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EP0086785B1 - Propulseur notamment pour soufflantes - Google Patents

Propulseur notamment pour soufflantes Download PDF

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Publication number
EP0086785B1
EP0086785B1 EP82901126A EP82901126A EP0086785B1 EP 0086785 B1 EP0086785 B1 EP 0086785B1 EP 82901126 A EP82901126 A EP 82901126A EP 82901126 A EP82901126 A EP 82901126A EP 0086785 B1 EP0086785 B1 EP 0086785B1
Authority
EP
European Patent Office
Prior art keywords
vane
propeller
sound suppressor
fin
pressure side
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP82901126A
Other languages
German (de)
English (en)
Other versions
EP0086785A1 (fr
Inventor
Heikki Vartiala
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.)
FOEHN Oy
Original Assignee
FOEHN Oy
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 FOEHN Oy filed Critical FOEHN Oy
Priority to AT82901126T priority Critical patent/ATE28497T1/de
Publication of EP0086785A1 publication Critical patent/EP0086785A1/fr
Application granted granted Critical
Publication of EP0086785B1 publication Critical patent/EP0086785B1/fr
Expired legal-status Critical Current

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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

Definitions

  • the present invention concerns a propeller particularly for pneumatic blower use as defined in the preamble of the main claim.
  • blowers known in the art are not satisfactory as to their output. Raising the output and input power of the blower and the pitch angle of the propeller and/or increasing the propeller diameter causes in most instances the noise level of the propeller to become intolerable.
  • the object of the present invention is to eliminate the drawbacks mentioned.
  • the object of the invention is to provide a propeller especially for blower use which is substantially more quiet than any propeller known in the art, that is, of which the sound level is substantially lower than that of propellers known in the art. It is a further object of the invention to provide a propeller particularly for blower use, which is more efficient referred to its size and noise level than those of prior art.
  • the propeller of the present invention gives better output and pressure difference results at remarkably (30%) lower noise level (same diameter, same number of revolutions, same number of blades).
  • Fig. 1 a blower provided with a propeller according to the invention.
  • the propeller comprises a hub 1, centrally and rotatably carried in a trumpet-like frame 13, with vanes 2, 2'.
  • the vanes 2, 2' project radially from the hub and have an oblique pitch a against the plane placed at right angles to the axis of the hub (visible in Fig. 2).
  • the propeller has been disposed to rotate with the aid of an electrical motor 14 located on the extension of the hub 1 in the frame 13 centrally and carried by supports 15.
  • the side 3 of the vane which first meets the fluid is the leading edge 3 and the opposite side is the trailing edge 4.
  • the side of the vane 2 which when rotating meets the fluid is the pressure side 5 and the opposite side is the vacuum side 6.
  • each vane 2 of the propeller shown in Figs. 1 and 2 in the direction of rotation of the vane partly in front of its leading edge 3, has been disposed a front louver element 7, substantially parallelling the vane and vane-shaped.
  • the front louver in part dips into the vacuum side 6 of the vane and it forms a slot 8 with the vane 2.
  • the front louver element 7 is thinner and more narrow in the cross section then the vane 2.
  • the front louver element 7 guides the fluid which the vane meets partly behind the vane to the vacuum side thereof and strongly reduces the turbulent flow in the region of the leading edge 3 of the vane.
  • the decrease of turbulent flow reduces the fluid resistance as the vane rotates in the fluid, simultaneously reducing the intensity (that is the power) of the noise generated.
  • the front louver elements 7 are fastened to the hub of the propeller similarly as the vanes of the propeller.
  • the front louver elements have substantially the same shape as the vanes 2 of the propeller, with a pitch angle smaller than the pitch angle of the propeller vane, positive or negative, e.g. in the range from 0 to 25°C.
  • the front louver element 7 may be fastened exclusively to the vane 2, e.g. by pin attachment, and/or to a vane circle which may be provided, encircling the vane tips, together with the vanes and the sound suppressor fins to be mentioned below.
  • a sound suppressorfin 9 which extends radially from the hub and substantially parallel to the vane and forms a slot 10 with the vane.
  • the sound suppressor fin is vane-shaped, substantially smaller in thickness and width than the vane.
  • the sound suppressor fin is affixed to the hub 1 of the propeller in the manner of the vane 2. If desired, it is possible to use the pin attachment mentioned, as sole mounting of the sound suppressor fin, and/or the vane circle mentioned above.
  • the present embodiment there has been disposed another sound suppressor fin 11 partly behind the trailing edge of the sound suppressor fin 9 of each vane 2, this fin 11 extending radially from the hub equally, substantially parallel to the vane and to the preceding sound suppressor fin, and each such fin forming a slot 12 with the preceding sound suppressor fin.
  • the latter sound suppressor fin 11 is substantially smaller than the vanes in its dimensions (width and thickness) and in the embodiment depicted also smaller than the first sound suppressor fin.
  • the latter sound suppressor fin 11 may be affixed by pin attachment to the preceding sound suppressor fin 9 or to the vane 2 or, like the vane, to the hub 1. Possibly, a vane circle may be used as sole or additional mounting, as mentioned above with reference to the vane, the front louver element and the preceding sound suppressor fin.
  • FIG. 2 The placement with reference to each other of the propeller vane 2, front louver element 7 and sound suppressor fins 9, 11 according to Fig. 1 is best revealed in Fig. 2, according to which the front louver element, vane and sound suppressor fins constitute a vane configuration which is substantially concave as viewed from the pressure side 5. Furthermore, the front louver element 7, the vane 2 and the sound suppressor fins 9, 11 are each concave as viewed from the pressure side 5.
  • the front louver element 7 is located mainly on the vacuum side 6 of the vane, the first sound suppressor fin on the pressure side 5 of the vane, and the second sound suppressor fin 11 on the pressure side of the vane 2 and of the preceding sound suppressor fin 9.
  • the front louver element 7, the vane 2 and the sound suppressor fins 9, 11 have greater thickness in their part adjacent to the leading edge and taper down towards the trailing edge.
  • a propeller as shown in Fig. 1 was tested side by side with propeller of equal size but of conventional design.
  • the number of vanes on each tested propeller was 8, the propeller diameter about 30 cm, the area of the propeller vane was substantially the same.
  • both propellers were run at 1400 r.p.m.
  • the quantity of air transported by the propeller was measured, as well as the over-pressure generated on the propeller's positive pressure side at a constant distance from the propeller; the noise level of the propeller was furthermore aurally assessed.
  • the power level of the propeller of the invention has been entered on line dB 1 in the table and that of the referenced propeller, on line dB 2 .
  • a second sound suppressor fin with 90° pitch angle known e.g. from centrifugal blowers, in which case the tubular frame of the blower may be outwardly flared at said second sound suppressor fin, in order to boost the blower's output.
  • the sound suppressor fins may, if desired, be placed equally on the vacuum side of the vane; similarly, the front louver element may be placed mainly on the pressure side of the vane.
  • the number of propeller vanes and accordingly of louver elements and sound suppressor fins may vary to be proper for instance for a propeller with 2, 3, 4, 5, 6, 7, 8 or more vanes.
  • vanes and preferably the front louver elements, and possibly the sound suppressor fins, belonging to a propeller according to the invention may be constructed each to be turnable about its axis, these axes being radial with reference to the hub of the propeller.
  • the vanes and preferably the front louver elements and the sound suppressor fins may all be turnable jointly and/or separately and placeable in desired position, towards controlling the pitch angles of the vanes, front louver elements and/or sound suppressor fins jointly and/or, if desired, separately.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Hydrogenated Pyridines (AREA)
  • Devices For Conveying Motion By Means Of Endless Flexible Members (AREA)

Claims (7)

1. Hélice, notamment destinée à être utilisée dans un ventilateur, comportant un moyeu (1) et au moins deux pales (2) faisant saillie radialement sur le moyeu et possédant un angle d'attaque oblique (a), le côté de la pale qui, lorsque l'hélice tourne, rencontre en premier le fluide étant le bord d'attaque (3) et le côté opposé étant le bord de fuite (4), et le côté de la pale, qui rencontre le fluide étant le côté sous pression (5) et le côté opposé étant le côté en dépression (6), et dans laquelle disposé partiellement en avant du bord d'attaque de chaque pale, dans le sens de rotation, se trouve un élément frontal formant volet abat-son (7) en forme de pale, disposé radialement tout en étant sensiblement parallèle à la pale et s'engageant partiellement d'un côté de la pale en délimitant une fente (8) avec cette dernière, caractérisée en ce que, disposée partiellement en arrière du bord de fuite (4) de chaque pale (2), se trouve une ailette d'atténuation acoustique (9), s'étendant radialement, sensiblement parallèlement à la pale, et réalisée en forme de pale tout en délimitant une fente (10) avec la pale, l'élément frontal formant volet abat-son (7) et l'ailette d'atténuation acoustique (9) possédant tous deux une épaisseur et une largeur nettement inférieures à celles de la pale.
2. Hélice selon la revendication 1, caractérisé en ce qu'en partie disposée derrière l'ailette d'atténuation acoustique (9) de chaque pale (1), se trouve une autre et éventuallement plusieurs autres ailettes d'atténuation acoustique (11), qui s'étendent radialement et sensiblement parallèlement à la pale, en délimitant chacune une fente (12) avec l'ailette précédente d'atténuation acoustique.
3. Hélice selon les revendications 1 et 2, caractérisée en ce que les ailettes d'atténuation acoustique (9, 11) sont disposées au moins en partie sur le côté sous pression (4) de la pale (2).
4. Hélice selon l'une quelconque des revendications 1 à 3, caractérisée en ce que l'élément frontal formant volet abat-son (7), la pale (2), l'ailette d'atténuation acoustique (9) et l'ailette d'atténuation acoustique suivante (11), dans le cas où elle est présente, forment un ensemble en forme de pale qui est concave lorsqu'on le regarde depuis le côté sous pression (5).
5. Hélice selon l'une quelconque des revendications 1 à 4, caractérisée en ce que la pale (2) est concave lorsqu'on la regarde depuis le côté sous pression (5).
6. Hélice selon l'une quelconque des revendications 1 et 5, caractérisée en ce que l'élément frontal forment volet abat-son, est concave lorsqu'on regarde depuis le côté sous pression (5).
7. Hélice selon l'une quelconque des revendications 1 à 6, caractérisée en ce que les ailettes d'atténuation acoustique (9, 11) appartenant à l'hélice, sont concaves lorsqu'on les regarde depuis le côté sous pression.
EP82901126A 1981-03-27 1982-03-29 Propulseur notamment pour soufflantes Expired EP0086785B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82901126T ATE28497T1 (de) 1981-03-27 1982-03-29 Schraube insbesondere fuer luefter.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FI810946 1981-03-27
FI810946A FI74115C (fi) 1981-03-27 1981-03-27 Propeller.

Publications (2)

Publication Number Publication Date
EP0086785A1 EP0086785A1 (fr) 1983-08-31
EP0086785B1 true EP0086785B1 (fr) 1987-07-22

Family

ID=8514260

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82901126A Expired EP0086785B1 (fr) 1981-03-27 1982-03-29 Propulseur notamment pour soufflantes

Country Status (7)

Country Link
EP (1) EP0086785B1 (fr)
JP (1) JPS58500449A (fr)
AU (1) AU8332382A (fr)
DE (1) DE3276831D1 (fr)
FI (1) FI74115C (fr)
NO (1) NO823967L (fr)
WO (1) WO1982003430A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FI85752C (fi) * 1989-05-02 1992-05-25 Heikki Vartiala Propeller.
US5328330A (en) * 1993-08-02 1994-07-12 Hudson Products Corporation Extruded aluminum fan blade
DE102007024840A1 (de) * 2007-05-29 2008-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschinenschaufel mit Multi-Profil-Gestaltung

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2045383A (en) * 1934-04-11 1936-06-23 Gen Regulator Corp Propeller
DE647287C (de) * 1934-10-24 1937-07-01 Walter Conrad Dipl Ing Dr Windkraftmaschine mit propelleraehnlichen, in der Windrichtung umklappbaren Windradfluegeln
FR973599A (fr) * 1941-10-06 1951-02-12 Compresseur
GB628263A (en) * 1943-06-01 1949-08-25 Louis Breguet Improvements in or relating to axial flow compressors
DE900372C (de) * 1951-09-09 1953-12-28 Babcock & Wilcox Dampfkessel W Laufrad mit verstellbaren Laufschaufeln fuer Radialgeblaese
US3075743A (en) * 1958-10-20 1963-01-29 Gen Dynamics Corp Turbo-machine with slotted blades
US3173604A (en) * 1962-02-15 1965-03-16 Gen Dynamics Corp Mixed flow turbo machine
DE1815291A1 (de) * 1968-12-18 1970-07-02 Gen Electric Angelenkte Schaufel mit Tragflaechenprofil insbesondere fuer Einlassleitschaufeln von Flugzeugkompressoren
US3627447A (en) * 1969-03-17 1971-12-14 United Aircraft Canada Radial turbines
GB1456020A (en) * 1972-12-06 1976-11-17 Lucas Industries Ltd Centrifugal pumps for liquids method of making a drained floor
US3958905A (en) * 1975-01-27 1976-05-25 Deere & Company Centrifugal compressor with indexed inducer section and pads for damping vibrations therein
JPS51123905A (en) * 1975-04-23 1976-10-29 Nissan Motor Co Ltd Fan

Also Published As

Publication number Publication date
WO1982003430A1 (fr) 1982-10-14
FI74115C (fi) 1987-12-10
FI74115B (fi) 1987-08-31
AU8332382A (en) 1982-10-19
FI810946L (fi) 1982-09-28
EP0086785A1 (fr) 1983-08-31
DE3276831D1 (en) 1987-08-27
JPS58500449A (ja) 1983-03-24
NO823967L (no) 1982-11-26

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