EP1568855A2 - Camshaft phasing device for vehicle engine - Google Patents

Camshaft phasing device for vehicle engine Download PDF

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Publication number
EP1568855A2
EP1568855A2 EP05004274A EP05004274A EP1568855A2 EP 1568855 A2 EP1568855 A2 EP 1568855A2 EP 05004274 A EP05004274 A EP 05004274A EP 05004274 A EP05004274 A EP 05004274A EP 1568855 A2 EP1568855 A2 EP 1568855A2
Authority
EP
European Patent Office
Prior art keywords
rotor
stator
side surfaces
sections
rotor blades
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
EP05004274A
Other languages
German (de)
French (fr)
Other versions
EP1568855B1 (en
EP1568855A3 (en
Inventor
Andreas Knecht
Ralf Naumann
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.)
Hilite Germany GmbH
Original Assignee
Hydraulik Ring GmbH
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
Priority claimed from DE102005007942A external-priority patent/DE102005007942B4/en
Application filed by Hydraulik Ring GmbH filed Critical Hydraulik Ring GmbH
Publication of EP1568855A2 publication Critical patent/EP1568855A2/en
Publication of EP1568855A3 publication Critical patent/EP1568855A3/en
Application granted granted Critical
Publication of EP1568855B1 publication Critical patent/EP1568855B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01L1/3442—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
    • F01L2001/34423—Details relating to the hydraulic feeding circuit
    • F01L2001/34436—Features or method for avoiding malfunction due to foreign matters in oil

Definitions

  • the invention relates to a camshaft adjusting device for internal combustion engines of motor vehicles according to the preamble of claim 1.
  • Camshaft adjusting devices serve to open and close the time the gas exchange valves by a relative rotation of the camshaft to move against the crankshaft.
  • the rotor and stator blades lie with their end faces on the respective mating surfaces of the stator or Rotor.
  • hydraulic medium used, which act on the rotor blades from both sides so can be that the rotor is rotated in the desired direction relative to the stator becomes.
  • To reduce the leakage flow of the hydraulic medium between The adjacent surfaces must be the rotor or stator with their faces abut sealingly against the mating surfaces. For this reason the sealing surfaces are formed correspondingly long. This will but reduces the swing angle of the rotor blades.
  • camshaft adjusting devices (DE 101 56 055 C2, DE 102 46 173 A1, DE 102 23 523 A1, US 2003/0217720 A1, US Pat 6 758 177 B1, US 6 637 390 B1, EP 1 143 113 A2) have the rotor blades and thus the stator blades even side surfaces. So that the sealing surfaces At the end faces of the rotor blades are sufficiently long, have the rotor blades a correspondingly large width, but only a limited Swing angle of the rotor allows.
  • Nockenwellenverstellvorraumen in which the Side surfaces of the rotor blade projections are provided (DE 101 34 320 A1), with which the rotor blades in the end position on the side surfaces of the stator vanes issue. By these projections, the pivot angle of the rotor also affected.
  • camshaft adjusting devices are known (US Pat 2003/0056744 A1), in which the free ends of the rotor blades in width are formed tapered. Even with such training is only a limited Swing angle achievable.
  • the invention is based on the object, the generic camshaft adjusting in such a way that with structurally simple training and cost-effective production ensures optimum operation is.
  • the side surfaces of the Rotor blades are concavely curved over part of their length, so that the Rotor blades can be kept narrow. This has the consequence that the Swivel angle of the rotor is increased because the rotor blades due to their small width only at larger swivel angles on the side surfaces of the Stator wings come to the plant.
  • the rotor blades and their end faces transverse to the longitudinal direction of Rotor blade extending sections provided.
  • the stator wings rest In the two end positions of the rotor, in which the rotor blades with their side surfaces on the side surfaces the stator wings rest, are between the sections and the Statorabêten without recesses must be made on the stator, formed chamber-like receiving spaces in which may be in the hydraulic medium or accumulate a pressure chamber existing dirt particles can. This prevents a structurally simple way that the Dirt particles between the end faces of the rotor blades and the counter surface get the stator and thereby affect the rotational movement of the rotor can.
  • the sections of the rotor blades are very easy produce, so that the camshaft adjusting device according to the invention can be manufactured inexpensively.
  • the transition areas are advantageous designed so that in the region of the front side scraping edges are formed, the possibly existing dirt particles simply into the end-side chambers strip.
  • the camshaft adjusting devices are used in internal combustion engines Used motor vehicles. With them, the opening duration of the injectors depending on the power requirement of the internal combustion engine controlled. During engine operation, the camshaft adjustment device the angular position between the crankshaft and the camshaft changed.
  • the camshaft adjusting device has a rotationally fixed with a chain / pulley connected stator 1.
  • a chain / pulley connected stator 1 About the drive wheel and a corresponding Drive element, such as a chain or a belt, is the stator 1 connected in a known manner with a (not shown) crankshaft.
  • the stator 1 has a cylindrical base body 2, of which in a uniform Spacing radially outwardly projecting wings 3 protrude. Neighboring one another Wings each delimit a pressure chamber 4, in the hydraulic medium can be introduced.
  • On the (not shown) camshaft rotatably seated a rotor 5, which has a cylindrical base body 6. With him, the rotor 5 is rotatably mounted on the camshaft.
  • the annular Base 2 of the stator 1 a cylindrical inner wall 8, on which the rotor blades 7 abut sealingly with their free end faces 9.
  • the faces 10 the stator vanes 3 are also sealingly on a cylindrical outer Jacket surface 11 of the rotor body 6 at.
  • the rotor blades 7 have side surfaces 12 and 13, which in the two end positions to corresponding Side surfaces 14, 15 of the stator 3 abut.
  • an end position of the rotor 5 is the Pressure medium in the pressure chamber 4a pressurized while the Pressure chamber 4b is relieved to the tank. If the rotor 5 from this end position Turned clockwise relative to the stator 1, the Pressure chamber 4b set under pressure, while the pressure chamber 4a depressurized becomes. Then the rotor 5 can be rotated until the rotor blades 7 with the side surfaces 12 on the side surfaces 14 of the stator 3 issue. The rotor 5 can also be brought into an intermediate position, wherein the rotor blades 7 are pressurized from both sides.
  • the contact surfaces 8, 9; 10, 11; 12, 13 and 14, 15 of the stator 1 and the rotor 5 are processed properly to prevent the rotor. 5 clamped against the stator 1.
  • dirt particles in all embodiments radially outer dirt receiving chambers 16, 17 formed. They are by a certain geometric training the rotor blade formed in the region of its radially outer edges.
  • the side surfaces 12, 13 of the rotor blades 7 are connected to the end faces 9 formed curved with a large radius of curvature. About a short radial length, the side surfaces 12, 13 are initially bent outward, so that the width of the rotor blades 7 initially increases. The side surfaces 12, 13 are then bent inwards, so that the width of the rotor blades 7 decreases radially inward.
  • a distance from the lateral surface 11 of the rotor body 6 go over the curved side surface sections over a circumferential shoulder surface 32, 33 parallel to one another Side surface portions 34, 35 over, perpendicular to the lateral surface 11th shoot the rotor body 6.
  • the shoulder surfaces 32, 33 are respectively directed in the direction of the adjacent stator 3 and lie at the same height. In the area of the side surface portions 34, 35 are the Rotor blades 7 narrower than in the region of their end faces.
  • the side surfaces 14, 15 of the stator vanes 3 are on the side surfaces 12, 13th the rotor blade 7 adapted so that they in the end position of the rotor. 5 lie flat against the side surfaces 14, 15 of the stator 3.
  • the inner wall 8 of the stator main body 2 is continuously curved in the side surfaces 14, 15 of the stator 3 via.
  • the adjoining the inner wall 8 Side surface sections are curved outwards and go over circumferentially extending shoulder surfaces 30, 31 in parallel to one another lying side surface portions 36, 37 over, passing through the front side 10 of the stator 3 are connected to each other.
  • the shoulder surfaces 30, 31 extend in the circumferential direction inward, are on the same Height and are the same width as the shoulder surfaces 31, 22 of the rotor blades.
  • the side surface portions 36, 37 are the same length in the radial direction as the Side surface portions 34, 35 of the rotor blades. 7
  • stator and the rotor blades 3, 7 are mirror-symmetrical in all embodiments formed to their respective Axialffenebene.
  • the side surfaces 12, 13 of the rotor blades go 7 via rounded portions 18, 19 in the end faces 9 via.
  • the radius of curvature of the sections 18, 19 is smaller than the radius of curvature the portions 20, 21, with which the inner wall 8 of the stator 2 in the side surfaces 14, 15 of the stator 3 passes. This will be in the end position of the rotor 5 between the stator-side sections 20, 21st and the rotor-side sections 18, 19, the receptacles 16 and 17 are formed. They are, seen in axial view, sickle-shaped.
  • the side surfaces 12, 13 of the rotor blades 7 are at the transition to the end faces 9 with rectangular recesses 22, 23 provided by the right angle mutually lying, shoulder surface forming portions 24, 25, 28, 29 be limited.
  • the circumferentially extending portions 28, 29 close to the curved side surfaces 12, 13 and the radially lying Sections 24, 25 on the end faces 9 of the rotor blades 7 at.
  • the rotor blades 7 have chamfered Sections 18, 19.
  • the straight sections 18, 19 connect the side surfaces 12, 13 with the end faces 9 of the rotor blades 7 and converge in the direction of the end faces 9.
  • the sections 18, 19 In the respective end position of the rotor blades 7 limit the sections 18, 19 with the rounded, to the Corners lying areas 20, 21 of the stator 1, the receptacles 16, 17th
  • Fig. 4 go in the circumferential direction Sections 28, 29 of the rotor blades 7 continuously curved in the side surfaces 12, 13 about.
  • the radially extending portions 24, 25 open into the front side 9 of the rotor blades 7.
  • the sections 24, 25, 28, 29 and the rounded Areas 20, 21 of the stator 1 limit in the respective stop position the rotor blade 7, the receptacles 16, 17th
  • the stator 1 and the rotor 5 may be made of plastic or metallic Material, in particular light metal, preferably aluminum, exist.
  • the stator 1 and the rotor 5 may also be different Materials exist.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Valve Device For Special Equipments (AREA)
  • Valve-Gear Or Valve Arrangements (AREA)

Abstract

The cam shaft adjustment device has a stator and a rotor which is placed relative to each other and are rotatable. The stator has wings with their faces sealing against a surface of the rotor. The wings of the rotor have, within the range of its faces (9) its largest width, and that the sides (12, 13) a part of their length being concave. The concave curved part of the sides are curved over an outward running section (18, 19) into the face of the wings.

Description

Die Erfindung betrifft eine Nockenwellenverstelleinrichtung für Brennkraftmaschinen von Kraftfahrzeugen nach dem Oberbegriff des Anspruches 1.The invention relates to a camshaft adjusting device for internal combustion engines of motor vehicles according to the preamble of claim 1.

Nockenwellenverstelleinrichtungen dienen dazu, die Öffnungs- und Schließzeitpunkt der Gaswechselventile durch eine Relativverdrehung der Nockenwelle gegenüber der Kurbelwelle zu verschieben. Die Rotor- und Statorflügel liegen mit ihren Stirnseiten an den jeweiligen Gegenflächen des Stators bzw. Rotors. Zur Relativverstellung des Stators bzw. Rotors wird Hydraulikmedium verwendet, das die Rotorflügel von beiden Seiten so beaufschlagen kann, daß der Rotor in der gewünschten Richtung relativ zum Stator gedreht wird. Zur Verringerung des Leckagestromes des Hydraulikmediums zwischen den aneinanderliegenden Flächen müssen die Rotor- bzw. Statorflügel mit ihren Stirnseiten dichtend an den Gegenflächen anliegen. Aus diesem Grunde werden die Dichtflächen entsprechend lang ausgebildet. Dadurch wird aber der Schwenkwinkel der Rotorflügel verringert.Camshaft adjusting devices serve to open and close the time the gas exchange valves by a relative rotation of the camshaft to move against the crankshaft. The rotor and stator blades lie with their end faces on the respective mating surfaces of the stator or Rotor. For relative adjustment of the stator or rotor is hydraulic medium used, which act on the rotor blades from both sides so can be that the rotor is rotated in the desired direction relative to the stator becomes. To reduce the leakage flow of the hydraulic medium between The adjacent surfaces must be the rotor or stator with their faces abut sealingly against the mating surfaces. For this reason the sealing surfaces are formed correspondingly long. This will but reduces the swing angle of the rotor blades.

Bei bekannten Nockenwellenverstelleinrichtungen (DE 101 56 055 C2, DE 102 46 173 A1, DE 102 23 523 A1, US 2003/0217720 A1, US 6 758 177 B1, US 6 637 390 B1, EP 1 143 113 A2) haben die Rotorflügel und damit auch die Statorflügel ebene Seitenflächen. Damit die Dichtflächen an den Stirnseiten der Rotorflügel ausreichend lang sind, haben die Rotorflügel eine entsprechend große Breite, die jedoch nur einen begrenzten Schwenkwinkel des Rotors zuläßt. In known camshaft adjusting devices (DE 101 56 055 C2, DE 102 46 173 A1, DE 102 23 523 A1, US 2003/0217720 A1, US Pat 6 758 177 B1, US 6 637 390 B1, EP 1 143 113 A2) have the rotor blades and thus the stator blades even side surfaces. So that the sealing surfaces At the end faces of the rotor blades are sufficiently long, have the rotor blades a correspondingly large width, but only a limited Swing angle of the rotor allows.

Es sind auch Nockenwellenverstellvorrichtungen bekannt, bei denen an den Seitenflächen der Rotorflügel Vorsprünge vorgesehen sind (DE 101 34 320 A1), mit denen die Rotorflügel in der Endlage an den Seitenflächen der Statorflügel anliegen. Durch diese Vorsprünge wird der Schwenkwinkel des Rotors ebenfalls beeinträchtigt.There are also known Nockenwellenverstellvorrichtungen in which the Side surfaces of the rotor blade projections are provided (DE 101 34 320 A1), with which the rotor blades in the end position on the side surfaces of the stator vanes issue. By these projections, the pivot angle of the rotor also affected.

Es sind schließlich Nockenwellenverstelleinrichtungen bekannt (US 2003/0056744 A1), bei denen die freien Enden der Rotorflügel in der Breite verjüngt ausgebildet sind. Auch mit einer solchen Ausbildung ist nur ein begrenzter Schwenkwinkel erreichbar.Finally, camshaft adjusting devices are known (US Pat 2003/0056744 A1), in which the free ends of the rotor blades in width are formed tapered. Even with such training is only a limited Swing angle achievable.

Der Erfindung liegt die Aufgabe zugrunde, die gattungsgemäße Nockenwellenverstelleinrichtung so auszubilden, daß bei konstruktiv einfacher Ausbildung und kostengünstiger Herstellung eine optimale Betriebsweise gewährleistet ist.The invention is based on the object, the generic camshaft adjusting in such a way that with structurally simple training and cost-effective production ensures optimum operation is.

Diese Aufgabe wird bei der gattungsgemäßen Nockenwellenverstelleinrichtung erfindungsgemäß mit den kennzeichnenden Merkmalen des Anspruches 1 gelöst.This object is achieved in the generic camshaft adjusting device according to the invention with the characterizing features of the claim 1 solved.

Bei der erfindungsgemäßen Nockenwellenverstelleinrichtung sind die Rotorflügel im Bereich ihrer Stirnseiten so ausgebildet, daß die Rotorflügel ihre größte Breite haben. Dadurch steht eine ausreichend große Dichtlänge zur Verfügung, um den Leckagestrom minimal zu halten. Die Seitenflächen der Rotorflügel sind über einen Teil ihrer Länge konkav gekrümmt, so daß die Rotorflügel schmal gehalten werden können. Dies hat zur Folge, daß der Schwenkwinkel des Rotors vergrößert ist, da die Rotorflügel aufgrund ihrer geringen Breite erst bei größeren Schwenkwinkeln an den Seitenflächen der Statorflügel zur Anlage kommen.In the camshaft adjusting device according to the invention, the rotor blades formed in the region of their end faces so that the rotor blades their have the largest width. This is a sufficiently large sealing length Available to minimize the leakage current. The side surfaces of the Rotor blades are concavely curved over part of their length, so that the Rotor blades can be kept narrow. This has the consequence that the Swivel angle of the rotor is increased because the rotor blades due to their small width only at larger swivel angles on the side surfaces of the Stator wings come to the plant.

Vorteilhaft sind bei der Nockenwellenverstelleinrichtung zwischen den Seitenflächen der Rotorflügel und deren Stirnseiten quer zur Längsrichtung der Rotorflügel verlaufende Abschnitte vorgesehen. In den beiden Endstellungen des Rotors, in denen die Rotorflügel mit ihren Seitenflächen an den Seitenflächen der Statorflügel anliegen, werden zwischen den Abschnitten und den Statorabschnitten, ohne daß Vertiefungen am Stator gefertigt werden müssen, kammerartige Aufnahmeräume gebildet, in denen sich eventuell im Hydraulikmedium bzw. einem Druckraum vorhandene Schmutzpartikel sammeln können. Dadurch wird auf konstruktiv einfache Weise verhindert, daß die Schmutzpartikel zwischen die Stirnseiten der Rotorflügel und der Gegenfläche des Stators gelangen und dadurch die Drehbewegung des Rotors beeinträchtigen können. Die Abschnitte der Rotorflügel lassen sich sehr einfach herstellen, so daß die erfindungsgemäße Nockenwellenverstelleinrichtung kostengünstig gefertigt werden kann. Vorteilhaft sind die Übergangsbereiche so ausgebildet, daß im Bereich der Stirnseite Abstreifkanten gebildet sind, die eventuell vorhandene Schmutzpartikel einfach in die endseitigen Kammern abstreifen.Advantageously, in the camshaft adjusting between the side surfaces the rotor blades and their end faces transverse to the longitudinal direction of Rotor blade extending sections provided. In the two end positions of the rotor, in which the rotor blades with their side surfaces on the side surfaces the stator wings rest, are between the sections and the Statorabschnitten without recesses must be made on the stator, formed chamber-like receiving spaces in which may be in the hydraulic medium or accumulate a pressure chamber existing dirt particles can. This prevents a structurally simple way that the Dirt particles between the end faces of the rotor blades and the counter surface get the stator and thereby affect the rotational movement of the rotor can. The sections of the rotor blades are very easy produce, so that the camshaft adjusting device according to the invention can be manufactured inexpensively. The transition areas are advantageous designed so that in the region of the front side scraping edges are formed, the possibly existing dirt particles simply into the end-side chambers strip.

Weitere Merkmale der Erfindung ergeben sich aus den weiteren Ansprüchen, der Beschreibung und den Zeichnungen.Further features of the invention will become apparent from the further claims, the description and the drawings.

Die Erfindung wird anhand mehrerer in den Zeichnungen dargestellter Ausführungsbeispiele näher erläutert. Es zeigen

Fig. 1
in Ansicht einen Teil einer erfindungsgemäßen Nockenwellenverstelleinrichtung mit einem Rotor und einem Stator,
Fig. 2 bis Fig. 4
jeweils eine weitere Ausführungsform einer erfindungsgemäßen Nockenwellenverstelleinrichtung in einer Darstellung entspre-chend Fig. 1.
The invention will be explained in more detail with reference to several embodiments shown in the drawings. Show it
Fig. 1
in view of part of a camshaft adjusting device according to the invention with a rotor and a stator,
Fig. 2 to Fig. 4
in each case a further embodiment of a camshaft adjusting device according to the invention in a representation corresponding to FIG. 1.

Die Nockenwellenverstelleinrichtungen werden bei Brennkraftmaschinen von Kraftfahrzeugen eingesetzt. Mit ihnen wird die Öffnungsdauer der Einspritzventile in Abhängigkeit vom Leistungsbedarf der Verbrennungskraftmaschine gesteuert. Während des Motorbetriebes wird mit der Nockenwellenverstelleinrichtung die Winkellage zwischen der Kurbelwelle und der Nockenwelle verändert.The camshaft adjusting devices are used in internal combustion engines Used motor vehicles. With them, the opening duration of the injectors depending on the power requirement of the internal combustion engine controlled. During engine operation, the camshaft adjustment device the angular position between the crankshaft and the camshaft changed.

Die Nockenwellenverstelleinrichtung hat einen drehfest mit einem Ketten/Riemenrad verbundenen Stator 1. Über das Antriebsrad und ein entsprechendes Antriebselement, wie eine Kette oder einen Riemen, ist der Stator 1 in bekannter Weise mit einer (nicht dargestellten) Kurbelwelle verbunden. Der Stator 1 hat einen zylindrischen Grundkörper 2, von dem in gleichmäßigem Abstand radial nach innen ragende Flügel 3 abstehen. Einander benachbarte Flügel begrenzen jeweils einen Druckraum 4, in die Hydraulikmedium eingebracht werden kann. Auf der (nicht dargestellten) Nockenwelle sitzt drehfest ein Rotor 5, der einen zylindrischen Grundkörper 6 aufweist. Mit ihm ist der Rotor 5 drehfest auf der Nockenwelle befestigt. Vom Grundkörper 6 stehen im gleichmäßigen Abstand radial nach außen ragende Flügel 7 ab, die sich im Ausführungsbeispiel vorteilhaft radial nach außen verbreitern. Die Rotorflügel 7 ragen in die Druckräume 4 zwischen einander benachbarte Statorflügel 3, wodurch die Druckräume in zwei Druckkammern 4a und 4b unterteilt werden. In die Druckkammern 4a, 4b mündet jeweils mindestens eine (nicht dargestellte) Bohrung, über die das Hydraulikmedium in die jeweilige Druckkammer gelangen bzw. aus ihr verdrängt werden kann. Das Druckmedium gelangt über (nicht dargestellte) Ventile gesteuert in die jeweiligen Druckkammern 4a, 4b.The camshaft adjusting device has a rotationally fixed with a chain / pulley connected stator 1. About the drive wheel and a corresponding Drive element, such as a chain or a belt, is the stator 1 connected in a known manner with a (not shown) crankshaft. The stator 1 has a cylindrical base body 2, of which in a uniform Spacing radially outwardly projecting wings 3 protrude. Neighboring one another Wings each delimit a pressure chamber 4, in the hydraulic medium can be introduced. On the (not shown) camshaft rotatably seated a rotor 5, which has a cylindrical base body 6. With him, the rotor 5 is rotatably mounted on the camshaft. From the main body 6 are at a uniform distance radially outwardly projecting wings 7, in the embodiment advantageously radially outward broaden. The rotor blades 7 protrude into the pressure chambers 4 between each other adjacent stator blades 3, causing the pressure chambers in two pressure chambers 4a and 4b are divided. In the pressure chambers 4a, 4b opens respectively at least one (not shown) bore through which the hydraulic medium enter the respective pressure chamber or can be displaced from it. The pressure medium passes via (not shown) valves controlled in the respective pressure chambers 4a, 4b.

Bei den Ausführungsformen gemäß den Fig. 1 bis 4 hat der ringförmige Grundkörper 2 des Stators 1 eine zylindrische Innenwand 8, an der die Rotorflügel 7 mit ihren freien Stirnseiten 9 dichtend anliegen. Die Stirnseiten 10 der Statorflügel 3 liegen ebenfalls dichtend an einer zylindrischen äußeren Mantelfläche 11 des Rotorgrundkörpers 6 an. Die Rotorflügel 7 weisen Seitenflächen 12 und 13 auf, die in den beiden Endstellungen an entsprechenden Seitenflächen 14, 15 der Statorflügel 3 anliegen. Durch die Druckbeaufschlagung des Mediums in der jeweiligen Druckkammer 4a bzw. 4b wird die Relativverdrehung zwischen dem Rotor 5 und dem Stator 1 erreicht. Bei der in den Zeichnungen dargestellten einen Endlage des Rotors 5 ist das Druckmedium in der Druckkammer 4a unter Druck gesetzt, während die Druckkammer 4b zum Tank hin entlastet ist. Soll der Rotor 5 aus dieser Endlage im Uhrzeigersinn gegenüber dem Stator 1 gedreht werden, wird die Druckkammer 4b unter Druck gesetzt, während die Druckkammer 4a druckentlastet wird. Dann kann der Rotor 5 so weit gedreht werden, bis die Rotorflügel 7 mit den Seitenflächen 12 an den Seitenflächen 14 der Statorflügel 3 anliegen. Der Rotor 5 kann auch in eine Zwischenlage gebracht werden, wobei die Rotorflügel 7 von beiden Seiten mit Druck beaufschlagt sind.In the embodiments according to FIGS. 1 to 4, the annular Base 2 of the stator 1, a cylindrical inner wall 8, on which the rotor blades 7 abut sealingly with their free end faces 9. The faces 10 the stator vanes 3 are also sealingly on a cylindrical outer Jacket surface 11 of the rotor body 6 at. The rotor blades 7 have side surfaces 12 and 13, which in the two end positions to corresponding Side surfaces 14, 15 of the stator 3 abut. By the pressurization the medium in the respective pressure chamber 4 a and 4 b is the Relative rotation between the rotor 5 and the stator 1 is reached. In the in the drawings shown an end position of the rotor 5 is the Pressure medium in the pressure chamber 4a pressurized while the Pressure chamber 4b is relieved to the tank. If the rotor 5 from this end position Turned clockwise relative to the stator 1, the Pressure chamber 4b set under pressure, while the pressure chamber 4a depressurized becomes. Then the rotor 5 can be rotated until the rotor blades 7 with the side surfaces 12 on the side surfaces 14 of the stator 3 issue. The rotor 5 can also be brought into an intermediate position, wherein the rotor blades 7 are pressurized from both sides.

Die Kontaktflächen 8, 9; 10, 11; 12, 13 und 14, 15 des Stators 1 und des Rotors 5 sind einwandfrei bearbeitet, um zu verhindern, daß sich der Rotor 5 gegenüber dem Stator 1 verklemmt. Außerdem muß gewährleistet sein, daß eventuell in den Druckkammern 4a und 4b vorhandene Schmutzpartikel nicht zu einer Verringerung des Schwenkwinkels des Stators 1 und des Rotors 5 gegeneinander bzw. zu einer Blockade dieser Teile führen.The contact surfaces 8, 9; 10, 11; 12, 13 and 14, 15 of the stator 1 and the rotor 5 are processed properly to prevent the rotor. 5 clamped against the stator 1. In addition, it must be ensured that possibly present in the pressure chambers 4a and 4b dirt particles not to a reduction of the swivel angle of the stator 1 and the rotor fifth against each other or lead to a blockage of these parts.

Zur Aufnahme von in die Druckräume 4 eindringenden Schmutzpartikeln sind bei sämtlichen Ausführungsformen radial äußere Schmutzaufnahmekammern 16, 17 gebildet. Sie sind durch eine bestimmte geometrische Ausbildung der Rotorflügel im Bereich ihrer radial äußeren Ränder gebildet.To receive penetrating into the pressure chambers 4 dirt particles in all embodiments radially outer dirt receiving chambers 16, 17 formed. They are by a certain geometric training the rotor blade formed in the region of its radially outer edges.

Die Seitenflächen 12, 13 der Rotorflügel 7 sind im Anschluß an die Stirnseiten 9 mit großem Krümmungsradius gekrümmt ausgebildet. Über eine kurze radiale Länge sind die Seitenflächen 12, 13 zunächst nach außen gebogen, so daß die Breite der Rotorflügel 7 zunächst zunimmt. Die Seitenflächen 12, 13 sind anschließend nach innen gebogen, so daß die Breite der Rotorflügel 7 radial nach innen abnimmt. Mit Abstand von der Mantelfläche 11 des Rotorgrundkörpers 6 gehen die gebogenen Seitenflächenabschnitte über eine in Umfangsrichtung liegende Schulterfläche 32, 33 in zueinander parallele Seitenflächenabschnitte 34, 35 über, die senkrecht an die Mantelfläche 11 des Rotorgrundkörpers 6 anschießen. Die Schulterflächen 32, 33 sind jeweils in Richtung auf den benachbarten Statorflügel 3 gerichtet und liegen auf gleicher Höhe. Im Bereich der Seitenflächenabschnitte 34, 35 sind die Rotorflügel 7 schmaler als im Bereich ihrer Stirnseiten 9.The side surfaces 12, 13 of the rotor blades 7 are connected to the end faces 9 formed curved with a large radius of curvature. About a short radial length, the side surfaces 12, 13 are initially bent outward, so that the width of the rotor blades 7 initially increases. The side surfaces 12, 13 are then bent inwards, so that the width of the rotor blades 7 decreases radially inward. At a distance from the lateral surface 11 of the rotor body 6 go over the curved side surface sections over a circumferential shoulder surface 32, 33 parallel to one another Side surface portions 34, 35 over, perpendicular to the lateral surface 11th shoot the rotor body 6. The shoulder surfaces 32, 33 are respectively directed in the direction of the adjacent stator 3 and lie at the same height. In the area of the side surface portions 34, 35 are the Rotor blades 7 narrower than in the region of their end faces. 9

Die Seitenflächen 14, 15 der Statorflügel 3 sind an die Seitenflächen 12, 13 der Rotorflügel 7 angepaßt, so daß diese in der Endstellung des Rotors 5 flächig an den Seitenflächen 14, 15 der Statorflügel 3 anliegen.The side surfaces 14, 15 of the stator vanes 3 are on the side surfaces 12, 13th the rotor blade 7 adapted so that they in the end position of the rotor. 5 lie flat against the side surfaces 14, 15 of the stator 3.

Die Innenwand 8 des Statorgrundkörpers 2 geht stetig gekrümmt in die Seitenflächen 14, 15 der Statorflügel 3 über. Die an die Innenwand 8 anschließenden Seitenflächenabschnitte sind nach außen gekrümmt und gehen über in Umfangsrichtung sich erstreckende Schulterflächen 30, 31 in parallel zueinander liegende Seitenflächenabschnitte 36, 37 über, die durch die Stirnseite 10 des Statorflügels 3 miteinander verbunden sind. Die Schulterflächen 30, 31 erstrecken sich in Umfangsrichtung nach innen, liegen auf gleicher Höhe und sind gleich breit wie die Schulterflächen 31, 22 der Rotorflügel 7. Die Seitenflächenabschnitte 36, 37 sind in Radialrichtung gleich lang wie die Seitenflächenabschnitte 34, 35 der Rotorflügel 7.The inner wall 8 of the stator main body 2 is continuously curved in the side surfaces 14, 15 of the stator 3 via. The adjoining the inner wall 8 Side surface sections are curved outwards and go over circumferentially extending shoulder surfaces 30, 31 in parallel to one another lying side surface portions 36, 37 over, passing through the front side 10 of the stator 3 are connected to each other. The shoulder surfaces 30, 31 extend in the circumferential direction inward, are on the same Height and are the same width as the shoulder surfaces 31, 22 of the rotor blades. 7 The side surface portions 36, 37 are the same length in the radial direction as the Side surface portions 34, 35 of the rotor blades. 7

Die Stator- und die Rotorflügel 3, 7 sind bei allen Ausführungsformen spiegelsymmetrisch zu ihrer jeweiligen Axialmittelebene ausgebildet.The stator and the rotor blades 3, 7 are mirror-symmetrical in all embodiments formed to their respective Axialmittelebene.

Bei der Ausführungsform nach Fig. 1 gehen die Seitenflächen 12, 13 der Rotorflügel 7 über gerundete Abschnitte 18, 19 in die Stirnseiten 9 über. Der Krümmungsradius der Abschnitte 18, 19 ist kleiner als der Krümmungsradius der Abschnitte 20, 21, mit denen die Innenwand 8 des Statorgrundkörpers 2 in die Seitenflächen 14, 15 der Statorflügel 3 übergeht. Dadurch werden in der Endlage des Rotors 5 zwischen den statorseitigen Abschnitten 20, 21 und den rotorseitigen Abschnitten 18, 19 die Aufnahmen 16 bzw. 17 gebildet. Sie sind, in Axialansicht gesehen, sichelförmig ausgebildet.In the embodiment of Fig. 1, the side surfaces 12, 13 of the rotor blades go 7 via rounded portions 18, 19 in the end faces 9 via. Of the The radius of curvature of the sections 18, 19 is smaller than the radius of curvature the portions 20, 21, with which the inner wall 8 of the stator 2 in the side surfaces 14, 15 of the stator 3 passes. This will be in the end position of the rotor 5 between the stator-side sections 20, 21st and the rotor-side sections 18, 19, the receptacles 16 and 17 are formed. They are, seen in axial view, sickle-shaped.

Die Seitenflächen 12, 13 der Rotorflügel 7 sind am Übergang zu den Stirnseiten 9 mit rechteckigen Ausnehmungen 22, 23 versehen, die durch rechtwinklig zueinander liegende, Schulterflächen bildende Abschnitte 24, 25, 28, 29 begrenzt werden. Die in Umfangsrichtung sich erstreckenden Abschnitte 28, 29 schließen an die gekrümmten Seitenflächen 12, 13 und die radial liegenden Abschnitte 24, 25 an die Stirnseiten 9 der Rotorflügel 7 an.The side surfaces 12, 13 of the rotor blades 7 are at the transition to the end faces 9 with rectangular recesses 22, 23 provided by the right angle mutually lying, shoulder surface forming portions 24, 25, 28, 29 be limited. The circumferentially extending portions 28, 29 close to the curved side surfaces 12, 13 and the radially lying Sections 24, 25 on the end faces 9 of the rotor blades 7 at.

In der jeweiligen Endstellung des Rotors 5 begrenzen die Abschnitte 24, 25, 28, 29 der Rotorflügel 7 und die gekrümmten Abschnitte 20, 21 des Stators 1 die Aufnahmen 16, 17.In the respective end position of the rotor 5, the sections 24, 25, 28, 29 of the rotor blade 7 and the curved portions 20, 21 of the stator first the pictures 16, 17.

Beim Ausführungsbeispiel nach Fig. 3 haben die Rotorflügel 7 abgeschrägte Abschnitte 18, 19. Die geraden Abschnitte 18, 19 verbinden die Seitenflächen 12, 13 mit den Stirnseiten 9 der Rotorflügel 7 und verlaufen konvergierend in Richtung auf die Stirnseiten 9. In der jeweiligen Endstellung der Rotorflügel 7 begrenzen die Abschnitte 18, 19 mit den abgerundeten, an den Ecken liegenden Bereichen 20, 21 des Stators 1 die Aufnahmen 16, 17.In the embodiment of FIG. 3, the rotor blades 7 have chamfered Sections 18, 19. The straight sections 18, 19 connect the side surfaces 12, 13 with the end faces 9 of the rotor blades 7 and converge in the direction of the end faces 9. In the respective end position of the rotor blades 7 limit the sections 18, 19 with the rounded, to the Corners lying areas 20, 21 of the stator 1, the receptacles 16, 17th

Bei der Ausführungsform nach Fig. 4 gehen die in Umfangsrichtung liegenden Abschnitte 28, 29 der Rotorflügel 7 stetig gekrümmt in die Seitenflächen 12, 13 über. Die radial verlaufenden Abschnitte 24, 25 münden in die Stirnseite 9 der Rotorflügel 7. Die Abschnitte 24, 25, 28, 29 und die abgerundeten Bereiche 20, 21 des Stators 1 begrenzen in der jeweiligen Anschlagstellung der Rotorflügel 7 die Aufnahmen 16, 17.In the embodiment of Fig. 4 go in the circumferential direction Sections 28, 29 of the rotor blades 7 continuously curved in the side surfaces 12, 13 about. The radially extending portions 24, 25 open into the front side 9 of the rotor blades 7. The sections 24, 25, 28, 29 and the rounded Areas 20, 21 of the stator 1 limit in the respective stop position the rotor blade 7, the receptacles 16, 17th

Bei den Ausführungsformen nach den Fig. 2 bis 4 sind an der Stirnseite 9 der Rotorflügel 7 die Abstreifkanten 26, 27 gebildet, mit denen im Druckraum 4 vorhandene Schmutzpartikel bei Rotation des Rotors 5 an der Innenwand 8 des Stators 1 entlang in die entsprechende Aufnahme 16 bzw. 17 in Drehrichtung geschoben werden.In the embodiments according to FIGS. 2 to 4 are on the front side. 9 the rotor blade 7, the scraping edges 26, 27 are formed, with which in the pressure chamber 4 existing dirt particles upon rotation of the rotor 5 on the inner wall 8 of the stator 1 along in the corresponding receptacle 16 and 17 in the direction of rotation be pushed.

Durch die beschriebenen Ausbildungen ist bei einfacher Geometrie der Rotorflügel 7 verhindert, daß im Druckraum 4 vorhandene Schmutzpartikel zwischen den Dichtflächen des Rotors 5 und des Stators 1 verklemmen und so deren Relativbewegung zueinander beeinträchtigen können. Due to the described training is simple geometry of the rotor blade 7 prevents existing in the pressure chamber 4 dirt particles between jam the sealing surfaces of the rotor 5 and the stator 1 and so their relative movement can interfere with each other.

Der Stator 1 und der Rotor 5 können aus Kunststoff oder auch aus metallischem Werkstoff, insbesondere Leichtmetall, vorzugsweise Aluminium, bestehen. Der Stator 1 und der Rotor 5 können auch aus unterschiedlichen Materialien bestehen.The stator 1 and the rotor 5 may be made of plastic or metallic Material, in particular light metal, preferably aluminum, exist. The stator 1 and the rotor 5 may also be different Materials exist.

Claims (19)

Nockenwellenverstelleinrichtung für Brennkraftmaschinen von Kraftfahrzeugen, mit einem Stator und einem Rotor, die relativ zueinander verdrehbar sind und jeweils radial abstehende Flügel aufweisen, die mit ihren Stirnseiten dichtend an einer Gegenfläche des Rotors bzw. Stators anliegen und Seitenflächen haben,
dadurch gekennzeichnet, daß die Rotorflügel (7) im Bereich ihrer Stirnseiten (9) ihre größte Breite haben, und daß die Seitenflächen (12, 13) der Rotorflügel (7) über einen Teil ihrer Länge konkav gekrümmt sind.Camshaft adjusting device for internal combustion engines of motor vehicles, with a stator and a rotor, which are rotatable relative to each other and each having radially projecting wings which bear sealingly with their end faces against a mating surface of the rotor or stator and have side surfaces,
characterized in that the rotor blades (7) in the region of their end faces (9) have their greatest width, and that the side surfaces (12, 13) of the rotor blades (7) are concavely curved over part of their length. Einrichtung nach Anspruch 1,
dadurch gekennzeichnet, daß der konkav gekrümmte Teil der Seitenflächen (12, 13) über einen nach außen gekrümmt verlaufenden Abschnitt (18, 19) in die Stirnseite (9) des Rotorflügels (7) übergeht.Device according to claim 1,
characterized in that the concavely curved portion of the side surfaces (12, 13) merges via an outwardly curved portion extending (18, 19) in the end face (9) of the rotor blade (7). Einrichtung nach Anspruch 2,
dadurch gekennzeichnet, daß der Krümmungsradius der nach außen gekrümmt verlaufenden Abschnitte (18, 19) der Seitenflächen (12, 13) kleiner ist als der Krümmungsradius der konkav gekrümmten Abschnitte der Seitenflächen (12, 13) der Rotorflügel (7).Device according to claim 2,
characterized in that the radius of curvature of the outwardly curved portions (18, 19) of the side surfaces (12, 13) is smaller than the radius of curvature of the concavely curved portions of the side surfaces (12, 13) of the rotor vanes (7). Einrichtung nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, daß die Seitenflächen (12, 13) der Rotorflügel (7) radial innen an zueinander parallele Seitenflächenabschnitte (34, 35) anschließen.Device according to one of claims 1 to 3,
characterized in that the side surfaces (12, 13) of the rotor blades (7) connect radially inwardly to mutually parallel side surface portions (34, 35). Einrichtung nach Anspruch 4,
dadurch gekennzeichnet, daß die Seitenflächen (12, 13) über Schulterflächen (32, 33) an die Seitenflächenabschnitte (34, 35) anschließen.Device according to claim 4,
characterized in that the side surfaces (12, 13) via shoulder surfaces (32, 33) to the side surface portions (34, 35) connect. Einrichtung nach Anspruch 5,
dadurch gekennzeichnet, daß die Schulterflächen (32, 33) auf gleicher Höhe liegen.Device according to claim 5,
characterized in that the shoulder surfaces (32, 33) are at the same height. Einrichtung nach einem der Ansprüche 1 bis 6,
dadurch gekennzeichnet, daß die Seitenflächen (12, 13) der Rotorflügel (7) über mindestens teilweise quer zur Längsrichtung der Rotorflügel (7) verlaufende Abschnitte (18, 19; 24, 25; 28, 29) an die Stirnseite (9) des Rotorflügels (7) anschließen.Device according to one of claims 1 to 6,
characterized in that the side surfaces (12, 13) of the rotor blades (7) extend over at least partially transversely to the longitudinal direction of the rotor blades (7) extending portions (18, 19, 24, 25, 28, 29) on the end face (9) of the rotor blade (7) connect. Einrichtung nach Anspruch 7,
dadurch gekennzeichnet, daß die Abschnitte (18, 19; 24, 25; 28, 29) in Anschlagstellung der Rotorflügel (7) an den Statorflügeln (3) unter Vermeidung von Vertiefungen am Stator mit Abschnitten (20, 21) des Stators (1) Aufnahmekammern (16, 17) bilden.Device according to claim 7,
characterized in that the sections (18, 19, 24, 25, 28, 29) in stop position of the rotor blades (7) on the stator vanes (3) while avoiding depressions on the stator with sections (20, 21) of the stator (1). Forming receiving chambers (16, 17). Einrichtung nach Anspruch 7 oder 8,
dadurch gekennzeichnet, daß die Abschnitte (18, 19) stetig gekrümmt in die Seitenflächen (12, 13) und die Stirnseite (9) des Rotorflügels (7) übergehen.Device according to claim 7 or 8,
characterized in that the sections (18, 19) continuously curved in the side surfaces (12, 13) and the end face (9) of the rotor blade (7) merge. Einrichtung nach Anspruch 7 oder 8,
dadurch gekennzeichnet, daß die Abschnitte (18, 19) gerade verlaufen und winklig an die Seitenflächen (12, 13) und an die Stirnseite (9) anschließen. Device according to claim 7 or 8,
characterized in that the sections (18, 19) are straight and connect at an angle to the side surfaces (12, 13) and to the end face (9). Einrichtung nach einem der Ansprüche 7 bis 10,
dadurch gekennzeichnet, daß die Abschnitte (24, 25, 28, 29) Ausnehmungen (22, 23) an den freien Enden des Rotorflügels (7) begrenzen.Device according to one of claims 7 to 10,
characterized in that the portions (24, 25, 28, 29) define recesses (22, 23) at the free ends of the rotor blade (7). Einrichtung nach Anspruch 11,
dadurch gekennzeichnet, daß die Ausnehmungen (22, 23) in die Seitenflächen (12, 13) und in die Stirnseite (9) des Rotorflügels (7) münden.Device according to claim 11,
characterized in that the recesses (22, 23) open into the side surfaces (12, 13) and in the end face (9) of the rotor blade (7). Einrichtung nach Anspruch 11 oder 12,
dadurch gekennzeichnet, daß die Abschnitte (24, 25, 28, 29) etwa rechtwinklig zueinander liegen.Device according to claim 11 or 12,
characterized in that the sections (24, 25, 28, 29) are approximately at right angles to each other. Einrichtung nach einem der Ansprüche 11 bis 13,
dadurch gekennzeichnet, daß die einen Abschnitte (24, 25) etwa radial und die anderen Abschnitte (28, 29) etwa in Umfangsrichtung des Rotors (5) verlaufen.Device according to one of claims 11 to 13,
characterized in that the one sections (24, 25) extend approximately radially and the other sections (28, 29) approximately in the circumferential direction of the rotor (5). Einrichtung nach Anspruch 14,
dadurch gekennzeichnet, daß die etwa in Umfangsrichtung des Rotors (5) verlaufenden Abschnitte (28, 29) stetig gekrümmt in die Seitenflächen (12, 13) des Rotorflügels (7) übergehen.Device according to claim 14,
characterized in that the approximately in the circumferential direction of the rotor (5) extending portions (28, 29) continuously curved in the side surfaces (12, 13) of the rotor blade (7) pass. Einrichtung nach Anspruch 14 oder 15,
dadurch gekennzeichnet, daß die etwa radial verlaufenden Abschnitte (24, 25) unter Bildung einer Abstreifkante (26, 27) winklig an die Stirnseite (9) des Rotorflügels (7) anschließen.Device according to claim 14 or 15,
characterized in that the approximately radially extending portions (24, 25) to form a Abstreifkante (26, 27) connect at an angle to the end face (9) of the rotor blade (7). Einrichtung nach einem der Ansprüche 7 bis 16,
dadurch gekennzeichnet, daß die Abschnitte (18, 19; 24, 25; 28, 29) in Anschlagstellung der Rotorflügel (7) an den Statorflügeln (3) unter Vermeidung von Vertiefungen am Stator mit Abschnitten (20, 21) des Stators (1) Aufnahmekammern (16, 17) bilden.Device according to one of claims 7 to 16,
characterized in that the sections (18, 19, 24, 25, 28, 29) in stop position of the rotor blades (7) on the stator vanes (3) while avoiding depressions on the stator with sections (20, 21) of the stator (1). Forming receiving chambers (16, 17). Einrichtung nach Anspruch 17,
dadurch gekennzeichnet, daß die die Aufnahmekammern (16, 17) begrenzenden Abschnitte (20, 21) des Stators (1) am Übergang von einer Innenwand (8) des Stators (1) zu den Seitenflächen (14,15) der Statorflügel (3) vorgesehen sind.Device according to claim 17,
characterized in that the receiving chambers (16, 17) limiting portions (20, 21) of the stator (1) at the transition from an inner wall (8) of the stator (1) to the side surfaces (14,15) of the stator vanes (3) are provided. Einrichtung nach Anspruch 17 oder 18,
dadurch gekennzeichnet, daß die Abschnitte (20, 21) des Stators (1) gekrümmt verlaufen.Device according to claim 17 or 18,
characterized in that the sections (20, 21) of the stator (1) are curved.
EP05004274A 2004-02-27 2005-02-28 Camshaft phasing device for vehicle engine Expired - Lifetime EP1568855B1 (en)

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DE102004010829 2004-02-27
DE102004010829 2004-02-27
DE102005007942A DE102005007942B4 (en) 2004-02-27 2005-02-22 Camshaft adjusting device for internal combustion engines of motor vehicles
DE102005007942 2005-02-22

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DE102010012652B4 (en) 2010-03-25 2018-05-17 Hilite Germany Gmbh Pivot camshaft adjuster with a rotor

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ATE356280T1 (en) 2007-03-15
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EP1568855A3 (en) 2006-04-12

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