EP2002084B1 - Rotary pump and vane for a rotary pump - Google Patents

Rotary pump and vane for a rotary pump Download PDF

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Publication number
EP2002084B1
EP2002084B1 EP06818881A EP06818881A EP2002084B1 EP 2002084 B1 EP2002084 B1 EP 2002084B1 EP 06818881 A EP06818881 A EP 06818881A EP 06818881 A EP06818881 A EP 06818881A EP 2002084 B1 EP2002084 B1 EP 2002084B1
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EP
European Patent Office
Prior art keywords
vane
truss
wing
tip
main body
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EP06818881A
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German (de)
French (fr)
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EP2002084A1 (en
Inventor
Willi Schneider
Martin Thoma
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Joma Polytec GmbH
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Joma Polytec GmbH
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Publication of EP2002084A1 publication Critical patent/EP2002084A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2/00—Rotary-piston machines or pumps
    • F04C2/30—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members
    • F04C2/34—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members
    • F04C2/344—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member
    • F04C2/3441—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member the inner and outer member being in contact along one line or continuous surface substantially parallel to the axis of rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C21/00—Component parts, details or accessories not provided for in groups F01C1/00 - F01C20/00
    • F01C21/08—Rotary pistons
    • F01C21/0809—Construction of vanes or vane holders

Definitions

  • the invention relates to a wing for a rotor pump with a pump housing and a rotor rotatably mounted therein, wherein the wing is slidably mounted in the rotor and rests with its protruding from the rotor, provided on a wing body wing tip on an inner peripheral surface of the pump housing, wherein the wing tip a is separate component and continues the wing body in the longitudinal direction.
  • the invention also relates to a rotor pump for such a wing.
  • Rotor pumps with wings which have a framework structure, are for example from DE 10 2004 034 921 B3 and the DE 10 2004 034 925 B3 known.
  • the longitudinal axis of the framework extends both transversely to the longitudinal axis of the wing and in the width direction, that is parallel to the axis of rotation of the rotor. It has been shown that in the truss penetrated liquid, such as lubricating oil, accumulates in the framework and accumulated there.
  • a vacuum pump with a housing and a blade is known, which has cavities.
  • the manufacture of this wing is complex.
  • the invention has for its object to provide a rotor pump and / or a wing of the type mentioned, which is easy to manufacture and is insensitive to the ingress of lubricating oil.
  • the axis of the truss that is, the longitudinal axis of the half-timbered chambers is parallel to the longitudinal axis of the wing.
  • the advantage is created that liquid in the wing is thrown along the half-timbered chambers in the direction of the wing tips and does not accumulate in the wing. This also creates a simple way of lubricating the pump room.
  • the truss has at least one internal compartment wall.
  • This internal compartment wall extends in the longitudinal direction of the wing and divides this into at least two half-timbered chambers whose longitudinal axes also extend parallel to the longitudinal axis of the wing.
  • the compartment wall has a deviating from 0 ° and from 90 ° angle to the external compartment walls or outer walls of the wing.
  • the internal compartment wall thus runs transversely or obliquely to the outer walls.
  • the internal compartment walls are laid so that bending forces are optimally supported.
  • the internal or a part of the internal compartment walls may also extend parallel to the outer walls.
  • the wing body is an injection molded part.
  • the wing body is made of plastic and is produced for example in an extruding machine as a continuous strand.
  • the wing body is an extrusion element.
  • the wing body is made of aluminum, for example, and also leaves as Endlosteil the continuous casting machine.
  • Such manufacturing methods are relatively inexpensive and the wing can be manufactured with high accuracy.
  • the wing body can be cut to length from an endless profile to the desired length. This is done for example by sawing or cutting by means of laser beam or water jet.
  • the assembly of the wing is done in a simple manner, that the wing tip is inserted at the free end of the wing body in the truss.
  • the truss thus serves to accommodate a portion of the wing tip, which is held in this way backlash and non-positive.
  • the wing tip of the cross-sectional shape of the or the chambers of the framework corresponding insertion pin.
  • the wing tip may also be provided with only a single insertion pin, which ensures the secure attachment of the wing tip on the wing body.
  • the one or more insertion pins are hollow.
  • the pin may be provided with one or more outflow openings, over which accumulating lubricating oil flows, these outflow openings preferably not open into the suction or pressure chamber, but in the adjacent to the wing tip boundary wall.
  • At least one insertion pin has a recess or recess on its outer surface to be introduced into a chamber and resting on the inner wall of the chamber.
  • This depression or recess has the advantage that the weight continues is reduced, but that also the depression or recess for anchoring the wing tip can be used on the wing body.
  • the plugged-in with the pin of the recess or recess region of the chamber is hineinverformbar in the recess or recess.
  • the region of the chamber opposite the indentation or recess when the spigot is inserted has a latching element which can be latched into the recess or recess.
  • This variant has the advantage that after inserting the pin in the half-timbered chamber no further step is required, since the fixation of the wing tip on the wing body automatically takes place in that the two components lock together.
  • the latching connection can be designed so that the wing tip can also be released again from the wing body, so the locking connection is a releasable latching connection.
  • the locking element is a projection or an elastic latching hook, which is formed by a tab which is U-shaped cut and slightly protruding in the direction of the depression.
  • the recess or recess may be provided on the wing body, the wing tip then having the locking element.
  • the depression or recess as well as the region lying opposite may be provided on the longitudinal broad side and / or on the longitudinal narrow side of the wing, the longitudinal broad side being preferred, since the longitudinal narrow side has a sealing function and the area may possibly have a disturbing effect.
  • the wing body and / or the wing tip may be made of metal, ceramic, plastic or a mixture thereof. It is used in each case the most suitable material, which seals well on the one hand, on the other hand has a low tendency to wear and yet allows a cheap and easy production of the wing.
  • the wing body is constructed in one piece and has at its two free ends in each case a wing tip.
  • the length of the wing can be easily adjusted by inserting spacers between the wing body and wing tip.
  • the invention also relates to a rotor pump with a wing having the above-mentioned features.
  • the rotor pump is preferably a vacuum pump.
  • FIG. 1 a total designed as a vacuum pump rotor pump, in which the housing 12 is shown without housing cover.
  • the housing 12 has a suction port 14, which opens into an interior 16.
  • this interior 16 is a generally designated 18 rotor in which a wing 20 is mounted orthogonal to the axis of rotation 22 slidably.
  • the rotor 18 passes through the housing 12, in particular a bottom 26 of the interior 16 via a drive opening 28, so that it can be driven from the outside via a rectangular section 30.
  • FIG. 2 shows a portion of the wing 20, which is composed of a wing body 32 and two wing tips 34.
  • the wing body 32 has transversely to its longitudinal direction 36 a truss structure with a truss 38 which extends in the longitudinal direction 36 within the wing body 32.
  • the truss 38 has inner compartment walls 40, 42 and 44, which also extend parallel to the longitudinal direction 36.
  • the compartment walls 40, 42 and 44 are surrounded by external compartment walls or outer walls 46 and form 48 with these specialist chambers.
  • the compartment wall 40 extends parallel to the adjacent outer wall 46 and perpendicular to the broad side walls of the wing body 32.
  • the compartment wall 42nd extends obliquely, that is, it is at a different from 0 ° or 90 ° angle to the outer walls 46.
  • the two compartment walls 40 and 42 have constant wall thicknesses.
  • the compartment wall 44 has a changing wall thickness, so that any forces acting unilaterally on the wing body 32 can be optimally supported.
  • the in the FIG. 2 shown inner compartment walls 40, 42 and 44 are to be understood only as an example.
  • the wing tip 34 has three insertion pins 50, 52 and 54, which engage in the compartment chambers 48.
  • the FIG. 3 shows the insertion pins 50, 52 and 54 for a regularly designed truss 38.
  • the insertion pins 50, 52 and 54 are hollow and continue the trays 48 to the inner end of the wing tip 34 continues.
  • the narrow side 56 of the wing tip 34 has an outlet opening 58, from which any lubricating or sealing oil, which is conveyed in the compartment chambers 48, can escape.
  • the insertion pin 54 is provided on its, the narrow side of the wing body 32 facing side with a recess 60, said depression 60 a portion 62 on the narrow side of the wing body 32 forming outer wall 46 opposite, when the wing tip 34 is inserted into the wing body 32.
  • the area 62 is designed with a smaller wall thickness and is pressed with inserted wing tip 34 in the direction of the depression 60, so that material of the wing body 32 is pressed into this depression 60. As a result, the wing tip 34 is fixed to the wing body 32.
  • the Einsteckzapfen 54 has a latching hook 64 which in a on the inside of the narrow side wall or outer wall 46 of the wing body 32nd provided, not shown depression or locking receptacle engages when the wing tip 34 is inserted into the wing body 32.
  • FIG. 4 shows a portion of the wing 20 with inserted into the wing body 32 wing tip 34, which is clearly seen that the compartment chambers 48 continue to the bottom of the wing tip 34, so that from there in a suitable manner, for example via an outlet opening 58, lubricant can flow out.
  • the wing tip 34 must be placed in order to complete the wing 20. In the case of repair, that is with worn wing tip 34, this only has to be subtracted from the wing body 32 and replaced by a new wing tip 34.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Rotary Pumps (AREA)

Abstract

The invention relates to a vane for a rotary pump comprising a pump housing and a rotor, mounted to rotate therein, the vane being mounted to be displaceable in the rotor and resting with its vane tip that protrudes from the rotor against an inner circumferential surface of the pump housing. The vane tip is a separate component and extends the tip base in the longitudinal direction thereof, the vane base having a framework structure at an angle to its longitudinal direction. The invention also relates to a rotary pump comprising said vane.

Description

Die Erfindung betrifft einen Flügel für eine Rotorpumpe mit einem Pumpengehäuse und einem darin drehbar gelagerten Rotor, wobei der Flügel verschieblich im Rotor gelagert ist und mit seiner aus dem Rotor herausragenden, an einem Flügelkörper vorgesehenen Flügelspitze an einer Innenumfangsfläche des Pumpengehäuses anliegt, wobei die Flügelspitze ein separates Bauteil ist und den Flügelkörper in dessen Längsrichtung fortsetzt. Die Erfindung betrifft außerdem eine Rotorpumpe für einen derartigen Flügel.The invention relates to a wing for a rotor pump with a pump housing and a rotor rotatably mounted therein, wherein the wing is slidably mounted in the rotor and rests with its protruding from the rotor, provided on a wing body wing tip on an inner peripheral surface of the pump housing, wherein the wing tip a is separate component and continues the wing body in the longitudinal direction. The invention also relates to a rotor pump for such a wing.

Rotorpumpen mit Flügel, welche eine Fachwerkstruktur aufweisen, sind zum Beispiel aus der DE 10 2004 034 921 B3 und der DE 10 2004 034 925 B3 bekannt. Dabei verläuft die Längsachse des Fachwerks sowohl quer zur Längsachse des Flügels als auch in Breitenrichtung, das heißt parallel zur Drehachse des Rotors. Dabei hat sich gezeigt, dass in das Fachwerk eingedrungene Flüssigkeit, zum Beispiel Schmieröl, sich im Fachwerk ansammelt und dort akkumuliert.Rotor pumps with wings, which have a framework structure, are for example from DE 10 2004 034 921 B3 and the DE 10 2004 034 925 B3 known. In this case, the longitudinal axis of the framework extends both transversely to the longitudinal axis of the wing and in the width direction, that is parallel to the axis of rotation of the rotor. It has been shown that in the truss penetrated liquid, such as lubricating oil, accumulates in the framework and accumulated there.

Aus der DE 100 59 275 A1 ist eine Vakuumpumpe mit einem Gehäuse und einem Flügel bekannt, welcher Hohlräume aufweist. Die Herstellung dieses Flügels ist aufwändig.From the DE 100 59 275 A1 For example, a vacuum pump with a housing and a blade is known, which has cavities. The manufacture of this wing is complex.

Der Erfindung liegt die Aufgabe zugrunde, eine Rotorpumpe und/oder einen Flügel der eingangs genannten Art bereitzustellen, der leicht herstellbar ist und der hinsichtlich eindringendem Schmieröl unempfindlich ist.The invention has for its object to provide a rotor pump and / or a wing of the type mentioned, which is easy to manufacture and is insensitive to the ingress of lubricating oil.

Diese Aufgabe wird erfindungsgemäß mit einem Flügel gelöst, der die Merkmale des Anspruchs 1 aufweist.This object is achieved with a wing having the features of claim 1.

Dies bedeutet, dass die Achse des Fachwerks, das heißt die Längsachse der Fachwerkkammern parallel zur Längsachse des Flügels verläuft. Hierdurch wird der Vorteil geschaffen, dass sich im Flügel befindende Flüssigkeit entlang der Fachwerkkammern in Richtung der Flügelspitzen geschleudert wird und sich nicht im Flügel ansammelt. Hierdurch wird auch eine einfache Möglichkeit der Schmierung des Pumpenraums geschaffen.This means that the axis of the truss, that is, the longitudinal axis of the half-timbered chambers is parallel to the longitudinal axis of the wing. As a result, the advantage is created that liquid in the wing is thrown along the half-timbered chambers in the direction of the wing tips and does not accumulate in the wing. This also creates a simple way of lubricating the pump room.

Bei einer Weiterbildung ist vorgesehen, dass das Fachwerk wenigstens eine interne Fachwand besitzt. Diese interne Fachwand erstreckt sich in Längsrichtung des Flügels und teilt diesen in mindestens zwei Fachwerkkammern auf, deren Längsachsen sich ebenfalls parallel zur Längsachse des Flügels erstrecken.In a further development it is provided that the truss has at least one internal compartment wall. This internal compartment wall extends in the longitudinal direction of the wing and divides this into at least two half-timbered chambers whose longitudinal axes also extend parallel to the longitudinal axis of the wing.

Dabei weist die Fachwand einen von 0° und von 90° abweichenden Winkel zu den externen Fachwänden oder Außenwänden des Flügels auf. Die interne Fachwand verläuft also quer oder schräg zu den Außenwänden. Die internen Fachwände sind so gelegt, dass Biegekräfte optimal abgestützt werden. Selbstverständlich können sich die internen oder ein Teil der internen Fachwände auch parallel zu den Außenwänden erstrecken.In this case, the compartment wall has a deviating from 0 ° and from 90 ° angle to the external compartment walls or outer walls of the wing. The internal compartment wall thus runs transversely or obliquely to the outer walls. The internal compartment walls are laid so that bending forces are optimally supported. Of course, the internal or a part of the internal compartment walls may also extend parallel to the outer walls.

Erfindungsgemäß ist der Flügelkörper ein Spritzgussteil. Dies bedeutet, dass der Flügelkörper aus Kunststoff besteht und zum Beispiel in einer Extrudiermaschine als Endlosstrang hergestellt wird.According to the invention, the wing body is an injection molded part. This means that the wing body is made of plastic and is produced for example in an extruding machine as a continuous strand.

Eine andere Variante der Erfindung sieht vor, dass der Flügelkörper ein Strangpresselement ist. Beim Stranggussteil ist der Flügelkörper zum Beispiel aus Aluminium hergestellt und verlässt ebenfalls als Endlosteil die Stranggießmaschine.Another variant of the invention provides that the wing body is an extrusion element. In the continuous casting, the wing body is made of aluminum, for example, and also leaves as Endlosteil the continuous casting machine.

Derartige Herstellverfahren sind relativ preiswert und der Flügel kann mit einer hohen Genauigkeit hergestellt werden.Such manufacturing methods are relatively inexpensive and the wing can be manufactured with high accuracy.

Mit Vorzug ist der Flügelkörper von einem Endlosprofil auf die gewünschte Länge ablängbar. Dies erfolgt zum Beispiel durch Sägen oder Schneiden mittels Laserstrahl oder Wasserstrahl.With preference the wing body can be cut to length from an endless profile to the desired length. This is done for example by sawing or cutting by means of laser beam or water jet.

Die Montage des Flügels erfolgt auf einfache Weise dadurch, dass die Flügelspitze am freien Ende des Flügelkörpers in das Fachwerk eingesteckt wird. Das Fachwerk dient also zur Aufnahme eines Teils der Flügelspitze, die auf diese Weise spielfrei und kraftschlüssig gehalten wird.The assembly of the wing is done in a simple manner, that the wing tip is inserted at the free end of the wing body in the truss. The truss thus serves to accommodate a portion of the wing tip, which is held in this way backlash and non-positive.

Hierfür weist bei einer bevorzugten Ausführungsform die Flügelspitze der Querschnittsform der oder den Kammern des Fachwerks entsprechende Einsteckzapfen auf. Selbstverständlich kann die Flügelspitze auch lediglich mit einem einzigen Einsteckzapfen versehen sein, der die sichere Befestigung der Flügelspitze am Flügelkörper gewährleistet.For this purpose, in a preferred embodiment, the wing tip of the cross-sectional shape of the or the chambers of the framework corresponding insertion pin. Of course, the wing tip may also be provided with only a single insertion pin, which ensures the secure attachment of the wing tip on the wing body.

Zur Gewichtsreduzierung ist vorgesehen, dass der oder die Einsteckzapfen hohl ausgebildet sind. Außerdem kann der Zapfen mit einer oder mehreren Abflussöffnungen versehen sein, über welche sich ansammelndes Schmieröl abfließt, wobei diese Abflussöffnungen bevorzugt nicht in den Saug- oder Druckraum ausmünden, sondern in die an der Flügelspitze seitlich anliegende Begrenzungswand.To reduce weight is provided that the one or more insertion pins are hollow. In addition, the pin may be provided with one or more outflow openings, over which accumulating lubricating oil flows, these outflow openings preferably not open into the suction or pressure chamber, but in the adjacent to the wing tip boundary wall.

Eine bevorzugte Ausführungsform sieht vor, dass wenigstens ein Einsteckzapfen an seiner in eine Kammer einzuführenden und an der Innenwand der Kammer anliegenden Außenfläche eine Einsenkung oder Ausnehmung aufweist. Diese Einsenkung oder Ausnehmung besitzt den Vorteil, dass das Gewicht weiter reduziert wird, dass aber auch die Einsenkung oder Ausnehmung zur Verankerung der Flügelspitze am Flügelkörper verwendet werden kann.A preferred embodiment provides that at least one insertion pin has a recess or recess on its outer surface to be introduced into a chamber and resting on the inner wall of the chamber. This depression or recess has the advantage that the weight continues is reduced, but that also the depression or recess for anchoring the wing tip can be used on the wing body.

Dies erfolgt bei einem bevorzugten Ausführungsbeispiel erfindungsgemäß dadurch, dass der bei eingestecktem Zapfen der Einsenkung oder Ausnehmung gegenüberliegende Bereich der Kammer in die Einsenkung oder Ausnehmung hineinverformbar ist. Nachdem die Flügelspitze am Flügelkörper montiert worden ist und sich der Zapfen in der Fachwerkkammer befindet, wird der der Einsenkung oder Ausnehmung gegenüberliegende Bereich zum Beispiel mittels eines Presswerkzeugs derart verformt, dass Material des Flügelkörpers in die Einsenkung oder Ausnehmung verdrängt wird. Die Flügelspitze ist dann unverlierbar am Flügelkörper befestigt. Diese Befestigung ist formschlüssig und/oder kraftschlüssig.This is done in a preferred embodiment according to the invention in that the plugged-in with the pin of the recess or recess region of the chamber is hineinverformbar in the recess or recess. After the wing tip has been mounted on the wing body and the pin is in the truss chamber, the area opposite the recess or recess is deformed, for example by means of a pressing tool, such that material of the wing body is displaced into the recess or recess. The wing tip is then captively attached to the wing body. This attachment is positive and / or non-positive.

Bei einer anderen Variante weist der bei eingestecktem Zapfen der Einsenkung oder Ausnehmung gegenüberliegende Bereich der Kammer ein in die Einsenkung oder Ausnehmung einrastbares Rastelement auf. Diese Variante besitzt den Vorteil, dass nach dem Einstecken des Zapfens in die Fachwerkkammer kein weiterer Arbeitsschritt erforderlich ist, da die Fixierung der Flügelspitze am Flügelkörper automatisch dadurch erfolgt, dass die beiden Bauteile miteinander verrasten. Dabei kann die Rastverbindung so gestaltet sein, dass die Flügelspitze auch wieder vom Flügelkörper gelöst werden kann, die Rastverbindung also eine lösbare Rastverbindung ist.In another variant, the region of the chamber opposite the indentation or recess when the spigot is inserted has a latching element which can be latched into the recess or recess. This variant has the advantage that after inserting the pin in the half-timbered chamber no further step is required, since the fixation of the wing tip on the wing body automatically takes place in that the two components lock together. In this case, the latching connection can be designed so that the wing tip can also be released again from the wing body, so the locking connection is a releasable latching connection.

Erfindungsgemäß ist bei einer bevorzugten Ausführungsform das Rastelement ein Vorsprung oder ein elastischer Rasthaken, der von einem Lappen gebildet wird, der U-förmig ausgeschnitten und geringfügig in Richtung der Einsenkung vorsteht. Selbstverständlich können auch die Einsenkung oder Ausnehmung am Flügelkörper vorgesehen sein, wobei die Flügelspitze dann das Rastelement aufweist.According to the invention, in a preferred embodiment, the locking element is a projection or an elastic latching hook, which is formed by a tab which is U-shaped cut and slightly protruding in the direction of the depression. Of course, the recess or recess may be provided on the wing body, the wing tip then having the locking element.

Die Einsenkung oder Ausnehmung sowie der gegenüber liegende Bereich können an der Längsbreitseite und/oder an der Längsschmalseite des Flügels vorgesehen sein, wobei die Längsbreitseite bevorzugt wird, da die Längsschmalseite eine Dichtfunktion besitzt und sich der Bereich eventuell als störend auswirkt.The depression or recess as well as the region lying opposite may be provided on the longitudinal broad side and / or on the longitudinal narrow side of the wing, the longitudinal broad side being preferred, since the longitudinal narrow side has a sealing function and the area may possibly have a disturbing effect.

Gemäß einem bevorzugten Ausführungsbeispiel können der Flügelkörper und/oder die Flügelspitze aus Metall, aus Keramik, aus Kunststoff oder einer Mischung hiervon bestehen. Es wird jeweils das geeignetste Material verwendet, welches zum einen gut abdichtet, zum anderen eine geringe Verschleißneigung besitzt und welches dennoch eine preiswerte und einfache Herstellung des Flügels erlaubt.According to a preferred embodiment, the wing body and / or the wing tip may be made of metal, ceramic, plastic or a mixture thereof. It is used in each case the most suitable material, which seals well on the one hand, on the other hand has a low tendency to wear and yet allows a cheap and easy production of the wing.

Bevorzugt ist der Flügelkörper einteilig aufgebaut und besitzt an seinen beiden freien Enden jeweils eine Flügelspitze. Die Länge des Flügels kann auf einfache Weise durch Einlegen von Distanzscheiben zwischen Flügelkörper und Flügelspitze eingestellt werden.Preferably, the wing body is constructed in one piece and has at its two free ends in each case a wing tip. The length of the wing can be easily adjusted by inserting spacers between the wing body and wing tip.

Die Erfindung betrifft auch eine Rotorpumpe mit einem Flügel, der die oben genannten Merkmale aufweist. Dabei ist die Rotorpumpe in bevorzugter Weise eine Vakuumpumpe.The invention also relates to a rotor pump with a wing having the above-mentioned features. In this case, the rotor pump is preferably a vacuum pump.

Weitere Vorteile, Merkmale und Einzelheiten der Erfindung ergeben sich aus den Unteransprüchen sowie der nachfolgenden Beschreibung, in der unter Bezugnahme auf die Zeichnung ein besonders bevorzugtes Ausführungsbeispiel im Einzelnen beschrieben ist. Dabei können die in der Zeichnung dargestellten sowie in der Beschreibung und in den Ansprüchen erwähnten Merkmale jeweils einzeln für sich oder in beliebiger Kombination erfindungswesentlich sein.Further advantages, features and details of the invention will become apparent from the subclaims and the following description in which, with reference to the drawing, a particularly preferred embodiment is described in detail. The features shown in the drawing and mentioned in the description and in the claims may each be essential to the invention individually or in any combination.

In der Zeichnung zeigen:

Figur 1
eine Explosionsdarstellung einer Rotorpumpe;
Figur 2
einen Teil eines Flügels mit vom Flügelkörper abgezogener Flügelspitze;
Figur 3
eine perspektivische Darstellung der Figur 2 mit einer anderen Blickrichtung; und
Figur 4
einen Teil des Flügels teilweise aufgeschnitten.
In the drawing show:
FIG. 1
an exploded view of a rotor pump;
FIG. 2
a part of a wing with wing tip removed from the wing body;
FIG. 3
a perspective view of FIG. 2 with a different perspective; and
FIG. 4
Part of the wing partially cut open.

In der Figur 1 ist mit dem Bezugszeichen 10 insgesamt eine als Vakuumpumpe ausgebildete Rotorpumpe bezeichnet, bei welcher das Gehäuse 12 ohne Gehäusedeckel dargestellt ist. Das Gehäuse 12 besitzt einen Sauganschluss 14, der in einen Innenraum 16 mündet. In diesem Innenraum 16 befindet sich ein insgesamt mit 18 bezeichneter Rotor, in welchem ein Flügel 20 orthogonal zur Drehachse 22 verschieblich gelagert ist. Der Rotor 18 durchgreift das Gehäuse 12, insbesondere einen Boden 26 des Innenraums 16 über eine Antriebsöffnung 28, so dass er von außen über einen rechteckförmigen Abschnitt 30 angetrieben werden kann.In the FIG. 1 is denoted by the reference numeral 10 a total designed as a vacuum pump rotor pump, in which the housing 12 is shown without housing cover. The housing 12 has a suction port 14, which opens into an interior 16. In this interior 16 is a generally designated 18 rotor in which a wing 20 is mounted orthogonal to the axis of rotation 22 slidably. The rotor 18 passes through the housing 12, in particular a bottom 26 of the interior 16 via a drive opening 28, so that it can be driven from the outside via a rectangular section 30.

Die Figur 2 zeigt einen Teil des Flügels 20, der von einem Flügelkörper 32 und zwei Flügelspitzen 34 aufgebaut ist. Der Flügelkörper 32 besitzt quer zu dessen Längsrichtung 36 eine Fachwerkstruktur mit einem Fachwerk 38, welches sich in Längsrichtung 36 innerhalb des Flügelkörpers 32 erstreckt. Das Fachwerk 38 weist innere Fachwände 40, 42 und 44 auf, die sich ebenfalls parallel zur Längsrichtung 36 erstrecken. Die Fachwände 40, 42 und 44 sind von externen Fachwänden oder Außenwänden 46 umgeben und bilden mit diesen Fachkammern 48.The FIG. 2 shows a portion of the wing 20, which is composed of a wing body 32 and two wing tips 34. The wing body 32 has transversely to its longitudinal direction 36 a truss structure with a truss 38 which extends in the longitudinal direction 36 within the wing body 32. The truss 38 has inner compartment walls 40, 42 and 44, which also extend parallel to the longitudinal direction 36. The compartment walls 40, 42 and 44 are surrounded by external compartment walls or outer walls 46 and form 48 with these specialist chambers.

Dabei erstreckt sich die Fachwand 40 parallel zur benachbarten Außenwand 46 und senkrecht zu den Breitseitenwänden des Flügelkörpers 32. Die Fachwand 42 verläuft schräg, das heißt sie steht unter einem von 0° beziehungsweise von 90° abweichenden Winkel zu den Außenwänden 46. Die beiden Fachwände 40 und 42 weisen gleichbleibende Wanddicken auf. Die Fachwand 44 besitzt eine sich verändernde Wanddicke, so dass eventuell auftretende, einseitig auf den Flügelkörper 32 einwirkende Kräfte optimal abgestützt werden können. Die in der Figur 2 dargestellten inneren Fachwände 40, 42 und 44 sollen nur beispielhaft verstanden werden.In this case, the compartment wall 40 extends parallel to the adjacent outer wall 46 and perpendicular to the broad side walls of the wing body 32. The compartment wall 42nd extends obliquely, that is, it is at a different from 0 ° or 90 ° angle to the outer walls 46. The two compartment walls 40 and 42 have constant wall thicknesses. The compartment wall 44 has a changing wall thickness, so that any forces acting unilaterally on the wing body 32 can be optimally supported. The in the FIG. 2 shown inner compartment walls 40, 42 and 44 are to be understood only as an example.

Die Flügelspitze 34 weist drei Einsteckzapfen 50, 52 und 54 auf, welche in die Fachkammern 48 eingreifen. Die Figur 3 zeigt die Einsteckzapfen 50, 52 und 54 für ein regelmäßig ausgestaltetes Fachwerk 38. Die Einsteckzapfen 50, 52 und 54 sind hohl ausgeführt und setzen die Fachkammern 48 bis ans innere Ende der Flügelspitze 34 fort. Wie aus der Figur 2 ersichtlich, weist die Schmalseite 56 der Flügelspitze 34 eine Austrittsöffnung 58 auf, aus welcher eventuelles Schmier- oder Dichtöl, welches in den Fachkammern 48 gefördert wird, austreten kann.The wing tip 34 has three insertion pins 50, 52 and 54, which engage in the compartment chambers 48. The FIG. 3 shows the insertion pins 50, 52 and 54 for a regularly designed truss 38. The insertion pins 50, 52 and 54 are hollow and continue the trays 48 to the inner end of the wing tip 34 continues. Like from the FIG. 2 can be seen, the narrow side 56 of the wing tip 34 has an outlet opening 58, from which any lubricating or sealing oil, which is conveyed in the compartment chambers 48, can escape.

Der Einsteckzapfen 54 ist an seiner, der Schmalseite des Flügelkörpers 32 zugewandten Seite mit einer Einsenkung 60 versehen, wobei diese Einsenkung 60 einem Bereich 62 an der die Schmalseite des Flügelkörpers 32 bildenden Außenwand 46 gegenüberliegt, wenn die Flügelspitze 34 in den Flügelkörper 32 eingesteckt ist. Der Bereich 62 ist mit einer geringeren Wanddicke ausgeführt und wird bei eingesteckter Flügelspitze 34 in Richtung der Einsenkung 60 verpresst, so dass Material des Flügelkörpers 32 in diese Einsenkung 60 hineingedrückt wird. Dadurch wird die Flügelspitze 34 am Flügelkörper 32 fixiert.The insertion pin 54 is provided on its, the narrow side of the wing body 32 facing side with a recess 60, said depression 60 a portion 62 on the narrow side of the wing body 32 forming outer wall 46 opposite, when the wing tip 34 is inserted into the wing body 32. The area 62 is designed with a smaller wall thickness and is pressed with inserted wing tip 34 in the direction of the depression 60, so that material of the wing body 32 is pressed into this depression 60. As a result, the wing tip 34 is fixed to the wing body 32.

In der Figur 3 besitzt der Einsteckzapfen 54 einen Rasthaken 64, der in eine an der Innenseite der Schmalseitenwand beziehungsweise Außenwand 46 des Flügelkörpers 32 vorgesehene, nicht dargestellte Einsenkung oder Rastaufnahme einrastet, wenn die Flügelspitze 34 in den Flügelkörper 32 eingeschoben ist.In the FIG. 3 the Einsteckzapfen 54 has a latching hook 64 which in a on the inside of the narrow side wall or outer wall 46 of the wing body 32nd provided, not shown depression or locking receptacle engages when the wing tip 34 is inserted into the wing body 32.

Die Figur 4 zeigt einen Teil des Flügels 20 mit in den Flügelkörper 32 eingeschobener Flügelspitze 34, wobei deutlich erkennbar ist, dass die Fachkammern 48 sich bis in den Grund der Flügelspitze 34 fortsetzen, so dass von dort in geeigneter Weise, zum Beispiel über eine Austrittsöffnung 58, Schmiermittel ausströmen kann. Außerdem ist erkennbar, dass nach dem Ablängen des Flügelkörpers 32 auf geeignete Länge lediglich die Flügelspitze 34 aufgesetzt werden muss, um den Flügel 20 fertig zu stellen. Im Reparaturfall, das heißt bei verschlissener Flügelspitze 34, muss diese lediglich vom Flügelkörper 32 abgezogen und gegen eine neue Flügelspitze 34 ausgetauscht werden.The FIG. 4 shows a portion of the wing 20 with inserted into the wing body 32 wing tip 34, which is clearly seen that the compartment chambers 48 continue to the bottom of the wing tip 34, so that from there in a suitable manner, for example via an outlet opening 58, lubricant can flow out. In addition, it can be seen that after cutting the blade body 32 to a suitable length only the wing tip 34 must be placed in order to complete the wing 20. In the case of repair, that is with worn wing tip 34, this only has to be subtracted from the wing body 32 and replaced by a new wing tip 34.

Claims (14)

  1. Vane (20), for a rotor pump (10) having a casing (12) and a rotor (18) which is rotatably mounted therein, the vane (20) being displaceably mounted in the rotor (18) and bearing against an inner circumferential surface of the pump casing (12) by its tip (34) which projects out of the rotor (18) and which is provided on a main body (32) of the vane, the tip (34) of the vane being a separate component and forming a continuation of the main body (32) of the vane in the longitudinal direction (36) of said main body (32), characterised in that the main body (32) of the vane is extruded or continuous cast and has, transversely to its longitudinal direction (36), a truss structure having walls (40, 42, 44) and compartments (48) extending in the longitudinal direction (36).
  2. Vane according to claim 1, characterised in that the truss (38) has at least one internal wall (40, 42, 44).
  3. Vane according to claim 2, characterised in that the internal wall (42) of the truss is at an angle other than 0° or 90° to the external walls of the truss or the outer walls (46) of the vane (20).
  4. Vane according to one of the preceding claims, characterised in that the main body (32) of the vane is cut to length from a continuous profile.
  5. Vane according to one of the preceding claims, characterised in that the tip (34) of the vane is inserted in the truss (38) at the free end of the main body (32) of the vane.
  6. Vane according to one of the preceding claims, characterised in that the tip (34) of the vane has spigots for insertion (50, 52, 54), and in particular hollow spigots for insertion (50, 52, 54), which correspond to the compartments (48) of the truss (38)
  7. Vane according to claim 6, characterised in that at least one spigot for insertion (54) has a depression (60) or opening in that one of its outer faces which is to be inserted in a compartment (48) of the truss and which is to rest against the inner wall of the compartment (48).
  8. Vane according to claim 7, characterised in that that region (62) of the compartment (48) of the truss which is situated opposite the depression (60) or opening when the spigots (54) are inserted can be deformed into the depression (60) or opening.
  9. Vane according to claim 7, characterised in that that region (62) of the compartment (48) of the truss which is situated opposite the depression (60) or opening when the spigots (54) are inserted has a latching member which is able to latch into the depression (60) or opening, the latching member being a projection or a resilient latching hook (64).
  10. Vane according to one claim 8 or 9, characterised in that the region (62) is situated on the wide longitudinal side and/or narrow longitudinal side of the main body (32) of the vane or of the tip (34) of the vane.
  11. Vane according to one of the preceding claims, characterised in that the main body (32) of the vane comprises metal, plastics material or a mixture thereof and/or the tip (34) of the vane comprises metal, ceramic material, plastics material or a mixture thereof.
  12. Vane according to one of the preceding claims, characterised in that two tips (34) of the vane are mounted on the main body (32) of the vane.
  13. Rotor pump (10) having a vane (20) according to one of the preceding claims.
  14. Rotor pump according to claim 13, characterised in that it is a vacuum pump.
EP06818881A 2006-03-31 2006-11-28 Rotary pump and vane for a rotary pump Active EP2002084B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200610016243 DE102006016243A1 (en) 2006-03-31 2006-03-31 Rotor pump`s e.g. vacuum pump, vane, has vane body comprising frame work structure with internal compartment walls transverse to longitudinal direction of vane, where internal compartment walls run in longitudinal axis
PCT/EP2006/011400 WO2007118504A1 (en) 2006-03-31 2006-11-28 Rotary pump and vane for a rotary pump

Publications (2)

Publication Number Publication Date
EP2002084A1 EP2002084A1 (en) 2008-12-17
EP2002084B1 true EP2002084B1 (en) 2012-01-04

Family

ID=37734858

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06818881A Active EP2002084B1 (en) 2006-03-31 2006-11-28 Rotary pump and vane for a rotary pump

Country Status (3)

Country Link
EP (1) EP2002084B1 (en)
DE (1) DE102006016243A1 (en)
WO (1) WO2007118504A1 (en)

Cited By (2)

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Publication number Priority date Publication date Assignee Title
DE202014005520U1 (en) 2014-07-08 2015-10-09 Joma-Polytec Gmbh Vane pump for generating a negative pressure
DE202014005521U1 (en) 2014-07-08 2015-10-09 Joma-Polytec Gmbh Vane pump for generating a negative pressure

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Publication number Priority date Publication date Assignee Title
ITTO20070764A1 (en) * 2007-10-26 2009-04-27 Vhit Spa SINGLE-PACK VACUUM PUMP

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GB191326604A (en) * 1913-11-19 1914-09-10 Selas Lighting Company Ltd Improvements relating to Rotary Pumps or Compressors.
DE898348C (en) * 1951-04-07 1953-11-30 Rudolf Bock Rotary piston compressor with double-walled compressor blades
DE1236879B (en) * 1961-10-17 1967-03-16 Karl Eickmann Working slide (wing) for rotary piston machines
DE2157450A1 (en) * 1971-11-19 1973-05-24 Eduard Dipl Ing Abadschieff FOUR-STROKE ROTOR MOTOR WITH HIGHER EFFICIENCY AND LESS PRODUCTION OF POISON GASES
GB2375374A (en) 1999-12-23 2002-11-13 Luk Automobiltech Gmbh & Co Kg Vacuum pump
ATE250722T1 (en) * 2000-03-15 2003-10-15 Joma Hydromechanic Gmbh DISPLACEMENT PUMP
US7048526B2 (en) * 2004-05-14 2006-05-23 1564330 Ontario Inc. Shared slot vane pump
DE102004064029B4 (en) * 2004-07-09 2008-04-10 Joma-Hydromechanic Gmbh A single-blade
DE102004034925B3 (en) 2004-07-09 2006-02-16 Joma-Hydromechanic Gmbh A single-blade
DE102004034919B3 (en) * 2004-07-09 2005-12-01 Joma-Hydromechanic Gmbh A single-blade

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202014005520U1 (en) 2014-07-08 2015-10-09 Joma-Polytec Gmbh Vane pump for generating a negative pressure
DE202014005521U1 (en) 2014-07-08 2015-10-09 Joma-Polytec Gmbh Vane pump for generating a negative pressure
DE102015211759A1 (en) 2014-07-08 2016-01-14 Joma-Polytec Gmbh Vane pump for generating a negative pressure

Also Published As

Publication number Publication date
WO2007118504A1 (en) 2007-10-25
EP2002084A1 (en) 2008-12-17
DE102006016243A1 (en) 2007-10-04

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