EP0217979B1 - Vane cell compressor - Google Patents

Vane cell compressor Download PDF

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Publication number
EP0217979B1
EP0217979B1 EP85112898A EP85112898A EP0217979B1 EP 0217979 B1 EP0217979 B1 EP 0217979B1 EP 85112898 A EP85112898 A EP 85112898A EP 85112898 A EP85112898 A EP 85112898A EP 0217979 B1 EP0217979 B1 EP 0217979B1
Authority
EP
European Patent Office
Prior art keywords
rings
blade
rotor
front faces
sliders
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP85112898A
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German (de)
French (fr)
Other versions
EP0217979A1 (en
Inventor
Wilfried Ball
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.)
Bayerische Motoren Werke AG
Original Assignee
Bayerische Motoren Werke AG
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 to DE19843417491 priority Critical patent/DE3417491A1/en
Application filed by Bayerische Motoren Werke AG filed Critical Bayerische Motoren Werke AG
Priority to DE8585112898T priority patent/DE3562792D1/en
Priority to EP85112898A priority patent/EP0217979B1/en
Priority to DE19853536368 priority patent/DE3536368A1/en
Publication of EP0217979A1 publication Critical patent/EP0217979A1/en
Application granted granted Critical
Publication of EP0217979B1 publication Critical patent/EP0217979B1/en
Expired 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
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C21/00—Component parts, details or accessories not provided for in groups F01C1/00 - F01C20/00
    • F01C21/08—Rotary pistons
    • F01C21/0809—Construction of vanes or vane holders
    • F01C21/0818—Vane tracking; control therefor
    • F01C21/0827—Vane tracking; control therefor by mechanical means
    • F01C21/0845—Vane tracking; control therefor by mechanical means comprising elastic means, e.g. springs

Definitions

  • the invention relates to a vane compressor of a type with the features of the preamble of claim 1.
  • the vane slides are arranged exactly radially to the axis of rotation of the rotor, the elastic rings are always with the inner end faces of the wing slide in contact and press them against the circular cylindrical inner surface of the housing cylinder, for which only resilient metallic rings are suitable, and between the rings and the inner diameter of the ring grooves in the rotor there is a relatively large free distance.
  • the elastic rings act constantly on the wing slide, so that their radial contact pressure is increased in addition to the centrifugal force and their wear and that of the inner surface increases.
  • the metallic rings also promote noise generation through radial and tangential whirring of the wing slides.
  • the object of the invention is to develop a vane compressor of the type mentioned so that it is characterized by a very smooth running.
  • the rings which can be deformed in cross-section, dampen the movements of the vane cells in the region of their inner dead position on the one hand as elastic stops and, on the other hand, accelerate the initial phase of the radial outward movement of the wing slides without increased wear on the outer end faces of the wing slides and the inner surface of the housing cylinder by constant additional radial To cause force.
  • the fatigue strength of the elastic rings themselves is also ensured without additional construction costs by their coordinated design and arrangement in the ring grooves, because there is no local overload due to their constant twisting.
  • the circular cross section of the O-rings results in a particularly favorable course of the damping and resilience function due to the higher deformability of the O-rings compared to elastic rings, for example with a rectangular cross-section.
  • a vane compressor 1 contains a concentrically mounted rotor 4 in a housing cylinder 2 with an elliptical cylindrical inner surface 3.
  • the rotor 4 consists of an axle shaft 5 and a circular-cylindrical rotor body 6 with radial end faces 7.
  • In the rotor body 6 there are approximately radial slots 8 ⁇ m
  • a few angular degrees from the radial direction in the direction of rotation inclined wing slide 9 are supported, which are supported against the inner surface 3 of the housing cylinder 2 to the outside, in the rotor body 6, an annular groove 10 is arranged concentrically to the axis of rotation 11 in its end faces 7, in each of which one lies in its circular cross-section elastically deformable 0-ring 12.
  • the O-rings 12 are preferably made of fluorine rubber (FPM), which withstands the occurring temperatures as well as mechanical and chemical influences, and represent spring and damping bodies that are elastically deformed by all wing slides 9 in their respective dead center positions because that radial cross-sectional dimension of the O-rings 12 is greater than the distance between the inner end faces 9 'of the wing slide 9, and the inner diameter of the ring grooves 10 in the inner dead position of the wing slide 9.
  • FPM fluorine rubber
  • the wing slides 9 move radially back and forth within the slots 8. This movement is determined by the inner surface 3 of the housing cylinder 2, along which the wing slides slide with their outer end faces 9 ′′ due to the centrifugal force effect.
  • the wing slides each reach the inner dead center at points 14 of the inner surface 3, which are from the axis of rotation 11 In this way, the wing slides 9 touch and deform with their inner end faces 9 'in a region in each case before to after their inner dead positions, the two 0-rings 12.
  • the O-rings 12 thereby act as resilient and damping stops and prevent the wing slides 9 from hitting the inner boundary surfaces of the slots 8 in the rotor body 6 and thereby generating very strong noises, the elastic restoring force of the 0-rings 12 after the inner dead positions of the wing slides 9 causing their acceleration from this rest position even at low speeds of the Rotor body 6 with a relatively low centrifugal force, so that take off and late he following re-opening of the outer end faces 9 "of the wing slide 9 from and onto the inner surface 3 of the housing cylinder 2 can also be avoided with further noise generation.
  • the O-rings 12 do not act on the wing slide 9, so that no additional pressing force for the centrifugal force on the inner surface 3 and thus no corresponding wear can occur.

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

Description

Die Erfindung bezieht sich auf einen Flügelzellenverdichter einer Bauart mit den Merkmalen des Oberbegriffes des Patentanspruches 1. Bei einem bekannten Verdichter dieser Bauart gemäß DE-B-2 117 102 sind die Flügelschieber genau radial zur Drehachse des Rotors angeordnet, die elastischen Ringe stehen ständig mit den inneren Stirnflächen der Flügelschieber in Berührung und drücken diese gegen die kreiszylindrische Innenfläche des Gehäusezylinders, wozu nur federelastische metallische Ringe geeignet sind, und zwischen den Ringen und dem Innen-Durchmesser der Ringnuten im Rotor besteht ein relativ großer freier Abstand. Dabei wirken die elastischen Ringe ständig auf die Flügelschieber, so daß deren radialer Anpressdruck zusätzlich zur Fliehkraftwirkung verstärkt wird und sich deren Abnützung sowie diejenige der Innenfläche erhöht. Die metallischen Ringe begünstigen mangels einer ausreichenden Schwingungsdämpfung auch die Geräuschbildung durch radiales und tangentiales Schwirren der Flügelschieber.The invention relates to a vane compressor of a type with the features of the preamble of claim 1. In a known compressor of this type according to DE-B-2 117 102, the vane slides are arranged exactly radially to the axis of rotation of the rotor, the elastic rings are always with the inner end faces of the wing slide in contact and press them against the circular cylindrical inner surface of the housing cylinder, for which only resilient metallic rings are suitable, and between the rings and the inner diameter of the ring grooves in the rotor there is a relatively large free distance. The elastic rings act constantly on the wing slide, so that their radial contact pressure is increased in addition to the centrifugal force and their wear and that of the inner surface increases. In the absence of sufficient vibration damping, the metallic rings also promote noise generation through radial and tangential whirring of the wing slides.

Aufgabe der Erfindung ist es, einen Flügelzellenverdichter der genannten Bauart so weiter zu bilden, daß er sich durch eine hohe Laufruhe auszeichnet.The object of the invention is to develop a vane compressor of the type mentioned so that it is characterized by a very smooth running.

Diese Aufgabe löst die Erfindung durch die Ausbildung gemäß den kennzeichnenden Merkmalen des Anspruches 1 in überraschend einfacher und rationell ausführbarer Weise. Die in ihrem Querschnitt verformbaren Ringe dämpfen einerseits als elastische Anschläge die Bewegungen der Flügelzellen im Bereich ihrer inneren Totlage und beschleunigen andererseits die Anfangsphase der radialen Auswärtsbewegung der Flügelschieber ohne eine erhöhte Abnutzung der äußeren Stirnflächen der Flügelschieber und der Innenfläche des Gehäuse- Zylinders durch ständige zusätzliche radiale Krafteinwirkung zu verursachen. Auch die Dauerstandfestigkeit der elastischen Ringe selbst wird ohne zusätzlichen Bauaufwand durch deren abgestimmte Ausbildung und Anordnung in den Ringnuten sichergestellt, weil durch deren ständiges Verdrehen keine örtliche Überbeanspruchung auftritt.This object is achieved by the invention in a surprisingly simple and rationally executable manner by the training according to the characterizing features of claim 1. The rings, which can be deformed in cross-section, dampen the movements of the vane cells in the region of their inner dead position on the one hand as elastic stops and, on the other hand, accelerate the initial phase of the radial outward movement of the wing slides without increased wear on the outer end faces of the wing slides and the inner surface of the housing cylinder by constant additional radial To cause force. The fatigue strength of the elastic rings themselves is also ensured without additional construction costs by their coordinated design and arrangement in the ring grooves, because there is no local overload due to their constant twisting.

Bei der Ausbildung nach Anspruch 2 ergibt der Kreisquerschnitt der O-Ringe einen besonders günstigen Verlauf der Dämpfungs- und Rückfeder-Funktion durch die höhere Verformbarkeit der O-Ringe gegenüber elastischen Ringen beispielsweise mit Rechteckquerschnitt.In the embodiment according to claim 2, the circular cross section of the O-rings results in a particularly favorable course of the damping and resilience function due to the higher deformability of the O-rings compared to elastic rings, for example with a rectangular cross-section.

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung dargestellt.In the drawing, an embodiment of the invention is shown.

Es zeigen:

  • Fig. 1 den Rotor eines Flügelzellenverdichters mit der Kontur der Innenfläche eines zugehörigen Gehäuse-Zylinders in Stirnansicht und
  • Fig. 2 einen Längsschnitt nach der Linie 11-11 in Fig.1.
Show it:
  • Fig. 1 shows the rotor of a vane compressor with the contour of the inner surface of an associated housing cylinder in front view and
  • Fig. 2 is a longitudinal section along the line 11-11 in Fig.1.

Ein Flügelzellenverdichter 1 enthält in einem Gehäuse-Zylinder 2 mit elliptischzylinderförmiger Innenfläche 3 einen konzentrisch gelagerten Rotor 4. Der Rotor 4 besteht aus einer Achswelle 5 und einem kreis-zylindrischen Rotorkörper 6 mit radialen Stirnflächen 7. Im Rotorkörper 6 sind in etwa radialen Schlitzen 8 um wenige Winkelgrade von der radialen Richtung in Drehrichtung geneigte Flügelschieber 9 gelagert, die sich gegen die Innenfläche 3 des Gehäuse-Zylinders 2 nach außen abstützen, im Rotorkörper 6 ist in seinen Stirnflächen 7 je eine Ringnut 10 konzentrisch zur Drehachse 11 angeordnet, in denen je ein in seinem Kreis-Querschnitt elastisch verformbarer 0-Ring 12 liegt. Die O-Ringe 12 bestehen bevorzugt aus Fluor-Kautschuck (FPM), das den auftretenden Temperaturen sowie mechanischen und chemischen Einflüssen standhält, und stellen Feder- und Dämpfungskörper dar, die von allen Flügelschiebern 9 in ihrer jeweiligen inneren Totlage elastisch verformt werden, weil das radiale Querschnittsmaß der O-Ringe 12 größer ist als der Abstand zwischen den inneren Stirn Flächen 9' der Flügelschieber 9, und dem Innen-Durchmesser der Ringnuten 10 in der inneren Totlage der Flügelschieber 9.A vane compressor 1 contains a concentrically mounted rotor 4 in a housing cylinder 2 with an elliptical cylindrical inner surface 3. The rotor 4 consists of an axle shaft 5 and a circular-cylindrical rotor body 6 with radial end faces 7. In the rotor body 6 there are approximately radial slots 8 µm A few angular degrees from the radial direction in the direction of rotation inclined wing slide 9 are supported, which are supported against the inner surface 3 of the housing cylinder 2 to the outside, in the rotor body 6, an annular groove 10 is arranged concentrically to the axis of rotation 11 in its end faces 7, in each of which one lies in its circular cross-section elastically deformable 0-ring 12. The O-rings 12 are preferably made of fluorine rubber (FPM), which withstands the occurring temperatures as well as mechanical and chemical influences, and represent spring and damping bodies that are elastically deformed by all wing slides 9 in their respective dead center positions because that radial cross-sectional dimension of the O-rings 12 is greater than the distance between the inner end faces 9 'of the wing slide 9, and the inner diameter of the ring grooves 10 in the inner dead position of the wing slide 9.

Beim Umlauf des Rotors 4 in Richtung des Pfeiles 13 bewegen sich die Flügelschieber 9 innerhalb der Schlitze 8 radial hin und her. Diese Bewegung ist durch die Innenfläche 3 des Gehäuse-Zylinders 2 bestimmt, an der die Flügelschieber aufgrund der Fliehkraftwirkung mit ihren äußeren Stirnflächen 9" entlang gleiten. Die Flügelschieber erreichen jeweils die innere Totlage in den Punkten 14 der Innenfläche 3, die von der Drehachse 11 den geringsten Abstand aufweisen. Auf diese Weise berühren und verformen die Flügelschieber 9 mit ihren inneren Stirnflächen 9' in einem Bereich jeweils vor bis nach ihren inneren Totlagen die beiden 0-Ringe 12. Die O-Ringe 12 wirken dadurch als federelastische und dämpfende Anschläge und verhindern, daß die Flügelschieber 9 auf die inneren Begrenzungsflächen der Schlitze 8 im Rotorkörper 6 aufschlagen und dabei sehr starke Geräusche erzeugen. Die elastische Rückformkraft der 0-Ringe 12 bewirkt nach den inneren Totlagen der Flügelschieber 9 deren Beschleunigung aus dieser Ruhelage auch bei niedrigen Drehzahlen des Rotorkörpers 6 mit relativ geringer Fliehkraft, so daß ein Abheben und später folgendes Wieder-aufschlagen der äußeren Stirnflächen 9" der Flügelschieber 9 von und auf die Innenfläche 3 des Gehäuse-Zylinders 2 unter weiterer Geräuschbildung ebenfalls vermieden werden. Außerhalb des Bereiches vor bis nach den inneren Totlagen 14 der Fiügelschieber 9 wirken die O-Ringe 12 nicht auf die Flügelschieber 9 ein, so daß keine zur Fliehkraft zusätzliche Anpreßkraft auf die Innenfläche 3 und somit auch keine dementsprechende Abnutzung entstehen kann. Auch im Bereich der inneren Totlage hält sich die zusätzliche Anpreßkraft aus der Elastizität der 0-Ringe in engen Grenzen, weil bei hohen Drehzahlen die Trägheitswirkung der Flügelschieber 9 einen Großteil der Rückstellkraft der O-Ringe aufzehrt.When the rotor 4 rotates in the direction of the arrow 13, the wing slides 9 move radially back and forth within the slots 8. This movement is determined by the inner surface 3 of the housing cylinder 2, along which the wing slides slide with their outer end faces 9 ″ due to the centrifugal force effect. The wing slides each reach the inner dead center at points 14 of the inner surface 3, which are from the axis of rotation 11 In this way, the wing slides 9 touch and deform with their inner end faces 9 'in a region in each case before to after their inner dead positions, the two 0-rings 12. The O-rings 12 thereby act as resilient and damping stops and prevent the wing slides 9 from hitting the inner boundary surfaces of the slots 8 in the rotor body 6 and thereby generating very strong noises, the elastic restoring force of the 0-rings 12 after the inner dead positions of the wing slides 9 causing their acceleration from this rest position even at low speeds of the Rotor body 6 with a relatively low centrifugal force, so that take off and late he following re-opening of the outer end faces 9 "of the wing slide 9 from and onto the inner surface 3 of the housing cylinder 2 can also be avoided with further noise generation. Outside of the area before to after the inner dead positions 14 of the wing slide 9, the O-rings 12 do not act on the wing slide 9, so that no additional pressing force for the centrifugal force on the inner surface 3 and thus no corresponding wear can occur. The additional contact pressure from the elasticity of the 0- Rings within narrow limits, because at high speeds the inertia effect of the wing slide 9 consumes a large part of the restoring force of the O-rings.

Die Tangentialkomponente der Aufschlagkraft der Flügelschieber 9 auf die O-Ringe 12 im Bereich der inneren Totlagen 14 der Flügelschieber 9, die sich aus der von der radialen Richtung abweichenden Anordnung der Flügelschieber ergibt, bewirkt während des Betriebes ein ständiges Verdrehen der O-Ringe 12 innerhalb der Ringnuten 10 in Richtung des Pfeiles 15. Auf diese Weise werden die O-Ringe 12 auf ihrem gesamten Umfang gleichmäßig beansprucht, so daß sich daraus eine hohe Standfestigkeit der O-Ringe über die gesamte Lebensdauer des Flügelzellenverdichters ergibt.The tangential component of the impact force of the wing slide 9 on the O-rings 12 in the area of the inner dead positions 14 of the wing slide 9, which results from the arrangement of the wing slide deviating from the radial direction, causes the O-rings 12 to rotate continuously during operation the annular grooves 10 in the direction of arrow 15. In this way, the O-rings 12 are evenly stressed over their entire circumference, so that this results in a high stability of the O-rings over the entire life of the vane compressor.

Claims (2)

1. A blade cell compressor,
comprising a rotor (4) mounted in a housing cylinder (2) and provided with blade sliders (9) which are carried so as to be radially movable therein and which slide against the inner surface (3) of the housing cylinder (2), which surface is eccentric to the rotation axis (11) of the rotor (4),
in which the rotor (4) on both front faces (7) has, in each case, an annular groove (10) in the region of the inner front faces (9') of the blade sliders (9) and, in each case within these annular grooves (10), has an elastically deformable ring (12) with a smaller cross-sectional area than the annular groove (10), and
in which the rings (12) co-operate with the inner front faces (9') of the blade sliders (9),
characterised in that
the blade sliders (9) are arranged to deviate by a few degrees of angle from the radial direction, and
that the rings (12) correspond in their internal diameter to the internal diameter of the annular groove (10), have a smaller cross-sectional measurement axially and radially than the annular grooves (12), are constructed so as to be deformable in their cross-section, have a larger radial cross-sectional measurement than the distance between the internal diameter of the annular grooves (12) and the inner front faces (9') of the blade sliders (9) in their inner dead position and, as regards their dimensioning, their deformability and their sliding properties, are coordinated in such a way that the tangential component of the impact force of the blade sliders (9) onto the rings (12) brings about a turning of the same within the annular grooves (10) in the direction (arrow 15) of the tangential force component.
2. A compressor according to Claim 1,
characterised in that
the rings (12) are constructed so as to have a circular cross-section (O-rings).
EP85112898A 1984-05-11 1985-10-11 Vane cell compressor Expired EP0217979B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE19843417491 DE3417491A1 (en) 1984-05-11 1984-05-11 Vane compressor
DE8585112898T DE3562792D1 (en) 1985-10-11 1985-10-11 Vane cell compressor
EP85112898A EP0217979B1 (en) 1985-10-11 1985-10-11 Vane cell compressor
DE19853536368 DE3536368A1 (en) 1984-05-11 1985-10-11 Vane cell compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP85112898A EP0217979B1 (en) 1985-10-11 1985-10-11 Vane cell compressor

Publications (2)

Publication Number Publication Date
EP0217979A1 EP0217979A1 (en) 1987-04-15
EP0217979B1 true EP0217979B1 (en) 1988-05-18

Family

ID=8193817

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85112898A Expired EP0217979B1 (en) 1984-05-11 1985-10-11 Vane cell compressor

Country Status (2)

Country Link
EP (1) EP0217979B1 (en)
DE (1) DE3562792D1 (en)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2117102A1 (en) * 1970-04-07 1971-10-14 K K Toyoda Jidoshokki Seisakusho, Kanya, Aichi (Japan) Rotary piston gas compressor

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1395916A (en) * 1917-09-05 1921-11-01 Carnot Dev Corp Rotary pump
US3473478A (en) * 1967-11-09 1969-10-21 Waukesha Foundry Co Vane pump with annular elastomeric vane-projecting springs
DE3324878A1 (en) * 1982-07-10 1984-01-12 Barmag Barmer Maschinenfabrik Ag, 5630 Remscheid Vane cell vacuum pump
DE3417491A1 (en) * 1984-05-11 1985-11-14 Bayerische Motoren Werke AG, 8000 München Vane compressor

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2117102A1 (en) * 1970-04-07 1971-10-14 K K Toyoda Jidoshokki Seisakusho, Kanya, Aichi (Japan) Rotary piston gas compressor

Also Published As

Publication number Publication date
EP0217979A1 (en) 1987-04-15
DE3562792D1 (en) 1988-06-23

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