EP2418389B1 - Hélice pour un ventilateur - Google Patents

Hélice pour un ventilateur 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
Authority
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.)
Active
Application number
EP11006483.9A
Other languages
German (de)
English (en)
Other versions
EP2418389A3 (fr
EP2418389A2 (fr
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
Original Assignee
Ziehl Abegg SE
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ziehl Abegg SE filed Critical Ziehl Abegg SE
Priority to SI201132093T priority Critical patent/SI2418389T1/sl
Publication of EP2418389A2 publication Critical patent/EP2418389A2/fr
Publication of EP2418389A3 publication Critical patent/EP2418389A3/fr
Application granted granted Critical
Publication of EP2418389B1 publication Critical patent/EP2418389B1/fr
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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.

Claims (9)

  1. Hélice pour ventilateur, comportant un moyeu (5) duquel dépassent en saillie des pales de ventilateur (7), qui sont pourvues d'au moins un élément d'écoulement dépassant en saillie (17) sur le bord radialement extérieur (12),
    caractérisée en ce que la hauteur axiale (h) de l'élément d'écoulement (17) s'étendant sur toute la longueur du bord extérieur (12) entre le bord avant (10) et le bord arrière (11) de la pale de ventilateur (7) dans la zone du bord avant (10) et du bord arrière (11) de la pale de ventilateur (7) a un maximum, et que la hauteur axiale (h) à partir des maxima diminue vers le centre de la pale de ventilateur (7).
  2. Hélice selon la revendication 1,
    caractérisée en ce que l'élément d'écoulement (17) forme avec la paroi (2) entourant l'hélice (4) un intervalle d'écoulement en forme de tuyère (26), qui relie le côté de pression (9) avec le côté d'aspiration (8) de l'hélice (4) et à travers lequel l'air s'écoule essentiellement sans entrave.
  3. Hélice selon la revendication 1 ou 2,
    caractérisée en ce que l'élément d'écoulement (17) ou le bord extérieur radial (12) de l'pale de ventilateur (7) sur le côté de pression (9) présente une zone d'entrée (20).
  4. Hélice, notamment selon une des revendications 1 à 3, caractérisée en ce que le rapport de la hauteur axiale (h) de l'élément d'écoulement (17) à l'épaisseur axiale de l'pale de ventilateur (7) diminue dans la région de l'élément d'écoulement (17) à partir du bord avant (10) et/ou du bord arrière (11) de l'aube de ventilateur (7) .
  5. Hélice selon une des revendications 1 à 4, caractérisée en ce que le bord avant (10) de l'pale de ventilateur (7) est au moins partiellement concave sur sa longueur.
  6. Hélice selon une des revendications 1 à 5, caractérisée en ce que le bord arrière (11) de l'pale de ventilateur (7) est au moins partiellement convexe sur sa longueur.
  7. Hélice selon une des revendications 1 à 6, caractérisée en ce que le bord arrière (11) de l'pale de ventilateur (7) est pourvu de dents (15) au moins sur une partie de sa longueur.
  8. Hélice selon une des revendications 1 à 7, caractérisée en ce que la zone de transition (14) entre le bord avant (10) et le bord radialement extérieur (12) de l'pale de ventilateur (7) dans la direction de rotation (6) dépasse en saillie à l'opposé de la zone de transition entre le bord avant (10) et le moyeu (5).
  9. Hélice selon une des revendications 1 à 8, caractérisée en ce que l'pale de ventilateur (7) est enroulée, avantageusement courbe.
EP11006483.9A 2010-08-13 2011-08-08 Hélice pour un ventilateur Active EP2418389B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI201132093T SI2418389T1 (sl) 2010-08-13 2011-08-08 Propeler za ventilator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102010034604A DE102010034604A1 (de) 2010-08-13 2010-08-13 Flügelrad für einen Ventilator

Publications (3)

Publication Number Publication Date
EP2418389A2 EP2418389A2 (fr) 2012-02-15
EP2418389A3 EP2418389A3 (fr) 2013-01-23
EP2418389B1 true EP2418389B1 (fr) 2023-07-05

Family

ID=44677300

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11006483.9A Active EP2418389B1 (fr) 2010-08-13 2011-08-08 Hélice pour un ventilateur

Country Status (8)

Country Link
US (1) US8915717B2 (fr)
EP (1) EP2418389B1 (fr)
CN (1) CN102374193B (fr)
BR (1) BRPI1103977B1 (fr)
DE (1) DE102010034604A1 (fr)
ES (1) ES2955590T3 (fr)
RU (1) RU2584633C2 (fr)
SI (1) SI2418389T1 (fr)

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Also Published As

Publication number Publication date
EP2418389A3 (fr) 2013-01-23
EP2418389A2 (fr) 2012-02-15
US8915717B2 (en) 2014-12-23
SI2418389T1 (sl) 2023-10-30
CN102374193A (zh) 2012-03-14
BRPI1103977B1 (pt) 2020-09-15
CN102374193B (zh) 2016-08-03
US20120207606A1 (en) 2012-08-16
ES2955590T3 (es) 2023-12-04
BRPI1103977A2 (pt) 2014-05-06
RU2584633C2 (ru) 2016-05-20
DE102010034604A1 (de) 2012-02-16
RU2011133880A (ru) 2013-02-20

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