EP1706595A1 - 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

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Publication number
EP1706595A1
EP1706595A1 EP04818152A EP04818152A EP1706595A1 EP 1706595 A1 EP1706595 A1 EP 1706595A1 EP 04818152 A EP04818152 A EP 04818152A EP 04818152 A EP04818152 A EP 04818152A EP 1706595 A1 EP1706595 A1 EP 1706595A1
Authority
EP
European Patent Office
Prior art keywords
housing
turbine
cover
compressor
spiral
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
EP04818152A
Other languages
German (de)
French (fr)
Other versions
EP1706595B1 (en
Inventor
Karl-Ernst Hummel
Stephan Wild
Günter Kröger
Norbert Poppenborg
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.)
Mann and Hummel GmbH
Original Assignee
Mann and Hummel GmbH
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Filing date
Publication date
Application filed by Mann and Hummel GmbH filed Critical Mann and Hummel GmbH
Publication of EP1706595A1 publication Critical patent/EP1706595A1/en
Application granted granted Critical
Publication of EP1706595B1 publication Critical patent/EP1706595B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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 a turbine rotor driven by exhaust gases drives a compressor rotor.
  • the compressor rotor is connected to the turbine rotor by a rigid shaft.
  • 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 spiraling, narrowing contour of the turbine housing and is directed specifically to turbine blades of the turbine rotor.
  • the turbine rotor is driven by these turbine blades.
  • the exhaust gas stream continues to flow axially from the turbine housing to the turbine wheel.
  • spiral channels require a high level of geometry and surface.
  • the spiral channels are formed in a turbine housing and a compressor housing. These two housings are flanged to the side of a middle part of the housing. Due to the shape, this configuration can only be produced with a high level of manufacturing complexity.
  • the object of the present invention is to change the design of the housing elements in such a way that the production of the spiral channels can be simplified.
  • the arrangement of the turbomachine according to the invention is based on the laying of at least part of a spiral geometry in a middle part of the housing. As a result, this forms at least part of a turbine or a compressor housing.
  • the spiral geometry is closed on the outside by a cover, the cover forming the second part of the spiral geometry. This defines a cross section of the spiral channel through the middle part of the housing and the cover.
  • the turbomachine can for example be a turbo machine e.g. be 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 allows a spiral contour to be laid in the central middle part of the housing, as a result of which the flow cross section of the spiral contour can be produced without undercuts in the primary molding process. Furthermore, the narrower design of the lid results in a reduced space requirement.
  • the lid on the area adjacent to the spiral contour, is made flat.
  • the spiral contour is formed exclusively in the middle part of the housing. The contour corresponding to the turbine rotor and the axial inflow and outflow connection can be carried out unchanged.
  • This configuration advantageously makes it possible to meet the high requirements of the spiral geometry with regard to geometry and dimensional tolerance. Due to the simple geometry of the lid, it can also be made from 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. This further reduces the installation space required.
  • An advantageous embodiment of the invention relates to the cross-sectional course of the spiral channel, in particular on the turbine side.
  • the cross section of the spiral channel can be widened by an axial and a radial expansion. If the expansion is achieved by radial expansion, the axial depth of the spiral channel is reduced. The outer circumference of the spiral channel increases. Since this circumference of the spiral duct on the turbine side is smaller than on the compressor side, there is enough space available in the radial direction. The entire housing can thus be made shorter.
  • a further advantageous variant relates to the rotational position of the spiral channels relative to one another. Due to the reduced axial depth of the spiral channels, any rotational position of the spiral channels relative to one another can be achieved. This is advantageous because for the tangential inflow and outflow nozzles there is often only one limited installation space is available. These can thus be arranged at any angle to one another. According to a particular embodiment, at least one tangential nozzle is angled parallel to the turbine shaft. The tangential nozzle is preferably angled against the respective cover side. This allows a core of the nozzle to be designed without undercuts. Spiral contour and the core of the nozzle can thus be produced by a tool part. A simple and economical manufacturability of the middle part of the housing is thereby achieved.
  • Another design provides for arranging the tangential nozzles at variable angles to the turbine shaft.
  • this variant can be implemented using sideshifts.
  • the possible angular range is approx. 0-90 °.
  • it is advantageously possible to make the incident angle of the tangential connecting piece to the turbine shaft variable.
  • one or both tangential nozzles are formed on the cover of the respective side.
  • this can be achieved in terms of production technology using a double-shell tool or with a sideshift.
  • the further possibility of adapting the tangential connecting piece to the geometry of the installation space is advantageous.
  • the parting plane present between the middle part of the housing and the cover is arranged essentially centrally in the flow cross section of the spiral channels.
  • a spiral channel can be arranged in its axial position towards the turbine shaft in a partial area essentially in the middle part of the housing and in a further partial area essentially in the cover. This advantageously makes it possible to use both the cover and the middle part of the housing for the arrangement of the spiral contours. This enables flow-optimized geometries to be formed.
  • FIG. 1 shows a turbo machine in full section
  • Figure 2 shows a further development of the turbomachine in full section
  • FIG. 3b shows a turbomachine according to FIG. 3a in a top view
  • Figure 3 c shows a turbo machine in full section
  • FIG. 3d shows a turbomachine according to FIG. 3c in a top view
  • FIG. 4 shows a perspective illustration of a middle part of the housing
  • FIG. 5a, b shows a sectional view through the middle part of the housing according to FIG. 4,
  • FIG. 6a, b show a schematic representation of two variants of a turbomachine in full section
  • FIG. 7 shows a schematic section of a turbomachine in full section
  • FIG. 8 shows a further schematic section of a turbomachine in full section
  • FIG. 9 shows a further variant of a turbomachine in full section.
  • a flow machine 10 according to the invention is shown in full section in FIG. 1, in which a turbine shaft 12 is mounted in a central housing middle part 11.
  • a compressor rotor 13 and a turbine rotor 14 on the opposite side are rigidly attached to the turbine shaft 12.
  • 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 clamped onto the middle part of the housing at planar parting planes 21, 22.
  • Spiral channels 17, 18 are formed in the middle part 11 of the housing; these spiral channels are closed on the cover sides at the planar parting planes 21, 22 by the covers 15, 16.
  • the middle part of the housing has a housing thickness a between the parting planes 21, 22.
  • the spiral channels 17, 18 change their circular cross-sectional area in the spiral course and overlap in the axial direction of the turbine shaft 12 with the dimension x in the area of the largest cross-sectional area.
  • an outflow connection 24 is arranged on a turbine-side outflow side 19
  • axial inflow connection 23 is arranged on a compressor-side inflow side.
  • FIG. 2 shows a further flow machine 10 in full section. Components corresponding to FIG. 1 are provided with the same reference symbols.
  • the spiral channels 17a, 18a are oval in the middle part of the housing. In the area of the maximum flow cross sections of the spiral channels 17a, 18a, these are dimension y spaced from each other.
  • FIG. 3a shows a further full section through a turbomachine 10. Components that correspond to the previous figures are provided with the same reference symbols.
  • a turbine-side inlet connection 25 and a compressor-side outlet connection 26 are shown.
  • the spiral channels 17, 18 are partially shown as dashed lines.
  • the two connecting pieces 25, 26 are arranged tangentially to the spiral channels 17, 18 and correspond to them.
  • FIG. 3b shows the middle part 11 of the housing according to FIG. 3a in a top view. Components corresponding to the previous figures are provided with the same reference symbols.
  • the course of the turbine-side spiral channel 17 is shown as a dashed line.
  • the middle section of the housing 11 is shown in partial section in the area of the compressor-side outflow connection.
  • the sockets 25, 26 are arranged at an angle of 180 ° to one another.
  • the housing thickness a (FIG. 3a) must be increased in order to avoid an overlap of the spiral channels 17, 18.
  • the connecting pieces 26, 25 of the middle part 11 of the housing are arranged at an angle of approximately 270 ° to one another by the two connecting pieces 25b, 26b crossing. This is the most unfavorable angular position because the housing thickness a is determined by the inner diameter c of the connecting pieces 25b, 26b. In order to minimize the housing thickness a in this angular position, the connecting pieces 25b, 26b are designed with an oval cross section in the crossing region.
  • FIG. 4 shows the middle part 11 of the housing viewed in perspective on the compressor side.
  • the dotted line shows the circular design of the compressor-side spiral duct 18 and the solid line shows the oval spiral duct 18b.
  • the oval design results in a larger width b over the entire geometry of the spiral channel 18b. This may require a larger case diameter. Because of the smaller cross-sectional area of the turbine-side spiral channel 17 (FIG. 3), only this can be made oval and thus wider. This makes it possible to produce a uniform housing diameter.
  • FIGS. 5a and 5b each show a partial section from the housing middle part 11 according to Figure 4 section CC and DD.
  • the width b of the oval spiral channel 18b is shown in relation to the width of the circular spiral channel 18 shown in dashed lines.
  • the turbomachine is shown schematically in full section in two variants.
  • the two tangential connections 125, 126 are angled at right angles to the parting planes 121, 122. Both outflow connections 125, 126 are directed against the side of their respective spiral channels 117, 118.
  • the two covers 115, 116 close the two spiral channels 117, 118 up to the area of the two connecting pieces 125, 126.
  • the spiral channels 117, 118 and the two connecting pieces 125, 126 are designed without undercuts. This allows a simple production method in the master molding process.
  • FIG. 1 A further variant of the fluid machine 10 is shown schematically in FIG.
  • the connecting piece 226 is arranged on the middle part 211 of the housing and angled at right angles to the parting 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 middle part 211 of the housing can be produced, for example, in the master molding process by a tool with a slide valve.
  • the middle housing part 211 is closed by the turbine cover 216.
  • FIG. 8 shows schematically the turbomachine 10.
  • the nozzle 326 is arranged on the cover 315 and corresponds to the spiral channel 317 at the parting plane 322.
  • the housing middle part 311 thus only forms the spiral contour 317 and can be done without the technically complicated nozzle 326 getting produced.
  • the middle housing part 311 is closed by the turbine cover 316.
  • FIG. 9 shows a turbomachine 10 on which the separating plane 22 runs essentially centrally through the cross section of the compressor-side spiral channel 18b.
  • the spiral duct 18b runs parallel to the parting plane 22 in the compressor cover 15 and angled to the parting plane 22 in the middle part 11 of the housing.
  • the parting plane 22 in the exemplary embodiment shown is arranged centrally only in a partial region in the spiral duct 18b.
  • the geometrically simple part can be formed, for example, by a simple planar groove in the compressor cover 15 and the geometrically complex and precise shape can be placed in the middle part 11 of the housing.
  • the two covers 15, 16 are preferably made of a plastic, the housing middle part 11 preferably being made of a metallic material.

Abstract

The invention relates to a non-positive-displacement machine (10), particularly a turbomachine for producing a mass flow, comprising a housing middle part (11), inside of which a turbine shaft (12) is mounted. A turbine housing is mounted on the housing middle part (11) on a turbine side and is mounted on a compressor side of a compressor housing. The spiral channels (17, 18) required for the compressor side and for the turbine side can be placed in a partial area inside the covers (15, 16) and at least in one partial area inside the housing middle part (11). This permits the contours, which are required for the spiral channels (17, 18) and which are geometrically complex, to be made in the housing middle part (11).

Description

Beschreibung STRÖMUNGSMASCHINE MIT EINEM IM GEHÄUSEMITTELTEIL VORGESEHENEN SPIRALKANAL Description FLOWING MACHINE WITH A SPIRAL CHANNEL PROVIDED IN THE HOUSING PART
[001] 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.
[002] 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 Turbinen- schaufeln 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 tan gentialen 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 DE 10297203 -. is known a turbine housing for an exhaust gas turbocharger, in which a turbine rotor driven by exhaust gases drives a compressor rotor. The compressor rotor is connected to the turbine rotor by a rigid shaft. 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 spiraling, narrowing contour of the turbine housing and is directed specifically to turbine blades of the turbine rotor. The turbine rotor is driven by these turbine blades. The exhaust gas 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 tan gential outflow. The spiral channels require a high level of geometry and surface. In the design shown, the spiral channels are formed in a turbine housing and a compressor housing. These two housings are flanged to the side of a middle part of the housing. Due to the shape, this configuration can only be produced with a high level of manufacturing complexity.
[003] 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 in such a way that the production of the spiral channels can be simplified.
[004] Diese Aufgabe wird durch die Merkmale des Patentanspruches 1 gelöst.This object is solved by the features of claim 1.
[005] Vorteile der ErfindungAdvantages of the invention
[006] Die erfindungsgemäße Anordnung der Strömungsmaschine beruht auf der Verlegung wenigstens eines Teiles 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, wobei der Deckel den zweiten Teil der Spiralgeometrie bildet. Dadurch ist ein Cuerschnitt 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 arrangement of the turbomachine according to the invention is based on the laying of at least part of a spiral geometry in a middle part of the housing. As a result, this forms at least part of a turbine or a compressor housing. The spiral geometry is closed on the outside by a cover, the cover forming the second part of the spiral geometry. This defines a cross section of the spiral channel through the middle part of the housing and the cover. There is a parting plane between the cover and the middle part of the housing, which is oriented perpendicular to a turbine shaft mounted in the middle part of the housing.
[007] 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 for example be a turbo machine e.g. be 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.
[008] 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 allows a spiral contour to be laid in the central middle part of the housing, as a result of which the flow cross section of the spiral contour can be produced without undercuts in the primary molding process. Furthermore, the narrower design of the lid results in a reduced space requirement.
[009] Gemäß einer Ausgestaltung 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 one embodiment of the invention, the lid, on the area adjacent to the spiral contour, is made flat. The spiral contour is formed exclusively in the middle part of the housing. The contour corresponding to the turbine rotor and the axial inflow and outflow connection can be carried out unchanged.
[010] 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 configuration advantageously makes it possible to meet the high requirements of the spiral geometry with regard to geometry and dimensional tolerance. Due to the simple geometry of the lid, it can also be made from plastics, such as polyamide.
[011] 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 a 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. This further reduces the installation space required.
[012] Eine vorteilhafte Ausbildung der Erfindung betrifft den Querschnitts verlauf 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 course of the spiral channel, in particular on the turbine side. The cross section of the spiral channel can be widened by an axial and a radial expansion. If the expansion is achieved by radial expansion, the axial depth of the spiral channel is reduced. The outer circumference of the spiral channel increases. Since this circumference of the spiral duct on the turbine side is smaller than on the compressor side, there is enough space available in the radial direction. The entire housing can thus be made shorter.
[013] 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. [014] Gemäß einer besonderen Ausführungsform ist wenigstens ein tangentialer Stutzten 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.A further advantageous variant relates to the rotational position of the spiral channels relative to one another. Due to the reduced axial depth of the spiral channels, any rotational position of the spiral channels relative to one another can be achieved. This is advantageous because for the tangential inflow and outflow nozzles there is often only one limited installation space is available. These can thus be arranged at any angle to one another. According to a particular embodiment, at least one tangential nozzle is angled parallel to the turbine shaft. The tangential nozzle is preferably angled against the respective cover side. This allows a core of the nozzle to be designed without undercuts. Spiral contour and the core of the nozzle can thus be produced by a tool part. A simple and economical manufacturability of the middle part of the housing is thereby achieved.
[015] Eine weitere Gestaltungs weise 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 for arranging the tangential nozzles at variable angles to the turbine shaft. In terms of production technology, this variant can be implemented using sideshifts. The possible angular range is approx. 0-90 °. As a result, it is advantageously possible to make the incident angle of the tangential connecting piece to the turbine shaft variable.
[016] 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 a further embodiment, one or both tangential nozzles are formed on the cover of the respective side. In accordance with the angular design already mentioned, this can be achieved in terms of production technology using a double-shell tool or with a sideshift. The further possibility of adapting the tangential connecting piece to the geometry of the installation space is advantageous.
[017] In einer Weiterbildung der Erfindung ist die zwischen Gehäusemittelteil 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 further development of the invention, the parting plane present between the middle part of the housing and the cover is arranged essentially centrally in the flow cross section of the spiral channels. A spiral channel can be arranged in its axial position towards the turbine shaft in a partial area essentially in the middle part of the housing and in a further partial area essentially in the cover. This advantageously makes it possible to use both the cover and the middle part of the housing for the arrangement of the spiral contours. This enables flow-optimized geometries to be formed.
[018] 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 schutzfällige Ausführungen darstellen können, für die hier Schutz beansprucht wird. ZeichnungThese and other features of preferred developments of the invention emerge from the claims and also from the description and the drawing, the individual features individually or in groups in the form of sub-combinations in the embodiment of the invention and in other areas be realized and can represent advantageous as well as protection-sensitive versions for which protection is claimed here. drawing
[019] Weitere Einzelheiten der Erfindung werden in der Zeichnung anhand von schematischen Ausführungsbeispielen beschrieben. Hierbei zeigenFurther details of the invention are described in the drawing using schematic exemplary embodiments. Show here
[020] Figur 1 eine Strömungsmaschine im Vollschnitt, [021] Figur 2 eine Weiterentwicklung der Strömungsmaschine im Vollschnitt[020] FIG. 1 shows a turbo machine in full section, Figure 2 shows a further development of the turbomachine in full section
[022] Figur 3 a eine Strömungsmaschine im Vollschnitt,3 a shows a turbomachine in full section,
[023] Figur 3b eine Strömungsmaschine gemäß Figur 3a in der Draufsicht,3b shows a turbomachine according to FIG. 3a in a top view,
[024] Figur 3 c eine Strömungsmaschine im VollschnittFigure 3 c shows a turbo machine in full section
[025] Figur 3d eine Strömungsmaschine gemäß Figur 3c in der Draufsicht,FIG. 3d shows a turbomachine according to FIG. 3c in a top view,
[026] Figur 4 eine perspektivische Darstellung eines Gehäusemittelteiles,[026] FIG. 4 shows a perspective illustration of a middle part of the housing,
[027] Figur 5a, b eine Schnittdarstellung durch das Gehäusemittelteils gemäß Figur 4,[027] FIG. 5a, b shows a sectional view through the middle part of the housing according to FIG. 4,
[028] Figur 6a, b eine schematische Darstellung zweier Varianten einer Strömungsmaschine im Vollschnitt, [029] Figur 7 einen schematischen Ausschnitt einer Strömungsmaschine im Vollschnitt,6a, b show a schematic representation of two variants of a turbomachine in full section, [029] FIG. 7 shows a schematic section of a turbomachine in full section,
[030] Figur 8 einen weiteren schematischen Ausschnitt einer Strömungsmaschine im Vollschnitt, [031] Figur 9 eine weitere Variante einer Strömungsmaschine im Vollschnitt.[030] FIG. 8 shows a further schematic section of a turbomachine in full section, [031] FIG. 9 shows a further variant of a turbomachine in full section.
[032] Beschreibung der AusführungsbeispieleDescription of the exemplary embodiments
[033] 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. [034] 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 Cuerschnittsfläche. 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. [035] 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 Ab- standsmaß 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. [036] 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 ver- dichterseitiger 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.A flow machine 10 according to the invention is shown in full section in FIG. 1, in which a turbine shaft 12 is mounted in a central housing middle part 11. A compressor rotor 13 and a turbine rotor 14 on the opposite side are rigidly attached to the turbine shaft 12. 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 clamped onto the middle part of the housing at planar parting planes 21, 22. Spiral channels 17, 18 are formed in the middle part 11 of the housing; these spiral channels are closed on the cover sides at the planar parting planes 21, 22 by the covers 15, 16. The middle part of the housing has a housing thickness a between the parting planes 21, 22. The spiral channels 17, 18 change their circular cross-sectional area in the spiral course and overlap in the axial direction of the turbine shaft 12 with the dimension x in the area of the largest cross-sectional area. On the turbine cover 16, an outflow connection 24 is arranged on a turbine-side outflow side 19, and on the compressor cover 15 a 20 axial inflow connection 23 is arranged on a compressor-side inflow side. FIG. 2 shows a further flow machine 10 in full section. Components corresponding to FIG. 1 are provided with the same reference symbols. In contrast to FIG. 1, the spiral channels 17a, 18a are oval in the middle part of the housing. In the area of the maximum flow cross sections of the spiral channels 17a, 18a, these are dimension y spaced from each other. This oval design of the spiral channels 17a, 18a does not have to take place over the entire length, but can also be formed only in the area of the largest cross-sectional area or only on one side of the housing. Due to the oval shape of the spiral channels 17a, 18a, the housing thickness a can be reduced. FIG. 3a shows a further full section through a turbomachine 10. Components that correspond to the previous figures are provided with the same reference symbols. A turbine-side inlet connection 25 and a compressor-side outlet connection 26 are shown. The spiral channels 17, 18 are partially shown as dashed lines. The two connecting pieces 25, 26 are arranged tangentially to the spiral channels 17, 18 and correspond to them.
[037] 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.3b shows the middle part 11 of the housing according to FIG. 3a in a top view. Components corresponding to the previous figures are provided with the same reference symbols. The course of the turbine-side spiral channel 17 is shown as a dashed line. The middle section of the housing 11 is shown in partial section in the area of the compressor-side outflow connection. The sockets 25, 26 are arranged at an angle of 180 ° to one another.
[038] 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. 3a) must be increased in order to avoid an overlap of the spiral channels 17, 18.
[039] 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 FIGS. 3c and 3d, the connecting pieces 26, 25 of the middle part 11 of the housing are arranged at an angle of approximately 270 ° to one another by the two connecting pieces 25b, 26b crossing. This is the most unfavorable angular position because the housing thickness a is determined by the inner diameter c of the connecting pieces 25b, 26b. In order to minimize the housing thickness a in this angular position, the connecting pieces 25b, 26b are designed with an oval cross section in the crossing region.
[040] 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 Cuerschnittsfläche 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 of the housing viewed in perspective on the compressor side. The dotted line shows the circular design of the compressor-side spiral duct 18 and the solid line shows the oval spiral duct 18b. The oval design results in a larger width b over the entire geometry of the spiral channel 18b. This may require a larger case diameter. Because of the smaller cross-sectional area of the turbine-side spiral channel 17 (FIG. 3), only this can be made oval and thus wider. This makes it possible to produce a uniform housing diameter.
[041] Die Figuren 5a und 5b zeigen jeweils einen Teilausschnitt aus dem Gehäuse- mittelteil 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. [042] 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 Abströmstutzen 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.[041] FIGS. 5a and 5b each show a partial section from the housing middle part 11 according to Figure 4 section CC and DD. The width b of the oval spiral channel 18b is shown in relation to the width of the circular spiral channel 18 shown in dashed lines. In Figures 6a and 6b, the turbomachine is shown schematically in full section in two variants. On the middle part 111 of the housing, the two tangential connections 125, 126 are angled at right angles to the parting planes 121, 122. Both outflow connections 125, 126 are directed against the side of their respective spiral channels 117, 118. The two covers 115, 116 close the two spiral channels 117, 118 up to the area of the two connecting pieces 125, 126. As a result, the spiral channels 117, 118 and the two connecting pieces 125, 126 are designed without undercuts. This allows a simple production method in the master molding process.
[043] 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.[043] A further variant of the fluid machine 10 is shown schematically in FIG. The connecting piece 226 is arranged on the middle part 211 of the housing and angled at right angles to the parting 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 middle part 211 of the housing can be produced, for example, in the master molding process by a tool with a slide valve. On the turbine side, the middle housing part 211 is closed by the turbine cover 216.
[044] 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.[044] FIG. 8 shows schematically the turbomachine 10. The nozzle 326 is arranged on the cover 315 and corresponds to the spiral channel 317 at the parting plane 322. The housing middle part 311 thus only forms the spiral contour 317 and can be done without the technically complicated nozzle 326 getting produced. On the turbine side, the middle housing part 311 is closed by the turbine cover 316.
[045] 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.FIG. 9 shows a turbomachine 10 on which the separating plane 22 runs essentially centrally through the cross section of the compressor-side spiral channel 18b. The spiral duct 18b runs parallel to the parting plane 22 in the compressor cover 15 and angled to the parting plane 22 in the middle part 11 of the housing. For this reason, the parting plane 22 in the exemplary embodiment shown is arranged centrally only in a partial region in the spiral duct 18b. The geometrically simple part can be formed, for example, by a simple planar groove in the compressor cover 15 and the geometrically complex and precise shape can be placed in the middle part 11 of the housing.
[046] Die beiden Deckel 15, 16 sind vorzugsweise aus einem Kunststoff hergestellt wobei das Gehäusemittelteil 11 vorzugsweise aus einem metallischen Werkstoff gebildet ist. [046] The two covers 15, 16 are preferably made of a plastic, the housing middle part 11 preferably being made of a metallic material.

Claims

Ansprüche [001] Strömungsmaschine insbesondere eine Turbomaschine zur Erzeugung eines Massenstromes, aufweisend ein Gehäusemittelteil in welchem eine Turbinenwelle gelagert ist, wobei das Gehäusemittelteil als Teil eines Turbinengehäuses an der Turbinenseite und an einer Verdichterseite als Teil eines Verdichtergehäuses angeformt ist, wobei an der Turbinenseite in tangentialer Richtung der Turbinenwelle, am Gehäusemittelteil ein Anströmstutzen und in axialer Richtung am Turbinengehäuse ein Abströmstutzen angeordnet sind, wobei an der Verdichterseite in tangentialer Richtung am Gehäusemittelteil, ein Abströmstutzen und am Verdichtergehäuse in axialer Richtung ein Anströmstutzen angeordnet sind, wobei auf der Verdichterseite und/oder auf der Turbinenseite jeweils ein Deckel vorgesehen ist, und der Deckel als Teil des Gehäuses gestaltet ist und im Gehäusemittelteil der Spiralkanal für die Turbinenseite und /oder die Verdichterseite vorgesehen ist. Fluid machine, in particular a turbomachine for generating a mass flow, comprising a middle housing part in which a turbine shaft is mounted, the middle housing part being formed as part of a turbine housing on the turbine side and on a compressor side as part of a compressor housing, being tangential on the turbine side Direction of the turbine shaft, an inflow socket on the middle part of the housing and an outflow socket in the axial direction on the turbine housing, an inflow socket being arranged on the compressor side in the tangential direction on the middle part of the housing, an outflow socket and on the compressor housing in the axial direction, with on the compressor side and / or on a cover is provided on the turbine side, and the cover is designed as part of the housing, and the spiral channel for the turbine side and / or the compressor side is provided in the middle part of the housing.
[002] Strömungsmaschine nach Anspruch 1, wobei der Deckel zum Gehäusemittelteil hin im Wesentlichen planförmig gestaltet ist.Fluid machine according to claim 1, wherein the cover is designed to be substantially planar towards the middle part of the housing.
[003] Strömungsmaschine nach einem der vorhergehenden Ansprüche, wobei beide Spiralkanäle durch Teile von Gehäusemittelteil und Deckel gebildet sind.Fluid machine according to one of the preceding claims, wherein both spiral channels are formed by parts of the housing middle part and cover.
[004] Strömungsmaschine nach einem der vorhergehenden Ansprüche, wobei der Spiralkanal insbesondere an der Turbinenseite, eine bestimmte maximale Tiefe in Richtung der Turbinenwelle aufweisen, wobei eine Veränderung des Querschnittes durch eine Aufweitung des Spiralkanals in radialer Richtung zur Turbinenwelle erfolgen kann.Fluid machine according to one of the preceding claims, wherein the spiral channel, in particular on the turbine side, have a certain maximum depth in the direction of the turbine shaft, wherein a change in the cross section can take place by widening the spiral channel in the radial direction to the turbine shaft.
[005] Strömungsmaschine nach Anspruch 4 wobei die Spiralkanäle aufgrund ihrer bestimmten maximalen Tiefe in beliebiger rotatorischer Position zueinander angeordnet sind, wodurch die tangentialen Stutzen in beliebigen Winkel zueinander positionierbar sind.Fluid machine according to claim 4, wherein the spiral channels are arranged due to their certain maximum depth in any rotational position to each other, whereby the tangential nozzle can be positioned at any angle to each other.
[006] Strömungsmaschine nach einem der vorhergehenden Ansprüche, wobei wenigstens ein Stutzen abgewinkelt ist und parallel zur Turbinenwelle verläuftFluid machine according to one of the preceding claims, wherein at least one nozzle is angled and runs parallel to the turbine shaft
[007] Strömungsmaschine nach Anspruch 6, wobei die tangentialen Stutzen in einem variablen Winkel zur Achse der Turbinenwelle angeordnet sind. [008] Strömungsmaschine nach einem der vorhergehenden Ansprüche, wobei die tangentialen Stutzen am Deckel der Turbinenseite und/oder am Deckel der Verdichterseite angeordnet sind.Fluid machine according to claim 6, wherein the tangential nozzle are arranged at a variable angle to the axis of the turbine shaft. Turbomachine according to one of the preceding claims, wherein the tangential nozzles are arranged on the cover of the turbine side and / or on the cover of the compressor side.
[009] Strömungsmaschine nach Anspruch 1, wobei eine Trennebene zwischen Deckel und Gehäusemittelteil im Wesentlichen mittig im Qierschnitt des Spiralkanales liegt. Fluid machine according to claim 1, wherein a parting plane between the cover and the middle part of the housing lies substantially centrally in the cross-section of the spiral channel.
EP04818152A 2003-11-04 2004-11-03 Non-positive-displacement machine comprising a spiral channel provided in the housing middle part Active EP1706595B1 (en)

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DE502004011691D1 (en) 2010-11-04
US20080034754A1 (en) 2008-02-14
US8062006B2 (en) 2011-11-22
ATE482326T1 (en) 2010-10-15

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