EP3805521A1 - Vane pump - Google Patents

Abstract

Vane pump, comprising: a rotor (1) rotatable about an axis of rotation (D) and a plurality of vanes (2) guided displaceably by the rotor (1), the rotor (1) having a lower vane chamber (3) for each vane (2) and each Wing (2) forms a movable wall of its associated lower wing chamber (3), a first end wall (30) adjoining the rotor (1) on the front side on a first side of the rotor (1), which is used to control the pressure of the lower wing chamber (3) has a lower wing recess (34; 37) extending in the circumferential direction, which, viewed in the circumferential direction, comprises a control edge (341; 342; 371; 372), a second end wall (20) adjoining the rotor (1) on the front side on a second side of the rotor (1) ), which for pressure control of the lower wing chamber (3) has a circumferentially extending lower wing recess (24; 27) which lies opposite the lower wing recess (34; 37) of the first end wall (30) and, viewed in the circumferential direction, a control cable nte (241; 242; 271; 272), which is similar to the control edge (341; 342; 371; 372) of the lower wing recess (34; 37) of the first end wall (30), the control edge (341; 342; 371; 372) of the lower wing recess (34; 37 ) the first end wall (30) and the similar control edge (241; 242; 271; 272) of the lower wing recess (24; 27) of the second end wall (20) designed differently and / or offset from one another, in particular about the axis of rotation (D) as Vertex angularly offset, are arranged to one another.

Description

The invention relates to a displacement pump designed as a vane pump, in particular a single- or double-flow or double-stroke vane pump. With the vane pump, a fluid, for example a gas or a liquid, such as oil, can be conveyed from a suction side of the pump to a pressure side of the pump. The pump can be provided, for example, for installation in a vehicle, in particular a motor vehicle. For example, the pump for delivering lubricating oil can be provided for a consumer in a motor vehicle, for example an engine or a transmission, in particular an automatic transmission, for example for a motor vehicle. The pump can be arranged or fastened, for example, in or on a transmission or a transmission housing.

Vane pumps are known from the prior art which have a rotor which is rotatable relative to a housing and which comprises a plurality of slot-shaped recesses, in each of which a vane is arranged and which guide the vane in a radially displaceable manner. A contour ring of the housing has an inner contour formed by its inner circumference, which extends around the rotor and along which the vanes slide during the rotation of the rotor in order to convey fluid from a suction side to a pressure side of the pump. In order to reduce the risk of the wings lifting off the inner contour, it is known that the rotor forms a lower wing chamber under each wing, which can be pressurized with fluid, whereby the wing of each lower wing chamber is urged radially outward against the inner contour. As a result of the fact that the vane is pressed against the inner contour, the friction between the vanes and the inner contour increases, as a result of which wear increases and / or the efficiency of the pump decreases.

The invention is based on the object of specifying a vane pump which has high levels of efficiency, but at the same time reduces the risk of the vanes lifting off the inner contour of the contour ring. For example, a good suction behavior of the pump during a cold start should also be guaranteed. It can be seen as a sub-task to specify a double-flow pump whose flows can be operated completely independently of one another and / or with different beneficial and high volumetric efficiencies.

The object is achieved with the features of the independent claims. Advantageous developments result from the dependent claims, the description and the figures.

The invention is based on a vane cell pump, in particular of a motor vehicle or for a motor vehicle, which has a rotor that can be rotated about an axis of rotation and a plurality of vanes that are displaceably guided by the rotor. For example, several blades can be arranged distributed over the circumference of the rotor, in particular evenly, and / or can be displaced relative to the rotor individually or independently of one another. For example, at least six wings, in particular 6, 8, 10, 12, 14 wings, can be provided. In particular, the blades can be displaceable relative to the rotor at least with a radial component or radially with respect to the axis of rotation of the rotor.

For example, the rotor can form a slot-shaped guide for each wing, which is designed to guide the wing assigned to it with a translational, in particular a single translational degree of freedom, in particular radially.

For each wing and / or slot-shaped guide, the rotor has a lower wing chamber, which can in particular be arranged between the axis of rotation of the rotor and the slot-shaped guide assigned to the lower wing chamber. Each wing forms a movable wall of its associated lower wing chamber. By applying pressure and / or relieving pressure of a fluid in the lower wing chamber, a force acting on the movable wall of the wing can be controlled, and thus for example the force with which the respective wing is pressed against the inner contour of a contour or lifting ring.

The vane pump can, for example, have a contour ring, in particular a stroke ring, which has an inner contour (inner circumferential surface) extending around the axis of rotation of the rotor, on which the vanes slide with their radially outer ends when the rotor is rotated, especially when the vane pump is in operation becomes.

The inner contour of the contour ring can have at least one ascending area, with a vane being moved out of the rotor, in particular at least supported by a fluid pressure in the lower vane chamber, while it slides over the ascending area, and at least one descending area, with one vane entering the rotor , in particular against a fluid pressure in the underwing chamber, is moved in while sliding over the descending area.

Optionally - based on the intended direction of rotation of the rotor for operation - between one end of the ascending area and the beginning of a descending area, the inner contour can have an area that is adapted to a top dead center for the wing that glides over this area, d. H. to define a maximally moved out of the rotor position for the wing. While the wing is being moved through this area, it is preferably at least approximately stationary with respect to the rotor. Therefore, this range can be referred to as the constant range or - more precisely - the upper constant range. When the vane is moved from the ascending range over the upper constant range into the descending range, the direction of movement of the vane in relation to the rotor is reversed.

Optionally - based on the direction of rotation of the rotor provided for operation - between one end of the descending area and the beginning of an ascending area, the inner contour can have an area that is adapted to a lower dead center for the wing that glides over this area, d. H. to define a maximally moved into the rotor position for the wing. While the wing is being moved through this area, it is preferably at least approximately stationary with respect to the rotor. Therefore, this range can be referred to as the constant range or - more precisely - the lower constant range. When the vane is moved from the descending range over the lower constant range into the ascending range, the direction of movement of the vane in relation to the rotor is reversed.

In the case of a multi-flow or multi-stroke vane pump, the inner contour of the contour ring can have a first ascending area and a first descending area, which corresponds to a first tide, ie. H. associated with a first fluid flow from a suction or low pressure side to a pressure or high pressure side, and at least one second ascending area and one second descending area which are associated with a second flow, d. H. a second fluid flow from a suction or low pressure side to a pressure or high pressure side, are assigned. A wing is moved out of the rotor, in particular at least supported by a fluid pressure in the lower wing chamber, when it slides over the ascending area, in particular the first or second ascending area, and into the rotor, in particular against a fluid pressure in the lower wing chamber, moves in when it slides over the descending area, in particular the first or second descending area.

With a single-flow or single-stroke vane pump, each vane is extended once and retracted once during a full rotation of the rotor. In the case of a double-flow or two-stroke vane pump is extended, retracted, extended and retracted again during one full revolution of the rotor, ie extended twice and retracted twice. In vane pumps with more than two flows or strokes, for example three-flow or three-stroke vane pumps, each wing is extended and retracted correspondingly more often during a full rotation of the rotor.

Optionally - based on the direction of rotation of the rotor intended for operation - the inner contour of the contour ring can be in each case between an end of the first ascending area and a start of the first descending area and / or between an end of the second ascending area and a start of the second descending area have an area which is adapted to define a top dead center (see above) for the wing that slides over this area. This range can be referred to as the constant range or - more precisely - as the first upper constant range if it is formed between the end of the first ascending range and the beginning of the first descending range, and as the second upper constant range if it is between the end of the second ascending range and the beginning of the second descending range is formed.

Optionally - based on the direction of rotation of the rotor intended for operation - the inner contour can each have an area between one end of the first descending area and the beginning of the second ascending area and / or between one end of the second descending area and the beginning of the first ascending area have, which is adapted, for the wing that slides over this area, a bottom dead center (see above), i. H. to define a maximally moved into the rotor position for the wing. This range can be referred to as the constant range or - more precisely - as the first lower constant range if it is formed between the end of the first descending range and the beginning of the second ascending range, and as the second lower constant range if it is between the end of the second descending range and the beginning of the first ascending range is formed.

On one side of the rotor, for example a first side, the vane pump can have an end wall adjoining the rotor on the end face, in particular a first end wall. On the side of the rotor facing away from one side, for example the first side, in particular on a second side of the rotor, the vane pump can have an end wall adjoining the rotor on the end face, in particular a second end wall. The first end wall can be at least one for pressure control or pressure supply of the lower vane chambers of the rotor, preferably a plurality of lower wing recesses extending in the circumferential direction, which are referred to or can be designed in particular as lower wing supply recesses or lower wing supply kidneys or lower wing supply grooves. Alternatively or additionally, the second end wall for pressure control or pressure supply to the lower wing chambers of the rotor can have at least one, preferably several, lower wing recesses extending in the circumferential direction, which are in particular referred to or can be designed as lower wing supply recesses or lower wing supply kidneys or lower wing supply grooves.

The contour ring, the first end wall and the second end wall can be separate parts which, when joined together, form a housing. The contour ring, the first end wall and the second end wall are preferably joined together so as to be non-rotatable about the axis of rotation of the rotor in relation to one another. Alternatively, the contour ring can be an integral part of the first end wall or the second end wall.

The first end wall and / or the second end wall can - in the case of a single-flow vane pump - in particular an ascending under-wing recess and a descending under-wing recess - in a double-flow vane pump - in particular in each case a first ascending under-wing recess, a first descending under-wing recess, a second ascending under-wing recess and a second descending under-wing recess - with a higher-flow vane pump, d. H. a vane pump with even more floods - accordingly have further under-wing recesses. The rising lower wing recess serves to control the pressure of a lower wing chamber when its wing is located in the rising area of the inner contour or slides along the rising area of the inner contour. The descending lower wing recess is used to control the pressure of a lower wing chamber when its wing is located in the descending area of the inner contour or slides along the descending area of the inner contour.

In particular, the first rising lower wing recess is used to control the pressure of a lower wing chamber and / or the first rising lower wing recess is connected to a lower wing chamber in a fluid-communicating manner when its wing is in the first rising area of the inner contour or slides along it. In particular, the second rising lower wing recess is used to control the pressure of a lower wing chamber and / or the second rising lower wing recess is fluidly connected to a lower wing chamber when its wing is in the second rising area of the Inside contour is or slides along it. In particular, the first descending lower wing recess is used to control the pressure of a lower wing chamber and / or the first descending lower wing recess is fluidly connected to a lower wing chamber when its wing is in the first descending area of the inner contour or slides along it. In particular, the second descending lower wing recess is used to control the pressure of a lower wing chamber and / or the second descending lower wing recess is connected to a lower wing chamber in a fluid-communicating manner when its wing is in the second descending area of the inner contour or slides along it.

The lower wing recesses can be groove-shaped or pocket-shaped. The lower wing recesses can extend in the circumferential direction, in particular curved around the axis of rotation. In particular, the lower wing recesses can each form an arcuate section rotating around the axis of rotation of the rotor and can be arranged one behind the other or in series in the direction of rotation.

For example, the lower wing recesses of the first end wall can be arranged in such a way that the lower wing chambers or each of the lower wing chambers are successively connected to the lower wing recesses of the first end wall in fluid communication during one complete rotation (360 °) of the rotor, whereby it is preferred that one lower wing chamber only ever a lower wing recess of the first end wall can be connected in a fluid-communicating manner or, in other words, that a lower wing chamber in all possible rotational positions of the rotor cannot be connected in a fluid-communicating manner to a plurality of lower wing recesses of the first end wall at the same time.

Alternatively or additionally, the lower wing recesses of the second end wall can be arranged in such a way that the lower wing chambers or each of the lower wing chambers are successively connected to the lower wing recesses of the second end wall in fluid communication during a complete rotation (360 °) of the rotor, whereby it is preferred that one lower wing chamber always can only be connected in a fluid-communicating manner to one under-wing recess of the second end wall or, in other words, that an under-wing chamber cannot be connected in a fluid-communicating manner to several under-wing recesses of the second end wall in all possible rotational positions of the rotor at the same time.

Nevertheless, it is preferred that a lower wing chamber at the same time with a lower wing recess of the first end wall and a lower wing recess of the second Front wall can be connected in a fluid-communicating manner. In particular, the rotor can assume a rotational position in which a lower wing chamber is connected at the same time to a lower wing recess of the first end wall and the second end wall. For example, the rotor can assume a rotational position in which a lower wing chamber is simultaneously connected to the first rising lower wing recess of the first end wall and the second end wall. For example, the rotor can assume a rotational position in which a lower wing chamber is simultaneously connected to the first descending lower wing recess of the first end wall and the second end wall. For example, the rotor can assume a rotational position in which a lower wing chamber is connected at the same time to the second rising lower wing recess of the first end wall and the second end wall. For example, the rotor can assume a rotational position in which a lower wing chamber is simultaneously connected to the second descending lower wing recess of the first end wall and the second end wall.

In particular, on the first end wall and / or second end wall between adjacent lower wing recesses, a separating web that fluidically separates the adjacent lower wing recesses from one another, or a hydraulic constriction, for example a groove or a channel, which is open to the rotor, which the adjacent lower wing recesses fluidly connects to one another, be formed.

For example, a separating web can be formed on the first end wall or on the second end wall between the first descending lower wing recess and the second rising lower wing recess. For example, a separating web can be formed on the first end wall or on the second end wall between the second descending lower wing recess and the first rising lower wing recess.

For example, a separating web can be formed on the first end wall between the first ascending lower wing recess and the first descending lower wing recess and / or between the second ascending lower wing recess and the second descending lower wing recess, in particular in each case. For example, a hydraulic bottleneck can be formed on the second end wall between the first ascending lower wing recess and the first descending lower wing recess and / or between the second ascending lower wing recess and the second descending lower wing recess.

The separating web or the separating webs are, for example, between the first descending lower wing recess and the second rising lower wing recess and / or between the second descending lower wing recess and the first ascending lower wing recess and / or between the first ascending lower wing recess and the first descending lower wing recess and / or between the second ascending lower wing recess and the second descending lower wing recess, designed so that he / she can close a lower wing chamber in a rotational position of the rotor and / or fluidically separate it from the lower wing recesses adjoining the relevant separating web.

In particular, each of the lower wing chambers can open out with a first opening to the first end wall and a second opening to the second end wall. The separating web or the separating webs are preferably dimensioned such that he / she can cover the first opening or the second opening completely or essentially completely in order to fluidically separate them from the adjoining lower wing chambers.

The lower wing recesses can be enclosed or limited in the circumferential direction or the direction of rotation of the rotor by a control edge which - based on the direction of rotation of the rotor - forms the beginning of a lower wing recess, and a control edge which forms one end of the lower wing recess. The control edge can be formed, for example, by the transition from the lower wing recess to the adjacent separating web or by a projection which forms the hydraulic constriction or which delimits it laterally.

One or more separating webs and / or lower wing recesses of one end wall, for example the first end wall, and the separating web corresponding to the respective separating web or the lower wing recess corresponding to the respective lower wing recess of the other end wall, for example the second end wall, lie opposite one another, i.e. H. overlap at least partially or completely in the projection along the axis of rotation of the rotor.

For example, an ascending lower wing recess of the first end wall can lie opposite the ascending lower wing recess of the second end wall, ie at least partially overlap the ascending lower wing recess of the second end wall in a projection along the axis of rotation of the rotor. Alternatively or additionally, a descending lower wing recess of the first end wall of the descending Opposite the lower wing recess of the second end wall, ie at least partially overlap the descending lower wing recess of the second end wall in a projection along the axis of rotation of the rotor. Two lower wing recesses lying opposite one another can be referred to as lower wing recesses of the same type.

• die erste aufsteigende Unterflügelausnehmung der ersten Stirnwand der ersten aufsteigenden Unterflügelausnehmung der zweiten Stirnwand gegenüberliegen und/oder
• die erste absteigende Unterflügelausnehmung der ersten Stirnwand der ersten absteigenden Unterflügelausnehmung der zweiten Stirnwand gegenüberliegen und/oder
• die zweite aufsteigende Unterflügelausnehmung der ersten Stirnwand der zweiten aufsteigenden Unterflügelausnehmung der zweiten Stirnwand gegenüberliegen und/oder
• die zweite absteigende Unterflügelausnehmung der ersten Stirnwand der zweiten absteigenden Unterflügelausnehmung der zweiten Stirnwand gegenüberliegen.

For example:

• the first rising lower wing recess of the first end wall opposite the first rising lower wing recess of the second end wall and / or
• the first descending lower wing recess of the first end wall opposite the first descending lower wing recess of the second end wall and / or
• the second rising lower wing recess of the first end wall opposite the second rising lower wing recess of the second end wall and / or
• the second descending lower wing recess of the first end wall opposite the second descending lower wing recess of the second end wall.

Alternatively or additionally, a separating web formed between an ascending lower wing recess and a descending lower wing recess of the first end wall can be opposite a separating web or hydraulic constriction formed between an ascending lower wing recess and a descending lower wing recess of the second end wall, i.e. H. at least partially overlap the separating web or the hydraulic constriction. Two mutually opposite separating webs can be referred to as mutually similar separating webs.

• der zwischen der ersten absteigenden Unterflügelausnehmung und der zweiten aufsteigenden Unterflügelausnehmung gebildete Trennsteg der ersten Stirnwand dem zwischen der ersten absteigenden Unterflügelausnehmung und der zweiten aufsteigenden Unterflügelausnehmung gebildeten Trennsteg der zweiten Stirnwand gegenüberliegen und/oder
• der zwischen der zweiten absteigenden Unterflügelausnehmung und der ersten aufsteigenden Unterflügelausnehmung gebildete Trennsteg der ersten Stirnwand dem zwischen der zweiten absteigenden Unterflügelausnehmung und der ersten aufsteigenden Unterflügelausnehmung gebildeten Trennsteg der zweiten Stirnwand gegenüberliegen und/oder
• der zwischen der ersten aufsteigenden Unterflügelausnehmung und der ersten absteigenden Unterflügelausnehmung gebildete Trennsteg der ersten Stirnwand dem bzw. der zwischen der ersten aufsteigenden Unterflügelausnehmung und der ersten absteigenden Unterflügelausnehmung gebildeten Trennsteg oder hydraulischen Engstelle (oder deren Vorsprung) der zweiten Stirnwand gegenüberliegen und/oder
• der zwischen der zweiten aufsteigenden Unterflügelausnehmung und der zweiten absteigenden Unterflügelausnehmung gebildete Trennsteg der ersten Stirnwand dem bzw. der zwischen der zweiten aufsteigenden Unterflügelausnehmung und der zweiten absteigenden Unterflügelausnehmung gebildeten Trennsteg oder hydraulischen Engstelle (oder deren Vorsprung) der zweiten Stirnwand gegenüberliegen.

For example:

• the separating web of the first end wall formed between the first descending lower wing recess and the second ascending lower wing recess are opposite to the separating web of the second end wall formed between the first descending lower wing recess and the second ascending lower wing recess and / or
• the separating web of the first end wall formed between the second descending lower wing recess and the first ascending lower wing recess are opposite to the separating web of the second end wall formed between the second descending lower wing recess and the first ascending lower wing recess and / or
• the separating web of the first end wall formed between the first ascending lower wing recess and the first descending lower wing recess is opposite to the separating web or hydraulic constriction (or its projection) formed between the first ascending lower wing recess and the first descending lower wing recess and / or the second end wall and / or
• the separating web of the first end wall formed between the second ascending lower wing recess and the second descending lower wing recess is opposite the separating web or hydraulic constriction (or its projection) of the second end wall formed between the second ascending lower wing recess and the second descending lower wing recess.

In particular, starting from a vane pump described herein, several aspects of the invention are described, which can optionally be combined with one another.

• einen um eine Drehachse drehbaren Rotor und mehrere von dem Rotor verschiebbar geführte Flügel, wobei der Rotor je Flügel eine Unterflügelkammer aufweist und jeder Flügel eine verschiebbare Wand seiner ihm zugeordneten Unterflügelkammer bildet,
• eine auf einer ersten Seite des Rotors stirnseitig angrenzende erste Stirnwand, welche zur Druckversorgung oder Drucksteuerung der Unterflügelkammer eine sich in Umfangsrichtung, insbesondere bogenabschnittsförmig um die Drehachse des Rotors, erstreckende Unterflügelausnehmung aufweist, die, insbesondere in Umfangsrichtung betrachtet, eine Steuerkante umfasst, die insbesondere in der für den Betrieb vorgesehenen Drehrichtung des Rotors einen Anfang oder ein Ende der Unterflügelausnehmung bilden kann,
• eine auf einer zweiten Seite des Rotors stirnseitig angrenzende zweite Stirnwand, welche zur Druckversorgung oder Drucksteuerung der Unterflügelkammer eine sich in Umfangsrichtung, insbesondere bogenabschnittsförmig um die Drehachse des Rotors, erstreckende Unterflügelausnehmung aufweist, die insbesondere in Umfangsrichtung betrachtet, eine Steuerkante umfasst, die zu der Steuerkante der Unterflügelausnehmung der ersten Stirnwand gleichartig ist und insbesondere in der für den Betrieb vorgesehenen Drehrichtung des Rotors einen Anfang oder ein Ende der Unterflügelausnehmung bilden kann,
• wobei die Unterflügelausnehmung der zweiten Stirnwand der Unterflügelausnehmung der ersten Stirnwand gegenüberliegt oder in einer Projektion entlang der Drehachse des Rotors die Unterflügelausnehmung der ersten Stirnwand zumindest teilweise überlappt,
• wobei die Steuerkante der Unterflügelausnehmung der ersten Stirnwand und die dazu gleichartige Steuerkante der Unterflügelausnehmung der zweiten Stirnwand voneinander unterschiedlich ausgebildet und/oder zueinander versetzt, insbesondere winkelversetzt, angeordnet sind.

A first aspect of the invention relates to a vane pump comprising:

• a rotor rotatable about an axis of rotation and several vanes guided displaceably by the rotor, the rotor having a lower wing chamber for each wing and each wing forming a displaceable wall of its associated lower wing chamber,
• a first end wall adjoining the end face of a first side of the rotor, which for pressure supply or pressure control of the lower wing chamber has a lower wing recess extending in the circumferential direction, in particular in the form of an arcuate section around the axis of rotation of the rotor, which, viewed in particular in the circumferential direction, comprises a control edge, which in particular in the direction of rotation of the rotor intended for operation can form a start or an end of the lower wing recess,
• a second end wall adjoining the end face of a second side of the rotor, which for pressure supply or pressure control of the lower vane chamber has a lower vane recess extending in the circumferential direction, in particular in the form of an arcuate section around the axis of rotation of the rotor, which, viewed in particular in the circumferential direction, comprises a control edge leading to the control edge the lower wing recess of the first end wall is of the same type and in particular can form a start or an end of the lower wing recess in the direction of rotation of the rotor intended for operation,
• wherein the lower wing recess of the second end wall lies opposite the lower wing recess of the first end wall or at least partially overlaps the lower wing recess of the first end wall in a projection along the axis of rotation of the rotor,
• wherein the control edge of the lower wing recess of the first end wall and the similar control edge of the lower wing recess of the second end wall are designed differently from one another and / or offset from one another, in particular offset at an angle, are arranged.

The control edges of the same type are in particular designed differently from one another and / or offset, in particular angularly offset from one another, so that the pressure supply or pressure control of the lower wing chambers via the lower wing recess of the first end wall and the pressure supply or pressure control of the lower wing chambers via the opposite or similar lower wing recess of the second end wall differs from one another, for example in such a way that a lower wing chamber, after being fluidically connected to both lower wing recesses, is still fluidically connected to one lower wing recess after a further rotation of the rotor in the direction of rotation, but is already fluidically separated from the other lower wing recess. For example, the lower wing recesses according to the invention can be used to switch between an axially bilateral and an axially unilateral pressure supply of a lower wing chamber, in particular within an ascending or descending region. An angle-dependent, axially asymmetrical pressure supply of a lower wing chamber can be implemented.

Control edges of the same type can be control edges which fulfill the same function of the axially opposite or similar lower wing recesses, for example each defining or forming the end or the beginning of the lower wing recess, for example the first ascending, the first descending, the second ascending or the second descending lower wing recess of the end walls . If the similar control edges each form one end of their lower wing recess, the lower wing recess of the first end wall, viewed in the direction of rotation, can end earlier or later than the opposite or similar lower wing recess of the second end wall, whereby the pressure supply of a lower wing chamber via the lower wing recess of the first end wall ends sooner or later as the pressure supply of the lower wing chamber via the lower wing recess of the second end wall. If the similar control edges each form the beginning of their lower wing recess, the lower wing recess of the first end wall, viewed in the direction of rotation, can start earlier or later than the opposite or similar lower wing recess of the second end wall, whereby the pressure supply of a lower wing chamber via the lower wing recess of the first end wall sooner or later begins as the pressure supply to the lower wing chamber via the lower wing recess of the second end wall.

The control edges can differ from one another in their shape, for example acute angles versus obtuse angles, inwardly kinked / bent versus outwardly kinked / bent, curved versus straight, ramp rising radially inward versus ramp falling radially outward. Furthermore, the control edges of the same type can differ from one another in their extension, for example with regard to their width, depth, length. The control edges can be offset from one another in the radial direction and / or in the circumferential direction.

The angular offset or distance between two similar control edges is advantageous in the projection between a first straight line (leg), which in the projection along the axis of rotation forms a tangent to the one control edge and intersects the axis of rotation, and a second straight line (leg), which forms a tangent to the other (similar) control edge in the projection along the axis of rotation and intersects the axis of rotation, measured, the axis of rotation forming the apex of the angle. The angular offset or distance between two similar control edges is preferably greater than 5 °, advantageously greater than 10 ° and particularly advantageously greater than 15 °.

Accordingly, the control edge of the lower wing recess of the first end wall and the similar control edge of the lower wing recess of the second end wall can be angularly offset around the axis of rotation of the rotor as a vertex.

The control edge of the lower wing recess of the first end wall and the similar control edge of the opposite or similar lower wing recess of the second end wall are preferably offset from one another by at least a width of the opening of the lower wing chamber pointing in the direction of rotation. The angular offset or spacing between two similar control edges is preferably at least one width, directed in the direction of rotation, of the opening of the lower wing chamber pointing towards the end wall. This makes it possible to realize that in at least one rotational position of the rotor at least one of the lower wing chambers is connected in a fluid-communicating manner to an under wing recess of one end wall and at the same time is fluidically separated from the opposite or similar under wing recess of the other end wall and therefore preferably only by one of the opposite or similar ones Under wing recesses with Pressure is supplied. As a result, there is advantageously only an axially unilateral pressure supply to this lower wing chamber.

Due to the offset similar control edges, the rotor has an angular position in which a lower wing recess, for example the first descending lower wing recess, the first end wall fluidically separated from a lower wing chamber and the opposite or similar lower wing recess, for example the first descending lower wing recess, the second end wall with this lower wing chamber is fluidly connected.

The rotor can advantageously assume a first rotational position in which the lower wing recess of the first end wall is connected in fluid communication with one of the lower wing chambers and the opposite or similar lower wing recess of the second end wall is also connected in fluid communication with this lower wing chamber, and a second rotational position different from the first rotational position occupy, in which the lower wing recess of the first end wall fluidly separated from one of the lower wing chambers and the opposite or similar lower wing recess of the second end wall is fluidly connected to this lower wing chamber. As an alternative or in addition to the second rotational position, the rotor can assume a third rotational position different from the first and / or second rotational position, in which the lower wing recess of the second end wall is fluidically separated from one of the lower wing chambers and the opposite or similar lower wing recess of the first end wall is in fluid communication with this lower wing chamber connected is.

In particular, due to the offset of the similar control edges, the angular distance around the axis of rotation of the rotor between a dead center and the control edge of the lower wing recess of the first end wall adjacent to the dead center and the angular distance around the axis of rotation of the rotor between a dead center and the similar control edge adjacent to the dead center is the opposite or similar lower wing recess of the second end wall, preferably of different sizes.

The rotor can preferably assume a rotational position in which the lower wing recess of the first end wall and the opposite or similar lower wing recess of the second end wall are connected in fluid communication with the same lower wing chamber when the wing assigned to it is located in the first, descending area or the second, ascending area , and assume a rotational position, in particular after a further rotation in the direction of rotation, in which the lower wing recess of the first end wall fluidically from a Separate lower wing chamber and the opposite or similar lower wing recess of the second end wall is fluidly connected to this lower wing chamber when the wing assigned to it is in the first, descending area or the second, ascending area.

The vane pump is preferably adapted so that, during the rotation of the rotor, a lower wing chamber is connected in fluid communication with the, in particular first, descending lower wing recess of the one, in particular second, end wall, until this lower wing chamber is in fluid communication with the, in particular second, rising lower wing recess of the other, in particular first, end wall is or will be connected.

• von einer, insbesondere ersten, absteigenden Unterflügelausnehmung der einen, insbesondere ersten, Stirnwand, fluidisch getrennt ist, aber mit der gegenüberliegenden oder gleichartigen, insbesondere ersten, absteigenden Unterflügelausnehmung der anderen, insbesondere zweiten, Stirnwand fluidkommunizierend verbunden ist, und gleichzeitig
• mit einer, insbesondere zweiten, aufsteigenden Unterflügelausnehmung der einen, insbesondere ersten, Stirnwand fluidkommunizierend verbunden ist, aber von der gegenüberliegenden oder gleichartigen, insbesondere zweiten, aufsteigenden Unterflügelausnehmung der anderen, insbesondere zweiten, Stirnwand, fluidisch getrennt ist.

The rotor can advantageously assume a rotational position in which at least one of the lower wing chambers

• is fluidically separated from one, in particular first, descending lower wing recess of one, in particular first, end wall, but is connected in fluid communication with the opposite or similar, in particular first, descending under wing recess of the other, in particular second, end wall, and at the same time
• is connected to a, in particular second, ascending lower wing recess of the one, in particular first, end wall in a fluid-communicating manner, but is fluidically separated from the opposite or similar, in particular second, ascending under wing recess of the other, in particular second, end wall.

The lower wing chamber of a wing that passes through the, in particular the lower, dead center or constant area, is preferably still connected to the, in particular the first, descending lower wing recess of the one, in particular the second, end wall, but preferably already by the, in particular the first, descending lower wing recess of the other, in particular the first, end wall fluidically separated, and already connected in fluid communication with the, in particular the second, ascending lower wing recess of the other, in particular first, end wall, but preferably still fluidically separated from the, in particular second, rising under wing recess of the one, in particular the second, end wall when this wing is at or in, in particular the lower, constant range or at its dead center.

• einen um eine Drehachse drehbaren Rotor und mehrere von dem Rotor verschiebbar geführte Flügel, wobei der Rotor je Flügel eine Unterflügelkammer aufweist und jeder Flügel eine verschiebbare Wand seiner ihm zugeordneten Unterflügelkammer bildet,
• einen Konturring mit einer sich um die Drehachse erstreckenden Innenkontur, an welcher die Flügel entlanggleiten, wenn der Rotor gedreht wird, wobei die Innenkontur des Konturrings angepasst ist, zumindest einen aufsteigenden Bereich, beispielsweise einen ersten aufsteigenden Bereich und einen zweiten aufsteigenden Bereich, und zumindest einen absteigenden Bereich, beispielsweise einen ersten absteigenden Bereich und einen zweiten absteigenden Bereich, zu definieren, wobei der Flügel aus dem Rotor herausbewegt wird, während er über den aufsteigenden Bereich gleitet, und in den Rotor hineinbewegt wird, während er über den absteigenden Bereich gleitet,
• wobei die Stirnwand, insbesondere die erste Stirnwand, und eine weitere Stirnwand, insbesondere die zweite Stirnwand, jeweils Folgendes aufweisen:
  • ∘ zumindest eine aufsteigende Unterflügelausnehmung, beispielsweise eine erste aufsteigende Unterflügelausnehmung und eine zweite aufsteigende Unterflügelausnehmung, mit der eine Unterflügelkammer fluidkommunizierend verbunden ist, wenn ihr Flügel sich in dem aufsteigenden Bereich des Konturrings befindet,
  • ∘ zumindest eine absteigende Unterflügelausnehmung, beispielsweise eine erste absteigende Unterflügelausnehmung und eine zweite absteigende Unterflügelausnehmung, mit der eine Unterflügelkammer fluidkommunizierend verbunden ist, wenn ihr Flügel sich in dem absteigenden Bereich des Konturrings befindet,
  • ∘ einen zwischen der absteigenden Unterflügelausnehmung und der aufsteigenden Unterflügelausnehmung gebildeten Trennsteg, beispielsweise einen zwischen der ersten absteigenden Unterflügelausnehmung und der zweiten aufsteigenden Unterflügelausnehmung gebildeten Trennsteg und/oder einen zwischen der zweiten absteigenden Unterflügelausnehmung und der ersten aufsteigenden Unterflügelausnehmung gebildeten Trennsteg,
• wobei ein zwischen der absteigenden Unterflügelausnehmung und der aufsteigenden Unterflügelausnehmung der einen Stirnwand gebildeter Trennsteg um die Drehachse des Rotors als Scheitelpunkt zu einem dem Trennsteg entlang oder parallel zu der Drehachse betrachtet gegenüberliegenden, zwischen der absteigenden Unterflügelausnehmung und der aufsteigenden Unterflügelausnehmung der anderen Stirnwand gebildeten Trennsteg winkelversetzt angeordnet ist.

A second aspect of the invention relates to a vane pump comprising:

• a rotor rotatable about an axis of rotation and several vanes guided displaceably by the rotor, the rotor having a lower wing chamber for each wing and each wing forming a displaceable wall of its associated lower wing chamber,
• a contour ring with an inner contour extending around the axis of rotation, along which the vanes slide when the rotor is rotated, the inner contour of the contour ring being adapted, at least one ascending area, for example a first ascending area and a second ascending area, and at least one defining a descending area, for example a first descending area and a second descending area, wherein the vane is moved out of the rotor while sliding over the ascending area and is moved into the rotor while sliding over the descending area,
• wherein the end wall, in particular the first end wall, and a further end wall, in particular the second end wall, each have the following:
  • ∘ at least one rising lower wing recess, for example a first rising lower wing recess and a second rising lower wing recess, with which a lower wing chamber is connected in a fluid-communicating manner when its wing is located in the rising area of the contour ring,
  • ∘ at least one descending lower wing recess, for example a first descending lower wing recess and a second descending lower wing recess, with which a lower wing chamber is connected in fluid communication when its wing is located in the descending area of the contour ring,
  • ∘ a separating web formed between the descending lower wing recess and the ascending lower wing recess, for example a separating web formed between the first descending lower wing recess and the second ascending lower wing recess and / or a separating web formed between the second descending lower wing recess and the first ascending lower wing recess,
• wherein a separating web formed between the descending lower wing recess and the rising lower wing recess of one end wall is angularly offset around the axis of rotation of the rotor as a vertex to a separating web, viewed along or parallel to the axis of rotation, opposite, formed between the descending lower wing recess and the rising lower wing recess of the other end wall is.

The angular offset between two separators is advantageous in the projection along the axis of rotation, i. H. measured parallel to the axis of rotation, between a straight line (leg) intersecting the axis of rotation of the rotor through the center point of one separating web and a straight line (leg) intersecting the axis of rotation of the rotor through the center point of the other (opposite or similar) separating web, the axis of rotation being the vertex of the angle forms. The center point of a separating web is preferably on the bisector of the angular distance around the axis of rotation of the rotor as the apex between the control edges which limit the separating web in the direction of rotation of the rotor. The angular offset between two opposing or similar separating webs is preferably greater than 5 °, advantageously greater than 10 ° and particularly advantageously greater than 15 °.

For example, the separating web of the first end wall and the similar or opposite separating web of the second end wall can preferably partially, in particular only partially and not completely, overlap in the projection along the axis of rotation, in particular in an overlapping area.

Advantageously, the circumferential width of the overlap region is smaller than the circumferential width of the opening facing the first end face and / or the opening of the lower wing chamber facing the second end face. In this way, it can be realized that the lower wing chamber of a wing that passes through the overlap area preferably also has a, in particular first, descending lower wing recess of the one, in particular second, end wall and already with the, in particular second, ascending under wing recess of the other, in particular first, end wall is fluidly connected when this wing is on or in the overlap area.

The constant region, in particular the lower constant region, is advantageously arranged in the angular region of the separating web of the first end wall and / or in the angular region of the separating web of the second end wall, in particular in the angular region of the overlap region.

Preferably, the separating web of the first end wall and / or the separating web of the second end wall has a circumferential width which is greater than the circumferential width of the opening pointing to the first end face and / or the opening of the second end face pointing Lower wing chamber. This can be realized that the relevant separating web in a rotational position of the rotor can completely close the opening of a lower wing chamber facing the front wall and / or that the rotor has or can assume a rotational position in which at least one of the lower wing chambers is fluidically separated from the two circumferentially adjacent lower wing recesses of a front wall is separated.

• einen Rotor und mehrere von dem Rotor verschiebbar geführte Flügel, wobei der Rotor je Flügel eine Unterflügelkammer aufweist und jeder Flügel eine verschiebbare Wand seiner ihm zugeordneten Unterflügelkammer bildet,
• einen Konturring mit einer sich um die Drehachse des Rotors erstreckenden Innenkontur, an welcher die Flügel entlanggleiten, wenn der Rotor gedreht wird, wobei die Innenkontur des Konturrings angepasst ist, zumindest einen aufsteigenden Bereich und zumindest einen absteigenden Bereich zu definieren, wobei ein Flügel aus dem Rotor herausbewegt wird, während er über den aufsteigenden Bereich gleitet, und in den Rotor hineinbewegt wird, während er über den absteigenden Bereich gleitet,
• eine an den Rotor stirnseitig angrenzende Stirnwand, insbesondere erste oder zweite Stirnwand, welche zur Druckversorgung oder Drucksteuerung der Unterflügelkammer eine sich in Umfangsrichtung erstreckende Unterflügelausnehmung, insbesondere eine erste absteigende Unterflügelausnehmung, mit einer Steuerkante, die in der Drehrichtung ein Ende der ersten Unterflügelausnehmung bildet, und eine weitere, sich in Umfangsrichtung erstreckende Unterflügelausnehmung, insbesondere eine zweite aufsteigende Unterflügelausnehmung, mit einer Steuerkante, die in Drehrichtung des Rotors einen Anfang der weiteren Unterflügelausnehmung bildet, aufweist,
• wobei die Innenkontur zwischen dem absteigenden Bereich und dem aufsteigenden Bereich einen Konstantbereich oder einen Bereich aufweist, der angepasst ist, für den Flügel, der über diesen Bereich gleitet, in Bezug auf die Bewegung relativ zu dem Rotor einen Totpunkt, insbesondere oberen oder unteren Totpunkt, zu definieren,
• wobei der Winkelabstand um die Drehachse des Rotors als Scheitelpunkt zwischen dem Bereich, insbesondere einem Mittelpunkt oder dem Totpunkt des Bereichs, und der Steuerkante der einen Unterflügelausnehmung und der Winkelabstand zwischen dem Bereich, insbesondere dem Mittelpunkt oder dem Totpunkt des Bereichs, und der Steuerkante der weiteren Unterflügelausnehmung unterschiedlich groß sind.

A third aspect of the invention relates to a vane pump comprising:

• a rotor and several vanes guided displaceably by the rotor, the rotor having a lower wing chamber for each wing and each wing forming a displaceable wall of its associated lower wing chamber,
• a contour ring with an inner contour extending around the axis of rotation of the rotor, along which the blades slide when the rotor is rotated, the inner contour of the contour ring being adapted to define at least one ascending area and at least one descending area, one blade from the The rotor is moved out while sliding over the ascending region and is moved into the rotor while it is sliding over the descending region,
• an end wall adjoining the end face of the rotor, in particular a first or second end wall, which, for the pressure supply or pressure control of the lower wing chamber, has a circumferentially extending lower wing recess, in particular a first descending lower wing recess, with a control edge which forms one end of the first lower wing recess in the direction of rotation, and has a further lower wing recess extending in the circumferential direction, in particular a second ascending lower wing recess, with a control edge which forms a start of the further lower wing recess in the direction of rotation of the rotor,
• wherein the inner contour between the descending area and the ascending area has a constant area or an area which is adapted for the wing that slides over this area, with respect to the movement relative to the rotor, a dead center, in particular top or bottom dead center, define,
• the angular distance around the axis of rotation of the rotor as the apex between the area, in particular a center point or the dead point of the area, and the control edge of the one underwing recess and the angular distance between the area, in particular the center point or the dead point of the area, and the control edge of the other Lower wing recess are of different sizes.

The angular distance around the axis of rotation of the rotor as the vertex between a control edge and a constant area or an area that defines an upper or lower dead point for a wing is advantageously used in a projection along the axis of rotation, i.e. H. parallel to the axis of rotation, between a straight line (leg) intersecting the axis of rotation, which in the projection along the axis of rotation forms a tangent to the control edge and a straight line intersecting the axis of rotation through the center point - based on the direction of rotation of the rotor, the center point between the beginning and the end of the constant range - or the dead center of the constant range or the range that defines the dead center for the wing. The center point or the dead point of the range or constant range is preferably on an angle bisector of the angular distance around the axis of rotation as the vertex between the start and the end of the range or constant range. The center of the area preferably forms the dead center of the area or the dead center of the area forms the center of the area.

The angular distance between the, preferably lower, area, in particular the center point or the dead center of the area, and the control edge of the, in particular first, descending lower wing recess of the one, in particular second, end wall is smaller than the angular distance between the area, in particular the center point or the dead center of the area, and the control edge of the, in particular the second, ascending lower wing recess of this, in particular the second, end wall and the angular distance between the area, in particular the center point or the dead center of the area, and the control edge of the, in particular the first, descending lower wing recess of the other, in particular the first, end wall greater than the angular distance between the area, in particular the center point or the dead center of the area, and the control edge of the, in particular the second, ascending lower wing recess of this, in particular the first, end wall.

The angular distance between the, preferably lower, area, in particular the center point or the dead center of the area, and the control edge of the, in particular first, descending lower wing recess of the one, in particular first, end wall is greater, equal to or smaller than the angular distance between the area, in particular the center point or the dead point of the area, and the control edge of the, in particular the first, descending lower wing recess of the other, in particular the second, end wall.

The angular distance between the, preferably lower, area, in particular the center point or the dead center of the area, and the control edge of the, in particular the second, ascending lower wing recess of the one, in particular the first, end wall is preferably larger, equal or smaller than the angular distance between the area, in particular the center point or the dead center of the area, and the control edge of the, in particular the second, ascending lower wing recess of the other, in particular the second, end wall.

The angular distance between the, preferably lower, area, in particular the center point or the dead center of the area, and the control edge of the, in particular first, descending lower wing recess of the one, in particular first, end wall is greater, equal to or smaller than the angular distance between the area, in particular the center point or the dead point of the area, and the control edge of the, in particular the second, ascending lower wing recess of the other, in particular the second, end wall.

In particular in the case of a multi-flow or multi-stroke vane pump, the, in particular the lower, constant range extends asymmetrically into two adjacent flows, ie. H. in particular so that the constant area is arranged in a first tide and a second tide adjacent to the first tide, its circumferential extent in one tide being greater than the circumferential extent in the other tide.

• einen Rotor und mehrere von dem Rotor verschiebbar geführte Flügel, wobei der Rotor je Flügel eine Unterflügelkammer aufweist und jeder Flügel eine verschiebbare Wand seiner ihm zugeordneten Unterflügelkammer bildet,
• einen Konturring mit einer sich um die Drehachse des Rotors erstreckenden Innenkontur, an welcher die Flügel entlanggleiten, wenn der Rotor gedreht wird, wobei die Innenkontur des Konturrings angepasst ist, zumindest einen aufsteigenden Bereich und zumindest einen absteigenden Bereich zu definieren, wobei ein Flügel aus dem Rotor herausbewegt wird, während er über den aufsteigenden Bereich gleitet, und in den Rotor hineinbewegt wird, während er über den absteigenden Bereich gleitet,
• eine an den Rotor stirnseitig angrenzende Stirnwand, insbesondere erste oder zweite Stirnwand, welche zur Druckversorgung oder Drucksteuerung der Unterflügelkammer eine sich in Umfangsrichtung erstreckende Unterflügelausnehmung, insbesondere eine erste absteigende Unterflügelausnehmung, mit einer Steuerkante, die in der Drehrichtung ein Ende der ersten Unterflügelausnehmung bildet, und eine weitere, sich in Umfangsrichtung erstreckende Unterflügelausnehmung, insbesondere eine zweite aufsteigende Unterflügelausnehmung, mit einer Steuerkante, die in Drehrichtung des Rotors einen Anfang der weiteren Unterflügelausnehmung bildet, aufweist, wobei zwischen den Steuerkanten ein Trennsteg gebildet ist,

• wobei die Innenkontur zwischen dem absteigenden Bereich und dem aufsteigenden Bereich einen Konstantbereich oder einen Bereich aufweist, der angepasst ist, für den Flügel, der über diesen Bereich gleitet, in Bezug auf die Bewegung relativ zu dem Rotor einen Totpunkt, insbesondere oberen oder unteren Totpunkt, zu definieren,
• wobei der Trennsteg, insbesondere ein in Umlaufrichtung des Rotors zwischen den Steuerkanten gebildeter Mittelpunkt des Trennstegs, um die Drehachse als Scheitelpunkt winkelversetzt zu dem Bereich oder Konstantbereich, insbesondere einem Mittelpunkt oder dem Totpunkt des Bereichs oder Konstantbereichs, ist.

A fourth aspect of the invention relates to a vane pump comprising:

• a rotor and several vanes guided displaceably by the rotor, the rotor having a lower wing chamber for each wing and each wing forming a displaceable wall of its associated lower wing chamber,
• a contour ring with an inner contour extending around the axis of rotation of the rotor, along which the blades slide when the rotor is rotated, the inner contour of the contour ring being adapted to define at least one ascending area and at least one descending area, one blade from the The rotor is moved out while sliding over the ascending region and is moved into the rotor while it is sliding over the descending region,
• an end wall adjoining the end face of the rotor, in particular a first or second end wall, which, for the pressure supply or pressure control of the lower wing chamber, has a circumferentially extending lower wing recess, in particular a first descending lower wing recess, with a control edge which forms one end of the first lower wing recess in the direction of rotation, and a further lower wing recess extending in the circumferential direction, in particular a second ascending lower wing recess, with a control edge which has a beginning in the direction of rotation of the rotor the further lower wing recess forms, wherein a separating web is formed between the control edges,

• wherein the inner contour between the descending area and the ascending area has a constant area or an area which is adapted for the wing that slides over this area, with respect to the movement relative to the rotor, a dead center, in particular top or bottom dead center, define,
• wherein the separating web, in particular a center point of the separating web formed in the direction of rotation of the rotor between the control edges, is angularly offset around the axis of rotation as a vertex to the area or constant area, in particular a center point or the dead center of the area or constant area.

The angular offset or distance between a separating web and a constant area or an area that defines an upper or lower dead point for a wing is advantageously related in the projection along the axis of rotation of the rotor between a straight line (leg) intersecting the axis of rotation through the center point in relation to the direction of rotation of the rotor the midpoint between the beginning and the end - of the separating web and a straight line (leg) intersecting the axis of rotation through the midpoint - in relation to the direction of rotation of the rotor the midpoint between the beginning and the end - of the constant range or the area, which defines the dead center for the wing, or measured the dead center. The center point or dead point of the range or constant range is preferably on an angle bisector of the angular distance around the axis of rotation as the vertex between the beginning and the end of the range or constant range. The center point of the separating web is preferably on an angle bisector of the angular distance around the axis of rotation as the apex between the beginning and the end of the separating web. The center of the area preferably forms the dead center of the area or the dead center of the area forms the center of the area.

The center point of the separating web is preferably angularly offset around the axis of rotation as the vertex to the center point or the, in particular the lower, dead point of the area or, in particular, the lower, constant area.

In particular in the case of a multi-flow or multi-stroke vane pump, the separating web of an end wall can extend asymmetrically into two adjacent flows, i.e. in particular that the separating web of the end wall is arranged in a first flow and a second flow adjacent to the first flow, with its circumferential extent in one flow is greater than the circumferential extent in the other flood.

• einen Rotor und mehrere von dem Rotor verschiebbar geführte Flügel, wobei der Rotor je Flügel eine Unterflügelkammer aufweist und jeder Flügel eine verschiebbare Wand seiner ihm zugeordneten Unterflügelkammer bildet,
• einen Konturring mit einer sich um die Drehachse des Rotors erstreckenden Innenkontur, an welcher die Flügel entlanggleiten, wenn der Rotor gedreht wird, wobei die Innenkontur des Konturrings angepasst ist, einen ersten aufsteigenden Bereich und einen ersten absteigenden Bereich, die einer ersten Flut zugeordnet sind, und einen zweiten aufsteigenden Bereich und einen zweiten absteigenden Bereich, die der zweiten Flut zugeordnet sind, zu definieren, wobei ein Flügel aus dem Rotor herausbewegt wird, während er über den aufsteigenden Bereich gleitet, und in den Rotor hineinbewegt wird, während er über den absteigenden Bereich gleitet,
• wobei die Stirnwand, insbesondere eine aus einer ersten Stirnwand und einer zweiten Stirnwand, oder die Stirnwand und eine weitere Stirnwand jeweils:
  • ∘ eine erste aufsteigende Unterflügelausnehmung, mit der eine Unterflügelkammer fluidkommunizierend verbunden ist, wenn ihr Flügel sich in dem ersten aufsteigenden Bereich des Konturrings befindet,
  • ∘ eine erste absteigende Unterflügelausnehmung, mit der eine Unterflügelkammer fluidkommunizierend verbunden ist, wenn ihr Flügel sich in dem ersten absteigenden Bereich des Konturrings befindet,
  • ∘ eine zweite aufsteigende Unterflügelausnehmung, mit der eine Unterflügelkammer fluidkommunizierend verbunden ist, wenn ihr Flügel sich in dem zweiten aufsteigenden Bereich des Konturrings befindet,
  • ∘ eine zweite absteigende Unterflügelausnehmung, mit der eine Unterflügelkammer fluidkommunizierend verbunden ist, wenn ihr Flügel sich in dem zweiten absteigenden Bereich des Konturrings befindet,
  • ∘ einen zwischen der ersten absteigenden Unterflügelausnehmung und der zweiten aufsteigenden Unterflügelausnehmung gebildeten Trennsteg und
  • ∘ einen zwischen der zweiten absteigenden Unterflügelausnehmung und der ersten aufsteigenden Unterflügelausnehmung gebildeten Trennsteg
    aufweisen, wobei
• die Trennstege zueinander um die Drehachse als Scheitelpunkt um einen Winkel ungleich 180° versetzt sind.

A fifth aspect of the invention relates to a vane pump with a double-flow or double-stroke design, for example, which comprises the following:

• a rotor and several vanes guided displaceably by the rotor, the rotor having a lower wing chamber for each wing and each wing forming a displaceable wall of its associated lower wing chamber,
• a contour ring with an inner contour extending around the axis of rotation of the rotor, along which the blades slide when the rotor is rotated, the inner contour of the contour ring being adapted, a first ascending area and a first descending area which are assigned to a first tide, and define a second ascending area and a second descending area associated with the second tide, wherein a vane is moved out of the rotor as it slides over the ascending area and is moved into the rotor as it is over the descending one Area slides,
• wherein the end wall, in particular one of a first end wall and a second end wall, or the end wall and a further end wall each:
  • ∘ a first ascending lower wing recess, with which a lower wing chamber is connected in a fluid-communicating manner when its wing is located in the first ascending area of the contour ring,
  • ∘ a first descending lower wing recess with which a lower wing chamber is connected in a fluid-communicating manner when its wing is located in the first descending area of the contour ring,
  • ∘ a second ascending lower wing recess, with which a lower wing chamber is connected in a fluid-communicating manner when its wing is located in the second rising area of the contour ring,
  • ∘ a second descending lower wing recess with which a lower wing chamber is connected in a fluid-communicating manner when its wing is located in the second descending area of the contour ring,
  • ∘ a separating web formed between the first descending lower wing recess and the second rising lower wing recess and
  • ∘ a separating web formed between the second descending lower wing recess and the first rising lower wing recess
    have, where
• the separators are offset from one another around the axis of rotation as a vertex by an angle other than 180 °.

The angular offset between two separating webs is advantageously measured in the projection along the axis of rotation between a straight line (leg) intersecting the axis of rotation of the rotor through the center point of one separating web and a straight line (leg) intersecting the axis of rotation of the rotor through the center point of the other separating web, whereby the axis of rotation forms the vertex of the angle. The center point of a separating web is preferably on the bisector of the angular distance around the axis of rotation of the rotor as the apex between the control edges which limit the separating web in the direction of rotation of the rotor.

The word fluidic is to be understood as relating to fluid communication. When two components are fluidically connected, this means that they are connected in a fluid-communicating manner. When two components are fluidly separated or disconnected, it is meant that they are not connected in terms of fluid communication.

Figur 1

eine Draufsicht auf eine Flügelzellenpumpe mit einer Ansichtsebene senkrecht zu einer Drehachse eines Rotors bei abgenommener zweiter Stirnwand;

Figur 2

einen Schnitt entlang der Drehachse der Flügelzellenpumpe aus Figur 1;

Figur 3

eine Draufsicht von links auf eine erste Stirnwand der Flügelzellenpumpe aus Figur 2 mit einer Ansichtsebene senkrecht zur Drehachse des Rotors; und

Figur 4

eine Draufsicht von rechts auf eine zweite Stirnwand der Flügelzellenpumpe aus Figur 2 mit einer Ansichtsebene senkrecht zur Drehachse des Rotors.

The invention has been described on the basis of several embodiments and aspects. A preferred embodiment of the invention is described below. The features disclosed thereby advantageously develop the subject matter of the invention individually and in any combination of features. Show it:

Figure 1

a plan view of a vane pump with a plane of view perpendicular to an axis of rotation of a rotor with the second end wall removed;

Figure 2

a section along the axis of rotation of the vane pump Figure 1 ;

Figure 3

a top view from the left of a first end wall of the vane pump Figure 2 with a plane of view perpendicular to the axis of rotation of the rotor; and

Figure 4

a plan view from the right of a second end wall of the vane pump Figure 2 with a plane of view perpendicular to the axis of rotation of the rotor.

The example of a positive displacement pump shown in the figures is designed as a vane pump. The vane pump has a rotor 1, which is connected to a pump shaft 5 in a rotationally fixed manner, for example via a shaft-hub connection. The rotor 1 is surrounded on the outer circumference by a contour ring 10, which is often also referred to as a stroke ring. On a first side of the rotor 1, a first end wall 30, which is formed, for example, by a first housing part, in particular a side plate, adjoins the rotor 1 at the end, and a second end wall 20 adjoins the rotor 1 at the end on a second side of the rotor 1 , which is formed, for example, by a second housing part, in particular a pressure plate. The rotor 1 is between the first end wall 30 and the second end wall 20 bordered. The shaft 5 is rotatably mounted on the first end wall 30, in particular the first housing part, and / or the second end wall 20, in particular the second housing part, for example by means of a pivot bearing. The pivot bearing can be, for example, a roller bearing or a plain bearing. The rotor 1 is rotatable relative to the first end wall 30, the second end wall 20 and the contour ring 10. In the Figures 3 and 4 the direction of rotation of the rotor 1 in the conveying operation, ie when conveying fluid from an inlet 31, 35, 21, 25 to an outlet 32, 36, 22, 26, is indicated by means of arrows for the direction of rotation. The direction of rotation arrows in the Figures 3 and 4 are in opposite directions, as the Figure 3 the first end wall 30 based on the Figure 2 in a view from the left and the Figure 4 the second end wall 20 based on the Figure 2 show in a right view.

The contour ring 10 is enclosed between the first end wall 30 and the second end wall 20 and is non-rotatable relative to them. The space extending annularly around the shaft 5, which is surrounded by the inner circumference of the contour ring 10 and axially delimited by the first end wall 30 and the second end wall 20, can also be referred to as a pump chamber. The rotor 1 and vanes 2 supported by the rotor 1 are arranged in the pump chamber. In the example shown, the contour ring 10 is a separate part from the first housing part and the second housing part. Optionally, the contour ring 10 can be formed integrally with the first housing part or the second housing part.

In the example shown, the first end wall 30, in particular the first housing part, and the second end wall 20, in particular the second housing part, the contour ring 10 and the rotor 1 including the vanes 2, and optionally the shaft 5, form a pump insert that can be inserted into a, for example cup-shaped outer housing (not shown) can be used. The outer housing has at least one inner peripheral wall and an end wall. A first seal 7 and a second seal 8 can be arranged between the pump insert and the inner circumference of the outer housing. The first seal 7 can be arranged between the first housing part and the inner circumference of the outer housing. In particular, the first housing part can have a, in particular groove-shaped, recess running around its outer circumference, in which the in particular ring-shaped seal 7 (for example an O-ring) is seated. The second seal 8 can be arranged between the second housing part and the inner circumference of the outer housing. In particular, the second housing part can have a, in particular groove-shaped, recess running around its outer circumference, in which the, in particular, annular seal 8 (for example an O-ring) is seated. A suction chamber can be formed between the first seal 7 and the second seal 8, from which the fluid is conveyed via the pump chamber to at least one pressure chamber. The at least one pressure chamber can be arranged or formed between the end wall of the outer housing and the first housing part 30.

The vane pump shown in the example has a double-flow design, i. This means that fluid can be conveyed into the at least one pressure chamber via a first fluid path running through the pump chamber and a second fluid path running separately from the first fluid path through the pump chamber, in particular in the pump chamber, into the at least one pressure chamber. The at least one pressure chamber can be a common pressure chamber into which fluid is conveyed via the first fluid path and the second fluid path, or a first pressure chamber into which fluid is conveyed via the first fluid path, and a second pressure chamber into which fluid is conveyed via the second Fluid path is promoted include. The first pressure chamber and the second pressure chamber can be sealed off from one another, for example by means of a seal (not shown). The seal can for example be arranged between the end wall of the outer housing and the first housing part.

The first end wall and / or the second end wall, in particular the relevant housing part, can each have a recess open towards the blades 2, which forms a first inlet 31, 21, which is assigned to the first fluid path, arranged between the suction chamber and the pump chamber and connects the suction chamber and the pump chamber to one another in a fluid-communicating manner. The first end wall and / or the second end wall, in particular the relevant housing part, can each have a recess which is open towards the blades 2 and which forms a first outlet 32, 22 which is assigned to the first fluid path, between the at least one pressure chamber and the Pump chamber is arranged and connects the at least one pressure chamber and the pump chamber to one another in a fluid-communicating manner. The first housing part 30 can have the recess forming the first outlet 32, in particular a channel, which is open to the blades 2 and to the end wall of the outer housing and / or opens into the at least one pressure chamber, for example. The inlets 31, 21 are each designed as a radially open recess in the respective end wall 30, 20 or in the respective housing part. The inputs 31, 21 are axially opposite one another. The outlet 32 is designed as an opening in the first end wall 30 or the first housing part. The outlet 22 is designed as a recess in the second end wall 20 or the second housing part. The outputs 32, 22 are axially opposite one another. The outputs 32, 22 are connected to one another via a channel 102 in the contour ring 10. The channel 102 is designed as an opening in the contour ring 10.

The first end wall and / or the second end wall, in particular the relevant housing part, can each have a recess open towards the blades 2, which forms a second inlet 35, 25, which is assigned to the second fluid path, arranged between the suction chamber and the pump chamber and connects the suction chamber and the pump chamber to one another in a fluid-communicating manner. The first end wall and / or the second end wall, in particular the relevant housing part, can each have a recess which is open towards the blades 2 and which forms a second outlet 36, 26 which is assigned to the second fluid path, between the at least one pressure chamber and the Pump chamber is arranged and connects the at least one pressure chamber and the pump chamber to one another in a fluid-communicating manner. The first housing part 30 can have the recess forming the second outlet 36, in particular a channel, which is open to the blades 2 and to the end wall of the outer housing and / or opens into the at least one pressure chamber, for example. The inlets 35, 25 are each formed as a radially open recess in the respective end wall 30, 20 or in the respective housing part. The inputs 35, 25 are axially opposite one another. The outlet 36 is designed as an opening in the first end wall 30 or the first housing part. The outlet 26 is designed as a recess in the second end wall 20 or the second housing part. The outputs 36, 26 are axially opposite one another. The outputs 36, 26 are connected to one another via a channel 103 in the contour ring 10. The channel 103 is designed as an opening in the contour ring 10.

How best from the Figure 1 As can be seen, a first delivery chamber, which is assigned to the first fluid path, and a second delivery chamber, which is assigned to the second fluid path, are formed radially between the rotor 1 and the contour ring 10.

The rotor 1 has, in particular, slot-shaped recesses that serve as guides. A conveying element, namely a wing 2, is assigned to each of the recesses. Each of the vanes 2 is at its recess radially or away from the axis of rotation D of the rotor 1 and displaceable towards the axis of rotation D of the rotor 1, in particular guided with a single translational degree of freedom, displaceable back and forth, for example from the Figure 1 is recognizable. The blades 2 are rotated with the rotor 1. A delivery cell 4 is formed between adjacent blades 2, the volume of which changes as a function of the rotational position of the rotor 1 about its axis of rotation D. Since the pump has a plurality of vanes 2, in particular evenly distributed over the circumference, it also has a corresponding number of delivery cells 4. In each of the two delivery chambers there are several delivery cells 4. The blades 2 and the rotor 1 form with the first end wall 30 a first sealing gap and with the second end wall 20 a second sealing gap.

The inner circumferential surface of the contour ring 10 has an inner contour 101, which causes the vanes 2 to extend at least once (increase in volume of the delivery cell 4) and retract once (decrease in the volume of the delivery cell 4) during a full revolution of the rotor 1. The vane pump shown in the example of the figures is double-stroke, d. H. formed with two conveying chambers, the blades 2 extending once while passing through a conveying chamber and retracting once when they are moved through the conveying chamber by means of rotation of the rotor. This has the effect that the vanes 2 extend, retract, extend and retract again during one full revolution of the rotor 1, or, in other words, extend twice and retract twice. A conveyor cell 4 is formed between adjacent vanes 2, the volume of which is increased or decreased by the extension and retraction of the vanes 2 delimiting this conveyor cell 4, namely depending on the inner contour 101 of the inner circumferential surface of the contour ring 10.

The rotor 1 has a lower wing chamber 3 for each wing 2. Each wing 2 forms a movable wall of its associated lower wing chamber 3. Between the outer circumference of the rotor 1 and each of the lower wing chambers 3 there is a slot-shaped recess for guiding the respective wing 2. The lower wing chambers 3 can have a greater width extending in the circumferential direction than the slot-shaped recesses which are used to guide the wings 2. By selective pressurization and / or selective pressure relief of the relevant lower wing chamber 3 with pressurized fluid, the displaceable wall of the wing 2 can be acted upon by a force pointing away from the axis of rotation D or relieved of this force. Optionally, this force can also be reduced. On the one hand, one would like to prevent the wings 2 from lifting off the inner contour 101 in order to avoid losses due to leaks; on the other hand, one would like to prevent the wings 2 from being pressed too hard against the inner contour 101 in order to avoid friction-related wear and to keep friction-related energy consumption low .

Each of the lower wing chambers 3 has a first opening which opens out towards the first end wall, and a second opening which opens out towards the second end wall 20.

The first end wall 30 adjoining the end face on the first side of the rotor 1 has elongated ones in the circumferential direction for the pressure supply or pressure control of the lower wing chambers 3 extending, in particular curved about the axis of rotation D, lower wing recesses 33, 34, 37, 38 on ( Figure 3 ). The lower wing recesses 33, 34, 37, 38 each form an arcuate section that runs around the axis of rotation D and are arranged one behind the other or in series in the direction of rotation, so that each first opening of the lower wing chambers 3 each of the lower wing recesses 33, 34, 37, 38 during one complete revolution of the rotor 1 sweeps over one another. While a first opening sweeps over one of the lower wing recesses 33, 34, 37, 38, the lower wing chamber 3 assigned to this opening is fluidly connected to this lower wing recess, whereby the lower wing chamber 3 can be pressurized or depressurized, for example.

In the direction of rotation around the axis of rotation D, a separating web 335 is formed between the lower wing recess 33 and the lower wing recess 34, which separates the lower wing recesses 33 and 34 from one another. In the direction of rotation around the axis of rotation D, a separating web 345 is formed between the lower wing recess 34 and the lower wing recess 37, which separates the lower wing recesses 34 and 37 from one another. In the direction of rotation around the axis of rotation D, a separating web 375 is formed between the lower wing recess 37 and the lower wing recess 38, which separates the lower wing recesses 37 and 38 from one another. In the direction of rotation around the axis of rotation D, a separating web 385 is formed between the lower wing recess 38 and the lower wing recess 33, which separates the lower wing recesses 38 and 33 from one another.

The second end wall 20 adjoining the end face of the second side of the rotor 1 has elongated lower wing recesses 23, 24, 27, 28 extending in the circumferential direction, in particular curved about the axis of rotation D, for the pressure supply or pressure control of the lower wing chambers 3 ( Figure 4 ). The lower wing recesses 23, 24, 27, 28 each form an arcuate section rotating around the axis of rotation D and are arranged one behind the other or in series in the direction of rotation, so that every second opening of the lower wing chambers 3 each of the lower wing recesses 23, 24, 27, 28 during one complete revolution of the rotor 1 sweeps over one another. While a second opening sweeps over one of the lower wing recesses 23, 24, 27, 28, the lower wing chamber 3 assigned to this opening is fluidly connected to this lower wing recess, whereby the lower wing chamber 3 can be pressurized or depressurized, for example.

In the direction of rotation around the axis of rotation D, an in particular groove-shaped channel 239 which is open towards the rotor and which connects the lower wing recess 23 with the lower wing recess 24 is formed by the end wall between the lower wing recess 23 and the lower wing recess 24 connects fluid-communicating as a hydraulic bottleneck. The width and / or depth of the channel 239 is / are smaller than the width and / or depth of the end of the lower wing recess 23 and / or the lower wing recess 24 adjacent to the channel 239. A flank of the channel 239 is formed by a projection 235 which extends from the outer flank of the lower wing recess 23 and the outer flank of the lower wing recess 24 towards the axis of rotation D. A throttled fluid exchange between the recesses 23 and 24 can take place through the channel 239.

In the direction of rotation around the axis of rotation D, the end wall between the lower wing recess 27 and the lower wing recess 28 forms a particularly groove-shaped channel 279 which is open towards the rotor and which connects the lower wing recess 27 with the lower wing recess 28 as a hydraulic constriction in a fluid-communicating manner. The width and / or depth of the channel 279 is / are smaller than the width and / or depth of the end of the lower wing recess 27 and / or the lower wing recess 28 adjoining the channel 279. A flank of the channel 279 is formed by a projection 275 which extends from the outer flank of the lower wing recess 27 and the outer flank of the lower wing recess 28 towards the axis of rotation D. A throttled fluid exchange between the recesses 27 and 28 can take place through the channel 279.

The projection 235, 275 can be referred to as a separating web which connects the adjacent lower wing recesses to one another in a throttled manner. Alternatively, the channels 239 and / or 279 can be dispensed with and instead a separating web can be formed in the direction of rotation around the axis of rotation D between the under wing recesses 23 and 24 and / or 27 and 28, which fluidically separates the under wing recesses 23 and 24 or 27 and 28 from one another separates.

In the direction of rotation around the axis of rotation D, a separating web 245 is arranged between the lower wing recess 24 and the lower wing recess 27, which separates the lower wing recesses 24 and 27 from one another. In the direction of rotation around the axis of rotation D, a separating web 285 is arranged between the lower wing recess 28 and the lower wing recess 23, which separates the lower wing recesses 28 and 23 from one another.

During one full revolution of the rotor 1, the first openings of the lower wing chambers 3 not only sweep over the lower wing recesses 33, 34, 37, 38, but also the separating webs 335, 345, 375, 385, or the second openings of the lower wing chambers 3, not only the lower wing chambers 23, 24, 27, 28, but also the separating webs 245, 285 and the channels 239, 279 and / or the projections 235, 275 or the separating webs (not shown) provided as an alternative to the channels or projections.

How out Figure 3 As can be seen, the first housing part forming the first end wall 30 has a channel 334 which opens into the lower wing recess 33. The channel 334 connects the pressure side, for example the first outlet 32 or the at least one pressure chamber or the first pressure chamber in a fluid-communicating manner with the lower wing recess 33. As a result, the lower wing recess 33 and the lower wing chamber (s) 3, the first opening of which is in one position, are in which it at least partially overlaps the lower wing recess 33, supplied with pressure fluid. Furthermore, the first housing part has a channel 374 which opens into the lower wing recess 37. The channel 374 connects the pressure side, for example the second outlet 36 or the at least one pressure chamber or the second pressure chamber in a fluid-communicating manner with the lower wing recess 37. As a result, the lower wing recess 37 and the lower wing chamber (s) 3, the first opening of which is in one position, are in which it at least partially overlaps the lower wing recess 37, supplied with pressure fluid.

In this example, the lower wing recesses 34, 38 are closed off with respect to the suction side and the pressure side of the first end wall 30, that is to say that the first housing part does not have a channel that communicates the pressure side or the suction side of the first end wall 30 with the lower wing recesses 34, 38 connects. In an alternative embodiment, the channels 334, 374 can open into the lower wing recesses 34, 38, the lower wing recesses 33, 37 being closed off with respect to the suction side and the pressure side. In yet another alternative embodiment, in addition to that in the Figure 3 The arrangement shown, the first housing part form a further channel which opens into the lower wing recess 34 and connects the suction side or the pressure side fluidly communicating with the lower wing recess 34, and also form a further channel which opens into the lower wing recess 38 and the suction side or the pressure side with fluid communication the lower wing recess 38 connects.

How out Figure 4 As can be seen, the lower wing recesses 23, 24 are closed off in relation to the suction side and the pressure side of the second end wall 20, that is to say that the second housing part does not have a channel that communicates the pressure side or the suction side of the second end wall 20 with the lower wing recesses 23, 24 connects. The same applies mutatis mutandis to the lower wing recesses 27, 28. Accordingly, the lower wing recesses 27, 28 are closed off with respect to the suction side and the pressure side of the second end wall 20, that is, the second housing part does not have a channel that is the pressure side or the suction side of the second end wall 20 connects to the lower wing recesses 27, 28 in a fluid-communicating manner.

The lower wing recess 23 of the second end wall 20 is supplied with pressurized fluid via the lower wing chambers 3 from the lower wing recess 33 of the first end wall 30. The fluid flows axially through the lower wing chambers 3 from the lower wing recess 33 of the first end wall 30 into the lower wing recess 23 of the second end wall 20. The lower wing recess 24 of the second end wall 20 is supplied with pressure fluid via the channel 239 through the lower wing recess 23 of the second end wall 20. The lower wing recess 34 of the first end wall 30 is supplied with pressurized fluid via the lower wing chambers 3 from the lower wing recess 24 of the second end wall 20. The fluid flows axially through the lower wing chambers 3 from the lower wing recess 24 of the second end wall 20 into the lower wing recess 34 of the first end wall 30. As a result, the fluid is forced axially through the lower wing chambers 3 and thus the rotor 1, whereby the pressurization of the wings 2 is improved, in particular takes place evenly.

The lower wing recess 27 of the second end wall 20 is supplied with pressurized fluid via the lower wing chambers 3 from the lower wing recess 37 of the first end wall 30. The fluid flows axially through the lower wing chambers 3 from the lower wing recess 37 of the first end wall 30 into the lower wing recess 27 of the second end wall 20. The lower wing recess 28 of the second end wall 20 is supplied with pressure fluid via the channel 279 through the lower wing recess 27 of the second end wall 20. The lower wing recess 38 of the first end wall 30 is supplied with pressurized fluid via the lower wing chambers 3 from the lower wing recess 28 of the second end wall 20. The fluid flows axially through the lower wing chambers 3 from the lower wing recess 28 of the second end wall 20 into the lower wing recess 38 of the first end wall 30. As a result, the fluid is forced axially through the lower wing chambers 3 and thus the rotor 1, whereby the pressurization of the wings 2 is improved, in particular takes place evenly.

The lower wing recesses 33, 34, 37, 38, 23, 24, 27, 28 each have a control edge 331, 341, 371, 381, 231, 241, 271, 281 which, based on the direction of rotation of the rotor 1, has a beginning of their respective Form lower wing recess 33, 34, 37, 38, 23, 24, 27, 28. In the direction of rotation of the rotor 1, the lower wing recesses 33, 34, 37, 38, 23, 24, 27, 28 each have a control edge 332, 342, 372, 382, 232, 242, 272, 282 which, based on the direction of rotation of the Rotor 1 form one end of their respective lower wing recess 33, 34, 37, 38, 23, 24, 27, 28. The control edges 241, 232 are formed by the projection 235 and the control edges 281, 272 are formed by the projection 275.

The lower wing recesses 33, 34, 37, 38, 23, 24, 27, 28 each have a base which delimits the respective lower wing recess along the axis of rotation D with regard to its depth. While the lower wing recesses 34, 38, 23, 24, 27, 28 each have a continuous floor, the floor of the lower wing recesses 33, 37 is interrupted by the channels 334, 374 opening into the lower wing recesses 33, 37. The transition 333, at which the bottom of the lower wing recess 33 merges into a wall of the channel 334, is angularly offset to the control edge 331 and the control edge 332 relative to the axis of rotation D as the apex, in particular approximately in the middle, such as in the middle third between the control edges 331, 332 arranged. The bottom of the lower wing recess 33 is formed between the control edge 331 and the transition 333. The transition 373, at which the bottom of the lower wing recess 37 merges into a wall of the channel 374, is angularly offset to the control edge 371 and the control edge 372 with respect to the axis of rotation D as the apex, in particular closer to the control edge 372 than to the control edge 371, in particular arranged in the third of the lower wing recess 37 adjoining the control edge 372. The bottom of the lower wing recess 37 is formed between the control edge 371 and the transition 373.

The opening cross section of the channel 334 and the opening cross section of the channel 374 differ from one another. The opening cross section of the channel 334 is larger than the opening cross section of the channel 374. The channels 334, 374 are each formed as an opening in the first end wall 30 or the first housing part.

The width at the beginning of the lower wing recesses 33, 37, 23, 27, which extends in the radial direction in relation to the axis of rotation D, is smaller than the width, which extends in the radial direction in relation to the axis of rotation D, at the end of the respective lower wing recess 33, 37, 23, 27 The width at the beginning of the lower wing recesses 34, 38, 24, 28, which extends in the radial direction in relation to the axis of rotation D, is greater than the width, which extends in the radial direction in relation to the axis of rotation D, at the end of the respective lower wing recess 34, 38, 24, 28.

How out Figure 1 As can be seen, the contour ring 10 has the inner contour 101. The inner contour 101 has a first ascending area 11, a constant area 12, a first descending area 13, a constant area 14, a second ascending area 15, a constant area 16, a second descending area 17 and a constant area 18, which with a full revolution are traversed in the order mentioned by the wings 2 sliding along the inner contour 101. When a wing 2 passes through area 11 or 15, it moves it emerges from the rotor 1, which is why these areas are referred to as rising areas 11, 15. When a wing 2 passes through the area 13 or 17, it moves into the rotor 1, which is why these areas are referred to as descending areas 13, 17. The ascending area 11 and the descending area 13 are assigned to the first tide and are therefore referred to as the first ascending area 11 and the first descending area 13. The ascending area 15 and the descending area 17 are assigned to the second tide and are therefore referred to as the second ascending area 15 and the second descending area 17.

When the wings 2 pass through the ascending area 11, 15, the wings 2 extend, as a result of which the conveyor cells 4 adjoining these wings 2 enlarge. When the wings 2 pass through the descending area 13, 17, the wings 2 retract, as a result of which the conveyor cells 4 adjoining these wings 2 are reduced in size.

The entrance 31 and / or 21 is arranged in relation to the first ascending area 11 of the inner contour 101 in such a way that the wing 2, which slides along the first ascending area 11, sweeps over the entrance 31 or 21, whereby the on the wing 2 fills the adjacent pumping cell 4 with fluid from the inlet 31 and 21, respectively.

The lower wing recess 33 is arranged in relation to the first ascending area 11 of the inner contour 101 in such a way that the lower wing chamber 3, the associated wing 2 of which slides along the first rising area 11, is at least partially overlapping with the lower wing recess 33 with its first opening, whereby the lower wing recess 33 is connected to the lower wing chamber 3 in a fluid-communicating manner when the associated wing 2 is located in the first ascending region 11 of the inner contour 101. In this way, the extension of the wing 2 out of the rotor 1 can be supported by pressurized fluid from the lower wing recess 33 and it can be ensured that the wing 2 rests against the inner contour 101.

The lower wing recess 23 is arranged in relation to the first ascending area 11 of the inner contour 101 in such a way that the lower wing chamber 3, the associated wing 2 of which slides along the first rising area 11, is at least partially overlapping with the lower wing recess 23 with its second opening, whereby the lower wing recess 23 is connected to the lower wing chamber 3 in a fluid-communicating manner when the associated wing 2 is located in the first ascending region 11 of the inner contour 101. In this way, the extension of the wing 2 from the rotor 1 can be supported by fluid from the lower wing recess 23, the lower wing recess 24 being supplied with fluid from the via the channel 239 Lower wing recess 23 is supplied. It can also be ensured in this way that the wing 2 rests against the inner contour 101. The lower wing recess 23 is in turn supplied with fluid from at least one of the lower wing chambers 3, as will be described further below.

Due to the interaction between the lower wing chamber 3, the wing 2 of which passes through the first ascending area 11, and the lower wing recesses 33, 23, the latter can be referred to as the first rising lower wing recesses 23, 33.

The exit 32 and optionally the recess 22 formed by the second end wall 20 are arranged in relation to the first descending area 13 of the inner contour 101 in such a way that the wing 2, which slides along the first descending area 13, the exit 32 or the recess 22, whereby the pumping cell 4 adjacent to the wing 2 empties into the outlet 32 and optionally into the recess 22.

The lower wing recess 34 is arranged in relation to the first descending area 13 of the inner contour 101 in such a way that the lower wing chamber 3, the associated wing 2 of which slides along the first descending area 13, is with its first opening at least partially overlapping with the lower wing recess 34, whereby the lower wing recess 34 is connected to the lower wing chamber 3 in a fluid-communicating manner when the associated wing 2 is located in the first descending region 13 of the inner contour 101. It can thereby be ensured that the wing 2 also rests against the inner contour 101 when it is retracted.

The lower wing recess 24 is arranged in relation to the first descending area 13 of the inner contour 101 in such a way that the lower wing chamber 3, the associated wing 2 of which slides along the first descending area 13, with its second opening at least partially overlaps the lower wing recess 24, whereby the lower wing recess 24 is connected to the lower wing chamber 3 in a fluid-communicating manner when the associated wing 2 is located in the first descending region 13 of the inner contour 101. The fluid released from the lower wing chamber 3 into the lower wing recess 23 - as described above - flows through the channel 239 into the lower wing recess 24 and through the lower wing chambers 3 from the lower wing recess 24 into the lower wing recess 34 in partial overlap with the lower wing recess 34 and / or the second opening of which is at least partially overlapped with the lower wing recess 24, fluid is thereby supplied.

Due to the interaction between the lower wing chamber 3, the wing 2 of which passes through the first descending region 13, and the lower wing recesses 34, 24, the latter can be referred to as the first descending lower wing recesses 24, 34.

The entrance 35 and / or 25 is arranged in relation to the second ascending area 15 of the inner contour 101 in such a way that the wing 2, which slides along the second ascending area 15, sweeps over the entrance 35 or 25, whereby the on the wing 2 adjoining pumping cell 4, filled with fluid from the inlet 35 and 25, respectively. The lower wing recess 37 is arranged in relation to the second ascending area 15 of the inner contour 101 in such a way that the lower wing chamber 3, the associated wing 2 of which slides along the second ascending area 15, with its first opening at least partially overlaps the lower wing recess 37, whereby the lower wing recess 37 is connected to the lower wing chamber 3 in a fluid-communicating manner when the associated wing 2 is located in the second ascending region 15 of the inner contour 101. In this way, the extension of the wing 2 out of the rotor 1 can be supported by pressurized fluid from the lower wing recess 37. The lower wing recess 27 is arranged in relation to the second ascending area 15 of the inner contour 101 in such a way that the lower wing chamber 3, the associated wing 2 of which slides along the second rising area 15, with its second opening at least partially overlaps the lower wing recess 27, whereby the lower wing recess 27 is connected to the lower wing chamber 3 in a fluid-communicating manner when the associated wing 2 is located in the second ascending region 15 of the inner contour 101. In this way, the extension of the wing 2 out of the rotor 1 can be supported by fluid from the lower wing recess 27, the lower wing recess 28 being supplied with fluid from the lower wing recess 27 via the channel 279. The lower wing recess 27 is in turn supplied with fluid from at least one of the lower wing chambers 3, as will be described further below.

Due to the interaction between the lower wing chamber 3, the wing 2 of which passes through the second ascending area 15, and the lower wing recesses 37, 27, the latter can be referred to as second rising lower wing recesses 27, 37.

The exit 36 and optionally the recess 26 formed by the second end wall 20 are arranged in relation to the second descending area 17 of the inner contour 101 in such a way that the wing 2, which slides along the second descending area 17, the exit 36 or the recess 26, whereby the pumping cell 4 adjoining the wing 2 empties into the outlet 36 and optionally into the recess 26. The under wing recess 38 is relative to the second The descending area 17 of the inner contour 101 is arranged so that the lower wing chamber 3, the associated wing 2 of which slides along the second descending area 17, is at least partially overlapping with the lower wing recess 38 with its first opening, whereby the lower wing recess 38 is connected to the lower wing chamber 3 in a fluid-communicating manner is when the assigned wing 2 is located in the second descending area 17 of the inner contour 101.

The lower wing recess 28 is arranged in relation to the second descending area 17 of the inner contour 101 in such a way that the lower wing chamber 3, the associated wing 2 of which slides along the second descending area 17, with its second opening at least partially overlaps the lower wing recess 28, whereby the lower wing recess 28 is connected to the lower wing chamber 3 in a fluid-communicating manner when the associated wing 2 is located in the second descending region 17 of the inner contour 101. The fluid released from the lower wing chamber 3 into the lower wing recess 27 - as described above - flows through the channel 279 into the lower wing recess 28 and through the lower wing chambers 3 from the lower wing recess 28 into the lower wing recess 38 in partial overlap with the lower wing recess 38 and / or the second opening of which is at least partially overlapped with the lower wing recess 28, fluid is thereby supplied.

Due to the interaction between the lower wing chamber 3, the wing 2 of which passes through the second descending area 17, and the lower wing recesses 38, 28, the latter can be referred to as second descending lower wing recesses 28, 38.

Between the first ascending area 11 and the first descending area 13 and between the second ascending area 15 and the second descending area 17, the inner contour 101 forms a constant area 12 or 16. Between the first descending area 13 and the second ascending area 15 and between the second descending area 17 and the first ascending area 11, the inner contour 101 forms a constant area 14 and 18, respectively. The constant areas 12, 14, 16, 18 are designed so that the wings 2, when they are moved through the constant area, in relation stand still on the rotor 1, d. H. neither retract nor extend. For example, the inner contour 101 can have a circular arc shape around the axis of rotation D as the center in the constant regions.

When a wing 2 passes through the constant range 12 or 16, it assumes a top dead center, at which its direction of movement with respect to the rotor is reversed. The constant ranges 12 and 16 can therefore be referred to as upper constant ranges 12, 16. Since the upper constant range 12 is assigned to the first tide, it can be referred to as the first upper constant range. Since the upper constant range 16 is assigned to the second tide, it can be referred to as the second upper constant range. When a wing passes through the constant range 14 or 18, it assumes a bottom dead center, at which its direction of movement with respect to the rotor 1 is reversed. The constant ranges 14 and 18 can therefore be referred to as lower constant ranges 14, 18. The constant areas 14, 18 separate the first and second tides from one another and are therefore not assigned to a specific tide or exclusively to one of the tides.

In the in the Figure 1 The example shown, the angular distance between two adjacent blades 2 is smaller than the angular distance between the beginning and the end of the constant range 12, 14, 16, 18. In other words, the rotor 1 can be rotated with respect to the contour ring 10 in one or more positions , in which a delivery cell 4 is completely in one of the constant areas 12, 14, 16, 18. In the in the Figure 1 As shown in the example shown, the rotor 1 can even be rotated in relation to the contour ring 10 into one or more positions in which at the same time a delivery cell 4 is located in the constant areas 12, 14, 16, 18.

The angular distance between two adjacent blades 2 is smaller than the angular distance between the opening of the inlet 31 opening into the pump chamber and the opening of the output 32 opening into the pump chamber Input 31 and output 32 are bridged or short-circuited. Alternatively or additionally, the angular distance between two adjacent blades 2 is smaller than the angular distance between the opening of the inlet 35 opening into the pump chamber and the opening of the outlet 36 opening into the pump chamber. This also prevents a delivery cell 4 from being able to assume a position in which it bridges or shorts the input 35 and the output 36.

The angular distance between two adjacent blades 2 is smaller than the angular distance between the opening of the first outlet 32 opening into the pump chamber and the opening of the second input 35 opening into the pump chamber. This prevents a pumping cell 4 from being able to assume a position in which it bridges or shorts the output 32 and the input 35. Alternatively or additionally, the angular distance between two adjacent blades 2 is smaller than the angular distance between the opening of the second outlet 36 opening into the pump chamber and the opening of the first input 31 opening into the pump chamber this prevents a conveyor cell 4 from being able to assume a position in which it bridges or short-circuits the output 36 and the input 31.

The lower wing recess 23 of the second end wall 20 lies axially opposite the lower wing recess 33. The lower wing recesses 23, 33 are similar to one another. They are both arranged in the first ascending area 11. The lower wing recess 24 lies axially opposite the lower wing recess 34. The lower wing recesses 24, 34 are similar to one another. They are both arranged in the first descending area 13. The lower wing recess 27 lies axially opposite the lower wing recess 37. The lower wing recesses 27, 37 are similar to one another. They are both arranged in the second ascending area 15. The lower wing recess 28 lies axially opposite the lower wing recess 38. The lower wing recesses 28, 38 are similar to one another. They are both arranged in the second descending area 17. The projection of the respective lower wing recess 23, 24, 27, 28 of the second end wall 20 along the axis of rotation D overlaps the respectively opposite lower wing recess 33, 34, 37, 38 of the first end wall 30, and vice versa. In the Figure 3 a section of the lower wing recess 24 overlapping the lower wing recess 34 in the projection is shown in the form of a dotted line in which the control edge 242 is marked accordingly. In the Figure 4 the projection of the control edge 342 is shown in the form of a dotted line. Furthermore, in the Figure 3 the projection of the control edge 271 is shown in the form of a dotted line. In the Figure 4 a section of the lower wing recess 37 overlapping the lower wing recess 27 in the projection is shown in the form of a dotted line in which the control edge 371 is marked accordingly.

In particular, a lower vane chamber 3 in a rotational angle position of the rotor 1 in which the vane 2 assigned to it is located in the first ascending area 11, in fluid communication with the lower vane recesses 23 and 33, in a rotational angle position of the rotor 1 in which the vane assigned to it is located 2 is located in the first descending area 13, communicating fluidly with the lower wing recesses 24 and 34, in a rotational angle position of the rotor 1 in which the wing 2 assigned to it is located in the second ascending area 15, communicating fluidly with the lower wing recesses 27 and 37, and in a rotational position of the rotor 1, in which the wing 2 assigned to it is located in the second descending region 17, can be connected to the lower wing recesses 27 and 38 in a fluid-communicating manner.

As from the Figures 3 and 4 As can be seen, the control edge 342 and the, in particular similar, control edge 242 are arranged angularly offset to one another in relation to the axis of rotation D as a vertex (in the projection along the axis of rotation D). This has the effect that when the rotor 1 rotates in the direction of rotation provided during operation (see direction of rotation arrows in FIGS Figures 3 and 4 ) the lower wing chamber 3 of a wing 2 is first separated from the lower wing recess 34 and then separated from the lower wing recess 24, in particular when the rotor 1 continues to rotate by an angle of rotation by which the control edges 342 and 242 are angularly offset about the axis of rotation D as a vertex. The rotor 1 can be rotated about the axis of rotation D into an angular position or have an angular position in which a lower wing chamber 3 is fluidly connected to the lower wing recess 24 and separated from the lower wing recess 34. For example, the control edges 242 and 342 can be angularly offset by an angle greater than 0 °, in particular greater than 5 ° and advantageously> 10 ° and / or <30 ° around the axis of rotation D as the vertex.

In alternative embodiments, the angular offset between the control edges 342 and 242 can be reversed. This can have the effect that the rotor 1 can be rotated into an angular position or can have an angular position in which a lower wing chamber 3 is fluidly connected to the lower wing recess 34 and separated from the lower wing recess 24.

The rotor 1, in particular from the angular position in which a lower wing chamber 3 is fluidly connected to the lower wing recess 24 and separated from the lower wing recess 34, can be rotated or further rotated about the axis of rotation D into an angular position or have an angular position in which the lower wing chamber 3 the fluid communication is separated from the lower wing recess 24 and from the lower wing recess 34. In particular, in this angular position, the first opening of this lower wing chamber 3 can be closed or covered by the separating web 345 and the second opening of this lower wing chamber 3 by the separating web 245.

As also from the Figures 3 and 4 can be seen, the control edge 371 and the, in particular similar, control edge 271 are arranged angularly offset to one another in relation to the axis of rotation D as a vertex. This has the effect that when the rotor 1 rotates in the direction of rotation provided during operation (see direction of rotation arrows in FIGS Figures 3 and 4 ) the lower wing chamber 3 of a wing 2 is only connected to the lower wing recess 37 in a fluid-communicating manner thereafter, in particular upon further rotation of the rotor 1 by an angle of rotation by which the control edges 371 and 271 are angularly offset, is connected to the lower wing recess 27 in a fluid-communicating manner. The rotor 1 can be rotated into an angular position or have an angular position in which a lower wing chamber 3 is connected to the lower wing recess 37 in a fluid-communicating manner and is separated from the lower wing recess 27. For example, the control edges 271 and 371 can be angularly offset by an angle greater than 0 °, in particular greater than 5 ° and advantageously> 10 ° and / or <30 ° around the axis of rotation D as the vertex.

In alternative embodiments, the angular offset between the control edges 371 and 271 can be reversed. This can have the effect that the rotor 1 can be rotated into an angular position or can have an angular position in which a lower wing chamber 3 is connected to the lower wing recess 27 in a fluid-communicating manner and is separated from the lower wing recess 37.

The rotor 1 can, in particular from the angular position in which a lower wing chamber 3 is separated from the lower wing recess 24 and from the lower wing recess 34 with regard to fluid communication, in particular when the first opening of this lower wing chamber 3 from the separating web 345 and the second opening of this lower wing chamber 3 from the separating web 245 is at least partially or completely closed or covered, rotated or further rotated about the axis of rotation D into an angular position or have an angular position in which the lower wing chamber 3 regarding fluid communication is (still) separated from the lower wing recess 27 and (already) with fluid communication the lower wing recess 37 is connected.

The rotor 1 can, in particular from the angular position in which the lower wing chamber 3 is (still) separated from the lower wing recess 27 and (already) connected to the lower wing recess 37 in a fluid communication manner, about the axis of rotation D into an angular position or further rotated or have an angular position in which the lower wing chamber 3 is fluidly connected to the lower wing recess 27 and is fluidly connected to the lower wing recess 37.

In the in the Figures 3 and 4 The example shown is around the axis of rotation D as the vertex of the angular offset between the control edges 371 and 271 smaller than the angular offset between the control edges 342 and 242. In alternative embodiments, the angular offset between the Control edges 371 and 271 may be greater than the angular offset between the control edges 342 and 242 or equal to the angular offset between the control edges 342 and 242.

In the example shown in the figures, the center point 14m of the constant region 14, i. H. the point - based on the direction of rotation of the rotor 1 - in the middle (bisector of the angle formed around the axis of rotation D as the vertex between the beginning and the end of the constant range 14) between the beginning and the end of the constant range 14, around the axis of rotation D as Vertex offset at an angle to control edges 342, 242, 371, 271.

In particular, in the projection along the axis of rotation D, a straight line (see dash-dotted line in FIGS Figures 3 and 4 ), which through the center point 14m (see Figure 1 ) runs and intersects the axis of rotation D, run through the separating webs 345 and 245, in particular run through the center of the overlap region 346. Alternatively or additionally, the straight line can run through the separating webs 385 and 285, in particular through the middle of the separating webs 385 and 285.

The angular offset between the control edge 342 and the center point 14m about the axis of rotation D as the vertex is different from the angular offset between the control edge 371 and the center point 14m. In the example shown, the angular offset between the control edge 342 and the center point 14m is greater than the angular offset between the control edge 371 and the center point 14m. This results in a separating web 345 on the first end wall 30, the predominant part of which is displaced towards the first descending area. Alternatively, the angular offset between the control edge 342 and the center point 14m could be smaller than or equal to the angular offset between the control edge 371 and the center point 14m.

The angular offset between the control edge 242 and the center point 14m about the axis of rotation D as the vertex is different from the angular offset between the control edge 271 and the center point 14m. In the example shown, the angular offset between the control edge 242 and the center point 14m is smaller than the angular offset between the control edge 271 and the center point 14m. This results in a separating web 245 on the second end wall 20, the predominant part of which is displaced towards the second ascending area. Alternatively, the angular offset between the control edge 242 and the center point 14m could be greater than or equal to the angular offset between the control edge 271 and the center point 14m.

In the example shown in the figures, the angular distance between the center point of the separating web 385 formed between the control edges 331 and 382 (the bisector of the angle formed around the axis of rotation D between the control edges 331 and 382) and that formed between the control edges 342 and 371 Center of the separating web 345 (bisector of the angle formed around the axis of rotation D as the vertex between the control edges 342 and 371) around the axis of rotation D as the vertex not equal to 180 °, in particular less than 180 °, measured over the area in which the lower wing recesses 33 and 34 lie. Alternatively, the angular offset could be greater, measured over the area in which the lower wing recesses 33 and 34 are located. Alternatively, the angular offset could be 180 °.

In the in the Figures 3 and 4 In the example shown, the control edges 331 to 231 and / or 382 to 282 are not angularly offset from one another. For example, in that the control edges 381 and 281 are not angularly offset from one another around the axis of rotation D as the vertex, the fluid communication of a lower vane chamber 3 can be separated from the lower vane recesses 28 and 38 at the same time by rotating the rotor 1 around the axis of rotation D. For example, because the control edges 331 and 231 are not angularly offset from one another around the axis of rotation D as the vertex, a lower vane chamber 3 can be connected to the lower vane recesses 23 and 33 in fluid communication by rotating the rotor 1 around the axis of rotation D at the same time.

However, alternative designs are possible in which the control edges 331 and 231 are offset from one another and / or the control edges 382 and 282 are angularly offset from one another. By rotating the rotor 1 about the axis of rotation D, one of the lower wing chambers 3 is first separated from one of the lower wing recesses 28, 38 (while it is still connected to the other of the lower wing recesses 28, 38) The lower wing chamber 3 is separated from the other of the lower wing recesses 28, 38. Alternatively or additionally, by rotating the rotor about the axis of rotation D, first one of the lower wing chambers 3 is connected to one of the lower wing recesses 23, 33 in a fluid-communicating manner (while it is not yet connected to the other of the lower wing recesses 23, 33) and by further turning the rotor 1 around the Axis of rotation D, the lower wing chamber 3 is connected to the other of the lower wing recesses 23, 33 in a fluid-communicating manner.

In the example shown in the figures, the center point 18m of the constant range 18, ie the point - based on the direction of rotation of the rotor 1 - is in the center (bisector of the Axis of rotation D as the vertex between the beginning and the end of the constant range 18) between the beginning and the end of the constant range 18, about the axis of rotation D as a vertex offset at an angle to the control edges 331, 231, 382, 282.

In particular, in the projection along the axis of rotation D, a straight line (see dash-dotted line in FIGS Figures 3 and 4 ), which through the midpoint 18m (see Figure 1 ) runs and intersects the axis of rotation D, run through the separating webs 285 and 385, in particular run through the center of the separating webs 285 and 385. In the example shown, the straight line corresponds to the straight line described above, which runs through the center point 14m and intersects the axis of rotation D.

The angular offset between the control edge 382 and the center point 18m about the axis of rotation D as the vertex is, in the example shown, equal to the angular offset between the control edge 331 and the center point 18m. Alternatively, the angular offset between the control edge 382 and the center point 18m about the axis of rotation D as a vertex could be smaller or larger than the angular offset between the control edge 331 and the center point 18m.

The angular offset between the control edge 282 and the center point 18m about the axis of rotation D as the vertex is, in the example shown, equal to the angular offset between the control edge 231 and the center point 18m. Alternatively, the angular offset between the control edge 282 and the center point 18m about the axis of rotation D as a vertex could be smaller or greater than the angular offset between the control edge 231 and the center point 18m.

In the example shown, the angular offset between the control edges 341 and 342 is smaller than the angular offset between the control edges 371 and 372 and / or the angular offset between the control edges 331 and 332.Alternatively or additionally, the angular offset between the control edges 241 and 242 is greater than, less than or equal to the angular offset between the control edges 271 and 272 and / or the angular offset between the control edges 231 and 232.

The width of the separating web 345 between the control edges 342 and 371 and / or the width of the separating web 385 between the control edges 382 and 331 is greater than the width of the first opening with which the lower wing chamber 3 opens towards the first end wall 30. This has the effect that the separating web 345 or the separating web 385 can completely close the relevant opening of the lower wing chamber 3 in a rotational position of the rotor 1.

The width of the separating web 245 between the control edges 242 and 271 and / or the width of the separating web 285 between the control edges 282 and 231 is greater than the width of the opening with which the lower wing chamber 3 opens towards the second end wall 20. This has the effect that the separating web 245 or the separating web 285 can completely close the relevant opening of the lower wing chamber in a rotational position of the rotor 1.

The angular distance between the control edges 242 and 371 or the distance 346, in particular the overlap area of the separating webs 245 and 345, ( Figure 3 ) between the control edges 242 and 371 in the projection along the axis of rotation D is larger than, alternatively smaller than or equal to the width of the openings with which a lower wing chamber 3 opens to the first end wall 30 and the second end wall 20. The rotor 1 can assume or have a rotational position in which the separating web 345 closes the opening of a lower wing chamber 3 opening towards the first end wall 30 and the separating web 245 closes the opening of a lower wing chamber 3 opening towards the second end wall 20, for example when the distance 346 is greater than or equal to the width of the openings of the relevant lower wing chamber 3.

Alternatively, the rotor 1 could assume or have a rotational position in which the opening of a lower wing chamber 3 opening towards the first end wall 30 is fluidly connected to the lower wing recess 37 and the opening of this lower wing chamber 3 opening towards the second end wall 20 is fluidly connected to the lower wing recess 24 is connected, for example if the distance 346 is smaller than the width of the openings of the relevant lower wing chamber 3. In alternative embodiments in which the angular offset between the control edges 342 and 242 is reversed to the illustration Figure 3 is, the rotor 1 can assume or have a rotational position in which the opening of a lower wing chamber 3 opening towards the first end wall 30 is fluidly connected to the lower wing recess 34 and the opening of this lower wing chamber 3 opening to the second end wall 20 is fluidly communicating with the lower wing recess 27 is connected.

Generally preferred is the center of the distance 346 resulting in the projection along the axis of rotation D ( Figure 3 ) between the control edges 242 and 371 (bisector of the angle around the axis of rotation D as the vertex between the control edges 242 and 371) around the axis of rotation D as the vertex with respect to the center of the constant range 14 ( Figure 1 ; The bisector of the angle about the axis of rotation D as the apex between the beginning and the end of the constant range 14) is not or only slightly offset at an angle and / or in relation to the midpoint of the separating web 385 (bisector of the angle about the axis of rotation D as the vertex between the control edges 382 and 331) and / or of the separating web 285 (bisector of the angle about the axis of rotation D as the vertex between the control edges 282 and 231) by 180 ° or offset at an angle of about 180 °.

The rotor 1 can be rotated into a rotary position or assume or have a rotary position in which the opening of a lower wing chamber 3 opening towards the first end wall 30 from the separating web 385 and the opening of this lower wing chamber 3 opening towards the second end wall 20 from the Separating web 285 is at least partially or completely closed.

In the example shown in the figures, the angular distance between the control edges 341 and 342 of the first descending lower wing recess 34 of the first end wall 30 around the axis of rotation D as the apex is smaller than the angular distance between the control edges 381 and 382 of the second descending lower wing recess 38 of the first end wall 30 Alternatively or additionally, the angular distance between the control edges 241 and 242 of the first descending lower wing recess 24 of the second end wall 20 around the axis of rotation D as the apex is greater than the angular distance between the control edges 281 and 282 of the second descending lower wing recess 28 of the second end wall 20.

Furthermore, in the example shown in the figures, the angular distance between the control edges 371 and 372 of the second ascending lower wing recess 37 of the first end wall 30 around the axis of rotation D as the apex is greater than the angular distance between the control edges 331 and 332 of the first ascending lower wing recess 33 of the first end wall 30. Alternatively or additionally, the angular distance between the control edges 271 and 272 of the second ascending lower wing recess 27 of the second end wall 20 around the axis of rotation D as the apex is smaller than the angular distance between the control edges 231 and 232 of the first ascending lower wing recess 23 of the first end wall 30.

In the example shown in the figures, the center point of the separating web 335 between the control edges 332 and 341 (bisector of the angle around the axis of rotation D as the apex between the control edges 332 and 341) is angularly offset around the axis of rotation D by 180 ° to the center point of the separating web 375 between the control edges 372 and 381 (bisector of the angle about the axis of rotation D as the vertex between the control edges 372 and 381).

Alternatively or additionally, the angular distance between the center point of the separating web 335 (bisector of the angle about the axis of rotation D as the apex between the control edges 332 and 341) and the center point of the separating web 345 (bisector of the angle about the axis of rotation D as the vertex between the control edges 342 and 342 371) around the axis of rotation D as the vertex smaller than the angular distance between the center point of the separating web 375 (bisector of the angle around the axis of rotation D as the vertex between the control edges 372 and 381) and the center point of the separating web 385 (bisector of the angle around the axis of rotation D as Vertex between the control edges 382 and 331) around the axis of rotation D as the vertex.

Alternatively or additionally, the angular distance between the center point of the projection 235 (bisector of the angle around the axis of rotation D as the vertex between the control edges 232 and 241) and the center point of the separating web 245 (bisector of the angle around the axis of rotation D as the vertex between the control edges 242 and 271) around the axis of rotation D as the vertex greater than the angular distance between the center of the projection 275 (bisector of the angle around the axis of rotation D as the vertex between the control edges 272 and 281) and the center of the separating web 285 (bisector of the angle around the axis of rotation D as Vertex between the control edges 282 and 231) around the axis of rotation D as the vertex.

List of reference symbols

1

rotor

2

wing

3

Lower wing chamber

4th

Delivery cell

5

wave

6th

bolt

7th

first seal

8th

second seal

9a

first pumping chamber

9b

second delivery chamber

10

Contour ring / lifting ring

101

Inner contour

102

Channel / connection channel

103

Channel / connection channel

11

first ascending area

12th

Constant range (upper reversal range)

121

Dead center

13th

first descending area

14th

Constant range (lower reversal range)

141

Dead center

14m

Focus

15th

second ascending area

16

Constant range (upper reversal range)

161

Dead center

17th

second descending area

18th

Constant range (lower reversal range)

181

Dead center

18m

Focus

20th

second housing part / second end wall

21

first entrance

22nd

first exit

221

Recess / groove-shaped channel

23

first ascending lower wing recess / groove

231

Control edge / beginning of the lower wing recess 23

232

Control edge / end of lower wing recess 23

235

head Start

24

first descending lower wing recess / groove

241

Control edge / beginning of the lower wing recess 24

242

Control edge / end of lower wing recess 24

245

Divider

25th

second entrance

26th

second exit

27

second ascending lower wing recess / groove

271

Control edge / beginning of the lower wing recess 27

272

Control edge / end of lower wing recess 27

275

head Start

279

channel

28

second descending lower wing recess / groove

281

Control edge / start of lower wing recess 28

282

Control edge / end of lower wing recess 28

285

Divider

30th

first housing part / first end wall

31

first entrance

32

first exit

33

first ascending lower wing recess / groove

331

Control edge / beginning of the lower wing recess 33

332

Control edge / end of lower wing recess 33

333

crossing

334

channel

335

Divider

34

first descending lower wing recess / groove

341

Control edge / beginning of the lower wing recess 34

342

Control edge / end of lower wing recess 34

345

Divider

346

Overlapping of the separators 345 and 245

35

second entrance

36

second exit

37

second ascending lower wing recess / groove

371

Control edge / start of lower wing recess 37

372

Control edge / end of lower wing recess 37

373

crossing

374

channel

375

Divider

38

second descending lower wing recess / groove

381

Control edge / beginning of lower wing recess 38

382

Control edge / end of lower wing recess 38

385

Divider

39

channel

D.

Rotation axis of the rotor

Claims (18)

Vane pump, comprising: a rotor (1) rotatable about an axis of rotation (D) and several vanes (2) guided displaceably by the rotor (1), the rotor (1) having a lower vane chamber (3) for each vane (2) and each vane (2) forms a movable wall of its associated lower wing chamber (3), a first end wall (30) adjoining the end face of the rotor (1) on a first side of the rotor (1), which has a circumferentially extending lower wing recess (34; 37) for pressure control of the lower wing chamber (3) which, viewed in the circumferential direction, has a Comprises control edge (341; 342; 371; 372), a second end wall (20) which adjoins the end face of the rotor (1) on a second side of the rotor (1) and which has a lower wing recess (24; 27) extending in the circumferential direction for pressure control of the lower wing chamber (3), which has the lower wing recess (34 ; 37) opposite the first end wall (30) and, viewed in the circumferential direction, comprises a control edge (241; 242; 271; 272) which leads to the control edge (341; 342; 371; 372) of the lower wing recess (34; 37) of the first end wall (30) is similar, characterized in that the control edge (341; 342; 371; 372) of the lower wing recess (34; 37) of the first end wall (30) and the similar control edge (241; 242; 271; 272) of the lower wing recess (24; 27) of the second end wall (20 ) designed differently from one another and / or offset, in particular angularly offset about the axis of rotation (D) as a vertex, are arranged to one another. Vane pump according to claim 1, wherein the control edge (342; 372; 341; 371) of the lower wing recess (34; 37) of the first end wall (30) and the similar control edge (242; 272; 241; 271) of the lower wing recess (24; 27) ) the second end wall (20) each form an end or a beginning of the respective lower wing recess (34; 37; 24; 27) in relation to the direction of rotation of the rotor (1). Vane pump according to claim 1 or 2, wherein the rotor (1) - Has or can assume a rotational position in which the lower wing recess (34; 37) of the first end wall (30) in fluid communication with one of the Is connected lower wing chambers (3) and the opposite lower wing recess (24; 27) of the second end wall (20) is also connected to this lower wing chamber (3) in a fluid-communicating manner, and - Has or can assume a rotary position in which the lower wing recess (34) of the first end wall (30) is fluidly separated from one of the lower wing chambers (3) and the opposite lower wing recess (24) of the second end wall (20) is in fluid communication with this lower wing chamber (3) connected, and / or - Has or can assume a rotational position in which the lower wing recess (27) of the second end wall (20) is fluidically separated from one of the lower wing chambers (3) and the opposite lower wing recess (37) of the first end wall (30) is in fluid communication with this lower wing chamber (3) connected is. Vane pump according to one of the preceding claims, characterized by a contour ring (10) with an inner contour (101) which extends around the axis of rotation (D) of the rotor (1) and along which the vanes (2) slide when the rotor (1) rotates is, wherein the inner contour (101) of the contour ring (10) is adapted to define at least one ascending area (11; 15) and at least one descending area (13; 17), a wing (2) from the rotor (1) is moved out while it slides over the ascending area (11; 15), and is moved into the rotor (1) while it slides over the descending area (13; 17), the inner contour (101) in an area (14 ; 18) between the descending area (13; 17) and the ascending area (15; 11) is designed to define a, in particular lower, dead point (141; 181) for the wings (2), at which the direction of movement of a Vane (2) with respect to the rotor (1) is reversed when this Fl bow (2) from the descending area (13; 17) slides over the dead center (141; 181) into the ascending area (15; 11), the angular distance around the axis of rotation (D) of the rotor (1) between the dead center (141) and the control edge (342; 371) of the Lower wing recess (34; 37) of the first end wall (30) and the angular distance around the axis of rotation (D) of the rotor (1) between the dead center (141) and the similar control edge (242; 271) of the lower wing recess (24; 27) of the second Front wall (20) are of different sizes. Vane pump according to the preceding claim, characterized in that the inner contour (101) of the contour ring (10) is adapted, at least one first ascending area (11), at least one first descending area (13), at least one second ascending area (15) and at least one second descending area (17) define, the area (14; 18) being arranged between the first descending area (13) and the second ascending area (15) and / or between the second descending area (17) and the first ascending area (11). Vane pump according to one of the preceding claims, characterized in that the first end wall (30) has a separating web (345) which, in a rotational position of the rotor (1), separates a lower wing chamber (3) from the lower wing recess (34; 37) of the first end wall ( 30) fluidically separates, while this lower wing chamber (3) is located in the area of the separating web (345) of the first end wall (30), in particular an opening of the lower wing chamber (3) facing the first end wall (30) from the separating web (345) is closed or covered, and the second end wall (20) has a similar or opposite separating web (245) which, in one, in particular a different, rotational position of the rotor (1), separates a lower wing chamber (3) from the lower wing recess (24; 27) of the fluidically separates the second end wall (20), while this lower wing chamber (3) is located in the region of the separating web (245) of the second end wall (20), in particular one facing the second end wall (20) pointing opening of the lower wing chamber (3) is closed or covered by the separating web (245), wherein the separating web (345) of the first end wall (30) and the similar or opposite separating web (245) of the second end wall (20) are designed differently from one another and / or are arranged offset from one another, in particular offset at an angle about the axis of rotation (D). Vane pump according to claim 6, wherein the separating web (345) of the first end wall (30) and the similar or opposite separating web (245) of the second end wall (20) are projected along the axis of rotation (D), in particular in an overlapping area (346) partially, in particular only partially and not completely, overlap. Vane pump according to claim 7, wherein the circumferential width of the overlap region (346) is smaller than the circumferential width of the opening facing the first end face and / or the opening of the lower vane chamber (3) facing the second end face. Vane pump according to one of claims 6 to 8, wherein the region (14) in the angular region of the separating web (345) of the first end wall (30) and / or in the angular region of the separating web (245) of the second end wall (20), in particular in the angular region of the Overlap area (346), is arranged. Vane pump at least according to one of the preceding claims, characterized in that the vane pump is adapted so that during the rotation of the rotor (1) a lower vane chamber (3) with a lower vane recess (24) of one end wall (20) arranged in the descending area (13) ) is connected in a fluid-communicating manner until this lower wing chamber (3) is or will be connected in a fluid-communicating manner to the lower wing recess (37) of the other end wall (30) arranged in the ascending area (15). Vane pump, comprising: - A rotor (1) rotatable about an axis of rotation (D) and several vanes (2) guided displaceably by the rotor (1), the rotor (1) having a lower vane chamber (3) for each vane (2) and each vane (2 ) forms a movable wall of its associated lower wing chamber (3), - A contour ring (10) with an inner contour (101) extending around the axis of rotation (D), along which the blades slide when the rotor (1) is rotated, the inner contour (101) of the contour ring (10) being adapted, define at least one ascending area (15) and at least one descending area (13), a vane (2) being moved out of the rotor (1) while sliding over the ascending area (15) and into the rotor (1 ) is moved in while sliding over the descending area (13), - A first end wall (30) adjoining the end face of the rotor (1) on a first side of the rotor (1), - a second end wall (20) adjoining the end face of the rotor (1) on a second side of the rotor (1), - wherein the first end wall (30) and the second end wall (20) respectively ∘ at least one rising lower wing recess (27; 37) with which a lower wing chamber (3) is connected in a fluid-communicating manner when its wing (2) is in the rising area (15) of the contour ring (10), ∘ at least one descending lower wing recess (24; 34) with which a lower wing chamber (3) is connected in fluid communication when its wing (2) is located in the descending area (13) of the contour ring (10), and ∘ a separating web (245; 345) formed between the descending lower wing recess (24; 34) and the rising lower wing recess (27; 37), exhibit, characterized in that
the separating web (345) formed between the descending lower wing recess (34) and the rising lower wing recess (37) of the first end wall (30) around the axis of rotation (D) to the separating web (345) of the first end wall (30) along or parallel to the Axis of rotation (D) opposite, between the descending lower wing recess (24) and the rising lower wing recess (27) of the second end wall (20) formed separating web (245) is arranged angularly offset. Vane pump according to the preceding claim, wherein the opposing, angularly offset separating webs (245; 345) partially overlap in a projection along or parallel to the axis of rotation (D). Vane pump, comprising: a contour ring (10) with an inner contour (101) extending around the axis of rotation (D) of the rotor (1), along which the blades (2) slide when the rotor (1) is rotated, the inner contour (101) of the Contour rings (10) is adapted to define at least one ascending area (11; 15) and at least one descending area (13; 17), a wing (2) being moved out of the rotor (1) as it moves over the ascending area (11; 15) slides and is moved into the rotor (1) while it slides over the descending area (13; 17), an end wall (20; 30) adjoining the end face of the rotor (1), which for pressure control or pressure fluid supply of the lower wing chamber (3) has a circumferentially extending first lower wing recess (24; 34) with a control edge (242; 342), which in the direction of rotation of the rotor (1) forms one end of the first lower wing recess (24; 34), and a second lower wing recess (27; 37) extending in the circumferential direction with a control edge (271; 371) which, in the direction of rotation of the rotor, forms the beginning of the second lower wing recess ( 27; 37) forms, has, wherein the inner contour (101) between the descending area (13) and the ascending area (15) has an area (14) which defines a bottom dead center (141) for the wing (2) passing through this area (14), the Direction of movement of a wing (2), which is moved from the descending area (13) via the area (14) into the ascending area (15), is reversed with respect to the rotor (1), the angular distance around the axis of rotation (D ) of the rotor (1) as the apex between the area (14), in particular its center point or its dead center (141), and the Control edge (242; 342) of the first lower wing recess (24; 34) and the angular distance between the area (14), in particular its center point or its dead center (141), and the control edge (271; 371) of the second lower wing recess (27; 37) differ from one another. Vane pump according to claim 13, wherein the first lower wing recess (24; 34) is designed as a descending lower wing recess which runs at least substantially in the descending area (13), and the second lower wing recess (27; 37) is designed as an ascending lower wing recess, which runs at least substantially in the ascending area (15). Vane pump, wherein the vane pump is multi-flow, in particular double-flow, or multi-stroke, in particular double-stroke, and also has: - A contour ring (10) with an inner contour (101) extending around the axis of rotation (D), along which blades (2) slide when the rotor (1) is rotated, the inner contour (101) of the contour ring (10) being adapted is, a first ascending area (11) and a first descending area (13) which are assigned to the first tide, and at least a second ascending area (15) and a second descending area (17) which are assigned to the second tide, to define, wherein a vane (2) is moved out of the rotor (1) while sliding over the ascending region (11; 15) and is moved into the rotor (1) while sliding over the descending region (13; 17) slides, - A first end wall (30) adjoining the end face of the rotor (1) on a first side of the rotor (1), and - a second end wall (20) adjoining the end face of the rotor (1) on a second side of the rotor (1), - One of the first end wall (30) and the second end wall (20), or the first end wall (30) and the second end wall (20), respectively, ∘ a first ascending lower wing recess (23; 33) with which a lower wing chamber (3) is connected in fluid communication when its wing (2) is located in the first rising area (11) of the contour ring (10), ∘ a first descending lower wing recess (24; 34) with which a lower wing chamber (3) is connected in a fluid-communicating manner when its wing (2) is located in the first descending area (13) of the contour ring (10), ∘ a second ascending lower wing recess (27; 37) with which a lower wing chamber (3) is connected in a fluid-communicating manner when its wing (2) is located in the second rising area (15) of the contour ring (10), ∘ a second descending lower wing recess (28; 38) with which a lower wing chamber (3) is connected in a fluid-communicating manner when its wing (2) is located in the second descending area (17) of the contour ring (10), ∘ a separating web (345; 245) formed between the first descending lower wing recess (24; 34) and the second rising lower wing recess (27; 37) and ∘ a separating web (385; 285) formed between the second descending lower wing recess (28; 38) and the first rising lower wing recess (23; 33) exhibit,
characterized in that
the separating webs (345; 385; 245; 285) are offset from one another around the axis of rotation (D) as the apex by an angle other than 180 °. Vane pump according to the preceding claim, characterized in that the center point of the separating web (245; 345) formed between the first descending lower vane recess (24; 34) and the second ascending lower vane recess (27; 37) offset by an angle not equal to 180 ° to the center point of the separating web (285; 385) formed between the second descending lower wing recess (28; 38) and the first rising lower wing recess (23; 33). Vane pump according to one of the two preceding claims, characterized in that the separating web (245; 345) formed between the first descending lower vane recess (24; 34) and the second ascending lower vane recess (27; 37) is formed in the circumferential direction by a control edge (242; 342) the first descending lower wing recess (24; 34) and is delimited by a control edge (271; 371) of the second rising lower wing recess (27; 37) and that between the second descending lower wing recess (28; 38) and the first rising lower wing recess (23; 33 ) formed separating web (285; 385) is limited in the circumferential direction by a control edge (282; 382) of the second descending lower wing recess (28; 38) and by a control edge (231; 331) of the first rising lower wing recess (23; 33),
wherein the bisector of the angular distance about the axis of rotation (D) between the control edge (242; 342) of the first descending lower wing recess (24; 34) and the control edge (271; 371) of the second rising lower wing recess (27; 37) about the axis of rotation (D ) as the vertex offset by an angle not equal to 180 ° to the bisector of the angular distance around the axis of rotation (D) between the control edge (282; 382) of the second descending lower wing recess (28; 38) and the control edge (231; 331) of the first rising lower wing recess (23; 33) is. Vane pump according to one of the three preceding claims, characterized in that the separating web (345) of the first end wall (30) formed between the first descending lower wing recess (34) and the second rising lower wing recess (37) in the circumferential direction from a control edge (342) of the first descending lower wing recess (34) and is limited by a control edge (371) of the second rising lower wing recess (37),
wherein the separating web (285) of the second end wall (20) formed between the first descending lower wing recess (24) and the second rising lower wing recess (27) in the circumferential direction from a control edge (242) of the first descending lower wing recess (24) and from a control edge (371 ) the second rising lower wing recess (27) is limited,
wherein the bisector of the angular distance around the axis of rotation (D) between the control edge (342) of the first descending lower wing recess (34) of the first end wall (30) and the control edge (371) of the second ascending lower wing recess (37) of the first end wall (30) the axis of rotation (D) as the vertex offset at an angle to the bisector of the angular distance around the axis of rotation (D) between the control edge (242) of the first descending lower wing recess (24) of the second end wall (20) and the control edge (271) of the second rising lower wing recess (27 ) the second end wall (20).

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