EP2418389B1 - Impeller for a ventilator - Google Patents

Impeller for a ventilator Download PDF

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Publication number
EP2418389B1
EP2418389B1 EP11006483.9A EP11006483A EP2418389B1 EP 2418389 B1 EP2418389 B1 EP 2418389B1 EP 11006483 A EP11006483 A EP 11006483A EP 2418389 B1 EP2418389 B1 EP 2418389B1
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EP
European Patent Office
Prior art keywords
fan blade
impeller
flow element
edge
fan
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.)
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Application number
EP11006483.9A
Other languages
German (de)
French (fr)
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EP2418389A2 (en
EP2418389A3 (en
Inventor
Michael Stephan
Ralf Neumeier
Volker Kress
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.)
Ziehl Abegg SE
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Ziehl Abegg SE
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Publication date
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Priority to SI201132093T priority Critical patent/SI2418389T1/en
Publication of EP2418389A2 publication Critical patent/EP2418389A2/en
Publication of EP2418389A3 publication Critical patent/EP2418389A3/en
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Publication of EP2418389B1 publication Critical patent/EP2418389B1/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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • the invention relates to an impeller for a fan according to the preamble of claim 1.
  • Fans and impellers are known ( DE 20 2004 005 548 U1 ), in which fan blades protrude from the hub of the impeller wheel, which are designed to be wound and are provided with a flow element on the radially outer edge.
  • the fan blades have approximately the cross-sectional shape of an airplane wing.
  • the flow elements on the outer edge of these fan blades have a similar course.
  • the outer edge of the flow elements runs approximately parallel to the top and bottom of the cross-section of the associated fan blades.
  • the axial height of the flow elements decreases to almost zero.
  • Such a design is intended to at least reduce noise development during operation of the impeller or the fan.
  • the flow elements provide increased resistance to the leakage flow that travels around the radially outer edge of the fan blades from the pressure side to the suction side.
  • a compressor blade for a compressor ( EP 1 624 192 A1 ), to arrange a sealing lip on the radially outer edge of the compressor blade, extending radially outward from the compressor blade.
  • the sealing lip is narrower than the blade profile and extends from a leading edge to a trailing edge of the compressor blade.
  • the sealing lip has a constant radial and axial height and thickness over its length.
  • the invention is based on the object of designing the impeller of the generic type in such a way that, with a simple structural design, very little noise is achieved during operation.
  • the impeller according to the invention is characterized in that the axial height of the flow element has a maximum in the area of the front and rear edges of the fan blades.
  • the height of the airfoil decreases towards the center of the fan blade. Due to this design of the flow element, there is an excellent noise reduction when using the impeller and an optimal, unhindered flow of air from the pressure side to the suction side, which promotes the noise reduction.
  • the ratio of the axial height of the flow element to the axial thickness of the fan blade decreases from the maximum towards the center of the fan blade.
  • the height of the flow element can decrease to 0 in the area between the leading and the trailing edge of the fan blade.
  • the fan has a housing 1 with a cylindrical casing 2 which encloses a conveying duct 3 .
  • a conveying duct 3 In the conveying channel 3 there is an impeller 4, the hub 5 of which is rotatably mounted in a known manner.
  • the impeller 4 is rotatably driven counterclockwise in the direction of arrow 6 by means of a drive 4a.
  • fan blades 7 protrude from the hub 5 and extend close to the jacket 2 .
  • the air flows like 6 shows, between the radially outer edge of the fan blades 7 and the inside of the jacket 2 from the pressure side 9 essentially without interference to the suction side 8 of the impeller 4.
  • the fan blades 7 are unevenly distributed over the circumference of the hub 5 .
  • the impeller 4 can also be designed in such a way that the fan blades 7 are distributed uniformly over the circumference of the hub 5 .
  • the fan blades 7 each have a front edge 10 in the direction of rotation 6 and a rear edge 11 at the rear in the direction of rotation 6.
  • the front edge 10 is crescent-shaped as seen in the axial direction of the impeller 4, i.e. it has a concave profile.
  • the leading edge 10 extends from the hub 5 to the outer edge 12 which extends in the circumferential direction of the impeller 4 .
  • the outer edge 12 has the radial distance 13 ( 6 ) from the housing shell 2. This distance is like this chosen so that the loss flow is as low as possible and a low noise level occurs.
  • Such a design of the fan blades 7 results in a reduction in noise during operation of the fan and an improvement in the tearing behavior.
  • the trailing edge 11 of the fan blade 7 is convex over at least part of its length.
  • the convex progression can be provided from the hub 5 to the outer edge 12 of the fan blade.
  • this convex course can only be provided in the region of the rear edge 11 adjoining the outer edge 12 .
  • the trailing edge 11 is provided with teeth 15 over part of its length, each tapering towards its free end.
  • the teeth 15 can have the same outline shape.
  • the teeth 15 are designed in such a way that their ends, which advantageously taper to a point, project up to a convex envelope line 16 ( 4 and 7 ).
  • This envelope line 16 can advantageously form a continuation of the non-toothed area of the trailing edge 11 .
  • the teeth 15 can also have different outline shapes and/or different lengths along the trailing edge 11 . By selecting the design of the teeth 15 appropriately, the noise development of the fan can be optimally adapted to the respective application.
  • the fan blades 7 are designed as twisted blades.
  • each fan blade 7 is in the embodiment according to Figures 1 to 6 provided with a flow element 17, which advantageously extends over the entire length of the outer edge 12 between the front edge 10 and the rear edge 11.
  • the flow elements extend on the outer edge 12 to the suction side 8 of the fan blade 7.
  • the flow element 17 it is also possible for the flow element 17 to extend both to the suction side 8 and to the pressure side 9. It is also possible for the flow element 17 to protrude only in the direction of the pressure side 9 .
  • the flow elements 17 are advantageously designed in one piece with the fan blades 7, but in principle they can also be components that are separate from the fan blades and are attached to the fan blades in a suitable manner.
  • the flow element 17 has its greatest height h in the region of the front and rear edges 10, 11 of the fan blade 7, measured in the axial direction 18 of the blade wheel 4 ( figure 5 ).
  • the flow element 17 and the profile of the associated fan blade 7 are shown at the level of the flow element 17 .
  • the axial height h of the flow element 17 decreases from the front edge 10 or the rear edge 11 until the flow element 17 has a height of 0 or approximately 0 in the region between the two edges 10, 11. This area can be half the width of the fan blade 7 .
  • the fan blade 7 has the axial thickness d in the area of the flow element 17 . In the rest of the area, the fan blade 7 can have different axial thicknesses.
  • the axial height h of the flow element 17 and the axial thickness d of the fan blade 7 are coordinated in such a way that the ratio h/d decreases from the front edge 10 and the rear edge 11, as shown by the dashed line 19 in figure 5 shows. In the area in which the axial height h des Flow element 17 is almost 0, this ratio h / d is lowest.
  • the flow element 17 can also be designed in such a way that its minimum axial height is not half the width of the fan blade 7 . It is essential that the given ratio h/d decreases from the leading edge 10 or the trailing edge 11 . Such a design of the fan blade with flow element results in excellent noise reduction when using the fan.
  • the fan blade 7 has an aircraft wing profile shape. In the area of the front edge 10 the fan blade 7 is rounded off, while in the area of the rear edge 11 it tapers to a point. In the area between the two edges 10, 11, the fan blade 7 can also have an approximately constant cross-sectional thickness.
  • the fan blade 7 has a large inlet area 20 ( 6 ) at the transition from fan blade 7 to flow element 17, preferably with a large radius 27. This makes an excellent contribution to low-noise operation of the fan.
  • the flow element 17 is designed such that its axial extent increases very sharply starting from the front edge 10 of the fan blade 7 over a very short area until the flow element has its greatest axial height h at a small distance from the front edge 10 .
  • the axial height h of the flow element 17 increases greatly from the trailing edge 11 of the fan blade 7 over a very short area until the flow element has its greatest axial height h in this area at a small distance from the trailing edge 10, which is in the direction of the center of the fan blade 7 decreases. Due to this design, the flow element 17 has a completely different course than the fan blade 7 in the area of the flow element 17.
  • FIGS. 7 to 11 show a twisted fan blade 7 which, instead of the flow element 17 in the radially outer area, has such a design that it has the same effect as a fan blade with a flow element, despite the lack of a flow element 17. This is achieved through a special design of the fan blade, which is described in more detail below.
  • the fan blade 7 has the profile sections 24.1 to 24.7 at equal intervals over its radial length, which have a similar cross-sectional configuration.
  • the fan blade 7 has an aircraft wing profile shape, in which the fan blade 7 is rounded off in the area of the front edge 10 and tapered in the area of the rear edge 11 .
  • the outer edge 12 of the fan blade 7 pointing towards the housing casing 2 is shaped in such a way that the radially outer profile section of the fan blade is shifted towards the suction side 8 .
  • different profile sections 21, 21.1 to 21.7 are given over the length of the fan blade.
  • the profile sections are cylindrical sections through the fan blade 7.
  • the profile sections 21.1 to 21.7 are provided at equal intervals in the radial direction of the fan blade 7.
  • the profile section 21.7 ( 7 ) is provided on the hub 5 of the impeller 4. It can be seen that all profile sections 21 to 21.7 have a similar cross-sectional shape, in the exemplary embodiment an aircraft wing profile shape. Starting from the inside profile section 21.7 and viewed in the radial direction of the fan blade 7, the profile sections are arranged offset.
  • this offset of the profile sections is continued up to the cylindrical envelope surface 22 of the impeller 4 in the usual way. Then the radially outermost profile section in the enveloping surface 22 would assume the position shown in 8 is indicated by the dashed line 21.1. In the present embodiment, however, this radially outermost profile section 21 is offset toward the suction side 8 in such a way that the profile section 21 has a relatively large offset in relation to the adjacent profile section 21.2. The offset between this radially outermost profile section 21 and the adjacent profile section 21.2 is greater than the offset between the profile section 21.2 and the profile section 21.3 adjacent to it. Due to this clear offset between the outermost profile section 21 and the adjacent profile section 21.1, a radially outer end region 20 ( 9 ), which has a significantly greater pitch than the remaining part of the fan blade in which the profile sections 21.2 to 21.7 are located.
  • the profile sections are placed in such a way that the distance between the profile sections is greater than the width 25 ( 9 ) of the radially outer end region 20 formed by the offset of the outermost profile section 21. Since the offset between the radially outermost profile section 21 and the adjacent profile section 21.2 is larger, preferably significantly larger, than the offset between the profile section 21.2 and 21.3, the radially outer end region has 20 has a greater slope than the rest of the fan blade 7, through which the profile sections are placed 21.1 to 21.7.
  • the radial end region 20 ( 9 ) produces an effect corresponding to the flow element 17 of the previous embodiment, which is achieved solely by the displacement of the profile section.
  • the profile sections 21 to 21.7 have a similar cross-sectional configuration.
  • the radially outer profile section 21 can have a different profile section shape than the remaining profile sections 21.2 to 21.6.
  • the profile section is displaced towards the suction side 8 .
  • the displacement can also be provided towards the pressure side 9 .
  • the fan blade 7 is formed in the same way as in the previous embodiment.
  • the optimal gap flow 24 is supported by the fact that the flow gap 26 ( 6 ) between the flow element 17 or the end region 20 and the housing jacket 2 from the pressure side 9 in the direction of the suction side 8 tapers.
  • the flow gap 26 is designed in the form of a nozzle, which contributes to the unhindered flow of air through the flow gap 26 to reduce noise.

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

Description

Die Erfindung betrifft ein Flügelrad für einen Ventilator nach dem Oberbegriff des Anspruches 1.The invention relates to an impeller for a fan according to the preamble of claim 1.

Es sind Ventilatoren und Flügelräder bekannt ( DE 20 2004 005 548 U1 ), bei denen von der Nabe des Flügelrades Lüfterflügel abstehen, die gewunden ausgebildet und am radial äußeren Rand mit einem Strömungselement versehen sind. Die Lüfterflügel haben etwa die Querschnittsform einer Flugzeug-Tragfläche. Die Strömungselemente am äußeren Rand dieser Lüfterflügel haben einen analogen Verlauf. Dadurch verläuft der Außenrand der Strömungselemente in etwa parallel zur Querschnittsober- und -unterseite der zugehörigen Lüfterflügel. Im Bereich der Vorder- und Hinterkante der Lüfterflügel nimmt die axiale Höhe der Strömungselemente bis nahezu 0 ab. Durch eine solche Gestaltung soll eine Geräuschentwicklung beim Betrieb des Flügelrades bzw. des Ventilators zumindest verringert werden. Die Strömungselemente bieten einen erhöhten Widerstand für die Verlustströmung, die um den radial äußeren Rand der Lüfterflügel von der Druckseite zur Saugseite verläuft.Fans and impellers are known ( DE 20 2004 005 548 U1 ), in which fan blades protrude from the hub of the impeller wheel, which are designed to be wound and are provided with a flow element on the radially outer edge. The fan blades have approximately the cross-sectional shape of an airplane wing. The flow elements on the outer edge of these fan blades have a similar course. As a result, the outer edge of the flow elements runs approximately parallel to the top and bottom of the cross-section of the associated fan blades. In the area of the front and rear edges of the fan blades, the axial height of the flow elements decreases to almost zero. Such a design is intended to at least reduce noise development during operation of the impeller or the fan. The flow elements provide increased resistance to the leakage flow that travels around the radially outer edge of the fan blades from the pressure side to the suction side.

Es ist weiter ein Flügelrad bekannt ( US-A-5 215 441 , JP 2006 312912 A , US 2009/0208333 A1 , US 2010/0104461 A1 ), dessen Lüfterflügel am radial äu-ßeren Rand mit einem abstehenden Strömungselement versehen sind, das sich von der Hinterkante des Lüfterflügels aus über einen Teil der Länge des radial äußeren Randes erstreckt.It is further known an impeller ( US-A-5,215,441 , JP 2006 312912 A , U.S. 2009/0208333 A1 , US 2010/0104461 A1 ), the fan blades of which are provided with a protruding flow element on the radially outer edge, which extends from the trailing edge of the fan blade over part of the length of the radially outer edge.

Es ist bei einer Verdichterschaufel für einen Verdichter bekannt ( EP 1 624 192 A1 ), am radial äußeren Rand der Verdichterschaufel eine Dichtlippe anzuordnen, die sich von der Verdichterschaufel aus radial nach außen erstreckt. Die Dichtlippe ist schmaler als das Schaufelprofil und erstreckt sich von einer Anströmkante zu einer Abströmkante der Verdichterschaufel. Über ihre Länge hat die Dichtlippe konstante radiale und axiale Höhe bzw. Dicke.It is known for a compressor blade for a compressor ( EP 1 624 192 A1 ), to arrange a sealing lip on the radially outer edge of the compressor blade, extending radially outward from the compressor blade. The sealing lip is narrower than the blade profile and extends from a leading edge to a trailing edge of the compressor blade. The sealing lip has a constant radial and axial height and thickness over its length.

Der Erfindung liegt die Aufgabe zugrunde, das gattungsgemäße Flügelrad so auszubilden, dass bei einfacher konstruktiver Gestaltung eine hohe Geräuscharmut im Betrieb erreicht wird.The invention is based on the object of designing the impeller of the generic type in such a way that, with a simple structural design, very little noise is achieved during operation.

Diese Aufgabe wird beim gattungsgemäßen Flügelrad erfindungsgemäß mit den kennzeichnenden Merkmalen des Anspruches 1 gelöst.This object is achieved according to the invention with the characterizing features of claim 1 in the generic impeller.

Das erfindungsgemäße Flügelrad zeichnet sich dadurch aus, dass die axiale Höhe des Strömungselementes im Bereich der Vorder- und der Hinterkante der Lüfterflügel ein Maximum aufweist. Die Höhe des Strömungselementes nimmt in Richtung auf die Mitte des Lüfterflügels ab. Aufgrund dieser Ausgestaltung des Strömungselementes ergibt sich eine hervorragende Geräuschreduzierung beim Einsatz des Flügelrades sowie ein optimaler behinderungsfreier Durchfluss der Luft von der Druck- zur Saugseite, wodurch die Geräuschverringerung begünstigt wird.The impeller according to the invention is characterized in that the axial height of the flow element has a maximum in the area of the front and rear edges of the fan blades. The height of the airfoil decreases towards the center of the fan blade. Due to this design of the flow element, there is an excellent noise reduction when using the impeller and an optimal, unhindered flow of air from the pressure side to the suction side, which promotes the noise reduction.

Bei einer vorteilhaften Ausbildung nimmt das Verhältnis der axialen Höhe des Strömungselementes zur axialen Dicke des Lüfterflügels vom Maximum aus in Richtung auf die Mitte des Lüfterflügels ab. Die Höhe des Strömungselementes kann bis auf 0 im Bereich zwischen Vorder- und der Hinterkante des Lüfterflügels abnehmen.In an advantageous embodiment, the ratio of the axial height of the flow element to the axial thickness of the fan blade decreases from the maximum towards the center of the fan blade. The height of the flow element can decrease to 0 in the area between the leading and the trailing edge of the fan blade.

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

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

Fig. 1
in perspektivischer Darstellung einen Teil eines Ventilators mit einem erfindungsgemäßen Flügelrad,
Fig. 2
in vergrößerter Darstellung einen Teil des Ventilators gemäß Fig. 1,
Fig. 3
in perspektivischer Darstellung den radial äußeren Bereich eines Lüfterflügels des erfindungsgemäßen Flügelrades,
Fig. 4
eine Draufsicht auf den Lüfterflügel gemäß Fig. 3,
Fig. 5
in einem Diagramm den Querschnittsverlauf des Lüfterflügels sowie eines am radial äußeren Ende des Lüfterflügels vorgesehenen Strömungselementes sowie das Verhältnis der in Achsrichtung des Ventilators gemessenen Höhe des Strömungselementes zur Dicke des Flügels,
Fig. 6
im Schnitt den Strömungsverlauf an einem Lüfterflügel des erfindungsgemäßen Flügelrades,
Fig. 7
in perspektivischer Darstellung eine zweite Ausführungsform eines nicht zur Erfindung gehörenden Lüfterflügels mit mehreren Schnitten,
Fig. 8
die Flügelschnitte gemäß Fig. 7 mit einer zylindrischen Hüllfläche des Flügelrades zur Erläuterung der Verschiebung des radial äußeren Flügelschnittes,
Fig. 9
in perspektivischer Darstellung die Vorder- und die Hinterkante und den durch die Verschiebung des äußeren Flügelschnittes gebildeten Endbereich des Lüfterflügels gemäß Fig. 7,
Fig. 10
in perspektivischer Darstellung den Lüfterflügel gemäß Fig. 3,
Fig. 11
mehrere Schnitte durch den Lüfterflügel gemäß Fig. 10.
The invention is explained in more detail with reference to several embodiments shown in the drawings. Show it
1
a perspective view of part of a fan with an impeller according to the invention,
2
in an enlarged view a part of the fan according to FIG 1 ,
3
in a perspective view the radially outer area of a fan blade of the impeller according to the invention,
4
a plan view of the fan blade according to FIG 3 ,
figure 5
in a diagram the cross-sectional course of the fan blade and a flow element provided at the radially outer end of the fan blade and the ratio of the height of the flow element measured in the axial direction of the fan to the thickness of the blade,
6
in section the course of flow on a fan blade of the impeller according to the invention,
7
a perspective view of a second embodiment of a fan blade not belonging to the invention with several sections,
8
the wing cuts according to 7 with a cylindrical enveloping surface of the impeller to explain the displacement of the radially outer blade section,
9
a perspective view of the front and rear edges and the end area of the fan blade formed by the displacement of the outer blade section according to FIG 7 ,
10
in a perspective view according to the fan blade 3 ,
11
several cuts through the fan blade according to 10 .

Der Ventilator hat ein Gehäuse 1 mit einem zylindrischen Mantel 2, der einen Förderkanal 3 umschließt. Im Förderkanal 3 befindet sich ein Flügelrad 4, dessen Nabe 5 in bekannter Weise drehbar gelagert ist. Das Flügelrad 4 wird in Pfeilrichtung 6 im Gegenuhrzeigersinn mittels eines Antriebes 4a drehbar angetrieben.The fan has a housing 1 with a cylindrical casing 2 which encloses a conveying duct 3 . In the conveying channel 3 there is an impeller 4, the hub 5 of which is rotatably mounted in a known manner. The impeller 4 is rotatably driven counterclockwise in the direction of arrow 6 by means of a drive 4a.

Von der Nabe 5 stehen beispielhaft sechs Lüfterflügel 7 ab, die sich bis nahe an den Mantel 2 erstrecken. Die Luft strömt, wie Fig. 6 zeigt, zwischen dem radial äußeren Rand der Lüfterflügel 7 und der Innenseite des Mantels 2 von der Druckseite 9 im Wesentlichen störungsfrei zur Saugseite 8 des Flügelrades 4.By way of example, six fan blades 7 protrude from the hub 5 and extend close to the jacket 2 . The air flows like 6 shows, between the radially outer edge of the fan blades 7 and the inside of the jacket 2 from the pressure side 9 essentially without interference to the suction side 8 of the impeller 4.

Damit beim Betrieb des Ventilators die Geräuschentwicklung in einem für das menschliche Ohr angenehmen Frequenzspektrum liegt, ist es vorteilhaft, wenn die Lüfterflügel 7 über den Umfang der Nabe 5 ungleichmäßig verteilt sind.In order for the noise generated during operation of the fan to be in a frequency spectrum that is pleasant for the human ear, it is advantageous if the fan blades 7 are unevenly distributed over the circumference of the hub 5 .

Selbstverständlich kann das Flügelrad 4 auch so ausgebildet sein, dass die Lüfterflügel 7 gleichmäßig verteilt über den Umfang der Nabe 5 vorgesehen sind.Of course, the impeller 4 can also be designed in such a way that the fan blades 7 are distributed uniformly over the circumference of the hub 5 .

Die Lüfterflügel 7 haben jeweils eine in Drehrichtung 6 vorn liegende Vorderkante 10 sowie eine in Drehrichtung 6 hinten liegende Hinterkante 11. Die Vorderkante 10 ist, in Achsrichtung des Flügelrades 4 gesehen, sichelförmig ausgebildet, das heißt, sie hat einen konkaven Verlauf. Die Vorderkante 10 erstreckt sich von der Nabe 5 aus bis zum Außenrand 12, der sich in Umfangsrichtung des Flügelrades 4 erstreckt. Der Außenrand 12 hat den radialen Abstand 13 (Fig. 6) vom Gehäusemantel 2. Dieser Abstand ist so gewählt, dass die Verlustströmung möglichst gering ist und eine geringe Geräuschentwicklung auftritt.The fan blades 7 each have a front edge 10 in the direction of rotation 6 and a rear edge 11 at the rear in the direction of rotation 6. The front edge 10 is crescent-shaped as seen in the axial direction of the impeller 4, i.e. it has a concave profile. The leading edge 10 extends from the hub 5 to the outer edge 12 which extends in the circumferential direction of the impeller 4 . The outer edge 12 has the radial distance 13 ( 6 ) from the housing shell 2. This distance is like this chosen so that the loss flow is as low as possible and a low noise level occurs.

Vorteilhaft liegt der Bereich 14 (Fig. 2), an dem die Vorderkante 10 den Außenrand 12 schneidet, in Drehrichtung 6 des Lüfterrades 4 weiter vorn als der Anschlussbereich der Vorderkante 10 an den Nabenmantel. Wird eine Radiale durch die Achse des Flügelrades 4 und durch diesen Eckbereich 14 gezogen, dann liegt, in Achsrichtung gesehen, der Anschlussbereich der Vorderkante 10 an den Nabenmantel in Drehrichtung hinter dieser Radialen. Durch eine solche Gestaltung der Lüfterflügel 7 ergibt sich eine Geräuschverringerung beim Betrieb des Ventilators und eine Verbesserung des Abrissverhaltens.The area 14 ( 2 ) at which the front edge 10 intersects the outer edge 12, further forward in the direction of rotation 6 of the fan wheel 4 than the connection area of the front edge 10 to the hub casing. If a radial line is drawn through the axis of the impeller 4 and through this corner area 14, then, seen in the axial direction, the connection area of the front edge 10 to the hub shell lies behind this radial line in the direction of rotation. Such a design of the fan blades 7 results in a reduction in noise during operation of the fan and an improvement in the tearing behavior.

Die Hinterkante 11 des Lüfterflügels 7 verläuft zumindest über einen Teil ihrer Länge konvex. Der konvexe Verlauf kann von der Nabe 5 bis zum Außenrand 12 des Lüfterflügels vorgesehen sein. Es ist aber auch möglich, den konvexen Verlauf nur über eine Teillänge der Hinterkante 11 des Lüfterflügels 7 vorzusehen. So kann beispielsweise dieser konvexe Verlauf nur in dem an den Außenrand 12 anschließenden Bereich der Hinterkante 11 vorgesehen sein.The trailing edge 11 of the fan blade 7 is convex over at least part of its length. The convex progression can be provided from the hub 5 to the outer edge 12 of the fan blade. However, it is also possible to provide the convex course only over a partial length of the trailing edge 11 of the fan blade 7 . For example, this convex course can only be provided in the region of the rear edge 11 adjoining the outer edge 12 .

Beim dargestellten Ausführungsbeispiel ist die Hinterkante 11 über einen Teil ihrer Länge mit Zähnen 15 versehen, die sich jeweils in Richtung auf ihr freies Ende verjüngen. Die Zähne 15 können gleiche Umrissform haben. Bei einer bevorzugten Ausführungsform sind die Zähne 15 so ausgebildet, dass ihre Enden, die vorteilhaft spitz zulaufen, bis zu einer konvex verlaufenden Hülllinie 16 ragen (Fig. 4 und 7). Diese Hülllinie 16 kann vorteilhaft eine Fortsetzung des nichtgezahnten Bereichs der Hinterkante 11 bilden.In the illustrated embodiment, the trailing edge 11 is provided with teeth 15 over part of its length, each tapering towards its free end. The teeth 15 can have the same outline shape. In a preferred embodiment, the teeth 15 are designed in such a way that their ends, which advantageously taper to a point, project up to a convex envelope line 16 ( 4 and 7 ). This envelope line 16 can advantageously form a continuation of the non-toothed area of the trailing edge 11 .

Die Zähne 15 können längs der Hinterkante 11 auch unterschiedliche Umrissformen und/oder unterschiedliche Länge haben. Durch entsprechende Wahl der Gestaltung der Zähne 15 lässt sich die Geräuschentwicklung des Ventilators an den jeweiligen Einsatzfall optimal anpassen.The teeth 15 can also have different outline shapes and/or different lengths along the trailing edge 11 . By selecting the design of the teeth 15 appropriately, the noise development of the fan can be optimally adapted to the respective application.

Die Lüfterflügel 7 sind als gewundene Flügel ausgebildet.The fan blades 7 are designed as twisted blades.

Am radial äußeren Rand 12 ist jeder Lüfterflügel 7 beim Ausführungsbeispiel nach den Fig. 1 bis 6 mit einem Strömungselement 17 versehen, das sich vorteilhaft über die gesamte Länge des Außenrandes 12 zwischen der Vorderkante 10 und der Hinterkante 11 erstreckt. Die Strömungselemente erstrecken sich am Außenrand 12 zur Saugseite 8 des Lüfterflügels 7. Es ist aber auch möglich, dass das Strömungselement 17 sich sowohl auf die Saugseite 8 als auch auf die Druckseite 9 erstreckt. Ebenso ist es möglich, dass das Strömungselement 17 lediglich in Richtung auf die Druckseite 9 ragt.At the radially outer edge 12, each fan blade 7 is in the embodiment according to Figures 1 to 6 provided with a flow element 17, which advantageously extends over the entire length of the outer edge 12 between the front edge 10 and the rear edge 11. The flow elements extend on the outer edge 12 to the suction side 8 of the fan blade 7. However, it is also possible for the flow element 17 to extend both to the suction side 8 and to the pressure side 9. It is also possible for the flow element 17 to protrude only in the direction of the pressure side 9 .

Die Strömungselemente 17 sind vorteilhaft einstückig mit den Lüfterflügeln 7 ausgebildet, können aber grundsätzlich auch vom Lüfterflügel getrennte Bauteile sein, die an den Lüfterflügeln in geeigneter Weise befestigt sind.The flow elements 17 are advantageously designed in one piece with the fan blades 7, but in principle they can also be components that are separate from the fan blades and are attached to the fan blades in a suitable manner.

Das Strömungselement 17 hat im Bereich der Vorder- und der Hinterkante 10, 11 des Lüfterflügels 7 jeweils seine größte Höhe h, in Achsrichtung 18 des Flügelrades 4 gemessen (Fig. 5). In Fig. 5 ist das Strömungselement 17 sowie das Profil des zugehörigen Lüfterflügels 7 in Höhe des Strömungselementes 17 dargestellt. Die axiale Höhe h des Strömungselementes 17 nimmt von der Vorderkante 10 bzw. der Hinterkante 11 aus jeweils ab, bis das Strömungselement 17 im Bereich zwischen den beiden Kanten 10, 11 die Höhe 0 oder annähernd 0 hat. Dieser Bereich kann in halber Breite des Lüfterflügels 7 liegen. Der Lüfterflügel 7 hat im Bereich des Strömungselementes 17 die axiale Dicke d. Im übrigen Bereich kann der Lüfterflügel 7 unterschiedliche axiale Dicke haben.The flow element 17 has its greatest height h in the region of the front and rear edges 10, 11 of the fan blade 7, measured in the axial direction 18 of the blade wheel 4 ( figure 5 ). In figure 5 the flow element 17 and the profile of the associated fan blade 7 are shown at the level of the flow element 17 . The axial height h of the flow element 17 decreases from the front edge 10 or the rear edge 11 until the flow element 17 has a height of 0 or approximately 0 in the region between the two edges 10, 11. This area can be half the width of the fan blade 7 . The fan blade 7 has the axial thickness d in the area of the flow element 17 . In the rest of the area, the fan blade 7 can have different axial thicknesses.

Die axiale Höhe h des Strömungselementes 17 sowie die axiale Dicke d des Lüfterflügels 7 sind so aufeinander abgestimmt, dass das Verhältnis h/d von der Vorderkante 10 sowie der Hinterkante 11 aus abnimmt, wie die gestrichelte Linie 19 in Fig. 5 zeigt. In dem Bereich, in dem die axiale Höhe h des Strömungselementes 17 nahezu 0 beträgt, ist dieses Verhältnis h/d am geringsten.The axial height h of the flow element 17 and the axial thickness d of the fan blade 7 are coordinated in such a way that the ratio h/d decreases from the front edge 10 and the rear edge 11, as shown by the dashed line 19 in figure 5 shows. In the area in which the axial height h des Flow element 17 is almost 0, this ratio h / d is lowest.

Je nach Anwendungsfall kann das Strömungselement 17 auch so gestaltet sein, dass seine minimale axiale Höhe nicht in halber Breite des Lüfterflügels 7 liegt. Wesentlich ist, dass das angegebene Verhältnis h/d von der Vorderkante 10 bzw. der Hinterkante 11 aus abnimmt. Durch eine solche Gestaltung des Lüfterflügels mit Strömungselement ergibt sich eine hervorragende Geräuschreduzierung beim Einsatz des Ventilators.Depending on the application, the flow element 17 can also be designed in such a way that its minimum axial height is not half the width of the fan blade 7 . It is essential that the given ratio h/d decreases from the leading edge 10 or the trailing edge 11 . Such a design of the fan blade with flow element results in excellent noise reduction when using the fan.

Wie sich aus Fig. 5 ergibt, hat der Lüfterflügel 7 eine Flugzeugtragflächen-Profilform. Im Bereich der Vorderkante 10 ist der Lüfterflügel 7 abgerundet, während er im Bereich der Hinterkante 11 etwa spitz ausläuft. Im Bereich zwischen den beiden Kanten 10, 11 kann der Lüfterflügel 7 auch etwa konstante Querschnittsdicke aufweisen.How out figure 5 results, the fan blade 7 has an aircraft wing profile shape. In the area of the front edge 10 the fan blade 7 is rounded off, while in the area of the rear edge 11 it tapers to a point. In the area between the two edges 10, 11, the fan blade 7 can also have an approximately constant cross-sectional thickness.

Bei der bevorzugten einteiligen Ausbildung von Lüfterflügel 7 und Strömungselement 17 weist der Lüfterflügel 7 an der Druckseite 9 einen großen Einlaufbereich 20 (Fig. 6) am Übergang vom Lüfterflügel 7 zum Strömungselement 17 auf, vorzugsweise mit einem großen Radius 27. Dies trägt zu einer geräuscharmen Betriebsweise des Ventilators hervorragend bei.In the preferred one-piece design of the fan blade 7 and flow element 17, the fan blade 7 has a large inlet area 20 ( 6 ) at the transition from fan blade 7 to flow element 17, preferably with a large radius 27. This makes an excellent contribution to low-noise operation of the fan.

Das Strömungselement 17 ist so ausgebildet, dass seine axiale Erstreckung von der Vorderkante 10 des Lüfterflügels 7 ausgehend über einen sehr kurzen Bereich sehr stark zunimmt, bis das Strömungselement mit geringem Abstand von der Vorderkante 10 seine größte axiale Höhe h aufweist. Ähnlich nimmt die axiale Höhe h des Strömungselementes 17 von der Hinterkante 11 des Lüfterflügels 7 aus über einen sehr kurzen Bereich sehr stark zu, bis das Strömungselement mit geringem Abstand von der Hinterkante 10 in diesem Bereich seine größte axiale Höhe h aufweist, die in Richtung auf die Mitte des Lüfterflügels 7 abnimmt. Aufgrund dieser Ausbildung hat das Strömungselement 17 einen völlig anderen Verlauf als der Lüfterflügel 7 im Bereich des Strömungselementes 17.The flow element 17 is designed such that its axial extent increases very sharply starting from the front edge 10 of the fan blade 7 over a very short area until the flow element has its greatest axial height h at a small distance from the front edge 10 . Similarly, the axial height h of the flow element 17 increases greatly from the trailing edge 11 of the fan blade 7 over a very short area until the flow element has its greatest axial height h in this area at a small distance from the trailing edge 10, which is in the direction of the center of the fan blade 7 decreases. Due to this design, the flow element 17 has a completely different course than the fan blade 7 in the area of the flow element 17.

Die Fig. 7 bis 11 zeigen einen gewundenen Lüfterflügel 7, der anstelle des Strömungselementes 17 im radial äußeren Bereich eine solche Gestaltung hat, dass er trotz fehlendem Strömungselement 17 die gleiche Wirkung wie ein Lüfterflügel mit Strömungselement zeigt. Erreicht wird dies durch eine besondere Gestaltung des Lüfterflügels, die im Folgenden näher beschrieben wird.The Figures 7 to 11 show a twisted fan blade 7 which, instead of the flow element 17 in the radially outer area, has such a design that it has the same effect as a fan blade with a flow element, despite the lack of a flow element 17. This is achieved through a special design of the fan blade, which is described in more detail below.

Wie die Fig. 7 und 8 zeigen, hat der Lüfterflügel 7 über seine radiale Länge in gleichen Abständen die Profilschnitte 24.1 bis 24.7, die eine ähnliche Querschnittsausbildung haben. Wie bei der vorigen Ausführungsform hat der Lüfterflügel 7 eine Flugzeugtragflächen-Profilform, bei der der Lüfterflügel 7 im Bereich der Vorderkante 10 abgerundet und im Bereich der Hinterkante 11 etwa spitz auslaufend ausgebildet ist.As the 7 and 8th show, the fan blade 7 has the profile sections 24.1 to 24.7 at equal intervals over its radial length, which have a similar cross-sectional configuration. As in the previous embodiment, the fan blade 7 has an aircraft wing profile shape, in which the fan blade 7 is rounded off in the area of the front edge 10 and tapered in the area of the rear edge 11 .

Der zum Gehäusemantel 2 weisende Außenrand 12 des Lüfterflügels 7 ist so geformt, dass der radial äußere Profilschnitt des Lüfterflügels zur Saugseite 8 hin verschoben ist. In Fig. 7 sind über die Länge des Lüfterflügels 7 verschiedene Profilschnitte 21, 21.1 bis 21.7 angegeben. Die Profilschnitte sind Zylinderschnitte durch den Lüfterflügel 7. Die Profilschnitte 21.1 bis 21.7 sind in gleichen Abständen in Radialrichtung des Lüfterflügels 7 vorgesehen. Der Profilschnitt 21.7 (Fig. 7) ist an der Nabe 5 des Flügelrades 4 vorgesehen. Erkennbar ist, dass sämtliche Profilschnitte 21 bis 21.7 eine ähnliche Querschnittsform haben, im Ausführungsbeispiel eine Flugzeugtragflächen-Profilform. Die Profilschnitte sind, ausgehend vom innenseitigen Profilschnitt 21.7 und in Radialrichtung des Lüfterflügels 7 gesehen, versetzt angeordnet.The outer edge 12 of the fan blade 7 pointing towards the housing casing 2 is shaped in such a way that the radially outer profile section of the fan blade is shifted towards the suction side 8 . In 7 7 different profile sections 21, 21.1 to 21.7 are given over the length of the fan blade. The profile sections are cylindrical sections through the fan blade 7. The profile sections 21.1 to 21.7 are provided at equal intervals in the radial direction of the fan blade 7. The profile section 21.7 ( 7 ) is provided on the hub 5 of the impeller 4. It can be seen that all profile sections 21 to 21.7 have a similar cross-sectional shape, in the exemplary embodiment an aircraft wing profile shape. Starting from the inside profile section 21.7 and viewed in the radial direction of the fan blade 7, the profile sections are arranged offset.

In Fig. 8 ist der Fall dargestellt, dass dieser Versatz der Profilschnitte bis zur zylindrischen Hüllfläche 22 des Flügelrades 4 in üblicher Weise weitergeführt ist. Dann würde der radial äußerste Profilschnitt in der Hüllfläche 22 die Position einnehmen, die in Fig. 8 durch die gestrichelte Linie 21.1 angedeutet ist. Bei der vorliegenden Ausführungsform jedoch ist dieser radial äußerste Profilschnitt 21 zur Saugseite 8 hin so versetzt angeordnet, dass der Profilschnitt 21 einen relativ großen Versatz in Bezug auf den benachbarten Profilschnitt 21.2 aufweist. Der Versatz zwischen diesem radial äußersten Profilschnitt 21 und dem benachbarten Profilschnitt 21.2 ist größer als der Versatz zwischen dem Profilschnitt 21.2 und dem ihm benachbarten Profilschnitt 21.3. Aufgrund dieses deutlichen Versatzes zwischen dem äußersten Profilschnitt 21 und dem benachbarten Profilschnitt 21.1 ergibt sich ein radial äußerer Endbereich 20 (Fig. 9), der eine wesentlich größere Steigung hat als der übrige Teil des Lüfterflügels, in dem sich die Profilschnitte 21.2 bis 21.7 befinden.In 8 the case is shown that this offset of the profile sections is continued up to the cylindrical envelope surface 22 of the impeller 4 in the usual way. Then the radially outermost profile section in the enveloping surface 22 would assume the position shown in 8 is indicated by the dashed line 21.1. In the present embodiment, however, this radially outermost profile section 21 is offset toward the suction side 8 in such a way that the profile section 21 has a relatively large offset in relation to the adjacent profile section 21.2. The offset between this radially outermost profile section 21 and the adjacent profile section 21.2 is greater than the offset between the profile section 21.2 and the profile section 21.3 adjacent to it. Due to this clear offset between the outermost profile section 21 and the adjacent profile section 21.1, a radially outer end region 20 ( 9 ), which has a significantly greater pitch than the remaining part of the fan blade in which the profile sections 21.2 to 21.7 are located.

Die Profilschnitte sind so gelegt, dass der Abstand der Profilschnitte voneinander größer ist als die Breite 25 (Fig. 9) des durch den Versatz des äußersten Profilabschnittes 21 gebildeten radial äußeren Endbereichs 20. Da der Versatz zwischen dem radial äußersten Profilschnitt 21 und dem benachbarten Profilschnitt 21.2 größer, vorzugsweise wesentlich größer ist als der Versatz zwischen dem Profilschnitt 21.2 und 21.3, hat der radial äußere Endbereich 20 eine größere Steigung als der übrige Teil des Lüfterflügels 7, durch den die Profilschnitte 21.1 bis 21.7 gelegt sind.The profile sections are placed in such a way that the distance between the profile sections is greater than the width 25 ( 9 ) of the radially outer end region 20 formed by the offset of the outermost profile section 21. Since the offset between the radially outermost profile section 21 and the adjacent profile section 21.2 is larger, preferably significantly larger, than the offset between the profile section 21.2 and 21.3, the radially outer end region has 20 has a greater slope than the rest of the fan blade 7, through which the profile sections are placed 21.1 to 21.7.

Grundsätzlich ist es ausreichend, wenn nur der äußerste Profilschnitt 21 zur Saugseite 8 hin gegenüber dem (den) benachbarten Profilschnitt(en) verschoben ist.In principle, it is sufficient if only the outermost profile section 21 is shifted toward the suction side 8 in relation to the adjacent profile section(s).

Der aufgrund des Versatzes des (der) Profilschnitt(e) entstehende radiale Endbereich 20 (Fig. 9) erzeugt eine dem Strömungselement 17 der vorigen Ausführungsform entsprechende Wirkung, die allein durch die Profilschnitt-Verschiebung erreicht wird.The radial end region 20 ( 9 ) produces an effect corresponding to the flow element 17 of the previous embodiment, which is achieved solely by the displacement of the profile section.

Im Ausführungsbeispiel haben die Profilschnitte 21 bis 21.7 ähnliche Querschnittsausbildung. Der radial äußere Profilschnitt 21 kann eine andere Profilschnittform als die restlichen Profilschnitte 21.2 bis 21.6 aufweisen. Somit kann durch Beeinflussung der Lage der jeweiligen Profilschnitte relativ zueinander der Lüfterflügel 7 optimal an den geforderten Einsatzfall im Hinblick auf Wirkungsgrad und/oder Geräuscharmut optimiert werden.In the exemplary embodiment, the profile sections 21 to 21.7 have a similar cross-sectional configuration. The radially outer profile section 21 can have a different profile section shape than the remaining profile sections 21.2 to 21.6. Thus, by influencing the position of the respective profile sections relative to one another the fan blade 7 can be optimally optimized for the required application in terms of efficiency and/or low noise.

Im beschriebenen und dargestellten Ausführungsbeispiel erfolgt die Verschiebung des Profilschnittes zur Saugseite 8 hin. Die Verschiebung kann aber auch zur Druckseite 9 hin vorgesehen sein.In the exemplary embodiment described and illustrated, the profile section is displaced towards the suction side 8 . However, the displacement can also be provided towards the pressure side 9 .

Im Übrigen ist der Lüfterflügel 7 gleich ausgebildet wie bei der vorigen Ausführungsform.Otherwise, the fan blade 7 is formed in the same way as in the previous embodiment.

Um eine möglichst behinderungsfreie Spaltströmung 24 im Bereich zwischen dem Strömungselement 17 bzw. dem Endbereich 20 und der Innenseite des Gehäusemantels 2 zu erreichen, haben das Strömungselement 17 bzw. der Endbereich 20, in Achsrichtung des Flügelrades 4 gesehen (Fig. 4), einen großen Krümmungsradius 27.In order to achieve a gap flow 24 that is as unhindered as possible in the area between the flow element 17 or the end area 20 and the inside of the housing jacket 2, the flow element 17 or the end area 20 have seen in the axial direction of the impeller 4 ( 4 ), a large radius of curvature 27.

Die optimale Spaltströmung 24 wird dadurch unterstützt, dass sich der Strömungsspalt 26 (Fig. 6) zwischen dem Strömungselement 17 bzw. dem Endbereich 20 und dem Gehäusemantel 2 von der Druckseite 9 aus in Richtung auf die Saugseite 8 verjüngt. Der Strömungsspalt 26 ist düsenförmig gestaltet, was zur behinderungsfreien Durchströmung der Luft zur Geräuschreduzierung durch den Strömungsspalt 26 beiträgt.The optimal gap flow 24 is supported by the fact that the flow gap 26 ( 6 ) between the flow element 17 or the end region 20 and the housing jacket 2 from the pressure side 9 in the direction of the suction side 8 tapers. The flow gap 26 is designed in the form of a nozzle, which contributes to the unhindered flow of air through the flow gap 26 to reduce noise.

Die anhand der Fig. 7 bis 11 beschriebene Verschiebung der Profilschnitte des Lüfterflügels 7 erfolgt im dargestellten Ausführungsbeispiel translatorisch und rotatorisch. In Fig. 11 sind die verschiedenen Profilschnitte in die Zeichenebene projiziert dargestellt. Aus Fig. 11 ergibt sich, dass diese Profilschnitte nicht nur translatorisch, sondern auch rotatorisch gegeneinander versetzt sind. Erkennbar ist, dass die radial innen liegenden Profilschnitte 21.7 bis 21.5 steiler verlaufen als die radial außen liegenden Profilschnitte 21 bis 21.4. Aus Fig. 11 ergibt sich weiter, dass durch diese Verlagerung des Profilschnittes über die radiale Länge des Lüfterflügels 7 die Form dieses Lüfterflügels durch den Konstrukteur sehr einfach festgelegt und an den Einsatzfall angepasst werden kann.The based on Figures 7 to 11 The displacement of the profile sections of the fan blade 7 described above takes place in a translatory and rotary manner in the exemplary embodiment shown. In 11 the various profile sections are shown projected into the plane of the drawing. Out of 11 it follows that these profile sections are not only offset in translation but also in rotation with respect to one another. It can be seen that the radially inner profile sections 21.7 to 21.5 are steeper than the radially outer profile sections 21 to 21.4. Out of 11 results further that by this displacement of the profile section over the radial length of the fan blade 7, the shape of this Fan blades can be set very easily by the designer and adapted to the application.

Claims (9)

  1. Impeller for a ventilator, having a hub (5), from which fan blades (7) protrude, which are provided with at least one protruding flow element (17) at the radially outer edge (12),
    characterized in that the axial height (h) of the flow element (17), which extends over the entire length of the outer edge (12) between the front edge (10) and the rear edge (11) of the fan blade (7), has a maximum in the region of the front edge (10) and the rear edge (11) of the fan blade (7), and in that the axial height (h) decreases from the maxima in the direction of the centre of the fan blade (7).
  2. Impeller according to Claim 1,
    characterized in that the flow element (17) together with the wall (2) surrounding the impeller (4) forms a nozzle-shaped flow gap (26), which connects the pressure side (9) to the suction side (8) of the impeller (4) and through which the air flows in a substantially hindrance-free manner.
  3. Impeller according to Claim 1 or 2,
    characterized in that the flow element (17) or the radial outer edge (12) of the fan blade (7) has an intake area (20) on the pressure side (9).
  4. Impeller, particularly according to one of Claims 1 to 3, characterized in that the relationship of the axial height (h) of the flow element (17) to the axial thickness of the fan blade (7) in the region of the flow element (17) decreases from the front edge (10) and/or the rear edge (11) of the fan blade (7).
  5. Impeller according to one of Claims 1 to 4,
    characterized in that the front edge (10) of the fan blade (7) is constructed at least partially concavely over its length.
  6. Impeller according to one of Claims 1 to 5,
    characterized in that the rear edge (11) of the fan blade (7) is constructed at least partially convexly over its length.
  7. Impeller according to one of Claims 1 to 6,
    characterized in that the rear edge (11) of the fan blade (7) is provided with teeth (15) at least over part of the length thereof.
  8. Impeller according to one of Claims 1 to 7,
    characterized in that the transition region (14) between the front edge (10) and the radially outer edge (12) of the fan blade (7) protrudes in the direction (6) of rotation in relation to the transition region between the front edge (10) and the hub (5).
  9. Impeller according to one of Claims 1 to 8,
    characterized in that the fan blade (7) is constructed to be twisted, advantageously curved.
EP11006483.9A 2010-08-13 2011-08-08 Impeller for a ventilator Active EP2418389B1 (en)

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DE102010034604A DE102010034604A1 (en) 2010-08-13 2010-08-13 Impeller for a fan

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CN (1) CN102374193B (en)
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RU2011133880A (en) 2013-02-20
US8915717B2 (en) 2014-12-23
CN102374193A (en) 2012-03-14
SI2418389T1 (en) 2023-10-30
EP2418389A2 (en) 2012-02-15
CN102374193B (en) 2016-08-03
DE102010034604A1 (en) 2012-02-16
BRPI1103977A2 (en) 2014-05-06
US20120207606A1 (en) 2012-08-16
EP2418389A3 (en) 2013-01-23
BRPI1103977B1 (en) 2020-09-15
RU2584633C2 (en) 2016-05-20

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