EP3020917A1 - Hydraulic vane cell machine - Google Patents

Hydraulic vane cell machine Download PDF

Info

Publication number
EP3020917A1
EP3020917A1 EP14193256.6A EP14193256A EP3020917A1 EP 3020917 A1 EP3020917 A1 EP 3020917A1 EP 14193256 A EP14193256 A EP 14193256A EP 3020917 A1 EP3020917 A1 EP 3020917A1
Authority
EP
European Patent Office
Prior art keywords
rotor
machine according
stator
vane machine
wings
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP14193256.6A
Other languages
German (de)
French (fr)
Other versions
EP3020917B1 (en
Inventor
Erik Haugaard
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Danfoss AS
Original Assignee
Danfoss AS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Danfoss AS filed Critical Danfoss AS
Priority to ES14193256T priority Critical patent/ES2813957T3/en
Priority to EP14193256.6A priority patent/EP3020917B1/en
Priority to CN201510683523.5A priority patent/CN105604781B/en
Priority to US14/930,720 priority patent/US9945231B2/en
Publication of EP3020917A1 publication Critical patent/EP3020917A1/en
Application granted granted Critical
Publication of EP3020917B1 publication Critical patent/EP3020917B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C21/00—Component parts, details or accessories not provided for in groups F01C1/00 - F01C20/00
    • F01C21/08—Rotary pistons
    • F01C21/0809—Construction of vanes or vane holders
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00—Rotary-piston machines or engines
    • F01C1/30—Rotary-piston machines or engines having the characteristics covered by two or more groups F01C1/02, F01C1/08, F01C1/22, F01C1/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members
    • F01C1/34—Rotary-piston machines or engines having the characteristics covered by two or more groups F01C1/02, F01C1/08, F01C1/22, F01C1/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F01C1/08 or F01C1/22 and relative reciprocation between the co-operating members
    • F01C1/344—Rotary-piston machines or engines having the characteristics covered by two or more groups F01C1/02, F01C1/08, F01C1/22, F01C1/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F01C1/08 or F01C1/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member
    • F01C1/3448—Rotary-piston machines or engines having the characteristics covered by two or more groups F01C1/02, F01C1/08, F01C1/22, F01C1/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F01C1/08 or F01C1/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member with axially movable vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C21/00—Component parts, details or accessories not provided for in groups F01C1/00 - F01C20/00
    • F01C21/08—Rotary pistons
    • F01C21/0809—Construction of vanes or vane holders
    • F01C21/0818—Vane tracking; control therefor
    • F01C21/0827—Vane tracking; control therefor by mechanical means
    • F01C21/0836—Vane tracking; control therefor by mechanical means comprising guiding means, e.g. cams, rollers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C21/00—Component parts, details or accessories not provided for in groups F01C1/00 - F01C20/00
    • F01C21/10—Outer members for co-operation with rotary pistons; Casings
    • F01C21/104—Stators; Members defining the outer boundaries of the working chamber
    • F01C21/106—Stators; Members defining the outer boundaries of the working chamber with a radial surface, e.g. cam rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C18/00—Rotary-piston pumps specially adapted for elastic fluids
    • F04C18/30—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members
    • F04C18/34—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F04C18/08 or F04C18/22 and relative reciprocation between the co-operating members
    • F04C18/344—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F04C18/08 or F04C18/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member
    • F04C18/3448—Rotary-piston pumps specially adapted for elastic fluids having the characteristics covered by two or more of groups F04C18/02, F04C18/08, F04C18/22, F04C18/24, F04C18/48, or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F04C18/08 or F04C18/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member with axially movable vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2/00—Rotary-piston machines or pumps
    • F04C2/30—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members
    • F04C2/34—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members
    • F04C2/344—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member
    • F04C2/3446—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member the inner and outer member being in contact along more than one line or surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C2/00—Rotary-piston machines or pumps
    • F04C2/30—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members
    • F04C2/34—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members
    • F04C2/344—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member
    • F04C2/3448—Rotary-piston machines or pumps having the characteristics covered by two or more groups F04C2/02, F04C2/08, F04C2/22, F04C2/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in groups F04C2/08 or F04C2/22 and relative reciprocation between the co-operating members with vanes reciprocating with respect to the inner member with axially movable vanes

Definitions

  • the invention relates to a hydraulic vane machine with a stator and a rotor having a plurality of vanes, which are each radially displaceable in a guide in the rotor, abut against an inner circumference of the stator and with the rotor, the stator and one side wall at each axial end of the rotor limit working chambers whose volumes change with rotation of the rotor relative to the stator.
  • Such a vane machine is off US Pat. No. 6,684,847 B1 known.
  • the wings are provided at both axial ends with projections which are respectively guided in grooves provided in the stator. The course of the grooves determines the movement of the wings.
  • Such a vane machine can be used for example as a boost pump in a reverse osmosis system and then acts as a water hydraulic machine.
  • the rotor is mounted eccentrically to the inner circumference of the stator. One point on the surface of the rotor then once approaches the inner circumference in one revolution until a minimum distance is reached, and then moves away from the inner circumference until a maximum distance is reached. If the vane machine is used as a pump, then an outlet opening for the respective working chamber is provided in the region of the minimum distance, from which then water can be discharged at a higher pressure. If the vane machine is used as a motor, then there is a feed or supply port in this area, can be fed to the pressurized water.
  • the invention has for its object to have a certain freedom in the design of the inner circumference. This object is achieved in a hydraulic vane machine of the type mentioned above in that each wing has on its radially inner side a contact surface which rests radially outward on a cam.
  • the abutment surface is formed on at least one axial end of the wings.
  • the cam can arrange the cam on an axial end face of the rotor, so that the structure of the rotor is not disturbed or impaired by the use of the cam.
  • the abutment surface is formed in a recess at the axial end of the wing. In this recess engages the cam. This makes it possible that the cam covers the wings slightly in the radial direction.
  • the wings project axially beyond the rotor.
  • the recess has a radial extent that is greater than a maximum stroke of the wing.
  • the cam thus covers the wings in the region of the recess over the entire stroke.
  • the cam thus serves with the axial sealing of the wings, so that leakage can be avoided or at least kept small.
  • the recess has an axial extent corresponding to an axial thickness of the cam.
  • the wings abut outside the recess with its axial end on the side wall and within the recess with its axial end on the cam. This results over the entire height of the wings in each angular position of the rotor relative to the stationary parts a sealing surface which extends over the entire radial length of the axial ends of the wings. This ensures a relatively good tightness.
  • the cam corresponds to the inner circumference of the stator reduced by twice the radial extent the wing plus twice the radial extent of the recess. This is a relatively simple design rule. You can form the cam so to speak as a reduced copy of the inner circumference of the stator.
  • the contact surface is rounded. This keeps friction between the wing and the cam small. It is practically unavoidable that the wing tilts in the guide. Although this tilting can be kept very small, problems could arise as a result of this tilting. Such problems are reliably prevented by the rounding of the contact surface.
  • the rotor is mounted centrically relative to the stator and a profile of a radial distance between the stator and the rotor has in the circumferential direction at least two maxima and two minima.
  • the rotor has a passage opening, which widens axially inward to a cavity, for receiving an axle.
  • the cavity serves to reduce the mass of the rotor.
  • the wings enter with their radial inner side in an inward stroke into the cavity. Then, while the cavity is filled with water when the machine is operated. But this is not critical, because the pressure of the water in the cavity can adjust to an average value.
  • the wings on a core of a steel and a coating of a steel friction-co-operating plastic.
  • the rotor and the stator can be made of steel. Since water has no lubricating properties, the friction reduction caused by a hydraulic oil in an oil-hydraulic machine is in this case effected by the friction-reducing plastic.
  • materials from the group of high-strength thermoplastics based on polyaryl ether ketones in particular polyether ether ketones, polyamides, polyacetals, polyaryl ethers, polyethylene terephthalates, polyphenylene sulfides, polysulfones, polyethersulfones, polyetherimides, polyamideimides, polyacrylates, phenol resins, such as novolak, are used as the plastic for the coating Resins, or the like, wherein as fillers glass, graphite, polytetrafluoroethylene or plastic, in particular in fiber form, can be used. When using such materials, water can also be used as hydraulic fluid.
  • each vane in the region of the guide has a surface formed from the plastic with a low-friction cooperating plastic surface and the abutment surface is at least partially formed of a steel, wherein the cam at least in an area in which abuts the contact surface, a from a Having formed with plastic friction co-operating plastic surface.
  • the cam at least in an area in which abuts the contact surface, a from a Having formed with plastic friction co-operating plastic surface.
  • the cam is formed integrally with the side plate. It may for example be formed by a projection on the side plate.
  • At least one side wall has at least one opening which is bounded radially on the outside by a web on which the wings abut. Also in the region of the opening is thus achieved that the wings are supported in the axial direction radially inward and radially outward. A tilting of the wings in a direction parallel to the axis of rotation can thus be reliably avoided.
  • a vane machine 1 has a stator 2 and a rotor 3, which are rotatably mounted to each other by means not shown.
  • the rotor 3 has a plurality of wings 4, which are each radially displaceable in a guide 5 in the rotor 3.
  • the wings 4 abut against an inner periphery 6 of the stator.
  • a side wall 7 is arranged.
  • openings 8, 9 may be provided, which can be used for the supply or for the discharge of water.
  • Fig. 1 only one side wall 7 is shown.
  • On the axially opposite end side of the stator 2 also has a side wall, which, however, is not shown. In this other side wall you can omit the openings 8, 9 under certain circumstances.
  • the openings 8, 9 extend radially outward not quite to the stator 2. Rather, radially outward webs 10, 11 are provided, on which the wings 4 can rest in the axial direction when the rotor rotates. Also in the region of the openings 9, 10 so the wings are supported radially inward and radially outward in the axial direction.
  • a through hole 12 is provided, through which, for example, a shaft can be guided, with which the rotor 3 is rotatably mounted relative to the stator 2.
  • the passage opening 12 widens to a cavity 13.
  • the wings 4 enter with their radial inner sides 14 in the cavity 13 when they are pressed by the inner periphery 6 of the stator 2 radially inward.
  • a cam 15 is arranged in each case.
  • the cam 15 may be fixed to the side wall 7 or formed integrally with the side wall 7. It has a shape that corresponds to the inner circumference 6 of the stator, but in a reduced version, as will be explained in more detail below.
  • the wings 4 each have a recess 16 at its two axial ends. In this recess 16, the cam 15 engages. Each recess 16 has an axial extent corresponding to the axial thickness of the cam 15. The wings 4 are about this axial extent axially over the rotor 3, so that it is possible to make the wings 4 and the cam 15 in the axial direction flush with each other.
  • the recesses 16 may have an extent in the radial direction, which is greater than a maximum stroke of the wing.
  • the cam 15 then covers the wings 4 over their entire radial stroke in the region of the recess 16.
  • the inner circumference 6 of the stator is about twice the radial Extension of the wings 4 reduced. Added twice the radial extent of the recesses 16. With such a shaped cam 15 ensures that the wings 4 always rest on the inner circumference 6 of the stator 2 and there ensure adequate sealing.
  • the wings 4 abut with their front side either on the side wall 7 or on the cam 4, so that even there is given a sufficient seal.
  • a seal radially inward results from the interaction of the wings 4 with the guides 5.
  • the vane machine 1 shown there has two cycles per revolution.
  • the result is a minimum distance between the inner periphery 6 of the stator 2 and the rotor 3 at points of the rotor 3, which point upwards and downwards, and a maximum distance at points which point to the left and to the right. Since a "delivery stroke" can always be realized when the maximum distance to the minimum distance decreases, the result in Fig. 2 illustrated embodiments two cycles per revolution. This possibility is provided by the cam 15.
  • FIGS Fig. 1 and 2 show the vane machine 1 in perspective view. Same parts are denoted by the same reference numerals as in FIGS Fig. 1 and 2 Mistake.
  • the cam 15 is formed here as a separate element. However, it may also be formed integrally with the side wall 7.
  • cam 15 If one forms the cam 15 as a separate element, then you can dimension their two faces or pressure application surfaces on the two end faces, which can be defined for example by seals, not shown, so that there is a force balance on the rotor in the axial direction. This allows you to minimize a game and accordingly keep a small leak.
  • the wings 4 have a core of a steel and a coating of a plastic friction-co-operating with steel.
  • the wings 4 are designed so that they can interact with low friction with the stator 2 and the guides 5 in the rotor 3. Also at their end faces, which bear against the side wall 7 formed of steel, results in a reduced friction.
  • plastics it is possible to use, for example, materials from the group of high-strength thermoplastics based on polyaryl ether ketones, in particular polyether ether ketones, Polyamides, polyacetals, polyaryl ethers, polyethylene terephthalates, polyphenylene sulfides, polysulfones, polyethersulfones, polyetherimides, polyamideimides, polyacrylates, phenolic resins such as novolak resins or the like, which may be glass, graphite, polytetrafluoroethylene or plastic, especially in fibrous form, as fillers , When using such materials, water can also be used as hydraulic fluid.
  • polyaryl ether ketones polyether ether ketones
  • the cam 15 should be provided with a corresponding plastic, at least in the area where the rotor 3 rests with its front side.
  • the recesses 6 are expediently milled out of the wings 4 after the plastic has been applied , This results in the contact surface 17, an area which is at least partially formed of a steel and then rests against the plastic of the cam 15. Due to the rounded shape of the contact surface 17 can also be achieved that a contact between the plastic of the wing 4 and the plastic of the cam 15 can be practically avoided.
  • the wing 4 then also has an end face 18, which is formed by the recess 6, which also consists essentially of the steel of the core of the wing 4 exists. This surface 18 then abuts axially on the cam 15, so that a pairing plastic - plastic is avoided and a mating steel - plastic is achieved here.

Abstract

Es wird eine hydraulische Flügelzellenmaschine (1) angegeben mit einem Stator (2) und einem Rotor (3), die mehrere Flügel (4) aufweist, die jeweils in einer Führung im Rotor (3) radial verlagerbar sind, an einem Innenumfang (6) des Stators (2) anliegen und mit dem Rotor (3), dem Stator (2) und je einer Seitenwand (7) an jedem axialen Ende des Rotors (3) Arbeitskammern begrenzen, deren Volumina sich bei einer Drehung des Rotors (3) gegenüber dem Stator (2) ändern. Man möchte eine gewisse Freiheit bei der Gestaltung des Innenumfangs haben. Hierzu ist vorgesehen, dass jeder Flügel (4) an seiner radialen Innenseite eine Anlagefläche (17) aufweist, die radial außen an einer Kurvenscheibe (15) anliegt.The invention relates to a hydraulic vane machine (1) comprising a stator (2) and a rotor (3) which has a plurality of vanes (4) which are radially displaceable in each case in a guide in the rotor (3) on an inner circumference (6). abut the stator (2) and with the rotor (3), the stator (2) and one side wall (7) at each axial end of the rotor (3) limit working chambers whose volumes are opposite to each other upon rotation of the rotor (3) change the stator (2). One would like to have a certain freedom in the design of the inner circumference. For this purpose, it is provided that each vane (4) has on its radially inner side a contact surface (17) which rests radially outward on a cam disc (15).

Description

Die Erfindung betrifft eine hydraulische Flügelzellenmaschine mit einem Stator und einem Rotor, der mehrere Flügel aufweist, die jeweils in einer Führung im Rotor radial verlagerbar sind, an einem Innenumfang des Stators anliegen und mit dem Rotor, dem Stator und je einer Seitenwand an jedem axialen Ende des Rotors Arbeitskammern begrenzen, deren Volumina sich bei einer Drehung des Rotors gegenüber dem Stator ändern.The invention relates to a hydraulic vane machine with a stator and a rotor having a plurality of vanes, which are each radially displaceable in a guide in the rotor, abut against an inner circumference of the stator and with the rotor, the stator and one side wall at each axial end of the rotor limit working chambers whose volumes change with rotation of the rotor relative to the stator.

Eine derartige Flügelzellenmaschine ist aus US 6 684 847 B1 bekannt. Die Flügel sind an beiden axialen Enden mit Vorsprüngen versehen, die jeweils in Nuten geführt sind, die im Stator vorgesehen sind. Der Verlauf der Nuten bestimmt die Bewegung der Flügel.Such a vane machine is off US Pat. No. 6,684,847 B1 known. The wings are provided at both axial ends with projections which are respectively guided in grooves provided in the stator. The course of the grooves determines the movement of the wings.

Eine derartige Flügelzellenmaschine kann beispielsweise als Verstärkungspumpe in einer Umkehrosmose-Anlage verwendet werden und wirkt dann als wasserhydraulische Maschine. In einer bislang verwendeten Ausgestaltung ist der Rotor exzentrisch zum Innenumfang des Stators gelagert. Ein Punkt an der Oberfläche des Rotors nähert sich dann bei einer Umdrehung einmal dem Innenumfang an, bis ein minimaler Abstand erreicht ist, und bewegt sich dann vom Innenumfang wieder weg, bis ein maximaler Abstand erreicht ist. Wenn die Flügelzellenmaschine als Pumpe verwendet wird, dann ist im Bereich des minimalen Abstandes eine Auslassöffnung für die jeweilige Arbeitskammer vorgesehen, aus der dann Wasser unter einem höheren Druck ausgegeben werden kann. Wenn die Flügelzellenmaschine als Motor verwendet wird, dann befindet sich in diesem Bereich ein Speise- oder Zuführanschluss, an dem Wasser unter Druck eingespeist werden kann.Such a vane machine can be used for example as a boost pump in a reverse osmosis system and then acts as a water hydraulic machine. In a previously used embodiment, the rotor is mounted eccentrically to the inner circumference of the stator. One point on the surface of the rotor then once approaches the inner circumference in one revolution until a minimum distance is reached, and then moves away from the inner circumference until a maximum distance is reached. If the vane machine is used as a pump, then an outlet opening for the respective working chamber is provided in the region of the minimum distance, from which then water can be discharged at a higher pressure. If the vane machine is used as a motor, then there is a feed or supply port in this area, can be fed to the pressurized water.

Bei einer derartigen Flügelzellenmaschine hat man bisher immer eine geradzahlige Anzahl von Flügeln verwendet und zwischen Flügeln, die einander diametral gegenüber liegen, einen Abstandshalter eingebaut, so dass zwei diametral einander gegenüber liegende Flügel immer genau einen Durchmesser abgebildet haben. Allerdings ist eine derartige Lösung nur bei Maschinen möglich, bei denen der Innenumfang des Stators eine Zylinderform aufweist.In such a vane machine has always been used an even number of wings and between wings, which are diametrically opposed, a spacer installed so that two diametrically opposed wings have always shown exactly one diameter. However, such a solution is possible only in machines in which the inner circumference of the stator has a cylindrical shape.

Der Erfindung liegt die Aufgabe zugrunde, eine gewisse Freiheit bei der Gestaltung des Innenumfangs zu haben. Diese Aufgabe wird bei einer hydraulischen Flügelzellenmaschine der eingangs genannten Art dadurch gelöst, dass jeder Flügel an seiner radialen Innenseite eine Anlagefläche aufweist, die radial außen an einer Kurvenscheibe anliegt.The invention has for its object to have a certain freedom in the design of the inner circumference. This object is achieved in a hydraulic vane machine of the type mentioned above in that each wing has on its radially inner side a contact surface which rests radially outward on a cam.

Bei einer derartigen Ausgestaltung ist man nicht länger darauf angewiesen, dass der Innenumfang für jede Winkelstellung des Rotors den gleichen Durchmesser aufweist. Vielmehr kann man hier wechselnde Durchmesser verwenden. Die Bewegung eines Flügels muss nicht mehr mit der Bewegung eines diametral gegenüber liegenden Flügels korrelieren. Dementsprechend kann man auch eine ungerade Anzahl von Flügeln verwenden. Die Verwendung einer Kurvenscheibe, an deren Außenumfang die Anlageflächen der Flügel anliegen, erlaubt es, die Flügel mit einer relativ großen Freiheit zu führen. Die Flügel werden durch die Kurvenscheibe radial nach außen gedrückt. Die Bewegung radial nach innen kann durch den Innenumfang des Stators bewirkt werden. Eine derartige Maschine kann auch mit Wasser als Hydraulikflüssigkeit betrieben werden und bildet dann eine wasserhydraulische Flügelzellenmaschine.In such an embodiment, it is no longer dependent on the inner circumference having the same diameter for each angular position of the rotor. Rather, you can use changing diameters here. The movement of a wing no longer has to correlate with the movement of a diametrically opposed wing. Accordingly, one can also use an odd number of wings. The use of a cam on the outer periphery abut the abutment surfaces of the wings, allows to guide the wings with a relatively large freedom. The wings are pressed radially outwards by the cam disc. The movement radially inward can be effected by the inner circumference of the stator. Such a machine can also be operated with water as hydraulic fluid and then forms a water-hydraulic vane machine.

Vorzugsweise ist die Anlagefläche an mindestens einem axialen Ende der Flügel ausgebildet. Damit kann man die Kurvenscheibe an einer axialen Stirnseite des Rotors anordnen, so dass der Aufbau des Rotors durch die Verwendung der Kurvenscheibe nicht gestört oder beeinträchtigt wird.Preferably, the abutment surface is formed on at least one axial end of the wings. Thus, one can arrange the cam on an axial end face of the rotor, so that the structure of the rotor is not disturbed or impaired by the use of the cam.

Vorzugsweise ist die Anlagefläche in einer Ausnehmung am axialen Ende des Flügels ausgebildet. In diese Ausnehmung greift die Kurvenscheibe ein. Damit ist es möglich, dass die Kurvenscheibe die Flügel in radialer Richtung etwas überdeckt.Preferably, the abutment surface is formed in a recess at the axial end of the wing. In this recess engages the cam. This makes it possible that the cam covers the wings slightly in the radial direction.

Hierbei ist es bevorzugt, dass die Flügel axial über den Rotor überstehen. Man kann die Kurvenscheibe dann teilweise oder sogar vollständig axial außerhalb des Rotors anordnen, was den Vorteil hat, dass sich die Kurvenscheibe und der Rotor gegenseitig nicht stören.In this case, it is preferred that the wings project axially beyond the rotor. One can then arrange the cam partially or even completely axially outside the rotor, which has the advantage that the cam and the rotor do not interfere with each other.

Vorzugsweise weist die Ausnehmung eine radiale Erstreckung auf, die größer als ein maximaler Hub des Flügels ist. Die Kurvenscheibe deckt also die Flügel im Bereich der Ausnehmung über den gesamten Hub ab. Die Kurvenscheibe dient also mit zur axialen Abdichtung der Flügel, so dass eine Leckage vermieden oder zumindest klein gehalten werden kann.Preferably, the recess has a radial extent that is greater than a maximum stroke of the wing. The cam thus covers the wings in the region of the recess over the entire stroke. The cam thus serves with the axial sealing of the wings, so that leakage can be avoided or at least kept small.

Bevorzugterweise weist die Ausnehmung eine axiale Erstreckung auf, die einer axialen Dicke der Kurvenscheibe entspricht. In diesem Fall kann man dafür sorgen, dass die Flügel außerhalb der Ausnehmung mit ihrem axialen Ende an der Seitenwand und innerhalb der Ausnehmung mit ihrem axialen Ende an der Kurvenscheibe anliegen. Damit ergibt sich über die gesamte Höhe der Flügel in jeder Winkelstellung des Rotors gegenüber den stehenden Teilen eine Dichtfläche, die sich über die gesamte radiale Länge der axialen Enden der Flügel erstreckt. Damit lässt sich eine relativ gute Dichtigkeit sicherstellen.Preferably, the recess has an axial extent corresponding to an axial thickness of the cam. In this case, one can ensure that the wings abut outside the recess with its axial end on the side wall and within the recess with its axial end on the cam. This results over the entire height of the wings in each angular position of the rotor relative to the stationary parts a sealing surface which extends over the entire radial length of the axial ends of the wings. This ensures a relatively good tightness.

Vorzugsweise entspricht die Kurvenscheibe dem Innenumfang des Stators vermindert um das Doppelte der radialen Erstreckung der Flügel zuzüglich dem Doppelten der radialen Erstreckung der Ausnehmung. Dies ist eine relativ einfache Bemessungsvorschrift. Man kann die Kurvenscheibe sozusagen als verkleinerte Kopie des Innenumfangs des Stators ausbilden.Preferably, the cam corresponds to the inner circumference of the stator reduced by twice the radial extent the wing plus twice the radial extent of the recess. This is a relatively simple design rule. You can form the cam so to speak as a reduced copy of the inner circumference of the stator.

Vorzugsweise ist die Anlagefläche gerundet. Damit hält man Reibung zwischen dem Flügel und der Kurvenscheibe klein. Es lässt sich praktisch nicht vermeiden, dass der Flügel in der Führung kippt. Auch wenn dieses Kippen sehr klein gehalten werden kann, könnten sich durch dieses Kippen Probleme einstellen. Derartige Probleme werden durch das Abrunden der Anlagefläche zuverlässig vermieden.Preferably, the contact surface is rounded. This keeps friction between the wing and the cam small. It is practically unavoidable that the wing tilts in the guide. Although this tilting can be kept very small, problems could arise as a result of this tilting. Such problems are reliably prevented by the rounding of the contact surface.

In einer bevorzugten Ausgestaltung ist der Rotor zentrisch relativ zum Stator gelagert und ein Verlauf eines radialen Abstands zwischen dem Stator und dem Rotor weist in Umfangsrichtung mindestens zwei Maxima und zwei Minima auf. Mit einer derartigen Ausgestaltung erreicht man mindestens zwei Arbeitsspiele der Maschine pro Umdrehung des Rotors. Man ist nicht mehr darauf angewiesen, den Rotor exzentrisch zum Stator zu lagern. Diese Ausgestaltung würde nur ein Arbeitsspiel erlauben.In a preferred embodiment, the rotor is mounted centrically relative to the stator and a profile of a radial distance between the stator and the rotor has in the circumferential direction at least two maxima and two minima. With such a configuration to achieve at least two cycles of the machine per revolution of the rotor. It is no longer necessary to store the rotor eccentric to the stator. This embodiment would only allow one working game.

Vorzugsweise weist der Rotor eine Durchgangsöffnung, die sich axial innen zu einem Hohlraum erweitert, zur Aufnahme einer Achse auf. Der Hohlraum dient dazu, die Masse des Rotors zu vermindern.Preferably, the rotor has a passage opening, which widens axially inward to a cavity, for receiving an axle. The cavity serves to reduce the mass of the rotor.

Hierbei ist bevorzugt, dass die Flügel mit ihrer radialen Innenseite bei einem Einwärtshub in den Hohlraum eintreten. Dann wird der Hohlraum zwar mit Wasser gefüllt, wenn die Maschine betrieben wird. Dies ist aber unkritisch, weil sich der Druck des Wassers im Hohlraum auf einen Mittelwert einstellen kann.It is preferred that the wings enter with their radial inner side in an inward stroke into the cavity. Then, while the cavity is filled with water when the machine is operated. But this is not critical, because the pressure of the water in the cavity can adjust to an average value.

Bevorzugterweise weisen die Flügel einen Kern aus einem Stahl und einem Überzug aus einem mit Stahl reibungsarm zusammenwirkenden Kunststoff auf. In diesem Fall kann man den Rotor und den Stator aus Stahl bilden. Da Wasser keine schmierenden Eigenschaften besitzt, wird die Reibungsverminderung, die bei einer ölhydraulischen Maschine durch ein Hydrauliköl bewirkt wird, in diesem Fall von dem reibungsvermindernden Kunststoff bewirkt. Als Kunststoff für den Überzug kommen insbesondere Werkstoffe aus der Gruppe der hochfesten thermoplastischen Kunststoffe auf der Basis von Polyaryletherketonen, insbesondere Polyetheretherketonen, Polyamiden, Polyacetalen, Polyarylether, Polyethylenterephtalaten, Polyphenylensulfiden, Polysulfonen, Polyethersulfonen, Polyetherimiden, Polyamidimiden, Polyacrylaten, Phenol-Harzen, wie Novolack-Harzen, oder Ähnliches in Betracht, wobei als Füllstoffe Glas, Graphit, Polytetrafluorethylen oder Kunststoff, insbesondere in Faserform, verwendet werden können. Bei Verwendung derartiger Materialien lässt sich auch Wasser als Hydraulikflüssigkeit verwenden.Preferably, the wings on a core of a steel and a coating of a steel friction-co-operating plastic. In this case, the rotor and the stator can be made of steel. Since water has no lubricating properties, the friction reduction caused by a hydraulic oil in an oil-hydraulic machine is in this case effected by the friction-reducing plastic. In particular, materials from the group of high-strength thermoplastics based on polyaryl ether ketones, in particular polyether ether ketones, polyamides, polyacetals, polyaryl ethers, polyethylene terephthalates, polyphenylene sulfides, polysulfones, polyethersulfones, polyetherimides, polyamideimides, polyacrylates, phenol resins, such as novolak, are used as the plastic for the coating Resins, or the like, wherein as fillers glass, graphite, polytetrafluoroethylene or plastic, in particular in fiber form, can be used. When using such materials, water can also be used as hydraulic fluid.

In diesem Fall ist bevorzugt, dass jeder Flügel im Bereich der Führung eine aus dem mit Stahl reibungsarm zusammenwirkenden Kunststoff gebildete Oberfläche aufweist und die Anlagefläche zumindest teilweise aus einem Stahl gebildet ist, wobei die Kurvenscheibe zumindest in einem Bereich, an dem die Anlagefläche anliegt, eine aus einem mit Stahl reibungsarm zusammenwirkenden Kunststoff gebildete Oberfläche aufweist. In diesem Fall kann man erreichen, dass zwischen bewegten Teilen immer eine Paarung Kunststoff - Stahl vorliegt. Man kann also vermeiden, dass sich über größere Kontaktbereiche eine Paarung Kunststoff - Kunststoff ergibt, was jedenfalls im Hinblick auf die Reibungsverminderung und den Verschleiß nachteilig wäre.In this case, it is preferred that each vane in the region of the guide has a surface formed from the plastic with a low-friction cooperating plastic surface and the abutment surface is at least partially formed of a steel, wherein the cam at least in an area in which abuts the contact surface, a from a Having formed with plastic friction co-operating plastic surface. In this case it can be achieved that there is always a pair of plastic - steel between moving parts. It is thus possible to avoid that a combination of plastic and plastic results over larger contact areas, which would be detrimental in any case with regard to the reduction of friction and wear.

Vorzugsweise ist die Kurvenscheibe einstückig mit der Seitenplatte ausgebildet. Sie kann beispielsweise durch einen Vorsprung auf der Seitenplatte gebildet sein.Preferably, the cam is formed integrally with the side plate. It may for example be formed by a projection on the side plate.

In einer bevorzugten Ausgestaltung ist vorgesehen, dass mindestens eine Seitenwand mindestens eine Öffnung aufweist, die radial außen von einem Steg begrenzt ist, an dem die Flügel anliegen. Auch im Bereich der Öffnung wird also erreicht, dass die Flügel in Axialrichtung radial innen und radial außen abgestützt sind. Ein Kippen der Flügel in eine Richtung parallel zur Rotationsachse kann damit zuverlässig vermieden werden.In a preferred embodiment it is provided that at least one side wall has at least one opening which is bounded radially on the outside by a web on which the wings abut. Also in the region of the opening is thus achieved that the wings are supported in the axial direction radially inward and radially outward. A tilting of the wings in a direction parallel to the axis of rotation can thus be reliably avoided.

Die Erfindung wird im Folgenden anhand eines bevorzugten Ausführungsbeispiels in Verbindung mit einer Zeichnung beschrieben. Hierin zeigen:

Fig. 1
eine Schnittdarstellung I-I einer Flügelzellenmaschine nach Fig. 2,
Fig. 2
eine Schnittdarstellung I-I der Flügelzellenmaschine nach Fig. 1,
Fig. 3
eine perspektivische Darstellung der Flügelzellenmaschine ohne Seitenwand und
Fig. 4
die Darstellung nach Fig. 3 ohne Kurvenscheibe.
The invention will be described below with reference to a preferred embodiment in conjunction with a drawing. Herein show:
Fig. 1
a sectional view II of a vane machine after Fig. 2 .
Fig. 2
a sectional view II of the vane machine after Fig. 1 .
Fig. 3
a perspective view of the vane machine without side wall and
Fig. 4
the representation after Fig. 3 without cam.

Eine Flügelzellenmaschine 1 weist einen Stator 2 und einen Rotor 3 auf, die mit nicht näher dargestellten Mitteln drehbar zueinander gelagert sind. Der Rotor 3 weist mehrere Flügel 4 auf, die jeweils in einer Führung 5 im Rotor 3 radial verlagerbar sind. Die Flügel 4 liegen an einem Innenumfang 6 des Stators an. An jedem axialen Ende des Stators ist eine Seitenwand 7 angeordnet. In der Seitenwand 7 können Öffnungen 8, 9 vorgesehen sein, die zur Zufuhr bzw. zur Abfuhr von Wasser verwendet werden können. In Fig. 1 ist nur eine Seitenwand 7 dargestellt. Auf der axial gegenüber liegenden Stirnseite weist der Stator 2 ebenfalls eine Seitenwand auf, die allerdings nicht dargestellt ist. In dieser anderen Seitenwand kann man die Öffnungen 8, 9 unter Umständen weglassen.A vane machine 1 has a stator 2 and a rotor 3, which are rotatably mounted to each other by means not shown. The rotor 3 has a plurality of wings 4, which are each radially displaceable in a guide 5 in the rotor 3. The wings 4 abut against an inner periphery 6 of the stator. At each axial end of the stator, a side wall 7 is arranged. In the side wall 7 openings 8, 9 may be provided, which can be used for the supply or for the discharge of water. In Fig. 1 only one side wall 7 is shown. On the axially opposite end side of the stator 2 also has a side wall, which, however, is not shown. In this other side wall you can omit the openings 8, 9 under certain circumstances.

Die Öffnungen 8, 9 erstrecken sich radial nach außen nicht ganz bis zum Stator 2. Vielmehr sind radial außen Stege 10, 11 vorgesehen, an denen die Flügel 4 in Axialrichtung anliegen können, wenn sich der Rotor dreht. Auch im Bereich der Öffnungen 9, 10 sind also die Flügel radial innen und radial außen in Axialrichtung abgestützt.The openings 8, 9 extend radially outward not quite to the stator 2. Rather, radially outward webs 10, 11 are provided, on which the wings 4 can rest in the axial direction when the rotor rotates. Also in the region of the openings 9, 10 so the wings are supported radially inward and radially outward in the axial direction.

Im Rotor 3 ist eine Durchgangsöffnung 12 vorgesehen, durch die beispielsweise eine Welle geführt werden kann, mit der der Rotor 3 drehbar gegenüber dem Stator 2 gelagert ist. Axial in der Mitte erweitert sich die Durchgangsöffnung 12 zu einem Hohlraum 13. Wie insbesondere aus Fig. 2 zu erkennen ist, treten die Flügel 4 mit ihren radialen Innenseiten 14 in den Hohlraum 13 ein, wenn sie durch den Innenumfang 6 des Stators 2 radial nach innen gedrückt werden.In the rotor 3, a through hole 12 is provided, through which, for example, a shaft can be guided, with which the rotor 3 is rotatably mounted relative to the stator 2. Axially in the middle, the passage opening 12 widens to a cavity 13. As in particular out Fig. 2 can be seen, the wings 4 enter with their radial inner sides 14 in the cavity 13 when they are pressed by the inner periphery 6 of the stator 2 radially inward.

An beiden axialen Stirnseiten des Rotors 3 ist jeweils eine Kurvenscheibe 15 angeordnet. Die Kurvenscheibe 15 kann an der Seitenwand 7 befestigt sein oder einstückig mit der Seitenwand 7 ausgebildet sein. Sie weist eine Form auf, die dem Innenumfang 6 des Stators entspricht, allerdings in einer verkleinerten Fassung, wie weiter unten näher erläutert wird.At both axial end faces of the rotor 3, a cam 15 is arranged in each case. The cam 15 may be fixed to the side wall 7 or formed integrally with the side wall 7. It has a shape that corresponds to the inner circumference 6 of the stator, but in a reduced version, as will be explained in more detail below.

Die Flügel 4 weisen an ihren beiden axialen Enden jeweils eine Ausnehmung 16 auf. In diese Ausnehmung 16 greift die Kurvenscheibe 15 ein. Jede Ausnehmung 16 weist eine axiale Erstreckung auf, die der axialen Dicke der Kurvenscheibe 15 entspricht. Die Flügel 4 stehen um diese axiale Erstreckung axial über den Rotor 3 über, so dass es möglich ist, die Flügel 4 und die Kurvenscheibe 15 in axialer Richtung bündig miteinander abschließen zu lassen.The wings 4 each have a recess 16 at its two axial ends. In this recess 16, the cam 15 engages. Each recess 16 has an axial extent corresponding to the axial thickness of the cam 15. The wings 4 are about this axial extent axially over the rotor 3, so that it is possible to make the wings 4 and the cam 15 in the axial direction flush with each other.

Die Ausnehmungen 16 können eine Erstreckung in radialer Richtung aufweisen, die größer ist als ein maximaler Hub des Flügels. Die Kurvenscheibe 15 deckt dann die Flügel 4 über ihren gesamten radialen Hub im Bereich der Ausnehmung 16 ab.The recesses 16 may have an extent in the radial direction, which is greater than a maximum stroke of the wing. The cam 15 then covers the wings 4 over their entire radial stroke in the region of the recess 16.

Dementsprechend kann man eine relativ einfache Vorschrift erstellen, wie die Kurvenscheibe zu gestalten ist. Der Innenumfang 6 des Stators wird um das Doppelte der radialen Erstreckung der Flügel 4 vermindert. Hinzugefügt wird das Doppelte der radialen Erstreckung der Ausnehmungen 16. Mit einer derartig gestalteten Kurvenscheibe 15 wird sichergestellt, dass die Flügel 4 immer am Innenumfang 6 des Stators 2 anliegen und dort für eine ausreichende Abdichtung sorgen.Accordingly, one can create a relatively simple rule on how to make the cam. The inner circumference 6 of the stator is about twice the radial Extension of the wings 4 reduced. Added twice the radial extent of the recesses 16. With such a shaped cam 15 ensures that the wings 4 always rest on the inner circumference 6 of the stator 2 and there ensure adequate sealing.

An den axialen Enden liegen die Flügel 4 mit ihrer Stirnseite entweder an der Seitenwand 7 oder an der Kurvenscheibe 4 an, so dass auch dort eine ausreichende Abdichtung gegeben ist. Eine Abdichtung radial nach innen ergibt sich durch das Zusammenwirken der Flügel 4 mit den Führungen 5. In allen Bereichen können natürlich kleine Leckagen auftreten, weil hier bewegte Teile gegeneinander abgedichtet werden müssen. Die Leckagen können jedoch relativ klein gehalten werden.At the axial ends, the wings 4 abut with their front side either on the side wall 7 or on the cam 4, so that even there is given a sufficient seal. A seal radially inward results from the interaction of the wings 4 with the guides 5. Of course, small leaks can occur in all areas, because here moving parts must be sealed against each other. However, the leaks can be kept relatively small.

Wie in Fig. 2 zu erkennen ist, weist die dort dargestellte Flügelzellenmaschine 1 zwei Arbeitsspiele pro Umdrehung auf. Bezogen auf die Darstellung der Fig. 2 ergibt sich ein minimaler Abstand zwischen dem Innenumfang 6 des Stators 2 und dem Rotor 3 an Punkten des Rotors 3, die nach oben und nach unten weisen, und ein maximaler Abstand an Punkten, die nach links und nach rechts weisen. Da sich ein "Förderhub" immer dann realisieren lässt, wenn sich der maximale Abstand zum minimalen Abstand hin verkleinert, ergeben sich bei der in Fig. 2 dargestellten Ausführungsformen zwei Arbeitsspiele pro Umdrehung. Diese Möglichkeit wird durch die Kurvenscheibe 15 zur Verfügung gestellt.As in Fig. 2 can be seen, the vane machine 1 shown there has two cycles per revolution. Related to the representation of the Fig. 2 The result is a minimum distance between the inner periphery 6 of the stator 2 and the rotor 3 at points of the rotor 3, which point upwards and downwards, and a maximum distance at points which point to the left and to the right. Since a "delivery stroke" can always be realized when the maximum distance to the minimum distance decreases, the result in Fig. 2 illustrated embodiments two cycles per revolution. This possibility is provided by the cam 15.

Die Fig. 3 und 4 zeigen die Flügelzellenmaschine 1 in perspektivischer Darstellung. Gleiche Teile sind mit den gleichen Bezugszeichen wie in den Fig. 1 und 2 versehen.The Fig. 3 and 4 show the vane machine 1 in perspective view. Same parts are denoted by the same reference numerals as in FIGS Fig. 1 and 2 Mistake.

Die Fig. 3 und 4 lassen etwas deutlicher erkennen, dass die radialen Innenseiten der Flügel 4 im Bereich der Ausnehmungen 16, die Anlageflächen 17 der Flügel 4 an der Kurvenscheibe 15 bilden, gerundet sind.The Fig. 3 and 4 Let it be seen more clearly that the radial inner sides of the wings 4 in the region of the recesses 16, the contact surfaces 17 of the wings 4 on the cam 15 form, are rounded.

Die Kurvenscheibe 15 ist hier als getrenntes Element ausgebildet. Sie kann jedoch auch einstückig mit der Seitenwand 7 ausgebildet sein.The cam 15 is formed here as a separate element. However, it may also be formed integrally with the side wall 7.

Wenn man die Kurvenscheibe 15 als getrenntes Element ausbildet, dann kann man ihre beiden Stirnseiten bzw. Druckangriffsflächen an den beiden Stirnseiten, die beispielsweise durch nicht dargestellte Dichtungen definiert werden können, so dimensionieren, dass sich ein Kraftgleichgewicht über den Rotor in axialer Richtung ergibt. Dadurch kann man ein Spiel minimieren und entsprechend auch eine Leckage klein halten.If one forms the cam 15 as a separate element, then you can dimension their two faces or pressure application surfaces on the two end faces, which can be defined for example by seals, not shown, so that there is a force balance on the rotor in the axial direction. This allows you to minimize a game and accordingly keep a small leak.

Die Flügel 4 weisen einen Kern aus einem Stahl und einen Überzug aus einem mit Stahl reibungsarm zusammenwirkenden Kunststoff auf. Damit sind die Flügel 4 so ausgestaltet, dass sie reibungsarm mit dem Stator 2 und den Führungen 5 im Rotor 3 zusammenwirken können. Auch an ihren Stirnseiten, die an der aus Stahl gebildeten Seitenwand 7 anliegen, ergibt sich eine verringerte Reibung. Als Kunststoffe kann man beispielsweise Werkstoffe aus der Gruppe der hochfesten thermoplastischen Kunststoffe auf der Basis von Polyaryletherketonen verwenden, insbesondere Polyetheretherketonen, Polyamiden, Polyacetalen, Polyarylether, Polyethylenterephtalaten, Polyphenylensulfiden, Polysulfonen, Polyethersulfonen, Polyetherimiden, Polyamidimiden, Polyacrylaten, Phenol-Harzen, wie Novolack-Harzen, oder Ähnliches, wobei als Füllstoffe Glas, Graphit, Polytetrafluorethylen oder Kunststoff, insbesondere in Faserform, verwendet werden können. Bei Verwendung derartiger Materialien lässt sich auch Wasser als Hydraulikflüssigkeit verwenden.The wings 4 have a core of a steel and a coating of a plastic friction-co-operating with steel. Thus, the wings 4 are designed so that they can interact with low friction with the stator 2 and the guides 5 in the rotor 3. Also at their end faces, which bear against the side wall 7 formed of steel, results in a reduced friction. As plastics it is possible to use, for example, materials from the group of high-strength thermoplastics based on polyaryl ether ketones, in particular polyether ether ketones, Polyamides, polyacetals, polyaryl ethers, polyethylene terephthalates, polyphenylene sulfides, polysulfones, polyethersulfones, polyetherimides, polyamideimides, polyacrylates, phenolic resins such as novolak resins or the like, which may be glass, graphite, polytetrafluoroethylene or plastic, especially in fibrous form, as fillers , When using such materials, water can also be used as hydraulic fluid.

Zweckmäßigerweise sollte auch die Kurvenscheibe 15 mit einem entsprechenden Kunststoff versehen sein, jedenfalls in dem Bereich, an dem der Rotor 3 mit seiner Stirnseite anliegt.Conveniently, the cam 15 should be provided with a corresponding plastic, at least in the area where the rotor 3 rests with its front side.

Um nun zu vermeiden, dass die Flügel 4 dann mit einem mit Kunststoff beschichteten Bereich an der Kurvenscheibe 15 dort anliegen, wo die Kurvenscheibe 15 ebenfalls mit Kunststoff beschichtet ist, sind die Ausnehmungen 6 zweckmäßigerweise aus den Flügeln 4 herausgefräst, nachdem der Kunststoff aufgetragen worden ist. Damit ergibt sich in der Anlagefläche 17 ein Bereich, der zumindest teilweise aus einem Stahl gebildet ist und der dann an dem Kunststoff der Kurvenscheibe 15 anliegt. Durch die gerundete Form der Anlagefläche 17 lässt sich auch erreichen, dass ein Kontakt zwischen dem Kunststoff des Flügels 4 und dem Kunststoff der Kurvenscheibe 15 praktisch vermieden werden kann.In order to avoid now that the wings 4 then bear with a plastic coated area on the cam 15 where the cam 15 is also coated with plastic, the recesses 6 are expediently milled out of the wings 4 after the plastic has been applied , This results in the contact surface 17, an area which is at least partially formed of a steel and then rests against the plastic of the cam 15. Due to the rounded shape of the contact surface 17 can also be achieved that a contact between the plastic of the wing 4 and the plastic of the cam 15 can be practically avoided.

Der Flügel 4 weist dann auch eine stirnseitige Fläche 18 auf, die durch die Ausnehmung 6 gebildet ist, die ebenfalls im Wesentlichen aus dem Stahl des Kerns des Flügels 4 besteht. Diese Fläche 18 liegt dann axial an der Kurvenscheibe 15 an, so dass auch hier eine Paarung Kunststoff - Kunststoff vermieden wird und eine Paarung Stahl - Kunststoff erreicht wird.The wing 4 then also has an end face 18, which is formed by the recess 6, which also consists essentially of the steel of the core of the wing 4 exists. This surface 18 then abuts axially on the cam 15, so that a pairing plastic - plastic is avoided and a mating steel - plastic is achieved here.

Claims (14)

Hydraulische Flügelzellenmaschine (1) mit einem Stator (2) und einem Rotor (3), der mehrere Flügel (4) aufweist, die jeweils in einer Führung (5) im Rotor (3) radial verlagerbar sind, an einem Innenumfang (6) des Stators (2) anliegen und mit dem Rotor (3), dem Stator (2) und je einer Seitenwand (7) an jedem axialen Ende des Rotors (3) Arbeitskammern begrenzen, deren Volumina sich bei einer Drehung des Rotors (3) gegenüber dem Stator (2) ändern, dadurch gekennzeichnet, dass jeder Flügel (4) an seiner radialen Innenseite eine Anlagefläche (17) aufweist, die radial außen an einer Kurvenscheibe (15) anliegt.Hydraulic vane machine (1) with a stator (2) and a rotor (3), which has a plurality of vanes (4) which are radially displaceable in each case in a guide (5) in the rotor (3) on an inner circumference (6) of the Stators (2) abut and with the rotor (3), the stator (2) and one side wall (7) at each axial end of the rotor (3) limit working chambers, the volumes at a rotation of the rotor (3) relative to the Change stator (2), characterized in that each wing (4) on its radially inner side has a contact surface (17) which rests radially on the outside of a cam disc (15). Flügelzellenmaschine nach Anspruch 1, dadurch gekennzeichnet, dass die Anlagefläche (17) an mindestens einem axialen Ende der Flügel (4) ausgebildet ist.Vane machine according to claim 1, characterized in that the abutment surface (17) is formed on at least one axial end of the wings (4) is. Flügelzellenmaschine nach Anspruch 2, dadurch gekennzeichnet, dass die Anlagefläche (17) in einer Ausnehmung (16) am axialen Ende des Flügels (4) ausgebildet ist.Vane machine according to claim 2, characterized in that the abutment surface (17) is formed in a recess (16) at the axial end of the blade (4). Flügelzellenmaschine nach Anspruch 3, dadurch gekennzeichnet, dass die Flügel (4) axial über den Rotor (3) überstehen.Vane machine according to claim 3, characterized in that the wings (4) protrude axially beyond the rotor (3). Flügelzellenmaschine nach Anspruch 3 oder 4,
dadurch gekennzeichnet, dass die Ausnehmung (16) eine radiale Erstreckung aufweist, die größer als ein maximaler Hub des Flügels (4) ist.Vane machine according to claim 3 or 4,
characterized in that the recess (16) has a radial extent which is greater than a maximum stroke of the wing (4). Flügelzellenmaschine nach einem der Ansprüche 3 bis 5, dadurch gekennzeichnet, dass die Ausnehmung (16) eine axiale Erstreckung aufweist, die einer axialen Dicke der Kurvenscheibe (15) entspricht.Vane machine according to one of claims 3 to 5, characterized in that the recess (16) has an axial extension which corresponds to an axial thickness of the cam disc (15). Flügelzellenmaschine nach einem der Ansprüche 5 oder 6, dadurch gekennzeichnet, dass die Kurvenscheibe (15) dem Innenumfang (6) des Stators (2) vermindert um das Doppelte der radialen Erstreckung der Flügel (4) zuzüglich dem Doppelten der radialen Erstreckung der Ausnehmung (16) entspricht.Vane machine according to one of claims 5 or 6, characterized in that the cam disc (15) the inner periphery (6) of the stator (2) reduced by twice the radial extension of the wings (4) plus twice the radial extension of the recess (16 ) corresponds. Flügelzellenmaschine nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Anlagefläche (17) gerundet ist.Vane machine according to one of claims 1 to 7, characterized in that the contact surface (17) is rounded. Flügelzellenmaschine nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass der Rotor (3) zentrisch relativ zum Stator (2) gelagert ist und ein Verlauf eines radialen Abstands zwischen dem Stator (2) und dem Rotor (3) in Umfangsrichtung mindestens zwei Maxima und zwei Minima aufweist.Vane cell machine according to one of claims 1 to 8, characterized in that the rotor (3) is mounted centrally relative to the stator (2) and a course of a radial distance between the stator (2) and the rotor (3) in the circumferential direction at least two maxima and two minima. Flügelzellenmaschine nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass der Rotor (3) eine Durchgangsöffnung (12) zur Aufnahme einer Achse aufweist, die sich axial innen zu einem Hohlraum (13) erweitert.Vane machine according to one of claims 1 to 9, characterized in that the rotor (3) has a passage opening (12) for receiving an axis which widens axially inward to a cavity (13). Flügelzellenmaschine nach Anspruch 10, dadurch gekennzeichnet, dass die Flügel (4) mit ihrer radialen Innenseite (14) bei einem Einwärtshub in den Hohlraum (13) eintreten.Vane machine according to claim 10, characterized in that the wings (4) with their radial inner side (14) enter the cavity (13) during an inward stroke. Flügelzellenmaschine nach einem der Ansprüche 1 bis 11, dadurch gekennzeichnet, dass die Flügel (4) einen Kern aus einem Stahl und einen Überzug aus dem mit Stahl reibungsarm zusammenwirkenden Kunststoff aufweisen.Vane machine according to one of claims 1 to 11, characterized in that the wings (4) have a core made of a steel and a coating of the steel with low friction cooperating plastic. Flügelzellenmaschine nach Anspruch 12, dadurch gekennzeichnet, dass jeder Flügel (4) im Bereich der Führung (5) eine aus einem mit Stahl reibungsarm zusammenwirkenden Kunststoff gebildete Oberfläche aufweist und die Anlagefläche (17) zumindest teilweise aus einem Stahl gebildet ist, wobei die Kurvenscheibe (15) zumindest in einem Bereich, an dem der Flügel (4) anliegt, eine aus einem mit Stahl reibungsarm zusammenwirkenden Kunststoff gebildete Oberfläche aufweist.Vane machine according to claim 12, characterized in that each wing (4) in the region of the guide (5) has a surface formed from a plastic friction-co-operating plastic surface and the contact surface (17) at least partially is formed of a steel, wherein the cam disc (15) at least in an area on which the wing (4) rests, one of a steel friction-co-operating cooperating plastic formed surface. Flügelzellenmaschine nach einem der Ansprüche 1 bis 13, dadurch gekennzeichnet, dass die Kurvenscheibe (15) einstückig mit der der Seitenwand (7) ausgebildet ist.Vane machine according to one of claims 1 to 13, characterized in that the cam disc (15) is formed integrally with the side wall (7).
EP14193256.6A 2014-11-14 2014-11-14 Hydraulic vane cell machine Active EP3020917B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
ES14193256T ES2813957T3 (en) 2014-11-14 2014-11-14 Hydraulic fin machine
EP14193256.6A EP3020917B1 (en) 2014-11-14 2014-11-14 Hydraulic vane cell machine
CN201510683523.5A CN105604781B (en) 2014-11-14 2015-10-20 Hydraulic vane formula machine
US14/930,720 US9945231B2 (en) 2014-11-14 2015-11-03 Hydraulic vane-type machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14193256.6A EP3020917B1 (en) 2014-11-14 2014-11-14 Hydraulic vane cell machine

Publications (2)

Publication Number Publication Date
EP3020917A1 true EP3020917A1 (en) 2016-05-18
EP3020917B1 EP3020917B1 (en) 2020-07-15

Family

ID=51904772

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14193256.6A Active EP3020917B1 (en) 2014-11-14 2014-11-14 Hydraulic vane cell machine

Country Status (4)

Country Link
US (1) US9945231B2 (en)
EP (1) EP3020917B1 (en)
CN (1) CN105604781B (en)
ES (1) ES2813957T3 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7037458B2 (en) * 2018-09-07 2022-03-16 日立Astemo株式会社 Pump device
CN111550361B (en) * 2020-06-28 2022-03-18 河北中清永晟石油科技有限公司 Novel positive displacement is electricity generation in pit device and contains its novel oil field water injection system

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1315068A (en) * 1961-11-09 1963-01-18 Internal combustion engine with rotary piston
DE2316529A1 (en) * 1973-04-03 1974-10-24 Alfons Lugauer POWER MACHINE, E.G. COMBUSTION OR HYDRAULIC MOTOR OR PUMP
US4454844A (en) * 1980-03-03 1984-06-19 Kinsey Lewis R Four cycle rotary engine employing eccentrical mounted rotor
DE3524275A1 (en) * 1985-07-06 1986-04-17 Daniel 7750 Konstanz Becker Rotary piston-like rotary engine
DE10109572A1 (en) * 2001-02-22 2001-10-31 Andreas Ohl Vane piston motor with rotor in casing has pressure constantly exerted on vane pistons from combustion stroke
US6684847B1 (en) 2002-07-10 2004-02-03 Osama Al-Hawaj Radial vane rotary device

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0247001A3 (en) * 1986-05-22 1988-09-28 Hans Dr. Wälchli Vane pump for the transport of pasty foodstuffs, especially of sausage meat
JP2009517583A (en) * 2005-11-23 2009-04-30 ベンジェンス・パワー・インコーポレーテッド Internal combustion engine
DE102011116869B4 (en) * 2011-10-25 2015-07-02 Danfoss A/S Vane machine
CN102536801B (en) * 2011-12-12 2015-04-22 马燕翔 Vane pump without stator wearing
JP5897945B2 (en) * 2012-03-22 2016-04-06 日立オートモティブシステムズ株式会社 Vane pump

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1315068A (en) * 1961-11-09 1963-01-18 Internal combustion engine with rotary piston
DE2316529A1 (en) * 1973-04-03 1974-10-24 Alfons Lugauer POWER MACHINE, E.G. COMBUSTION OR HYDRAULIC MOTOR OR PUMP
US4454844A (en) * 1980-03-03 1984-06-19 Kinsey Lewis R Four cycle rotary engine employing eccentrical mounted rotor
DE3524275A1 (en) * 1985-07-06 1986-04-17 Daniel 7750 Konstanz Becker Rotary piston-like rotary engine
DE10109572A1 (en) * 2001-02-22 2001-10-31 Andreas Ohl Vane piston motor with rotor in casing has pressure constantly exerted on vane pistons from combustion stroke
US6684847B1 (en) 2002-07-10 2004-02-03 Osama Al-Hawaj Radial vane rotary device

Also Published As

Publication number Publication date
EP3020917B1 (en) 2020-07-15
CN105604781A (en) 2016-05-25
US20160138398A1 (en) 2016-05-19
ES2813957T3 (en) 2021-03-25
CN105604781B (en) 2018-11-27
US9945231B2 (en) 2018-04-17

Similar Documents

Publication Publication Date Title
DE2443720C3 (en) Rotary lobe pump for liquids
DE102006057364B4 (en) Water hydraulic machine
EP2359005B1 (en) Sliding vane pump
DE102011116869B4 (en) Vane machine
DE102011116858B4 (en) Vane machine
WO2016173798A1 (en) Pump device
EP0659237B1 (en) Vane cell machine
WO2008148472A1 (en) Vane pump
DE1653801A1 (en) Capsule pump
EP3020917A1 (en) Hydraulic vane cell machine
DE102018100614B4 (en) Flow-optimized vane pump
DE2835457C2 (en)
EP2961988B1 (en) Screw pump with at least two parts
DE1812251C3 (en) Vane pump
DE102011000533A1 (en) Variable displacement pump for steering system of motor vehicles, has rotor elements that coincide with point contact, which are made to abut against sintered cam track
DE102004021216B4 (en) High-pressure internal gear machine with multiple hydrostatic bearings per ring gear
DE3242983A1 (en) ADJUSTABLE WING CELL PUMP
DE1728268A1 (en) Vane pump or motor
DE19529806C2 (en) Vane pump
DE102016117802A1 (en) pump device
WO2014191176A1 (en) Positive displacement pump, especially rotary vane pump
DE4415663B4 (en) Vane pump
DE102010005072A1 (en) High pressure internal gear pump has multi-part pump housing which defines pump chamber that has low pressure area, pressure build-up area and high pressure area
DE102019127389A1 (en) Vane pump
DE102013224660A1 (en) Vane machine with defined pressure in the hindwing spaces

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20161116

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20181116

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20200227

RIN1 Information on inventor provided before grant (corrected)

Inventor name: HAUGAARD, ERIK

Inventor name: PETERSEN, HANS CHRISTIAN

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAR Information related to intention to grant a patent recorded

Free format text: ORIGINAL CODE: EPIDOSNIGR71

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

INTC Intention to grant announced (deleted)
AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

INTG Intention to grant announced

Effective date: 20200605

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502014014450

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1291248

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200815

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201116

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201015

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201016

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201015

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201115

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2813957

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20210325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502014014450

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

26N No opposition filed

Effective date: 20210416

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201114

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20201130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201114

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1291248

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200715

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230617

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231006

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20231208

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20231003

Year of fee payment: 10