US20080253897A1 - Axial Flow Fan - Google Patents

Axial Flow Fan Download PDF

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Publication number
US20080253897A1
US20080253897A1 US11/922,599 US92259906A US2008253897A1 US 20080253897 A1 US20080253897 A1 US 20080253897A1 US 92259906 A US92259906 A US 92259906A US 2008253897 A1 US2008253897 A1 US 2008253897A1
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US
United States
Prior art keywords
impeller blades
edge portion
outer peripheral
rear edge
axial flow
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.)
Abandoned
Application number
US11/922,599
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English (en)
Inventor
Jiro Yamamoto
Masahiro Shigemori
Kouji Somahara
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.)
Daikin Industries Ltd
Original Assignee
Daikin Industries Ltd
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Filing date
Publication date
Application filed by Daikin Industries Ltd filed Critical Daikin Industries Ltd
Assigned to DAIKIN INDUSTRIES, LTD. reassignment DAIKIN INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SOMAHARA, KOUJI, SHIGEMORI, MASAHIRO, YAMAMOTO, JIRO
Publication of US20080253897A1 publication Critical patent/US20080253897A1/en
Abandoned 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
    • 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
    • F04D29/388—Blades characterised by construction
    • 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
    • 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
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/10—Kind or type
    • F05D2210/12—Kind or type gaseous, i.e. compressible
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S417/00—Pumps

Definitions

  • the present invention relates to a structure of an axial flow fan such as a propeller fan or the like.
  • This kind of axial flow fan is used as an air blower of an outdoor unit for an air conditioner.
  • the outdoor unit for the air conditioner is provided with a box-like casing 1 .
  • An air suction port 10 a is provided on a back surface of the casing 1 .
  • a heat exchanger 2 is arranged within the casing 1 so as to be adjacent to the air suction port 10 a.
  • a fan motor 12 and an air blowing unit 3 driven by the fan motor 12 are arranged downstream of the heat exchanger 2 .
  • the fan motor 12 is fixed to the casing 1 using a bracket (not shown).
  • the air blowing unit 3 is provided with a propeller fan 4 serving as an axial flow fan.
  • the propeller fan 4 is provided with a hub 14 , and a plurality of impeller blades 13 . Each of the impeller blades 13 is integrated on an outer peripheral surface of the hub 14 .
  • the propeller fan 4 is coupled to a driving shaft 12 a of the fan motor 12 .
  • the air blowing unit 3 is provided with a bell mouth 5 arranged near an outer periphery of the propeller fan 4 , and a fan guard 6 arranged in a front side of the propeller fan 4 .
  • the bell mouth 5 partitions a suction region X positioned in a rear side of the propeller fan 4 and a blow region Y positioned in a front side thereof.
  • the center of the eddy current (A 2 ) gradually separates from the negative pressure surface 13 e of each of the impeller blades 13 .
  • the eddy current (A 2 ) comes into collision with the pressure surface 13 d of each of the impeller blades 13 , the inner peripheral surface of the bell mouth 5 , the fan guard 6 and the like, which can further increase the noise of the blower.
  • each of the impeller blades 13 For example, if the chord length of each of the impeller blades 13 is shortened for weight saving (cost reduction), a blade lattice performance generated by each of the impeller blades 13 is lowered. Accordingly, the eddy current (A 2 ) tends to separate from the negative pressure surface 13 e of each of the impeller blades 13 . As shown in FIG. 11 , the eddy current (A 2 ) interferes with the subsequent impeller blade 13 early in comparison with the case in FIG. 10 . Therefore, the noise of the blower tends to be further increased.
  • a propeller fan provided with a bent portion 13 c along the outer peripheral edge of each of the impeller blades 13 (for example, refer to Patent Document 1).
  • the bent portion 13 c is formed by bending the outer peripheral edge of the impeller blade 13 toward the negative pressure surface 13 e (the suction side).
  • the width d of the bent portion 13 c is set to become gradually larger toward the rear edge portion 13 b from the front edge portion 13 a of each of the impeller blades 13 .
  • the air flow (A 1 ) smoothly goes around to the negative pressure surface 13 e from the pressure surface 13 d through the bent portion 13 c of each of the impeller blades 13 .
  • the eddy current (A 2 ) generated by the air flow (A 1 ) is formed near the outer peripheral edge of each of the impeller blades 13 .
  • the diameter of the eddy current (A 2 ) is small, it is possible to suppress the interference between the eddy current (A 2 ) and the air flow (A 3 ) of the negative pressure surface 13 e of each of the impeller blades 13 .
  • the diameter of the eddy current (A 2 ) becomes gradually larger toward the rear edge portion 13 b from the front edge portion 13 a of each of the impeller blades 13 . If the width d of each of the bent portions 13 c is made larger toward the rear edge portion 13 b from the front edge portion 13 a of each of the impeller blades 13 in correspondence thereto, the operations and effects mentioned above can be achieved over the entire outer peripheral edge of each of the impeller blades 13 , and it is hard for the eddy current (A 2 ) to separate from the negative pressure surface 13 e of each of the impeller blades 13 .
  • the eddy currents (A 2 ) do not interfere with each other between adjacent impeller blades 13 , and the turbulence of the air flow is reduced in the downstream side of the blower.
  • the noise of the blower can be effectively reduced by incorporating the propeller fan in the outdoor unit for the air conditioner.
  • Patent Document 1 Japanese Patent No. 3629702
  • the width d of the bent portion 13 c is preferably set to be equal to or less than 15% of the length from the center of rotation of each of the impeller blades 13 to the outer peripheral end.
  • the width d of the bent portion 13 c is optimized, a certain degree of reduction of the amount of rise in pressure is unavoidable.
  • each of the impeller blades 13 is formed along a circular arc, and shallowly and widely protrude in an inverse direction to a rotating direction of each of the impeller blades 13 with respect to a straight line L connecting a proximal end of each of the impeller blades 13 and the outer peripheral edge. Accordingly, a vane area of each of the impeller blades 13 is sufficiently secured.
  • An objective of the present invention is to provide an axial flow fan which effectively compensates for shortage of the amount of rise in static pressure which is lowered by bending the outer peripheral edge of an impeller blade.
  • an axial flow fan includes a plurality of impeller blades ( 13 ) provided on a hub ( 14 ), and a plurality of bent portions ( 13 c ) each formed by bending an outer peripheral edge of each of the impeller blades ( 13 ) toward a negative pressure surface ( 13 e ) of the impeller blade ( 13 ).
  • a protruding portion ( 13 f ) is provided in a portion in which a blowing wind speed is high and a pressure rising work is most effectively carried out in a rear edge portion ( 13 b ) of each of the impeller blades ( 13 ).
  • Each of the protruding portions ( 13 f ) protrudes to an inverse direction to a rotating direction of the impeller blade ( 13 ) with respect to a straight line L connecting a proximal end and an outer peripheral end in the rear edge portion ( 13 b ) of each of the impeller blades ( 13 ).
  • an air flow (A 1 ) in the pressure surface 13 d of each of the impeller blades 13 smoothly goes around to the negative pressure surface 13 e from the outer peripheral edge of each of the impeller blades 13 .
  • an eddy current (A 2 ) having a small diameter is formed near the outer peripheral edge of each of the impellers 13 . Accordingly, it is possible to suppress an interference between an air flow (A 3 ) of the negative pressure surface 13 e of each of the impeller blades 13 and the eddy current (A 2 ).
  • the protruding portion 13 f is provided in the portion in which the blowing wind speed is high and the pressure rising work is most effectively carried out. Further, the protruding portion 13 f is protruded in the inverse direction to the rotating direction of each of the impeller blades 13 with respect to the straight line L connecting the proximal end and the outer peripheral end in the rear edge portion of each of the impellers 13 . If the vane area of each of the impeller blades 13 is enlarged as mentioned above, it is possible to effectively compensate for the shortage of the amount of rise in static pressure which is lowered by bending the outer peripheral edge of each of the impeller blades 13 to the negative pressure surface 13 e. Accordingly, it is possible to achieve a reduction of a blowing noise and a high efficiency of the blowing performance.
  • each of the bent portions ( 13 c ) is provided over the entirety of each of the impeller blades ( 13 ) from the front edge portion ( 13 a ) to the rear edge portion ( 13 b ).
  • the air flow (A 1 ) of the pressure surface 13 d of each of the impeller blades 13 smoothly goes around to the negative pressure surface 13 e from the outer peripheral edge of each of the impeller blades 13
  • the eddy current (A 2 ) having the small diameter is formed near the outer peripheral edge of each of the impeller blades 13 , and it is possible to suppress the interference between the air flow (A 3 ) of the negative pressure surface 13 e of each of the impeller blades 13 and the eddy current (A 2 ).
  • each of the bent portions ( 13 c ) is provided in the portion from the position between the front edge portion ( 13 a ) and the rear edge portion ( 13 b ) in each of the impeller blades ( 13 ) to the rear edge portion ( 13 b ).
  • the air flow (A 1 ) of the pressure surface 13 d of each of the impeller blades 13 smoothly goes around to the negative pressure surface 13 e from the outer peripheral edge of each of the impeller blades 13 , the eddy current (A 2 ) having the small diameter is formed near the outer peripheral edge of each of the impeller blades 13 , and it is possible to suppress the interference between the air flow (A 3 ) of the negative pressure surface 13 e in each of the impeller blades 13 and the eddy current (A 2 ).
  • each of the bent portions ( 13 c ) is formed so as to become gradually larger toward the rear edge portion ( 13 b ) from the front edge portion ( 13 a ) of each of the impeller blades ( 13 ).
  • the portion protruding most largely in the inverse direction to the rotating direction with respect to the straight line L is set in a region in which a value of an expression (R ⁇ Rh)/(Rt ⁇ Rh) is between 0.65 and 0.85, in which the radius of the axial flow fan is represented by Rt, the radius of the hub ( 14 ) is represented by Rh, and the distance in a radial direction from the center O of rotation of the axial flow fan is represented by R.
  • the portion in which the blowing wind speed is highest and the pressure rising work is most effectively carried out is a region in which a value of the expression (R ⁇ Rh)/(Rt ⁇ Rh) is between 0.65 and 0.85 in which the radius of the axial flow fan is represented by Rt, the radius of the hub 14 is represented by Rh, and the distance in a radial direction from the center O of rotation of the axial flow fan is represented by R.
  • the vane area of each of the impeller blades 13 is enlarged by setting the protruding portion 13 f protruding in the opposite direction to the rotating direction of the axial flow fan with respect to the straight line L connecting the proximal end and the outer peripheral end of each of the impeller blades in the rear edge portion of each of the impeller blades.
  • FIG. 1 is a rear view showing a propeller fan and a bell mouth in accordance with the present embodiment
  • FIG. 2 is a perspective view showing the propeller fan
  • FIG. 3 is a rear view showing the propeller fan
  • FIG. 4 is a graph showing a relation between the position of a rear edge portion of an impeller blade and a blowing wind speed
  • FIG. 5 is a partly enlarged plain view showing an impeller blade in accordance with a modified embodiment
  • FIG. 6 is a vertical cross-sectional view showing the whole structure of an outdoor unit for an air conditioner using a conventional propeller fan;
  • FIG. 7 is a rear view showing the conventional propeller fan
  • FIG. 8 is a partly cross-sectional view showing a cross-sectional structure of an impeller blade of the conventional propeller fan and its problems;
  • FIG. 9 is an explanatory view showing a generating mechanism of an eddy current of the conventional propeller fan
  • FIG. 10 is an explanatory view showing an eddy current interference phenomenon of the conventional propeller fan
  • FIG. 11 is an explanatory view showing the eddy current interference phenomenon in the case that the chord length of an impeller blade is made short in the conventional propeller fan;
  • FIG. 12 is a perspective view showing a basic shape of the impeller blade coping with a problem of the conventional propeller fan
  • FIG. 13 is a cross-sectional view showing an eddy current suppressing effect of the propeller fan in FIG. 12 ;
  • FIG. 14 is an explanatory view showing an eddy current interference phenomenon of the propeller fan in FIG. 12 ;
  • FIG. 15 is a partly enlarged plain view showing a problem of the propeller fan in FIG. 12 .
  • a propeller fan according to one embodiment of the present invention will now be described with reference to FIGS. 1 to 4 .
  • a propeller fan 4 is provided with a hub 14 made of a synthetic resin, and three impeller blades 13 .
  • Each of the impeller blades 13 is integrally formed on an outer peripheral surface of the hub 14 .
  • An outer peripheral end of a front edge portion 13 a and an outer peripheral end of a rear edge portion 13 b in each of the impeller blades 13 are arranged in an offset manner in a rotating direction of the impeller blade 13 in comparison with a proximal end of the impeller blade 13 .
  • the entire outer peripheral edge of each of the impeller blades 13 is bent toward a negative pressure surface 13 e (a suction side) of the impeller blade 13 shown in FIG. 2 , from the front edge portion 13 a to the rear edge portion 13 b.
  • the width d of each of the bent portions 13 c is enlarged at a predetermined rate toward the rear edge portion 13 b from the front edge portion 13 a of each of the impeller blades 13 .
  • the maximum value of the width d of the bent portion 13 c be equal to or less than 15% of the length from the center of rotation of the propeller fan 4 (the center of the hub 14 ) to an outer peripheral end of each of the impeller blades 13 .
  • a protruding portion 13 f is provided in the rear edge portion 13 b of each of the impeller blades 13 .
  • Each of the protruding portions 13 f is provided in a portion in which a blowing wind speed is highest and a pressure rising work can be effectively carried out (a region shown by an outer peripheral line having a diameter ⁇ 1 to ⁇ 5 of the propeller fan 4 in FIG. 3 ).
  • Each of the protruding portions 13 f protrudes to an inverse direction to a rotating direction M of each of the impeller blades 13 , with respect to a straight line L (a broken line in FIG. 3 ) connecting the proximal end and the outer peripheral end of the rear edge portion 13 b in each of the impeller blades 13 .
  • each of the protruding portions 13 f a portion which most largely protrudes to the inverse direction to the rotating direction M of the impeller blade 13 is set to a maximum protruding portion T.
  • the radius of the propeller fan 4 is represented by Rt
  • the radius of the hub 14 is represented by Rh
  • the distance in a radial direction from the center O of rotation of the propeller fan 4 is represented by R
  • the maximum protruding portion T is set in a region in which a value (R ⁇ Rh)/(Rt ⁇ Rh) is between 0.65 and 0.85.
  • a blowing wind speed of the fan at a time of changing the value (R ⁇ Rh)/(Rt ⁇ Rh) between 0 and 1.0 is measured with respect to the impeller blade 13 of the propeller fan 4 which does not have the bent portion 13 c shown in FIGS. 7 and 8 , and the impeller blade 13 of the propeller fan 4 which has the bent portion 13 c shown in FIGS. 1 to 3 , and FIGS. 12 and 13 .
  • the results thereof are shown in FIG. 4 .
  • the bent portion 13 c is provided in a region (between outer peripheral lines having diameters ⁇ 5 and ⁇ 6 of the propeller fan 4 in FIG. 3 ) in which the value (R ⁇ Rh)/(Rt ⁇ Rh) is between 0.9 and 1.0. Accordingly, it is preferable that the protruding portion 13 f is provided in a region in which the value of (R ⁇ Rh)/(Rt ⁇ Rh) is between 0.65 and 0.85.
  • the maximum protruding portion T of the protruding portion 13 f is provided in a region in which the blowing wind speed becomes highest, in a region radially inside of the boundary (the outer peripheral line having the diameter ⁇ 5 of the propeller fan in FIG. 3 ) with the bent portion 13 c, for example, a region in which the value (R ⁇ Rh)/(Rt ⁇ Rh) is about 0.75.
  • the maximum protruding portion T of the protruding portion 13 f is provided in a region in which the value of (R ⁇ Rh)/(Rt ⁇ Rh) is about 0.5.
  • the blowing wind speed is low despite the enlargement of the vane area of each of the impeller blades 13 , so that the amount of rise in static pressure cannot be sufficiently enlarged.
  • each of the impeller blades 13 is bent toward the negative pressure surface 13 e of the impeller blade 13 from the front edge portion 13 a to the rear edge portion 13 b.
  • the air flow (A 1 ) of the pressure surface 13 d of each of the impeller blades 13 smoothly goes around to the negative pressure surface 13 e from the outer peripheral edge of each of the impeller blades 13 .
  • the small eddy current (A 2 ) having a small diameter is formed near the outer peripheral edge of each of the impeller blades 13 . Accordingly, an interference between the air flow A 3 and the eddy current (A 2 ) in the negative pressure surface 13 e of each of the impeller blades 13 is suppressed.
  • the protruding portion 13 f is provided in the portion in which the blowing wind speed is high, and the pressure rising work can be most effectively carried out.
  • Each of the protruding portions 13 f protrudes to the inverse direction to the rotating direction of each of the impeller blades 13 with respect to the straight line L connecting the base and the outer peripheral end of the rear edge portion 13 b of each of the impeller blades 13 . If the vane area of each of the impeller blades 13 is enlarged as mentioned above, it is possible to effectively compensate for the shortage of the amount of rise in static pressure which is lowered by bending the outer peripheral edge of each of the impeller blades 13 . Accordingly, it is possible to achieve a reduction of a blowing noise and a high efficiency of the blowing performance.
  • each of the bent portions 13 c is formed to become larger toward the rear edge portion 13 b from the front edge portion 13 a of each of the impeller blades 13 . Accordingly, it is possible to effectively make the eddy current (A 2 ) small from the front edge portion 13 a to the rear edge portion 13 b in correspondence to the eddy current (A 2 ) in which the diameter becomes larger toward the rear edge portion 13 b from the front edge portion 13 a of each of the impeller blades 13 , and it is possible to make it hard for the eddy current (A 2 ) to separate from the negative pressure surface 13 e of each of the impeller blades 13 .
  • the position of the maximum protruding portion T is set in the region in which the value of (R ⁇ Rh)/(Rt ⁇ Rh) is between 0.65 and 0.85.
  • the region in which the blowing wind speed is high and the pressure rising work can be most effectively carried out is the region in which the value of (R ⁇ Rh)/(Rt ⁇ Rh) is between 0.65 and 0.85. if the vane area of each of the impeller blades 13 is enlarged by protruding the region to the opposite direction to the rotating direction of the propeller fan 4 , it is possible to effectively compensate for the shortage of the amount of rise in static pressure which is lowered by bending the outer peripheral edge of each of the impeller blades 13 .
  • the bent portion 13 c is provided over the entire outer peripheral edge of each impeller blade 13 from the front edge portion 13 a to the rear edge portion 13 b.
  • the bent portion 13 c may be provided in a portion from a position between the front edge portion 13 a and the rear edge portion 13 b to the rear edge portion 13 b.
  • the position between the front edge portion 13 a and the rear edge portion 13 b is preferably set to a position which is offset from the front edge portion 13 a to the rear edge portion 13 b at about 25% of the entire length of the outer peripheral edge of the impeller blade 13 .
  • the air flow (A 1 ) of the pressure surface 13 d in each of the impeller blades 13 smoothly goes around to the negative pressure surface 13 e from the outer peripheral edge of the impeller blade 13 .
  • the eddy current (A 2 ) having a small diameter is formed near the outer peripheral edge of each of the impeller blades 13 . Accordingly, the interference between the air flow (A 3 ) of the negative pressure surface 13 e in each of the impeller blades 13 and the eddy current (A 2 ) is suppressed.
  • the present invention is embodied in impeller blades having a thin vane structure.
  • the present invention is not limited to thin vane structures, but may be applied, for example, to a vane having a thick structure, various air foil vane 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)
US11/922,599 2005-07-21 2006-07-19 Axial Flow Fan Abandoned US20080253897A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2005-211542 2005-07-21
JP2005211542A JP5259919B2 (ja) 2005-07-21 2005-07-21 軸流ファン
PCT/JP2006/314259 WO2007010936A1 (ja) 2005-07-21 2006-07-19 軸流ファン

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US20080253897A1 true US20080253897A1 (en) 2008-10-16

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US11/922,599 Abandoned US20080253897A1 (en) 2005-07-21 2006-07-19 Axial Flow Fan

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US (1) US20080253897A1 (zh)
EP (1) EP1906028A4 (zh)
JP (1) JP5259919B2 (zh)
KR (1) KR20080009762A (zh)
CN (1) CN101203680B (zh)
AU (1) AU2006270875B2 (zh)
WO (1) WO2007010936A1 (zh)

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US20110127019A1 (en) * 2009-11-27 2011-06-02 Sanyo Electric Co., Ltd. Bell-mouth structure of air blower
US20140356149A1 (en) * 2013-05-30 2014-12-04 Delta Electronics, Inc. Fan
US20150345513A1 (en) * 2012-12-27 2015-12-03 Mitsubishi Electric Corporation Propeller fan, air blower, outdoor unit
US9647501B2 (en) 2013-02-14 2017-05-09 Mitsubishi Electric Corporation Interior permanent magnet motor, compressor and refrigeration and air conditioning apparatus
CN107882772A (zh) * 2016-09-29 2018-04-06 山洋电气株式会社 可逆式送风扇
CN112253537A (zh) * 2020-11-19 2021-01-22 泛仕达机电股份有限公司 一种仿生轴流风轮
CN114641619A (zh) * 2019-11-12 2022-06-17 三菱电机株式会社 轴流风扇、送风装置及制冷循环装置

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JP5379138B2 (ja) * 2007-08-23 2013-12-25 グーグル・インコーポレーテッド 領域辞書の作成
DE102008055631A1 (de) * 2008-11-03 2010-05-06 Rolls-Royce Deutschland Ltd & Co Kg Nabenkonus für ein Flugzeugtriebwerk
JP5287329B2 (ja) * 2009-02-17 2013-09-11 株式会社日立プラントテクノロジー ポンプインペラ
WO2011116231A2 (en) 2010-03-19 2011-09-22 Sp Tech Propeller blade
CN103185037B (zh) * 2011-12-28 2015-12-02 珠海格力电器股份有限公司 轴流风扇及具有其的空调器
CN103185036B (zh) * 2011-12-28 2015-06-03 珠海格力电器股份有限公司 轴流风扇及具有其的空调器
CN103486081B (zh) * 2012-06-11 2017-02-01 珠海格力电器股份有限公司 轴流风叶、风机及空调器室外机
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CN104895838A (zh) * 2014-03-05 2015-09-09 珠海格力电器股份有限公司 轴流风叶及轴流风机
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CN104358712A (zh) * 2014-11-28 2015-02-18 德清振达电气有限公司 一种安全高效的轴流风扇扇叶
WO2016117413A1 (ja) * 2015-01-20 2016-07-28 シャープ株式会社 プロペラファン、流体送り装置および成形用金型
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CN108151287A (zh) * 2017-12-04 2018-06-12 周亮 一种柜式空调内机固定架
CN114909325A (zh) * 2022-05-30 2022-08-16 华中科技大学 一种低噪声轴流风机叶片及轴流风机

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JP2007024004A (ja) 2007-02-01
WO2007010936A1 (ja) 2007-01-25
JP5259919B2 (ja) 2013-08-07
CN101203680A (zh) 2008-06-18
EP1906028A4 (en) 2011-06-01
KR20080009762A (ko) 2008-01-29

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