JP4680840B2 - Axial blower - Google Patents

Axial blower Download PDF

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Publication number
JP4680840B2
JP4680840B2 JP2006175532A JP2006175532A JP4680840B2 JP 4680840 B2 JP4680840 B2 JP 4680840B2 JP 2006175532 A JP2006175532 A JP 2006175532A JP 2006175532 A JP2006175532 A JP 2006175532A JP 4680840 B2 JP4680840 B2 JP 4680840B2
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chord
blade
center point
line center
region
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JP2008002441A (en
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俊勝 新井
仁 菊地
克己 荒木
慎悟 濱田
誠治 中島
普道 青木
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Mitsubishi Electric Corp
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Mitsubishi Electric Corp
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Priority to JP2006175532A priority Critical patent/JP4680840B2/en
Priority to TW096117583A priority patent/TW200809091A/en
Priority to KR1020070060355A priority patent/KR100858395B1/en
Priority to CNA2007101120871A priority patent/CN101096965A/en
Publication of JP2008002441A publication Critical patent/JP2008002441A/en
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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
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
    • 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
    • F04D29/663—Sound attenuation
    • 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
    • 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

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

Description

本発明は、換気扇やエアコン等に用いる軸流送風機に関するものである。   The present invention relates to an axial blower used for a ventilation fan, an air conditioner, or the like.

従来の軸流送風機として、回転翼を取り付けて回転するボス部と、回転方向に面する翼前縁部、回転方向と反対の方向に面する翼後縁部、及び上記ボス部に対向する翼外周部から周が構成される回転翼とを有する軸流送風機において、上記ボス部から上記翼外周部の間に位置する屈曲点までの第１領域に存在する各翼弦線中心点に対応する第１前傾角を一定とし、かつ前記第１領域と上記翼外周部間の第２領域に存在する各翼弦線中心点に対応する第２前傾角を前記第１前傾角より大きくなるように形成したものがある（例えば、特許文献１参照）。   As a conventional axial flow blower, a boss portion that rotates by attaching a rotary blade, a blade leading edge portion that faces the rotation direction, a blade trailing edge portion that faces the direction opposite to the rotation direction, and a blade that faces the boss portion Corresponding to each chord line center point existing in the first region from the boss portion to the bending point located between the blade outer peripheral portions, in the axial flow fan having the rotating blades configured from the outer peripheral portion. The first forward tilt angle is constant, and the second forward tilt angle corresponding to each chord line center point existing in the second region between the first region and the blade outer peripheral portion is larger than the first forward tilt angle. Some have been formed (for example, see Patent Document 1).

特許第３２０３９９４号公報Japanese Patent No. 3320994

しかしながら、上記従来の技術によれば、翼端渦に起因する騒音を低減することができるが、回転翼に第１、第２の前傾角をつけることによって、翼外周部がボス部よりかなり前方（上流側）へ出るので、軸流送風機の軸方向の寸法が大きくなる。そのため、製品全体の寸法が大きくなってしまう、という問題があった。   However, according to the above conventional technique, noise caused by the blade tip vortex can be reduced. However, by providing the first and second forward tilt angles to the rotary blade, the blade outer peripheral portion is considerably forward of the boss portion. Since it goes out (upstream side), the axial dimension of an axial-flow fan becomes large. For this reason, there is a problem that the size of the entire product becomes large.

本発明は、上記に鑑みてなされたものであって、軸流送風機の軸方向の寸法を増大させずに騒音を低減する軸流送風機を得ることを目的とする。   This invention is made in view of the above, Comprising: It aims at obtaining the axial flow fan which reduces a noise, without increasing the dimension of the axial direction of an axial flow fan.

上述した課題を解決し、目的を達成するために、本発明は、モータにより回転駆動されるボス部と、前記ボス部に放射状に取付けられ回転軸方向に送風する複数の回転翼と、を備える軸流送風機において、前記回転翼の、前記ボス部から径方向中間部の屈曲点までの第１領域における翼弦中心線を、０°より大きい一定の第１前傾角で上流側へ傾斜させ、前記屈曲点から翼外周部までの第２領域における翼弦中心線を、前記第１前傾角よりもさらに上流側に傾斜させ、かつ、前記翼外周部における翼弦中心線の接線の前傾角が３０°〜４５°の範囲内となるように前記第１前傾角を設定することを特徴とする。 In order to solve the above-described problems and achieve the object, the present invention includes a boss portion that is rotationally driven by a motor, and a plurality of rotor blades that are radially attached to the boss portion and blown in the direction of the rotation axis. In the axial blower, the chord centerline in the first region from the boss portion to the bending point of the radial intermediate portion of the rotor blade is inclined upstream at a constant first forward inclination angle greater than 0 °. The chord centerline in the second region from the bending point to the outer periphery of the blade is inclined further upstream than the first forward tilt angle, and the forward tilt angle of the tangent to the chord centerline in the outer periphery of the blade is The first forward tilt angle is set to be within a range of 30 ° to 45 °.

この発明によれば、回転翼の軸方向寸法を増大させずに、翼端渦に起因する騒音を低減させ、かつ、送風性能の低下が小さい軸流送風機が得られる、という効果を奏する。   According to the present invention, there is an effect that an axial fan can be obtained without increasing the axial dimension of the rotor blade, reducing the noise caused by the blade tip vortex and reducing the deterioration of the air blowing performance.

以下に、本発明にかかる軸流送風機の実施の形態を図面に基づいて詳細に説明する。なお、この実施の形態によりこの発明が限定されるものではない。   Embodiments of an axial fan according to the present invention will be described below in detail with reference to the drawings. Note that the present invention is not limited to the embodiments.

実施の形態
図１は、軸流送風機の翼車を示す斜視図であり、図２は、翼車を回転軸３に直交する平面Ｓｃに投影した平面投影図であり、図３は、図２におけるボス部翼弦線中心点Ｐｂ´から外周部翼弦線中心点Ｐｔ´までの各翼弦線中心点の軌跡、すなわち翼弦線中心点Ｐｂ´−Ｐｒ´−Ｐｔ´について、任意の半径Ｒにおける各翼弦線中心点Ｐｒ´を、回転軸３と０Ｘ軸とを含む垂直平面に半径Ｒで回転投影した各翼弦線中心点Ｐｒの軌跡を示す図であり、図４は、本発明の実施の形態の各翼弦線中心点Ｐｒ２の軌跡を示す図３と同様の図であり、図５は、実施の形態の各翼弦線中心点Ｐｒ２の軌跡の定義方法を示す図４と同様の図であり、図６は、実施の形態の翼車の流量係数φと比騒音ＫT、流量係数φとファン効率ηSとの関係を実験的に求めた結果を示す図である。 Embodiment FIG. 1 is a perspective view showing an impeller of an axial blower, FIG. 2 is a plan view of the impeller projected onto a plane Sc orthogonal to the rotation shaft 3, and FIG. The radius of the chord line center point from the boss chord line center point Pb 'to the outer peripheral chord line center point Pt', that is, the chord line center point Pb'-Pr'-Pt ' FIG. 4 is a diagram showing the trajectory of each chord line center point Pr obtained by rotating and projecting each chord line center point Pr ′ in R with a radius R on a vertical plane including the rotation axis 3 and the 0X axis. FIG. 5 is a view similar to FIG. 3 showing the trajectory of each chord line center point Pr2 according to the embodiment of the invention, and FIG. 5 is a diagram illustrating a method of defining the trajectory of each chord line center point Pr2 according to the embodiment. and a similar view, Fig. 6, flow coefficient φ and the specific noise level K T for wheel according to the embodiment, the relationship between the flow coefficient φ and the fan efficiency eta S experimentally It is a diagram illustrating a meta results.

図１に示すように、実施の形態の翼車は３枚羽根であるが、本発明の翼車の回転翼枚数は、他の複数の枚数であってもよい。以下の説明は、主に１枚の回転翼の形状について述べるが、他の回転翼の形状も同一の形状である。   As shown in FIG. 1, the impeller of the embodiment has three blades, but the number of rotating blades of the impeller of the present invention may be a plurality of other numbers. In the following description, the shape of one rotor blade is mainly described, but the shapes of the other rotor blades are the same.

３次元立体形状を有する回転翼１が、図示しないモータに回転駆動されて回転軸３回りに矢印４方向に回転する円柱状のボス部２の外周に放射状に取付けられている。回転翼１の回転によって矢印Ａ方向の気流が発生する。   A rotating blade 1 having a three-dimensional solid shape is radially attached to the outer periphery of a cylindrical boss portion 2 that is driven to rotate by a motor (not shown) and rotates in the direction of arrow 4 around a rotating shaft 3. An airflow in the direction of arrow A is generated by the rotation of the rotary blade 1.

図１に示す回転翼１を回転軸３に直交する平面Ｓｃ（図３、図４参照）に投影すると、図２に示す回転翼１´の形状となる。図２に示す点Ｐｂ´は、ボス部２の外周における翼前縁部１ｂ´から翼後縁部１ｃ´までの翼弦線中心点（中点）を示す。   When the rotating blade 1 shown in FIG. 1 is projected onto a plane Sc (see FIGS. 3 and 4) orthogonal to the rotating shaft 3, the shape of the rotating blade 1 ′ shown in FIG. 2 is obtained. A point Pb ′ shown in FIG. 2 indicates a chord line center point (middle point) from the blade leading edge 1b ′ to the blade trailing edge 1c ′ on the outer periphery of the boss portion 2.

同様に、Ｐｔ´は、翼外周部１ｄにおける翼前縁部１ｂから翼後縁部１ｃ´までの翼弦線中心点（中点）を示す。図２に示す線Ｐｒ´は、ボス部の翼弦線中心点Ｐｂ´から外周部の翼弦線中心点Ｐｔ´までの任意の半径Ｒにおける各翼弦線中心点の軌跡（翼弦中心線）を示す。   Similarly, Pt ′ indicates a chord line center point (middle point) from the blade leading edge 1b to the blade trailing edge 1c ′ in the blade outer periphery 1d. A line Pr ′ shown in FIG. 2 indicates the locus of each chord line center point (chond chord center line) at an arbitrary radius R from the chord line center point Pb ′ of the boss to the chord line center point Pt ′ of the outer periphery. ).

図３は、図２におけるボス部の翼弦線中心点Ｐｂ´から外周部の翼弦線中心点Ｐｔ´までの各翼弦線中心点の軌跡（翼弦中心線）、すなわち翼弦線中心点Ｐｂ´−Ｐｒ´−Ｐｔ´について、任意の半径Ｒにおける各翼弦線中心点Ｐｒ´を、回転軸３と０Ｘ軸とを含む垂直平面に半径Ｒで回転投影した各翼弦線中心点Ｐｒの軌跡（翼弦中心線）を示す図である。   3 shows the trajectory (blade chord centerline) of each chord line center point from the chord line center point Pb ′ of the boss portion to the chord line center point Pt ′ of the outer periphery in FIG. For each point Pb'-Pr'-Pt ', each chord line center point Pr' at an arbitrary radius R is rotationally projected with a radius R onto a vertical plane including the rotation axis 3 and the 0X axis. It is a figure which shows the locus | trajectory (chord centerline) of Pr.

図３に示すように、回転軸３と０Ｘ軸とを含む垂直平面に回転投影された翼弦中心線Ｐｒ（各翼弦線中心点Ｐｒの軌跡）は、ボス部の翼弦線中心点Ｐｂから翼外周部の翼弦線中心点Ｐｔまで、空気流の上流側に傾斜する前傾角δｚが、回転軸３に直交する平面Ｓｃと一定角度を成す線として表すことができる。   As shown in FIG. 3, the chord centerline Pr (the trajectory of each chord line center point Pr) that is rotationally projected onto a vertical plane including the rotation axis 3 and the 0X axis is the chord line center point Pb of the boss portion. From the chord line center point Pt of the blade outer periphery, the forward inclination angle δz that is inclined upstream of the airflow can be expressed as a line that forms a constant angle with the plane Sc that is orthogonal to the rotating shaft 3.

図４に破線で示す翼弦中心線Ｐｒは、図３に示す、前傾角δｚが一定角度の回転翼１の翼弦中心点の軌跡であり、本発明の実施の形態の翼弦中心線Ｐｒ１は、ボス部の翼弦線中心点Ｐｂから翼外周部の翼弦線中心点Ｐｔまでの領域で前傾角一定の場合の翼弦中心線Ｐｒと、ボス部の翼弦線中心点Ｐｂを通り回転軸３に直交する０Ｘ軸（前傾角＝０°）とに挟まれた領域内に位置させる。   A chord centerline Pr indicated by a broken line in FIG. 4 is a locus of the chord center point of the rotary blade 1 having a constant forward inclination δz shown in FIG. 3, and the chord centerline Pr1 according to the embodiment of the present invention. Passes through the chord line center point Pr when the forward tilt angle is constant in the region from the chord line center point Pb of the boss part to the chord line center point Pt of the outer periphery of the wing part, and the chord line center point Pb of the boss part. It is positioned within a region sandwiched between 0X axes (forward tilt angle = 0 °) orthogonal to the rotation axis 3.

翼弦線中心線Ｐｒと翼弦線中心線Ｐｒ１とは、ボス部の翼弦線中心点Ｐｂと翼外周部の翼弦線中心点Ｐｔとが同一位置にあり、翼外周部の翼弦線中心点Ｐｔの０Ｘ軸からの距離は、Ｈとなっている。   The chord line center line Pr and the chord line center line Pr1 are such that the chord line center point Pb of the boss and the chord line center point Pt of the outer periphery of the blade are at the same position, and the chord line of the outer periphery of the blade The distance from the 0X axis of the center point Pt is H.

図５に、実施の形態の各翼弦線中心点Ｐｒ２の軌跡と前傾角を示す。回転軸３から任意の半径Ｒでの翼弦線中心点をＰｒ２とし、翼弦中心線Ｐｒ１上に位置する翼弦線中心点Ｐｒ２の、回転軸３に直交する０Ｘ軸からの距離をＬｓとする。   FIG. 5 shows the trajectory and forward tilt angle of each chord line center point Pr2 of the embodiment. The chord line center point at an arbitrary radius R from the rotation axis 3 is Pr2, and the distance from the 0X axis perpendicular to the rotation axis 3 of the chord line center point Pr2 located on the chord line center line Pr1 is Ls. To do.

実施の形態の回転翼１は、ボス部２（半径Ｒｂ）から径方向中間部の屈曲点Ｐｗまでの第１領域は、一定の第１前傾角δｚｗで上流側に傾斜させ、屈曲点Ｐｗから翼外周部までの第２領域は、前記第１領域よりもさらに上流側に傾斜させている。   In the rotor blade 1 according to the embodiment, the first region from the boss part 2 (radius Rb) to the bending point Pw in the radial intermediate part is inclined upstream at a constant first forward inclination angle δzw, and from the bending point Pw. The second region up to the outer periphery of the blade is inclined further upstream than the first region.

翼弦中心線Ｐｒ１上の屈曲点Ｐｗの半径をＲｗ、翼外周部における翼弦線中心点Ｐｔとボス部２の外周における翼弦中心点Ｐｂとを結ぶ線Ｐｒの上流側への傾斜角である第２前傾角をδｚｔとする。第１前傾角δｚｗは、次の式で表わされる。
δｚｗ＝ｔａｎ-1（Ｌｓ／（Ｒ−Ｒｂ））
（Ｒｂ＜Ｒ≦Ｒｗ） The radius of the bending point Pw on the chord centerline Pr1 is Rw, and the inclination angle toward the upstream side of the line Pr connecting the chord line center point Pt on the outer periphery of the blade and the chord center point Pb on the outer periphery of the boss 2 is A second forward tilt angle is assumed to be δzt. The first forward tilt angle δzw is expressed by the following equation.
δzw = tan −1 (Ls / (R−Rb))
(Rb <R ≦ Rw)

屈曲点Ｐｗから翼外周部（半径Ｒｔ）までの間の第２領域における任意の半径Ｒでの翼弦線中心点Ｐｒ２に対応する傾斜角δｚｄは、下記に示すように、半径Ｒのｎ次関数（１≦ｎ）になるように形成し、さらに、翼外周部の翼弦線中心点Ｐｔにおける翼弦中心線Ｐｒ１の接線１５の傾斜角δｚｓを、３０°〜４５°の範囲内とする。
δｚｄ＝α（Ｒ−Ｒｗ)n＋δｚｗ
α＝（δｚｔ−δｚｗ）／（Ｒｔ−Ｒｗ）n
（Ｒｗ＜Ｒ≦Ｒｔ)
なお、上記の傾斜角δｚｄを半径Ｒのｎ次関数（１≦ｎ）とせずに、第２領域における翼弦中心線Ｐｒ１を、一定の前傾角で直線状に上流側に傾斜させるようにしてもよい。 The inclination angle δzd corresponding to the chord line center point Pr2 at an arbitrary radius R in the second region from the bending point Pw to the blade outer peripheral portion (radius Rt) is n-th order of the radius R as shown below. Further, the inclination angle δzs of the tangent line 15 of the chord center line Pr1 at the chord line center point Pt of the outer periphery of the blade is set within a range of 30 ° to 45 °. .
δzd = α (R− Rw ) n + δzw
α = (δzt−δzw) / (Rt−Rw) n
(Rw <R ≦ Rt)
It should be noted that the chord center line Pr1 in the second region is linearly inclined upstream at a certain forward tilt angle without using the tilt angle δzd as an n-order function (1 ≦ n) of the radius R. Also good.

図６は、上述の実施の形態の軸流送風機において、屈曲点半径Ｒｗ＝０．７×Ｒｔとし、屈曲点Ｐｗから翼外周部（半径Ｒｔ）までの間の第２領域における任意の半径Ｒでの翼弦線中心点Ｐｒ２に対応する傾斜角δｚｄを半径Ｒの２次関数により決定し、さらに、図５に示すように、翼外周部の翼弦線中心点Ｐｔにおける翼弦中心線Ｐｒ１の接線１５の傾斜角がδｚｓ＝３０°の場合、及び、接線１５の傾斜角がδｚｓ＝４５°の場合の、流量係数φと比騒音ＫT、流量係数φとファン効率ηTの関係を実験的に求めた結果を示す。 FIG. 6 shows an arbitrary radius R in the second region between the bending point Pw and the blade outer peripheral portion (radius Rt) with the bending point radius Rw = 0.7 × Rt in the axial flow fan of the above-described embodiment. Is determined by a quadratic function of radius R, and, as shown in FIG. 5, the chord centerline Pr1 at the chord line center point Pt of the outer periphery of the blade is determined. When the inclination angle of the tangential line 15 is δzs = 30 ° and when the inclination angle of the tangential line 15 is δzs = 45 °, the relationship between the flow coefficient φ and the specific noise K T , the flow coefficient φ and the fan efficiency η T is Results obtained experimentally are shown.

図６に示すように、翼外周部の翼弦線中心点Ｐｔにおける回転翼１の翼弦中心線Ｐｒ１の接線１５の傾斜角δｚｓが３０°の軸流送風機では、流量係数φの大きい動作領域において、従来の、前傾角δｚが一定の軸流送風機に比べ、比騒音ＫTが低減（−２〜−３ｄＢ(Ａ)）され、かつ、ファン効率ηTが改善（１％程度）されている。 As shown in FIG. 6, in the axial flow fan in which the inclination angle δzs of the tangent line 15 of the chord center line Pr1 of the rotor blade 1 at the chord line center point Pt of the outer peripheral portion of the blade is 30 °, the operating region having a large flow coefficient φ , The specific noise K T is reduced (−2 to −3 dB (A)) and the fan efficiency η T is improved (about 1%) as compared with the conventional axial fan with the constant forward inclination δz. Yes.

また、翼外周部の翼弦線中心点Ｐｔにおける翼弦中心線Ｐｒ１の接線１５の傾斜角δｚｓが４５°の軸流送風機では、若干ファン効率ηTが低下する動作領域があるが、開放点においては、従来の、前傾角δｚが一定の軸流送風機に比べ、比騒音ＫTが低減（−２〜−３ｄＢ(Ａ)）され、かつ、ファン効率ηTが改善（０．５％程度）されている。 Further, in the axial flow fan in which the inclination angle δzs of the tangent line 15 of the chord center line Pr1 at the chord line center point Pt on the outer peripheral portion of the blade is 45 °, there is an operating region in which the fan efficiency η T slightly decreases. , The specific noise K T is reduced (−2 to −3 dB (A)) and the fan efficiency η T is improved (about 0.5%) compared to the conventional axial flow fan with a constant forward inclination δz. )

なお、流量係数φ、比騒音ＫT及びファン効率ηTは、次の式で定義される。
φ＝Ｑ／（（π2／４）Ｄ3・（１−ν2）Ｎ）
ＫT＝ＳＰＬA−１０Ｌｏｇ（Ｑ・ＰT 2.5）
ηT＝（ＰT・Ｑ）／(６０ＰW）
Ｑ ：風量[ｍ3／ｍｉｎ]
ＰT ：全圧[Ｐａ]
ＳＰＬA ：騒音特性（Ａ補正）[ｄＢ(Ａ)]
Ｄ ：軸流送風機外径[ｍ]
ν ：ボス比（＝ボス部外径/軸流送風機外径）
Ｎ ：回転数[ｒｐｍ]
ＰW ：軸動力[Ｗ] The flow coefficient φ, the specific noise KT, and the fan efficiency η T are defined by the following equations.
φ = Q / ((π 2 /4) D 3 · (1-ν 2) N)
K T = SPL A -10 Log (Q · P T 2.5 )
η T = (P T · Q) / (60P W )
Q: Air volume [m 3 / min]
P T : Total pressure [Pa]
SPL A : Noise characteristics (A correction) [dB (A)]
D: Axial blower outer diameter [m]
ν: Boss ratio (= outer diameter of boss part / outer diameter of axial fan)
N: Number of revolutions [rpm]
P W : Shaft power [W]

以上のように、本発明にかかる軸流送風機は、換気扇やエアコン等に適している。   As described above, the axial blower according to the present invention is suitable for a ventilation fan, an air conditioner, and the like.

軸流送風機の翼車を示す斜視図である。It is a perspective view which shows the impeller of an axial-flow fan. 翼車を回転軸に直交する平面に投影した平面投影図である。It is the plane projection figure which projected the impeller on the plane orthogonal to a rotating shaft. 図２における各翼弦線中心点Ｐｒ´の軌跡を、回転軸と０Ｘ軸とを含む垂直平面に半径Ｒで回転投影した図である。FIG. 3 is a diagram in which the trajectory of each chord line center point Pr ′ in FIG. 2 is rotationally projected with a radius R onto a vertical plane including a rotation axis and a 0X axis. 本発明の実施の形態の翼弦中心線Ｐｒ１を示す図３と同様の図である。It is a figure similar to FIG. 3 which shows the chord centerline Pr1 of embodiment of this invention. 実施の形態の各翼弦線中心点Ｐｒ２の軌跡（翼弦中心線Ｐｒ１）の定義方法を示す図４と同様の図である。FIG. 5 is a view similar to FIG. 4 illustrating a method of defining the trajectory (chord chord centerline Pr1) of each chord line center point Pr2 according to the embodiment. 実施の形態の翼車の流量係数φと比騒音ＫT、流量係数φとファン効率ηSとの関係を実験的に求めた結果を示す図である。Is a diagram showing a result obtained flow coefficient of impeller Embodiment φ and the specific noise K T, the relationship between the flow coefficient φ and the fan efficiency eta S experimentally.

符号の説明Explanation of symbols

１ 回転翼
１´ 回転軸に直交する面に投影した回転翼
１ｂ´ 翼前縁部
１ｃ´ 翼後縁部
１ｄ´ 翼外周部
２ ボス部
３ 回転軸
４ 回転方向
Ａ 気流の方向
Ｐｂ，Ｐｂ´ ボス部の翼弦線中心点
Ｐｔ，Ｐｔ´ 翼外周部の翼弦線中心点
Ｐｒ，Ｐｒ´ 翼弦線中心点の軌跡（翼弦中心線）
Ｐｒ１ 本発明の実施の形態の翼弦線中心点の軌跡（翼弦中心線）
Ｐｒ２ 本発明の実施の形態の翼弦線中心点
Ｐｗ 一定の前傾角を変化させる起点となる屈曲点
Ｓｃ ボス部の翼弦線中心点を通り回転軸に直交する平面
Ｈ 翼外周部の翼弦線中心点Ｐｔの０Ｘ軸からの距離
１５ 翼外周部の翼弦線中心点Ｐｔにおける翼弦中心線の接線
δｚ 回転翼の前傾角
δｚｗ 屈曲点Ｐｗより内側の第１領域の一定の前傾角（第１前傾角）
δｚｔ ボス部の翼弦線中心点Ｐｂと翼外周部の翼弦線中心点Ｐｔとを結ぶ線の傾斜角（第２前傾角）
δｚｄ 屈曲点Ｐｗより外側の第２領域における任意の半径Ｒでの翼弦線中心点Ｐｒ２とボス部の翼弦線中心点Ｐｂとを結ぶ線の上流側への傾斜角
δｚｓ 翼外周部の翼弦線中心点Ｐｔにおける翼弦中心線Ｐｒ１の接線１５の前傾角 DESCRIPTION OF SYMBOLS 1 Rotary blade 1 'Rotary blade projected on the surface orthogonal to a rotating shaft 1b' Blade front edge part 1c 'Blade trailing edge part 1d' Blade outer peripheral part 2 Boss part 3 Rotary axis 4 Rotating direction A Air flow direction Pb, Pb ' Chord chord line center point of the boss Pt, Pt 'Chord chord line center point of the outer periphery of the blade Pr, Pr' Chord chord line center point (chord chord center line)
Pr1 Trajectory of chord line center point (chord center line) of the embodiment of the present invention
Pr2 The chord line center point Pw according to the embodiment of the present invention Pw A bending point that is a starting point for changing a certain forward tilt angle Sc A plane that passes through the chord line center point of the boss portion and is orthogonal to the rotation axis H The chord of the outer periphery of the blade Distance from the 0X axis of the line center point Pt 15 Tangent line of the chord center line at the chord line center point Pt of the outer periphery of the blade δz Forward tilt angle of the rotary blade δzw 1st forward tilt angle)
δzt Inclination angle (second forward inclination angle) of the line connecting the chord line center point Pb of the boss and the chord line center point Pt of the outer periphery of the blade
δzd Inclination angle toward the upstream side of the line connecting the chord line center point Pr2 and the chord line center point Pb of the boss at an arbitrary radius R in the second region outside the bending point Pw δzs The forward tilt angle of the tangent line 15 of the chord center line Pr1 at the chord line center point Pt

Claims (2)

モータにより回転駆動されるボス部と、前記ボス部に放射状に取付けられ回転軸方向に送風する複数の回転翼と、を備える軸流送風機において、
前記回転翼の、前記ボス部から径方向中間部の屈曲点までの第１領域における翼弦中心線を、０°より大きい一定の第１前傾角で上流側へ傾斜させ、前記屈曲点から翼外周部までの第２領域における翼弦中心線を、前記第１前傾角よりもさらに上流側に傾斜させ、かつ、前記翼外周部における翼弦中心線の接線の前傾角が３０°〜４５°の範囲内となるように前記第１前傾角を設定することを特徴とする軸流送風機。 In an axial blower comprising: a boss portion that is rotationally driven by a motor; and a plurality of rotor blades that are radially attached to the boss portion and blown in the direction of the rotation axis.
The chord centerline in the first region from the boss portion to the bending point of the radially intermediate portion of the rotating blade is inclined upstream with a constant first forward inclination angle greater than 0 °, and the blade is moved from the bending point to the blade. The chord centerline in the second region to the outer peripheral portion is inclined further upstream than the first forward tilt angle, and the tangential forward tilt angle of the chord centerline in the outer peripheral portion of the blade is 30 ° to 45 °. The axial flow blower is characterized in that the first forward tilt angle is set so as to fall within the range. 前記ボス部における翼弦中心線上の点と前記第２領域における翼弦中心線上の任意の点とを結ぶ線の上流側への傾斜角が、前記第２領域における翼弦中心線上の任意の点の半径のｎ次関数（１≦ｎ）となっていることを特徴とする請求項１に記載の軸流送風機。 An inclination angle to the upstream side of a line connecting a point on the chord centerline in the boss portion and an arbitrary point on the chord centerline in the second region is an arbitrary point on the chord centerline in the second region. The axial blower according to claim 1, wherein the axial flow fan is an n-order function (1 ≦ n) of the radius.
JP2006175532A 2006-06-26 2006-06-26 Axial blower Active JP4680840B2 (en)

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TW096117583A TW200809091A (en) 2006-06-26 2007-05-17 Axial blower
KR1020070060355A KR100858395B1 (en) 2006-06-26 2007-06-20 Axial Fan
CNA2007101120871A CN101096965A (en) 2006-06-26 2007-06-22 Axial flow forced draft fan

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US10859095B2 (en) 2016-06-16 2020-12-08 Mitsubishi Electric Corporation Impeller and axial flow fan

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JP5649608B2 (en) * 2012-03-30 2015-01-07 三菱電機株式会社 Axial blower
CN104632679B (en) * 2015-01-13 2016-08-24 西安交通大学 Counter-rotating fan operating mode self adaptation variable speed matching process
CN108138787B (en) * 2015-10-07 2019-12-06 美蓓亚三美株式会社 Impeller and axial fan comprising same
EP3372841B1 (en) * 2015-11-02 2019-12-25 Mitsubishi Electric Corporation Axial fan and air-conditioning device having said axial fan
CN114688049B (en) * 2020-12-25 2024-02-20 广东美的白色家电技术创新中心有限公司 Fan assembly and air conditioner

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JP2730344B2 (en) * 1991-09-19 1998-03-25 三菱電機株式会社 Blower impeller
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JP2002048094A (en) 2000-08-07 2002-02-15 Komatsu Ltd Fan
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Cited By (1)

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Publication number Priority date Publication date Assignee Title
US10859095B2 (en) 2016-06-16 2020-12-08 Mitsubishi Electric Corporation Impeller and axial flow fan

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TWI335384B (en) 2011-01-01
KR20070122376A (en) 2007-12-31

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