially inner, spiral-shaped housing wall of the spiral housing 11 ends at a base plate 28 which is adapted in its outer contour to the radially inner, spiral-shaped housing wall and is expediently connected thereto, for example by welding, as a result of which a seal between the spiral housing 11 and the base plate 28 is also achieved.
  • the base plate 28 can, however, also be cylindrical in the outer region, but then has a spiral groove 31 for receiving the radially inner housing wall of the spiral housing 11.
  • the base plate te 28 can also be integrally formed in one piece in the form of a flange on the spiral housing 11. In all embodiments of the base plate 28, it is sealingly connected to the contour sleeve 13.
  • the seal between the base plate 28 and the contour sleeve 13 can be made axially or radially by being pressed against the contour sleeve 13 by a clamping element 29 in the form of a clamping ring with spring tongues 39 and tool eyelets 40.
  • the seal shown causes an axial seal.
  • a radial seal is conceivable in which a clamping ring comprising the base plate 28 presses the base plate 28 against the contour sleeve 13.
  • heat-resistant sealing means can be inserted between the components 13, 28, 11.

Landscapes

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

Abstract

The invention relates to an exhaust gas turbine (10) for an exhaust gas turbocharger, comprising a spiral housing (11), which is made from sheet metal and which surrounds a distributor (13, 17), and comprising a tangentially in-flowing inlet funnel (41), whereby a sheet metal outer shell (21) surrounds the spiral housing (11) with an air gap (22). The invention provides that the spiral housing (11) and the outer shell (21) are provided in the shape of a pot, and the faces oriented toward the distributor (13, 17) are delimited by portions of the distributor (13, 17) to which the spiral housing (11) adjoins via at least one axially flexible element (32).

Description

IHI Charging Systems International GmbHIHI Charging Systems International GmbH
Abgasturbine für einen AbgasturboladerExhaust gas turbine for an exhaust gas turbocharger
Die Erfindung betrifft eine Abgasturbine für einen Abgasturbolader nach dem Oberbegriff des Anspruchs 1.The invention relates to an exhaust gas turbine for an exhaust gas turbocharger according to the preamble of claim 1.
Aus der WO 02/06637 ist eine Abgasturbine für einen Abgasturbolader bekannt, bei der ein Spiralgehäuse aus Blech einerseits mit einer Konturhülse fest verbunden ist und andererseits über einen Zwischenring mittels eines Spannbandes mit einem zentralen Lagergehäuse der Turbine verspannt ist. Der Zwischenring kann nach einer Version der Abgasturbine einstückig mit der Konturhülse ausgebildet sein oder ein separates Bauteil bilden. Das Spiralgehäuse ist aus zwei Blechschalen zusammengesetzt, von denen eine die Kanalwand des Spiralkanals bildet, die dem Leitapparat zugewandt ist, während die andere Schale die Kanalwand des Spiralkanals bildet, die nach außen gewandt ist. Die nach außen gewandte Schale kann zur Wärmeisolierung von einer weiteren Schale mit einem Luftspalt umgeben sein. Das Spiralgehäuse ist kompliziert gestaltet und ist daher aufwändig in der Herstellung und Montage. Ferner besitzt es ein erhebliches Gewicht und erlaubt insbesondere keinen Ausgleich unterschiedlicher Wärmeausdehnungen der einzelnen Gehäuseteile zueinander, ohne dass erhebliche Wärmespannungen auftreten. Derartige Wärmespannungen können zu Funktionsstörungen führen und haben einen vorzeitigen Verschleiß zur Folge. Der Verstellmechanismus für die Leitschaufeln, ein Lagerring für die Leitschaufeln, die Konturhülse sowie die Leitschau eln selbst können eine vormontierbare Baueinheit bilden. Aus der DE 100 22 052 AI ist ein Turbinengehäuse für einen Abgasturbolader bekannt, bei dem das Spiralgehäuse doppelwandig ausgeführt ist. Die innere Wand, die den Spiralkanal bildet, schließt sich über einen Einlasstrichter, der tangential in das Spiralgehäuse einmündet, an einen Einlassflansch an. Die äußere Wand ist mit dem Einlassflansch verschweißt, während die innere Wand zur äußeren Wand und zum Einlassflansch einen Schiebesitz aufweist, so dass Wärmedehnungen in Richtung des Einlasstrichters zwischen der inneren und äußeren Wand keine Wärmespannungen erzeugen. Prinzipbedingt ist jedoch kein Ausgleich der inneren und äußeren Wand des Spiralgehäuses in axialer Richtung der Abgasturbine vorgesehen, so dass insbesondere bei hohen Temperaturunterschieden zwischen der Innen- und Außenschale auf Grund starker Spannungen eine Dauerhaltbarkeit nicht mehr gewährleistet werden kann.From WO 02/06637 an exhaust gas turbine for an exhaust gas turbocharger is known, in which a spiral housing made of sheet metal is firmly connected on the one hand to a contour sleeve and on the other hand is clamped to a central bearing housing of the turbine via an intermediate ring by means of a tensioning band. According to one version of the exhaust gas turbine, the intermediate ring can be formed in one piece with the contour sleeve or form a separate component. The spiral housing is composed of two sheet metal shells, one of which forms the channel wall of the spiral channel which faces the diffuser, while the other shell forms the channel wall of the spiral channel which faces outwards. The shell facing outwards can be surrounded by another shell with an air gap for thermal insulation. The volute casing is designed to be complicated and is therefore complex to manufacture and assemble. Furthermore, it has a considerable weight and, in particular, does not allow any compensation for different thermal expansions of the individual housing parts to one another without significant thermal stresses occurring. Such thermal stresses can lead to malfunctions and result in premature wear. The adjustment mechanism for the guide vanes, a bearing ring for the guide vanes, the contour sleeve and the guide vanes themselves can form a preassembled unit. From DE 100 22 052 AI a turbine housing for an exhaust gas turbocharger is known in which the spiral housing is double-walled. The inner wall, which forms the spiral channel, adjoins an inlet flange via an inlet funnel that opens tangentially into the spiral housing. The outer wall is welded to the inlet flange, while the inner wall has a sliding fit to the outer wall and the inlet flange, so that thermal expansions in the direction of the inlet funnel between the inner and outer walls do not generate any thermal stresses. In principle, however, there is no compensation for the inner and outer wall of the volute casing in the axial direction of the exhaust gas turbine, so that durability can no longer be guaranteed, particularly in the case of high temperature differences between the inner and outer shells, due to strong stresses.
Der Erfindung liegt die Aufgabe zu Grunde, eine Abgasturbine mit einem zweischaligen Turbinengehäuse aus Blech so zu gestalten, dass die Teile einfach und leicht sind und unter Wärmeeinfluss möglichst geringe Spannungen erzeugen. Sie wird gemäß der Erfindung durch die Merkmale des Anspruchs 1 gelöst. Weitere vorteilhafte Ausgestaltungen ergeben sich aus den Unteransprüchen.The invention is based on the object of designing an exhaust gas turbine with a double-shell turbine housing made of sheet metal in such a way that the parts are simple and light and generate the lowest possible stresses under the influence of heat. It is solved according to the invention by the features of claim 1. Further advantageous embodiments result from the subclaims.
Nach der Erfindung sind das Spiralgehäuse und die äußere Schale topfförmig ausgebildet. Dabei kann die äußere Schale weitgehend zylindrisch ausgeführt werden, während das Spiralgehäuse entsprechend den Vorgaben der gewünschten Strömungsverhältnisse einen Spiralkanal bildet, dessen Strömungsquerschnitt sich zu einem Leitapparat hin verjüngt. Das Spiralgehäuse und die äußere Schale werden an der dem Leitapparat zugewandten Stirnseite von Teilen des Leitapparats begrenzt, der eine Konturhülse, einen Lagerring und einen Zwischenring umfasst. Ein im Quer- schnitt v-förmiger Spannring verspannt die äußere Schale über den Zwischenring mit einem zentralen Lagergehäuse des Abgasturboladers, während das innere Spiralgehäuse ü- ber mindestens ein axial nachgiebiges Element sich an ein Teil des Leitapparats, z.B. an den Zwischenring oder den Lagerring anschließt. Dadurch kann das Spiralgehäuse sich unter Wärmeeinfluss in axialer und radialer Richtung ausdehnen, ohne nennenswerte Spannungen auf die angrenzenden Teile des Leitapparates oder die äußere Schale auszuüben.According to the invention, the spiral housing and the outer shell are cup-shaped. The outer shell can be made largely cylindrical, while the spiral housing forms a spiral channel in accordance with the requirements of the desired flow conditions, the flow cross section of which tapers towards a diffuser. The spiral housing and the outer shell are delimited on the end face facing the diffuser by parts of the diffuser which comprises a contour sleeve, a bearing ring and an intermediate ring. One in cross Section V-shaped clamping ring clamps the outer shell over the intermediate ring with a central bearing housing of the exhaust gas turbocharger, while the inner spiral housing connects to part of the guide apparatus, for example to the intermediate ring or the bearing ring, via at least one axially flexible element. As a result, the spiral housing can expand in the axial and radial direction under the influence of heat without exerting any significant stresses on the adjacent parts of the diffuser or on the outer shell.
Das nachgiebige Element kann in einfacher Weise durch ein wellrohrartiges Teil des Spiralgehäuses gebildet werden, das während der Herstellung des Spiralgehäuses unmittelbar an dieses angeformt wird und zweckmäßigerweise eine geringere Wandstärke aufweist als das übrige Spiralgehäuse. Eine weitere Möglichkeit besteht nach einer Ausgestaltung der Erfindung darin, dass das nachgiebige Element aus einem Schiebesitz besteht, der zwischen einem Teil des Leitapparats und dem Spiralgehäuse vorgesehen ist. Hierzu besitzt zweckmäßigerweise ein Zwischenring oder der Lagerring des Leitapparats eine Schulter, an dem ein vorzugsweise zylindrischer Anschluss des Spiralgehäuses anliegt und einen Schiebesitz bildet. Die Durchmesserdifferenz zwischen einem zylindrischen Anschluss und der radialen Begrenzung des Spiralkanals wird durch einen radial gerichteten, angeformten Übergang überbrückt.The resilient element can be formed in a simple manner by a corrugated tube-like part of the spiral housing which is molded directly onto the spiral housing during manufacture and expediently has a smaller wall thickness than the rest of the spiral housing. Another possibility according to one embodiment of the invention is that the resilient element consists of a sliding seat which is provided between a part of the diffuser and the spiral housing. For this purpose, an intermediate ring or the bearing ring of the guide apparatus expediently has a shoulder, against which a preferably cylindrical connection of the volute housing rests and forms a sliding seat. The difference in diameter between a cylindrical connection and the radial boundary of the spiral channel is bridged by a radially directed, integrally formed transition.
Ferner ist es zweckmäßig, die Anschlussstelle zusätzlich zu dem Schiebesitz durch ein hitzebeständiges Dichtelement abzudichten, z.B. in Form einer Sicke, die an den Anschluss des Spiralgehäuses angeformt ist und an der Schulter anliegt.It is also expedient to seal the connection point in addition to the sliding seat with a heat-resistant sealing element, e.g. in the form of a bead that is molded onto the connection of the volute casing and rests on the shoulder.
Besondere Vorteile ergeben sich bei einer Abgasturbine, bei der der Leitapparat eine Konturhülse und einen Lagerring für verstellbare Leitschaufeln umfasst, die durch Distanzbolzen miteinander verbunden sind und einen Strömungskanal bilden, der sich an einen durch das Spiralgehäuse gebildeten Spiralkanal anschließt. Der Lagerring ist an einem Zwischenring befestigt, der an einem nach außen weisenden äußeren Flansch zusammen mit einem Flansch der äußeren Schale durch einen Spannring mit einem angrenzenden Gehäuseteil des Abgasturboladers verspannt ist. Hierbei bilden der Lagerring bzw. der Lagerring und der Zwischenring die stirnseitige Begrenzung des Spiralkanals, so dass die Anzahl der erforderlichen Bauelemente, der Materialaufwand und das Gewicht sehr gering sind. Somit ergibt sich eine sehr leichte Turbinenkonstruktion, bei der das Turbinengehäuse eine geringe Masse und Wärmekapazität besitzt, so dass nach dem Start sehr schnell die optimale Betriebstemperatur erreicht wird. Ferner kann es vorteilhaft sein, dass der Zwischenring ü- ber einen elastisch nachgiebigen Stützblechring mit dem Lagerring verbunden ist. Dadurch wirken sich Wärmedehnungen des Leitapparats nicht durch Wärmespannungen auf den Verstellmechanismus der Leitschaufeln und auf das Lagergehäuse aus .Particular advantages result in an exhaust gas turbine in which the guide apparatus comprises a contour sleeve and a bearing ring for adjustable guide vanes, which by Spacer bolts are connected to one another and form a flow channel which adjoins a spiral channel formed by the spiral housing. The bearing ring is fastened to an intermediate ring which is braced on an outward-pointing outer flange together with a flange of the outer shell by a tension ring with an adjacent housing part of the exhaust gas turbocharger. Here, the bearing ring or the bearing ring and the intermediate ring form the end boundary of the spiral channel, so that the number of components required, the cost of materials and the weight are very low. This results in a very light turbine construction, in which the turbine housing has a low mass and heat capacity, so that the optimum operating temperature is reached very quickly after starting. Furthermore, it can be advantageous for the intermediate ring to be connected to the bearing ring by means of an elastically flexible support plate ring. As a result, thermal expansion of the guide device does not affect the adjustment mechanism of the guide vanes and the bearing housing through thermal stresses.
Der radial innere Teil des Spiralgehäuses ist zweckmäßigerweise über eine Grundplatte mit der Konturhülse verbunden. Die Grundplatte, die unmittelbar an das Spiralgehäuse angeformt sein kann oder durch eine separate Dichtung abgedichtet wird, dient gleichzeitig zum Abdichten des Spiralgehäuses gegenüber der Konturhülse. Dies kann zum einen in axialer Richtung oder in radialer Richtung durch einen entsprechend wirkenden Spannring erfolgen, der die Grundplatte in der entsprechenden radialen oder axialen Richtung gegen die Konturhülse presst. Hierbei kann zwischen der Grundplatte und der Konturhülse eine zusätzliche Dichtung vorgesehen werden. Weitere Vorteile ergeben sich aus der folgenden Zeichnungsbeschreibung. In der Zeichnung sind Ausführungsbeispiele der Erfindung dargestellt. Die Zeichnung, die Beschreibung und die Ansprüche enthalten zahlreiche Merkmale in Kombination. Der Fachmann wird die Merkmale zweckmäßigerweise auch einzeln betrachten und zu sinnvollen weiteren Kombinationen zusammenfassen.The radially inner part of the volute casing is expediently connected to the contour sleeve via a base plate. The base plate, which can be molded directly onto the spiral housing or is sealed by a separate seal, also serves to seal the spiral housing from the contour sleeve. This can be done on the one hand in the axial direction or in the radial direction by a correspondingly acting clamping ring which presses the base plate in the corresponding radial or axial direction against the contour sleeve. Here, an additional seal can be provided between the base plate and the contour sleeve. Further advantages result from the following description of the drawing. Exemplary embodiments of the invention are shown in the drawing. The drawing, the description and the claims contain numerous features in combination. The person skilled in the art will expediently also consider the features individually and combine them into useful further combinations.
Dabei zeigen:Show:
Fig. 1 einen halben Längsschnitt durch eine Abgasturbine ohne Laufrad, Fig. 2 eine Variante zu Fig. 1, Fig. 3 stirnseitige Ansicht einer Abgasturbine nach Fig.1 shows a half longitudinal section through an exhaust gas turbine without an impeller, FIG. 2 shows a variant of FIG. 1, FIG. 3 shows an end view of an exhaust gas turbine according to FIG.
1 in einem kleineren Maßstab ohne äußere Schale und Fig. 4 eine Ansicht in Richtung eines Pfeils IV in Fig.1 on a smaller scale without an outer shell, and FIG. 4 is a view in the direction of an arrow IV in FIG.
3.Third
Von einer Abgasturbine 10 sind nur die für die Erfindung wesentlichen Teile dargestellt. Die Abgasturbine 10 um- fasst eine Konturhülse 13, die über Distanzbolzen 14 mit einem Lagerring 17 für nicht dargestellte, verstellbare Leitschaufeln verbunden ist. Die Distanzbolzen 14, von denen mehrere auf dem Umfang verteilt sind, besitzen Anschläge 15, an denen die Konturhülse 13 bzw. der Lagerring 17 anliegen und durch einen Nietkopf 16 am Ende des Distanzbolzens 14 gehalten sind. Zwischen der Konturhülse 13 und dem Lagerring 17 wird ein Strömungskanal 30 gebildet, der zu einem radial innen liegenden, nicht dargestellten Laufrad führt und in dem die Leitschaufeln über den Umfang verteilt angeordnet sind.Of an exhaust gas turbine 10, only the parts essential to the invention are shown. The exhaust gas turbine 10 comprises a contour sleeve 13, which is connected via spacer bolts 14 to a bearing ring 17 for adjustable guide vanes, not shown. The spacer bolts 14, of which several are distributed over the circumference, have stops 15, against which the contour sleeve 13 or the bearing ring 17 abut and are held at the end of the spacer bolt 14 by a rivet head 16. Between the contour sleeve 13 and the bearing ring 17, a flow channel 30 is formed, which leads to a radially inner impeller, not shown, and in which the guide vanes are arranged distributed over the circumference.
Der Lagerring 17 ist an einem Zwischenring 18 befestigt, der mit einem äußeren konischen Flansch 19 durch einen im Querschnitt v-förmigen Spannring 24 in bekannter Weise gegen ein nicht dargestelltes zentrales Lagergehäuse der Abgasturbine verspannt ist. Während bei der Ausführung nach Fig. 1 der Zwischenring 18 unmittelbar mit seinem inneren radialen Flansch 20 am Lagerring 17 befestigt ist, ist bei der Ausführung nach Fig. 2 der Lagerring 17 über einen Stützblechring 25 mit einer Flanschkontur 38 des nur angedeuteten Lagergehäuses 37 verbunden, indem ein innerer Flansch 26 des Stützblechrings 25 am Lagerring 17 befestigt ist, und ein äußerer Flansch 27 des Stützblechrings 25 durch den Spannring 24 mit einer geeigneten Flanschkontur 38 des Lagergehäuses 37 verspannt ist. Der Stützblechring 25 ist elastisch nachgiebig und gleicht somit Wärmedehnungen zwischen dem Leitapparat 13, 14, 17 und dem Gehäuse des Turboladers aus.The bearing ring 17 is fastened to an intermediate ring 18, which has an outer conical flange 19 by means of a clamping ring 24 with a V-shaped cross section in a known manner is clamped against a central bearing housing, not shown, of the exhaust gas turbine. 1, the intermediate ring 18 is directly attached to the bearing ring 17 with its inner radial flange 20, in the embodiment according to FIG. 2 the bearing ring 17 is connected via a support plate ring 25 to a flange contour 38 of the bearing housing 37 (only indicated), in that an inner flange 26 of the support plate ring 25 is fastened to the bearing ring 17, and an outer flange 27 of the support plate ring 25 is braced by the clamping ring 24 with a suitable flange contour 38 of the bearing housing 37. The support plate ring 25 is resilient and thus compensates for thermal expansion between the diffuser 13, 14, 17 and the housing of the turbocharger.
Der Strömungskanal 30 wird radial außen von einem Spiralkanal 12 umgeben, durch den Abgas zugeführt wird. Zur Beschleunigung der Abgasströmung im Spiralkanal 12 verengt sich sein Strömungsquerschnitt kontinuierlich von einem tangential einmündenden Einlasstrichter 41 zum Strömungskanal 30 hin, wodurch sich eine spiralförmige Gestalt des Spiralgehäuses 11 ergibt, das im Wesentlichen den Spiralkanal 12 bildet. Die Querschnittverengung des Spiralkanals 12 ist durch mehrere gestrichelt eingezeichnete Schnitte des Spiralgehäuses angedeutet, die einen Winkel zueinander bilden und in der Fig. 1 und 2 in die Zeichenebene gedreht wurden.The flow channel 30 is surrounded radially on the outside by a spiral channel 12 through which exhaust gas is supplied. In order to accelerate the exhaust gas flow in the spiral channel 12, its flow cross section narrows continuously from a tangentially opening inlet funnel 41 to the flow channel 30, which results in a spiral shape of the spiral housing 11, which essentially forms the spiral channel 12. The narrowing of the cross section of the spiral channel 12 is indicated by a number of dashed sections of the spiral housing which form an angle to one another and were rotated into the plane of the drawing in FIGS. 1 and 2.
Eine äußere Schale 21 umgibt das Spiralgehäuse 11 und bildet mit diesem zur Wärmeisolation einen Luftspalt 22. Die äußere Schale 21 braucht keine Spiralform zu besitzen. Sie ist aus fertigungstechnischen Gründen zweckmäßigerweise als zylindrischer Topf ausgebildet, dessen konischer Flansch 23 dem Zwischenring 18 zugewandt und mit diesem (Fig. 1) und ggf. mit dem Stützblechring 25 (Fig. 2) zusammen durch den Spannring 24 verspannt ist. Das Spiralgehäuse 11 hat ebenfalls die Form eines Topfes mit einem ringförmigen Querschnitt, wobei die radial außen liegende Gehäusewand an ihrem freien, dem Lagerring 17 zugewandten Ende einen Anschluss 34 aufweist, mit dem sie an einer Schulter 33 des Zwischenrings 18 (Fig. 1) o- der des Lagerrings 17 (Fig. 2) anliegt, und einen Schiebesitz 32 bildet. Der Schiebesitz 32 wird zweckmäßigerweise durch eine zusätzliche Dichtung, z.B. in Form einer Sicke 36 am Anschluss 34 des Spiralgehäuses 11 abgedichtet. Es können auch andere hitzebeständige Dichtelemente vorgesehen werden.An outer shell 21 surrounds the spiral housing 11 and forms an air gap 22 with it for thermal insulation. The outer shell 21 need not have a spiral shape. For manufacturing reasons, it is expediently designed as a cylindrical pot, the conical flange 23 of which faces the intermediate ring 18 and is braced together with the latter (FIG. 1) and possibly with the support plate ring 25 (FIG. 2) by the clamping ring 24. The spiral housing 11 also has the shape of a pot with an annular cross section, the radially outer housing wall having at its free end facing the bearing ring 17 a connection 34, with which it on a shoulder 33 of the intermediate ring 18 (FIG. 1) o - The bearing ring 17 (Fig. 2) abuts, and forms a sliding seat 32. The sliding seat 32 is expediently sealed by an additional seal, for example in the form of a bead 36 at the connection 34 of the spiral housing 11. Other heat-resistant sealing elements can also be provided.
Der Schiebesitz 32 ermöglicht dem Spiralgehäuse 11, das im Betrieb sehr heiß wird, sowohl radial auch axial sich frei auszudehnen, ohne Wärmespannungen am Leitapparat 13, 17 oder der äußeren Schalung 21 zu erzeugen. Der Anschluss 34 kann der äußeren Kontur des Spiralgehäuses 11 folgend spiralförmig verlaufen, wobei die Schulter 33 entsprechend, zum Teil durch eine Nut in der Stirnseite des Zwischenrings 18 bzw. des Lagerrings 17 gebildet werden kann. Zweckmäßigerweise ist die Schulter wie dargestellt kreiszylindrisch, so dass ein Übergang 35 den Abstand zwischen dem Anschluss 34 und der spiralförmigen Querschnittkontur des Spiralgehäuses 11 überbrückt.The sliding seat 32 enables the volute casing 11, which becomes very hot during operation, to expand both radially and axially without generating thermal stresses on the diffuser 13, 17 or the outer formwork 21. The connection 34 can follow the outer contour of the spiral housing 11 in a spiral shape, the shoulder 33 being able to be formed accordingly, in part by a groove in the end face of the intermediate ring 18 or the bearing ring 17. The shoulder is expediently cylindrical as shown, so that a transition 35 bridges the distance between the connection 34 and the spiral cross-sectional contour of the spiral housing 11.
Die radial innen liegende, spiralförmige Gehäusewand des Spiralgehäuses 11 endet an einer in ihrer Außenkontur der radial inneren, spiralförmigen Gehäusewand angepassten Grundplatte 28 und ist zweckmäßigerweise mit dieser beispielsweise durch Schweißen verbunden, wodurch auch eine Abdichtung zwischen dem Spiralgehäuse 11 und der Grundplatte 28 erreicht wird. Die Grundplatte 28 kann aber auch im Außenbereich zylindrisch ausgeführt sein, weist dann aber eine Spiralnut 31 zur Aufnahme der radial inneren Gehäusewand des Spiralgehäuses 11 auf. Die Grundplat- te 28 kann aber auch einstückig in Form eines Flansches an das Spiralgehäuse 11 unmittelbar angeformt sein. In allen Ausführungsarten der Grundplatte 28 ist diese dichtend mit der Konturhülse 13 verbunden.The radially inner, spiral-shaped housing wall of the spiral housing 11 ends at a base plate 28 which is adapted in its outer contour to the radially inner, spiral-shaped housing wall and is expediently connected thereto, for example by welding, as a result of which a seal between the spiral housing 11 and the base plate 28 is also achieved. The base plate 28 can, however, also be cylindrical in the outer region, but then has a spiral groove 31 for receiving the radially inner housing wall of the spiral housing 11. The base plate te 28 can also be integrally formed in one piece in the form of a flange on the spiral housing 11. In all embodiments of the base plate 28, it is sealingly connected to the contour sleeve 13.
Die Abdichtung zwischen der Grundplatte 28 und der Konturhülse 13 kann axial oder radial erfolgen, indem sie durch ein Spannelement 29 in Form eines Spannrings mit Federzungen 39 und Werkzeugösen 40 gegen die Konturhülse 13 gedrückt wird. Die dargestellte Abdichtung bewirkt eine axiale Abdichtung. Es ist jedoch eine radiale Abdichtung denkbar, bei der ein die Grundplatte 28 umfassender Spannring die Grundplatte 28 gegen die Konturhülse 13 drückt. Zur Verstärkung der Dichtwirkung können zwischen den Bauelementen 13, 28, 11 hitzebeständige Dichtungsmittel eingefügt werden. The seal between the base plate 28 and the contour sleeve 13 can be made axially or radially by being pressed against the contour sleeve 13 by a clamping element 29 in the form of a clamping ring with spring tongues 39 and tool eyelets 40. The seal shown causes an axial seal. However, a radial seal is conceivable in which a clamping ring comprising the base plate 28 presses the base plate 28 against the contour sleeve 13. To increase the sealing effect, heat-resistant sealing means can be inserted between the components 13, 28, 11.

Claims

IHI Charging Systems International GmbHPatentansprüche IHI Charging Systems International GmbH patent claims
1. Abgasturbine (10) für einen Abgasturbolader mit einem aus Blech gefertigten Spiralgehäuse (11), das einen Leitapparat (13, 17, 18) umgibt und einen tangential einmündenden Einlasstrichter (41) aufweist, wobei eine äußere Schale (21) aus Blech das Spiralgehäuse (11) mit einem Luftspalt (22) umgibt, d a d u r c h g e k e n n z e i c h n e t , dass das Spiralgehäuse (11) und die äußere Schale (21) topfförmig ausgebildet sind und die dem Leitapparat (13, 17) zugewandten Stirnseiten von Teilen des Leitapparats (13, 17, 18) begrenzt sind, an die sich das Spiralgehäuse (11) über mindestens ein axial nachgiebiges Element (32) anschließt.1. exhaust gas turbine (10) for an exhaust gas turbocharger with a sheet metal spiral housing (11) surrounding a diffuser (13, 17, 18) and a tangentially opening inlet funnel (41), wherein an outer shell (21) made of sheet metal Surrounding the spiral housing (11) with an air gap (22), characterized in that the spiral housing (11) and the outer shell (21) are cup-shaped and the end faces of the guide apparatus (13, 17) facing parts of the guide apparatus (13, 17, 18) are limited, to which the spiral housing (11) is connected via at least one axially flexible element (32).
2. Abgasturbine nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t , dass das nachgiebige Element durch einen wellrohrartigen Teil des Spiralgehäuses (11) gebildet ist.2. Exhaust gas turbine according to claim 1, so that the resilient element is formed by a corrugated tube-like part of the volute casing (11).
3. Abgasturbine nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t , dass das nachgiebige Element ein Schiebesitz (32) zwischen einem Teil des Leitapparats (13, 17, 18) und dem Spiralgehäuse (11) ist.3. Exhaust gas turbine according to claim 1, so that the resilient element is a sliding seat (32) between part of the guide apparatus (13, 17, 18) and the volute casing (11).
4. Abgasturbine nach Anspruch 3, d a d u r c h g e k e n n z e i c h n e t , dass das Spiralgehäuse (11) an seinem stirnseitigen Ende, das dem Leitapparat (13, 17, 18) zugewandt ist, einen vorzugsweise zylindrischen Anschluss (34) besitzt, der an einer entsprechend ausgebildeten Schulter (33) eines Teils des Leitapparats (13, 17, 18) anliegt und den Schiebesitz (32) bildet.4. Exhaust gas turbine according to claim 3, characterized in that the spiral housing (11) on its end face End, which faces the guide device (13, 17, 18), has a preferably cylindrical connection (34) which bears against a correspondingly designed shoulder (33) of a part of the guide device (13, 17, 18) and the sliding seat (32 ) forms.
5. Abgasturbine nach Anspruch 4, d a d u r c h g e k e n n z e i c h n e t , dass an dem Schiebesitz (32) ein Dichtelement (36) vorgesehen ist.5. Exhaust gas turbine according to claim 4, that a sealing element (36) is provided on the sliding seat (32).
6. Abgasturbine nach Anspruch 5, d a d u r c h g e k e n n z e i c h n e t , dass das Dichtelement (36) eine Sicke ist, die an den Anschluss (34) angeformt ist und an der Schulter (33) anliegt .6. Exhaust gas turbine according to claim 5, so that the sealing element (36) is a bead which is integrally formed on the connection (34) and rests on the shoulder (33).
7. Abgasturbine nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , dass der Leitapparat eine Konturhülse (13) und einen Lagerring (17) für verstellbare Leitschaufeln um- fasst, die durch Distanzbolzen (14) miteinander verbunden sind und einen Strömungskanal (30) bilden, der sich an einen durch das Spiralgehäuse (11) gebildeten Spiralkanal (12) anschließt, wobei der Lagerring (17) an einem Zwischenring (18) befestigt ist, der an einem nach außen weisenden, äußeren Flansch (19) zusammen mit einem Flansch (23) der äußeren Schale (21) durch einen Spannring (24) mit einem angrenzenden Gehäuseteil des Abgasturboladers verspannt ist.7. Exhaust gas turbine according to one of the preceding claims, characterized in that the guide apparatus comprises a contour sleeve (13) and a bearing ring (17) for adjustable guide vanes which are connected to one another by spacer bolts (14) and form a flow channel (30) which adjoins a spiral channel (12) formed by the spiral housing (11), the bearing ring (17) being fastened to an intermediate ring (18) which is connected to an outwardly facing outer flange (19) together with a flange (23) the outer shell (21) is clamped by a clamping ring (24) to an adjacent housing part of the exhaust gas turbocharger.
8. Abgasturbine nach Anspruch 7, d a d u r c h g e k e n n z e i c h n e t , dass der Zwischenring (18) die Schulter (33) für den Anschluss (34) aufweist. 8. Exhaust gas turbine according to claim 7, characterized in that the intermediate ring (18) has the shoulder (33) for the connection (34).
9. Abgasturbine nach Anspruch 7, d a d u r c h g e k e n n z e i c h n e t , dass das Lagergehäuse (37) über einen Stützblechring (25) mit dem Lagerring (17) verbunden ist, der die Schulter (33) für den Anschluss (34) aufweist und den Schiebesitz (32) bildet.9. Exhaust gas turbine according to claim 7, characterized in that the bearing housing (37) is connected via a support plate ring (25) to the bearing ring (17) which has the shoulder (33) for the connection (34) and forms the sliding seat (32) ,
10. Abgasturbine nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , dass der radial innere Teil des Spiralgehäuses (11) über eine Grundplatte (28) mit der Konturhülse (13) verbunden ist.10. Exhaust gas turbine according to one of the preceding claims, that the radial inner part of the volute casing (11) is connected to the contour sleeve (13) via a base plate (28).
11. Abgasturbine nach Anspruch 10, d a d u r c h g e k e n n z e i c h n e t , dass die Grundplatte (28) an der Konturhülse (13) angeformt ist.11. The exhaust gas turbine according to claim 10, so that the base plate (28) is integrally formed on the contour sleeve (13).
12. Abgasturbine nach Anspruch 10 oder 11, d a d u r c h g e k e n n z e i c h n e t , dass die Grundplatte (28) zum Abdichten zwischen dem Spiralgehäuse (11) und der Konturhülse (13) dient.12. Exhaust gas turbine according to claim 10 or 11, so that the base plate (28) is used for sealing between the spiral housing (11) and the contour sleeve (13).
13. Abgasturbine nach Anspruch 12, d a d u r c h g e k e n n z e i c h n e t , dass die Grundplatte (28) durch ein Spannelement (29, 37) gegen die Konturhülse (13) verspannt ist.13. Exhaust gas turbine according to claim 12, so that the base plate (28) is clamped against the contour sleeve (13) by a clamping element (29, 37).
14. Abgasturbine nach Anspruch 13, d a d u r c h g e k e n n z e i c h n e t , dass das Spannelement (29) ein Spannring ist, der a- xial auf die Grundplatte (28) wirkt und sich in einer Nut der Konturhülse (13) abstützt.14. Exhaust gas turbine according to claim 13, so that the clamping element (29) is a clamping ring which acts axially on the base plate (28) and is supported in a groove in the contour sleeve (13).
15. Abgasturbine nach Anspruch 13, d a d u r c h g e k e n n z e i c h n e t , dass die Grundplatte (28) in radialer Richtung gegenüber der Konturhülse (13) abgedichtet ist, indem ein konzentrischer Spannring die Grundplatte (28) in radialer Richtung auf die Konturhülse (13) presst. 15. Exhaust gas turbine according to claim 13, characterized in that the base plate (28) is sealed in the radial direction from the contour sleeve (13) by a concentric clamping ring pressing the base plate (28) in the radial direction onto the contour sleeve (13).
EP04729870.8A 2003-06-06 2004-04-28 Exhaust gas turbine for an exhaust gas turbocharger Expired - Lifetime EP1631736B1 (en)

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DE10325649.0A DE10325649B4 (en) 2003-06-06 2003-06-06 Exhaust gas turbine for an exhaust gas turbocharger
PCT/EP2004/004452 WO2004109062A1 (en) 2003-06-06 2004-04-28 Exhaust gas turbine for an exhaust gas turbocharger

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US7371047B2 (en) 2008-05-13
JP2006527322A (en) 2006-11-30
US20060133931A1 (en) 2006-06-22
EP1631736B1 (en) 2015-07-29
DE10325649B4 (en) 2014-10-23
WO2004109062A1 (en) 2004-12-16
DE10325649A1 (en) 2004-12-23
JP4269184B2 (en) 2009-05-27

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