EP2582929A1 - Rotor for a camshaft adjuster and camshaft adjuster - Google Patents

Rotor for a camshaft adjuster and camshaft adjuster

Info

Publication number
EP2582929A1
EP2582929A1 EP11722084.8A EP11722084A EP2582929A1 EP 2582929 A1 EP2582929 A1 EP 2582929A1 EP 11722084 A EP11722084 A EP 11722084A EP 2582929 A1 EP2582929 A1 EP 2582929A1
Authority
EP
European Patent Office
Prior art keywords
rotor
camshaft adjuster
stator
sealing
wing
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
EP11722084.8A
Other languages
German (de)
French (fr)
Other versions
EP2582929B1 (en
Inventor
Armin Braun
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.)
Schaeffler Technologies AG and Co KG
Original Assignee
Schaeffler Technologies AG and Co KG
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 Schaeffler Technologies AG and Co KG filed Critical Schaeffler Technologies AG and Co KG
Publication of EP2582929A1 publication Critical patent/EP2582929A1/en
Application granted granted Critical
Publication of EP2582929B1 publication Critical patent/EP2582929B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01L—CYCLICALLY OPERATING VALVES FOR MACHINES OR ENGINES
    • F01L1/00—Valve-gear or valve arrangements, e.g. lift-valve gear
    • F01L1/34—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift
    • F01L1/344—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift changing the angular relationship between crankshaft and camshaft, e.g. using helicoidal gear
    • F01L1/356—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift changing the angular relationship between crankshaft and camshaft, e.g. using helicoidal gear making the angular relationship oscillate, e.g. non-homokinetic drive
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01L—CYCLICALLY OPERATING VALVES FOR MACHINES OR ENGINES
    • F01L1/00—Valve-gear or valve arrangements, e.g. lift-valve gear
    • F01L1/34—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift
    • F01L1/344—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift changing the angular relationship between crankshaft and camshaft, e.g. using helicoidal gear
    • F01L1/3442—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift changing the angular relationship between crankshaft and camshaft, e.g. using helicoidal gear using hydraulic chambers with variable volume to transmit the rotating force
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01L—CYCLICALLY OPERATING VALVES FOR MACHINES OR ENGINES
    • F01L1/00—Valve-gear or valve arrangements, e.g. lift-valve gear
    • F01L1/34—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift
    • F01L1/344—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift changing the angular relationship between crankshaft and camshaft, e.g. using helicoidal gear
    • F01L1/3442—Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening and without affecting the magnitude of the valve lift changing the angular relationship between crankshaft and camshaft, e.g. using helicoidal gear using hydraulic chambers with variable volume to transmit the rotating force
    • F01L2001/3445—Details relating to the hydraulic means for changing the angular relationship
    • F01L2001/34479—Sealing of phaser devices

Definitions

  • the invention relates to a rotor for a camshaft adjuster with a rotor base body and with a number of arranged on the rotor base body and extending radially outwardly rotor blades. Furthermore, the invention relates to a camshaft adjuster with such a rotor.
  • a rotor serves to support the targeted adjustment of the phase position between a camshaft and a crankshaft in an internal combustion engine.
  • it is usually held as part of a camshaft adjuster in a rotatably connected to the crankshaft stator.
  • the rotor In the installed state, the rotor is non-rotatably connected to the camshaft and can be adjusted relative to the stator, whereby rotation of the camshaft relative to the stator in a predetermined angular range can be achieved. In this way, for example, specifically the performance of an internal combustion engine can be increased or its fuel consumption can be reduced.
  • the wings of a rotor divided in the installed state usually formed in the stator pressure chambers each in hydraulic areas, which are acted upon to control the Nockwellenverstellers with hydraulic fluid.
  • functional gaps occur, in particular at the point of contact of the rotor blades and the outer surface of the stator, as a result of which the hydraulic fluid can pass uncontrollably from one to the other hydraulic area.
  • various concepts for sealing are known. From WO 2007/088108 A1 a rotor of the aforementioned type is known, which is used in a camshaft adjuster for an internal combustion engine.
  • the rotor has a number of radially oriented vanes, which seal in the region of their end face with respect to the inner circumferential surface of the stator.
  • WO 2007/088 08 A1 proposes the use of a separate sealing element.
  • the sealing element is formed with a U-shaped base cross section with a circumferentially oriented base leg and two radially oriented side legs.
  • the U-shaped base cross-section can embrace the entire end region of the end face of the rotor blade from the outside.
  • Another embodiment provides that the wing has end-side grooves, in which engage the side legs of the separate sealing element.
  • WO 2006/1 1217 A1 discloses a rotor as part of a device for adjusting the camshaft of an internal combustion engine, the rotor body is formed with a number of grooves. In these grooves, the rotor blades are inserted. Between the groove bottom of the groove and the rotor blade here is a separate so-called spring element is arranged, which presses the rotor blade on the one hand radially outward and on the other hand sealingly abuts the groove bottom. The spring element acts accordingly as a spring and sealing element alike and thus prevents the flow of hydraulic fluid between the hydraulic areas both between the blade end of the rotor blade and in the groove bottom within the rotor body.
  • a vane rotor is known as part of a valve timing control device for an internal combustion engine.
  • the blades of the rotor are provided with a retaining groove cut in the axial direction on the end face of the blade end.
  • a separate sealing element can be fitted, which is in sliding contact with the inner peripheral surface of the stator.
  • the sealing element is additionally held with a leaf spring in the retaining groove of the wing.
  • a first object of the invention to provide a rotor which is improved over the prior art and which offers a cost-neutral and production-technically easily implementable possibility for reducing the leakage in a camshaft adjuster.
  • a second object of the invention is to provide a camshaft adjuster with such a rotor.
  • the first object of the invention is achieved by a rotor for a camshaft adjuster, with a rotor base body and with a number of arranged on the rotor body and radially outwardly extending rotor blades, each having a wing tip. It is provided that the wing ends of the rotor blades are formed to reduce leakage to radially outwardly elastically deformable sealing webs.
  • the invention is based on the recognition that the internal leakage in a camshaft adjuster is caused by too wide a gap between the components delimiting the hydraulic regions.
  • the gaps can be reduced such that during operation of a camshaft adjuster sufficient sealing of the hydraulic areas is given from each other. This can be achieved, for example, by narrower slit reach dimensions.
  • a high dimensional accuracy in the manufacture of the components is required in order to ensure a trouble-free function of the camshaft adjuster. This can only be achieved with great effort up to the present time.
  • the sealing webs are part of the rotor blades and fulfill due to their elasticity the required sealing function in the operation of a camshaft adjuster, which was previously taken over by separate sealing elements.
  • the sealing effect of the rotor blades is based, in particular, on the centrifugal forces acting during operation of the internal combustion engine or of the camshaft adjuster, which act on a body in a rotating system. The centrifugal force is directed radially outward from the axis of rotation and depends on the mass of the body and its distance from the axis of rotation.
  • the rotor may be formed, for example, with a substantially circular base body.
  • the number of blades arranged on the main body can be variable depending on the adjustment angle to be set. Basically, the more rotor blades are arranged on the rotor body, the lower the adjustable adjustment angle.
  • the rotor blades may be attached to the rotor base body as separate components or preferably be made in one piece with this.
  • the rotor blades extend in the radial direction, so that they lie in the installed state with their wing tips on the inner circumference or on the inner circumferential surface of a stator.
  • the wing ends extend in the circumferential direction, preferably with an outer radius corresponding to the inner radius of the stator, in order, for example, during operation to prevent tilting of the wing ends on the inner circumferential surface of the stator.
  • the functionality is ensured due to the elastic deformability of the wing tips.
  • one of the rotor blades may be formed with a locking bore, which serves in the installed state for locking with a stator, so that the stator and rotor can be kept in an optimal position, in particular for the start or idle of an internal combustion engine.
  • the sealing webs can basically be designed differently.
  • the material thickness of the sealing webs is in this case particularly dependent on the overall component nature of the rotor or the rotor blades.
  • the dimensions of the Sealing webs and the material affect the elastic deformability of the sealing webs.
  • the material can be selected correspondingly to the forces acting during operation, so that an adjustment of the resulting radial leakage gaps between the wing tips and the inner circumferential surface of a stator is possible both at standstill and during operation.
  • the webs are formed in particular by a targeted material weakening at the wing tip.
  • material recesses are introduced in the wing tips to form the sealing webs.
  • the material recesses are in this case preferably limited in the radial direction of the sealing webs.
  • the material recesses can be introduced, for example, as cavities, as recesses or depressions in the rotor blades. They are preferably already introduced into the rotor blades during the immediate production of the rotor, for example in the case of a sintered or cast part by the use of a corresponding shape, so that no subsequent processing steps are necessary.
  • the elastic sealing webs can be designed durable by a vote of the material recesses with the material thickness, so that they can always withstand the forces acting on them resistant.
  • the material recesses are formed at the wing ends along the circumferential direction with a constant radial width.
  • a uniform sealing effect occurs over the circumference.
  • the highest sealing effect is achieved in the middle of the web, since the elastic deformation is most pronounced at this point.
  • the material recesses defining at the wing ends sealing webs are formed with a freely movable web end. Since the web is firmly connected to the wing end only on one side, in this case the freely movable end can be elastically deformed particularly easily during operation. This embodiment also makes it possible to influence the width of the radial leakage gaps along the circumferential direction.
  • the rotor body is made with the rotor blades in one piece with a powder metallurgy process.
  • the one-piece production is particularly advantageous because a simplification of the manufacturing process can be achieved.
  • the invention makes it possible to manufacture rotor body and rotor blades as a component in a common process to provide the density functionality. An assembly of individual parts is eliminated. In contrast to a multi-part manufacturing additional possible leaks are avoided at the contact point of Rotorgrundköpers with the rotor blades.
  • a sintering process is preferred.
  • a sintering process can achieve a high precision, which is advantageous for the adjustment of the radial leakage gaps. Since sintered components have a high dimensional accuracy, additional elaborate post-processing steps of the rotor can be omitted.
  • a sintering process additionally offers the Possibility of using an automated process flow, which avoids increased process costs and additional processing effort.
  • the sintered material has an influence on the strength and the weight of the rotor, which in turn can affect the elastic deformation of the sealing webs. Accordingly, the choice of sintering material can also influence the remaining width of the radial leakage gaps in the operation of a camshaft adjuster.
  • the sealing webs may have a wall thickness, through which the desired sealing effect is given at a sufficiently high strength.
  • the wall thickness in this case depends in the circumferential direction on the shape of the material recesses formed in the wing ends. For example, the wall thickness of a dumbbell-shaped material recess at the outer ends of the sealing webs, in the region of the larger recesses, less than in the intervening area.
  • the second object of the invention is achieved by a camshaft adjuster for an internal combustion engine, comprising a stator and disposed within the stator, relative to this rotatable rotor according to the aforementioned embodiments. It is provided that the sealing webs of the radially outwardly extending wing ends seal against the inner circumferential surface of the stator.
  • the sealing effect of the sealing webs is based on the centrifugal forces acting during operation of the camshaft adjuster.
  • the sealing webs are radially elastically deformed and pressed against the inner circumferential surface of the stator. This results in a reduction of the radial leakage gaps between the rotor blades and the inner wall of the stator.
  • the sealing effect achieved thereby allows the operation of a camshaft adjuster without an additional sealing element.
  • the stator usually has a number of radially inwardly extending webs, between which pressure chambers are formed.
  • the radially outwardly extending vanes of the rotor can be positioned in the pressure chambers, so that the hydraulic regions for acting on hydraulic fluid are formed on the outer sides of the vanes.
  • the camshaft adjuster is usually formed next to the stator and the rotor still with a sealing cover and with a locking cover.
  • the locking cover is preferably connected to the stator and limits the pressure chambers on the camshaft side. It serves to seal the pressure chamber to the outside, prevents uncontrolled leakage of hydraulic fluid and thus reduces external leakage.
  • a gate is formed, which serves to lock the stator and rotor in a designated position.
  • the gap dimensions decrease as a function of the centrifugal forces acting on the rotor or on the wing ends.
  • the dimensions or the width of the radial leakage gaps here depend, for example, on the component thickness of the rotor and on the wall thickness of the sealing webs. These and the material recesses can be matched to each other, so that a durable design of the elastic or elastically deformable sealing webs is possible.
  • FIG. 1 to 3 each show a rotor with differently shaped rotor blades in a cross section and
  • FIG. 4 shows a camshaft adjuster with a rotor according to FIG. 1 in the installed state in a cross section.
  • Fig. 1 shows a rotor 1 for a camshaft adjuster in a cross section.
  • the rotor 1 has a rotor base body 3 with four radially outwardly extending rotor blades 5.
  • the rotor blades 5 serve to divide a respective pressure chamber of a camshaft adjuster into two adjacent hydraulic areas.
  • a phaser is shown in FIG.
  • the rotor base body 3 and the rotor blades 5 are made in one piece by a sintering process of a metallic material.
  • a sintering process offers the possibility of using an automated process flow and is therefore inexpensive and easy to carry out. Due to the dimensional accuracy of the method, the rotor 1 can be made so that the radial leakage gaps between the wing tips and the inner circumferential surface of a stator when installed are sufficiently low.
  • the rotor blades 5 have wing tips 7, which are designed to reduce the leakage in a camshaft adjuster.
  • the wing tips 7 are formed to radially outwardly elastically deformable sealing webs 9. They persist made of the same material as the rotor blades 5 and are produced during the sintering process as part of the rotor blades 5 or as part of the rotor 1.
  • the elastic deformability of the sealing webs 9 is caused by the material recesses 1 1 introduced into the wings 7.
  • the material recesses 11 are limited in the radial direction of the sealing webs 9 and extend in the circumferential direction with a constant radial gap. As a result, a uniform sealing effect occurs over the circumference during operation. In the middle of the sealing webs 9 in this case the highest sealing effect is achieved, since at this point the elastic deformation of the blade ends 7 is most pronounced.
  • the material recesses 1 1 are already introduced by the manufacturing process of the rotor 1 directly into the rotor blades 5. Overall, a reduction in internal leakage can be achieved without the use of separate sealing elements.
  • a locking bore 13 is included for locking with a stator in the installed state.
  • a piston can engage through the locking bore 13 into a slot in the base of a locking cover, so that the rotor 1 and a stator can be held in an optimum position, in particular for starting or idling an internal combustion engine.
  • the scenery for locking can be seen in Fig. 4.
  • a rotor 21 for a phaser can be seen in a cross section.
  • the rotor 21 also has a rotor base body 23 with four radially outwardly extending rotor blades 25 which divide the pressure chambers of a camshaft adjuster into hydraulic areas when installed.
  • the rotor 21 is also made in one piece by means of a sintering process of a metallic material.
  • material recesses 29 are also introduced, which are bounded radially outwardly by sealing webs 31.
  • the material recesses 29 are formed with a circumferentially extending variable radial gap in the form of a dumbbell. Accordingly, the sealing webs 31 have a wall thickness changed along the circumferential direction.
  • Their designation 33, 35 is shown only on a material recess 29 for the sake of clarity. At the circular recesses 33 a deformation point for the elastic movement of the sealing web 31 is created specifically to the outside.
  • a locking bore 37 for locking with a stator in the installed state is also encompassed by a rotor blade 25 of the rotor 21.
  • the rotor 41 likewise shown in a cross-section in FIG. 3 with a rotor main body 43 and four rotor blades 45 arranged thereon is produced in one piece according to FIGS. 1 and 2 by sintering.
  • the radially outwardly extending rotor vanes 45 have at the wing ends 47 sealing webs 49.
  • sealing webs 49 limit the material recesses 51 introduced into the wing ends 47 in the radial direction.
  • the material recesses 51 are formed in the circumferential direction with a variable radial gap and opened to one of the wing stop surfaces 71, 73 out.
  • the wing ends 47 are weakened by the material recesses 51 on one side to be hinged sealing webs 49.
  • the respective free web end 53 of the sealing webs 49 is pressed radially outward by the centrifugal force acting on the rotor 41 during operation.
  • the wall thickness at the location of the circular recess 57 is increased relative to the location of the adjoining web-shaped recess 57.
  • Their name 55, 57 is shown in Fig. 2 for the sake of clarity only on a material recess 51.
  • a locking hole 59 is inserted in a rotor blade 45 of the rotor 41, which serves in the installed state, the locking of the rotor and stator in a desired position.
  • FIG. 4 shows a camshaft adjuster 61 with a rotor 1 inserted in a stator 63 according to FIG. 1 in a plan view.
  • the rotor 1 has a rotor main body 3 with four rotor blades 5 extending radially outwards.
  • Rotor main bodies 3 and rotor blades 5 are produced in one piece by sintering from a metallic material. For the description of the rotor 1, reference is made to FIG. 1 at this point.
  • the stator 63 has radially inwardly extending webs 65, between each of which a rotor blade 5 of the rotor 1 is positioned.
  • the rotor blades 5 divide the pressure chambers 67 formed in the stator 63 into two hydraulic areas 69, which are located on the right or left of the rotor blades 5, respectively. Due to the clarity, this is indicated in FIG. 4 only for one pressure chamber 67 or two hydraulic regions 69.
  • At two webs 65 each have a wing stop surface 71, 73 is formed, which stop the rotor blades 5 in a certain position by a stop. Both wing stop surfaces 71, 73 are located within a pressure chamber 67 or respectively in a hydraulic region 69, so that the rotor blade 5 can abut the pressure chamber 67 on both sides.
  • Fig. 4 shows the camshaft adjuster 61 at a standstill, wherein the radially outwardly extending wing ends 7 of the rotor blades 5, and the sealing webs 9 with its outer periphery do not rest directly on the inner circumference of the stator 63.
  • the radial leakage gaps 75 which are formed between the inner circumferential surface 77 of the stator 63 and the blade ends, can therefore be clearly seen.
  • the leakage gaps 75 decrease while increasing the tightness between the hydraulic regions 69.
  • the sealing webs 9 are deformed radially in the direction of the inner lateral surface 77 of the stator 63, so that the radial Reduce the gap between rotor 1 and stator 63. As a result, the leakage is reduced and a sealing of the hydraulic regions 69 from each other can be achieved without the use of separate sealing elements.
  • the rotor 1 has oil passages for pressurizing the pressure chambers 67 with oil, wherein these passages can not be recognized, since they are located inside the body of the rotor 1.
  • a locking bore 13 is introduced, by means of which a piston (not shown) can engage in the crank 81 introduced into the locking cover 79.
  • a piston (not shown) can engage in the crank 81 introduced into the locking cover 79.
  • the rotor 1 can be held in a predetermined position.
  • the piston is raised and the rotor 1 can move at a certain adjustment angle.
  • the locking cover 79 is connected to the stator 63 and limits the pressure chambers 67 camshaft side. In this way, the locking lid 79 additionally serves to reduce the external leakage of the camshaft adjuster 61.

Abstract

The invention relates to a rotor (1, 21, 41) for a camshaft adjuster (61), comprising a rotor base body (3, 23, 43) and a number of rotor blades (5, 25, 45) extending radially outwards and located on the rotor base body (3, 23, 43), each of said blades having a blade end (7, 27, 47). To reduce leakage, the blade ends (7, 27, 47) of the rotor blades (5, 25, 45) take the form of sealing fins (9, 31, 49) that can be deformed radially outwards. A rotor (1, 21, 41) of this type affords the possibility of reducing leakage in a camshaft adjuster (61) using simple engineering and without added costs. The invention also relates to a camshaft adjuster (61) for an internal combustion engine, comprising a rotor (1, 21, 41) of this type.

Description

Bezeichnung der Erfindung  Name of the invention
Rotor für einen Nockenwellenversteller und Nockenwellenversteller Beschreibung Rotor for a Camshaft adjuster and Camshaft adjuster Description
Gebiet der Erfindung Field of the invention
Die Erfindung betrifft einen Rotor für einen Nockenwellenversteller mit einem Rotorgrundkörper sowie mit einer Anzahl von am Rotorgrundkörper angeordneten und sich radial nach außen erstreckenden Rotorflügeln. Weiterhin betrifft die Erfindung einen Nockenwellenversteller mit einem derartigen Rotor. The invention relates to a rotor for a camshaft adjuster with a rotor base body and with a number of arranged on the rotor base body and extending radially outwardly rotor blades. Furthermore, the invention relates to a camshaft adjuster with such a rotor.
Hintergrund der Erfindung Background of the invention
Ein Rotor dient der Unterstützung der gezielten Verstellung der Phasenlage zwischen einer Nockenwelle und einer Kurbelwelle in einer Brennkraftmaschine. Hierzu ist er als Teil eines Nockenwellenverstellers üblicherweise in einem drehfest mit der Kurbelwelle verbundenen Stator gehalten. Im eingebauten Zu- stand ist der Rotor drehfest mit der Nockenwelle verbunden und kann gegenüber dem Stator verstellt werden, wodurch eine Drehung der Nockenwelle gegenüber dem Stator in einem vorbestimmten Winkelbereich erreicht werden kann. Auf diese Weise kann beispielsweise gezielt die Leistung einer Brennkraftmaschine erhöht oder deren Kraftstoffverbrauch gesenkt werden. A rotor serves to support the targeted adjustment of the phase position between a camshaft and a crankshaft in an internal combustion engine. For this purpose, it is usually held as part of a camshaft adjuster in a rotatably connected to the crankshaft stator. In the installed state, the rotor is non-rotatably connected to the camshaft and can be adjusted relative to the stator, whereby rotation of the camshaft relative to the stator in a predetermined angular range can be achieved. In this way, for example, specifically the performance of an internal combustion engine can be increased or its fuel consumption can be reduced.
Die Flügel eines Rotors unterteilen im eingebauten Zustand üblicherweise im Stator ausgebildete Druckkammern jeweils in Hydraulikbereiche, die zur Steuerung des Nockwellenverstellers mit Hydraulikflüssigkeit beaufschlagt werden. Hierbei treten insbesondere an der Kontaktstelle der Rotorflügel und der Man- telfläche des Stators funktionsbedingte Spalte auf, wodurch das Hydraulikfluid unkontrolliert von einem in den anderen Hydraulikbereich gelangen kann. Um diese unerwünschte interne Leckage zu verringern, sind verschiedene Konzepte zur Abdichtung bekannt. Aus der WO 2007/088108 A1 ist hierzu ein Rotor der eingangs genannten Art bekannt, der in einem Nockenwellenversteller für eine Brennkraftmaschine eingesetzt ist. Der Rotor weist eine Anzahl von radial orientierten Flügeln auf, die im Bereich ihrer Stirnfläche gegenüber der inneren Mantelfläche des Stators abdichten. Zur Abdichtung der durch die Flügel voneinander getrennten Hydraulikbereiche schlägt die WO 2007/088 08 A1 die Verwendung eines separaten Dichtelementes vor. Das Dichtelement ist mit einem U-förmigen Grundquerschnitt mit einem in Umfangsrichtung orientierten Grundschenkel und zwei radial orientierten Seitenschenkeln ausgebildet. Der U-förmige Grundquerschnitt kann den gesamten Endbereich der Stirnseite des Rotorflügels von außen umgreifen. Eine andere Ausführungsvariante sieht vor, dass der Flügel stirnseitige Nuten aufweist, in die die Seitenschenkel des separaten Dichtelements eingreifen. The wings of a rotor divided in the installed state usually formed in the stator pressure chambers each in hydraulic areas, which are acted upon to control the Nockwellenverstellers with hydraulic fluid. In this case, functional gaps occur, in particular at the point of contact of the rotor blades and the outer surface of the stator, as a result of which the hydraulic fluid can pass uncontrollably from one to the other hydraulic area. To reduce this unwanted internal leakage, various concepts for sealing are known. From WO 2007/088108 A1 a rotor of the aforementioned type is known, which is used in a camshaft adjuster for an internal combustion engine. The rotor has a number of radially oriented vanes, which seal in the region of their end face with respect to the inner circumferential surface of the stator. For sealing the hydraulic areas separated by the wings, WO 2007/088 08 A1 proposes the use of a separate sealing element. The sealing element is formed with a U-shaped base cross section with a circumferentially oriented base leg and two radially oriented side legs. The U-shaped base cross-section can embrace the entire end region of the end face of the rotor blade from the outside. Another embodiment provides that the wing has end-side grooves, in which engage the side legs of the separate sealing element.
Die WO 2006/1 1217 A1 offenbart einen Rotor als Teil einer Vorrichtung zur Nockenwellenverstellung einer Brennkraftmaschine, dessen Rotorgrundkörper mit einer Anzahl von Nuten ausgebildet ist. In diese Nuten werden die Rotorflügel eingesteckt. Zwischen dem Nutgrund der Nut und dem Rotorflügel ist hier ein separates sogenanntes Federelement angeordnet, welches den Rotorflügel einerseits radial nach außen drückt und zum anderen am Nutgrund dichtend anliegt. Das Federelement wirkt entsprechend als Feder- und Dichtelement gleichermaßen und verhindert so den Fluss von Hydraulikflüssigkeit zwischen den Hydraulikbereichen sowohl zwischen dem Flügelende des Rotorflügels als auch im Nutgrund innerhalb des Rotorgrundkörpers. WO 2006/1 1217 A1 discloses a rotor as part of a device for adjusting the camshaft of an internal combustion engine, the rotor body is formed with a number of grooves. In these grooves, the rotor blades are inserted. Between the groove bottom of the groove and the rotor blade here is a separate so-called spring element is arranged, which presses the rotor blade on the one hand radially outward and on the other hand sealingly abuts the groove bottom. The spring element acts accordingly as a spring and sealing element alike and thus prevents the flow of hydraulic fluid between the hydraulic areas both between the blade end of the rotor blade and in the groove bottom within the rotor body.
Weiterhin ist aus der DE 199 805 80 T1 ein Flügelrotor als Teil einer Ventilzeitsteuervorrichtung für eine Verbrennungskraftmaschine bekannt. Die Flügel des Rotors sind mit einer in axialer Richtung geschnittenen Haltenut an der Stirnflä- che des Flügelendes versehen. In diese Haltenut kann ein separates Dichtelement eingepasst werden, welches in Gleitkontakt mit der inneren Umfangsflä- che des Stators steht. Das Dichtelement wird zusätzlich mit einer Blattfeder in der Haltenut des Flügels gehalten. Zwar bieten alle vorgenannten Ausgestaltungen für einen Rotor eine Möglichkeit zur Verringerung der Leckage innerhalb eines Nockenwellenverstellers, allerdings sind separate Dichtelemente nachteiligerweise mit einem zusätzli- chen fertigungstechnischen Aufwand und Mehrkosten verbunden. Furthermore, from DE 199 805 80 T1 a vane rotor is known as part of a valve timing control device for an internal combustion engine. The blades of the rotor are provided with a retaining groove cut in the axial direction on the end face of the blade end. In this retaining groove, a separate sealing element can be fitted, which is in sliding contact with the inner peripheral surface of the stator. The sealing element is additionally held with a leaf spring in the retaining groove of the wing. Although all of the aforementioned embodiments for a rotor offer a possibility for reducing the leakage within a camshaft adjuster, however, separate sealing elements are disadvantageously associated with an additional manufacturing outlay and additional costs.
Aufgabe der Erfindung Es ist demnach eine erste Aufgabe der Erfindung, einen gegenüber dem Stand der Technik verbesserten Rotor anzugeben, der eine kostenneutralen und fertigungstechnisch einfach umsetzbare Möglichkeit zur Verringerung der Leckage in einem Nockenwellenversteller bietet. Eine zweite Aufgabe der Erfindung ist es, ein Nockenwellenversteller mit einem solchen Rotor anzugeben. OBJECT OF THE INVENTION It is therefore a first object of the invention to provide a rotor which is improved over the prior art and which offers a cost-neutral and production-technically easily implementable possibility for reducing the leakage in a camshaft adjuster. A second object of the invention is to provide a camshaft adjuster with such a rotor.
Lösung der Aufgabe Solution of the task
Die erste Aufgabe der Erfindung wird erfindungsgemäß gelöst durch einen Rotor für einen Nockenwellenversteller, mit einem Rotorgrundkörper sowie mit einer Anzahl von am Rotorgrundkörper angeordneter und sich radial nach außen erstreckender Rotorflügel, die jeweils ein Flügelende aufweisen. Hierbei ist vorgesehen, dass die Flügelenden der Rotorflügel zur Leckagereduzierung zu radial nach außen elastisch verformbaren Dichtstegen geformt sind. The first object of the invention is achieved by a rotor for a camshaft adjuster, with a rotor base body and with a number of arranged on the rotor body and radially outwardly extending rotor blades, each having a wing tip. It is provided that the wing ends of the rotor blades are formed to reduce leakage to radially outwardly elastically deformable sealing webs.
Die Erfindung geht von der Erkenntnis aus, dass die interne Leckage in einem Nockenwellenversteller durch zu breite Spalte zwischen den die Hydraulikbe- reiche begrenzenden Bauteilen hervorgerufen wird. Zur Minimierung dieser Leckage können die Spalte derart verringert werden, dass im Betrieb eines Nockenwellenverstellers eine ausreichende Abdichtung der Hydraulikbereiche voneinander gegeben ist. Dies lässt sich beispielsweise durch engere Spalt- maße erreichen. Allerdings ist hierbei eine hohe Maßgenauigkeit bei der Herstellung der Bauteile gefordert, um eine störungsfreie Funktion des Nockenwel- lenverstellers zu gewährleisten. Dies kann bis zum jetzigen Zeitpunkt nur mit sehr hohem Aufwand erreicht werden. The invention is based on the recognition that the internal leakage in a camshaft adjuster is caused by too wide a gap between the components delimiting the hydraulic regions. To minimize this leakage, the gaps can be reduced such that during operation of a camshaft adjuster sufficient sealing of the hydraulic areas is given from each other. This can be achieved, for example, by narrower slit reach dimensions. However, a high dimensional accuracy in the manufacture of the components is required in order to ensure a trouble-free function of the camshaft adjuster. This can only be achieved with great effort up to the present time.
Vor diesem Hintergrund werden daher separate Dichtelemente zur Abdichtung verwendet. Durch eine derartige Ausgestaltung sind die Anforderungen an die Maßgenauigkeit bei der Fertigung zwar geringer, jedoch ist auch hiermit ein erhöhter Kostenfaktor und eine aufwändigere Montage verbunden, da die Dichtelemente zum einen separat gefertigt und in zusätzlichen Prozessschritten montiert werden müssen. Zusätzlich kann beispielsweise auch eine Anpassung des Rotors bei der Verwendung eines separaten Dichtelementes notwendig sein. Die Erfindung löst diese Problematik überraschenderweise dadurch, dass sie auf die Verwendung eines separaten Dichtelements verzichtet. Dazu sind die Flügelenden der Rotorflügel als solche zur Leckagereduzierung zu radial nach außen elastisch verformbaren Dichtstegen geformt. Die Dichtstege sind Teil der Rotorflügel und erfüllen aufgrund ihrer Elastizität die erforderliche Dichtfunktion im Betrieb eines Nockenwellenverstellers, die bislang von separaten Dichtelementen übernommen wurde. Durch den Verzicht auf separate Dichtelemente können bislang notwendige Bearbeitungsschritte der Rotorflügel, wie zum Beispiel ein Einbringen von Nuten zur Positionierung der Dichtelemente entfallen. Die Dichtwirkung der Rotorflügel beruht insbesondere auf den im Betrieb der Brennkraftmaschine bzw. des Nockenwellenverstellers wirkenden Zentrifugalkräften, die in einem rotierenden System auf einen Körper wirken. Die Zentrifugalkraft ist von der Drehachse weg radial nach außen gerichtet und abhängig von der Masse des Körpers und dessen Abstand von der Drehachse. Against this background, therefore, separate sealing elements are used for sealing. By such a configuration, the requirements for dimensional accuracy in the production are indeed lower, but also an increased cost factor and a more complex assembly is connected because the sealing elements must be made separately for a separately and mounted in additional process steps. In addition, for example, an adjustment of the rotor when using a separate sealing element may be necessary. The invention surprisingly solves this problem by omitting the use of a separate sealing element. For this purpose, the wing ends of the rotor blades are formed as such for leakage reduction to radially outwardly elastically deformable sealing webs. The sealing webs are part of the rotor blades and fulfill due to their elasticity the required sealing function in the operation of a camshaft adjuster, which was previously taken over by separate sealing elements. By dispensing with separate sealing elements previously necessary processing steps of the rotor blades, such as an introduction of grooves for positioning the sealing elements omitted. The sealing effect of the rotor blades is based, in particular, on the centrifugal forces acting during operation of the internal combustion engine or of the camshaft adjuster, which act on a body in a rotating system. The centrifugal force is directed radially outward from the axis of rotation and depends on the mass of the body and its distance from the axis of rotation.
Infolge der Rotation des Rotors im eingebauten Zustand wirkt eine radial nach außen gerichtete Kraft auf die Flügelenden und insbesondere auf die Dichtstege. Die elastisch verformbaren Dichtstege werden radial nach außen gegen die Innenwandung des Stators gedrückt, wodurch sich die radialen Leckspalten zwischen den Flügelenden und der inneren Mantelfläche des Stators verringern. Auf diese Weise kann eine sichere Abdichtung zwischen den Hydraulikbereichen innerhalb des Nockenwellenverstellers erreicht werden kann. As a result of the rotation of the rotor in the installed state acts a radially outward force on the wing tips and in particular on the sealing webs. The elastically deformable sealing webs are radially outwardly against the Inner wall of the stator pressed, thereby reducing the radial leakage gaps between the blade ends and the inner circumferential surface of the stator. In this way, a secure seal between the hydraulic areas within the camshaft adjuster can be achieved.
Mit anderen Worten übernehmen die Flügelenden bzw. die Dichtstege aufgrund ihrer elastischen Ausgestaltung die Dichtfunktion innerhalb des Nockenwellenverstellers, so dass auf die Verwendung separater Dichtkomponenten gänzlich verzichtet werden kann. In other words, assume the wing ends or the sealing webs due to their elastic configuration, the sealing function within the camshaft adjuster, so that can be completely dispensed with the use of separate sealing components.
Der Rotor kann beispielsweise mit einem im Wesentlichen kreisförmigen Grundkörper ausgebildet sein. Die Anzahl der am Grundkörper angeordneten Rotorflügel kann in Abhängigkeit des einzustellenden Verstellwinkels variabel sein. Grundsätzlich gilt hierbei, dass, je mehr Rotorflügel an dem Rotorgrund- körper angeordnet sind, desto geringer ist der einstellbare Verstell Winkel. Die Rotorflügel können an dem Rotorgrundkörper als separate Komponenten angebracht sein oder bevorzugt einteilig mit diesem gefertigt sein. The rotor may be formed, for example, with a substantially circular base body. The number of blades arranged on the main body can be variable depending on the adjustment angle to be set. Basically, the more rotor blades are arranged on the rotor body, the lower the adjustable adjustment angle. The rotor blades may be attached to the rotor base body as separate components or preferably be made in one piece with this.
Die Rotorflügel erstrecken sich in radialer Richtung, so dass sie im eingebauten Zustand mit ihren Flügelenden am Innenumfang bzw. an der inneren Mantelfläche eines Stators anliegen. Die Flügelenden erstrecken sich in Umfangsrich- tung vorzugsweise mit einem dem Innenradius des Stators entsprechenden äußeren Radius, um im Betrieb beispielsweise ein Verkanten der Flügelenden an der inneren Mantelfläche des Stators zu vermeiden. Die Funktionalität ist aufgrund der elastischen Verformbarkeit der Flügelenden gewährleistet. Weiterhin kann einer der Rotorflügel mit einer Verriegelungsbohrung ausgebildet sein, die im eingebauten Zustand zur Verriegelung mit einem Stator dient, so dass Stator und Rotor in einer optimalen Position insbesondere für den Start oder Leerlauf einer Brennkraftmaschine gehalten werden können. The rotor blades extend in the radial direction, so that they lie in the installed state with their wing tips on the inner circumference or on the inner circumferential surface of a stator. The wing ends extend in the circumferential direction, preferably with an outer radius corresponding to the inner radius of the stator, in order, for example, during operation to prevent tilting of the wing ends on the inner circumferential surface of the stator. The functionality is ensured due to the elastic deformability of the wing tips. Furthermore, one of the rotor blades may be formed with a locking bore, which serves in the installed state for locking with a stator, so that the stator and rotor can be kept in an optimal position, in particular for the start or idle of an internal combustion engine.
Die Dichtstege können grundsätzlich verschieden ausgestaltet sein. Die Materialstärke der Dichtstege ist hierbei insbesondere abhängig von der gesamten Bauteilbeschaffenheit des Rotors bzw. der Rotorflügel. Die Bemaßungen der Dichtstege sowie das Material wirken sich auf die elastische Verformbarkeit der Dichtstege auf. Das Material kann insbesondere den im Betrieb wirkenden Kräften entsprechend gewählt werden, so dass eine Einstellung der resultierenden radialen Leckspalten zwischen den Flügelenden und der inneren Mantelfläche eines Stators sowohl im Stillstand als auch im Betrieb möglich ist. Die Stege sind insbesondere durch eine gezielte Materialschwächung am Flügelende ausgebildet. The sealing webs can basically be designed differently. The material thickness of the sealing webs is in this case particularly dependent on the overall component nature of the rotor or the rotor blades. The dimensions of the Sealing webs and the material affect the elastic deformability of the sealing webs. In particular, the material can be selected correspondingly to the forces acting during operation, so that an adjustment of the resulting radial leakage gaps between the wing tips and the inner circumferential surface of a stator is possible both at standstill and during operation. The webs are formed in particular by a targeted material weakening at the wing tip.
In einer vorteilhaften Ausgestaltung der Erfindung sind in den Flügelenden zur Ausbildung der Dichtstege Materialaussparungen eingebracht. Die Materialaussparungen sind hierbei vorzugsweise in radialer Richtung von den Dichtstegen begrenzt. Durch die Materialaussparungen wird eine Schwächung der Flügelenden hervorgerufen und die elastische Verformbarkeit der Dichtstege erreicht. Die Materialaussparungen können beispielsweise als Hohlräume, als Ausnehmungen oder als Vertiefungen in die Rotorflügel eingebracht sein. Sie sind vorzugsweise bereits während der unmittelbaren Herstellung des Rotors, zum Beispiel bei einem Sinter- oder Gußteil durch die Verwendung einer entsprechenden Form, in die Rotorflügel eingebracht, so dass keine nachträglichen Bearbeitungsschritte notwendig sind. Weiterhin können die elastischen Dichtstege durch eine Abstimmung der Materialaussparungen mit der Materialstärke dauerfest ausgelegt werden, so dass sie grundsätzlich den auf sie wirkenden Kräften beständig standhalten können. In an advantageous embodiment of the invention material recesses are introduced in the wing tips to form the sealing webs. The material recesses are in this case preferably limited in the radial direction of the sealing webs. By the material recesses a weakening of the wing tips is caused and achieved the elastic deformability of the sealing webs. The material recesses can be introduced, for example, as cavities, as recesses or depressions in the rotor blades. They are preferably already introduced into the rotor blades during the immediate production of the rotor, for example in the case of a sintered or cast part by the use of a corresponding shape, so that no subsequent processing steps are necessary. Furthermore, the elastic sealing webs can be designed durable by a vote of the material recesses with the material thickness, so that they can always withstand the forces acting on them resistant.
Bevorzugt sind die Materialaussparungen an den Flügelenden entlang der Um- fangsrichtung mit einer gleichbleibenden radialen Breite ausgebildet. Im Betrieb tritt so über den Umfang verteilt eine gleichmäßige Dichtwirkung ein. Hierbei wird in der Mitte des Steges die höchste Dichtwirkung erreicht, da die elastische Verformung an dieser Stelle am stärksten ausgeprägt ist. Durch die Befestigung der Dichtstege an den Rändern der Rotorflügel ist die nötige Stabilität der Flügelenden gewährleistet. Preferably, the material recesses are formed at the wing ends along the circumferential direction with a constant radial width. During operation, a uniform sealing effect occurs over the circumference. Here, the highest sealing effect is achieved in the middle of the web, since the elastic deformation is most pronounced at this point. By attaching the sealing webs at the edges of the rotor blades, the necessary stability of the wing tips is ensured.
In einer weiter vorteilhaften Ausgestaltung sind die Materialaussparungen an den Flügelenden entlang der Umfangsrichtung mit einer veränderlichen radia- len Breite ausgebildet. Daraus resultiert eine sich entlang der Umfangsrichtung ändernde Materialstärke, wodurch die elastische Verformbarkeit gezielt den Anforderungen angepasst werden kann. Insbesondere wird hierdurch für die Dichtstege ein lokaler Verform- oder Biegebereich geschaffen. In a further advantageous embodiment, the material recesses at the wing ends along the circumferential direction with a variable radia- len width trained. This results in a varying material thickness along the circumferential direction, whereby the elastic deformability can be specifically adapted to the requirements. In particular, this creates a local deformation or bending area for the sealing webs.
Vorzugsweise sind die die Materialaussparungen an den Flügelenden begrenzenden Dichtstege mit einem freibeweglichen Stegende ausgebildet sind. Da der Steg nur an einer Seite fest mit dem Flügelende verbunden ist, kann hierbei das freibewegliche Ende im Betrieb besonders einfach elastisch verformt wer- den. Auch diese Ausgestaltung ermöglicht eine Einflussnahme auf die Breite der radialen Leckspalte entlang der Umfangsrichtung. Preferably, the material recesses defining at the wing ends sealing webs are formed with a freely movable web end. Since the web is firmly connected to the wing end only on one side, in this case the freely movable end can be elastically deformed particularly easily during operation. This embodiment also makes it possible to influence the width of the radial leakage gaps along the circumferential direction.
Grundsätzlich sind zusätzlich weitere Möglichkeiten zur Ausgestaltung der Flügelenden bzw. der Dichtstege eines Rotors denkbar. Die Materialaussparungen und die Materialdicke können im Hinblick auf die im Betrieb wirkenden Zentrifugalkräfte aufeinander abgestimmt werden, um so eine störungsfreie Funktion des Nockenwellenverstellers zu gewährleisten. In principle, additional possibilities for the design of the wing tips or the sealing webs of a rotor are also conceivable. The material recesses and the material thickness can be matched to each other in view of the centrifugal forces acting during operation, so as to ensure a trouble-free function of the camshaft adjuster.
Zweckmäßigerweise ist der Rotorgrundkörper mit den Rotorflügeln einstückig mit einem pulvermetallurgischen Verfahren hergestellt. Die einstückige Fertigung ist besonders von Vorteil, da eine Vereinfachung des Herstellungsprozesses erreicht werden kann. Die Erfindung ermöglicht es, Rotorgrundkörper und Rotorflügel als ein Bauteil in einem gemeinsamen Prozess unter Schaffung der Dichtefunktionalität herzustellen. Ein Zusammenbau von Einzelteilen entfällt. Im Gegensatz zu einer mehrteiligen Fertigung werden zusätzlich mögliche Undichtigkeiten an der Kontaktstelle des Rotorgrundköpers mit den Rotorflügeln vermieden. Conveniently, the rotor body is made with the rotor blades in one piece with a powder metallurgy process. The one-piece production is particularly advantageous because a simplification of the manufacturing process can be achieved. The invention makes it possible to manufacture rotor body and rotor blades as a component in a common process to provide the density functionality. An assembly of individual parts is eliminated. In contrast to a multi-part manufacturing additional possible leaks are avoided at the contact point of Rotorgrundköpers with the rotor blades.
Als pulvermetallurgisches Verfahren ist insbesondere ein Sinterverfahren be- vorzugt. Mit einem Sinterverfahren lässt sich eine hohe Präzision erreichen, die für die Einstellung der radialen Leckspalte von Vorteil ist. Da gesinterte Bauteile eine hohe Maßgenauigkeit aufweisen, können zusätzliche aufwändige Nachbearbeitungsschritte des Rotors entfallen. Ein Sinterprozess bietet zusätzlich die Möglichkeit der Nutzung eines automatisierten Prozessablaufs, wodurch erhöhte Prozesskosten und zusätzlicher Bearbeitungsaufwand vermieden werden. Weiterhin hat beispielsweise das Sintermaterial Einfluss auf die Festigkeit und das Gewicht des Rotors, wodurch wiederum die elastische Verformung der Dichtstege beeinflusst werden kann. Dementsprechend kann durch die Wahl des Sintermaterials auch Einfluss auf die verbleibende Breite der radialen Leckspalte im Betreib eines Nockenwellenverstellers genommen werden. As a powder metallurgical process, in particular a sintering process is preferred. With a sintering process can achieve a high precision, which is advantageous for the adjustment of the radial leakage gaps. Since sintered components have a high dimensional accuracy, additional elaborate post-processing steps of the rotor can be omitted. A sintering process additionally offers the Possibility of using an automated process flow, which avoids increased process costs and additional processing effort. Furthermore, for example, the sintered material has an influence on the strength and the weight of the rotor, which in turn can affect the elastic deformation of the sealing webs. Accordingly, the choice of sintering material can also influence the remaining width of the radial leakage gaps in the operation of a camshaft adjuster.
Bei der Auslegung der Dichtstege sind die im Betrieb wirkenden Kräfte zu be- rücksichtigen, um eine sichere Funktion des Nockenwellenverstellers zu gewährleisten. Hierbei können die Dichtstege eine Wandstärke haben, durch die die gewünschte Dichtwirkung bei einer ausreichend hohen Festigkeit gegeben ist. Die Wandstärke ist hierbei in Umfangsrichtung abhängig von der Form der in den Flügelenden ausgebildeten Materialaussparungen. Beispielsweise ist die Wandstärke bei einer hanteiförmigen Materialaussparung an den äußeren Enden der Dichtstege, im Bereich der größeren Aussparungen, geringer als in dem sich dazwischen befindlichen Bereich. When designing the sealing webs, the forces acting during operation must be taken into account in order to ensure safe operation of the camshaft adjuster. Here, the sealing webs may have a wall thickness, through which the desired sealing effect is given at a sufficiently high strength. The wall thickness in this case depends in the circumferential direction on the shape of the material recesses formed in the wing ends. For example, the wall thickness of a dumbbell-shaped material recess at the outer ends of the sealing webs, in the region of the larger recesses, less than in the intervening area.
Die zweite Aufgabe der Erfindung wird erfindungsgemäß gelöst durch einen Nockenwellenversteller für eine Brennkraftmaschine, umfassend einen Stator sowie einen innerhalb des Stators angeordneten, relativ zu diesem drehbaren Rotor entsprechend den vorgenannten Ausgestaltungen. Hierbei ist vorgesehen, dass die Dichtstege der sich radial nach außen erstreckenden Flügelenden gegenüber der inneren Mantelfläche des Stators abdichten. The second object of the invention is achieved by a camshaft adjuster for an internal combustion engine, comprising a stator and disposed within the stator, relative to this rotatable rotor according to the aforementioned embodiments. It is provided that the sealing webs of the radially outwardly extending wing ends seal against the inner circumferential surface of the stator.
Wie vorhergehend bereits erläutert, beruht die Dichtwirkung der Dichtstege auf den im Betrieb des Nockenwellenverstellers wirkenden Zentrifugalkräften. Die Dichtstege werden hierbei radial elastisch verformt und gegen die innere Mantelfläche des Stators gedrückt. Hierdurch kommt eine Reduzierung der radialen Leckspalte zwischen den Rotorflügeln und der Innenwand des Stators zustande. Die hierdurch erreichte Dichtwirkung ermöglicht den Betrieb eines Nockenwellenverstellers ohne ein zusätzliches Dichtelement. Der Stator weist üblicherweise eine Anzahl sich radial nach innen erstreckender Stege auf, zwischen denen Druckkammern gebildet sind. In den Druckkammern können die sich radial nach außen erstreckenden Flügel des Rotors positioniert werden, so dass jeweils an den Außenseiten der Flügel die Hydraulikbe- reiche zur Beaufschlagung mit Hydraulikflüssigkeit entstehen. Zur Beaufschlagung weist der Rotor insbesondere Ölkanäle in seinem Grundkörper auf, durch die Öl in die Druckkammern des Stators bzw. des Nockenwellenverstellers gepumpt werden können. An den Stegen des Stators können Flügelanschlagsflächen ausgebildet sein, an denen im eingebauten Zustand die Flügel eines Ro- tors anschlagen können. As previously explained, the sealing effect of the sealing webs is based on the centrifugal forces acting during operation of the camshaft adjuster. The sealing webs are radially elastically deformed and pressed against the inner circumferential surface of the stator. This results in a reduction of the radial leakage gaps between the rotor blades and the inner wall of the stator. The sealing effect achieved thereby allows the operation of a camshaft adjuster without an additional sealing element. The stator usually has a number of radially inwardly extending webs, between which pressure chambers are formed. The radially outwardly extending vanes of the rotor can be positioned in the pressure chambers, so that the hydraulic regions for acting on hydraulic fluid are formed on the outer sides of the vanes. To act on the rotor in particular oil passages in its base body, can be pumped through the oil in the pressure chambers of the stator or the camshaft adjuster. On the webs of the stator wing stop surfaces can be formed, which can strike the wings of a rotor in the installed state.
Der Nockenwellenversteller ist neben dem Stator und dem Rotor üblicherweise noch mit einem Dichtdeckel sowie mit einem Verriegelungsdeckel ausgebildet. Der Verriegelungsdeckel ist vorzugsweise mit dem Stator verbunden und be- grenzt die Druckkammern nockenwellenseitig. Er dient der Abdichtung des Druckraums nach außen, verhindert ein unkontrolliertes Auslaufen von Hydraulikflüssigkeit und verringert somit eine externe Leckage. In dem Verriegelungsdeckel ist üblicherweise eine Kulisse ausgebildet, die der Verriegelung von Stator und Rotor in einer vorgesehenen Position dient. The camshaft adjuster is usually formed next to the stator and the rotor still with a sealing cover and with a locking cover. The locking cover is preferably connected to the stator and limits the pressure chambers on the camshaft side. It serves to seal the pressure chamber to the outside, prevents uncontrolled leakage of hydraulic fluid and thus reduces external leakage. In the locking cover usually a gate is formed, which serves to lock the stator and rotor in a designated position.
Im Betrieb verringern sich die Spaltmaße in Abhängigkeit der auf den Rotor bzw. auf die Flügelenden wirkenden Zentrifugalkräfte. Die Abmessungen bzw. die Breite der radialen Leckspalte ist hierbei beispielsweise abhängig von der Bauteildicke des Rotors und von der Wandstärke der Dichtstege. Diese und die Materialaussparungen können aufeinander abgestimmt werden, so dass eine dauerfeste Auslegung der elastischen bzw. elastisch verformbaren Dichtstege möglich ist. During operation, the gap dimensions decrease as a function of the centrifugal forces acting on the rotor or on the wing ends. The dimensions or the width of the radial leakage gaps here depend, for example, on the component thickness of the rotor and on the wall thickness of the sealing webs. These and the material recesses can be matched to each other, so that a durable design of the elastic or elastically deformable sealing webs is possible.
Weitere vorteilhafte Ausgestaltungen finden sich in den auf den Rotor gerichte- ten Unteransprüchen, die sinngemäß auf den Nockenwellenversteller übertragen werden können. Kurze Beschreibung der Zeichnung Further advantageous embodiments can be found in the dependent claims on the rotor, which can be transferred to the camshaft adjuster analogously. Short description of the drawing
Im Folgenden werden Ausführungsbeispiele der Erfindung in einer Zeichnung näher erläutert. Dabei zeigen die Fig. 1 bis 3 jeweils einen Rotor mit unter- schiedlich ausgebildeten Rotorflügeln in einem Querschnitt und Fig. 4 einen Nockenwellenversteller mit einem Rotor gemäß Fig. 1 im eingebauten Zustand in einem Querschnitt. In the following, embodiments of the invention will be explained in more detail in a drawing. 1 to 3 each show a rotor with differently shaped rotor blades in a cross section and FIG. 4 shows a camshaft adjuster with a rotor according to FIG. 1 in the installed state in a cross section.
Ausführliche Beschreibung der Zeichnung Detailed description of the drawing
Fig. 1 zeigt einen Rotor 1 für einen Nockenwellenversteller in einem Querschnitt. Der Rotor 1 hat einen Rotorgrundkörper 3 mit vier sich radial nach außen erstreckenden Rotorflügeln 5. Im eingebauten Zustand, wenn der Rotor 1 in einem Stator positioniert ist, dienen die Rotorflügel 5 der Unterteilung jeweils einer Druckkammer eines Nockenwellenverstellers in zwei benachbarte Hydraulikbereiche. Ein Nockenwellenversteller ist in Fig. 4 gezeigt. Fig. 1 shows a rotor 1 for a camshaft adjuster in a cross section. The rotor 1 has a rotor base body 3 with four radially outwardly extending rotor blades 5. In the installed state, when the rotor 1 is positioned in a stator, the rotor blades 5 serve to divide a respective pressure chamber of a camshaft adjuster into two adjacent hydraulic areas. A phaser is shown in FIG.
Der Rotorgrundkörper 3 und die Rotorflügel 5 sind einteilig durch ein Sinterver- fahren aus einem metallischen Werkstoff hergestellt. Im Unterschied zu einer zweiteiligen Fertigung, bei welcher die Rotorflügel 5 beispielsweise in Nuten im Rotorgrundkörper 3 gehalten werden, werden durch die Einteiligkeit mögliche Stellen für Undichtigkeiten minimiert. Weiterhin bietet der Sinterprozess die Möglichkeit der Nutzung eines automatisierten Prozessablaufs und ist somit kostengünstig und einfach durchzuführen. Aufgrund der Maßgenauigkeit des Verfahrens kann der Rotor 1 so hergestellt werden, dass die radialen Leckspalten zwischen den Flügelenden und der inneren Mantelfläche eines Stators im eingebauten Zustand hinreichend gering sind. Die Rotorflügel 5 weisen Flügelenden 7 auf, die zur Leckagereduzierung in einem Nockenwellenversteller ausgebildet sind. Hierzu sind die Flügelenden 7 zu radial nach außen elastisch verformbaren Dichtstegen 9 geformt. Sie bestehen aus demselben Material wie die Rotorflügel 5 und sind während des Sinterprozesses als Teil der Rotorflügel 5 bzw. als Teil des Rotors 1 hergestellt. The rotor base body 3 and the rotor blades 5 are made in one piece by a sintering process of a metallic material. In contrast to a two-part production, in which the rotor blades 5 are held, for example, in grooves in the rotor base 3, possible locations for leaks are minimized by the one-piece. Furthermore, the sintering process offers the possibility of using an automated process flow and is therefore inexpensive and easy to carry out. Due to the dimensional accuracy of the method, the rotor 1 can be made so that the radial leakage gaps between the wing tips and the inner circumferential surface of a stator when installed are sufficiently low. The rotor blades 5 have wing tips 7, which are designed to reduce the leakage in a camshaft adjuster. For this purpose, the wing tips 7 are formed to radially outwardly elastically deformable sealing webs 9. They persist made of the same material as the rotor blades 5 and are produced during the sintering process as part of the rotor blades 5 or as part of the rotor 1.
Die elastische Verformbarkeit der Dichtstege 9 wird durch die in den Flügelen- den 7 eingebrachten Materialaussparungen 1 1 hervorgerufen. Die Materialaussparungen 11 sind in radialer Richtung von den Dichtstegen 9 begrenzt und verlaufen in Umfangsrichtung mit einem gleichbleibenden radialen Spaltmaß. Hierdurch tritt im Betrieb über den Umfang verteilt eine gleichmäßige Dichtwirkung ein. In der Mitte der Dichtstege 9 wird hierbei die höchste Dichtwirkung erreicht, da an dieser Stelle die elastische Verformung der Flügelenden 7 am stärksten ausgeprägt ist. Die Materialaussparungen 1 1 sind durch das Herstellungsverfahren des Rotors 1 bereits unmittelbar in die Rotorflügel 5 eingebracht. Insgesamt kann eine Verringerung der internen Leckage ohne die Verwendung separater Dichtelemente erreicht werden. The elastic deformability of the sealing webs 9 is caused by the material recesses 1 1 introduced into the wings 7. The material recesses 11 are limited in the radial direction of the sealing webs 9 and extend in the circumferential direction with a constant radial gap. As a result, a uniform sealing effect occurs over the circumference during operation. In the middle of the sealing webs 9 in this case the highest sealing effect is achieved, since at this point the elastic deformation of the blade ends 7 is most pronounced. The material recesses 1 1 are already introduced by the manufacturing process of the rotor 1 directly into the rotor blades 5. Overall, a reduction in internal leakage can be achieved without the use of separate sealing elements.
Zusätzlich ist in einem Rotorflügel 5 eine Verriegelungsbohrung 13 zur Verriegelung mit einem Stator im eingebauten Zustand umfasst. Hierzu kann bei- spielsweise ein Kolben durch die Verriegelungsbohrung 13 in eine Kulisse im Grund eines Verriegelungsdeckels eingreifen, so dass der Rotor 1 und ein Stator in einer optimalen Position insbesondere für den Start oder Leerlauf einer Brennkraftmaschine gehalten werden können. Die Kulisse zur Verriegelung ist in Fig. 4 zu sehen. In addition, in a rotor blade 5, a locking bore 13 is included for locking with a stator in the installed state. For this purpose, for example, a piston can engage through the locking bore 13 into a slot in the base of a locking cover, so that the rotor 1 and a stator can be held in an optimum position, in particular for starting or idling an internal combustion engine. The scenery for locking can be seen in Fig. 4.
Auch in Fig. 2 ist ein Rotor 21 für einen Nockenwellenversteller in einem Querschnitt zu sehen. Der Rotor 21 hat ebenfalls einen Rotorgrundkörper 23 mit vier sich radial nach außen erstreckenden Rotorflügeln 25, die im eingebauten Zustand die Druckkammern eines Nockenwelienverstellers in Hydraulikbereiche unterteilen. Der Rotor 21 ist ebenfalls einstückig mittels eines Sinterprozesses aus einem metallischen Werkstoff hergestellt. In die Flügelenden 27 sind ebenfalls Materialaussparungen 29 eingebracht, die radial nach außen von Dichtstegen 31 begrenzt werden. Die Materialaussparungen 29 sind mit einem in Umfangsrichtung verlaufenden veränderlichen radialen Spaltmaß in Form einer Hantel ausgebildet. Dementsprechend haben die Dichtstege 31 eine sich entlang der Umfangsrichtung veränderte Wandstärke. Deren Bezeichnung 33, 35 ist der Übersichtlichkeit halber nur an einer Ma- terialausnehmung 29 gezeigt. An den kreisförmigen Aussparungen 33 ist gezielt eine Verformstelle zur elastischen Bewegung des Dichtstegs 31 nach außen geschaffen. Also in Fig. 2, a rotor 21 for a phaser can be seen in a cross section. The rotor 21 also has a rotor base body 23 with four radially outwardly extending rotor blades 25 which divide the pressure chambers of a camshaft adjuster into hydraulic areas when installed. The rotor 21 is also made in one piece by means of a sintering process of a metallic material. In the wing ends 27 material recesses 29 are also introduced, which are bounded radially outwardly by sealing webs 31. The material recesses 29 are formed with a circumferentially extending variable radial gap in the form of a dumbbell. Accordingly, the sealing webs 31 have a wall thickness changed along the circumferential direction. Their designation 33, 35 is shown only on a material recess 29 for the sake of clarity. At the circular recesses 33 a deformation point for the elastic movement of the sealing web 31 is created specifically to the outside.
Entsprechend Fig. 1 ist auch von einem Rotorflügel 25 des Rotors 21 eine Verriegelungsbohrung 37 zur Verriegelung mit einem Stator im eingebauten Zustand umfasst. Der in Fig. 3 ebenfalls in einem Querschnitt gezeigte Rotor 41 mit einem Rotorgrundkörper 43 und vier an diesem angeordneten Rotorflügeln 45 ist entsprechend den Fig. 1 und 2 einteilig durch Sintern hergestellt. Die sich radial nach außen erstreckenden Rotorflügel 45 weisen an den Flügelenden 47 Dichtstege 49 auf. According to FIG. 1, a locking bore 37 for locking with a stator in the installed state is also encompassed by a rotor blade 25 of the rotor 21. The rotor 41 likewise shown in a cross-section in FIG. 3 with a rotor main body 43 and four rotor blades 45 arranged thereon is produced in one piece according to FIGS. 1 and 2 by sintering. The radially outwardly extending rotor vanes 45 have at the wing ends 47 sealing webs 49.
Diese Dichtstege 49 begrenzen die in die Flügelenden 47 eingebrachten Materialaussparungen 51 in radialer Richtung. Die Materialaussparungen 51 sind in Umfangsrichtung mit einem veränderlichen radialen Spaltmaß ausgebildet und zu einer der Flügelanschlagsflächen 71 , 73 hin geöffnet. Die Flügelenden 47 sind durch die Materialaussparungen 51 einseitig zu angelenkten Dichtstegen 49 geschwächt. Das jeweils freie Stegende 53 der Dichtstege 49 wird durch die im Betrieb auf den Rotor 41 wirkende Zentrifugalkraft radial nach außen gedrückt. Die Wandstärke an der Stelle der kreisförmigen Aussparung 57 ist gegenüber der Stelle der sich anschließenden stegförmigen Aussparung 57 erhöht. Deren Bezeichnung 55, 57 ist wie in Fig. 2 der Übersichtlichkeit halber nur an einer Materialausnehmung 51 gezeigt. Auch in Fig. 3 ist in einem Rotorflügel 45 des Rotors 41 eine Verriegelungsbohrung 59 eingebracht, die im eingebauten Zustand der Verriegelung von Rotor und Stator in einer gewünschten Position dient. These sealing webs 49 limit the material recesses 51 introduced into the wing ends 47 in the radial direction. The material recesses 51 are formed in the circumferential direction with a variable radial gap and opened to one of the wing stop surfaces 71, 73 out. The wing ends 47 are weakened by the material recesses 51 on one side to be hinged sealing webs 49. The respective free web end 53 of the sealing webs 49 is pressed radially outward by the centrifugal force acting on the rotor 41 during operation. The wall thickness at the location of the circular recess 57 is increased relative to the location of the adjoining web-shaped recess 57. Their name 55, 57 is shown in Fig. 2 for the sake of clarity only on a material recess 51. Also in Fig. 3, a locking hole 59 is inserted in a rotor blade 45 of the rotor 41, which serves in the installed state, the locking of the rotor and stator in a desired position.
Fig. 4 zeigt einen Nockenwellenversteller 61 mit einem in einem Stator 63 eingesetzten Rotor 1 gemäß Fig. 1 in einer Draufsicht. Der Rotor 1 hat einen Rotorgrundkörper 3 mit vier sich radial nach außen erstreckenden Rotorflügeln 5. Rotorgrundkörper 3 und Rotorflügeln 5 sind einteilig durch Sintern aus einem metallischen Werkstoff hergestellt. Zur Beschreibung des Rotors 1 wird an dieser Stelle auf Fig. 1 verwiesen. FIG. 4 shows a camshaft adjuster 61 with a rotor 1 inserted in a stator 63 according to FIG. 1 in a plan view. The rotor 1 has a rotor main body 3 with four rotor blades 5 extending radially outwards. Rotor main bodies 3 and rotor blades 5 are produced in one piece by sintering from a metallic material. For the description of the rotor 1, reference is made to FIG. 1 at this point.
Der Stator 63 weist sich radial nach innen erstreckende Stege 65 auf, zwischen denen jeweils ein Rotorflügel 5 des Rotors 1 positioniert ist. Die Rotorflügel 5 unterteilen die im Stator 63 ausgebildeten Druckkammern 67 in jeweils zwei Hydraulikbereiche 69, die sich jeweils rechts bzw. links von den Rotorflügeln 5 befinden. Dies ist in Fig. 4 aufgrund der Übersichtlichkeit nur für eine Druckkammer 67 bzw. zwei Hydraulikbereiche 69 kenntlich gemacht. An zwei Stegen 65 ist jeweils eine Flügelanschlagsfläche 71 , 73 ausgebildet, die die Rotorflügel 5 in einer bestimmten Position durch einen Anschlag stoppen. Beide Flügelanschlagsflächen 71 , 73 befinden sich innerhalb einer Druckkammer 67 bzw. jeweils in einem Hydraulikbereich 69, so dass der Rotorflügel 5 an beiden Seiten der Druckkammer 67 anschlagen kann. The stator 63 has radially inwardly extending webs 65, between each of which a rotor blade 5 of the rotor 1 is positioned. The rotor blades 5 divide the pressure chambers 67 formed in the stator 63 into two hydraulic areas 69, which are located on the right or left of the rotor blades 5, respectively. Due to the clarity, this is indicated in FIG. 4 only for one pressure chamber 67 or two hydraulic regions 69. At two webs 65 each have a wing stop surface 71, 73 is formed, which stop the rotor blades 5 in a certain position by a stop. Both wing stop surfaces 71, 73 are located within a pressure chamber 67 or respectively in a hydraulic region 69, so that the rotor blade 5 can abut the pressure chamber 67 on both sides.
Fig. 4 zeigt den Nockenwellenversteller 61 im Stillstand, wobei die sich radial nach außen erstreckenden Flügelenden 7 der Rotorflügel 5, bzw. die Dichtstege 9 mit ihrem Außenumfang nicht direkt am Innenumfang des Stators 63 anliegen. Deutlich zu erkennen sind dementsprechend die radialen Leckspalten 75, die zwischen der inneren Mantelfläche 77 des Stators 63 und den Flügelenden ausgebildet ist. Im Betrieb, also bei der Rotation des Rotors 1 innerhalb des Stators 63, verringern sich die Leckspalten 75 unter Erhöhung der Dichtigkeit zwischen den Hydraulikbereichen 69. Die Dichtstege 9 werden radial in Richtung der inneren Mantelfläche 77 des Stators 63 verformt, so dass sich die radialen Spaltmaße zwischen Rotor 1 und Stator 63 verkleinern. Hierdurch wird die Leckage reduziert und eine Abdichtung der Hydraulikbereiche 69 voneinander kann ohne die Verwendung separater Dichtelemente erreicht werden. Fig. 4 shows the camshaft adjuster 61 at a standstill, wherein the radially outwardly extending wing ends 7 of the rotor blades 5, and the sealing webs 9 with its outer periphery do not rest directly on the inner circumference of the stator 63. The radial leakage gaps 75, which are formed between the inner circumferential surface 77 of the stator 63 and the blade ends, can therefore be clearly seen. During operation, ie during the rotation of the rotor 1 within the stator 63, the leakage gaps 75 decrease while increasing the tightness between the hydraulic regions 69. The sealing webs 9 are deformed radially in the direction of the inner lateral surface 77 of the stator 63, so that the radial Reduce the gap between rotor 1 and stator 63. As a result, the leakage is reduced and a sealing of the hydraulic regions 69 from each other can be achieved without the use of separate sealing elements.
Weiterhin weist der Rotor 1 Ölkanäle zum Beaufschlagen der Druckkammern 67 mit Öl auf, wobei diese Kanäle nicht zu erkennen sind, da sie sich im Inneren des Körpers des Rotors 1 befinden. Furthermore, the rotor 1 has oil passages for pressurizing the pressure chambers 67 with oil, wherein these passages can not be recognized, since they are located inside the body of the rotor 1.
In einem Rotorflügel 5 ist eine Verriegelungsbohrung 13 eingebracht, durch die ein nicht gezeigter Kolben in die im Verriegelungsdeckel 79 eingebrachte Kulis- se 81 eingreifen kann. So kann der Rotor 1 in einer vorgesehenen Position gehalten werden. Im entriegelten Zustand ist der Kolben angehoben und der Rotor 1 kann sich in einem bestimmten Verstell Winkel bewegen. Der Verriegelungsdeckel 79 ist mit dem Stator 63 verbunden und begrenzt die Druckkammern 67 nockenwellenseitig. Auf diese Weise dient der Verriegelungsdeckel 79 zusätzlich der Verringerung der externen Leckage des Nockenwellenverstellers 61. In a rotor blade 5, a locking bore 13 is introduced, by means of which a piston (not shown) can engage in the crank 81 introduced into the locking cover 79. Thus, the rotor 1 can be held in a predetermined position. In the unlocked state, the piston is raised and the rotor 1 can move at a certain adjustment angle. The locking cover 79 is connected to the stator 63 and limits the pressure chambers 67 camshaft side. In this way, the locking lid 79 additionally serves to reduce the external leakage of the camshaft adjuster 61.
Liste der Bezugszahlen Rotor List of reference numbers rotor
3 Rotorgrundkörper  3 rotor body
5 Rotorflügel 5 rotor blades
7 Flügelende 7 wing ends
9 Dichtsteg 9 sealing bar
I Materialaussparung  I material recess
13 Verriegelungsbohrung 13 locking hole
21 Rotor 21 rotor
23 Rotorgrundkörper  23 rotor body
25 Rotorflügel  25 rotor blades
27 Flügelende  27 wing end
29 Materialaussparung  29 material recess
31 Dichtsteg  31 sealing bridge
33 Aussparung  33 recess
35 Aussparung  35 recess
37 Verriegelungsbohrung  37 locking hole
41 Rotor  41 rotor
43 Rotorgrundkörper  43 rotor body
45 Rotorflügel  45 rotor blades
47 Flügelende  47 wing end
49 Dichtsteg  49 sealing bar
51 Materialaussparung  51 material recess
53 Stegende  53 bridge end
55 Aussparung  55 recess
57 Aussparung  57 recess
59 Verriegelungsbohrung  59 locking hole
61 Nockenwellenversteller  61 Camshaft adjuster
63 Stator  63 stator
65 Stege  65 bridges
67 Druckkammern  67 pressure chambers
69 Hydraulikbereiche Flügelanschlagsfläche Flügelanschlagsfläche radiale Leckspalten innere Mantelfläche erriegelungsdeckel Kulisse 69 hydraulic areas Wing stop surface Wing stop surface Radial leakage gaps Inner lateral surface Locking cover Sliding link

Claims

Patentansprüche claims
1. Rotor (1 , 21 , 41) für einen Nockenwellenversteller (61), mit einem Rotorgrundkörper (3, 23, 43) sowie mit einer Anzahl von am Rotorgrund körper (3, 23, 43) angeordneter und sich radial nach außen erstreckender Rotorflügel (5, 25, 45), die jeweils ein Flügelende (7, 27, 47) aufweisen, dadurch gekennzeichnet, dass die Flügelenden (7, 27, 47) der Rotorflügel (5, 25, 45) zur Leckagereduzierung zu radial nach außen elastisch verformbaren Dichtstegen (9, 31 , 49) geformt sind. 1. rotor (1, 21, 41) for a camshaft adjuster (61), with a rotor base body (3, 23, 43) and with a number of rotor base body (3, 23, 43) arranged and extending radially outwardly extending rotor blades (5, 25, 45), each having a wing end (7, 27, 47), characterized in that the wing ends (7, 27, 47) of the rotor vanes (5, 25, 45) for leakage reduction to radially outwardly elastic deformable sealing webs (9, 31, 49) are formed.
2. Rotor (1 , 21 , 41) nach Anspruch 1 , dadurch gekennzeichnet, dass in die2. rotor (1, 21, 41) according to claim 1, characterized in that in the
Flügelenden (7, 27, 47) zur Ausbildung der Dichtstege (9, 31 , 49) Materialaussparungen (11 , 29, 51 ) eingebracht sind. Wings ends (7, 27, 47) for forming the sealing webs (9, 31, 49) material recesses (11, 29, 51) are introduced.
3. Rotor (1 , 21 , 41) nach Anspruch 2, dadurch gekennzeichnet, dass die Materialaussparungen (11 , 29, 51 ) an den Flügelenden (7, 27, 47) in radialer Richtung von den Dichtstegen (9, 31 , 49) begrenzt sind. 3. rotor (1, 21, 41) according to claim 2, characterized in that the material recesses (11, 29, 51) on the wing ends (7, 27, 47) in the radial direction of the sealing webs (9, 31, 49) are limited.
4. Rotor (1 , 21 , 41 ) nach Anspruch 2 oder 3, dadurch gekennzeichnet, dass die Materialaussparungen (11 , 29, 51) an den Flügelenden (7, 27,4. rotor (1, 21, 41) according to claim 2 or 3, characterized in that the material recesses (11, 29, 51) at the wing ends (7, 27,
47) entlang der Umfangsrichtung mit einer gleichbleibenden radialen Breite ausgebildet sind. 47) along the circumferential direction are formed with a constant radial width.
5. Rotor (1 , 21 , 41 ) nach Anspruch 2 oder 3, dadurch gekennzeichnet, dass die Materialaussparungen (1 1 , 29, 51) an den Flügelenden (7, 27,5. rotor (1, 21, 41) according to claim 2 or 3, characterized in that the material recesses (1 1, 29, 51) at the wing ends (7, 27,
47) entlang der Umfangsrichtung mit einer veränderlichen radialen Breite ausgebildet sind. 47) are formed along the circumferential direction with a variable radial width.
6. Rotor (1 , 21 , 41) nach Anspruch 3, dadurch gekennzeichnet, dass die die Materialaussparungen (11 , 29, 51) an den Flügelenden (7, 27, 47) begrenzenden Dichtstege (9, 31 , 49) mit einem freibeweglichen Stegende (53) ausgebildet sind. Rotor (1 , 21 , 41) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Rotorgrundkörper (3, 23, 43) mit den Rotorflügeln (5, 25, 45) einstückig mit einem pulvermetallurgischen Verfahren hergestellt ist. 6. rotor (1, 21, 41) according to claim 3, characterized in that the material recesses (11, 29, 51) at the wing ends (7, 27, 47) delimiting sealing webs (9, 31, 49) with a freely movable Web end (53) are formed. Rotor (1, 21, 41) according to one of the preceding claims, characterized in that the rotor base body (3, 23, 43) with the rotor blades (5, 25, 45) is made in one piece with a powder metallurgy process.
Nockenwellenversteller (61) für eine Brennkraftmaschine, umfassend einen Stator (63) sowie einen innerhalb des Stators (63) angeordneten, relativ zu diesem drehbaren Rotor (1 , 21 , 41) nach einem der Ansprüche 1 bis 7, wobei die Dichtstege (9, 31 , 49) der sich radial nach außen erstreckenden Flügelenden (7, 27, 47) gegenüber der inneren Mantelfläche (77) des Stators (63) abdichten. Camshaft adjuster (61) for an internal combustion engine, comprising a stator (63) and a rotor (1, 21, 41), which is arranged inside the stator (63) and rotatable relative thereto, according to one of claims 1 to 7, wherein the sealing webs (9, 31, 49) of the radially outwardly extending wing ends (7, 27, 47) against the inner circumferential surface (77) of the stator (63) seal.
EP11722084.8A 2010-06-17 2011-05-31 Rotor for a camshaft phasing device and corresponding camshaft phasing device Not-in-force EP2582929B1 (en)

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DE102010024197A DE102010024197A1 (en) 2010-06-17 2010-06-17 Rotor for a camshaft phaser and camshaft adjuster
PCT/EP2011/058879 WO2011157542A1 (en) 2010-06-17 2011-05-31 Rotor for a camshaft adjuster and camshaft adjuster

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DE102012213176B4 (en) * 2012-07-26 2021-07-01 Schaeffler Technologies AG & Co. KG Hydraulic camshaft adjuster
DE102013209520A1 (en) * 2013-05-23 2014-12-11 Schaeffler Technologies Gmbh & Co. Kg Rotor for a vane positioner of a camshaft adjusting device
US10773308B2 (en) 2017-01-03 2020-09-15 Gkn Sinter Metals, Llc Rotor and method of manufacturing rotor with equalized surface areas for grinding

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WO1999049187A1 (en) 1998-03-25 1999-09-30 Unisia Jecs Corporation Valve timing control device of internal combustion engine
DE19834143B4 (en) * 1998-07-29 2014-03-20 Schaeffler Technologies AG & Co. KG Device for changing the timing of gas exchange valves of an internal combustion engine, in particular camshaft adjusting device with impeller
DE10356907A1 (en) * 2003-12-02 2005-07-07 Hydraulik-Ring Gmbh Cam shaft adjuster for internal combustion engines has stator and rotor with demolition edges to reduce leakage flow of hydraulic medium between end sides of vanes and mating surfaces
DE102005017436A1 (en) 2005-04-15 2006-10-19 Schaeffler Kg Device for adjusting the camshaft of an internal combustion engine
DE102006004718A1 (en) 2006-02-02 2007-08-23 Schaeffler Kg Camshaft adjuster in vane-type construction
DE102006022219B4 (en) * 2006-05-11 2008-01-03 Hydraulik-Ring Gmbh Leakage-proof camshaft adjuster with return spring
US7878164B2 (en) * 2006-12-13 2011-02-01 Delphi Technologies, Inc. Apparatus for preventing leakage across rotor vanes in a vane-type camshaft phaser

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DE102010024197A1 (en) 2011-12-22
US8635978B2 (en) 2014-01-28

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