WO2022070500A1 - プロペラファン - Google Patents
プロペラファン Download PDFInfo
- Publication number
- WO2022070500A1 WO2022070500A1 PCT/JP2021/018644 JP2021018644W WO2022070500A1 WO 2022070500 A1 WO2022070500 A1 WO 2022070500A1 JP 2021018644 W JP2021018644 W JP 2021018644W WO 2022070500 A1 WO2022070500 A1 WO 2022070500A1
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- WO
- WIPO (PCT)
- Prior art keywords
- propeller fan
- wing
- blade
- tip
- rotation
- Prior art date
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- 230000002093 peripheral effect Effects 0.000 claims description 14
- 230000000052 comparative effect Effects 0.000 description 9
- 230000003068 static effect Effects 0.000 description 9
- 238000012986 modification Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 230000007423 decrease Effects 0.000 description 3
- 230000001771 impaired effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229920003002 synthetic resin Polymers 0.000 description 1
- 239000000057 synthetic resin Substances 0.000 description 1
Images
Classifications
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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
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
- F04D29/326—Rotors specially for elastic fluids for axial flow pumps for axial flow fans comprising a rotating shroud
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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
- F04D29/325—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
- 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
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
-
- 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
- F05D2240/301—Cross-sectional characteristics
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- 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
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
- F05D2250/611—Structure; Surface texture corrugated undulated
Definitions
- This disclosure relates to propeller fans.
- Patent Document 1 discloses a propeller fan whose blade design is devised so as to suppress the generation of a blade tip vortex, which is a factor that impairs fan efficiency.
- the wing tip vortex is a vortex flow generated by the backflow of air around the wing tip from the positive pressure surface side to the negative pressure surface side of the wing, and develops as the maximum warp position at the wing tip moves away from the trailing edge of the wing. become longer.
- the maximum warp position ratio is gradually increased from the blade base to the blade tip so that the maximum warp position is not significantly separated from the trailing edge on the blade tip side. It is designed.
- the maximum warp position ratio is the ratio of the distance from the leading edge to the maximum warp position in the blade cross section to the chord length.
- the maximum warp position is the position on the chord where the warp height in the cross section of the wing is maximum.
- the warp height is the distance from the chord to the warp line in the cross section of the wing.
- a propeller fan as in Patent Document 1 is designed so that the maximum warp position ratio of the blade is closer to the trailing edge toward the blade tip. Therefore, the load on the blade surface when the propeller fan is rotated is leveled, and it is not possible to do a large work on the outer peripheral portion where the peripheral speed of the propeller fan is relatively high. That is, in the propeller fan, in order to suppress the development of the tip vortex in each blade, the workload on the tip side is sacrificed and the fan efficiency is impaired.
- the purpose of the present disclosure is to improve the fan efficiency while suppressing the generation of the tip vortex in the propeller fan.
- the first aspect of the present disclosure is a cylindrical hub (12) that rotates about a rotation axis (A), and a plurality of wings (14) that extend outward in the radial direction from the outer peripheral surface of the hub (12). ) And the propeller fan (10).
- each blade tip (20) which is an outer end in the radial direction of the plurality of blades (14), is provided so as to surround the plurality of blades (14).
- the ring (16) is connected.
- Each of the plurality of blades (14) has the maximum distance from the chord (34) to the warp line (36) in the arcuate cross section of the blade (14) centered on the rotation axis (A).
- the position on the warp line (36) is defined as the maximum warp position (X), and the wing (14) is along the rotation axis (A) from the trailing edge (24) which is the rear edge in the rotation direction (D).
- the axial height at the maximum warp position (X) provided inside the blade (14) in the turning radius direction is substantially constant.
- the axial height at the maximum warp position (X) provided on the outer side of the first portion (30) and the blade (14) in the radial direction of rotation increases toward the blade tip (20). It has a second part (32).
- a first portion (30) having a substantially constant axial height at the maximum warp position (X) is provided inside in the radius of gyration direction, and the maximum warp outward in the direction of radius of gyration. Since a second portion (32) is provided in which the axial height at position (X) increases toward the tip (20), the tip (20) side of each blade (14), that is, the propeller fan (10). ) The amount of work on the outer peripheral side is increased, and the fan efficiency can be improved.
- a second aspect of the present disclosure is that in the propeller fan (10) of the first aspect, the first portion (30) is 70 of the portions inside the intermediate position in the radial direction of the blade (14). % Or more of the propeller fan (10), wherein the second portion (32) constitutes 70% or more of the portion outside the intermediate position in the radial direction of the blade (14). Is.
- the first portion (30) constitutes 70% or more of the inner portion, so that the amount of work on the inner side in the radius of gyration is relatively small. ..
- the second portion (32) constitutes 70% or more of the outer portion, the amount of work on the outer side in the radial direction of rotation becomes relatively large.
- a third aspect of the present disclosure is the radius of gyration of the second portion (32) at the maximum warp position (X) in the propeller fan (10) of the first or second aspect with respect to the axial height. It is a propeller fan (10) in which the change width per unit length in the direction increases toward the tip (20).
- the rate of change in the axial height (change width with respect to the unit length) at the maximum warp position (X) of the second portion (32) increases toward the wing tip (20).
- the increase in the amount of work performed by the rotation of the propeller fan (10) increases toward the outside in the radial direction of rotation.
- the chord length (c) of the first portion (30) is substantially constant, and the first aspect is described.
- chord length (c) of the first portion (30) is substantially constant in each wing (14), the amount of work on the inside in the radius of gyration is relatively small.
- chord length (c) of the second part (32) increases toward the wing tip (20), so that the amount of work on the outside in the radial direction of rotation becomes relatively large. ..
- a fifth aspect of the present disclosure is that in the propeller fan (10) of the fourth aspect, the change width per unit length of the chord length (c) of the second part (32) in the radius of gyration is determined. It is a propeller fan (10) that increases toward the tip of the wing (20).
- the rate of change of the chord length (c) of the second portion (32) increases as the (change width with respect to the unit length) increases toward the wing tip (20), so that each wing (14) In the second part (32) of the above, the increase in the amount of work performed by the rotation of the propeller fan (10) increases toward the outside in the radial direction of rotation.
- a sixth aspect of the present disclosure is that in the propeller fan (10) of any one of the first to fifth aspects, the wing (14) has the axial height at the maximum warp position (X). Hf, the inner end of the wing (14) in the radial direction of rotation, where Hl is the axial height at the leading edge (22), which is the leading edge in the direction of rotation (D) of the wing (14). It is a propeller fan (10) that satisfies Hf / Hl ⁇ 0.45 at the wing base (18).
- the wing (14) is designed to satisfy Hf / Hl ⁇ 0.45.
- the ratio (d / c) to the chord length (c) is good for increasing the static pressure efficiency.
- a seventh aspect of the present disclosure is a propeller fan (10) in which serrations (40) are provided on the trailing edge (24) of the wing (14) in any one of the first to sixth aspects. (10).
- the serration (40) is provided on the trailing edge (24) of the wing (14), the wind noise of the wing (14) due to the rotation of the propeller fan (10) can be reduced.
- FIG. 1 is a cross-sectional view taken along the line II-II of FIG.
- FIG. 2 is a perspective view illustrating the propeller fan of the embodiment.
- FIG. 3 is a rear view illustrating the propeller fan of the embodiment.
- FIG. 4 is a cross-sectional view illustrating the cross section of the blade of the propeller fan of the embodiment.
- FIG. 5 is a graph showing the relationship between the radius ratio and the chord length in the propeller fan of the embodiment.
- FIG. 6 is a graph showing the relationship between the radius ratio of the blades and the mounting angle in the propeller fan of the embodiment.
- FIG. 7 is a graph showing the relationship between the radius ratio and the warp ratio of the blades in the propeller fan of the embodiment.
- FIG. 8 is a graph showing the relationship between the radius ratio of the blade and the maximum warp position ratio in the propeller fan of the embodiment.
- FIG. 9 is a graph showing the relationship between the radius ratio of the blade and the maximum warp position height in the propeller fan of the embodiment.
- FIG. 10 is a graph showing the relationship between the axial height ratio of the blade and the static pressure efficiency in the propeller fan.
- FIG. 11 is a graph showing the relationship between the radius ratio and the air volume ratio of the blades in the propeller fan of the embodiment.
- FIG. 12 is a graph showing the relationship between the air volume and the static pressure efficiency in the propeller fan of the embodiment.
- FIG. 13 is a perspective view showing a propeller fan of the first modification.
- FIG. 14 is a perspective view showing a propeller fan of the second modification.
- the propeller fan of this embodiment is used for a blower.
- the blower is provided, for example, in the heat source unit of the air conditioner, and is for supplying outdoor air to the heat source side heat exchanger.
- the blower device includes a bell mouth (1) having an annular cylinder shape as shown in FIG.
- the bell mouth (1) constitutes the air outlet (3) that blows the wind.
- the propeller fan (10) is arranged inside the bell mouth (1) with the ring (16) facing each other.
- the propeller fan (10) is an axial fan made of synthetic resin. As shown in FIGS. 2 and 3, the propeller fan (10) comprises one hub (12), four wings (14), and one ring (16). One hub (12), four wings (14) and one ring (16) are integrally formed.
- the propeller fan (10) is molded, for example, by injection molding.
- the hub (12) is formed in a cylindrical shape. This hub (12) is a rotation shaft portion of the propeller fan (10) and is located at the center of the propeller fan (10). A drive shaft of a fan motor (not shown) is attached to the hub (12). The hub (12) is driven by a fan motor and rotates about a rotation axis (A). The central axis of the hub (12) coincides with the axis of rotation (A) of the propeller fan (10).
- the four wings (14) are arranged at a certain angular distance from each other in the circumferential direction of the hub (12). Each wing (14) extends outward in the radial direction from the outer peripheral surface of the hub (12). The four wings (14) radiate outward from the hub (12) in the radial direction of the propeller fan (10). Adjacent wings (14) do not overlap in front or back view. Each blade (14) is formed in a plate shape that is smoothly curved along the radial direction and the direction of rotation (D). The shapes of the four wings (14) are the same as each other.
- each blade (14) the radial end of the propeller fan (10), that is, the inner end in the radius of gyration, is the blade base (18).
- the wing base (18) and wing tip (20) of each wing (14) extend along the direction of rotation (D) of the propeller fan (10), respectively.
- each wing (14) The wing base (18) of each wing (14) is connected to the hub (12). In each blade (14), the distance Ri from the rotation axis (A) of the propeller fan (10) to the blade base (18) is substantially constant over the entire length of the blade base (18). Also, the tip (20) of each wing (14) is connected to the ring (16). In each blade (14), the distance Ro from the axis of rotation (A) of the propeller fan (10) to the tip (20) is substantially constant over the overall length of the tip (20).
- the length of the wing tip (20) is longer than the length of the wing base (18).
- the front end of the wing tip (20) is located anterior to the front end of the wing base (18).
- the rear end of the wing base (18) is located posterior to the rear end of the wing tip (20).
- each blade (14) is located on the outer peripheral side (outside in the radius of gyration) of the propeller fan (10) from the blade base (18) toward the blade tip (20), respectively. Extend.
- the leading edge (22) of each wing (14) is curved so as to form a concave shape that is recessed toward the rear in the rotation direction (D) of the propeller fan (10).
- the trailing edge (24) of each wing (14) is curved so as to form a concave shape that is recessed toward the front in the rotation direction (D) of the propeller fan (10).
- the portion of the trailing edge (24) of each wing (14) on the wing root (18) side extends along the leading edge (22).
- the portion of the trailing edge (24) of each wing (14) on the wing tip (20) side extends away from the leading edge (22) toward the wing tip (20) side.
- Each wing (14) is tilted so as to intersect a plane orthogonal to the rotation axis (A) of the propeller fan (10).
- the leading edge (22) of each wing (14) is located closer to one end (the end facing upward in FIG. 2) of the hub (12).
- the trailing edge (24) of each wing (14) is located closer to the other end of the hub (12) (the end facing downward in FIG. 2).
- the concave surface (downward surface in FIG. 2) facing the front side in the rotation direction (D) of the propeller fan (10) is the positive pressure surface (26), and the rotation direction of the propeller fan (10) ( The convex surface facing the rear side (upward surface in FIG. 2) in D) is the negative pressure surface (28).
- the ring (16) is provided so as to surround multiple wings (14).
- the ring (16) is formed in an annular shape.
- the inner peripheral surface of the ring (16) is connected to each tip (20) in the four blades (14). That is, the four wings (14) are connected by a ring (16).
- the ring (16) covers the entire wing (14) from the leading edge (22) to the trailing edge (24) in a lateral view of the propeller fan (10).
- Each end of the ring (16) is bent so as to warp toward the outer peripheral side.
- the air pushed out by the propeller fan (10) is provided with a ring (16), so that the tip (20) of each blade (14) is moved from the positive pressure surface (26) side to the negative pressure surface (28) side. It becomes difficult to go around. As a result, the generation of the tip vortex is suppressed.
- the wing cross section shown in FIG. 4 is a plane of a cross section of one wing (14) located at a distance Rn from the rotation axis (A) of the propeller fan (10), that is, an arcuate cross section centered on the rotation axis (A). It was developed in. As shown in FIG. 5, each blade (14) is warped so as to bulge toward the negative pressure surface (28). Each wing (14) has a first portion (30) provided inside in the radius of gyration and a second portion (32) provided outside in the radius of gyration.
- the first part (30) constitutes 70% or more, preferably 80% or more of the part inside the intermediate position in the radial direction of the wing (14).
- the second portion (32) constitutes 70% or more, preferably 80% or more of the portion outside the intermediate position in the radial direction of the blade (14).
- the inner half of each wing (14) is composed of the first portion (30) and the outer half of each wing (14) is composed of the second portion (32). That is, the first part (30) and the second part (32) divide the wing (14) into two at an intermediate position in the radial direction.
- the line segment connecting the leading edge (22) and the trailing edge (24) of the wing (14) is the chord (34).
- the angle formed by the chord (34) with the plane orthogonal to the rotation axis (A) of the propeller fan (10) is the mounting angle ⁇ .
- the length of the chord (34) is the chord length c.
- ⁇ is the central angle of the blade (14) at the position of the distance Rn from the rotation axis (A) of the propeller fan (10) (see FIG. 3), and its unit is radians.
- the line connecting the midpoints of the positive pressure surface (26) and the negative pressure surface (28) is the warp line (36).
- the distance from the chord (34) to the warp line (36) is the warp height.
- the warp height gradually increases from the leading edge (22) to the trailing edge (24) along the chord (34), halfway between the leading edge (22) and the trailing edge (24). It becomes the maximum value at, and gradually decreases as it approaches the trailing edge (24) from the maximum position.
- the maximum value of the warp height is the maximum warp height f.
- the position on the warp line (36) where the warp height is the maximum warp height f is the maximum warp position (X).
- the maximum warp position (X) is continuous from the wing base (18) to the wing tip (20) in the vicinity of the middle of the chord length c over the entire length in the radial direction of the wing (14), as shown by the broken line in FIG. It is set to form the maximum warp position line (L).
- the height from the trailing edge (24) of the wing (14) to the warp line (36) in the direction (Z) toward the rear side along the rotation axis (A) is the axial height. That's right.
- the axial height of the wing (14) at the leading edge (22) is the leading edge height Hl.
- the leading edge height Hl is determined by the mounting angle ⁇ of the wing (14) and the chord length c.
- the axial height at the maximum warp position (X) is the maximum warp position height Hf.
- the maximum warp position height Hf is determined by the mounting angle ⁇ of the wing, the distance d from the trailing edge (24) to the maximum warp position (X), and the warp height f.
- Axial height gradually increases from the leading edge (22) to the trailing edge (24).
- the change width per unit length of the wing (14) in the rotation direction (D) is that of the wing (14). It gets bigger toward the leading edge (22).
- the change width per unit length in the rotation direction (D) of the wing (14) is that of the wing (14). It becomes smaller or constant toward the leading edge (22).
- the chord length c is an arbitrary position with respect to the length (R: Ro-Ri) from the blade base (18) to the blade tip (20) in the radius of gyration. It changes according to the radius ratio, which is the ratio (r / R) of the length (r: Rn-Ri) from the wing base (18) at.
- the radius ratio (r / R) indicates the position of the blade (14) from the blade base (18) in the radial direction of rotation.
- the chord length c is substantially constant in the first portion (30) and gradually increases toward the tip (20) in the second portion (32).
- chord length c being “substantially constant” means that the change width of the chord length c is within ⁇ 10% of the chord length c at the wing base (18).
- the change width of the chord length c in the first portion (30) is preferably a length within ⁇ 5% with respect to the chord length c in the blade base (18).
- the change width per unit length in the radius of gyration of the chord length c of the second portion (32) increases toward the tip (20).
- the chord length c of each wing (14) does not reach its maximum in the middle of the second part (32), but reaches its maximum at the wing tip (20).
- the mounting angle ⁇ changes according to the radius ratio (r / R). Specifically, the mounting angle ⁇ gradually increases toward the tip (20) at the first portion (30) and gradually decreases toward the tip (20) at the second portion (32).
- the degree of increase in the mounting angle ⁇ in the first portion (30) is relatively gradual.
- the degree of decrease in the mounting angle ⁇ in the second portion (32) is steeper than the degree of increase in the mounting angle ⁇ in the first portion (30).
- the mounting angle ⁇ of each blade (14) becomes maximum around the intermediate position in the radius of gyration direction.
- the ratio (f / c) of the maximum warp height f to the chord length c is the warp ratio.
- the warp ratio (f / c) hardly changes depending on the radius ratio (r / R). That is, the warp ratio (f / c) is substantially constant over the entire length of the blade (14) in the radial direction from the blade base (18) to the blade tip (20).
- the warp ratio (f / c) of the first portion (30) and the warp ratio (f / c) of the second portion (32) are about the same over the entire area of each portion.
- the change width of the warp ratio (f / c) is within ⁇ 0.5 with respect to the warp ratio (f / c) at the wing base (18). Means that.
- the change width of the warp ratio (f / c) is preferably within ⁇ 0.2 with respect to the warp ratio (f / c) at the blade base (18).
- the warp ratio (f / c) of each blade (14) is 0.25 or more and 0.45 or less.
- ⁇ Maximum warp position ratio> In the blade cross section shown in FIG. 4, the ratio of the distance from the leading edge (22) of the blade (14) to the maximum warp position (X) to the chord length c is the maximum warp position ratio. As shown in FIG. 8, in each blade (14), the maximum warp position ratio hardly changes depending on the radius ratio (r / R). That is, the maximum warp position ratio is substantially constant over the entire length of the blade (14) in the radial direction from the blade base (18) to the blade tip (20). The maximum warp position ratio of the first portion (30) and the maximum warp position ratio of the second portion (32) are about the same as each other over the entire area of each portion.
- the fact that the maximum warp position ratio is "substantially constant” means that the change width of the maximum warp position ratio is within ⁇ 0.5 with respect to the maximum warp position ratio at the wing base (18). ..
- the range of change in the maximum warp position ratio is preferably within ⁇ 0.2 with respect to the maximum warp position ratio at the wing base (18).
- the maximum warp position ratio of each blade (14) is 0.55 or more and 0.6 or less.
- the maximum warp position height Hf changes according to the radius ratio (r / R). Specifically, the maximum warp position height Hf is substantially constant in the first portion (30) and gradually increases toward the wing tip (20) in the second portion (32).
- the fact that the maximum warp position height is "substantially constant” means that the change width of the maximum warp height position Hf is within ⁇ 10% of the maximum warp position height Hf at the wing base (18). It means that it is.
- the change width of the maximum warp position height Hf in the first portion (30) is preferably a length within ⁇ 5% with respect to the maximum warp position height Hf in the blade base (18).
- the change width per unit length in the radius of gyration direction with respect to the maximum warp position height Hf of the second portion (32) increases toward the tip (20).
- the maximum warp position height Hf of each blade (14) does not reach the maximum in the middle part of the second portion (32), but reaches the maximum at the blade tip (20).
- the ratio (Hf / Hl) of the maximum warp position height Hf to the leading edge height Hl is the axial height ratio.
- the static pressure efficiency in the blower using the propeller fan (10) sharply increases from 0.38 to 0.45 in the axial height ratio (Hf / Hl), and the shaft When the directional height ratio (Hf / Hl) exceeds 0.45, it gradually increases up to 0.75. From this, the axial height ratio (Hf / Hl) of each blade (14) satisfies at least 0.45 or more (Hf / Hl ⁇ 0.45) at the blade base (18).
- each blade (14) has an axial height ratio (Hf / Hl) extending from the blade base (18) to the blade tip (20) over the entire length of the blade (14) in the radial direction of rotation. It is designed to satisfy 0.45 or more (Hf / Hl ⁇ 0.45).
- the air volume ratio to the radius ratio (r / R) of the propeller fan (10) of this example is shown by a solid line
- the air volume ratio to the radius ratio (r / R) of the propeller fan of the comparative example is shown by a broken line.
- the air volume ratio is the ratio of the air volume at an arbitrary position in the radial direction of the fan (10) to the total air volume of the propeller fan (10).
- the static pressure efficiency with respect to the air volume of the blower using the propeller fan (10) of this example is shown by a solid line
- the static pressure efficiency with respect to the air volume of the blower using the propeller fan of the comparative example is shown by a broken line.
- the propeller fan of the comparative example has four wings (14) arranged at regular intervals in the circumferential direction like the propeller fan (10) of this example, and does not have a ring (16).
- the propeller fan of the comparative example has a chord length c shown by a broken line in FIG. 5, a mounting angle ⁇ shown by a broken line in FIG. 6, a warp ratio (f / c) shown by a broken line in FIG. 7, and a broken line shown in FIG. It has a maximum warp position ratio (d / c) and a maximum warp position height Hf shown by a broken line in FIG.
- the propeller fan (10) of this example is different from the propeller fan of the comparative example in the air volume ratio over substantially the entire radial direction.
- the air volume ratio in the portion where the radius ratio (r / R) of the propeller fan (10) of this example is 0.8 or less is such that the radius ratio (r / R) of the propeller fan of the comparative example is 0. It is suppressed to be lower than the air volume ratio in the portion of 8 or less.
- the portion where the radius ratio (r / R) of the propeller fan (10) of this example exceeds 0.8 is larger than the portion where the radius ratio (r / R) of the propeller fan of the comparative example exceeds 0.8. Including the part where the ratio is significantly high.
- the maximum warp position (X) is designed to suppress the development of the tip vortex, so the air volume ratio on the outer peripheral side of the fan drops sharply. Therefore, as shown in FIG. 12, in the propeller fan of the comparative example, the static pressure efficiency is impaired.
- the propeller fan (10) of this example has the effect of increasing the air volume ratio on the outer peripheral side of the fan due to the suitable design of the maximum warp position (X). On the outer peripheral side of the propeller fan (10), the peripheral speed when the blade (14) rotates is high, and the chord length c is relatively long, so that the Reynolds number is high.
- the boundary layer on the surface of the wing (14) becomes thin, and the energy loss due to the dissipation of kinetic energy can be reduced.
- the static pressure efficiency is enhanced.
- a second portion (32) is provided in which the axial height at position (X) increases toward the tip (20), the tip (20) side of each blade (14), that is, the propeller fan (10). ) The amount of work on the outer peripheral side is increased, and the fan efficiency can be improved.
- the first portion (30) constitutes 70% or more of the inner portion, so that the work amount on the inner side in the radial direction of rotation is increased. Is relatively small.
- the second portion (32) constitutes 70% or more of the outer portion, the amount of work on the outer side in the radial direction of rotation becomes relatively large. This is advantageous for increasing the fan efficiency of the propeller fan (10).
- the rate of change in the axial height (change width with respect to the unit length) at the maximum warp position (X) of the second portion (32) is toward the tip (20). Therefore, in the second part (32) of each blade (14), the amount of work performed by the rotation of the propeller fan (10) increases toward the outside in the radial direction of rotation. This is advantageous for increasing the fan efficiency of the propeller fan (10).
- the chord length c of the first portion (30) is substantially constant in each blade (14), the amount of work inside in the radial direction of rotation is relatively small. Become. On the other hand, in each blade (14), the chord length c of the second portion increases toward the blade tip (20), so that the amount of work on the outside in the radial direction of rotation becomes relatively large. This is advantageous for increasing the fan efficiency of the propeller fan (10).
- the rate of change of the chord length c of the second part (32) increases as the (change width with respect to the unit length) increases toward the tip (20), so that each blade In the second part (32) of (14), the increase in the amount of work performed by the rotation of the propeller fan (10) increases toward the outside in the radial direction of rotation. This is advantageous for increasing the fan efficiency of the propeller fan (10).
- the wing (14) is designed to satisfy Hf / Hl ⁇ 0.45. By doing so, the balance between the warp ratio (f / c) and the maximum warp position ratio (d / c) becomes good for increasing the static pressure efficiency.
- the above embodiment may have the following configuration.
- the propeller fan (10) may include five wings (14).
- the number of wings (14) included in the propeller fan (10) may be three or less, or may be six or more. Further, in the propeller fan (10), the adjacent wings (14) may partially overlap each other in front view or rear view.
- serrations (40) may be provided on the trailing edge (24) of each wing (14).
- the serration (40) is a saw blade-shaped portion.
- the serrations (40) are provided, for example, over substantially the entire trailing edge (24) of each wing (14).
- the serration (40) is provided at the trailing edge (24) of each wing (14), so that the serration (40) causes the negative pressure surface (28) of the wing (14). It is possible to suppress the turbulence of the air flowing on the side and reduce the wind noise of the wing (14) due to the rotation of the propeller fan (10). Furthermore, it can be expected to improve the fan efficiency of the propeller fan (10).
- the portion of the wing (14) formed by the first portion (30) may be about 50% of the portion inside the intermediate position in the radial direction of the wing (14), and may be less than 50%. It doesn't matter. Further, the portion of the wing (14) formed by the second portion (32) may be about 50% of the portion outside the intermediate position in the radius of gyration direction of the wing (14), and may be less than 50%. It doesn't matter if there is one.
- this disclosure is useful for propeller fans.
- Rotation axis D Rotation direction X Maximum warp position 10 Propeller fan 12 Hub 14 Wing 16 Ring 20 Wing tip 22 Leading edge 24 Trailing edge 30 1st part 32 2nd part 34 Chord 36 Warp line 40 Serration
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Abstract
Description
以下、例示的な実施形態を図面に基づいて説明する。
プロペラファン(10)は、合成樹脂製の軸流ファンである。図2および図3に示すように、プロペラファン(10)は、1つのハブ(12)と、4つの翼(14)と、1つのリング(16)とを備える。1つのハブ(12)と4つの翼(14)と1つのリング(16)とは、一体に形成される。プロペラファン(10)は、例えば射出成形によって成形される。
図4に示す翼断面は、プロペラファン(10)の回転軸(A)から距離Rnに位置する1つの翼(14)の断面、つまり回転軸(A)を中心とした円弧状の断面を平面に展開したものである。この図5に示すように、各翼(14)は、負圧面(28)側に膨らむように反っている。各翼(14)は、回転半径方向における内側に設けられた第1部分(30)と、回転半径方向における外側に設けられた第2部分(32)とを有する。
図5に示すように、各翼(14)において、翼弦長cは、回転半径方向における翼元(18)から翼端(20)にかけての長さ(R:Ro-Ri)に対する任意の位置での翼元(18)からの長さ(r:Rn-Ri)の比(r/R)である半径比に応じて変化する。半径比(r/R)は、翼(14)の回転半径方向における翼元(18)からの位置を示す。具体的には、翼弦長cは、第1部分(30)で略一定であり、第2部分(32)で翼端(20)に向かって次第に増大する。ここで、翼弦長cが「略一定」であるとは、翼弦長cの変化幅が翼元(18)での翼弦長cに対して±10%以内の長さであることを意味する。第1部分(30)での翼弦長cの変化幅は、翼元(18)での翼弦長cに対して±5%以内の長さであることが好ましい。第2部分(32)の翼弦長cについての回転半径方向における単位長さ当たりの変化幅は、翼端(20)に向かうほど大きくなる。各翼(14)の翼弦長cは、第2部分(32)の中途部では極大とならず、翼端(20)で最大となる。
図6に示すように、各翼(14)において、取付け角αは、半径比(r/R)に応じて変化する。具体的には、取付け角αは、第1部分(30)で翼端(20)に向かって次第に増大し、第2部分(32)で翼端(20)に向かって次第に減少する。第1部分(30)での取付け角αの増大具合は、比較的緩やかである。第2部分(32)での取付け角αの減少具合は、第1部分(30)での取付け角αの増大具合よりも急である。各翼(14)の取付け角αは、回転半径方向における中間位置辺りで極大となる。
図4に示す翼断面において、翼弦長cに対する最大反り高さfの比(f/c)は、反り比である。図7に示すように、各翼(14)において、反り比(f/c)は、半径比(r/R)に応じてほとんど変化しない。すなわち、反り比(f/c)は、翼元(18)から翼端(20)に至るまで翼(14)の回転半径方向における全長に亘って略一定である。第1部分(30)の反り比(f/c)と第2部分(32)の反り比(f/c)とは、各部分の全域に亘って互いに同じ程度である。ここで、反り比が「略一定」であるとは、反り比(f/c)の変化幅が翼元(18)での反り比(f/c)に対して±0.5以内であることを意味する。反り比(f/c)の変化幅は、翼元(18)での反り比(f/c)に対して±0.2以内であることが好ましい。本例において、各翼(14)の反り比(f/c)は、0.25以上且つ0.45以下である。
図4に示す翼断面において、翼(14)の前縁(22)から最大反り位置(X)までの距離の翼弦長cに対する比は、最大反り位置比である。図8に示すように、各翼(14)において、最大反り位置比は、半径比(r/R)に応じてほとんど変化しない。すなわち、最大反り位置比は、翼元(18)から翼端(20)に至るまで翼(14)の回転半径方向における全長に亘って略一定である。第1部分(30)の最大反り位置比と第2部分(32)の最大反り位置比とは、各部分の全域に亘って互いに同じ程度である。ここで、最大反り位置比が「略一定」であるとは、最大反り位置比の変化幅が翼元(18)での最大反り位置比に対して±0.5以内であることを意味する。最大反り位置比の変化幅は、翼元(18)での最大反り位置比に対して±0.2以内であることが好ましい。本例において、各翼(14)の最大反り位置比は、0.55以上且つ0.6以下である。
図9に示すように、各翼(14)において、最大反り位置高さHfは、半径比(r/R)に応じて変化する。具体的には、最大反り位置高さHfは、第1部分(30)で略一定であり、第2部分(32)で翼端(20)に向かって次第に増大する。ここで、最大反り位置高さが「略一定」であるとは、最大反り高さ位置Hfの変化幅が翼元(18)での最大反り位置高さHfに対して±10%以内の高さであることを意味する。第1部分(30)での最大反り位置高さHfの変化幅は、翼元(18)での最大反り位置高さHfに対して±5%以内の長さであることが好ましい。第2部分(32)の最大反り位置高さHfについての回転半径方向における単位長さ当たりの変化幅は、翼端(20)に向かうほど大きくなる。各翼(14)の最大反り位置高さHfは、第2部分(32)の中途部では極大とならず、翼端(20)で最大となる。
図11では、本例のプロペラファン(10)の半径比(r/R)に対する風量比を実線で示し、比較例のプロペラファンの半径比(r/R)に対する風量比を破線で示す。風量比は、プロペラファン(10)のトータル風量に対するファン(10)の径方向における任意の位置での風量の比である。図12では、本例のプロペラファン(10)を用いた送風装置の風量に対する静圧効率を実線で示し、比較例のプロペラファンを用いた送風装置の風量に対する静圧効率を破線で示す。
この実施形態のプロペラファン(10)によると、複数の翼(14)の各翼端(20)にリング(16)が接続されているので、空気が翼(14)の正圧面(26)側から負圧面(28)側に翼端(20)を回り込み難くなり、翼端渦の発生を抑制できる。そして、各翼(14)において、回転半径方向における内側に最大反り位置(X)での軸方向高さが略一定である第1部分(30)が設けられ、回転半径方向における外側に最大反り位置(X)での軸方向高さが翼端(20)に向かって増大する第2部分(32)が設けられるので、各翼(14)の翼端(20)側、つまりプロペラファン(10)の外周側での仕事量が増大し、ファン効率を高めることができる。
上記実施形態については、以下のような構成としてもよい。
図13に示すように、プロペラファン(10)は、5つの翼(14)を備えてもよい。プロペラファン(10)が備える翼(14)は、3つ以下であってもよく、6つ以上であってもよい。また、プロペラファン(10)において、隣り合う翼(14)同士は、正面視または背面視で部分的に重なり合っていてもよい。
図14に示すように、プロペラファン(10)において、各翼(14)の後縁(24)にはセレーション(40)が設けられてもよい。セレーション(40)は、鋸刃状に形成された部分である。セレーション(40)は、例えば各翼(14)の後縁(24)の略全体に亘って設けられる。
翼(14)において第1部分(30)が構成する部分は、翼(14)の回転半径方向における中間位置よりも内側の部分のうち50%程度であってもよく、50%未満であっても構わない。また、翼(14)において第2部分(32)が構成する部分は、翼(14)の回転半径方向における中間位置よりも外側の部分のうち50%程度であってもよく、50%未満であっても構わない。
D 回転方向
X 最大反り位置
10 プロペラファン
12 ハブ
14 翼
16 リング
20 翼端
22 前縁
24 後縁
30 第1部分
32 第2部分
34 翼弦
36 反り線
40 セレーション
Claims (7)
- 回転軸(A)を中心に回転するハブ(12)と、該ハブ(12)の外周面から回転半径方向の外方へ延びる複数の翼(14)とを備えるプロペラファンであって、
前記複数の翼(14)の回転半径方向における外側の端である各翼端(20)には、前記複数の翼(14)を囲むように設けられたリング(16)が接続され、
前記複数の翼(14)のそれぞれは、
当該翼(14)の前記回転軸(A)を中心とした円弧状の断面における翼弦(34)から反り線(36)までの距離が最大となる反り線(36)上の位置を最大反り位置(X)とし、当該翼(14)の回転方向(D)における後側の縁である後縁(24)から前記回転軸(A)に沿う方向における反り線(36)までの高さを軸方向高さとしたとき、
当該翼(14)の回転半径方向における内側に設けられた、前記最大反り位置(X)での前記軸方向高さが略一定である第1部分(30)と、当該翼(14)の回転半径方向における外側に設けられた、前記最大反り位置(X)での前記軸方向高さが前記翼端(20)に向かって増大する第2部分(32)とを有する
ことを特徴とするプロペラファン。 - 請求項1に記載されたプロペラファンにおいて、
前記第1部分(30)は、前記翼(14)の回転半径方向における中間位置よりも内側の部分のうち70%以上の部分を構成し、
前記第2部分(32)は、前記翼(14)の回転半径方向における中間位置よりも外側の部分のうち70%以上の部分を構成する
ことを特徴とするプロペラファン。 - 請求項1または2に記載されたプロペラファンにおいて、
前記第2部分(32)の前記最大反り位置(X)での前記軸方向高さについての回転半径方向における単位長さ当たりの変化幅は、前記翼端(20)に向かうほど大きくなる
ことを特徴とするプロペラファン。 - 請求項1~3のいずれか1項に記載されたプロペラファンにおいて、
前記第1部分(30)の翼弦長(c)は、略一定であり、
前記第2部分(32)の翼弦長(c)は、前記翼端(20)に向かって増大する
ことを特徴とするプロペラファン。 - 請求項4に記載されたプロペラファンにおいて、
前記第2部分(32)の翼弦長(c)についての回転半径方向における単位長さ当たりの変化幅は、前記翼端(20)に向かうほど大きくなる
ことを特徴とするプロペラファン。 - 請求項1~5のいずれか1項に記載されたプロペラファンにおいて、
前記翼(14)は、前記最大反り位置(X)での前記軸方向高さをHf、当該翼(14)の回転方向(D)における前側の縁である前縁(22)での前記軸方向高さをHlとしたとき、当該翼(14)の回転半径方向における内側の端である翼元(18)で、
Hf/Hl≧0.45を満たす
ことを特徴とするプロペラファン。 - 請求項1~6のいずれか1項に記載されたプロペラファンにおいて、
前記翼(14)の後縁(24)には、セレーション(40)が設けられる
ことを特徴とするプロペラファン。
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EP21874807.7A EP4212737A4 (en) | 2020-09-29 | 2021-05-17 | PROPELLER FAN |
CN202180066448.1A CN116249838B (zh) | 2020-09-29 | 2021-05-17 | 螺旋桨式风扇 |
BR112023005289-0A BR112023005289B1 (pt) | 2020-09-29 | 2021-05-17 | Ventilador de hélice |
US18/125,573 US12012969B2 (en) | 2020-09-29 | 2023-03-23 | Propeller fan |
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JP2020163792A JP6930644B1 (ja) | 2020-09-29 | 2020-09-29 | プロペラファン |
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DE69934489T2 (de) * | 1999-09-07 | 2007-04-26 | Lg Electronics Inc. | Axiallüfter für Klimaanlage |
EP1801422B1 (de) * | 2005-12-22 | 2013-06-12 | Ziehl-Abegg AG | Ventilator und Ventilatorflügel |
FR2953571B1 (fr) * | 2009-12-07 | 2018-07-13 | Valeo Systemes Thermiques | Helice de ventilateur, en particulier pour vehicule automobile |
US11333165B2 (en) | 2016-12-28 | 2022-05-17 | Daikin Industries, Ltd. | Propeller fan |
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WO2018229081A1 (fr) * | 2017-06-12 | 2018-12-20 | Valeo Systemes Thermiques | Ventilateur de vehicule automobile |
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