WO2010125645A1 - Ventilateur hélicoïde - Google Patents

Ventilateur hélicoïde Download PDF

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Publication number
WO2010125645A1
WO2010125645A1 PCT/JP2009/058369 JP2009058369W WO2010125645A1 WO 2010125645 A1 WO2010125645 A1 WO 2010125645A1 JP 2009058369 W JP2009058369 W JP 2009058369W WO 2010125645 A1 WO2010125645 A1 WO 2010125645A1
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WO
WIPO (PCT)
Prior art keywords
blade
edge
camber
wing
propeller fan
Prior art date
Application number
PCT/JP2009/058369
Other languages
English (en)
Japanese (ja)
Inventor
俊勝 新井
誠治 中島
仁 菊地
公宣 塩野入
克己 荒木
Original Assignee
三菱電機株式会社
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 三菱電機株式会社 filed Critical 三菱電機株式会社
Priority to PCT/JP2009/058369 priority Critical patent/WO2010125645A1/fr
Priority to CN200980157715.5A priority patent/CN102341603B/zh
Priority to KR1020117018383A priority patent/KR101251130B1/ko
Priority to JP2011511214A priority patent/JP5425192B2/ja
Priority to TW098128650A priority patent/TWI400391B/zh
Publication of WO2010125645A1 publication Critical patent/WO2010125645A1/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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • 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
    • 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 present invention relates to a propeller fan used for a ventilation fan, an air conditioner, or the like.
  • the blades are thin-walled blades and have warpage.
  • An axial fan is disclosed that is provided within a range of 5 to 8% of the chord length and has a maximum camber position within a range of 20 to 40% of the chord length (for example, Patent Document 2). reference).
  • the present invention has been made in view of the above, and an object of the present invention is to obtain a propeller fan that suppresses the blade outer edge vortex generated at the blade outer edge of the propeller fan and has improved air blowing-noise characteristics.
  • the present invention provides a propeller fan including a hub fitted to a rotating shaft and a plurality of blades provided radially on the hub for blowing air in the rotating shaft direction.
  • the ridge line of the largest camber in the cylindrical section of the blade cut along the arbitrary radius from the rotation axis is the chord length from the blade leading edge.
  • the ridgeline of the maximum camber in the cylindrical section of the blade cut along the arbitrary radius from the rotation axis is Is connected to the ridge line of the largest camber in the first region, is located on the blade trailing edge side as the radius increases, and is within 50% of the chord length from the blade leading edge at the blade outer edge.
  • the propeller fan according to the present invention has the effect of suppressing the blade outer edge vortex generated at the blade outer edge and improving the air blowing-noise characteristics.
  • FIG. 1 is a perspective view showing a general propeller fan.
  • FIG. 2-1 is a plan view of the propeller fan according to the first embodiment of the present invention.
  • FIG. 2-2 is a cylindrical cross-sectional view of the first region of the wing of the first embodiment.
  • FIG. 3A is a perspective view schematically showing an air flow on the suction surface side of the blade according to the first embodiment.
  • 3-2 is a cross-sectional view taken along line FF in FIG. 3-1.
  • FIG. 4A is a diagram illustrating an airflow around the blade of the blade having the conventional camber CLD of FIG.
  • FIG. 4-2 is a diagram showing an airflow around the blade of the blade having the camber CLD ′ of the first embodiment shown in FIG. 2-2.
  • FIG. 5 shows a comparison between the specific noise characteristics of the blade having the ridge line CL ′ of the maximum camber of the first embodiment and the specific noise characteristic of the blade having the ridge line CL of the conventional maximum camber shown in FIG.
  • FIG. 6 is a perspective view showing a propeller fan having a blade according to the second embodiment in which the blade inner peripheral front edge side of the blade having the maximum camber ridge line CL ′ of the first embodiment is formed in a waveform.
  • FIG. 7 is a perspective view schematically showing an airflow on the suction surface side of the blade of the second embodiment shown in FIG. FIG.
  • FIG. 8 is a perspective view showing a propeller fan having the blade of the third embodiment in which the blade inner peripheral trailing edge side of the blade having the maximum camber ridge line CL ′ of the first embodiment is formed in a waveform.
  • FIG. 9 is a perspective view schematically showing an air flow on the suction surface side of the blade of the third embodiment shown in FIG.
  • FIG. 10 is a diagram showing the specific noise of the blades shown in FIGS. 6 and 8.
  • FIG. 11 is a perspective view showing a propeller fan having a blade whose outer peripheral side is bent toward the upstream side of the airflow.
  • 12 is a perspective view schematically showing an air flow on the suction surface side of the blade shown in FIG.
  • FIG. 13 is a plan view of the propeller fan shown in FIG.
  • FIG. 14 is a diagram in which the trajectory of each chord center point Pr in FIG. 13 is rotationally projected with a radius R onto a vertical plane including the rotation axis and the 0X axis.
  • FIG. 15 is a diagram showing a chord centerline Pr1 of a blade whose outer peripheral side is bent toward the upstream side of the airflow.
  • FIG. 16 is a view similar to FIG. 15 showing a method of defining the chord centerline Pr1 of the blade whose outer peripheral side is bent toward the upstream side of the airflow.
  • FIG. 17 schematically shows the airflow on the suction surface side of the blade shown in FIG.
  • FIG. 18 is a diagram illustrating specific noise of the propeller fan according to the fourth embodiment of the present invention.
  • FIG. 19 is a diagram illustrating the fan efficiency of the propeller fan according to the fourth embodiment.
  • FIG. 1 is a perspective view showing a general propeller fan
  • FIG. 2-1 is a plan view of the propeller fan according to the first embodiment of the present invention
  • FIG. 2-2 is a blade according to the first embodiment. It is a cylindrical sectional view of the 1st field.
  • the propeller fan shown in FIG. 1 has three blades. However, in the present invention, the number of blades is not limited, and other plural blades may be used. In the following description, the shape of one wing is mainly described, but the shapes of the other wings are the same.
  • a wing 1 having a three-dimensional solid shape shown in FIG. 1 is radially attached to the outer peripheral portion of a cylindrical hub 2 that is driven to rotate by a motor (not shown) and rotates about a rotation axis 3 in the direction of rotation B. Yes.
  • the hub 2 is cylindrical, the wings 1 may be formed radially on the outer periphery of a boss formed by bending a sheet metal.
  • the rotation of the blade 1 generates an airflow in the airflow direction A.
  • the upstream surface of the blade 1 is a negative pressure surface, and the downstream surface is a positive pressure surface.
  • a broken line CL shown in FIG. 2A is a ridge line of the conventional maximum camber of the blade 1 (the locus of the top of the camber), and is located at the center of the blade leading edge 1b and the blade trailing edge 1c.
  • the camber of the blade 1 has an arc shape like a broken line CLD (conventional camber) shown in FIG.
  • the ridge line CL ′ of the maximum camber is positioned at the rim line of the maximum camber at CL1 ′ on the inner periphery side from the radius R2 with the predetermined radius R2 as the boundary, and the maximum camber ridge line CL2
  • the ridge line of the camber is positioned at CL2 ′. That is, on the inner peripheral side from the radius R2, the ridge line CL1 ′ of the maximum camber is closer to the blade leading edge 1b than the ridge line CL of the conventional maximum camber located at the center of the blade leading edge 1b and the blade trailing edge 1c of the blade 1. It has a non-arc shape like the solid line CLD ′ (the camber of the first embodiment) shown in FIG.
  • FIG. 3-1 is a perspective view schematically showing an air flow on the suction surface side of the blade of the first embodiment
  • FIG. 3-2 is a cross-sectional view taken along the line FF in FIG. 3-1.
  • FIG. 4-1 is a diagram showing the airflow around the blade of the wing having the conventional camber CLD of FIG. 2-2
  • FIG. 4-2 has the camber CLD ′ of the first embodiment of FIG. 2-2. It is a figure which shows the airflow around the wing
  • the negative pressure surface air flow H ′ in the camber CLD ′ of the first embodiment having the maximum camber ridge line CL ′ is such that the air flowing in from the blade leading edge 1 b is more than the conventional camber CLD. Also flows along the suction surface 1f, the generation of vortices is suppressed, the size of the blade trailing edge vortex J 'generated at the blade trailing edge 1c is reduced, and the noise is reduced as compared with a blade having a conventional camber CLD. .
  • the wing 1 is shaped like the camber CLD ′, so that the turbulence of the suction surface airflow H ′ is reduced and the noise is reduced.
  • the flow state is significantly different from the blade inner peripheral flow E. Therefore, if the camber on the outer periphery of the blade is uniformly the camber CLD ′, the blade outer edge vortex G may change greatly, and the blowing-noise characteristics may deteriorate.
  • the ridge line CL ′ of the maximum camber of the blade 1 is set to ridge lines having different forms of CL1 ′ and CL2 ′, and the ridge line CL1 ′ of the maximum camber is set.
  • the blade is positioned within 50% of the chord length from the blade leading edge 1b, and the blade trailing edge 1c side as the radius increases from the position where the ridge line CL2 'of the maximum camber outer peripheral portion is connected to the ridge line CL1' of the maximum camber And located within 50% of the chord length at the blade outer edge 1d.
  • Reference sign CLt shown in FIG. 2A is the maximum camber position at the blade outer edge
  • reference sign CLb is the maximum camber position at the blade inner edge of the conventional blade
  • reference sign CLb ′ is the blade inner edge of the blade of the first embodiment. Is the maximum camber position.
  • FIG. 5 shows a comparison between the specific noise characteristics of the blade having the ridge line CL ′ of the maximum camber of the first embodiment and the specific noise characteristic of the blade having the ridge line CL of the conventional maximum camber shown in FIG. FIG.
  • the ridge line CL ′ of the maximum camber of the first embodiment shown in FIG. 5 is from the blade leading edge 1b.
  • the radius increases from 35% of the blade chord length.
  • the conventional blade used for comparison is a blade in which the ridge line CL of the maximum camber is located at a position of 50% of the chord length from the blade leading edge 1b.
  • K T SPL A -10 Log (Q ⁇ P T 2.5 ) Q: Air volume [m 3 / min] P T : Total pressure [Pa] SPL A : Noise characteristics (after A correction) [dB]
  • the vertical axis represents specific noise
  • one scale indicated by a broken line represents a difference of 1 [dBA]
  • the horizontal axis represents the air volume.
  • the blade having the maximum camber ridge line CL ′ of the first embodiment has a noise level of about ⁇ 1 [dBA] at maximum.
  • FIG. FIG. 6 is a perspective view showing a propeller fan 92 having the blade 21 of the second embodiment in which the blade inner peripheral front edge side of the blade having the maximum camber ridge line CL ′ of the first embodiment is formed in a waveform 21 m.
  • the waveform of the blade leading edge 21b is the maximum waveform, and gradually decreases toward the blade center.
  • FIG. 7 is a perspective view schematically showing an air flow on the suction surface side of the blade 21 of the second embodiment shown in FIG. As shown in FIG. 7, a vertical vortex is generated in the air flowing into the blade leading edge 21b by the waveform 21m of the blade 21, and the blade inner circumferential flow E is changed to an air flow E2 with less turbulence, resulting from the turbulence of the air flow. Noise can be reduced.
  • FIG. FIG. 8 is a perspective view showing a propeller fan 93 having the blade 31 of the third embodiment in which the trailing edge side of the inner peripheral portion of the blade having the ridge line CL ′ of the maximum camber of the first embodiment is formed in a waveform 31n.
  • the waveform of the blade trailing edge 31c is set to the maximum waveform, and gradually decreases toward the center of the blade.
  • FIG. 9 is a perspective view schematically showing the airflow on the suction surface side of the blade 31 of the third embodiment shown in FIG.
  • the turbulence of the air due to the vortex generated at the blade trailing edge 31c is reduced by the vertical vortex generated by the waveform 31n of the wing 31 to further reduce the turbulence to the air flow E3. Noise can be reduced.
  • FIG. 10 is a diagram showing the specific noise of the blades 21 and 31 shown in FIG. 6 and FIG. As shown in FIG. 10, in the region where the air volume is large, the blades 21 and 31 having a waveform on the inner circumferential side of the blade have a lower noise level by about ⁇ 0.5 [dBA].
  • FIG. 11 is a perspective view showing a propeller fan having a blade whose outer peripheral side is bent toward the upstream side of the airflow
  • FIG. 12 is a perspective view schematically showing an airflow on the suction surface side of the blade shown in FIG. .
  • the propeller fan having a blade whose outer peripheral side is bent toward the upstream side of the airflow shown in FIGS. 11 and 12 can weaken the blade outer edge vortex generated on the blade outer edge suction surface and reduce noise caused by the blade outer edge vortex.
  • the pressure increase component generated by the rotation of the blade partially leaks to the negative pressure surface side, and the fan efficiency is slightly reduced.
  • the blade noise sources shown in FIGS. 1 and 11 are caused by the blade outer edge vortex generated at the blade outer edge, the blade suction surface flow turbulence, and the blade trailing edge vortex. There is something. In a blade whose outer peripheral side is bent toward the upstream side of the airflow, the proportion of noise caused by the blade outer edge vortex is reduced, and the proportion of noise generated from the inner peripheral flow is relatively increased. Therefore, it is necessary to improve the inner peripheral flow of the blade and to examine the shape of the blade that does not affect the outer peripheral flow of the blade.
  • FIG. 13 is a plan view in which the propeller fan shown in FIG. 1 is projected onto a plane orthogonal to the rotation axis, and FIG. 14 shows the trajectory of each chord center point Pr in FIG. 13 including the rotation axis and the 0X axis.
  • FIG. 15 is a diagram showing the blade chord centerline Pr1 of the blade whose outer peripheral side is bent toward the upstream side of the airflow
  • FIG. 16 is a diagram showing the blade outer peripheral side upstream of the airflow.
  • FIG. 16 is a view similar to FIG. 15 showing a method of defining a chord centerline Pr1 of a wing bent sideways.
  • FIG. 13 to FIG. 16 the definition of the shape of the blade whose outer peripheral side is bent toward the upstream side of the airflow will be described.
  • the shape of the blade 1 shown in FIG. 13 is obtained.
  • a point Pb shown in FIG. 13 indicates a chord center point (middle point) from the blade leading edge 1 b to the blade trailing edge 1 c on the outer periphery of the hub 2.
  • Pt represents the chord center point (midpoint) from the blade leading edge 1b to the blade trailing edge 1c at the blade outer edge 1d.
  • a line Pr shown in FIG. 13 indicates a locus (chord chord centerline) of each chord center point at an arbitrary radius R from the chord center point Pb of the hub to the chord center point Pt of the outer edge of the blade.
  • FIG. 14 shows the trajectory (blade chord centerline) of each chord center point from the chord center point Pb of the hub to the chord center point Pt of the outer edge of FIG. 13, that is, the chord center point Pb-Pr-Pt.
  • FIG. 5 is a diagram showing a locus (chord chord centerline) of each chord center point Pr obtained by rotating and projecting each chord center point Pr at an arbitrary radius R on the vertical plane including the rotation axis 3 and the 0X axis at the radius R. is there.
  • chord centerline Pr (the trajectory of each chord center point Pr) that is rotationally projected onto a vertical plane including the rotation axis 3 and the 0X axis is the blade chord center point Pb of the hub 2.
  • the forward tilt angle ⁇ z that is inclined to the upstream side of the airflow up to the chord center point Pt of the outer edge can be represented as a line that forms a certain angle with the plane Sc that is orthogonal to the rotation axis 3.
  • the chord centerline Pr indicated by a broken line in FIG. 15 is a locus of the chord center point of the wing 1 having a forward tilt angle ⁇ z shown in FIG. 14, and the wing outer periphery is bent toward the upstream side of the airflow.
  • chord centerline Pr and the chord centerline Pr1 are such that the chord center point Pb of the hub and the chord center point Pt of the blade outer edge are at the same position, and the chord center point Pt of the blade outer edge from the plane Sc of the chord center point Pt.
  • the distance is H.
  • FIG. 16 shows the trajectory and forward tilt angle of each chord center point Pr2 of the blade of the fourth embodiment in which the blade outer peripheral portion is bent toward the upstream side of the airflow A.
  • a chord center point at an arbitrary radius R from the rotation axis 3 is Pr2, and a distance from the plane Sc perpendicular to the rotation axis 3 of the chord center point Pr2 located on the chord centerline Pr1 is Ls.
  • the first region from the hub 2 (radius Rb) to the bending point Pw in the radial intermediate portion is inclined to the upstream side at a constant first forward inclination angle ⁇ zw.
  • the second region from the point Pw to the blade outer edge is inclined further upstream than the first region.
  • the radius of the bending point Pw on the chord center line Pr1 is Rw
  • the second inclination angle is the upstream angle of the line Pr connecting the chord center point Pt on the outer edge of the blade and the chord center point Pb on the outer periphery of the hub 2.
  • the forward tilt angle be ⁇ zt.
  • the inclination angle ⁇ zd corresponding to the chord center point Pr2 at an arbitrary radius R in the second region between the bending point Pw and the blade outer edge (radius Rt) is an n-order function of the radius R ( 1 ⁇ n).
  • the chord center line Pr1 in the second region is linearly inclined upstream at a certain forward tilt angle without using the tilt angle ⁇ zd as an n-order function (1 ⁇ n) of the radius R. Also good.
  • FIG. 17 is a blade having the maximum camber ridge line CL ′ of the first embodiment shown in FIG. 2-1, and the airflow on the blade suction surface side of the blade 41 whose outer periphery is bent toward the upstream side of the airflow.
  • FIG. 17 according to the blade 41 of the fourth embodiment, the blade outer peripheral flow and the blade inner peripheral flow can be improved at the same time, and the blower-noise characteristics can be improved.
  • FIG. 18 is a diagram illustrating the specific noise of the propeller fan according to the fourth embodiment of the present invention
  • FIG. 19 is a diagram illustrating the fan efficiency of the propeller fan according to the fourth embodiment.
  • the maximum camber ridgeline CL ′ is located 35% of the chord length from the blade leading edge in the propeller fan blade 41 of the fourth embodiment.
  • the ridge line CL ′ of the maximum camber is arranged from the position of 35% of the chord length to the position of 50% of the chord length at the blade outer edge. .
  • Figure 18 shows the result of obtaining a relation between air volume Q and the specific noise K T experimentally
  • Figure 19 shows the results obtained experimentally the relationship between the air volume Q and the fan efficiency E T.
  • the propeller fan 94 according to the fourth embodiment has a specific noise KT reduced in a practical range as compared with a conventional propeller fan whose blade outer peripheral portion is bent toward the upstream side of the airflow. (-1DBA) is, and the fan efficiency E T is improved (up to + 2-3 about points).
  • E T (P T ⁇ Q) / (60 ⁇ P W ) Q: Air volume [m 3 / min]
  • P T Total pressure [Pa]
  • P W Shaft power [W]
  • the propeller fan according to the present invention is suitable for a ventilation fan, an air conditioner, and the like.

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

Abstract

L'invention porte sur un ventilateur hélicoïde qui comprend un moyeu adapté sur une tige, et une pluralité de pales montées radialement sur le moyeu pour souffler de l'air dans la direction de la tige. Dans une première région de la pale à partir de la tige jusqu'à un rayon prédéterminé, les lignes de bord de la cambrure maximale dans la section cylindrique de la pale, qui est coupée de la tige le long d'un rayon arbitraire, est à l'intérieur de 50% d'une longueur de corde de pale à partir d'un bord d'attaque de pale. Dans une seconde région de la pale à partir du rayon prédéterminé jusqu'à un bord externe de pale, la ligne de bord de la cambrure maximale dans la section cylindrique de la pale, qui est coupée de la tige le long du rayon arbitraire, est reliée, en la position radiale prédéterminée, à la ligne de bord de la cambrure maximale de la première région et est positionnée, en étant élargie radialement, sur le côté d'un bord de fuite de pale, de telle sorte que la ligne de bord est comprise à l'intérieur des 50% de la longueur de corde de pale à partir d'un bord d'attaque de pale jusqu'à un bord externe de pale.
PCT/JP2009/058369 2009-04-28 2009-04-28 Ventilateur hélicoïde WO2010125645A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
PCT/JP2009/058369 WO2010125645A1 (fr) 2009-04-28 2009-04-28 Ventilateur hélicoïde
CN200980157715.5A CN102341603B (zh) 2009-04-28 2009-04-28 螺旋桨式风扇
KR1020117018383A KR101251130B1 (ko) 2009-04-28 2009-04-28 프로펠러 팬
JP2011511214A JP5425192B2 (ja) 2009-04-28 2009-04-28 プロペラファン
TW098128650A TWI400391B (zh) 2009-04-28 2009-08-26 螺旋翼風扇

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Application Number Priority Date Filing Date Title
PCT/JP2009/058369 WO2010125645A1 (fr) 2009-04-28 2009-04-28 Ventilateur hélicoïde

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WO2010125645A1 true WO2010125645A1 (fr) 2010-11-04

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JP (1) JP5425192B2 (fr)
KR (1) KR101251130B1 (fr)
CN (1) CN102341603B (fr)
TW (1) TWI400391B (fr)
WO (1) WO2010125645A1 (fr)

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CN103629156A (zh) * 2013-11-28 2014-03-12 浙江亿利达风机股份有限公司 一种低噪高效的中央空调室外机冷却轴流风机
JP6373439B1 (ja) * 2017-03-31 2018-08-15 テラル株式会社 軸流ファン
EP3613994A4 (fr) * 2017-04-19 2020-04-22 Mitsubishi Electric Corporation Ventilateur à hélice et unité extérieure de dispositif de climatisation

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WO2013154102A1 (fr) * 2012-04-10 2013-10-17 シャープ株式会社 Ventilateur à hélice, dispositif d'envoi de fluide, et moule destiné au moulage
US11333165B2 (en) 2016-12-28 2022-05-17 Daikin Industries, Ltd. Propeller fan
JP6414268B2 (ja) * 2016-12-28 2018-10-31 ダイキン工業株式会社 プロペラファン
CN106903875A (zh) * 2017-03-16 2017-06-30 青岛科技大学 一种3d打印用小型螺杆塑化装置
JP6428833B2 (ja) * 2017-04-14 2018-11-28 ダイキン工業株式会社 プロペラファン

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JP2002021787A (ja) * 2000-07-05 2002-01-23 Fujitsu General Ltd 軸流送風機の羽根車
JP2005307788A (ja) * 2004-04-20 2005-11-04 Mitsubishi Electric Corp 軸流ファン
JP2008255966A (ja) * 2007-04-09 2008-10-23 Mitsubishi Electric Corp プロペラファン

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103629156A (zh) * 2013-11-28 2014-03-12 浙江亿利达风机股份有限公司 一种低噪高效的中央空调室外机冷却轴流风机
JP6373439B1 (ja) * 2017-03-31 2018-08-15 テラル株式会社 軸流ファン
EP3613994A4 (fr) * 2017-04-19 2020-04-22 Mitsubishi Electric Corporation Ventilateur à hélice et unité extérieure de dispositif de climatisation

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KR20110104548A (ko) 2011-09-22
JP5425192B2 (ja) 2014-02-26
JPWO2010125645A1 (ja) 2012-10-25
CN102341603A (zh) 2012-02-01
TW201038825A (en) 2010-11-01
KR101251130B1 (ko) 2013-04-05
TWI400391B (zh) 2013-07-01

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