WO2016031339A1 - Ventilateur hélicoïde, distributeur de fluide, et matrice de moulage - Google Patents

Ventilateur hélicoïde, distributeur de fluide, et matrice de moulage Download PDF

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Publication number
WO2016031339A1
WO2016031339A1 PCT/JP2015/066333 JP2015066333W WO2016031339A1 WO 2016031339 A1 WO2016031339 A1 WO 2016031339A1 JP 2015066333 W JP2015066333 W JP 2015066333W WO 2016031339 A1 WO2016031339 A1 WO 2016031339A1
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WO
WIPO (PCT)
Prior art keywords
blade
outer peripheral
propeller fan
wing
edge portion
Prior art date
Application number
PCT/JP2015/066333
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English (en)
Japanese (ja)
Inventor
ゆい 公文
大塚　雅生
Original Assignee
シャープ株式会社
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 シャープ株式会社 filed Critical シャープ株式会社
Priority to JP2016545001A priority Critical patent/JP6173606B2/ja
Priority to CN201580011614.2A priority patent/CN106062379B/zh
Publication of WO2016031339A1 publication Critical patent/WO2016031339A1/fr

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    • 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
    • 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 relates to a propeller fan, a fluid feeder, and a molding die.
  • the fluid feeder sends out fluid using a propeller fan.
  • the fluid feeder include a hair dryer, a curl dryer, a pet dryer, an air conditioner outdoor unit, a garden blower, and a fan.
  • a propeller fan disclosed in Japanese Patent No. 3127850 has a cross-sectional shape in the vicinity of the outer peripheral edge portion (first region) of a blade, a negative pressure surface extending linearly, and a negative pressure surface from the leading edge of the negative pressure surface. Between a straight surface portion extending linearly toward the pressure surface side with a predetermined depression angle, and an arc surface portion smoothly extending with an arc that bulges the straight surface portion and the pressure surface toward the pressure surface side. It is characterized by a wedge shape.
  • the propeller fan disclosed in Japanese Patent Application Laid-Open No. 06-147193 is characterized in that it has a circular arc surface in which the corner on the pressure surface side of the outer peripheral edge of the blade is smoothly cut into an arc shape.
  • a blade tip vortex is generated in the vicinity of the outer peripheral edge of the blade provided in the propeller fan.
  • the blade tip vortex is generated so as to draw a vortex from the pressure surface side toward the suction surface side while winding the outer peripheral edge of the blade.
  • the shape of the tip vortex is easily affected by the Reynolds number.
  • the diameter of the tip vortex (vortex core) varies greatly depending on the Reynolds number.
  • the diameter of the blade tip vortex is relatively small with respect to the typical thickness of the blade when the Reynolds number is high, and relatively large with respect to the typical thickness of the blade when the Reynolds number is low.
  • the effect of the tip vortex on the flow around the blade surface is greater at low Reynolds numbers than at high Reynolds numbers.
  • Patent Document 1 Japanese Patent No. 3127850 (Patent Document 1) is high by smoothly flowing air from the outer peripheral edge of the blade toward the blade surface without generating a blade tip vortex in the vicinity of the outer peripheral edge of the blade. It states that the air blowing performance can be realized.
  • the influence of the viscosity of the fluid is increased, and the diameter of the blade tip vortex is also increased.
  • the blade tip vortex being formed at a halfway end in the vicinity of the outer peripheral edge of the blade, the blade tip vortex tends to adhere to the portion immediately downstream on the suction surface side of the outer peripheral edge of the blade.
  • the flow around the blade forms a state similar to the flow in the case of a blade having an irregular shape in which the outer peripheral edge is greatly rounded and raised toward the suction surface side. It will be.
  • Patent Document 1 Japanese Patent No. 3127850 (Patent Document 1)
  • Patent Document 1 Japanese Patent No. 3127850
  • the outer peripheral edge portion of the blade is not generated in the vicinity of the outer peripheral edge portion of the blade without causing a blade tip vortex. It is not easy for air to flow smoothly from the blade toward the blade surface. Rather, it is considered that it is difficult to realize high air blowing performance because the flow flowing into the blade surface from the outer peripheral edge of the blade is largely separated from the blade surface.
  • the present invention relates to a propeller fan capable of exhibiting high air blowing performance even in the case of a low Reynolds number, a fluid feeder including such a propeller fan, and a molding metal used for molding such a propeller fan.
  • the purpose is to provide a mold.
  • a propeller fan that receives rotational power and rotates around a rotation axis, comprising a boss portion and a plurality of blades extending outward in the rotational radial direction from the boss portion, the blade being the most in the rotation direction
  • a blade tip located at the tip, a leading edge extending from the blade tip to the boss, forming a leading edge of the blade in the rotational direction, and a rear side in the rotational direction from the front edge Provided at the rear edge portion extending from the boss portion toward the outer side in the rotational radius direction and forming the trailing edge of the blade in the rotational direction, and at the outer end portion in the rotational radius direction of the rear edge portion.
  • An outer peripheral edge that connects the outer peripheral rear end, the wing tip and the outer peripheral rear end, and forms an outer peripheral edge of the wing in the rotational radius direction. At least a portion of the area between the blade tip and the outer peripheral rear end When the cross-sectional shape of the wing is viewed, the portion of the blade surface that extends from the outer peripheral edge to the pressure surface side of the blade surface is a straight line that extends linearly as the distance from the outer peripheral edge increases. A portion that extends from the outer peripheral edge portion to the suction surface side of the blade surface of the blade, and bulges in an arc shape from the outer peripheral edge portion toward the suction surface side. An arcuate portion extending so as to approach the boss portion after being bent is formed.
  • a propeller fan that receives rotational power and rotates around a rotation axis, comprising a boss portion and a plurality of blades extending outward in the rotational radial direction from the boss portion, the blade being the most in the rotation direction
  • a blade tip located at the tip, a leading edge extending from the blade tip to the boss, forming a leading edge of the blade in the rotational direction, and a rear side in the rotational direction from the front edge Provided at the rear edge portion extending from the boss portion toward the outer side in the rotational radius direction and forming the trailing edge of the blade in the rotational direction, and at the outer end portion in the rotational radius direction of the rear edge portion.
  • An outer peripheral edge that connects the outer peripheral rear end, the wing tip and the outer peripheral rear end, and forms an outer peripheral edge of the wing in the rotational radius direction. At least a portion of the area between the blade tip and the outer peripheral rear end When the cross-sectional shape of the blade is viewed, the portion of the blade surface that extends from the outer peripheral edge portion to the pressure surface side of the blade surface of the blade has a linear extension as the distance from the outer peripheral edge portion increases.
  • a straight line portion is formed, and a portion of the blade surface extending from the outer peripheral edge portion to the suction surface side of the blade surface of the blade has the first edge toward the suction surface side from the outer peripheral edge portion.
  • a second linear portion extending linearly with a depression angle between the linear portion and the distal end portion in the extending direction of the second linear portion is curved in an arc shape and then approaches the boss portion And an arcuate portion extending in the direction.
  • At least a part of the region between the blade tip portion and the outer peripheral rear end portion of the outer peripheral edge portion is from the blade tip portion of the outer peripheral edge portion to the outer peripheral edge portion. It is an area located in the range up to the middle part in the rotation direction.
  • the front portion of the blade in the rotation direction is along a part or all of the front edge. And has a thick portion formed so that a part of the blade surface bulges, and the thick portion is 20% or less of the chord length of the wing from the leading edge portion.
  • the maximum blade thickness is formed within the range, and the line drawn when connecting the portions forming the maximum blade thickness of the thick part with one line is the maximum blade thickness.
  • the distance between the maximum blade thickness line and the leading edge in the direction along the chord length of the blade is D, the maximum blade thickness line extends from the inside to the outside in the rotational radius direction. It has a portion where the distance D gradually increases as it goes.
  • a portion extending from the trailing edge to the pressure surface side of the blade surface of the blade is separated from the trailing edge.
  • the other straight part extending linearly is formed as the wing surface of the wing extends from the trailing edge to the negative pressure surface.
  • Another arc-shaped portion is formed that extends so as to approach the boss portion after being curved so as to bulge in an arc shape toward the pressure surface side.
  • a portion extending from the trailing edge to the pressure surface side of the blade surface of the blade is separated from the trailing edge.
  • the other straight part extending linearly is formed as the wing surface of the wing extends from the trailing edge to the negative pressure surface. Curved in a circular arc continuously to the other straight line portion extending in a straight line with the other straight line portion toward the pressure surface side and the distal end portion in the extending direction of the other straight line portion. After that, another arc-shaped portion extending so as to approach the boss portion is formed.
  • the fluid feeder includes a flow path forming member through which a fluid flows, a drive motor, and the propeller fan that is driven by the drive motor and disposed in the flow path forming member.
  • the outer diameter of the propeller fan is defined as DA (m)
  • the peripheral speed of the outermost peripheral portion of the blade in the rotational radius direction of the propeller fan is defined as V (m / s)
  • the kinematic viscosity of the fluid The coefficient is defined as ⁇ (m 2 / s)
  • the tensile elastic modulus of the propeller fan is defined as E (MPa)
  • Reynolds number outer diameter DA ⁇ circumferential speed V / dynamic viscosity coefficient ⁇
  • the Reynolds number is less than 1.0 ⁇ 10 6 and the blade tip position variation coefficient is 1.0 ⁇ 10 6. Less than -2 .
  • Molding mold is used to mold the above propeller fan.
  • the propeller fan which can exhibit ventilation performance even in the case of a low Reynolds number, the fluid feeder provided with such a propeller fan, and the shaping
  • FIG. 3 is a cross-sectional view showing the fluid feeder in the first embodiment. It is sectional drawing which expands and shows the area
  • FIG. 3 is a side view showing the propeller fan in the first embodiment.
  • FIG. 3 is a perspective view showing a part (wings) of the propeller fan in the first embodiment.
  • FIG. 3 is a plan view showing the propeller fan in the first embodiment.
  • FIG. 6 is a cross-sectional view taken along the line VI-VI in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along line VII-VII in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along line VIII-VIII in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along the line VI-VI in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along line VII-VII in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along line VIII-VIII in FIG
  • FIG. 6 is a cross-sectional view taken along the line IX-IX in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along line XX in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along line XI-XI in FIG. 5.
  • FIG. 6 is a cross-sectional view taken along line XII-XII in FIG. 5. It is a top view which shows a mode when the propeller fan in Embodiment 1 is rotating. It is a side view which shows a mode when the propeller fan in Embodiment 1 is rotating.
  • FIG. 14 is a cross-sectional view taken along line XV-XV in FIG. 13. It is a figure which expands and shows the area
  • FIG. 5 is a cross-sectional view for explaining the action and effect of the propeller fan in the first embodiment. It is sectional drawing for demonstrating the effect
  • (A) is sectional drawing which shows the wing
  • (B) is sectional drawing which shows the blade
  • FIG. 10 is a perspective view showing a blade provided in a propeller fan in a second modification of the first embodiment.
  • 5 is a plan view showing a propeller fan in Comparative Example 1.
  • FIG. 22 is a cross-sectional view taken along the line XXII-XXII in FIG. 21.
  • FIG. 22 is a cross-sectional view taken along the line XXIII-XXIII in FIG. 21.
  • FIG. 22 is a cross-sectional view taken along line XXIV-XXIV in FIG. 21.
  • FIG. 22 is a cross-sectional view taken along line XXV-XXV in FIG. 21.
  • FIG. 22 is a cross-sectional view taken along the line XXVI-XXVI in FIG.
  • FIG. 22 is a cross-sectional view taken along the line XXVII-XXVII in FIG. 21.
  • FIG. 21 is a cross-sectional view taken along the line XXVII-XXVII in FIG. 21.
  • FIG. 22 is a cross-sectional view taken along the line XXVIII-XXVIII in FIG. It is a top view which shows a mode when the propeller fan in the comparative example 1 is rotating. It is a side view which shows a mode when the propeller fan in the comparative example 1 is rotating.
  • FIG. 30 is a cross-sectional view taken along the line XXXI-XXXI in FIG. 29. It is a figure which expands and shows the area
  • FIG. 1 is a cross-sectional view showing a blade of a propeller fan in Comparative Example 1.
  • FIG. 6 is a cross-sectional view showing a blade of a propeller fan in Comparative Example 2.
  • FIG. 10 is a cross-sectional view showing a blade of a propeller fan in Comparative Example 3.
  • FIG. It is a model figure which shows typically the behavior of the fluid around the wing
  • FIG. It is a model figure which shows typically the behavior of the fluid around the wing
  • FIG. 6 is a diagram showing the pressure flow characteristics (PQ) characteristics of the propeller fan in the example (the above-described first embodiment) and the above-described comparative examples 1 to 3.
  • FIG. 10 is a perspective view showing a propeller fan in a second embodiment.
  • FIG. 5 is a plan view showing a propeller fan in a second embodiment.
  • FIG. 6 is a plan view showing in detail a blade of a propeller fan in a second embodiment.
  • FIG. It is sectional drawing along the XLVII line in FIG. It is sectional drawing along the XLVIII line in FIG.
  • FIG. 46 is a cross-sectional view taken along line XLVIX in FIG. 45. It is sectional drawing along the L line in FIG. It is sectional drawing along the LI line in FIG.
  • FIG. 10 is another plan view showing the propeller fan in the second embodiment.
  • FIG. 53 is a diagram showing blade thicknesses of portions along the chord lengths LS1 to LS4 shown in FIG. (A) is sectional drawing which shows typically a mode when the propeller fan in Embodiment 2 is rotating.
  • FIG. 6 is a perspective view showing a propeller fan in a comparative example of Embodiment 2.
  • FIG. 6 is a plan view showing a propeller fan in a comparative example of Embodiment 2.
  • FIG. It is sectional drawing along the LVII line in FIG. It is sectional drawing along the LVIII line in FIG. It is sectional drawing along the LVIX line
  • FIG. 10 is another plan view showing a propeller fan in a comparative example of the second embodiment.
  • FIG. 63 is a diagram showing the blade thickness of portions along the chord lengths LT1 to LT4 shown in FIG. 62. It is sectional drawing which shows typically a mode when the propeller fan in the comparative example of Embodiment 2 is rotating.
  • FIG. 6 is a plan view showing a propeller fan in a third embodiment.
  • FIG. 6 is a plan view showing in detail a blade of a propeller fan in a third embodiment.
  • FIG. 10 is a plan view showing a propeller fan in a fourth embodiment.
  • FIG. 9 is a plan view showing in detail a blade of a propeller fan in a fourth embodiment.
  • FIG. 10 is a plan view showing a propeller fan in a fifth embodiment.
  • FIG. 10 is a plan view showing in detail a blade of a propeller fan in a fifth embodiment.
  • FIG. 20 is a plan view for explaining a propeller fan provided in the fluid feeder in the sixth embodiment.
  • FIG. 10 is a cross-sectional view showing a fluid feeder in a seventh embodiment.
  • FIG. 25 is another cross-sectional view showing the fluid feeder in the seventh embodiment.
  • FIG. 10 is a front view showing a propeller fan in a seventh embodiment.
  • FIG. 75 is a cross-sectional view taken along the line LXXV-LXXV in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXVI-LXXVI in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along the line LXXVII-LXXVII in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXVIII-LXXVIII in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXIX-LXXIX in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXX-LXXX in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXXI-LXXXI in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXII-LXXII in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXII-LXXII in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along the line LXXXIII-LXXXIII in FIG. 74.
  • FIG. 75 is a cross-sectional view taken along line LXXXIV-LXXXIV in FIG. 74.
  • FIG. 20 is a perspective view showing a fluid feeder in Embodiment 8.
  • FIG. 10 is a cross-sectional view showing a molding die in a ninth embodiment. It is a figure which shows the experimental condition and result regarding an experiment example.
  • FIG. 1 is a cross-sectional view showing a fluid feeder 100 according to the first embodiment.
  • the fluid feeder 100 is a hair dryer and includes a main body unit 10, a gripping unit 18, and an operation unit 19.
  • the main body 10 includes an outer case 11, an inner case 12 (flow path forming member), a drive motor 30, a propeller fan 50, a rectifying blade 40, and a heater 17. Both the outer case 11 and the inner case 12 have a cylindrical shape.
  • the outer case 11 has an inlet opening 13 and an outlet opening 14, and the inlet opening 13 communicates with the outlet opening 14.
  • the inner case 12 has a suction port 15 and a discharge port 16 through which fluid (air) flows.
  • the suction port 15 is located on the inlet opening 13 side, and the discharge port 16 is located on the outlet opening 14 side.
  • the drive motor 30, the propeller fan 50 and the rectifying blade 40 are disposed in the inner case 12.
  • a motor support 44 (see FIG. 2) is provided inside the rectifying blade 40.
  • the drive motor 30 is arranged such that its output shaft 31 (see FIG. 2) is substantially parallel to the longitudinal direction of the main body 10.
  • the propeller fan 50 is attached to the drive motor 30.
  • the propeller fan 50 is disposed closer to the suction port 15 than the drive motor 30.
  • Propeller fan 50 is arranged such that the rotation axis of propeller fan 50 (see rotation axis 80 in FIG. 2) is substantially parallel to the longitudinal direction of main body 10.
  • the propeller fan 50 receives the rotational power from the drive motor 30 and rotates around the rotation shaft 80, and the airflow flowing from the upstream inlet opening 13 and the suction opening 15 toward the downstream discharge opening 16 and the outlet opening 14. (Air flow) is generated.
  • FIG. 2 is an enlarged cross-sectional view showing a region surrounded by line II in FIG.
  • the cross-sectional view of FIG. 2 is illustrated such that the suction port 15 is located above the paper surface and the discharge port 16 is located below the paper surface.
  • the propeller fan 50 and the rectifying blade 40 are provided in the inner case 12.
  • the rectifying blade 40 is disposed on the downstream side of the propeller fan 50.
  • the rectifying blade 40 includes a plate-like portion 42.
  • the plate-like portion 42 has an upstream edge portion 43 on the upstream side.
  • the upstream edge 43 extends along a direction perpendicular to the rotation shaft 80 of the propeller fan 50.
  • FIG. 3 is a side view showing the propeller fan 50.
  • FIG. 4 is a perspective view showing a part of the propeller fan 50 (blade 70).
  • FIG. 5 is a plan view showing the propeller fan 50.
  • propeller fan 50 rotates around rotation shaft 80 in the direction of arrow AR1 by receiving rotational power from drive motor 30 (FIG. 2).
  • the propeller fan 50 includes a boss portion 60 and four blades 70, and is made of a synthetic resin such as AS (acrylonitrile-styrene), POM (polyoxymethylene), PP (polypropylene), and PAGF (glass reinforced polyamide). It is integrally manufactured as a molded product.
  • Propeller fan 50 has, for example, an outer diameter of ⁇ 54 mm and a height of 25 mm.
  • Boss portion 60 includes an outer surface 61 having a smooth surface shape.
  • the upstream end 62 of the outer surface 61 is formed at the most upstream (vertical) position of the outer surface 61.
  • the downstream end 63 of the outer surface 61 is a part formed at the most downstream position of the outer surface 61.
  • the wing 70 includes a wing tip portion 71, a front edge portion 72, a root portion 73, a rear edge portion 74, an outer peripheral rear end portion 75, and an outer peripheral edge portion 76.
  • the blade tip 71 is located at the most tip (front side) in the rotation direction of the propeller fan 50 (arrow AR1 direction).
  • the leading edge 72 extends from the blade tip 71 to the outer surface 61 of the boss 60 and forms the leading edge of the blade 70 in the rotational direction.
  • the front edge portion 72 extends in a substantially arc shape so as to advance toward the front side in the rotational direction as it goes from the outer surface 61 of the boss portion 60 to the outer side in the rotational radius direction (see FIG. 5).
  • the root portion 73 is formed between the wing 70 and the outer surface 61 of the boss portion 60 (boundary).
  • the rear edge portion 74 is provided behind the front edge portion 72 in the rotation direction (arrow AR1 direction), extends from the outer surface 61 of the boss portion 60 toward the outer side in the rotation radius direction, and The trailing edge of the blade 70 in the rotation direction (arrow AR1 direction) is formed.
  • the rear edge portion 74 extends so as to slightly advance toward the front side in the rotational direction as it goes from the outer surface 61 of the boss portion 60 toward the outer side in the rotational radius direction (see FIG. 5).
  • the outer peripheral rear end 75 is formed at the outermost end (outer end) of the rear edge 74 in the rotational radius direction.
  • the outer peripheral rear end portion 75 is a portion where the rear edge portion 74 and the outer peripheral edge portion 76 are connected, and is a portion where the radius of curvature is minimized between the rear edge portion 74 and the outer peripheral edge portion 76.
  • the outer peripheral edge portion 76 connects the blade tip portion 71 and the outer peripheral rear end portion 75 to form the outer peripheral edge of the blade 70 in the rotational radius direction.
  • the wing 70 as a whole has a sickle-pointed shape with the wing tip 71 as a tip.
  • the wing 70 has a shape in which the width in the direction along the rotation direction between the front edge portion 72 and the rear edge portion 74 is sharply reduced from the outer peripheral edge 76 side toward the inner side in the rotation radial direction.
  • the wing 70 has a shape in which the width in the direction along the rotation direction between the front edge portion 72 and the rear edge portion 74 increases steeply from the root portion 73 toward the outer side in the rotation radius direction.
  • the outer peripheral edge portion 76 extends in a substantially arc shape between the blade tip portion 71 and the outer peripheral rear end portion 75.
  • the blade tip 71, the leading edge 72, the root 73, the trailing edge 74, the outer peripheral rear end 75, and the outer peripheral edge 76 form the peripheral edge of the blade 70.
  • the blade surface of the blade 70 is formed in the entire region inside the region surrounded by the periphery.
  • the blade surface of the blade 70 has a shape in which the leading edge 72 is located on the upstream side in the direction of airflow and the trailing edge 74 is located on the downstream side in the direction of airflow.
  • a positive pressure surface 77 is formed on the surface of the blade surface of the blade 70 on the discharge port 16 (FIG. 2) side, and the surface of the suction port 15 (FIG. 2) of the blade surface of the blade 70.
  • a negative pressure surface 79 is formed.
  • FIGS. 6 to 12 (Detailed structure of the periphery of the wing 70) 6 to 12 are taken along lines VI-VI, VII-VII, VIII-VIII, IX-IX, XX, XI-XI, and XII-XII in FIG. 5, respectively. It is arrow sectional drawing.
  • the rotary shaft 80 is shown in FIGS. 6 to 12, but the relative positional relationship between the blade 70 and the rotary shaft 80 (between the blade 70 and the rotary shaft 80 is not shown). The distance) may differ from that shown in FIGS. 6 to 9 show the cross-sectional shape of the outer peripheral edge portion 76, FIG. 10 shows the cross-sectional shape of the rear edge portion 74, and FIGS. 11 and 12 show the cross-sectional shape of the front edge portion 72. .
  • This cross-sectional shape is a cross-sectional shape obtained when the blade 70 is viewed in cross section with a cut surface parallel to the rotating shaft 80.
  • a straight portion 76 ⁇ / b> L is formed in a portion of the blade surface of the blade 70 that extends from the outer peripheral edge portion 76 to the positive pressure surface 77 side.
  • the straight portion 76L extends linearly as the distance from the outer peripheral edge 76 increases.
  • the straight portion 76L has a shape extending in an inclined manner in a direction from the negative pressure surface 79 side to the positive pressure surface 77 side as it goes from the outer peripheral edge portion 76 to the side where the rotation shaft 80 is located.
  • the degree of inclination of the straight line portion 76L is the steepest in the case shown in FIG. 6, and becomes gentler in the order of FIGS.
  • an arc-shaped portion 76 ⁇ / b> R is formed in a portion of the blade surface of the blade 70 that extends from the outer peripheral edge portion 76 toward the negative pressure surface 79.
  • the arc-shaped portion 76R extends so as to approach the boss portion 60 (see FIGS. 4 and 5, etc.) after being curved so as to bulge out from the outer peripheral edge portion 76 toward the suction surface 79 side. .
  • the linear portion 76L and the arc-shaped portion 76R as described above are formed over the entire region between the blade tip portion 71 and the outer peripheral rear end portion 75 in the outer peripheral edge portion 76. (See FIG. 4).
  • a straight portion 74L is formed in a portion of the blade surface of the blade 70 that extends from the rear edge portion 74 to the pressure surface 77 side.
  • the straight portion 74L extends in a straight line as the distance from the rear edge portion 74 increases.
  • the straight line portion 74L has a shape extending in an inclined manner in a direction from the positive pressure surface 77 side to the negative pressure surface 79 side as it goes from the rear edge portion 74 to the side where the rotation shaft 80 is located.
  • an arc-shaped portion 74R (another arc-shaped portion) is formed in a portion of the blade surface of the blade 70 that extends from the trailing edge portion 74 to the suction surface 79 side.
  • the arcuate part 74R extends so as to approach the boss part 60 (see FIG. 4, FIG.
  • the surface shape of the trailing edge portion 74 located between the straight line portion 74L and the arc-shaped portion 74R exhibits an edge shape starting from the trailing edge portion 74.
  • the depression angle is, for example, 30 °.
  • the cross-sectional shape of the wing 70 in at least a part of the leading edge 72 between the wing tip 71 and the root 73 is viewed.
  • the portion 72R to be seen can be seen.
  • the portions 72L and 72R have shapes that extend from the leading edge 72 toward the positive pressure surface 77 and the negative pressure surface 79 so as to extend substantially uniformly in the thickness direction of the blade 70.
  • the leading edge 72 and the portions 72L and 72R also have an edge shape starting from the leading edge 72.
  • the wing 70 is configured as described above.
  • FIGS. 13 and 14 are a plan view and a side view, respectively, showing a state when the propeller fan 50 is rotating.
  • FIG. 15 is a cross-sectional view taken along line XV-XV in FIG.
  • FIG. 16 is an enlarged view of a region surrounded by the XVI line in FIG.
  • outer peripheral edge portion 76 between blade tip 71 and outer peripheral rear end 75.
  • a straight portion 76 ⁇ / b> L is formed in a portion extending from the outer peripheral edge 76 to the pressure surface 77 side in the blade surface of the blade 70.
  • An arc-shaped portion 76R is formed in a portion of the surface extending from the outer peripheral edge portion 76 to the negative pressure surface 79 side.
  • the linear portion 76L extends linearly as it moves away from the outer peripheral edge portion 76, and the arc-shaped portion 76R is curved so as to bulge out from the outer peripheral edge portion 76 toward the negative pressure surface 79. It extends so that it may approach the boss
  • the surface shape of the outer peripheral edge portion 76 located between the straight portion 76L and the arc-shaped portion 76R exhibits an edge shape starting from the outer peripheral edge portion 76.
  • a straight portion 76L is formed at a portion extending toward the pressure surface 77
  • an arc-shaped portion 76R is formed at a portion extending toward the suction surface 79.
  • a blade tip vortex is generated in the vicinity of the surface of the outer peripheral edge portion 76 (edge portion), and the generated blade tip vortex is caused to be generated in the vicinity of the surface of the arc-shaped portion 76R (outer peripheral edge by the action of viscosity. It can be fixed to the vicinity of the outer portion of the portion 76 (see FIGS. 15 and 16).
  • the flow around the blade 70 is assumed to be a virtual line LL1 (FIGS. 13 and 15). Will flow along the circumference of the wing (see arrow AR2 in FIG. 15). That is, the blade tip vortex fixed near the surface of the arc-shaped portion 76R (near the outer portion of the outer peripheral edge 76) can cooperate with the blade 70 and function as a part of the blade of the propeller fan 50. Become.
  • a linear portion 76L is formed in a portion extending from the outer peripheral edge portion 76 (edge portion) to the positive pressure surface 77 side and extending toward the negative pressure surface 79 side. Is formed with an arcuate portion 76R. Therefore, the shape of the virtual wing indicated by the line LL1 (FIGS. 13 and 15) has a streamline shape that smoothly extends from the front end portion to the rear end portion in the rotation direction. The flow that has flowed into the blade surface from the outer peripheral edge 76 of the blade 70 is hardly separated from the blade surface, and high air blowing performance can be realized.
  • the cord length of the virtual wing indicated by the line LL1 is longer than the actual cord length of the wing 70. Therefore, the blade 70 can exhibit the characteristics corresponding to the cord length longer than the actual cord length. In other words, it is possible to shorten the wing cord length necessary to obtain the desired performance. Further, the blade tip vortex fixed near the surface of the arc-shaped portion 76R (near the outer portion of the outer peripheral edge 76) behaves like a thick wing and generates lift, so that desired performance is obtained. It is also possible to reduce the necessary wing thickness. Considering the above comprehensively, according to the propeller fan 50 of the present embodiment, it is possible to obtain lift even when the cord length is shortened and the thickness is thin, and the weight is high while being lightweight. It becomes possible to exhibit performance and high efficiency.
  • the surface shape of the outer peripheral edge portion 76 located between the linear portion 76L and the arcuate portion 76R exhibits an edge shape starting from the outer peripheral edge portion 76.
  • the depression angle is preferably 45 ° or more and 90 ° or less. Among 45 ° to 90 °, the depression angle is more preferably a value close to 90 °.
  • the blade tip vortex generated at the edge portion of the depression angle can be dammed near the surface of the arc-shaped portion 76R, and the blade tip vortex is generated further outside the tip of the outer peripheral edge portion 76. It becomes possible to fix more firmly. Therefore, according to these additional configurations, higher effects can be obtained.
  • root portion 73 of rear edge portion 74 of rear edge portion 74 (see FIGS. 5 and 10) and rear periphery
  • a straight line extends from the trailing edge 74 to the pressure surface 77 of the blade surface of the blade 70.
  • a portion 74L is formed, and an arcuate portion 74R is formed in the portion of the blade surface of the blade 70 that extends from the trailing edge portion 74 to the suction surface 79 side.
  • the linear portion 74L extends linearly as it moves away from the rear edge portion 74, and the arc-shaped portion 74R is curved so as to bulge out from the rear edge portion 74 toward the suction surface 79. It extends so that it may approach the boss
  • the surface shape of the trailing edge portion 74 located between the straight portion 74L and the arcuate portion 74R exhibits an edge shape starting from the trailing edge portion 74.
  • the depression angle is preferably about 30 °.
  • the trailing edge portion 74 also has an edge shape similar to that of the outer peripheral edge portion 76, so that the wake vortex generated on the downstream side of the trailing edge portion 74 can function as if part of the blades of the propeller fan 50. .
  • lift can be obtained, and high performance and high efficiency can be exhibited while being lightweight.
  • the front edge 72 of the wing 70 has a thick portion as shown in FIGS. 11 and 12 (second embodiment).
  • a thick portion 78) may be formed.
  • the thick portion (details will be described later) that can be adopted in the first embodiment is a portion that is located below the dotted lines 72LS1 (FIG. 11) and 72LS2 (FIG. 12) in FIGS. It is formed in the vicinity of the leading edge 72 of the wing 70.
  • the thick part is formed so that a part of the blade surface bulges. The operation and effect of forming the thick portion will be described in detail in the second embodiment.
  • the shape in the vicinity of the front edge portion 72 of the wing 70 is represented as a portion positioned above the dotted lines 72LS1 and 72LS2 in FIGS. Can do.
  • the surface shape of the front edge portion 72 located between the dotted lines 72LS1 and 72LS2 and the portion 72R has an edge shape starting from the front edge portion 72.
  • FIG. 18 is a cross-sectional view showing a blade 70Z in a comparative example.
  • the wing 70Z is a comparative example with respect to the wing 70 shown in FIG. Unlike the wing 70 (FIG. 10), the trailing edge 74 of the wing 70Z does not have an edge shape.
  • the wake vortex generated on the downstream side of the trailing edge 74 can act as a resistance to the wind (arrow AR3) flowing around the blade 70Z. Therefore, in order to improve performance and efficiency, it is preferable to employ a configuration having an edge shape such as the blade 70 (FIG. 10).
  • FIG. 19A corresponds to FIG. 6 in Embodiment 1. It is assumed that the cross-sectional shape of the blade 70A in at least a partial region between the blade tip 71 (see FIG. 5) and the outer peripheral rear end 75 (see FIG. 5) in the outer peripheral edge 76 is seen.
  • This cross-sectional shape is a cross-sectional shape obtained when the blade 70 ⁇ / b> A is viewed in cross section with a cut surface parallel to the rotating shaft 80.
  • a straight portion 76L (first straight portion) is formed in a portion of the blade surface of the blade 70A that extends from the outer peripheral edge portion 76 to the pressure surface 77 side.
  • the straight portion 76L extends linearly as the distance from the outer peripheral edge 76 increases.
  • the straight portion 76L has a shape extending in an inclined manner in a direction from the negative pressure surface 79 side to the positive pressure surface 77 side as it goes from the outer peripheral edge portion 76 to the side where the rotation shaft 80 is located.
  • a straight portion 76J (second straight portion) and an arc-shaped portion 76R are formed in a portion of the blade surface of the blade 70A that extends from the outer peripheral edge portion 76 to the suction surface 79 side.
  • the straight line portion 76J extends linearly from the outer peripheral edge portion 76 toward the negative pressure surface 79 with a depression angle ⁇ between the straight line portion 76J and the straight line portion 76L.
  • the arc-shaped portion 76R smoothly continues to the tip portion 76E in the extending direction of the linear portion 76J, and extends so as to approach the boss portion 60 (see FIGS. 4 and 5) after being curved in an arc shape.
  • the direction of curvature of the arc-shaped portion 76R is a direction that is convex toward the suction surface 79 side.
  • the straight portions 76L and 76J and the arc-shaped portion 76R are formed over the entire region between the blade tip portion 71 and the outer peripheral rear end portion 75 in the outer peripheral edge portion 76 (similar to the case shown in FIG. 4). .
  • the surface shape of the outer peripheral edge portion 76 located between the linear portion 76L and the linear portion 76J exhibits an edge shape starting from the outer peripheral edge portion 76.
  • a straight portion 76L is formed at a portion extending toward the positive pressure surface 77
  • a straight portion 76J is formed at a portion extending toward the negative pressure surface 79.
  • a blade tip vortex is generated in the vicinity of the surface of the outer peripheral edge portion 76 (edge portion), and the generated blade tip vortex is converted into the vicinity of the surface of the straight portion 76J (outer peripheral edge portion) by the action of viscosity. It is possible to fix it to the vicinity of the outer portion of 76.
  • the blade tip vortex fixed near the surface of the straight portion 76J can cooperate with the blade 70A and function as a part of the blade of the propeller fan.
  • the virtual wing shape has a streamline shape that smoothly extends from the front end portion to the rear end portion in the rotation direction. The flow that has flowed into the blade surface from the outer peripheral edge of the blade 70A is hardly separated from the blade surface, and high air blowing performance can be realized. Even when the cord length is shortened and the thickness is reduced, lift can be obtained, and high performance and high efficiency can be exhibited while being lightweight.
  • the depression angle ⁇ is preferably 45 ° or more and 90 ° or less. Among 45 ° to 90 °, the depression angle is more preferably a value close to 90 °.
  • the depression angle ⁇ is set to about 90 °, the blade tip vortex generated at the edge portion of the depression angle can be dammed near the surface of the straight portion 76J, and the blade tip vortex is generated further outside the tip of the outer peripheral edge portion 76. It becomes possible to fix more firmly. Therefore, according to these additional configurations, higher effects can be obtained.
  • the edge shape portion formed in the outer peripheral edge portion 76 (FIG. 19A) is rounded within a range where the depression angle ⁇ can be formed or within a range where the depression angle ⁇ can be formed substantially. Thus, substantially the same operations and effects as those of the first embodiment are obtained.
  • FIG. 19B corresponds to FIG. 10 in Embodiment 1.
  • This cross-sectional shape is a cross-sectional shape obtained when the blade 70 ⁇ / b> A ⁇ b> 1 is viewed in cross section with a cut surface parallel to the rotation shaft 80.
  • a straight portion 74L (another straight portion) is formed in the portion of the blade surface of the blade 70A1 that extends from the rear edge portion 74 to the pressure surface 77 side.
  • the straight line portion 74L extends linearly as the distance from the rear edge portion 74 increases.
  • the straight line portion 74L has a shape extending in an inclined manner in a direction from the positive pressure surface 77 side to the negative pressure surface 79 side as it goes from the rear edge portion 74 to the side where the rotation shaft 80 is located.
  • a straight portion 74J (another straight portion) and an arcuate portion 74R are formed in a portion extending from the trailing edge portion 74 to the suction surface 79 side of the blade surface of the blade 70A1.
  • the straight line portion 74J extends linearly with a depression angle ⁇ between the straight edge portion 74J and the straight line portion 74L from the trailing edge portion 74 toward the suction surface 79 side.
  • the arcuate portion 74R smoothly continues to the tip end portion 74E in the extending direction of the linear portion 74J, and extends so as to approach the boss portion 60 (see FIGS. 4 and 5, etc.) after being curved in an arc shape.
  • the direction of curvature of the arcuate portion 74R is a direction that is convex toward the suction surface 79 side.
  • the straight portions 74L and 74J and the arc-shaped portion 74R are formed over the entire region between the root portion 73 and the outer peripheral rear end portion 75 of the rear edge portion 74 (similar to the case shown in FIG. 4).
  • the surface shape of the rear edge portion 74 located between the straight portion 74L and the straight portion 74J exhibits an edge shape starting from the rear edge portion 74.
  • the trailing edge portion 74 also has an edge shape similar to that of the outer peripheral edge portion 76, so that the wake vortex generated on the downstream side of the trailing edge portion 74 can function as a part of the blades of the propeller fan. Even when the cord length is shortened and the thickness is reduced, lift can be obtained, and high performance and high efficiency can be exhibited while being lightweight.
  • the edge shape portion formed on the rear edge portion 74 (FIG. 19B) is rounded within a range where the depression angle ⁇ can be formed or within a range where the depression angle ⁇ can be formed substantially.
  • the propeller fan having the blades 70B will be described.
  • the straight portion 76L and the arc-shaped portion 76R in the first embodiment are formed over a partial region between the wing tip portion 71 and the outer peripheral rear end portion 75 in the outer peripheral edge portion 76.
  • the partial area referred to here is an area located in a range from the blade tip 71 of the outer peripheral edge 76 to the middle portion 76M in the rotation direction of the outer peripheral edge 76.
  • the region RR shown in FIG. 20 does not have a configuration like the linear portion 76L and the arc-shaped portion 76R in the first embodiment.
  • propeller fan 50Z1 in the comparative example 1 will be described with reference to FIGS. 21 to 32 correspond to FIGS. 5 to 16 in the first embodiment described above, respectively.
  • Propeller fan 50Z1 includes boss portion 60Z1 and four blades 70Z1.
  • 22 to 28 are taken along lines XXII-XXII, XXIII-XXIII, XXIV-XXIV, XXV-XXV, XXVI-XXVI, XXVII-XXVII, and XXVIII-XXVIII in FIG. 21, respectively.
  • It is arrow sectional drawing. 22 to 25 show the cross-sectional shape of the outer peripheral edge portion 76
  • FIG. 26 shows the cross-sectional shape of the rear edge portion 74
  • FIGS. 27 and 28 show the cross-sectional shape of the front edge portion 72.
  • the wing 70Z1 has a rectangular cross-sectional shape obtained by cutting a flat plate-like member.
  • a portion 76V extending from the outer peripheral edge 76 of the blade surface of the blade 70Z1 to the pressure surface 77 side, and a negative portion from the outer peripheral edge 76 of the blade surface of the blade 70Z1.
  • the portions 76W and 76Y extending toward the pressure surface 79 have shapes different from those in the first embodiment. 26 to 28, the cross-sectional shape in the vicinity of the trailing edge 74 of the blade surface of the blade 70Z1 and the sectional shape in the vicinity of the leading edge 72 of the blade 70Z1 are also the same as those in the first embodiment. It has a different shape.
  • FIG. 29 and FIG. 30 are a plan view and a side view, respectively, showing a state when the propeller fan 50Z1 is rotating.
  • FIG. 31 is a cross-sectional view taken along the line XXXI-XXXI in FIG.
  • FIG. 32 is an enlarged view of a region surrounded by the line XXXII in FIG.
  • propeller fan 50Z1 of comparative example 1 has a rectangular cross-sectional shape obtained by cutting a flat plate member. According to such a surface shape, when the blade tip vortex is fixed near the surface of the outer peripheral edge portion 76, the flow around the blade 70Z1 is as if the outer peripheral edge portion 76 is greatly rounded and raised toward the suction surface 79 side. A state similar to the flow in the case of a wing having such an irregular shape is formed (see line LL2 in FIG. 31). Since the flow that has flowed into the blade surface from the outer peripheral edge 76 of the blade 70Z1 is largely separated from the blade surface (see arrow AR4 in FIG. 31), it is difficult to achieve high air blowing performance.
  • FIG. 33 is a cross-sectional view showing a state when the propeller fan having the blades 70Z2 in the comparative example 2 is rotating.
  • FIG. 34 is an enlarged view showing a region surrounded by the line XXXIV in FIG. A portion 76V of the blade surface of the blade 70Z2 extending from the outer peripheral edge 76 to the pressure surface 77 side, and a portion 76W of the blade surface of the blade 70Z2 extending from the outer peripheral edge 76 to the negative pressure surface 79 side.
  • a portion in the vicinity of the outer peripheral edge 76 of the blade 70Z2 has a round arc-shaped cross-sectional shape.
  • the wing 70Z2 is suitable for use in a high Reynolds number region such as an aircraft engine or a gas turbine, but is not very suitable for use in a low Reynolds number region such as a fan or a fan for an air conditioner outdoor unit. For this reason, the flow that has flowed into the blade surface from the outer peripheral edge 76 of the blade 70Z2 is largely separated from the blade surface (see arrow AR4 in FIG. 33), so it is difficult to achieve high air blowing performance.
  • FIG. 35 is a cross-sectional view showing a state when the propeller fan having the blades 70Z3 in the comparative example 3 is rotating.
  • FIG. 36 is an enlarged view of a region surrounded by the XXXVI line in FIG. Of the blade surface of the blade 70Z3, the portion 76V extending from the outer peripheral edge 76 to the pressure surface 77 side, and of the blade surface of the blade 70Z3, the portion 76W extending from the outer peripheral edge portion 76 to the negative pressure surface 79 side. Has a shape different from that of the first embodiment.
  • the vicinity of the outer peripheral edge 76 of the blade 70Z3 has a cross-sectional shape similar to the configuration described in Japanese Patent No. 3127850 (Patent Document 1) described at the beginning.
  • Wing 70Z3 is also not well suited for use in the low Reynolds number region. Therefore, since the flow that has flowed into the blade surface from the outer peripheral edge 76 of the blade 70Z3 is largely separated from the blade surface (see arrow AR4 in FIG. 35), it is difficult to achieve high air blowing performance.
  • FIG. 37 is a cross-sectional view showing the blade 70 of the propeller fan in the example (the first embodiment described above).
  • 38 to 40 are sectional views showing the propeller fan blades 70Z1 (FIGS. 21 to 32), 70Z2 (FIGS. 33 and 34), and 70Z3 (FIGS. 35 and 36) in Comparative Examples 1 to 3, respectively. is there.
  • the wings 70, 70Z1, 70Z2, and 70Z3 differ only in the shape of the outer peripheral edge portion 76.
  • FIG. 41 is a model diagram schematically showing the behavior of the fluid around the blades in the example (the above-described first embodiment) and the comparative example 1.
  • FIG. 42 is a model diagram schematically showing the behavior of fluid around the blades in Comparative Examples 2 and 3.
  • FIG. 41 and 42 show the behavior of the fluid around the blades for each load size (four types) acting on the blades of the propeller fan.
  • the reference load is a vicinity of a so-called design point (a load assumed at the time of design (degree of pressure loss)).
  • the performances A to D shown in the figure are evaluated in the order of A, B, C, and D.
  • FIG. 43 is a diagram showing the pressure flow characteristics (PQ) characteristics of the propeller fan in the example (the above-described first embodiment) and the above-described comparative examples 1 to 3.
  • PQ pressure flow characteristics
  • Comparative Example 3 is intended to improve performance at the reference load (design point). In the vicinity of the reference load, the effect of the blade tip vortex can be suppressed, so performance can be demonstrated. However, if a load larger than the reference load acts on the blade surface, the flow is greatly separated from the blade surface, and the embodiment (practical example) The effect as in the case of mode 1) cannot be obtained.
  • FIG. 44 and 45 are a perspective view and a plan view showing the propeller fan 50F, respectively.
  • Propeller fan 50F includes a boss portion 60F and a blade 70F.
  • FIG. 46 is a plan view showing the wing 70F in detail. 47 to 51 are cross-sectional views taken along line XLVII, XLVIII, XLIX, L, and LI in FIG. 45, respectively.
  • FIG. 52 is another plan view showing the propeller fan 50F
  • FIG. 53 is a view showing the blade thickness of portions along the chord lengths LS1 to LS4 shown in FIG.
  • the blade 70F of the propeller fan 50F has a rotation direction (in the direction of the arrow AR1) of the blades 70F when the blade thickness in the direction parallel to the rotation shaft 80 is referred to as the blade thickness.
  • the blade thickness referred to here is the distance between the surface on the pressure surface 77 side and the surface on the suction surface 79 side of the blade.
  • the thick portion 78 formed so that a part of the blade surface bulges preferably has a shape bulging to the pressure surface side, and bulges to both the pressure surface side and the suction surface side. You may have.
  • the thick portion 78 has a shape in which the maximum blade thickness is formed within a range of 20% or less of the chord length of the blade 70 ⁇ / b> F from the leading edge portion 72.
  • the maximum blade thickness line 78M is a line drawn when connecting the portions forming the maximum blade thickness with one line, and the maximum blade thickness line 78M and the leading edge in the direction along the chord length of the blade 70F. Assuming that the distance to 72 is D, the maximum blade thickness line 78M has a portion where the distance D gradually increases from the inside to the outside in the rotational radius direction.
  • the chord length means the length of a line segment connecting the leading edge 72 and the trailing edge 74 of the wing shape.
  • the thick portion 78 gradually increases in thickness as it moves away from the leading edge portion 72, and has a shape in which the blade thickness is maximized at the position of the maximum blade thickness line 78M.
  • the maximum blade thickness line 78M is formed at a position of about 5% of the chord length.
  • the distance D increases from the inside in the radial direction to around 30% (D1 ⁇ D2 ⁇ D3), and then gradually decreases. Yes.
  • the thick portion 78 has a shape that swells toward the pressure side.
  • the thick wall portion 78 is not formed, and a part of the blade surface does not bulge.
  • FIG. 54A is a cross-sectional view schematically showing a state when the propeller fan 50F is rotating.
  • the blade 70F has a thick portion 78, and has a thin tip, and the blade tip vortex generated from the blade tip 71 is small. Therefore, the energy of the vortex becomes strong, and wind with high straightness reaches far.
  • a strong blade tip vortex is generated from the blade tip toward the suction surface from the pressure surface of the blade 70F, and the energy of the vortex becomes strong. Reach far.
  • V ⁇ a rotational component
  • ⁇ P ⁇ ( ⁇ u) ⁇ 2/2 from the Bernoulli's theorem
  • ⁇ u ⁇ ( ⁇ u) ⁇ 2/2 from the Bernoulli's theorem
  • the maximum blade thickness position may be provided up to 20% of the chord length, and the blowing performance of the fan and the blade tip generated at the blade tip. If importance is placed on the balance with the blowing of wind up to the scalp by strengthening the vortex, it is desirable to provide up to 15%. When it is desired to specialize the arrival of the wind up to the scalp by the tip vortex generated at the tip, it is desirable to provide up to 10%, and a remarkable effect can be obtained.
  • the width of the maximum thickness position can be gradually increased from the vicinity of the root portion 73. According to this configuration, the circulation can be strengthened near the radial center of the blade, which should be strengthened, and the increase of the drag near the root of the blade can be prevented. Can be strengthened more appropriately.
  • the circulation of the entire region in the span direction of the blade circulation is reduced. Since the sizes are different, the balance of the entire blade is lost, and the tip vortex generated from the tip is weakened. Since the chord length is short at the root portion, if the width of the thick portion 78 (length in the chord length direction) is too large, the drag force may increase and the performance may deteriorate. Further, the circulation flow is strong on the blade tip 71 side (outside of the blade), and if the circulation flow in this part is strengthened, the balance of the circulation flow in the entire blade region is lost.
  • the wing 70F has a shape that is advantageous for the generation of lift, and can achieve air blowing with high straightness and strong wind pressure, and further receives a large centrifugal force due to high-speed rotation. Even in such a case, since the strength of the front root portion 73F is improved, the risk of breakage or the like during ultra high-speed rotation can be reduced. Since the tip of the blade deflected at the time of rotation rides on the circumference, the fan can be used most efficiently in a range where it does not interfere with the casing even at the time of rotation.
  • the action and effect obtained from the thick part as described above is the action obtained from the configuration of Embodiment 1, that is, the blade tip vortex is changed to the outer periphery. It is possible to cooperate with the effect that the portion 76 is fixed in the vicinity of the outer portion (the effect that the blade vortex behaves like a thick wing and generates lift).
  • the blade tip vortex and the circulation generated on the blade surface have a great influence on each other.
  • the tip vortex is likely to be formed.
  • a region LSR indicated by a two-dot chain line is a region approximately inside in the radial direction of the blade and extends from the blade tip 71 to the trailing edge 74 and the boss.
  • the blade tip vortex of the outer peripheral edge 76 can be strengthened to maintain a stable airfoil, and the performance as a propeller fan can be improved by, for example, about 30%.
  • the structure of the thick portion is also adopted in the propeller fan of the first embodiment.
  • FIGS. 55 and 56 are a perspective view and a plan view showing propeller fan 50G in the comparative example of the second embodiment, respectively.
  • Propeller fan 50G includes boss portion 60G and wing 70G.
  • 57 to 61 are sectional views taken along lines LVII, LVIII, LIX, LX, and LXI in FIG. 56, respectively.
  • FIG. 62 is another plan view showing the propeller fan 50G
  • FIG. 63 is a view showing the blade thickness of the portion along the chord lengths LT1 to LT4 shown in FIG.
  • Propeller fan 50G does not have a portion corresponding to thick portion 78 in the second embodiment, and has a shape in which the maximum blade thickness is formed in the vicinity of 30% of the chord length of blade 70G from leading edge portion 72. (See FIG. 63).
  • FIG. 64 is a cross-sectional view schematically showing a state when the propeller fan 50G in the comparative example of the second embodiment is rotating.
  • the circulation (circulation flow) efficiently merges with the flow that is wound from the pressure surface to the suction surface at the blade tip, and is less likely to become a blade tip vortex away from the blade tip.
  • the thick portion 78 is not formed, a circulating flow is generated such that the flow on the blade suction surface is accelerated ( ⁇ u) by the shape and angle of attack of the blade. As a result, a pressure difference is generated between the upper and lower blades, and lift is generated.
  • the mainstream velocity U is the same, but the presence of the thick portion 78 affects the flow in the vicinity of the blade surface.
  • the amount of air flowing on the suction surface side of the blade 70F is increased, and the flow on the suction surface side of the blade 70F is further accelerated ( ⁇ u ′> in FIG. 54A). ⁇ u in FIG. 64.
  • the amount of air flowing on the pressure surface side of the blade 70F is reduced, and the flow on the pressure surface side of the blade 70F is further decelerated. Therefore, in the blade 70F of the second embodiment, the circulation around the blade 70F is strengthened, and the vortex generated at the blade tip is further strengthened. Since the energy of the vortex becomes strong, it is possible to realize air blowing having high straightness and strong wind pressure.
  • FIGS. 65 and 66 propeller fan 50H in the third embodiment will be described.
  • 65 is a plan view showing the propeller fan 50H
  • FIG. 66 is a plan view showing the blades 70H of the propeller fan 50H in detail.
  • Propeller fan 50H includes a boss portion 60H and four blades 70H.
  • Propeller fan 50H has a diameter of 39 mm and a height of 15 mm.
  • the distance D (similar to D1 ⁇ D2 ⁇ D3 shown in FIG. 41) increases to about 40% of the leading edge portion 72, as in the second embodiment. After that, it has a shape that gradually decreases.
  • FIG. 67 is a plan view showing the propeller fan 50H1
  • FIG. 68 is a plan view showing the blade 70H1 of the propeller fan 50H1 in detail.
  • Propeller fan 50H1 includes a boss 60H1 and three blades 70H1.
  • the distance D gradually increases to about 30% of the front edge portion 72 (D1 ⁇ D2 ⁇ D3), and outside the front edge portion to near 100%. 72 to 20% or less of the chord length.
  • FIG. 69 is a plan view showing the propeller fan 50H2
  • FIG. 70 is a plan view showing the blades 70H2 of the propeller fan 50H2 in detail.
  • Propeller fan 50H2 includes boss portion 60H2 and three blades 70H2.
  • the distance D gradually increases to about 30% of the leading edge portion 72 (D1 ⁇ D2 ⁇ D3), and the distance D increases to the vicinity of 100% outside it. It has a constant shape.
  • FIG. 71 is a plan view for explaining the propeller fan provided in the fluid feeder in the sixth embodiment.
  • the length of the line segment connecting the rotation shaft 80 and the blade tip 71 is R1
  • the boss 60 A portion where the front edge portion 72 intersects is a front root portion 73F
  • a length of a line segment connecting the rotation shaft 80 and the front root portion 73F is R2
  • the rotation shaft 80 and a thick portion 78 (not shown) It is preferable that the relationship of 0.4 ⁇ (R3-R2) / (R1-R2) is satisfied, where R3 is the length of the line segment connecting the outermost portion ZT in the rotation radius direction .
  • the point CQ that is bent (curved) from the leading edge portion 72 toward the blade tip portion 71 is in the vicinity of approximately 0.4 (40%) of the length of the leading edge portion 72, the blowing efficiency becomes high. Therefore, by providing the thick portion 78 at least in the vicinity of the inflection, the effect of enhancing the circulation and strengthening the blade tip vortex can be further exhibited.
  • the fluid feeder 200 is an air conditioner outdoor unit, and includes a housing 21, a heat exchanger 22, a motor angle 23, a drive motor 30, and a propeller fan 50K.
  • the housing 21 can function as a flow path forming member through which a fluid flows.
  • the propeller fan 50K is disposed in the housing 21.
  • Propeller fan 50K has, for example, an outer diameter of ⁇ 466 mm and a height of 163 mm.
  • a bell mouth (not shown) is also arranged in the housing 21.
  • the bell mouth is a plate-like body provided with an arc-shaped orifice, and is arranged with a predetermined gap with respect to the outer diameter of the propeller fan 50K.
  • the bell mouth and the propeller fan are arranged on the same axis.
  • FIG. 74 is a front view showing the propeller fan 50K.
  • the propeller fan 50K includes a boss portion 60K and two blades 70K.
  • 75 to 84 show the LXXV-LXXV line, the LXXVI-LXXVI line, the LXXVII-LXXVII line, the LXXVIII-LXXVIII line, the LXXIX-LXXIX line, the LXXX-LXXX line, the LXXXI-LXXI line in FIG. 74, respectively.
  • FIG. 4 is a cross-sectional view taken along the line LXXXII, LXXXIII-LXXXIII, and LXXXIV-LXXXIV.
  • FIGS. 75 to 78 show the cross-sectional shape of the outer peripheral edge portion 76
  • FIGS. 79 to 81 show the cross-sectional shape of the rear edge portion 74
  • FIGS. 82 to 84 show the cross-sectional shape of the front edge portion 72. Show.
  • This cross-sectional shape is a cross-sectional shape obtained when the blade 70 ⁇ / b> K is viewed in cross section with a cut surface parallel to the rotation shaft 80.
  • a straight portion 76L is formed in the portion of the blade surface of the blade 70K that extends from the outer peripheral edge portion 76 to the positive pressure surface 77 side, as in the first embodiment.
  • the straight portion 76L extends linearly as the distance from the outer peripheral edge 76 increases.
  • the straight portion 76L has a shape extending in an inclined manner in a direction from the negative pressure surface 79 side to the positive pressure surface 77 side as it goes from the outer peripheral edge portion 76 to the side where the rotation shaft 80 is located.
  • the degree of inclination of the straight line portion 76L is the steepest in the case shown in FIG. 75, and becomes gradual in the order of FIG. 76 to FIG.
  • an arc-shaped portion 76R is formed in a portion of the blade surface of the blade 70K that extends from the outer peripheral edge portion 76 to the suction surface 79 side.
  • the arc-shaped portion 76R extends so as to approach the boss portion 60K (see FIG. 74) after being curved in an arc shape from the outer peripheral edge portion 76 toward the suction surface 79 side.
  • the surface shape of the outer peripheral edge portion 76 located between the straight line portion 76L and the arc-shaped portion 76R exhibits an edge shape starting from the outer peripheral edge portion 76.
  • the depression angle is preferably 45 ° or more and 90 ° or less.
  • the depression angle is more preferably a value close to 90 °.
  • the depression angle is 70 °.
  • a straight portion 74L is formed in a portion of the blade surface of the blade 70K that extends from the rear edge portion 74 to the positive pressure surface 77 side.
  • the straight portion 74L extends in a straight line as the distance from the rear edge portion 74 increases.
  • the straight line portion 74L has a shape extending in an inclined manner in a direction from the positive pressure surface 77 side to the negative pressure surface 79 side as it goes from the rear edge portion 74 to the side where the rotation shaft 80 is located.
  • an arc-shaped portion 74R (another arc-shaped portion) is formed in a portion of the blade surface of the blade 70K that extends from the trailing edge portion 74 to the suction surface 79 side.
  • the arc-shaped portion 74R extends so as to approach the boss portion 60K (see FIG. 74) after being curved in an arc shape from the rear edge portion 74 toward the suction surface 79 side.
  • the cross-sectional shape of the blade 70K in at least a partial region of the leading edge 72 between the blade tip 71 and the root 73 is seen.
  • the portion 72R to be seen can be seen.
  • the portions 72L and 72R have shapes that extend from the leading edge 72 toward the positive pressure surface 77 and the negative pressure surface 79 so as to extend substantially uniformly in the thickness direction of the blade 70K.
  • the wing 70K is configured as described above.
  • the front edge portion 72 has a thick portion as shown in FIGS. 82 to 84 (thick portion in the second embodiment). 78) may be formed.
  • the thick portion that can be employed in the seventh embodiment is a portion that is located below the dotted lines 72LS1, 72LS2, and 72LS3 in FIGS. 82 to 84, and is formed in the vicinity of the leading edge portion 72 of the blade 70K.
  • the shape in the vicinity of the front edge portion 72 of the wing 70 is represented as a portion located in the upper part of the drawing with respect to the dotted lines 72LS1, 72LS2, and 72LS3 in FIGS. It will be.
  • the surface shape of the front edge portion 72 located between the dotted lines 72LS1, 72LS2, 72LS3 and the portion 72R has an edge shape starting from the front edge portion 72.
  • FIG. 85 is a perspective view showing a fluid feeder 300 in the eighth embodiment.
  • the fluid feeder 300 is a horticultural blower and includes a housing 28, a cylinder 29, a drive motor 30, and a propeller fan 50.
  • the housing 28 can function as a flow path forming member through which a fluid flows.
  • Propeller fan 50 can have the same configuration as that described in the first embodiment, and is arranged in housing 28.
  • the propeller fan 50 has a diameter of 110 mm, a height of 40 mm, and four blades.
  • FIG. 86 is a cross-sectional view showing a molding die.
  • a molding die 400 has a movable side die 401 and a fixed side die 402.
  • the movable side mold 401 and the fixed side mold 402 define a cavity having substantially the same shape as the propeller fan in each of the above-described embodiments and into which a fluid resin is injected.
  • the propeller fan in each of the above-described embodiments can be manufactured by resin molding.
  • FIG. 87 is a diagram showing experiments conducted on the physical properties of materials for producing propeller fans and the results thereof.
  • the experiment includes Experimental Examples 1 to 5.
  • Experimental Examples 1 and 2 relate to a dryer (see FIG. 1), and only the materials (tensile elastic modulus) used for manufacturing the propeller fan are different from each other.
  • Experimental Example 1 is PP and Experimental Example 2 is POM.
  • Experimental Examples 3 and 4 relate to an air conditioner outdoor unit (see FIGS. 72 and 73), and only the materials (tensile elastic modulus) used to manufacture the propeller fan are different from each other.
  • Experimental Example 3 is ASGF20
  • Experimental Example 4 is ASCF20.
  • Experimental Example 5 relates to a garden blower (see FIG. 85). The material of the fan in Experimental Example 5 is PA6-GF30.
  • the fan outer diameter in the figure is a value obtained by doubling the distance between the rotating shaft 80 and the outermost peripheral portion of the blade in the direction of the rotating radius.
  • the peripheral speed is calculated from the rotational speed, and is the peripheral speed of the outermost peripheral portion of the blade in the rotational radius direction.
  • the kinematic viscosity coefficient is a value determined by air in a room temperature (20 ° C.) environment.
  • the outer diameter of the propeller fan is defined as DA (m)
  • the peripheral speed of the outermost peripheral portion of the blade in the rotational radius direction of the propeller fan is defined as V (m / s)
  • the kinematic viscosity coefficient of the fluid is represented by ⁇ (m 2 / S)
  • the tensile modulus of the propeller fan is defined as E (MPa).
  • the Reynolds number is a value defined by the formula of (outer diameter DA ⁇ circumferential speed V / kinematic viscosity coefficient ⁇ )
  • the blade tip position variation coefficient is (outer diameter DA ⁇ peripheral speed V / tensile elastic modulus E).
  • the values of Reynolds numbers in Experimental Examples 1 to 5 are all less than 1.0 ⁇ 10 6 and are included in the low Reynolds region. Under these low Reynolds region conditions, the tip position variation coefficients of Experimental Examples 1 to 5 are all less than 1.0 ⁇ 10 ⁇ 2 .
  • the performances A to C shown in the figure are evaluated in the order of A, B, and C.
  • the tip position variation coefficient may be less than 1.0 ⁇ 10 ⁇ 3 .

Landscapes

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

Abstract

　Cette invention concerne un ventilateur hélicoïde, présentant, du point de vue de la forme de la section transversale d'une aile (70), dans au moins une zone entre une extrémité d'embout d'aile et une extrémité périphérique arrière externe dans un bord périphérique externe (76), une partie linéaire (76L) s'étendant en ligne droite à l'écart du bord périphérique externe formée dans une partie de la surface d'aile de l'aile qui s'étend depuis le bord périphérique externe (76) vers une surface de pression positive (77), et une partie arquée (76R), qui s'étend de manière à s'approcher d'une partie de bossage après avoir formé une courbe de manière se renfler en forme d'arc à partir du bord périphérique externe jusqu'à une surface de pression négative (79), formée dans une partie de la surface d'aile de l'aile qui s'étend à partir du bord périphérique externe jusqu'à la surface de pression négative. Le ventilateur hélicoïde ainsi obtenu peut présenter une bonne performance même en cas de faibles valeurs de Reynolds.
PCT/JP2015/066333 2014-08-29 2015-06-05 Ventilateur hélicoïde, distributeur de fluide, et matrice de moulage WO2016031339A1 (fr)

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JP2016545001A JP6173606B2 (ja) 2014-08-29 2015-06-05 プロペラファン、流体送り装置、および成形用金型
CN201580011614.2A CN106062379B (zh) 2014-08-29 2015-06-05 螺旋桨式风扇、流体输送装置以及成型用模具

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JP2014-175797 2014-08-29

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JP7165433B2 (ja) * 2021-03-17 2022-11-04 シロカ株式会社 プロペラファン、扇風機、およびサーキュレータ

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JPH06307396A (ja) * 1993-04-23 1994-11-01 Daikin Ind Ltd 軸流羽根車
JP4140236B2 (ja) * 2000-12-28 2008-08-27 ダイキン工業株式会社 送風装置および空気調和機用室外機
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CN201574972U (zh) * 2009-07-14 2010-09-08 广东顺威精密塑料股份有限公司 轴流风轮
CN102828996B (zh) * 2011-06-14 2015-12-16 珠海格力电器股份有限公司 一种轴流风扇
CN103122872B (zh) * 2011-11-21 2016-02-10 珠海格力电器股份有限公司 轴流风扇
JP5629720B2 (ja) * 2012-04-10 2014-11-26 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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JPH06307396A (ja) * 1993-04-23 1994-11-01 Daikin Ind Ltd 軸流羽根車
JP4140236B2 (ja) * 2000-12-28 2008-08-27 ダイキン工業株式会社 送風装置および空気調和機用室外機
US20110094460A1 (en) * 2008-02-21 2011-04-28 Borgwarner Inc. Partial ring cooling fan

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WO2018064854A1 (fr) * 2016-10-07 2018-04-12 王保华 Structure de turbine

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JP6173606B2 (ja) 2017-08-02

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