EP1706595B1 - Non-positive-displacement machine comprising a spiral channel provided in the housing middle part - Google Patents

Non-positive-displacement machine comprising a spiral channel provided in the housing middle part Download PDF

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Publication number
EP1706595B1
EP1706595B1 EP04818152A EP04818152A EP1706595B1 EP 1706595 B1 EP1706595 B1 EP 1706595B1 EP 04818152 A EP04818152 A EP 04818152A EP 04818152 A EP04818152 A EP 04818152A EP 1706595 B1 EP1706595 B1 EP 1706595B1
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EP
European Patent Office
Prior art keywords
turbine
housing
compressor
spiral
turbo
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EP04818152A
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German (de)
French (fr)
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EP1706595A1 (en
Inventor
Karl-Ernst Hummel
Stephan Wild
Günter Kröger
Norbert Poppenborg
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Mann and Hummel GmbH
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Mann and Hummel GmbH
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Publication of EP1706595A1 publication Critical patent/EP1706595A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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 turbomachine for generating a mass flow according to the preamble of claim 1.
  • a turbine housing for an exhaust gas turbocharger in which an exhaust-driven turbine rotor drives a compressor rotor.
  • the compressor rotor is connected by a rigid shaft to the turbine rotor.
  • the shaft, which carries the compressor wheel and the turbine wheel, is mounted in a middle part of the housing, which is closed on the turbine side by a turbine housing and on the compressor side by a compressor housing.
  • the exhaust gas flows tangentially into a spiral, narrowing contour of the turbine housing and is directed to turbine blades of the turbine rotor. These turbine blades drive the turbine rotor.
  • the exhaust stream continues to flow axially from the turbine housing to the turbine wheel.
  • spiral channels require a high geometric and surface requirement.
  • the spiral channels are formed in a turbine housing and a compressor housing. These two housings are laterally flanged to a middle part of the housing. This configuration can only be produced due to the shaping with high production engineering effort.
  • the expert takes from the US 4598542 , of the GB 1315307 , of the US 4009568 and the US 3844676 Turbines and compressors in different construction variants, in which the compressor or turbine channels are arranged in each case at least two housing parts. Again, therefore, a very high component and fit accuracy is required.
  • the post-published font EP 1394366 A shows a turbomachine with a surrounding a storage space
  • Housing which is at least partially formed integrally with the housing surrounding at least one of the rotor chambers.
  • the object of the present invention is to change the design of the housing elements such that the production of the spiral channels can be simplified.
  • the inventive arrangement of the turbomachine is based on the laying of at least one spiral geometry in a middle part of the housing. This forms thereby at least a part of a turbine or a compressor housing.
  • the spiral geometry is closed on the outside by a lid.
  • a cross section of the spiral channel is defined by the middle part of the housing and the cover.
  • a parting plane Between the cover and the middle part of the housing is a parting plane, which is aligned perpendicular to a turbine shaft mounted in the middle part of the housing.
  • the turbomachine can be, for example, a turbomachine, for example, as an exhaust gas turbocharger or a secondary air charger for secondary air injection in catalytic converters. However, it can also be used as a simple turbine for converting a mass flow into a rotor movement.
  • the turbomachine according to the invention advantageously makes it possible to lay a spiral contour in the central housing middle part, thereby the flow cross-section of the spiral contour can be produced undercut-free in the primary molding process. Furthermore, results from the narrower design of the lid, a reduced space requirement.
  • the lid is flat on the area adjacent to the spiral contour.
  • the spiral contour is formed exclusively in the middle part.
  • the contour corresponding to the turbine rotor and the axial inlet or outlet connection can be carried out unchanged.
  • This embodiment advantageously makes it possible to meet the high requirement of the spiral geometry in terms of geometry and dimensional tolerance. Due to the simple geometry of the lid this can also be made of plastics, such as polyamide.
  • the spiral geometries of the turbine and the compressor side are arranged in the middle part of the housing. As a result, the length of the turbine shaft and thus the entire housing can be shortened. Thus, the required space is further reduced.
  • An advantageous embodiment of the invention relates to the cross-sectional profile of the spiral channel, in particular on the turbine side.
  • the widening of the cross section of the spiral channel can be effected by an axial and a radial expansion. If the expansion is achieved by radial expansion, so reduces the axial depth of the spiral channel. This increases the outer circumference of the spiral channel. Since this circumference of the spiral channel on the turbine side is smaller compared to the compressor side, there is sufficient space available in the radial direction. Thus, the entire housing can be made shorter.
  • a further advantageous variant relates to the rotational position of the spiral channels to each other. Due to the reduced axial depth of the spiral channels, any desired rotational position of the spiral channels relative to one another can be achieved. This is advantageous because often only very much for the tangential arrival or Abströmstutzen limited installation space is available. These can thus be arranged at any angle to each other.
  • At least one tangential nozzle is angled parallel to the turbine shaft.
  • the tangential connection piece is preferably angled against the respective cover side.
  • Another design provides to arrange the tangential nozzle in variable angle to the turbine shaft. Manufacturing technology, this variant is realized by side shift.
  • the possible Angular range is approx. 0-90 °. This makes it advantageously possible to make the angle of attack of the tangential nozzle to the turbine shaft variable.
  • one or both tangential nozzles are integrally formed on the cover of the respective side. According to the above-mentioned angle design, this can be realized by a double-shell mold or with a side slide manufacturing technology. Advantageous is the possibility of further adaptation of the tangential nozzle to the geometry of the installation space.
  • the dividing plane present between housing center part and cover is arranged substantially centrally in the flow cross-section of the spiral channels.
  • a spiral channel in its axial position toward the turbine shaft can be arranged substantially in the cover in a partial area substantially in the middle part of the housing and in a further partial area.
  • this makes it possible to use both the cover and the middle part of the housing for the arrangement of the spiral contours.
  • aerodynamically optimized geometries can be formed.
  • a turbomachine 10 according to the invention is shown in full section, in which in a central housing middle part 11, a turbine shaft 12 is mounted. On the turbine shaft 12, a compressor rotor 13 and on the opposite side of a turbine rotor 14 is rigidly fixed.
  • the housing middle part 11 is closed on the opposite sides by a turbine cover 16 and a compressor cover 15. These two covers 15, 16 are tensioned on plane-shaped parting planes 21, 22 on the middle part of the housing.
  • spiral channels 17, 18 are formed on both sides, these spiral channels are closed to the lid sides on the plane-shaped parting planes 21, 22 through the lid 15,16. Between the parting planes 21, 22, the middle part of the housing has a housing thickness a.
  • spiral channels 17,18 change their circular cross-sectional area in a spiral shape and overlap in the axial direction of the turbine shaft 12 with the dimension x in the region of the largest cross-sectional area.
  • a discharge nozzle 24 is arranged to a turbine-side downstream side 19
  • the compressor cover 15 is arranged to a compressor-side upstream side of a 20 axial flow connection 23.
  • FIG. 2 shows a further flow machine 10 in full section.
  • the spiral channels 17a, 18a in contrast to FIG. 1 designed in an oval shape.
  • this oval configuration of the spiral channels 17a, 18a need not be made over the entire length, but may also be formed only in the region of the largest cross-sectional area or only on one side of the housing. Due to the oval design of the spiral channels 17a, 18a, the housing thickness a can be reduced.
  • FIG. 3a shows a further full section through a turbomachine 10.
  • a turbine-side inflow pipe 25 and a compressor-side outflow pipe 26 are shown.
  • the spiral channels 17, 18 are partially shown as dashed lines.
  • the two sockets 25, 26 are arranged tangentially to the spiral channels 17, 18 and correspond with them.
  • FIG. 3b shows the housing middle part 11 according to the FIG. 3a in the plan view.
  • the components corresponding to the preceding figures are given the same reference numerals.
  • the course of the turbine-side spiral channel 17 is shown as a dashed line.
  • the middle part 11 is shown in partial section.
  • the sockets 25, 26 are arranged at an angle of 180 ° to each other.
  • the housing thickness a (FIG. Fig. 3a ) are increased in order to avoid an overlap of the spiral channels 17, 18.
  • the sockets 26, 25 of the housing middle part 11 are arranged at an angle of approximately 270 ° to each other, by crossing the two sockets 25b, 26b. This is the most unfavorable angular position, because the housing thickness a of the inner diameter c of the nozzle 25b, 26b is determined. In order to minimize the housing thickness a in this angular position, the sockets 25b, 26b are designed in the crossing region with an oval cross-section.
  • FIG. 4 shows the middle part 11 viewed in perspective on the compressor side.
  • the dashed line shows the circular design of the compressor-side spiral channel 18 and the solid line of the oval spiral channel 18b. Due to the oval design results over the entire geometry of the spiral channel 18b a larger width b. This may require a larger case diameter. Due to the smaller cross-sectional area of the turbine-side spiral channel 17 (FIG. FIG. 3 ), only this oval and thus wider can be designed. As a result, a uniform housing diameter can be produced.
  • FIGS. 5a and 5b each show a partial section of the housing middle part 11 according to the FIG. 4 Cut CC and DD.
  • the width b of the oval spiral channel 18b is shown with respect to the dashed line width of the circular spiral channel 18.
  • the turbomachine in two variants shown schematically in full section.
  • the two tangential stubs 125, 126 are angled at right angles to the parting planes 121, 122.
  • both nozzles 125, 126 directed against the side of their respective spiral channels 117, 118.
  • the two covers 115, 116 close the two spiral channels 117, 118 to the region of the two stubs 125, 126.
  • the spiral channels 117, 118 and the two stubs 125, 126 designed undercut. This allows a simple production method in the original molding process.
  • FIG. 7 a further variant of the turbomachine 10 is shown schematically.
  • the nozzle 226 is in this case arranged on the housing middle part 211, and angled at right angles to the separating plane 222 in the direction of the compressor-side spiral channel 218.
  • the spiral channel 218 is closed by the compressor cover 215.
  • the undercut formed in the housing middle part 211 can be produced, for example, in the original molding process by a tool with a drag slider.
  • the housing middle part 211 is closed by the turbine cover 216.
  • FIG. 8 schematically shows the turbomachine 10.
  • the nozzle 326 is in this case arranged on the cover 315 and corresponds to the parting plane 322 with the spiral channel 317.
  • the middle part 311 thus forms only the spiral contour 317 and can be made without the form-technically complicated nozzle 326.
  • On the turbine side of the housing middle part 311 is closed by the turbine cover 316.
  • FIG. 9 shows a turbomachine 10 at which the dividing plane 22 extends substantially centrally through the cross section of the compressor-side spiral channel 18b.
  • the spiral channel 18b extends in the compressor cover 15 parallel to the parting plane 22 and angled in the middle part 11 to the parting plane 22. Therefore, the parting plane 22 is arranged in the embodiment shown only in a partial region in the middle in the spiral channel 18b.
  • the geometrically simple part can be formed for example by a simple plan-shaped groove in the compressor cover 15 and the geometrically complex and precise shape be placed in the middle part 11.
  • the two covers 15, 16 are preferably made of a plastic, wherein the housing middle part 11 is preferably formed of a metallic material.

Abstract

A non-positive-displacement machine (10), particularly a turbomachine for producing a mass flow, having a central housing part (11) inside which a turbine shaft is mounted. A turbine housing is mounted on the central housing part (11) on a turbine side and a compressor housing is mounted on the central housing part (11) on a compressor side. The spiral channels (17, 18) required for the compressor side and for the turbine side can be arranged in a partial area inside the covers (15, 16) and at least in one partial area inside the central housing part (11). This permits the contours, which are required for the spiral channels (17, 18) and which are geometrically complex, to be constructed in the central housing part (11).

Description

Die Erfindung betrifft eine Strömungsmaschine zur Erzeugung eines Massenstromes nach dem Oberbegriff des Patentanspruches 1.The invention relates to a turbomachine for generating a mass flow according to the preamble of claim 1.

Aus der DE 10297203 Ist ein Turbinengehäuse für einen Abgasturbolader bekannt in welchem, ein durch Abgase angetriebener Turbinenrotor, einen Verdichterrotor antreibt. Dabei ist der Verdichterrotor durch eine starre Welle mit dem Turbinenrotor verbunden. Die Welle, welche das Verdichterrad und das Turbinenrad trägt, wird in einem Gehäusemittelteil gelagert, welches auf der Turbinenseite durch ein Turbinengehäuse und auf der Verdichterseite durch ein Verdichtergehäuse verschlossen ist. Das Abgas strömt tangential in eine spiralförmige, sich verengende Kontur des Turbinengehäuses ein und wird gezielt auf Turbinenschaufeln des Turbinenrotors geleitet. Durch diese Turbinenschaufeln wird der Turbinenrotor angetrieben. Der Abgasstrom strömt weiter axial zum Turbinenrad aus dem Turbinengehäuse aus. Auf der Verdichterseite wird ein Massenstrom axial vom Verdichterrotor über die spiralförmigen Kanäle zur tangentialen Abströmung gefördert. An die spiralförmigen Kanäle ist eine hohe Anforderung bezüglich der Geometrie und der Oberfläche gefordert. In der gezeigten Gestaltung sind die spiralförmigen Kanäle in einem Turbinengehäuse und einem Verdichtergehäuse eingeformt. Diese beiden Gehäuse sind seitlich an einem Gehäusemittelteil angeflanscht. Diese Ausgestaltung ist aufgrund der Formgebung nur mit hohem fertigungstechnischem Aufwand herstellbar.From the DE 10297203 A turbine housing for an exhaust gas turbocharger is known in which an exhaust-driven turbine rotor drives a compressor rotor. In this case, the compressor rotor is connected by a rigid shaft to the turbine rotor. The shaft, which carries the compressor wheel and the turbine wheel, is mounted in a middle part of the housing, which is closed on the turbine side by a turbine housing and on the compressor side by a compressor housing. The exhaust gas flows tangentially into a spiral, narrowing contour of the turbine housing and is directed to turbine blades of the turbine rotor. These turbine blades drive the turbine rotor. The exhaust stream continues to flow axially from the turbine housing to the turbine wheel. On the compressor side, a mass flow is conveyed axially from the compressor rotor via the spiral channels to the tangential outflow. The spiral channels require a high geometric and surface requirement. In the illustrated embodiment, the spiral channels are formed in a turbine housing and a compressor housing. These two housings are laterally flanged to a middle part of the housing. This configuration can only be produced due to the shaping with high production engineering effort.

Der Fachmann entnimmt aus der US 4598542 , der GB 1315307 , der US 4009568 und der US 3844676 Turbinen und Verdichter in unterschiedlichen Bauvarianten, bei denen die Verdichter- oder Turbinenkanäle in jeweils mindestens zwei Gehäuseteilen angeordnet sind. Auch hier ist deshalb eine sehr hohe Bauteil- und Passgenauigkeit erforderlich.The expert takes from the US 4598542 , of the GB 1315307 , of the US 4009568 and the US 3844676 Turbines and compressors in different construction variants, in which the compressor or turbine channels are arranged in each case at least two housing parts. Again, therefore, a very high component and fit accuracy is required.

Die nachveröffentlichte Schrift EP 1394366 A zeigt eine Strömungsmaschine mit einem ein Lagerungsraum umgebendesThe post-published font EP 1394366 A shows a turbomachine with a surrounding a storage space

Gehäuse, das mindestens zum Teil mit dem wenigstens einen der Rotorräume umgebenden Gehäuse einstückig ausgebildet ist.Housing, which is at least partially formed integrally with the housing surrounding at least one of the rotor chambers.

Die Aufgabe der vorliegenden Erfindung besteht darin, die Gestaltung der Gehäuseelemente derart zu verändern, dass die Herstellung der spiralförmigen Kanäle vereinfacht werden kann.The object of the present invention is to change the design of the housing elements such that the production of the spiral channels can be simplified.

Diese Aufgabe wird durch die kennzeichnenden Merkmale des Patentanspruches 1 gelöst.This object is solved by the characterizing features of claim 1.

Vorteile der ErfindungAdvantages of the invention

Die erfindungsgemäße Anordnung der Strömungsmaschine beruht auf der Verlegung wenigstens einer Spiralgeometrie in ein Gehäusemittelteil. Dieses bildet dadurch zumindest einen Teil eines Turbinen- oder eines Verdichtergehäuses. Die Spiralgeometrie wird an der Außenseite durch einen Deckel verschlossen. Dadurch ist ein Querschnitt des Spiralkanales durch Gehäusemittelteil und Deckel definiert. Zwischen Deckel und Gehäusemittelteil befindet sich eine Trennebene, die senkrecht zu einer im Gehäusemittelteil gelagerten Turbinenwelle ausgerichtet ist.The inventive arrangement of the turbomachine is based on the laying of at least one spiral geometry in a middle part of the housing. This forms thereby at least a part of a turbine or a compressor housing. The spiral geometry is closed on the outside by a lid. As a result, a cross section of the spiral channel is defined by the middle part of the housing and the cover. Between the cover and the middle part of the housing is a parting plane, which is aligned perpendicular to a turbine shaft mounted in the middle part of the housing.

Die Strömungsmaschine kann beispielsweise eine Turbomaschine z.B. als Abgasturbolader oder ein Sekundärluftlader zur Sekundärlufteinblasung in Abgaskatalysatoren sein. Sie kann aber auch als einfache Turbine zur Wandlung eines Massenstromes in eine Rotorbewegung genutzt werden.The turbomachine can be, for example, a turbomachine, for example, as an exhaust gas turbocharger or a secondary air charger for secondary air injection in catalytic converters. However, it can also be used as a simple turbine for converting a mass flow into a rotor movement.

Die erfindungsgemäße Strömungsmaschine erlaubt es vorteilhaft, eine Spiralkontur in den zentralen Gehäusemittelteil zu verlegen, dadurch kann der Strömungsquerschnitt der Spiralkontur hinterschnittsfrei im Urformverfahren hergestellt werden. Weiterhin ergibt sich durch die schmalere Gestaltung des Deckels, ein reduzierter Raumbedarf.The turbomachine according to the invention advantageously makes it possible to lay a spiral contour in the central housing middle part, thereby the flow cross-section of the spiral contour can be produced undercut-free in the primary molding process. Furthermore, results from the narrower design of the lid, a reduced space requirement.

Gemäß der Erfindung ist der Deckel, an dem zur Spiralkontur angrenzenden Bereich hin, plan ausgeführt. Die Spiralkontur ist dabei ausschließlich im Gehäusemittelteil gebildet. Die mit dem Turbinenrotor korrespondierende Kontur und der axiale An- bzw. Abströmstutzen können dabei unverändert ausgeführt werden.According to the invention, the lid is flat on the area adjacent to the spiral contour. The spiral contour is formed exclusively in the middle part. The contour corresponding to the turbine rotor and the axial inlet or outlet connection can be carried out unchanged.

Diese Ausgestaltung erlaubt es vorteilhaft, die hohe Anforderung der Spiralgeometrie hinsichtlich Geometrie und Maßtoleranz zu erfüllen. Durch die einfache Geometrie des Deckels kann dieser auch aus Kunststoffen, wie beispielsweise Polyamid hergestellt werden.This embodiment advantageously makes it possible to meet the high requirement of the spiral geometry in terms of geometry and dimensional tolerance. Due to the simple geometry of the lid this can also be made of plastics, such as polyamide.

In einer Variante sind die Spiralgeometrien der Turbinen- und der Verdichterseite im Gehäusemittelteil angeordnet. Dadurch kann die Länge der Turbinenwelle und somit das gesamte Gehäuse verkürzt werden. Somit wird der erforderliche Bauraum weiter reduziert.In one variant, the spiral geometries of the turbine and the compressor side are arranged in the middle part of the housing. As a result, the length of the turbine shaft and thus the entire housing can be shortened. Thus, the required space is further reduced.

Eine vorteilhafte Ausbildung der Erfindung betrifft den Querschnittsverlauf des Spiralkanales insbesondere auf der Turbinenseite. Die Aufweitung des Querschnittes des Spiralkanales kann durch eine axiale und eine radiale Ausdehnung erfolgen. Wird die Aufweitung durch radiale Ausdehnung erreicht, so reduziert sich die axiale Tiefe des Spiralkanales. Dabei vergrößert sich der äußere Umfang des Spiralkanales. Da dieser Umfang des Spiralkanales auf der Turbinenseite kleiner gegenüber der Verdichterseite ist, steht in radiale Richtung genügend Raum zur Verfügung. Somit kann das gesamte Gehäuse kürzer ausgeführt werden.An advantageous embodiment of the invention relates to the cross-sectional profile of the spiral channel, in particular on the turbine side. The widening of the cross section of the spiral channel can be effected by an axial and a radial expansion. If the expansion is achieved by radial expansion, so reduces the axial depth of the spiral channel. This increases the outer circumference of the spiral channel. Since this circumference of the spiral channel on the turbine side is smaller compared to the compressor side, there is sufficient space available in the radial direction. Thus, the entire housing can be made shorter.

Eine weitere vorteilhafte Variante betrifft die rotatorische Position der Spiralkanäle zueinander. Durch die verringerte axiale Tiefe der Spiralkanäle kann eine beliebige rotatorische Position der Spiralkanäle zueinander erreicht werden. Dies ist deshalb vorteilhaft, weil für die tangentialen An- bzw. Abströmstutzen oft nur ein sehr begrenzter Einbauraum zur Verfügung steht. Diese können somit in beliebigem Winkel zueinander angeordnet werden.A further advantageous variant relates to the rotational position of the spiral channels to each other. Due to the reduced axial depth of the spiral channels, any desired rotational position of the spiral channels relative to one another can be achieved. This is advantageous because often only very much for the tangential arrival or Abströmstutzen limited installation space is available. These can thus be arranged at any angle to each other.

Gemäß einer besonderen Ausführungsform ist wenigstens ein tangentialer Stutzen parallel zur Turbinenwelle angewinkelt. Dabei ist der tangentiale Stutzen vorzugsweise entgegen der jeweiligen Deckelseite abgewinkelt. Dadurch kann ein Kern des Stutzens hinterschnittsfrei gestaltet werden. Spiralkontur und der Kern des Stutzens sind somit durch ein Werkzeugteil herstellbar. Dadurch wird eine einfache und wirtschaftliche Herstellbarkeit des Gehäusemittelteils erreicht.According to a particular embodiment, at least one tangential nozzle is angled parallel to the turbine shaft. In this case, the tangential connection piece is preferably angled against the respective cover side. As a result, a core of the neck can be designed without an undercut. Spiral contour and the core of the nozzle are thus produced by a tool part. As a result, a simple and economical manufacturability of the middle part is achieved.

Eine weitere Gestaltungsweise sieht vor, die tangentialen Stutzen in variablen Winkel zur Turbinenwelle anzuordnen. Fertigungstechnisch ist diese Variante durch Seitenschieber realisierbar. Der mögliche Winkelbereich beträgt ca. 0-90°. Dadurch ist es vorteilhaft möglich, den Anströmwinkel der tangentialen Stutzen zur Turbinenwelle hin variabel zu gestalten.Another design provides to arrange the tangential nozzle in variable angle to the turbine shaft. Manufacturing technology, this variant is realized by side shift. The possible Angular range is approx. 0-90 °. This makes it advantageously possible to make the angle of attack of the tangential nozzle to the turbine shaft variable.

Gemäß einer weiteren Ausgestaltung sind einer oder beide tangentiale Stutzen am Deckel der jeweiligen Seite angeformt. Entsprechend der bereits erwähnten Winkelgestaltung kann dies fertigungstechnisch durch ein zweischaliges Werkzeug oder mit einem Seitenschieber verwirklicht werden. Vorteilhaft ist dabei die weitere Anpassungsmöglichkeit der tangentialen Stutzen an die Geometrie des Einbauraumes.According to another embodiment, one or both tangential nozzles are integrally formed on the cover of the respective side. According to the above-mentioned angle design, this can be realized by a double-shell mold or with a side slide manufacturing technology. Advantageous is the possibility of further adaptation of the tangential nozzle to the geometry of the installation space.

In einer nicht zur Erfindung gehörenden Weiterbildung ist die zwischen Gehäusemitteiteil und Deckel vorhanden Trennebene im Wesentlichen mittig im Strömungsquerschnitt der Spiralkanäle angeordnet. Dabei kann ein Spiralkanal in seiner axialen Position zu der Turbinenwelle hin in einem Teilbereich im Wesentlichen im Gehäusemittelteil und in einem weiteren Teilbereich Im Wesentlichen im Deckel angeordnet sein. Vorteilhaft wird es hierdurch möglich, sowohl den Deckel als auch das Gehäusemittelteil für die Anordnung der Spiralkonturen zu nutzen. Dadurch können strömungstechnisch optimierte Geometrien gebildet werden.In a development not belonging to the invention, the dividing plane present between housing center part and cover is arranged substantially centrally in the flow cross-section of the spiral channels. In this case, a spiral channel in its axial position toward the turbine shaft can be arranged substantially in the cover in a partial area substantially in the middle part of the housing and in a further partial area. Advantageously, this makes it possible to use both the cover and the middle part of the housing for the arrangement of the spiral contours. As a result, aerodynamically optimized geometries can be formed.

Diese und weitere Merkmale von bevorzugten Weiterbildungen der Erfindung gehen außer aus den Ansprüchen auch aus der Beschreibung und der Zeichnung hervor, wobei die einzelnen Merkmale jeweils für sich allein oder zu mehreren in Form von Unterkombinationen bei der Ausführungsform der Erfindung und auf anderen Gebieten verwirklicht sein und vorteilhafte sowie für sich schutzfähige Ausführungen darstellen können, für die hier Schutz beansprucht wird.These and other features of preferred embodiments of the invention will become apparent from the claims and from the description and the drawings, wherein the individual features are realized individually or in each case in the form of sub-combinations in the embodiment of the invention and in other fields and can represent advantageous and protectable versions for which protection is claimed here.

Weitere Einzelheiten der Erfindung werden in der Zeichnung anhand von schematischen Ausführungsbeispielen beschrieben. Hierbei zeigen

  • Figur 1 eine Strömungsmaschine im Vollschnitt,
  • Figur 2 eine Weiterentwicklung der Strömungsmaschine im Vollschnitt
  • Figur 3a eine Strömungsmaschine im Vorschnitt,
  • Figur 3b eine Strömungsmaschine gemäß Figur 3a in der Draufsicht,
  • Figur 3c eine Strömungsmaschine im Vollschnitt
  • Figur 3d eine Strömungsmaschine gemäß Figur 3c in der Draufsicht,
  • Figur 4 eine perspektivische Darstellung eines Gehäusemittelteiles,
  • Figur 5a, b eine Schnittdarstellung durch das Gehäusemittelteils gemäß Figur 4,
  • Figur 6a, b eine schematische Darstellung zweier Varianten einer Strömungsmaschine im Vollschnitt,
  • Figur 7 einen schematischen Ausschnitt einer Strömungsmaschine im Vollschnitt,
  • Figur 8 einen weiteren schematischen Ausschnitt einer Strömungsmaschine im Vollschnitt,
  • Figur 9 eine nicht beanspruchte Variante einer Strömungsmaschine im Vollschnitt.
Further details of the invention are described in the drawing with reference to schematic embodiments. Show here
  • FIG. 1 a turbomachine in full section,
  • FIG. 2 a further development of the turbomachine in full section
  • FIG. 3a a turbomachine in the precut,
  • FIG. 3b a turbomachine according to FIG. 3a in the plan view,
  • Figure 3c a turbomachine in full section
  • 3d figure a turbomachine according to Figure 3c in the plan view,
  • FIG. 4 a perspective view of a middle part of the housing,
  • FIG. 5a, b a sectional view through the middle part according to FIG. 4 .
  • FIG. 6a, b a schematic representation of two variants of a turbomachine in full section,
  • FIG. 7 a schematic section of a turbomachine in full section,
  • FIG. 8 a further schematic section of a turbomachine in full section,
  • FIG. 9 an unclaimed variant of a turbomachine in full section.

Beschreibung der AusführungsbeispieleDescription of the embodiments

In der Figur 1 ist eine erfindungsgemäße Strömungsmaschine 10 im Vollschnitt gezeigt, in welcher in einem zentralen Gehäusemittelteil 11 eine Turbinenwelle 12 gelagert ist. An der Turbinenwelle 12 ist ein Verdichterrotor 13 und auf der gegenüberliegenden Seite ein Turbinenrotor 14 starr befestigt. Der Gehäusemittelteil 11 ist an den gegenüberliegenden Seiten von einem Turbinendeckel 16 und einem Verdichterdeckel 15 verschlossen. Diese beiden Deckel 15, 16 sind an planförmigen Trennebenen 21, 22 auf das Gehäusemittelteil gespannt. Im Gehäusemittelteil 11 sind an beiden Seiten Spiralkanäle 17, 18 eingeformt, diese Spiralkanäle werden zu den Deckelseiten an den planförmigen Trennebenen 21, 22 durch die Deckel 15,16 verschlossen. Zwischen den Trennebenen 21, 22 weist das Gehäusemittelteil ein Gehäusedicke a auf.In the FIG. 1 a turbomachine 10 according to the invention is shown in full section, in which in a central housing middle part 11, a turbine shaft 12 is mounted. On the turbine shaft 12, a compressor rotor 13 and on the opposite side of a turbine rotor 14 is rigidly fixed. The housing middle part 11 is closed on the opposite sides by a turbine cover 16 and a compressor cover 15. These two covers 15, 16 are tensioned on plane-shaped parting planes 21, 22 on the middle part of the housing. In the middle part 11 spiral channels 17, 18 are formed on both sides, these spiral channels are closed to the lid sides on the plane-shaped parting planes 21, 22 through the lid 15,16. Between the parting planes 21, 22, the middle part of the housing has a housing thickness a.

Die Spiralkanäle 17,18 verändern ihre kreisförmige Querschnittsfläche im spiralförmigen Verlauf und überschneiden sich in axiale Richtung der Turbinenwelle 12 mit dem Maß x im Bereich der größten Querschnittsfläche. Am Turbinendeckel 16 ist zu einer turbinenseitigen Abströmseite 19 ein Abströmstutzen 24 angeordnet, und am Verdichterdeckel 15 ist zu einer verdichterseitigen Anströmseite ein 20 axialer Anströmstutzen 23 angeordnet.The spiral channels 17,18 change their circular cross-sectional area in a spiral shape and overlap in the axial direction of the turbine shaft 12 with the dimension x in the region of the largest cross-sectional area. At the turbine cover 16, a discharge nozzle 24 is arranged to a turbine-side downstream side 19, and the compressor cover 15 is arranged to a compressor-side upstream side of a 20 axial flow connection 23.

Figur 2 zeigt eine weitere Strömungsmaschine 10 im Vollschnitt. Der Figur 1 entsprechende Bauteile sind mit denselben Bezugszeichen versehen. Im Gehäusemittelteil sind die Spiralkanäle 17a, 18a im Gegensatz zur Figur 1 oval gestaltet. Im Bereich der maximalen Strömungsquerschnitte der Spiralkanäle 17a, 18a sind diese durch das Abstandsmaß y voneinander beabstandet. Diese ovale Gestaltung der Spiralkanäle 17a, 18a muss nicht über die gesamte Länge erfolgen, sondern kann auch nur im Bereich der größten Querschnittsfläche oder nur auf einer Gehäuseseite gebildet sein. Aufgrund der ovalen Gestaltung der Spiralkanäle 17a, 18a kann die Gehäusedicke a verringert werden. FIG. 2 shows a further flow machine 10 in full section. Of the FIG. 1 corresponding components are provided with the same reference numerals. In the middle part of the housing, the spiral channels 17a, 18a in contrast to FIG. 1 designed in an oval shape. In the area of the maximum flow cross sections of the spiral channels 17a, 18a, these are determined by the distance dimension y spaced from each other. This oval configuration of the spiral channels 17a, 18a need not be made over the entire length, but may also be formed only in the region of the largest cross-sectional area or only on one side of the housing. Due to the oval design of the spiral channels 17a, 18a, the housing thickness a can be reduced.

Figur 3a zeigt einen weiteren Vollschnitt durch eine Strömungsmaschine 10. Bauteile die den vorhergehenden Figuren entsprechen, sind mit denselben Bezugszeichen versehen. Dabei sind ein turbinenseitiger Einströmstutzen 25 und ein verdichterseitiger Abströmstutzen 26 gezeigt. Die Spiralkanäle 17, 18 sind teilweise als gestrichelte Linien dargestellt. Die beiden Stutzen 25, 26 sind tangential zu den Spiralkanälen 17,18 angeordnet und korrespondieren mit diesen. FIG. 3a shows a further full section through a turbomachine 10. Components which correspond to the preceding figures are provided with the same reference numerals. In this case, a turbine-side inflow pipe 25 and a compressor-side outflow pipe 26 are shown. The spiral channels 17, 18 are partially shown as dashed lines. The two sockets 25, 26 are arranged tangentially to the spiral channels 17, 18 and correspond with them.

Figur 3b zeigt das Gehäusemittelteil 11 gemäß der Figur 3a in der Draufsicht. Den vorhergehenden Figuren entsprechende Bauteile sind mit denselben Bezugszeichen versehen. Der Verlauf des turbinenseitigen Spiralkanales 17 ist als gestrichelte Linie dargestellt. Im Bereich des verdichterseitigen Abströmstutzens ist das Gehäusemittelteil 11 im Teilschnitt dargestellt. Die Stutzen 25, 26 sind im einem Winkel von 180° zueinander angeordnet. FIG. 3b shows the housing middle part 11 according to the FIG. 3a in the plan view. The components corresponding to the preceding figures are given the same reference numerals. The course of the turbine-side spiral channel 17 is shown as a dashed line. In the region of the compressor-side outflow nozzle, the middle part 11 is shown in partial section. The sockets 25, 26 are arranged at an angle of 180 ° to each other.

Bei einer Winkelanordnung gemäß dem gestrichelt dargestellten, dritten Stutzen 25c muss die Gehäusedicke a (Fig. 3a) vergrößert werden um eine Überschneidung der Spiralkanäle 17, 18 zu vermeiden.In the case of an angular arrangement according to the third connecting piece 25c shown in dashed lines, the housing thickness a (FIG. Fig. 3a ) are increased in order to avoid an overlap of the spiral channels 17, 18.

In Figur 3c und 3d sind die Stutzen 26, 25 des Gehäusemittelteiles 11 in einem Winkel von ca. 270° zueinander angeordnet, indem sich die beiden Stutzen 25b, 26b kreuzen. Dies ist die ungünstigste Winkelposition, weil die Gehäusedicke a von dem Innendurchmesser c der Stutzen 25b, 26b bestimmt wird. Um in dieser Winkelposition die Gehäusedicke a zu minimieren, sind die Stutzen 25b, 26b im kreuzenden Bereich mit ovalem Querschnitt gestaltet.In Figure 3c and 3d the sockets 26, 25 of the housing middle part 11 are arranged at an angle of approximately 270 ° to each other, by crossing the two sockets 25b, 26b. This is the most unfavorable angular position, because the housing thickness a of the inner diameter c of the nozzle 25b, 26b is determined. In order to minimize the housing thickness a in this angular position, the sockets 25b, 26b are designed in the crossing region with an oval cross-section.

Figur 4 zeigt das Gehäusemittelteil 11 perspektivisch auf die Verdichterseite betrachtet. Dabei ist mit der gestrichelten Linie die kreisförmige Gestaltung des verdichterseitigen Spiralkanales 18 und mit der Vollinie der ovale Spiralkanal 18b gezeigt. Durch die ovale Gestaltung ergibt sich über die gesamte Geometrie des Spiralkanales 18b eine größere Breite b. Dies kann einen größeren Gehäusedurchmesser erfordern. Aufgrund der kleineren Querschnittsfläche des turbinenseitigen Spiralkanales 17 (Figur 3) kann auch nur dieser oval und somit breiter gestaltet werden. Dadurch ist ein gleichmäßiger Gehäusedurchmesser herstellbar. FIG. 4 shows the middle part 11 viewed in perspective on the compressor side. The dashed line shows the circular design of the compressor-side spiral channel 18 and the solid line of the oval spiral channel 18b. Due to the oval design results over the entire geometry of the spiral channel 18b a larger width b. This may require a larger case diameter. Due to the smaller cross-sectional area of the turbine-side spiral channel 17 (FIG. FIG. 3 ), only this oval and thus wider can be designed. As a result, a uniform housing diameter can be produced.

Die Figuren 5a und 5b zeigen jeweils einen Teilausschnitt aus dem Gehäusemittelteil 11 gemäß der Figur 4 Schnitt C-C und D-D. Dabei ist die Breite b des ovalen Spiralkanales 18b gegenüber der gestrichelt gezeichneten Breite des kreisförmigen Spiralkanales 18 dargestellt.The FIGS. 5a and 5b each show a partial section of the housing middle part 11 according to the FIG. 4 Cut CC and DD. The width b of the oval spiral channel 18b is shown with respect to the dashed line width of the circular spiral channel 18.

In den Figuren 6a und 6b ist die Strömungsmaschine in zwei Varianten schematisch im Vollschnitt dargestellt. Am Gehäusemittelteil 111 sind die beiden tangentialen Stutzen 125, 126 rechtwinklig zur den Trennebenen 121, 122 angewinkelt. Dabei sind beide Stutzen 125, 126 entgegen der Seite ihrer jeweiligen Spiralkanäle 117, 118 gerichtet. Die beiden Deckel 115, 116 verschließen die beiden Spiralkanäle 117, 118 bis zum Bereich der beiden Stutzen 125, 126. Dadurch sind die Spiralkanäle 117, 118 und die beiden Stutzen 125, 126 hinterschnittsfrei gestaltet. Dies erlaubt eine einfache Herstellungsweise im Urformverfahren.In the Figures 6a and 6b is the turbomachine in two variants shown schematically in full section. On the housing middle part 111, the two tangential stubs 125, 126 are angled at right angles to the parting planes 121, 122. In this case, both nozzles 125, 126 directed against the side of their respective spiral channels 117, 118. The two covers 115, 116 close the two spiral channels 117, 118 to the region of the two stubs 125, 126. As a result, the spiral channels 117, 118 and the two stubs 125, 126 designed undercut. This allows a simple production method in the original molding process.

In Figur 7 ist eine weitere Variante der Strömungsmaschine 10 schematisch gezeigt. Der Stutzen 226 ist hierbei am Gehäusemittelteil 211 angeordnet, und rechtwinklig zur Trennebene 222 in Richtung des verdichterseitigen Spiralkanales 218 angewinkelt. Der Spiralkanal 218 wird durch den Verdichterdeckel 215 verschlossen. Der im Gehäusemittelteil 211 entstehende Hinterschnitt kann beispielsweise im Urformverfahren durch ein Werkzeug mit Schleppschieber hergestellt werden. Auf der Turbinenseite wird das Gehäusemittelteil 211 durch den Turbinendeckel 216 verschlossen.In FIG. 7 a further variant of the turbomachine 10 is shown schematically. The nozzle 226 is in this case arranged on the housing middle part 211, and angled at right angles to the separating plane 222 in the direction of the compressor-side spiral channel 218. The spiral channel 218 is closed by the compressor cover 215. The undercut formed in the housing middle part 211 can be produced, for example, in the original molding process by a tool with a drag slider. On the turbine side, the housing middle part 211 is closed by the turbine cover 216.

Figur 8 zeigt schematisch dargestellt, die Strömungsmaschine 10. Der Stutzen 326 ist hierbei am Deckel 315 angeordnet und korrespondiert an der Trennebene 322 mit dem Spiralkanal 317. Der Gehäusemittelteil 311 bildet somit nur die Spiralkontur 317 und kann ohne den formtechnisch komplizierten Stutzen 326 hergestellt werden. Auf der Turbinenseite wird der Gehäusemittelteil 311 durch den Turbinendeckel 316 verschlossen. FIG. 8 schematically shows the turbomachine 10. The nozzle 326 is in this case arranged on the cover 315 and corresponds to the parting plane 322 with the spiral channel 317. The middle part 311 thus forms only the spiral contour 317 and can be made without the form-technically complicated nozzle 326. On the turbine side of the housing middle part 311 is closed by the turbine cover 316.

Die nicht zu Erfindung gehörende Figur 9 zeigt eine Strömungsmaschine 10 an welcher die Trennebene 22 im Wesentlichen mittig durch den Querschnitt des verdichterseitigen Spiralkanales 18b verläuft. Der Spiralkanal 18b verläuft dabei im Verdichterdeckel 15 parallel zur Trennebene 22 und im Gehäusemittelteil 11 angewinkelt zur Trennebene 22. Deshalb ist die Trennebene 22 im gezeigten Ausführungsbeispiel nur in einem Teilbereich mittig im Spiralkanal 18b angeordnet. Der geometrisch einfache Teil kann beispielsweise durch eine einfache planförmige Nut im Verdichterdeckel 15 eingeformt werden und die geometrisch aufwendige und präzise Form in das Gehäusemittelteil 11 gelegt sein.The not belonging to the invention FIG. 9 shows a turbomachine 10 at which the dividing plane 22 extends substantially centrally through the cross section of the compressor-side spiral channel 18b. The spiral channel 18b extends in the compressor cover 15 parallel to the parting plane 22 and angled in the middle part 11 to the parting plane 22. Therefore, the parting plane 22 is arranged in the embodiment shown only in a partial region in the middle in the spiral channel 18b. The geometrically simple part can be formed for example by a simple plan-shaped groove in the compressor cover 15 and the geometrically complex and precise shape be placed in the middle part 11.

Die beiden Deckel 15, 16 sind vorzugsweise aus einem Kunststoff hergestellt wobei das Gehäusemittelteil 11 vorzugsweise aus einem metallischen Werkstoff gebildet ist.The two covers 15, 16 are preferably made of a plastic, wherein the housing middle part 11 is preferably formed of a metallic material.

Claims (7)

  1. Turbo-machine, in particular a turbo-engine for generating a mass flow, featuring a central housing component in which a turbine shaft is supported,
    wherein the central housing component is integrally molded as part of a turbine housing at the turbine side and at a compressor side as part of a compressor housing,
    wherein on the turbine side an inflow connection in tangential direction of the turbine shaft at the central housing component and a discharge flow connection in axial direction at the turbine housing are disposed,
    wherein on the compressor side a discharge flow connection in tangential direction at the central housing component and an inflow connection in axial direction at the compressor housing are disposed,
    wherein on the compressor side and/or on the turbine side each a cover is provided, and the cover being designed as part of the housing, characterized in that in the central housing component the spiral duct for the turbine side and/or the compressor side is provided, the cover being formed by a radially extending surface in only one plane at the area adjacent to the spiral contour, except for the contour which communicates with the rotor wheel.
  2. Turbo-machine according to claim 1, wherein both spiral ducts are formed by parts of the central housing component and the cover.
  3. Turbo-machine according to one of the above claims, wherein the spiral duct features in particular on the turbine side a certain maximum depth in the direction of the turbine shaft, wherein a modification of the cross-section can be realized by expanding the spiral duct in the radial direction in relation to the turbine shaft.
  4. Turbo-machine according to claim 3, wherein the spiral ducts due to their defined maximum depth are disposed to each other in any rotatory position, so that the tangential connecting pieces can be positioned to each other in any angle.
  5. Turbo-machine according to one of the above claims, wherein at least one connecting piece is angled and runs parallel to the turbine shaft.
  6. Turbo-machine according to claim 5, wherein the tangential connecting pieces are disposed in a variable angle in relation to the axis of the turbine shaft.
  7. Turbo-machine according to one of the above claims, wherein the tangential connecting pieces are disposed at the cover on the turbine side and/or at the cover on the compressor side.
EP04818152A 2003-11-04 2004-11-03 Non-positive-displacement machine comprising a spiral channel provided in the housing middle part Active EP1706595B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10352156 2003-11-04
PCT/EP2004/052774 WO2005045201A1 (en) 2003-11-04 2004-11-03 Non-positive-displacement machine comprising a spiral channel provided in the housing middle part

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EP1706595A1 EP1706595A1 (en) 2006-10-04
EP1706595B1 true EP1706595B1 (en) 2010-09-22

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EP (1) EP1706595B1 (en)
JP (1) JP4638878B2 (en)
AT (1) ATE482326T1 (en)
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WO (1) WO2005045201A1 (en)

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US9200636B2 (en) * 2009-04-22 2015-12-01 Dsm Ip Assets B.V. Plastic housing of a radial flow compressor
DE102009035573A1 (en) 2009-07-31 2011-02-10 Man Diesel & Turbo Se Radial compressor and method of manufacturing a radial compressor
BR112013001314A2 (en) 2010-07-21 2016-05-17 Itt Mfg Entpr Llc wear reduction device for rotary solids handling equipment
WO2012087907A2 (en) * 2010-12-22 2012-06-28 Honeywell International, Inc. Turbocharger and engine cylinder head assembly
US20120186247A1 (en) * 2011-01-26 2012-07-26 Honeywell International Inc. Turbocharger with Reversed Compressor Volute Optionally Integrated into the Center Housing
DE102011075449A1 (en) * 2011-05-06 2012-11-08 Bosch Mahle Turbo Systems Gmbh & Co. Kg Supercharger for internal combustion engine of motor car, has bearing housing designed as single-piece together with channel element of compressor housing, where element comprises spiral channel of compressor housing
US8966895B2 (en) 2012-03-21 2015-03-03 Honeywell International Inc. Turbocharger cartridge, bypass, and engine cylinder head assembly
US9091200B2 (en) 2012-03-21 2015-07-28 Honeywell International Inc. Turbocharger and engine cylinder head assembly
US8955318B2 (en) 2012-03-21 2015-02-17 Honeywell International Inc. Turbocharger cartridge and engine cylinder head assembly
US8966894B2 (en) 2012-03-21 2015-03-03 Honeywell International Inc. Turbocharger cartridge and engine cylinder head assembly
DE102016209951A1 (en) * 2016-06-07 2017-12-07 Ford Global Technologies, Llc Composite turbine housing

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ATE482326T1 (en) 2010-10-15
EP1706595A1 (en) 2006-10-04
JP2007510854A (en) 2007-04-26
US8062006B2 (en) 2011-11-22
WO2005045201A1 (en) 2005-05-19
JP4638878B2 (en) 2011-02-23
DE502004011691D1 (en) 2010-11-04
US20080034754A1 (en) 2008-02-14

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