EP0153452A1 - Axial blower - Google Patents

Axial blower Download PDF

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Publication number
EP0153452A1
EP0153452A1 EP84113344A EP84113344A EP0153452A1 EP 0153452 A1 EP0153452 A1 EP 0153452A1 EP 84113344 A EP84113344 A EP 84113344A EP 84113344 A EP84113344 A EP 84113344A EP 0153452 A1 EP0153452 A1 EP 0153452A1
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EP
European Patent Office
Prior art keywords
wing
sealing
impeller
axial fan
foot
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
EP84113344A
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German (de)
French (fr)
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EP0153452B1 (en
Inventor
Walter Heingärtner
Werner Kolb
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Turbo-Lufttechnik GmbH
Turbo Lufttechnik GmbH
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Turbo-Lufttechnik GmbH
Turbo Lufttechnik GmbH
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Application filed by Turbo-Lufttechnik GmbH, Turbo Lufttechnik GmbH filed Critical Turbo-Lufttechnik GmbH
Priority to AT84113344T priority Critical patent/ATE31106T1/en
Publication of EP0153452A1 publication Critical patent/EP0153452A1/en
Application granted granted Critical
Publication of EP0153452B1 publication Critical patent/EP0153452B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F04D29/36—Blade mountings adjustable
    • F04D29/362—Blade mountings adjustable during rotation

Definitions

  • the invention relates to an axial fan with the features of the preamble of claim 1.
  • the hub of the impeller and the blades must be made from a corrosion-resistant material or coated with a corrosion-resistant coating.
  • a particularly irritating point is the corrosion-resistant design of the adjustable blades of the impeller and the seal at the point of attachment of the movable blades on the impeller.
  • the invention has for its object to improve the corrosion protection at the attachment point of the blades in a generic axial fan.
  • the heads of the fastening screws no longer come into contact with the corrosive gases.
  • the seals are used in such a way that the relative movement between the seals and the metallic wing foot and not between the seals and the coating that may have been drawn into the bore takes place. These seals are also preloaded so that the preload can follow the inevitable displacements of the wing spar arrangement within the bores of the impeller without leakage and the preload force on the sealing surfaces changes only insignificantly.
  • the axial fan contains a running gear that has a shaft 1 and an impeller 2.
  • the impeller 2 is provided on its end face with a removable cover 3.
  • blades 4 On the circumference of the impeller 2 blades 4 are arranged, which are adjustable to adapt the blower to the desired operating points.
  • the vanes 4 are guided in bores of the impeller 2 and connected to spars 5 arranged in the interior of the impeller 2.
  • the spars 5 are supported by roller bearings 6 in a support ring 7 connected to the shaft 1.
  • an adjusting lever 8 At the lower end of each spar 5, an adjusting lever 8 is attached, which engages in grooves of an adjusting disc 9, which is connected to an adjusting cylinder, not shown.
  • the hub of the impeller 2 is made of a corrosion-resistant material for protection against corrosion by components in the pumped medium (Fig. 4).
  • the hub can also be coated with a corrosion-resistant, non-metallic coating 10, for example a soft or hard rubber coating (FIGS. 2, 3, 5).
  • the coating 10 projects into the bore for receiving the foot 11 of the wing 4.
  • the blades 4 can consist of a corrosion-resistant stainless steel (Fig. 2, 4) or of a non-corrosion-resistant steel, in which case the blade 4 as well as the impeller 2 with a Corrosion-resistant coating 10 is coated (Fig. 3, 5).
  • the coating 10 covers part of the foot 11 of the wing 4.
  • screws 12 which are provided with an Allen head 13. These screws 12 are inserted from the inside of the impeller 2 through a flange 14 of the spar 5 into the foot 11 of the wing 4. The screws 12 are accessible from the front side of the impeller 2 after the removable cover 3 has been removed.
  • the foot 11 of the wing 4 is surrounded by a plurality of sealing rings 16, 16, 17.
  • the inner sealing ring 17 is designed as a flat ring.
  • Several evenly distributed resilient elements press against this sealing ring 17, e.g. in the form of coil springs 18 which are received by a guide bush 19.
  • a preload is introduced into the sealing rings 15, 16, 17 via the coil springs 18.
  • the tension path of the coil springs 18 is so large that, in the event of unavoidable displacements in the wing spar arrangement due to the centrifugal forces occurring when the impeller rotates, the sealing rings 15, 16, 17 always remain pretensioned, since the pretension force can only change insignificantly.
  • the sealing rings 15, 16 have recesses into which star-shaped, deformable rings 20 (quad rings) are inserted. These rings 20 hold the sealing rings 15, 16 in place and prevent the occurrence of relative movements between the sealing rings 15, 16, 17 and the coating 10 of the impeller 2.
  • a surface on serves as a sliding surface 21 on which a relative movement occurs Foot 11 of the wing 4, which is perpendicular to the line of action of the coil springs 18. This area is not included in the coating 10.
  • the sealing rings 15, 16 have sealing lips 22, 23.
  • the sealing lip 22 of the radially outer sealing ring 15 lies against the foot 11 of the wing 4 between the sliding surface 21 and the outer circumference of the impeller 2.
  • an axial groove is also cut into the foot 11 of the wing 4.
  • Flat piston rings 24 made of stainless steel are inserted into this groove.
  • the sealing lip 22 of the sealing ring 15 and the flat piston rings 24 serve to keep coarse dirt away from the sliding surface 21.
  • the sealing lip 23 of the sealing ring 16 is molded onto the radially outer edge of this sealing ring 16 and points obliquely inwards, the sealing lip 23 abutting the foot 11 of the wing 4. Under the action of the centrifugal force and the grease filled in there, the sealing lip 23 is additionally pressed against the foot 11 of the wing 4.
  • FIG. 3 which has wings 4 coated with a coating 10, largely corresponds to the embodiment according to FIG. 2.
  • a static 0-ring seal 25 and a metallic seal bushing 26 are provided for the perfect sealing of the transition of the coating 10 of the wing 4 into the uncoated part of the wing 4 14 of the spar 5 and the foot 11 of the wing 4 used.
  • the sliding surface 21 is here also outside of the coating 10, namely between the seal bushing 26 and the outer sealing ring 15.
  • the 0-ring seal 25 applied to the coating 10 of the wing 4 is covered by the projecting flange 14 of the spar 5 and by the sealing liner 26 is biased, thereby forming a perfect seal between the coating 10 and the f-western, non-coated part of the wing 4 is achieved.
  • compressed O-rings 29, 30 made of an elastic polymer are used as resilient elements for pressing on the sealing rings 27, 28 used there.
  • the 0-rings 29, 30 rest on the hub of the impeller 2. They get their preload by screwing the screw 12 in the wing 4.
  • the O-rings 29, 30 have the task of sealing the wings 4 against the impeller 2 and securing the sealing rings 27, 28 against rotation.
  • sealing rings 27, 28 are arranged one behind the other, which have diameters of different sizes.
  • Each sealing ring 27, 28 is pressed on by its own 0-ring 29, 30.
  • the sealing surface of the sealing rings 27, 28 is opposite a metallic surface of the foot 11 of the wing 4 as a sliding surface 21.
  • a further seal in the form of a grooved ring 31 is provided in front of the sealing rings 27, 28.
  • the groove of the grooved ring 31 faces the inside of the impeller 2.
  • the edges of the groove ring 31, which limit the groove lie against the wall of the bore of the hub and against the foot 11 of the wing 4 or against the seal bushing 26 when the impeller 2 rotates under the influence of the centrifugal force.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1. Axial flow fan with a fan wheel (2) having holes through which adjustable-pitch blades (4) are passed and which are sealed by sealing rings (15, 16, 17, 27, 28), the root (11) of each blade (4) being connected by screws (12) to a shaft (5) arranged inside the fan wheel, characterized in that the screws (12) are passed from the fan wheel inside through a flange (14) of shaft (5) into the root (11) of blade (4), that the sealing rings (15, 16, 17, 27, 28) are prestressed radially to the fan wheel (2) by resilient elements and pressed against a sliding face (21) at the root (11) of blade (4) located perpendicular to the line of force of the resilient elements and that the prestress deflection of the resilient elements is greater than the displacement caused by centrifugal forces in the area of the sealing rings (15, 16, 17, 27, 28).

Description

Die Erfindung betrifft ein Axialgebläse mit den Merkmalen des Oberbegriffes des Anspruches 1.The invention relates to an axial fan with the features of the preamble of claim 1.

Wenn derartige Axialgebläse für die Förderung von feuchten Abgasen mit hochkorrosiven Schwefel- und Chloridbestandteilen zum Beispiel als Saugzuggebläse hinter Rauchgasentschwefelungsanlagen eingesetzt werden sollen, so sind die Nabe des Laufrades und die Flügel aus einem korrosionsbeständigen Werkstoff zu fertigen oder mit einer korrosionsbeständigen Beschichtung zu überziehen. Ein besonders irritischer Punkt ist dabei die korrosionsbeständige Ausbildung der verstellbaren Flügel des Laufrades und die Abdichtung an der Befestigungsstelle der beweglichen Flügel auf dem Laufrad.If such axial fans are to be used for the conveyance of moist exhaust gases with highly corrosive sulfur and chloride components, for example as suction fans behind flue gas desulfurization systems, then the hub of the impeller and the blades must be made from a corrosion-resistant material or coated with a corrosion-resistant coating. A particularly irritating point is the corrosion-resistant design of the adjustable blades of the impeller and the seal at the point of attachment of the movable blades on the impeller.

Der Erfindung liegt die Aufgabe zugrunde, bei einem gattungsgemäßen Axialgebläse den Korrosionsschutz an der Befestigungsstelle der Flügel zu verbessern.The invention has for its object to improve the corrosion protection at the attachment point of the blades in a generic axial fan.

Diese Aufgabe wird erfindungsgemäß durch die Merkmale des Anspruches 1 gelöst. Vorteilhafte Ausgestaltungen der Erfindung sind in den Unteransprüchen angegeben.This object is achieved by the features of claim 1. Advantageous embodiments of the invention are specified in the subclaims.

Bei dem erfindungsgemäßen Axialgebläse kommen die Köpfe der Befestigungsschrauben mit den korrosiven Gasen nicht mehr in Berührung. Die Dichtungen sind so eingesetzt, daß die Relativbewegung zwischen den Dichtungen und dem metallischen Flügelfuß und nicht zwischen den Dichtungen und der unter Umständen in die Bohrung eingezogenen Beschichtung stattfindet. Diese Dichtungen sind darüber hinaus so vorgespannt, daß die Vorspannung auch den unvermeidlichen Verlagerungen der Flügelholmanordnung innerhalb der Bohrungen des Laufrades ohne Leckage folgen kann und sich die Vorspannkraft an den Dichtflächen nur unwesentlich ändert.In the axial fan according to the invention, the heads of the fastening screws no longer come into contact with the corrosive gases. The seals are used in such a way that the relative movement between the seals and the metallic wing foot and not between the seals and the coating that may have been drawn into the bore takes place. These seals are also preloaded so that the preload can follow the inevitable displacements of the wing spar arrangement within the bores of the impeller without leakage and the preload force on the sealing surfaces changes only insignificantly.

Mehrere Ausführungsbeispiele der Erfindung sind in der Zeichnung dargestellt und werden im folgenden näher erläutert. Es zeigen:

  • n. 1 den Längsschnitt durch ein Laufrad eines Axialgebläses gemäß der Erfindung und
  • Fig. 2 bis 5 die Einzelheit Z nach Fig. 1 in verschiedenen Ausführungsformen.
Several embodiments of the invention are shown in the drawing and are explained in more detail below. Show it:
  • 1 shows the longitudinal section through an impeller of an axial fan according to the invention and
  • Fig. 2 to 5, the detail Z of FIG. 1 in different embodiments.

Das Axialgebläse enthält ein Laufzeug, das eine Welle 1 und ein Laufrad 2 aufweist. Das Laufrad 2 ist an seiner Stirnseite mit einem abnehmbaren Deckel 3 versehen.The axial fan contains a running gear that has a shaft 1 and an impeller 2. The impeller 2 is provided on its end face with a removable cover 3.

Auf dem Umfang des Laufrades 2 sind Flügel 4 angeordnet, die zur Anpassung des Gebläses an die gewünschten Betriebspunkte verstellbar sind. Die Flügel 4 sind in Bohrungen des Laufrades 2 geführt und mit im Inneren des Laufrades 2 angeordneten Holmen 5 verbunden. Die Holme 5 sind über Wälzlager 6 in einem mit der Welle 1 verbundenen Tragring 7 gelagert. An dem unteren Ende jedes Holmes 5 ist ein Verstellhebel 8 befestigt, der in Nuten einer Verstellscheibe 9 eingreift, die mit einem nicht dargestellten Verstellzylinder verbunden ist.On the circumference of the impeller 2 blades 4 are arranged, which are adjustable to adapt the blower to the desired operating points. The vanes 4 are guided in bores of the impeller 2 and connected to spars 5 arranged in the interior of the impeller 2. The spars 5 are supported by roller bearings 6 in a support ring 7 connected to the shaft 1. At the lower end of each spar 5, an adjusting lever 8 is attached, which engages in grooves of an adjusting disc 9, which is connected to an adjusting cylinder, not shown.

Die Nabe des Laufrades 2 ist zum Schutz gegen Korrosion durch Bestandteile im Fördermedium aus einem korrosionsbeständigen Werkstoff gefertigt (Fig. 4). Die Nabe kann auch mit einer korrosionsbeständigen, nichtmetallischen Beschichtung 10, z.B. einer Weich- oder auch Hartgummierung, überzogen sein (Fig. 2, 3, 5). In diesem Fall ragt die Beschichtung 10 in die Bohrung zur Aufnahme des Fußes 11 des Flügels 4 hinein. Die Flügel 4 können aus einem korrosionsbeständigen Edelstahl (Fig. 2, 4) oder aus einem nicht korrosionsbeständigen Stahl bestehen, wobei in diesem Fall der Flügel 4 ebenso wie Laufrad 2 mit einer korrosionsbeständigen Beschichtung 10 überzogen ist (Fig. 3, 5). Dabei überdeckt die Beschichtung 10 einen Teil des Fußes 11 des Flügels 4.The hub of the impeller 2 is made of a corrosion-resistant material for protection against corrosion by components in the pumped medium (Fig. 4). The hub can also be coated with a corrosion-resistant, non-metallic coating 10, for example a soft or hard rubber coating (FIGS. 2, 3, 5). In this case, the coating 10 projects into the bore for receiving the foot 11 of the wing 4. The blades 4 can consist of a corrosion-resistant stainless steel (Fig. 2, 4) or of a non-corrosion-resistant steel, in which case the blade 4 as well as the impeller 2 with a Corrosion-resistant coating 10 is coated (Fig. 3, 5). The coating 10 covers part of the foot 11 of the wing 4.

Die Befestigung der Flügel 4 an den Holmen 5 erfolgt nach den Fig. 2 bis 5 durch Schrauben 12, die mit einem Innensechskantkopf 13 versehen sind. Diese Schrauben 12 sind vom Inneren des Laufrades 2 her durch einen Flansch 14 des Holmes 5 in den Fuß 11 des Flügels 4 eingesetzt. Die Schrauben 12 sind nach dem Lösen des abnehmbaren Deckels 3 von der Stirnseite des Laufrades 2 her zugänglich.The attachment of the wings 4 to the spars 5 is carried out according to FIGS. 2 to 5 by screws 12 which are provided with an Allen head 13. These screws 12 are inserted from the inside of the impeller 2 through a flange 14 of the spar 5 into the foot 11 of the wing 4. The screws 12 are accessible from the front side of the impeller 2 after the removable cover 3 has been removed.

Der Fuß 11 des Flügels ,4 ist von mehreren Dichtringen 16, 16, 17 umschlossen. Der innenliegende Dichtring 17 ist als Flachring ausgebildet. Gegen diesen Dichtring 17 drücken mehrere gleichmäßig verteilte federnde Elemente, z.B. in Form von Schraubenfedern 18, die von einer Führungsbuchse 19 aufgenommen sind. über die Schraubenfedern 18 wird in die Dichtringe 15, 16, 17 eine Vorspannung eingebracht. Dabei ist der Verspannungsweg der Schraubenfedern 18 so groß, daß bei unvermeidlichen Verlagerungen in der Flügelholmanordnung infolge der bei Rotation des Laufrades auftretenden Zentrifugalkräfte die Dichtringe 15, 16, 17 stets vorgespannt bleiben, da sich die Vorspannkraft nur unwesentlich ändern kann.The foot 11 of the wing 4 is surrounded by a plurality of sealing rings 16, 16, 17. The inner sealing ring 17 is designed as a flat ring. Several evenly distributed resilient elements press against this sealing ring 17, e.g. in the form of coil springs 18 which are received by a guide bush 19. A preload is introduced into the sealing rings 15, 16, 17 via the coil springs 18. The tension path of the coil springs 18 is so large that, in the event of unavoidable displacements in the wing spar arrangement due to the centrifugal forces occurring when the impeller rotates, the sealing rings 15, 16, 17 always remain pretensioned, since the pretension force can only change insignificantly.

Die Dichtringe 15, 16 weisen Ausnehmungen auf, in die sternförmige, verformbare Ringe 20 (Quadringe) eingelegt sind. Diese Ringe 20 halten die Dichtringe 15, 16 an der vorgesehenen Stelle fest und verhindern ein Auftreten von Relativbewegungen zwischen den Dichtringen 15, 16, 17 und der Beschichtung 10 des Laufrades 2. Als Gleitfläche 21, an der eine Relativbewegung auftritt, dient eine Fläche am Fuß 11 des Flügels 4, die senkrecht zur Wirkungslinie der Schraubenfedern 18 liegt. Diese Fläche ist nicht in die Beschichtung 10 einbezogen. Die Dichtringe 15, 16 weisen Dichtlippen 22, 23 auf. Die Dichtlippe 22 des radial äußeren Dichtringes 15 legt sich zwischen der Gleitfläche 21 und dem Außenumfang des Laufrades 2 an den Fuß 11 des Flügels 4 an.The sealing rings 15, 16 have recesses into which star-shaped, deformable rings 20 (quad rings) are inserted. These rings 20 hold the sealing rings 15, 16 in place and prevent the occurrence of relative movements between the sealing rings 15, 16, 17 and the coating 10 of the impeller 2. A surface on serves as a sliding surface 21 on which a relative movement occurs Foot 11 of the wing 4, which is perpendicular to the line of action of the coil springs 18. This area is not included in the coating 10. The sealing rings 15, 16 have sealing lips 22, 23. The sealing lip 22 of the radially outer sealing ring 15 lies against the foot 11 of the wing 4 between the sliding surface 21 and the outer circumference of the impeller 2.

Vor der Gleitfläche 21 ist weiterhin in den Fuß 11 des Flügels 4 eine axiale Nut eingeschnitten. In diese Nut sind Flachkolbenringe 24 aus Edelstahl eingelegt. Die Dichtlippe 22 des Dichtringes 15 und die Flachkolbenringe 24 dienen dazu, groben Schmutz von der Gleitfläche 21 fernzuhalten.In front of the sliding surface 21, an axial groove is also cut into the foot 11 of the wing 4. Flat piston rings 24 made of stainless steel are inserted into this groove. The sealing lip 22 of the sealing ring 15 and the flat piston rings 24 serve to keep coarse dirt away from the sliding surface 21.

Die Dichtlippe 23 des Dichtringes 16 ist an den radial äußeren Rand dieses Dichtringes 16 angeformt und weist schräg nach innen, wobei die Dichtlippe 23 sich an den Fuß 11 des Flügels 4 anlegt. Unter der Wirkung der Zentrifugalkraft und des dort eingefüllten Fettes wird die Dichtlippe 23 zusätzlich gegen den Fuß 11 des Flügels 4 angepreßt.The sealing lip 23 of the sealing ring 16 is molded onto the radially outer edge of this sealing ring 16 and points obliquely inwards, the sealing lip 23 abutting the foot 11 of the wing 4. Under the action of the centrifugal force and the grease filled in there, the sealing lip 23 is additionally pressed against the foot 11 of the wing 4.

Die Ausführungsform nach Fig. 3, die mit einer Beschichtung 10 beschichtete Flügel 4 aufweist, stimmt weitgehend mit der Ausführungsform nach Fig. 2 überein. Zur einwandfreien Abdichtung des Überganges der Beschichtung 10 des Flügels 4 in den unbeschichteten Teil des Flügels 4 ist eine statische 0-Ring-Abdichtung 25 und eine metallische Dichtungslaufbüchse 26 vorgesehene Die metallische Dichtungslaufbüchse 26 ist innerhalb der Bohrung des Laufrades 2 zwischen einem überstehenden Teil des Flansches 14 des Holmes 5 und dem Fuß 11 des Flügels 4 eingesetzt. Die Gleitfläche 21 liegt auch hier außerhalb der Beschichtung 10, und zwar zwischen der Dichtungslaufbüchse 26 und dem äußeren Dichtring 15. Die an der Beschichtung 10 des Flügels 4 anliegende 0-Ring-Abdichtung 25 wird durch den überstehenden Flansch 14 des Holmes 5 und durch die Dichtungslaufbüchse 26 vorgespannt, wodurch eine einwandfreie Abdichtung zwischen der Beschichtung 10 und dem festlichen, nicht beschichteten Teil des Flügels 4 erreicht wird.The embodiment according to FIG. 3, which has wings 4 coated with a coating 10, largely corresponds to the embodiment according to FIG. 2. A static 0-ring seal 25 and a metallic seal bushing 26 are provided for the perfect sealing of the transition of the coating 10 of the wing 4 into the uncoated part of the wing 4 14 of the spar 5 and the foot 11 of the wing 4 used. The sliding surface 21 is here also outside of the coating 10, namely between the seal bushing 26 and the outer sealing ring 15. The 0-ring seal 25 applied to the coating 10 of the wing 4 is covered by the projecting flange 14 of the spar 5 and by the sealing liner 26 is biased, thereby forming a perfect seal between the coating 10 and the f-western, non-coated part of the wing 4 is achieved.

Bei den in den Fig. 4 und 5 dargestellten Ausführungsformen sind als federnde Elemente für das Andrücken der dort verwendeten Dichtringe 27, 28 komprimierte 0-Ringe 29, 30 aus einem elastischen Polymer eingesetzt. Die 0-Ringe 29, 30 liegen an der Nabe des Laufrades 2 an. Sie erhalten ihre Vorspannung durch das Einschrauben der Schraube 12 in den Flügel 4. Außer dem Andrücken der Dichtringe 27, 28 haben die O-Ringe 29, 30 die Aufgabe, die Flügel 4 gegenüber dem Laufrad 2 abzudichten und die Dichtringe 27, 28 gegen Verdrehen zu sichern.In the embodiments shown in FIGS. 4 and 5, compressed O-rings 29, 30 made of an elastic polymer are used as resilient elements for pressing on the sealing rings 27, 28 used there. The 0-rings 29, 30 rest on the hub of the impeller 2. They get their preload by screwing the screw 12 in the wing 4. In addition to pressing the sealing rings 27, 28, the O-rings 29, 30 have the task of sealing the wings 4 against the impeller 2 and securing the sealing rings 27, 28 against rotation.

In radialer Richtung sind mehrere, vorzugsweise zwei Dichtringe 27, 28 hintereinander angeordnet, die unterschiedlich große Durchmesser aufweisen. Jeder Dichtring 27, 28 wird durch einen eigenen 0-Ring 29, 30 angedrückt. Auch hier liegt der Dichtfläche der Dichtringe 27, 28 eine metallische Fläche des Fußes 11 des Flügels 4 als Gleitfläche 21 gegenüber. Zum Inneren des Laufrades 2 hin ist vor den Dichtringen 27, 28 eine weitere Dichtung in Form eines Nutringes 31 vorgesehen. Die Nut des Nutringes 31 ist dem Inneren des Laufrades 2 zugewandt. Die die Nut.begrenzenden Ränder des Nutringes 31 legen sich bei Rotation des Laufrades 2 unter dem Einfluß der Zentrifugalkraft dichtend an die Wand der Bohrung der Nabe und an den Fuß 11 des Flügels 4 oder an die Dichtungslaufbuchse 26 an.In the radial direction, several, preferably two sealing rings 27, 28 are arranged one behind the other, which have diameters of different sizes. Each sealing ring 27, 28 is pressed on by its own 0-ring 29, 30. Here, too, the sealing surface of the sealing rings 27, 28 is opposite a metallic surface of the foot 11 of the wing 4 as a sliding surface 21. To the inside of the impeller 2, a further seal in the form of a grooved ring 31 is provided in front of the sealing rings 27, 28. The groove of the grooved ring 31 faces the inside of the impeller 2. The edges of the groove ring 31, which limit the groove, lie against the wall of the bore of the hub and against the foot 11 of the wing 4 or against the seal bushing 26 when the impeller 2 rotates under the influence of the centrifugal force.

Claims (8)

1. Axialgebläse mit einem Laufrad (2), das Bohrungen aufweist, durch die verstellbare Flügel (4) hindurchgeführt und über Dichtringe (15, 16, 17, 27, 28) abgedichtet sind, wobei der Fuß (11) jedes Flügels (4) über Schrauben (12) mit einem im Inneren des Laufrades angeordneten Holm (5) verbunden ist, dadurch gekennzeichnet , daß die Schrauben (12) vom Laufradinneren her durch einen Flansch (14) des Holmes (5) in den Fuß (11) des Flügels (4) geführt sind und daß die Dichtringe (15, 16, 17, 27, 28) gegen eine Gleitfläche (21) am Fuß (11) des Flügels (4) gedrückt und durch federnde Elemente vorgespannt sind, deren Vorspannweg größer ist als die Verlagerung im Bereich der Dichtringe (15, 16, 17, 27, 28).1. axial fan with an impeller (2) which has bores, is guided through the adjustable blades (4) and is sealed by means of sealing rings (15, 16, 17, 27, 28), the foot (11) of each blade (4) Is connected via screws (12) to a spar (5) arranged inside the impeller, characterized in that the screws (12) from the inside of the impeller through a flange (14) of the spar (5) into the foot (11) of the wing (4) are guided and that the sealing rings (15, 16, 17, 27, 28) are pressed against a sliding surface (21) at the base (11) of the wing (4) and are prestressed by resilient elements, the prestressing path of which is greater than that Relocation in the area of the sealing rings (15, 16, 17, 27, 28). 2. Axialgebläse nach Anspruch 1, dadurch gekennzeichnet , daß die Bohrung in der Nabe des Laufrades (2) und/oder ein Teil des in die Bohrung eingreifenden Fußes (11) des Flügels (4) mit einer nichtmetallischen Beschichung (10) überzogen ist und daß die Dichtfläche der Dichtringe (15, 16, 17, 27, 28) auf einer metallischen Gleitfläche (21) am Fuß (11) des Flügels (4) aufliegt.2. Axial fan according to claim 1, characterized in that the bore in the hub of the impeller (2) and / or part of the engaging foot in the bore (11) of the wing (4) is coated with a non-metallic coating (10) and that the sealing surface of the sealing rings (15, 16, 17, 27, 28) rests on a metallic sliding surface (21) at the base (11) of the wing (4). 3. Axialgebläse nach Anspruch 1 oder 2, dadurch gekennzeichnet , daß der radial äußere Dichtring (15) mit einer die Dichtfläche (21) nach außen überragenden Dichtlippe (22) versehen ist, die sich an den Fuß (11) des Flügels (4) anlegt.3. Axial fan according to claim 1 or 2, characterized in that the radially outer sealing ring (15) is provided with a sealing surface (21) outwardly projecting sealing lip (22) which is located on the foot (11) of the wing (4) creates. 4. Axialgebläse nach einem oder mehreren der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß radial außen von der Dichtfläche (21) in dem Fuß (11) des Flügels (4) eine Nut vorgesehen ist, in die Flachkolbenringe (24) aus Edelstahl eingelegt sind.4. Axial fan according to one or more of claims 1 to 3, characterized in that a groove is provided radially outside of the sealing surface (21) in the foot (11) of the wing (4), inserted in the flat piston rings (24) made of stainless steel are. 5. Axialgebläse nach einem oder mehreren der Ansprüche 1 bis 4, dadurch gekennzeichnet , daß die federnden Elemente aus Schraubenfedern (18) bestehen.5. Axial fan according to one or more of claims 1 to 4, characterized in that the resilient elements consist of coil springs (18). 6. Axialgebläse nach einem oder mehreren der Ansprüche 1 bis 4, dadurch gekennzeichnet , daß die federnden Elemente aus komprimierten 0-Ringen (29, 30) bestehen.6. Axial fan according to one or more of claims 1 to 4, characterized in that the resilient elements consist of compressed 0-rings (29, 30). 7. Axialgebläse nach Anspruch 6, dadurch gekennzeichnet , daß in radialer Richtung hintereinander mehrere, jeweils durch einen komprimierten 0-Ring (29, 30) belastete Dichtringe (27, 28) angeordnet sind.7. Axial fan according to claim 6, characterized in that in the radial direction one behind the other, each by a compressed 0-ring (29, 30) loaded sealing rings (27, 28) are arranged. 8. Axialgebläse nach einem oder mehreren der Ansprüche 1 bis 7, dadurch gekennzeichnet , daß radial innen von den Dichtringen (15, 16, 17, 27, 28) ein Nutring (31) mit einer zum Inneren des Laufrades (2) hinweisenden Nut angeordnet ist und daß die die Nut begrenzenden Ränder des Nutringes (31) sich unter dem Einfluß der Zentrifugalkraft nach außen legen.8. Axial fan according to one or more of claims 1 to 7, characterized in that radially inside of the sealing rings (15, 16, 17, 27, 28) a groove ring (31) with an inside of the impeller (2) pointing groove and that the edges of the groove ring (31) delimiting the groove lie outwards under the influence of the centrifugal force.
EP84113344A 1984-02-03 1984-11-06 Axial blower Expired EP0153452B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT84113344T ATE31106T1 (en) 1984-02-03 1984-11-06 AXIAL FAN.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3403674 1984-02-03
DE3403674A DE3403674C1 (en) 1984-02-03 1984-02-03 Axial fan

Publications (2)

Publication Number Publication Date
EP0153452A1 true EP0153452A1 (en) 1985-09-04
EP0153452B1 EP0153452B1 (en) 1987-11-25

Family

ID=6226610

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Application Number Title Priority Date Filing Date
EP84113344A Expired EP0153452B1 (en) 1984-02-03 1984-11-06 Axial blower

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EP (1) EP0153452B1 (en)
JP (1) JPS6134399A (en)
AT (1) ATE31106T1 (en)
CA (1) CA1282752C (en)
DE (2) DE3403674C1 (en)
ES (1) ES8704593A1 (en)
MX (1) MX161116A (en)
ZA (1) ZA849876B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106337838A (en) * 2016-10-21 2017-01-18 珠海格力电器股份有限公司 Centrifugal compressor and air conditioner with same
CN112283159A (en) * 2020-11-20 2021-01-29 西安热工研究院有限公司 Sealing structure for blade root of rotor blade of dynamic air adjusting fan

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1635315A (en) * 1925-10-19 1927-07-12 Carl F Ehinger Automobile fan
CH220098A (en) * 1941-08-05 1942-03-15 Escher Wyss Maschf Ag Seal on controllable pitch propellers, in which the wing and wing shaft are detachably connected to one another.
GB592065A (en) * 1943-09-15 1947-09-05 Englesson John Elov Improvements in packings for adjustable blades of water turbines, ship's propellers and the like
CH264087A (en) * 1947-06-18 1949-09-30 Nydqvist & Holm Ab Sealing device for vane pins rotatably mounted in a hub filled with liquid.
GB651569A (en) * 1949-11-24 1951-04-04 Aerex Australia Company Improvements in hubs of screw fan impellers
US3037458A (en) * 1957-04-15 1962-06-05 Goulds Pumps Glass pump
FR1529422A (en) * 1966-07-05 1968-06-14 Karlstad Mekaniska Ab Sealing device
EP0104343A1 (en) * 1982-09-06 1984-04-04 Balcke-Dürr AG Fluid flow machine with adjustable blades

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT340032B (en) * 1975-01-11 1977-11-25 Voith Getriebe Kg AXIAL BLOWER WITH CONTINUOUSLY ADJUSTABLE IMPELLER BLADES

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1635315A (en) * 1925-10-19 1927-07-12 Carl F Ehinger Automobile fan
CH220098A (en) * 1941-08-05 1942-03-15 Escher Wyss Maschf Ag Seal on controllable pitch propellers, in which the wing and wing shaft are detachably connected to one another.
GB592065A (en) * 1943-09-15 1947-09-05 Englesson John Elov Improvements in packings for adjustable blades of water turbines, ship's propellers and the like
CH264087A (en) * 1947-06-18 1949-09-30 Nydqvist & Holm Ab Sealing device for vane pins rotatably mounted in a hub filled with liquid.
GB651569A (en) * 1949-11-24 1951-04-04 Aerex Australia Company Improvements in hubs of screw fan impellers
US3037458A (en) * 1957-04-15 1962-06-05 Goulds Pumps Glass pump
FR1529422A (en) * 1966-07-05 1968-06-14 Karlstad Mekaniska Ab Sealing device
EP0104343A1 (en) * 1982-09-06 1984-04-04 Balcke-Dürr AG Fluid flow machine with adjustable blades

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106337838A (en) * 2016-10-21 2017-01-18 珠海格力电器股份有限公司 Centrifugal compressor and air conditioner with same
CN112283159A (en) * 2020-11-20 2021-01-29 西安热工研究院有限公司 Sealing structure for blade root of rotor blade of dynamic air adjusting fan

Also Published As

Publication number Publication date
ES8704593A1 (en) 1987-04-01
EP0153452B1 (en) 1987-11-25
ES540017A0 (en) 1987-04-01
DE3467796D1 (en) 1988-01-07
MX161116A (en) 1990-07-31
JPS6134399A (en) 1986-02-18
ZA849876B (en) 1985-12-24
DE3403674C1 (en) 1985-06-05
CA1282752C (en) 1991-04-09
ATE31106T1 (en) 1987-12-15

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