WO2019069374A1 - プロペラファンおよび軸流送風機 - Google Patents

プロペラファンおよび軸流送風機 Download PDF

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Publication number
WO2019069374A1
WO2019069374A1 PCT/JP2017/036010 JP2017036010W WO2019069374A1 WO 2019069374 A1 WO2019069374 A1 WO 2019069374A1 JP 2017036010 W JP2017036010 W JP 2017036010W WO 2019069374 A1 WO2019069374 A1 WO 2019069374A1
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WIPO (PCT)
Prior art keywords
rotor
angle
distribution
comparative example
region
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Application number
PCT/JP2017/036010
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English (en)
French (fr)
Japanese (ja)
Inventor
新井　俊勝
菊地　仁
千景 門井
Original Assignee
三菱電機株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Application filed by 三菱電機株式会社 filed Critical 三菱電機株式会社
Priority to CN201780095281.5A priority Critical patent/CN111133201B/zh
Priority to PCT/JP2017/036010 priority patent/WO2019069374A1/ja
Priority to US16/643,647 priority patent/US20200240430A1/en
Priority to JP2019546443A priority patent/JP6811873B2/ja
Priority to TW107112572A priority patent/TWI658215B/zh
Publication of WO2019069374A1 publication Critical patent/WO2019069374A1/ja

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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
    • 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
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • 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
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • the present invention relates to a propeller fan and an axial flow fan used for a ventilation fan, an air conditioner, and the like.
  • the rotor blade is inclined upstream with a fixed first front inclination angle on the inner peripheral side of the rotor blade, and rotated on the outer peripheral side with a second front inclination angle larger than the first front inclination angle. It is shown that the wing is inclined upstream.
  • Patent Document 2 shows that the stagger angle of a rotary blade is linearly increased from the inner peripheral edge to the outer peripheral edge. Further, Patent Document 2 shows that the stagger angle on the inner peripheral side is a distribution having a local minimum value, and the stagger angle on the outer peripheral side is a distribution having a maximum value.
  • the present invention has been made in view of the above, and it is an object of the present invention to obtain a propeller fan and an axial fan capable of achieving further noise reduction and improvement of fan efficiency.
  • a propeller fan comprises: a boss which is rotationally driven; and a plurality of rotors which are radially attached to the boss and generate air flow in the rotational axis direction. Equipped with The radial cross section on the inner peripheral side of the rotor has a convex shape with respect to the direction of the air flow, and the radial cross section on the outer peripheral side of the rotary blade is concave with respect to the air flow It has a shape.
  • the radial cross section of the rotor blade is inclined to the upstream side of the air flow in the leading edge area, and the inclination angle increases as it goes to the leading edge, and is inclined to the downstream side of the air flow in the trailing edge area.
  • the inclination angle increases as it goes to the trailing edge.
  • the stagger angle of the rotor has a first stagger angle distribution having a minimum value in the region from the inner peripheral edge to the first boundary position, and in the region from the first boundary position to the outer peripheral edge, It has a second stagger angle distribution including an n-order function whose variable is the radius of the rotor, which increases as going to the outer peripheral edge.
  • the n is a value from 1 to 2 and does not include 1.
  • the rotor can be shaped so as to conform to the air flow from the inner circumferential edge to the outer circumferential edge, noises caused by tip vortices can be reduced, and fan efficiency can be improved.
  • a perspective view showing an example of an axial flow fan A perspective view showing an example of a propeller fan Schematic diagram showing the generation of wing tip vortices
  • a cross-sectional view of the rotor of the present embodiment, cut in the radial direction The figure which showed typically the cross-sectional shape in the several cutting position of the rotary blade of this Embodiment, the tip vortex, and the flow in the radial direction.
  • Diagram showing multiple cutting positions Diagram showing the positional relationship between the rotary wing and the half bell mouse Diagram showing the positional relationship between the rotary wing and the full bell mouse
  • Diagram for explaining the definition of stagger angle The figure which shows an example of distribution of the stagger angle of the rotary blade of this Embodiment
  • the figure which shows distribution of the stagger angle of the rotor of comparative example 1 and comparative example 2 A developed cross-sectional view comparing the stagger angle of Comparative Example 1 and the stagger angle of Comparative Example 2 in the first region
  • Schematic view showing a rotor of Comparative Example 1 Schematic view showing a rotor of Comparative Example 2 Diagram for explaining the definition of advancing angle
  • a diagram showing fan efficiency characteristics, specific noise characteristics and static pressure characteristics of the rotors of Example 1 and Example 3 and Comparative Example 5 when using a half bell mouse A diagram showing fan efficiency characteristics, specific noise characteristics and static pressure characteristics of the rotors of Example 1 and Example 3 and Comparative Example 5 when using a full bell mouse
  • FIG. 1 is a perspective view showing an example of an axial flow fan 100 according to the embodiment.
  • FIG. 2 is a perspective view showing an example of a propeller fan 10 according to the embodiment.
  • the axial flow fan 100 includes a propeller fan 10, a main body 20, a bell mouth 30, a motor (not shown), and a motor fixing member (not shown).
  • the propeller fan 10 and the motor are disposed inside the bell mouth 30.
  • the propeller fan 10 has a cylindrical boss portion 2 and a plurality of rotary blades 1 having the same three-dimensional three-dimensional shape.
  • the boss 2 is rotationally driven by a motor, and rotates in the direction of arrow W around the rotation axis O.
  • Each rotary wing 1 is radially attached to the outer periphery of the boss 2.
  • the rotary wing 1 is a front edge 1a which is a front end in the rotational direction W, a rear edge 1b which is a rear end in the rotational direction W, and an end which is an inner peripheral side (a boss 2 side) It has an inner peripheral edge 1c and an outer peripheral edge 1d which is an end on the outer peripheral side.
  • the rotor 1 As the propeller fan 10 rotates, the rotor 1 generates an air flow in the direction of the arrow A. In FIG. 1, five rotors 1 are shown, and in FIG. 2, three rotors 1 are shown. Other numbers may be adopted as the number of rotary wings 1.
  • FIG. 3 shows one rotor 1 of the propeller fan 10.
  • a pressure difference is generated between the blade pressure surface and the blade suction surface of the rotary blade 1.
  • leakage vortices are generated from the blade pressure surface with high pressure to the blade suction surface with low pressure as shown in FIG. 3. This is called wing tip vortex 5.
  • the blade surface on the upstream side is a suction surface 1 f with low pressure
  • the surface on the downstream side is a pressure surface 1 g with high pressure with respect to the air flow direction A.
  • the rotation axis O as the Z axis and the two axes perpendicular to the Z axis as the X axis and the Y axis.
  • FIG. 4 is a cross-sectional view showing the radial shape of the rotary wing 1 according to the embodiment.
  • the rotary wing 1 has a convex shape with respect to the direction A of the air flow in the radial direction cross section on the boss 2 side, and has a concave shape with respect to the direction A of the air flow in the radial direction cross section with the outer peripheral portion. That is, the rotary wing 1 has a convex vertex m1 on the inner peripheral side and a concave vertex m2 on the outer peripheral side. Therefore, the cross section of the rotary wing 1 has an S shape in which the inner peripheral side is convex with respect to the air flow and the outer peripheral side is concave with respect to the air flow.
  • FIG. 5 is a view schematically showing a blade shape of a radial cross section of the rotary blade 1 according to the embodiment, a tip vortex and a radial flow.
  • FIG. 5 (a) shows each cross-sectional shape along O-D1 in FIG. 6,
  • FIG. 5 (b) shows each cross-sectional shape along O-D2 in FIG. 6, and
  • FIG. 5 (c) shows Each cross-sectional shape along O-D 3 in FIG. 6 is shown, and
  • FIG. 5 (d) shows each cross-sectional shape along O-D 4 in FIG.
  • O-D1 is a line extending a line connecting the rotation axis O and the rear end Fr of the front edge 1a to the outer peripheral edge 1d.
  • O-D4 is a line connecting the rotation axis O and the front end Rf of the trailing edge 1b.
  • the front edge side region of the rotor 1 which is a region closer to the front edge 1 a than the blade center C, is inclined upstream of the air flow A.
  • the inclination angle ⁇ (O ⁇ D1) in the ⁇ D1 cross section is larger than the inclination angle ⁇ (O ⁇ D2) in the O ⁇ D2 cross section. That is, in the front edge region, the inclination angle ⁇ becomes larger as it goes to the front edge 1a.
  • the wing center C corresponds to the bisector of the angle between O-D1 and O-D4.
  • the inclination angle ⁇ is an angle formed by a line segment connecting the inner peripheral edge 1c and the vertex m2 on the outer peripheral side, and the XY plane.
  • the leading edge region of the rotor 1 is shaped to be compatible with the tip vortices 5 and the transverse suction flow 9 to the wing periphery.
  • the trailing edge region of the rotary blade 1 which is the region closer to the trailing edge 1 b than the blade center C is inclined to the downstream side of the air flow A.
  • the inclination angle ⁇ (O ⁇ D4) in the ⁇ D4 cross section is larger than the inclination angle ⁇ (O ⁇ D3) in the O ⁇ D3 cross section. That is, in the trailing edge region, the inclination angle ⁇ becomes larger as it goes to the trailing edge 1 b.
  • the trailing edge region of the rotary blade 1 is shaped so as not to leak the centrifugal component 14 of the flow on the raised inner peripheral side while controlling the tip vortices 5, and the efficiency is reduced. It is prevented.
  • the curvature radius value R2 of the outer recess which is the area from the vertex m2 on the outer peripheral side to the outer peripheral edge 1d, gradually decreases from the front edge 1a toward the rear edge 1b. Distribution. That is, R2 (O-D1)> R2 (O-D2)> R2 (O-D3)> R2 (O-D4). Further, the curvature radius value R2 decreases as the gradually decreasing rate approaches the trailing edge 1b.
  • the wing end vortex 5 generated at the outer peripheral portion can be smoothly separated from the wing surface, and the wing end vortex 5 is concentrated.
  • the noise is diffused to reduce the generation of noise by weakening the disturbance caused by the tip vortices 5.
  • FIG. 7 is a schematic cross-sectional view of an axial flow fan using the rotary wing 1 and the half bell mouth 30a.
  • the half bell mouse 30a surrounds the rotor 1 so that the area including the leading edge 1a is opened.
  • FIG. 8 is a schematic cross-sectional view of an axial flow fan using the rotary wing 1 and the full bell mouse 30b.
  • the full bell mouse 30 b surrounds the rotor 1 so as to cover the entire rotor 1 from the side.
  • Each of the half bell mouse 30a and the full bell mouse 30b has a suction side curved surface Rin, a straight portion ST having a cylindrical shape, and a discharge side curved surface Rout.
  • FIG. 9 is a view showing the distribution of the air flow of the axial flow fan using the rotary wing 1 and the half bell mouth 30a.
  • the axial flow fan having the half bell mouth 30a since the front edge 1a side of the rotary wing 1 is largely open, the lateral suction flow 9 and the flow 11 inside the wing from the front edge 1a to the rear edge 1b are the rotary wing 1 Flow into For this reason, the wing tip vortex 5 largely develops from the front edge 1 a side of the rotary wing 1. Further, the flow 11 inside the wing changes its condition as it goes from the leading edge 1a to the trailing edge 1b, so the condition of the wing tip vortex 5 largely differs depending on the axial position.
  • FIG. 10 is a view showing the distribution of the air flow of the axial flow fan using the rotary wing 1 and the full bell mouse 30b.
  • the flow to the rotor 1 is generally only the flow 11 inside the wing. For this reason, the generation of the tip vortices 5 does not start from the leading edge 1a, and the tip vortices 5 start to be generated from a point at which the pressure increase starts to some extent.
  • the position of the wing tip vortex 5 changes according to the shape of the bellmouth.
  • the inner circumferential edge 1c to the outer circumferential edge 1d of the rotary wing 1 It divides into an outside 2nd field, defines, and proposes the shape of the 1st field and the shape of the 2nd field which can realize noise reduction and the improvement of fan efficiency.
  • FIG. 11 is a developed cross-sectional view in which the rotary wing 1 is cut at an arc 6-6 'of an arbitrary radius shown in FIG. 6, and the cylindrical surface of the arc 6-6' is developed into a plane.
  • the stagger angle is an angle formed by the chord line 41 and the line segment 42.
  • the chord line 41 is a straight line connecting the front edge 1 a of the cut surface 40 of the rotary wing 1 and the rear edge 1 b of the cut surface 40.
  • the line segment 42 is a straight line which is parallel to the rotation axis O and intersects the front edge 1a.
  • FIG. 12 is a diagram showing an example of the distribution of the stagger angle stick of the present embodiment.
  • the horizontal axis corresponds to the radius R of the rotary wing 1
  • the vertical axis indicates the stagger angle ⁇ .
  • the solid line Ls indicates the distribution of the stagger angle of the present embodiment
  • the broken line Lv1 indicates the distribution of the stagger angle of the comparative example 1.
  • the left end of the line segment Ls is a stagger angle ⁇ c at the radial position Rc of the inner peripheral edge 1c connected to the boss portion 2, and the right end of the line segment Ls represents the stagger angle ⁇ d at the radial position Rd of the outer peripheral edge 1d. .
  • the stagger angle ⁇ of the present embodiment has the first stagger angle distribution Ls1 in the first area AR1 from the radial position Rc to the boundary position Re1, and in the second area AR2 from the boundary position Re1 to the radial position Rd. It has a second stagger angle distribution Ls2 different from the first stagger angle distribution Ls1.
  • the first stagger angular distribution Ls1 has a minimum value ⁇ min at a position Rmin close to the boundary position Re1.
  • the position Rmin is between the middle point of the first area AR1 and the boundary position Re1.
  • the stagger angle ⁇ ⁇ ⁇ gradually decreases from the radial position Rc toward the radial position Rmin, and the stagger angle ⁇ ⁇ ⁇ gradually increases from the radial position Rmin toward the boundary position Re1.
  • the second stagger angle distribution Ls2 has a distribution in which the stagger angle ⁇ ⁇ ⁇ gradually increases so as to be smoothly continuous with the first stagger angle distribution Ls1.
  • the second stagger angle distribution Ls2 has a distribution defined by a 1 to 2 dimensional function with the radius R as a variable. However, the second stagger angle distribution Ls2 does not include a linear function. The second stagger angle distribution Ls2 is defined as a function that is convex downward. The second stagger angle distribution Ls2 shown in FIG. 12 is a 1.2-order function. Further, the increase rate of the second stagger angle distribution Ls2 is set larger than the decrease rate of the first stagger angle distribution Ls1.
  • FIG. 13 is a view showing a distribution Lv1 of the stagger angle rods of Comparative Example 1 and a distribution Lv2 of the stagger angle rods of Comparative Example 2.
  • Comparative Example 1 and Comparative Example 2 are shown in Patent Document 2.
  • the stagger angle ⁇ ⁇ increases linearly (in a linear function) at a constant increasing rate.
  • the distribution Lv2 the distribution of the first area AR1 'from the radial position Rc of the inner peripheral edge 1c to the boundary position Re' and the radius of the outer peripheral edge 1d from the boundary position Re 'as in the stagger angle of the present embodiment. It has distribution of 2nd area
  • the stagger angle ⁇ ⁇ ⁇ gradually decreases in a curved manner from the radial position Rc to the radial position Re ′, and has a local minimum value at the radial position Re ′.
  • the stagger angle ⁇ ⁇ ⁇ ⁇ at the radial position Rc is the maximum value of the stagger angle ⁇ of the entire rotor 1.
  • the stagger angle ⁇ ⁇ ⁇ gradually increases from the boundary position Re ′ to reach the local maximum, and gradually decreases from the radial position of the local maximum to the radial position Rd.
  • FIG. 14 is a developed cross-sectional view comparing the stagger angle of Comparative Example 1 and the stagger angle of Comparative Example 2 in the first region AR1 ′.
  • FIG. 14 is a view in which the rotors of Comparative Example 1 and Comparative Example 2 are cut at a radius R1 ′ shown in FIG. 13 and the cut cylindrical surface is developed into a plane.
  • the broken line 43 corresponds to the first comparative example
  • the thick solid line 44 corresponds to the second comparative example.
  • the ridge R11 indicates the stagger angle at the radius R1 'of the first comparative example
  • the ridge R12 indicates the stagger angle at the radius R1' of the second comparative example.
  • the wing in the comparative example 2 is lying as compared to the comparative example 1.
  • FIG. 15 is a developed cross-sectional view comparing the stagger angle of Comparative Example 1 and the stagger angle of Comparative Example 2 in the second region AR2 ′.
  • FIG. 15 is a diagram in which the rotary wings of Comparative Example 1 and Comparative Example 2 are cut at a radius R2 ′ shown in FIG. 13 and the cut cylindrical surface is developed into a plane.
  • the broken line 45 corresponds to the first comparative example
  • the thick solid line 46 corresponds to the second comparative example.
  • the ridge R21 indicates the stagger angle at the radius R2 'of the first comparative example
  • the ridge R22 indicates the stagger angle at the radius R2' of the second comparative example.
  • the wing of the comparative example 2 is higher than that of the comparative example 1.
  • FIG. 16 is a schematic view showing a rotor of Comparative Example 1.
  • FIG. 17 is a schematic view showing a rotor of Comparative Example 2. As shown in FIGS. 16 and 17, the blade height H2 at the outer peripheral edge of Comparative Example 2 is larger than the blade height H1 of Comparative Example 1.
  • the blade angle with respect to the flow is set to an appropriate value in the high flow velocity area and the low flow velocity area, respectively, and noise reduction and high efficiency are achieved.
  • the blade height at the outer peripheral portion is increased.
  • the stagger angle distribution as shown in FIG. 12 it is possible to optimize the stagger angle distribution while suppressing the outer peripheral height that leads to an increase in the product height.
  • the wing shape of the present embodiment is the same as that of Comparative Example 1 on the outer peripheral side, and the same shape as that of Comparative Example 2 on the inner peripheral side. Therefore, in the present embodiment, it is possible to match the wing angle and the flow angle while suppressing the height of the outer peripheral portion. As a result, it is possible to reduce wing leading edge separation and wake vortex loss, and to achieve low noise and high efficiency.
  • the stagger angle of the second region AR2 can be adjusted, and it is possible to smoothly connect with the second region AR2.
  • FIG. 18 is a plan view for explaining the advancing angle [delta] theta.
  • g is a chord center line.
  • the chord center line g is a line connecting the middle point of the leading edge 1a and the trailing edge 1b at each radial position from the inner peripheral edge 1c to the outer peripheral edge 1d.
  • An angle is defined as an advancing angle ⁇ ⁇ .
  • Figure 19 is a diagram showing the one example of the distribution of the advancing angle [delta] theta of this embodiment, the distribution of the advancing angle [delta] theta of Comparative Example 3.
  • the solid line corresponds to the present embodiment, and the broken line corresponds to comparative example 3.
  • the advancing angle [delta] theta has increased linearly from the inner circumferential edge 1c on the outer periphery 1d.
  • the outer peripheral portion has a triangular wing shape. In the case of the triangular wing shape, peeling vortices are generated from the triangular wing, and the generated peeling vortices can suppress leading edge peeling vortices and wing tip vortices, and noise can be reduced.
  • FIG. 20 is a diagram showing the wing shape of Comparative Example 3 when the rate of increase of the advancing angle is small.
  • FIG. 21 is a diagram showing the wing shape of Comparative Example 3 in the case where the rate of increase of the advancing angle is larger than that in FIG.
  • the length of the inner peripheral edge 1c in FIG. 20 and the length of the inner peripheral edge 1c in FIG. 21 are equal.
  • the length of the outer peripheral edge 1 d in FIG. 20 and the length of the outer peripheral edge 1 d in FIG. 21 are equal. From advancing angle [delta] theta 1 of the outer peripheral edge 1d in FIG. 20, the larger the advancing angle [delta] theta 2 of the outer peripheral edge 1d in FIG.
  • the advance angle of the rotor blade of the present embodiment has different distributions in the first area AR1 and the second area AR2, as shown by the solid line in FIG.
  • the first area AR1 is an area from the radius Rc corresponding to the inner peripheral edge 1c to the boundary position Re2.
  • the second area AR2 is an area from the boundary position Re2 to the outer peripheral edge 1d.
  • Advancing angle [delta] theta is in the first region AR1, having a linear distribution which increases gradually from the radial position Rc the boundary position Re2.
  • Advancing angle [delta] theta is in the second region AR2, with gradual 1-2 quadratic function distribution that increases from the boundary position Re2 to the radial position Rd.
  • the advancing angle [delta] theta in the second region AR2 having from 1 to 2 linear function of the radius R and the variable.
  • the advance angle [delta] theta in the second region AR2 does not include the linear function.
  • the advancing angle [delta] theta in the second region AR2, as 1-2 linear function is convex downward, are defined.
  • a 1.2-order function is shown as a distribution function of the second region AR2.
  • the linear distribution in the first region AR1 and the 1.2-order function distribution in the second region AR2 are connected smoothly.
  • the increase rate of the distribution of the advancing angle [delta] theta in the first region AR1 more increase in the distribution of the advancing angle [delta] theta in the second region AR2 is large is desirable.
  • FIG. 22 shows an example of a rotary wing shape in the case where the advance angle distribution of the present embodiment shown in FIG. 19 is adopted.
  • the forward angle distribution according to the present embodiment in the outer peripheral portion of the blade, the blade area at the inner peripheral portion of the blade is increased while securing the triangular blade shape for noise reduction, and It is possible to increase the strength.
  • FIG. 23 is a diagram for explaining the definition of the anteversion angle ⁇ z.
  • FIG. 23 is a diagram in which a rotary wing having a constant forward inclination angle ⁇ z is rotationally projected on a plane including the rotation axis O and the X axis.
  • the anteversion angle ⁇ z is an angle formed by the chord center line g ′ with a plane perpendicular to the rotation axis O of the rotary blade 1, and the direction toward the upstream side is positive.
  • FIG. 23 is a diagram for explaining the definition of the anteversion angle ⁇ z.
  • FIG. 23 is a diagram in which a rotary wing having a constant forward inclination angle ⁇ z is rotationally projected on a plane including the rotation axis O and the X axis.
  • the anteversion angle ⁇ z is an angle formed by the chord center line g ′ with a plane perpendicular to the rotation axis O of the rotary blade 1, and the direction toward the upstream
  • FIG. 24 is a view showing a chord center line g of the rotary wing 1 according to the present embodiment in which the outer peripheral portion of the wing is bent upstream, and the rotary wing is projected on a plane including the rotation axis O and the X axis.
  • FIG. 24 is a view showing a chord center line g of the rotary wing 1 according to the present embodiment in which the outer peripheral portion of the wing is bent upstream, and the rotary wing is projected on a plane including the rotation axis O and the X axis.
  • FIG. 25 is a view showing an example of the distribution of the anteversion angle ⁇ z of the present embodiment and the distribution of the anteversion angle ⁇ z of the comparative example 4.
  • a solid line corresponds to the present embodiment, and a broken line corresponds to comparative example 4.
  • Comparative Example 4 is shown in Patent Document 1.
  • the anteversion angle ⁇ z is the distribution of the first area AR1 from the radial position Rc of the inner peripheral edge 1c to the boundary position Re3 and the radial position Rd of the outer peripheral edge 1d from the boundary position Re3. It has distribution of 2nd field AR2.
  • the anteversion angle ⁇ z of the first area AR1 is a constant value ⁇ z1
  • the anteversion angle ⁇ z of the second area AR2 is an upstream so as to be an n-order function (1 ⁇ n) with the radius R as a variable It is further inclined to the side.
  • the anteversion angle ⁇ z of the first area AR1 is a constant value ⁇ z1 as in Comparative Example 4, and the anteversion angle ⁇ z of the second area AR2 is 2 to 6 with the radius R as a variable. Further noise reduction is realized by making the distribution of the fifth order function.
  • the comparative example 4 is shown as a quadratic function, and the present embodiment is shown as a cubic function.
  • second to fifth degree functions second to third degree functions are particularly preferable.
  • FIG. 26 to FIG. 37 show the evaluation results when the rotor with a diameter of 260 (mm) is rotated at a constant rotational speed.
  • Specific noise Kt based on total pressure, specific noise Ks based on static pressure, fan efficiency Et based on total pressure, and fan efficiency Es based on static pressure, which are used in FIGS. 26 to 37, are defined by the following equations Calculated value.
  • Kt SPLA-10 Log (Q ⁇ PT 2.5 )
  • Q Air volume [m 3 / min]
  • PT Total pressure [Pa]
  • SPLA Noise characteristics (after A correction) [dB]
  • Ks SPLA-10 Log (Q, PS 2.5 ) Q: Air volume [m 3 / min] PS: Static pressure [Pa] SPLA: Noise characteristics (after A correction) [dB]
  • Es (PS ⁇ Q) / (60 ⁇ PW) Q: Air volume [m 3 / min] PS: Static pressure [Pa] PW: Shaft power [W]
  • the A correction is a correction to reduce low-frequency sound in accordance with the characteristics of human hearing, and is a correction based on, for example, the A characteristics defined in JIS C 1502-1990.
  • FIG. 26 is a view showing various characteristics of the rotor of Comparative Example 5, the rotor of Example 1, and the rotor of Example 2 when the half bell mouse 30a shown in FIG. 7 is used.
  • Comparative Example 5 is shown by a broken line
  • Example 1 is shown by a solid line
  • Example 2 is shown by a dashed dotted line.
  • FIG. 26 (a) shows the relationship between fan efficiency Es and air volume
  • FIG. 26 (b) shows the relationship between specific noise Kt and air volume
  • FIG. 26 (c) shows the relationship between static pressure PS and air volume ing.
  • the rotor of Comparative Example 5 has the rotor shape shown in FIG. 4 and FIG. 5, has a stagger angle distribution Lv1 shown by a broken line in FIG.
  • the rotor of Example 1 and the rotor of Example 2 are the rotors shown in FIGS. 4 and 5, and have a stagger angle distribution indicated by a solid line in FIG. 12 and indicated by a solid line in FIG. It has an advancing angle distribution, and has an anteversion angle distribution shown by a solid line in FIG.
  • the order of the function set as the stagger angle distribution in the second area AR2 is 1.2
  • the order of the function set as the advancing angle distribution in the second area AR2 is 1.
  • the order of the function set as the anteversion angle distribution in the second region AR2 is three.
  • the degree of the function set as the stagger angle distribution in the second area AR2 is 2
  • the degree of the function set as the advancing angle distribution in the second area AR2 is 2
  • the order of the function set as the anteversion angle distribution in the two areas AR2 is three.
  • FIG. 27 shows various characteristics of the rotor of Comparative Example 5 described above, the rotor of Example 1 described above, and the rotor of Example 2 described above when the full bell mouse 30b shown in FIG. 8 is used.
  • FIG. Comparative Example 5 is shown by a broken line
  • Example 1 is shown by a solid line
  • Example 2 is shown by a dashed dotted line.
  • 27 (a) shows the relationship between fan efficiency Es and air volume
  • FIG. 27 (b) shows the relationship between specific noise Kt and air volume
  • FIG. 27 (c) shows the relationship between static pressure PS and air volume. ing.
  • the rotors of Example 1 and Example 2 can improve the air blowing characteristic, the noise characteristic, and the fan efficiency characteristic regardless of the form of the bell mouth. is there.
  • FIG. 28 shows various characteristics of the rotor of Comparative Example 5 described above, the rotor of Example 1 described above, and the rotor of Example 3 when the half bell mouse 30a shown in FIG. 7 is used.
  • FIG. Comparative Example 5 is shown by a broken line
  • Example 1 is shown by a solid line
  • Example 3 is shown by an alternate long and short dash line.
  • Fig. 28 (a) shows the relationship between fan efficiency Es and air volume
  • Fig. 28 (b) shows the relationship between specific noise Kt and air volume
  • Fig. 28 (c) shows the relationship between static pressure PS and air volume.
  • the rotor according to the third embodiment like the rotors according to the first and second embodiments, has the shape of the rotor shown in FIGS.
  • the rotor of Example 3 has an order of a function set as a stagger angle distribution in the second area AR2 of 1.2 and an order of a function set as a forward angle distribution in the second area AR2 of 1. At 2, the order of the function set as the anteversion angle distribution in the second region AR2 is four.
  • FIG. 29 shows various characteristics of the rotor of Comparative Example 5 described above, the rotor of Example 1 described above, and the rotor of Example 3 described above when using the full bell mouse 30b shown in FIG.
  • FIG. Comparative Example 5 is shown by a broken line
  • Example 1 is shown by a solid line
  • Example 3 is shown by an alternate long and short dash line.
  • Fig. 29 (a) shows the relationship between fan efficiency Es and air volume
  • Fig. 29 (b) shows the relationship between specific noise Kt and air volume
  • Fig. 29 (c) shows the relationship between static pressure PS and air volume. ing.
  • the rotor of the third embodiment can improve the air blowing characteristics, the noise characteristics, and the fan efficiency characteristics regardless of the form of the bell mouth.
  • FIG. 30 is a view showing specific noise characteristics at the open point of the rotor of Comparative Example 5 described above and the rotor of Example 1 described above when using the half bell mouse 30a illustrated in FIG. 7. .
  • FIG. 30 shows the relationship between the order of the function used as the forward inclination angle distribution in the second area AR2 and the specific noise Kt at the open point. The order is changed from 1.2 to 5 orders.
  • a quadratic function is used as the anteversion angle distribution in the second region AR2.
  • the specific noise Kt is larger than that of Comparative Example 5, but in the region from 2 to 7, the ratio is The noise Kt is improved compared to Comparative Example 5.
  • FIG. 31 is a diagram showing fan efficiency characteristics at the opening point of the rotor of Comparative Example 5 described above and the rotor of Example 1 described above when the half bell mouse 30a shown in FIG. 7 is used. .
  • FIG. 31 shows the relationship between the order of the function used as the forward inclination angle distribution in the second area AR2 and the fan efficiency Et at the open point. The order is changed from 1.2 to 5 orders. As shown in FIG. 31, in the case of the rotor of Example 1, the fan efficiency Et is improved over Comparative Example 5 over all the orders.
  • FIG. 32 is a graph showing the minimum specific noise characteristics of the rotor of Comparative Example 5 described above and the rotor of Example 1 described above when static pressure is applied, when the half bell mouse 30a shown in FIG. 7 is used It is.
  • FIG. 32 shows the relationship between the order of the function used as the anteversion angle distribution in the second region AR2 and the minimum specific noise Ks at the time of static pressure application. The order is changed from 1.2 to 5 orders. As shown in FIG. 32, when the order is 1.2, the specific noise Ks is larger than that of Comparative Example 5, but in the range from 2 to 5, the specific noise Ks is improved compared to Comparative Example 5. ing.
  • FIG. 33 is a graph showing the maximum fan efficiency characteristics of the above-described rotor of Comparative Example 5 and the rotor of Example 1 described above when the half bell mouse 30a shown in FIG. 7 is used.
  • FIG. 33 shows the relationship between the order of the function used as the anteversion angle distribution in the second region AR2 and the maximum fan efficiency Esmax. The order is changed from 1.2 to 5 orders. As shown in FIG. 33, the maximum fan efficiency Esmax is improved over Comparative Example 5 over all the orders.
  • FIG. 34 is a diagram showing specific noise characteristics at the open point of the rotor of Comparative Example 5 described above and the rotor of Example 1 described above when using the full bell mouse 30 b illustrated in FIG. 8. .
  • FIG. 34 shows the relationship between the order of the function used as the forward inclination angle distribution in the second region AR2 and the specific noise Kt at the open point. The order is changed from 1.2 to 5 orders. As shown in FIG. 34, in the case of the rotor of Example 1, the specific noise Kt is improved over that of Comparative Example 5 over all the orders.
  • FIG. 35 is a diagram showing fan efficiency characteristics at the opening point of the rotor of Comparative Example 5 described above and the rotor of Example 1 described above when using the full bell mouse 30 b illustrated in FIG. 8. .
  • FIG. 35 shows the relationship between the order of the function used as the anteversion angle distribution in the second region AR2 and the fan efficiency Et at the open point. The order is changed from 1.2 to 5 orders.
  • the fan efficiency Et is substantially the same as Comparative Example 5.
  • the fan efficiency Et is worse than that of Comparative Example 5 when the order is 5, but the fan efficiency Et is improved compared to Comparative Example 5 in the second to fourth regions. It is done.
  • FIG. 36 is a diagram showing minimum specific noise characteristics of the rotor of Comparative Example 5 described above and the rotor of Example 1 described above when static pressure is applied, when the full bell mouse 30b shown in FIG. 8 is used It is.
  • FIG. 36 shows the relationship between the order of the function used as the anteversion angle distribution in the second region AR2 and the minimum specific noise Ks at the time of static pressure application. The order is changed from 1.2 to 5 orders. As shown in FIG. 36, in the case of the rotor of Example 1, the specific noise Ks is improved over that of Comparative Example 5 over all the orders.
  • FIG. 37 is a graph showing the maximum fan efficiency characteristics of the above-described rotor of Comparative Example 5 and the rotor of Example 1 described above when the full bell mouse 30b shown in FIG. 8 is used.
  • FIG. 37 shows the relationship between the order of the function used as the anteversion angle distribution in the second region AR2 and the maximum fan efficiency Esmax. The order is changed from 1.2 to 5 orders. As shown in FIG. 37, the highest fan efficiency Esmax is improved over the fifth comparative example over the second to fifth orders.
  • the air flow characteristic is It is possible to improve noise characteristics and fan efficiency characteristics.
  • the stagger angle of the rotor has the first stagger angle distribution having a local minimum value in the region from the inner peripheral edge to the first boundary position Re1.
  • a second stagger angular distribution including an n-order function having the radius of the rotor as a variable, which increases toward the outer peripheral edge.
  • the n is a value from 1 to 2 and does not include 1. Therefore, according to the present embodiment, low noise and high efficiency can be achieved while suppressing the height of the outer peripheral portion.
  • the advancing angle [delta] theta of the rotor blades, in the region from the inner peripheral edge to the second boundary position Re2 has a linearly first advancing angle distribution increases, the second boundary position Re2 In the region from to the outer rim, there is a second advancing angle distribution including an m-order function whose radius is variable, which increases as going to the outer rim.
  • the m is a value from 1 to 2 and does not include 1. Therefore, according to the present embodiment, in the outer peripheral portion of the blade, it is possible to increase the strength at the blade root portion while securing the triangular blade shape for noise reduction.
  • the anteversion angle ⁇ z of the rotor blade has a first anteversion angle distribution which is a constant value in a region from the inner peripheral edge to the third boundary position Re3, and is outside the third boundary position Re3. In the region up to the periphery, it has a second anteversion distribution including a p-order function whose radius is variable, which increases as it goes to the outer periphery.
  • the p is a value of 2 to 5. Therefore, according to the present embodiment, the noise can be further reduced.
  • the configuration shown in the above embodiment shows an example of the contents of the present invention, and can be combined with another known technique, and one of the configurations is possible within the scope of the present invention. Parts can be omitted or changed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
PCT/JP2017/036010 2017-10-03 2017-10-03 プロペラファンおよび軸流送風機 WO2019069374A1 (ja)

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CN201780095281.5A CN111133201B (zh) 2017-10-03 2017-10-03 螺旋桨式风扇以及轴流式鼓风机
PCT/JP2017/036010 WO2019069374A1 (ja) 2017-10-03 2017-10-03 プロペラファンおよび軸流送風機
US16/643,647 US20200240430A1 (en) 2017-10-03 2017-10-03 Propeller fan and axial flow blower
JP2019546443A JP6811873B2 (ja) 2017-10-03 2017-10-03 プロペラファンおよび軸流送風機
TW107112572A TWI658215B (zh) 2017-10-03 2018-04-12 螺槳風扇及軸流送風機

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