EP0205036B1 - Rotary vane pump - Google Patents

Rotary vane pump Download PDF

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Publication number
EP0205036B1
EP0205036B1 EP19860107221 EP86107221A EP0205036B1 EP 0205036 B1 EP0205036 B1 EP 0205036B1 EP 19860107221 EP19860107221 EP 19860107221 EP 86107221 A EP86107221 A EP 86107221A EP 0205036 B1 EP0205036 B1 EP 0205036B1
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EP
European Patent Office
Prior art keywords
vane
rotor
stop
wing
projection
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP19860107221
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German (de)
French (fr)
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EP0205036A2 (en
EP0205036A3 (en
Inventor
Robert Lange
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Oerlikon Barmag AG
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Barmag AG
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Publication date
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Publication of EP0205036A2 publication Critical patent/EP0205036A2/en
Publication of EP0205036A3 publication Critical patent/EP0205036A3/en
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Publication of EP0205036B1 publication Critical patent/EP0205036B1/en
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    • 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
    • F01C21/0881—Construction of vanes or vane holders the vanes consisting of two or more parts

Definitions

  • the invention relates to a vane pump according to the first part of claim 1.
  • Vane pumps In vane pumps, the vanes move radially back and forth. If the rotor is very eccentric in relation to the housing, considerable forces are required to reverse the direction of the blades. Vane pumps can be designed with particularly strong eccentricity if two vanes slide in a rotor slot, which are supported on one another by force transmitters with a radial force. Such a vane pump is such. B. known from Japanese utility model 26-6486.
  • the wings are supported relative to each other by springs which are attached between the hook head of one wing and the web foot of the other wing.
  • springs which are attached between the hook head of one wing and the web foot of the other wing.
  • the vane pump therefore has the disadvantage that insufficient forces are available to reverse the direction of movement of the vane at bottom dead center. This disadvantage also exists if, instead of the springs, another system is used to generate the wing's outward movement (see, for example, DE-A-3 507 176).
  • the invention has for its object in a vane pump, the rotor has only one guide slot in which two vanes, which are supported radially on each other by means of force, are radially movable, to reduce the forces exerted on the other vane and thereby reduce the forces to reduce the radial forces required and the wear caused by the power means.
  • the rotor is mounted eccentrically in the housing. Therefore, when the rotor rotates on the compression side, the blades execute a radial retraction movement until they have reached their radially innermost position at bottom dead center. At the bottom dead center, the direction of movement is reversed and from here the wing executes a radial extension movement over the area of the suction zone.
  • the rotor is preferably mounted in such a way that it forms a seal with the housing peripheral wall. The bottom dead center of the wing is therefore - if you look at the wing head - on the circumference of the rotor.
  • a vane pump is known from US-A-2 919 651, which is now to be regarded as the closest prior art, in which the radially outer region of each vane and the radially inner region of the wall of each guide slot act as a circumferential projection is trained.
  • these projections form a pressure chamber for receiving a pressure fluid, the projections not touching one another even in the dead center position of the wings.
  • the stops proposed according to the invention consist on the one hand of a groove and on the other hand of a projection. This pairing of groove and projection is provided in the pairing of the sliding surfaces with which the wings are guided in their slot.
  • the groove is provided in the sliding surface of the slot, while the wing has a projection on its sliding surface in the region of its head. This projection dips into the groove when bottom dead center is reached and strikes the bottom of the groove.
  • the stop i.e. the projection on the one hand and the groove on the other hand extend over the entire wing length.
  • the stop and groove only extend over a partial length and are preferably arranged in the central region of the wing length.
  • the stop is preferably a thickening in the form of a circular section arranged on the rear of the wing.
  • the groove is a corresponding depression in the wall of the rotor slot. With its straight cutting edge, the circular section is formed by the longitudinal edge of the wing protruding from the rotor slot. This lead and the corresponding lowering match each other with medium play. This configuration ensures that no undue air build-up can form at the bottom of the depression.
  • a certain amount of air congestion can be used for a preferred exemplary embodiment to dampen the wing movement.
  • the countersink is designed as a damping chamber, the projection as a damping piston.
  • the damping effect can be influenced in a targeted manner by preventing the air from lowering in the direction of the retracting movement - i.e. radial to the rotor - escapes, but that the bottom of the countersink is provided with holes which open on the outer circumference of the rotor and exert a desired throttling on the air escaping from the countersink.
  • a relief channel is provided which is radial connects the inner part of the groove to the suction side.
  • the relief channel can e.g. B. penetrate the rotor so that it opens before the bottom of the groove.
  • the rotoe 2 is rotatably mounted in the housing 1.
  • the rotor has a rotor slot 4. This extends from the end of the shaft 3 over the entire axial length of the rotor.
  • the resulting two rotor halves are molded onto the correspondingly thick shaft 3.
  • the inner channel 29, which penetrates the shaft and the rotor, serves to supply lubricating oil.
  • the inlet is designated with a check valve open in the inlet direction.
  • With 33 the outlet opening is designated.
  • a check valve lying in the outlet opening and opening in the outlet direction is not shown.
  • the blades 5 and 6 are slidably guided in the rotor slot 4.
  • the wings with their webs 9 and 10 lie on top of each other.
  • the thickness of the vanes 9 and 10 corresponds to the sum of the width of the rotor slot 4.
  • the ends of the vanes mesh with the cylindrical inner wall of the housing 1.
  • the ends are designed as hook heads 7.
  • the thickness of these hook heads also corresponds to the slot width.
  • the wing webs 9, 10 have recesses 50, 51 at their ends. In certain rotational positions, these recesses connect the so-called hook spaces 15.1 and 15.2 to the oil supply through the inner channel 29.
  • the hook spaces 15.1 and 15.2 are formed by the hook heads 7.8 and the web feet 14 of the wing webs 9, 10.
  • FIG. 1 shows the situation in the direction of rotation 22 in which the wing 5 approaches its bottom dead center position.
  • the wing 6 is moved radially outward by the pressure existing in the hook space 15.2, while the wing 5 still performs a rectified movement radially inward.
  • this direction of movement must reverse. For this it is necessary that there is a very high oil pressure in the hook space 15.2. This in turn would lead to a very strong contact of the wing 6 on the housing circumference.
  • a stop 60 is provided on the hook head of each wing and the rotor has grooves 61 which are aligned with the stop 60.
  • the radial length of the grooves is such that the stop strikes the bottom of the groove in the bottom dead center position of the wing.
  • Groove base or stop can also be designed as a spring, so that the energy required for decelerating the wing can be stored and used for the radial extension movement of the wing.
  • the bottom of the groove 61 is provided with a relief channel 62 which secantially penetrates the rotor.
  • the groove is connected to the suction chamber of the pump when the stop 60 is immersed, so that any air, liquid or oil quantities are sucked out of the groove.
  • this relief channel 62 By dimensioning the size of this relief channel 62, the fluid pressure that can be built up in the groove can be influenced in such a way that a desired resistance to damping is counteracted by the wing that moves into the bottom dead center position.
  • Fig. 3 shows the view of a wing from the back. It can be seen that the stop 60 of the embodiment shown in FIGS. 1 and 2 is designed as a thickening on the back of the wings 5 and 6 and has the shape of a circular section. The straight cutting edge of the circular section is formed by the upper edge of the wing, which meshes with the inner circumference of the housing.
  • a stop 60 is shown which extends as a bar over the entire length of the wing. Consequently, the groove 61 also has a corresponding shape. Likewise, relief channels 62 are again provided, through which the air can escape from the groove 61 with targeted throttling.
  • the invention succeeds in reducing the forces required to generate the radial movement of the vanes and thus the power loss of the pump and its wear. Furthermore, the pump works with the inventive measure noiseless.

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

Description

Die Erfindung betrifft eine Flügelzellenpumpe gemäß dem ersten Teil des Anspruchs 1.The invention relates to a vane pump according to the first part of claim 1.

Bei Flügelzellenpumpen führen die Flügel eine radiale Hin- und Herbewegung aus. Bei starker Exzentrizität des Rotors gegenüber dem Gehäuse werden für die Richtungsumkehr der Flügel erhebliche Kräfte benötigt. Flügelzellenpumpen lassen sich mit besonders starker Exzentrizität auslegen, wenn in einem Rotorschlitz zwei Flügel gleiten, die sich-durch Kraftgeber aufeinander mit einer radialen Kraft abstützen. Eine solche Flügelzellenpumpe ist z. B. durch die japanische Gebrauchsmusterschrift 26-6486 bekannt.In vane pumps, the vanes move radially back and forth. If the rotor is very eccentric in relation to the housing, considerable forces are required to reverse the direction of the blades. Vane pumps can be designed with particularly strong eccentricity if two vanes slide in a rotor slot, which are supported on one another by force transmitters with a radial force. Such a vane pump is such. B. known from Japanese utility model 26-6486.

Die Flügel sind relativ zueinander durch Federn abgestützt, welche zwischen dem Hakenkopf des einen und dem Stegfuß des anderen Flügels angebracht sind. Bei schnell drehenden Flügelzellenpumpen, insbesondere Flügelzellenvakuumpumpen, die in Kraftfahrzeugen zur Erzeugung eines Vakuums für Servoverbraucher, insbesondere Bremskraftverstärker, Anwendung finden, führt die durch die Federn ausgeübte Kraft zu einer entsprechend großen Reibung der Flügel am Gehäuseumfang und damit zu einer entsprechend großen Verlustarbeit. Die Federkräfte sind daher jedenfalls zu minimieren.The wings are supported relative to each other by springs which are attached between the hook head of one wing and the web foot of the other wing. In the case of rapidly rotating vane pumps, in particular vane vacuum pumps, which are used in motor vehicles to generate a vacuum for servo consumers, in particular brake boosters, the force exerted by the springs leads to a correspondingly large friction of the vanes on the circumference of the housing and thus to a correspondingly large amount of lost energy. The spring forces must therefore be minimized in any case.

Daher hat die Flügelzellenpumpe den Nachteil, daß für die Umkehr der Bewegungsrichtung des Flügels im unteren Totpunkt keine ausreichenden Kräfte zur Verfügung stehen. Dieser Nachteil besteht auch, wenn statt der Federn ein anderes System zur Erzeugung der Ausfahrbewegung der Flügel verwandt wird (vgl. z. B. DE-A-3 507 176).The vane pump therefore has the disadvantage that insufficient forces are available to reverse the direction of movement of the vane at bottom dead center. This disadvantage also exists if, instead of the springs, another system is used to generate the wing's outward movement (see, for example, DE-A-3 507 176).

Der Erfindung liegt die Aufgabe zugrunde, in einer Flügelzellenpumpe, deren Rotor nur einen Führungsschlitz besitzt, in welchem zwei Flügel, die sich durch Kraftmittel radial aufeinander abstützen, radial beweglich sind, die durch den einen auf den anderen Flügel ausgeübten Kräfte zu verkleinern und dadurch die durch die Kraftmittel ausgeübten, erforderlichen Radialkräfte sowie den Verschleiß zu verringern.The invention has for its object in a vane pump, the rotor has only one guide slot in which two vanes, which are supported radially on each other by means of force, are radially movable, to reduce the forces exerted on the other vane and thereby reduce the forces to reduce the radial forces required and the wear caused by the power means.

Die Lösung ergibt sich aus den Merkmalen des kennzeichnenden Teils von Anspruch 1. Durch den Umstand, daß die Flügelbewegung im unteren Totpunkt durch Anschläge begrenzt wird, wird erreicht, daß die Mittel, die die Ausfahrbewegung der Flügel hervorrufen, nicht auch die Kräfte hervorbringen müssen, die zur Umkehr der Bewegungsrichtung erforderlich sind.The solution results from the features of the characterizing part of claim 1. The fact that the wing movement at bottom dead center is limited by stops means that the means which cause the wing to move outward do not also have to produce the forces. which are required to reverse the direction of movement.

Hierzu sei aufgrund des allgemeinen Konstruktionsprinzips der Flügelzellenpumpen bemerkt, daß der Rotor in dem Gehäuse exzentrisch gelagert ist. Daher führen die Flügel bei einer Drehung des Rotors auf der Kompressionsseite eine radiale Einfahrbewegung aus, bis sie im unteren Totpunkt ihre radial innerste Stellung erreicht haben. Im unteren Totpunkt wird die Bewegungsrichtung umgekehrt und von hier aus führt der Flügel eine radiale Ausfahrbewegung über den Bereich der Saugzone aus. Bevorzugt ist der Rotor derart gelagert, daß er mit der Gehäuseumfangswand eine Dichtung bildet. Der untere Totpunkt des Flügels liegt daher - wenn man den Flügelkopf betrachtet - auf dem Umfang des Rotors.Due to the general design principle of the vane pumps, it should be noted that the rotor is mounted eccentrically in the housing. Therefore, when the rotor rotates on the compression side, the blades execute a radial retraction movement until they have reached their radially innermost position at bottom dead center. At the bottom dead center, the direction of movement is reversed and from here the wing executes a radial extension movement over the area of the suction zone. The rotor is preferably mounted in such a way that it forms a seal with the housing peripheral wall. The bottom dead center of the wing is therefore - if you look at the wing head - on the circumference of the rotor.

Zwar ist durch die US-A-2 919 651, die nunmehr als nächstligender Stand der Technik anzusehen ist, eine Flügelzellenpumpe bekannt, bei welcher der radial äußere Bereich eines jeden Flügels und der radial innere Bereich der Wandung eines jeden Führungsschlitzes als in Umfangsrichtung weisender Vorsprung ausgebildet ist. Diese Vorsprünge bilden jedoch eine Druckkammer zur Aufnahme einer Druckflüssigkeit, wobei sich die Vorsprünge auch in der Totpunktlage der Flügel nicht berühren.A vane pump is known from US-A-2 919 651, which is now to be regarded as the closest prior art, in which the radially outer region of each vane and the radially inner region of the wall of each guide slot act as a circumferential projection is trained. However, these projections form a pressure chamber for receiving a pressure fluid, the projections not touching one another even in the dead center position of the wings.

Die erfindungsgemäß vorgeschlagenen Anschläge bestehen einerseits aus einer Nut und andererseits aus einem Vorsprung. Diese Paarung von Nut und Vorsprung ist in der Paarung der Gleitflächen vorgesehen, mit denen die Flügel in ihrem Schlitz geführt sind.The stops proposed according to the invention consist on the one hand of a groove and on the other hand of a projection. This pairing of groove and projection is provided in the pairing of the sliding surfaces with which the wings are guided in their slot.

In einem bevorzugten Ausführungsbeispiel ist die Nut in der Gleitfläche des Schlitzes vorgesehen, während der Flügel im Bereich seines Kopfes auf seiner Gleitfläche einen Vorsprung aufweist. Dieser Vorsprung taucht bei Erreichen des unteren Totpunktes in die Nut ein und schlägt am Nutengrund an.In a preferred embodiment, the groove is provided in the sliding surface of the slot, while the wing has a projection on its sliding surface in the region of its head. This projection dips into the groove when bottom dead center is reached and strikes the bottom of the groove.

Um ein Verkanten zu vermeiden, kann sich der Anschlag, d.h. der Vorsprung einerseits und die Nut andererseits über die gesamte Flügellänge erstrecken. Aus Gründen der Materialersparnis und Gewichtsersparnis kann jedoch auch vorgesehen sein, daß sich Anschlag und Nut lediglich über eine Teillänge erstrecken und vorzugsweise im mittleren Bereich der Flügellänge angeordnet sind.In order to avoid tilting, the stop, i.e. the projection on the one hand and the groove on the other hand extend over the entire wing length. For reasons of material savings and weight savings, however, it can also be provided that the stop and groove only extend over a partial length and are preferably arranged in the central region of the wing length.

Vorzugsweise ist der Anschlag eine auf der Flügelrückseite angeordnete Verdickung in Form eines Kreisausschnitts. Die Nut ist eine entsprechende Senkung in der Wandung des Rotorschlitzes. Mit seiner geraden Schnittkante wird der Kreisabschnitt von der aus dem Rotorschlitz herausragenden Längskante des Flügels gebildet. Dieser Vorsprung und die entsprechende Senkung passen mit mittlerem Spiel zueinander. Bei dieser Ausgestaltung wird sichergestellt, daß sich am Grunde der Senkung kein unzulässiger Luftstau bilden kann. Ein gewisser Luftstau kann für ein bevorzugtes Ausführungsbeispiel ausgenutzt werden zur Dämpfung der Flügelbewegung. Hierzu sind die Senkung als Dämpfkammer, der Vorsprung als Dämpfkolben ausgebildet. Die Dämpfwirkung kann dadurch gezielt beeinflußt werden, daß die Luft aus der Senkung nicht in Richtung der Einfahrbewegung - d.h. radial zum Rotor - entweicht, sondern daß der Grund der Senkung mit Bohrungen versehen wird, die auf dem Außenumfang des Rotors münden und eine gewünschte Drosselung auf die aus der Senkung entweichende Luft ausüben.The stop is preferably a thickening in the form of a circular section arranged on the rear of the wing. The groove is a corresponding depression in the wall of the rotor slot. With its straight cutting edge, the circular section is formed by the longitudinal edge of the wing protruding from the rotor slot. This lead and the corresponding lowering match each other with medium play. This configuration ensures that no undue air build-up can form at the bottom of the depression. A certain amount of air congestion can be used for a preferred exemplary embodiment to dampen the wing movement. For this purpose, the countersink is designed as a damping chamber, the projection as a damping piston. The damping effect can be influenced in a targeted manner by preventing the air from lowering in the direction of the retracting movement - i.e. radial to the rotor - escapes, but that the bottom of the countersink is provided with holes which open on the outer circumference of the rotor and exert a desired throttling on the air escaping from the countersink.

In einem bevorzugten Ausführungsbeispiel ist ein Entlastungskanal vorgesehen, der den radial inneren Teil der Nut mit der Saugseite verbindet. Der Entlastungskanal kann z. B. den Rotor so durchdringen, daß er vor dem Nutengrund mündet. Es bildet sich dadurch beim Einfahren des Vorsprungs in die Nut auf dem Nutengrund ein Luft- oder Flüssigkeitspolster, das das Auftreffen des Anschlages dämpft.In a preferred embodiment, a relief channel is provided which is radial connects the inner part of the groove to the suction side. The relief channel can e.g. B. penetrate the rotor so that it opens before the bottom of the groove. As a result, when the projection is inserted into the groove, an air or liquid cushion is formed on the groove base, which dampens the impact of the stop.

Im folgenden wird ein Ausführungsbeispiel der Erfindung beschrieben.An embodiment of the invention is described below.

Es zeigen:

  • Fig. 1 den schematischen Normalschnitt durch eine Flügelzellenpumpe;
  • Fig. 2 die Aufsicht auf einen Rotor mit Flügel, wobei das Gehäuse aufgeschnitten dargestellt ist.
Show it:
  • Figure 1 shows the schematic normal section through a vane pump.
  • Fig. 2 shows the top view of a rotor with blades, the housing being shown cut away.

In dem Gehäuse 1 ist der Rotoe 2 drehbar gelagert. Der Rotor weist einen Rotorschlitz 4 auf. Dieser erstreckt sich vom Ende der Welle 3 über die gesamte axiale Länge des Rotors. Die dadurch entstehenden beiden Rotorhälften sind an die entsprechend dick ausgeführte Welle 3 angeformt. Der Innenkanal 29, der die Welle und den Rotor durchdringt, dient zur Zufuhr von Schmieröl. Mit 32 ist der Einlaß mit einem in Einlaßrichtung offenen Röckschlagventil bezeichnet. Mit 33 ist die Auslaßöffnung bezeichnet. Ein in der Auslaßöffnung liegendes, in Auslaßrichtung öffnendes Rückschlagventil ist nicht dargestellt.The rotoe 2 is rotatably mounted in the housing 1. The rotor has a rotor slot 4. This extends from the end of the shaft 3 over the entire axial length of the rotor. The resulting two rotor halves are molded onto the correspondingly thick shaft 3. The inner channel 29, which penetrates the shaft and the rotor, serves to supply lubricating oil. With 32 the inlet is designated with a check valve open in the inlet direction. With 33 the outlet opening is designated. A check valve lying in the outlet opening and opening in the outlet direction is not shown.

In dem Rotorschlitz 4 sind die Flügel 5 und 6 gleitend geführt. Dabei liegen die Flügel mit ihren Stegen 9 und 10 aufeinander. Die Dicke der Flügel 9 und 10 entspricht in der Summe der Weite des Rotorschlitzes 4. Die Flügel kämmen mit ihren Enden an der zylindrischen Innenwand des Gehäuses 1. Die Enden sind als Hakenköpfe 7, ausgebildet. Die Dicke dieser Hakenköpfe entspricht ebenfalls der Schlitzweite. Im dargestellten Ausführungsbeispiel weisen die Flügelstege 9,10 an ihren Enden Ausnehmungen 50, 51 auf. Diese Ausnehmungen verbinden in bestimmten Drehpositionen die sog. Hakenräume 15.1 und 15.2 mit der Ölzufuhr durch Innenkanal 29. Die Hakenräume 15.1 und 15.2 werden gebildet durch die Hakenköpfe 7.8 sowie die Stegfüße 14 der Flügelstege 9,10. Beim Eintauchen dieser Hakenräume 15.1 bzw. 15.2 in den Flügelschlitz wirkt sich in ihnen der Öldruck des Schmieröls derart aus, daß die Flügel die erforderliche radiale Ausfahrbewegung durchführen. Bezüglich der Ausgestaltung der Mittel zur Erzeugung der radialen Ausfahrbewegung wird auf die DE-A-3 507 176 verwiesen.The blades 5 and 6 are slidably guided in the rotor slot 4. The wings with their webs 9 and 10 lie on top of each other. The thickness of the vanes 9 and 10 corresponds to the sum of the width of the rotor slot 4. The ends of the vanes mesh with the cylindrical inner wall of the housing 1. The ends are designed as hook heads 7. The thickness of these hook heads also corresponds to the slot width. In the exemplary embodiment shown, the wing webs 9, 10 have recesses 50, 51 at their ends. In certain rotational positions, these recesses connect the so-called hook spaces 15.1 and 15.2 to the oil supply through the inner channel 29. The hook spaces 15.1 and 15.2 are formed by the hook heads 7.8 and the web feet 14 of the wing webs 9, 10. When these hook spaces 15.1 or 15.2 are immersed in the wing slot, the oil pressure of the lubricating oil has an effect on them such that the wings perform the required radial extension movement. With regard to the configuration of the means for generating the radial extension movement, reference is made to DE-A-3 507 176.

In Fig. 1 ist bei Drehrichtung 22 die Situation gezeigt, in der der Flügel 5 sich seiner unteren Totpunktlage nähert. Durch den in Hakenraum 15.2 bestehenden Druck wird der Flügel 6 radial nach außen gefahren, während der Flügel 5 noch eine gleichgerichtete Bewegung radial nach innen durchführt. Sobald der Flügel den unteren Totpunkt erreicht hat, muß sich diese Bewegungsrichtung umkehren. Hierzu ist es erforderlich, daß im Hakenraum 15.2 ein sehr hoher Öldruck herrscht. Das wiederum würde aber zu einer sehr starken Anlage des Flügels 6 am Gehäuseumfang führen. Um die Beschleunigungskräfte zumindest teilweise zu eliminieren, ist ein Anschlag 60 am Hakenkopf eines jeden Flügels vorgesehen und der Rotor weist Nuten 61 auf, die mit dem Anschlag 60 fluchten. Die radiale Länge der Nuten ist so bemessen, daß der Anschlag in der unteren Totpunktlage des Flügels an den Nutengrund anschlägt. Nutengrund oder Anschlag können auch als Feder ausgebildet sein, so daß die für die Verzögerung des Flügels erforderliche Energie gespeichert und für die radiale Ausfahrbewegung des Flügels benutzt werden kann.1 shows the situation in the direction of rotation 22 in which the wing 5 approaches its bottom dead center position. The wing 6 is moved radially outward by the pressure existing in the hook space 15.2, while the wing 5 still performs a rectified movement radially inward. As soon as the wing has reached bottom dead center, this direction of movement must reverse. For this it is necessary that there is a very high oil pressure in the hook space 15.2. This in turn would lead to a very strong contact of the wing 6 on the housing circumference. In order to at least partially eliminate the acceleration forces, a stop 60 is provided on the hook head of each wing and the rotor has grooves 61 which are aligned with the stop 60. The radial length of the grooves is such that the stop strikes the bottom of the groove in the bottom dead center position of the wing. Groove base or stop can also be designed as a spring, so that the energy required for decelerating the wing can be stored and used for the radial extension movement of the wing.

Der Nutengrund der Nuten 61 ist mit einem Entlastungskanal 62 versehen, der den Rotor sekantial durchdringt. Dadurch wird die Nut beim Eintauchen des Anschlages 60 mit der Saugkammer der Pumpe verbunden, so daß etwaige Luft- oder Flüssigkeits- oder Ölmengen aus der Nut abgesaugt werden.The bottom of the groove 61 is provided with a relief channel 62 which secantially penetrates the rotor. As a result, the groove is connected to the suction chamber of the pump when the stop 60 is immersed, so that any air, liquid or oil quantities are sucked out of the groove.

Durch die Dimensionierung der Größe dieses Entlastungskanals 62 kann der in der Nut aufbaubare Flüssigkeitsdruck derart beeinflußt werden, daß sich dem in die untere Totpunktlage einfahrenden Flügel zur Dämpfung ein gewünschter Widerstand entgegensetzt.By dimensioning the size of this relief channel 62, the fluid pressure that can be built up in the groove can be influenced in such a way that a desired resistance to damping is counteracted by the wing that moves into the bottom dead center position.

Fig. 3 zeigt die Ansicht eines Flügels von der Rückseite her. Es ist zu sehen, daß der Anschlag 60 des in Fig. 1 und 2 gezeigten Ausführungsbeispiels als Verdickung auf der Rückseite der Flügel 5 bzw. 6 ausgebildet und die Form eines Kreisausschnitts hat. Die gerade Schnittkante des Kreisausschnitts wird durch die Oberkante des Flügels, die mit dem Innenumfang des Gehäuses kämmt, gebildet.Fig. 3 shows the view of a wing from the back. It can be seen that the stop 60 of the embodiment shown in FIGS. 1 and 2 is designed as a thickening on the back of the wings 5 and 6 and has the shape of a circular section. The straight cutting edge of the circular section is formed by the upper edge of the wing, which meshes with the inner circumference of the housing.

Bei dem Ausführungsbeispiel nach den Fig. 4 und 5 ist ein Anschlag 60 gezeigt, der als Leiste sich über die gesamte Länge des Flügels erstreckt. Folglich hat auch die Nut 61 eine entsprechende Gestalt. Ebenso sind wiederum Entlastungskanäle 62 vorgesehen, durch die die Luft aus der Nut 61 mit gezielter Drosselung entweichen kann.In the embodiment of FIGS. 4 and 5, a stop 60 is shown which extends as a bar over the entire length of the wing. Consequently, the groove 61 also has a corresponding shape. Likewise, relief channels 62 are again provided, through which the air can escape from the groove 61 with targeted throttling.

Durch die Erfindung gelingt es, die zur Erzeugung der radialen Bewegung der Flügel erforderlichen Kräfte und damit die Verlustleistung der Pumpe und ihren Verschleiß zu vermindern. Ferner arbeitet die Pumpe mit der erfindungsmäßigen Maßnahme geräuschloser.The invention succeeds in reducing the forces required to generate the radial movement of the vanes and thus the power loss of the pump and its wear. Furthermore, the pump works with the inventive measure noiseless.

BezugszeichenaufstellungList of reference symbols

  • 1 Gehäuse1 housing
  • 2 Rotor2 rotor
  • 3 Welle3 wave
  • 4 Rotorschlitz4 rotor slot
  • 5 Flügel5 wings
  • 6 Flügel6 wings
  • 7 Hakenkopf7 hook head
  • 8 Hakenkopf8 hook head
  • 9 Flügelsteg9 wing bridge
  • 10 Flügelsteg10 wing bridge
  • 14 Stegfuß14 bridge foot
  • 15 Hakenraum15 hook space
  • 22 Drehrichtung22 Direction of rotation
  • 29 Innenkanal29 inner channel
  • 32 Einlaß32 inlet
  • 33 Auslaß33 outlet
  • 50 Ausnehmung50 recess
  • 51 Ausnehmung51 recess
  • 60 Anschlag60 stop
  • 61 Einbuchtung61 indentation
  • 62 Entlastungskanal62 Relief channel

Claims (5)

1. Vane-cell pump, having pump vanes (5, 6), which can move back and forth radially in the pump housing (1) in a rotor slit (4) and which can move outwards by generation of a radial force, a sliding surface of each vane having a step- shaped projection and the counter-sliding surface in the associated rotor slit having a step- shaped indentation receiving the projection, characterized in that the pump has only one rotor slit (4), in which two vanes (5, 6) slide and are supported one on the other and in that the projection (60) and the indentation (61) are dimensioned such that the radially inwardly facing limiting surface of the projection (60) acts with the radially outwardly facing limiting surface of the indentation (61) as stop (60) limiting the vane movement at the lower dead centre when entering the rotor slit (4).
2. Vane-cell pump according to Claim 1, characterized in that the stop (60) is provided on what is the rear surface of each vane (5, 6) in the direction of rotation (22) of the rotor.
3. Vane-cell pump according to Claim 1 or 2, characterized in that the stop (60) extends over the entire vane length.
4. Vane-cell pump according to Claim 1 or 2, characterized in that the stop (60) takes up only a part of the vane length and has the shape of a circle segment, which fits into a corresponding indentation (61) in the corresponding slit wall of the rotor (2) with central play.
5. Vane-cell pump according to one of the preceding claims, characterized in that the stop (60) is formed on each vane and the corresponding indentation (61) is formed in the corresponding slit wall of the rotor (2) as damping elements with damping effect during the braking of the vane.
EP19860107221 1985-06-13 1986-05-28 Rotary vane pump Expired EP0205036B1 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE3521186 1985-06-13
DE3521186 1985-06-13
DE3531963 1985-09-07
DE3531963 1985-09-07

Publications (3)

Publication Number Publication Date
EP0205036A2 EP0205036A2 (en) 1986-12-17
EP0205036A3 EP0205036A3 (en) 1987-10-28
EP0205036B1 true EP0205036B1 (en) 1989-05-31

Family

ID=25833085

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19860107221 Expired EP0205036B1 (en) 1985-06-13 1986-05-28 Rotary vane pump

Country Status (2)

Country Link
EP (1) EP0205036B1 (en)
DE (1) DE3663720D1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4020082C2 (en) * 1989-07-07 1998-09-03 Barmag Barmer Maschf Vane vacuum pump
IT1400885B1 (en) * 2010-07-08 2013-07-02 Vhit Spa VOLUMETRIC PUMP WITH PALETTE ROTOR.

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1008206A (en) * 1949-01-11 1952-05-15 Pump, compressor or rotary motor
US2919651A (en) * 1954-10-19 1960-01-05 Vickers Inc Power transmission
CH634385A5 (en) * 1978-07-21 1983-01-31 Hans Ryffel Sliding-vane machine
DE3303906C2 (en) * 1983-02-05 1986-07-03 Pierburg Gmbh & Co Kg, 4040 Neuss Rotary piston machine

Also Published As

Publication number Publication date
EP0205036A2 (en) 1986-12-17
EP0205036A3 (en) 1987-10-28
DE3663720D1 (en) 1989-07-06

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