WO2019111973A1 - プロペラファン - Google Patents
プロペラファン Download PDFInfo
- Publication number
- WO2019111973A1 WO2019111973A1 PCT/JP2018/044795 JP2018044795W WO2019111973A1 WO 2019111973 A1 WO2019111973 A1 WO 2019111973A1 JP 2018044795 W JP2018044795 W JP 2018044795W WO 2019111973 A1 WO2019111973 A1 WO 2019111973A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- wing
- propeller fan
- wing element
- hub
- rotation
- Prior art date
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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
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
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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
- F04D29/329—Details of the hub
-
- 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
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
-
- 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
- F04D29/26—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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
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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
- F05D2240/303—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
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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
- 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
- F05D2240/305—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 pressure side 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
- F05D2240/306—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 suction side of a rotor blade
Definitions
- the present invention relates to a propeller fan.
- the outdoor unit of the air conditioner has a propeller fan inside.
- the wind velocity at the outer periphery of the blade is high, and the wind velocity decreases toward the center of rotation.
- the air flow of a propeller fan has been increased, and the diameter of the propeller fan has been increased and the speed has been increased.
- the above-mentioned prior art has the following problems. That is, the wind velocity distribution in the radial direction becomes uneven, and a surging phenomenon such as suction of air from the downstream side occurs in the inner circumferential portion of the wing, resulting in an abnormal operation state.
- a surging phenomenon such as suction of air from the downstream side occurs in the inner circumferential portion of the wing, resulting in an abnormal operation state.
- the inner peripheral portion where the wind speed is slow does not contribute to the air flow, the air flow amount obtained with respect to the size is small, the air flow is easily disturbed, and the blade surface can not be used effectively.
- the present invention has been made in view of the above problems, and an object of the present invention is to provide a propeller fan capable of increasing the air flow rate of a propeller fan while suppressing the occurrence of a surging phenomenon.
- a propeller fan disclosed in the present application includes, for example, a hub having a side surface around a central axis, and a plurality of wings provided on the side surface.
- the wing includes an inner peripheral portion located on the base side and an outer peripheral portion located on the outer peripheral side in a portion from a base connected to the hub and extending from the outer peripheral portion to the inner peripheral portion. It has multiple wing elements branched on the way.
- the plurality of blade elements have a trailing edge on the downstream side of rotation about the central axis and a leading edge on the upstream side of the rotation, and the respective pitch angles with respect to the central axis Holes that are connected to the side surfaces and serve as air flow paths are formed between the adjacent wing elements.
- the plurality of blade elements are adjacent to the first blade element on the upstream side of the rotation branched at a branch point on the way from the outer peripheral portion to the inner peripheral portion and the downstream side of the rotation of the first blade element. And an extending portion which is a part of the first wing element at the trailing edge of the first wing element from the branch point to the side surface. At least a portion of the front edge portion of the second blade element overlaps a rotational path around the central axis of the extension portion as a rotation center.
- the present invention for example, it is possible to increase the air volume of the propeller fan while suppressing the occurrence of the surging phenomenon.
- FIG. 1 is a schematic view showing an outdoor unit having a propeller fan according to a first embodiment.
- FIG. 2 is a schematic plan view of the propeller fan according to the first embodiment as viewed from the pressure side.
- FIG. 3 is a plan view of one of the propeller fan blades according to the first embodiment as viewed from the pressure side.
- FIG. 4 is a schematic plan view of the propeller fan according to the first embodiment as viewed from the suction side.
- FIG. 5 is a plan view of one of the propeller fan blades according to the first embodiment as viewed from the suction side.
- FIG. 6 is a perspective view of the propeller fan according to the first embodiment.
- FIG. 7 is a side view of the propeller fan according to the first embodiment.
- FIG. 1 is a schematic view showing an outdoor unit having a propeller fan according to a first embodiment.
- FIG. 2 is a schematic plan view of the propeller fan according to the first embodiment as viewed from the pressure side.
- FIG. 3 is
- FIG. 8 is a side view showing one of the propeller fan blades according to the first embodiment.
- FIG. 9 is a cross-sectional view schematically illustrating an II cross section of the propeller fan according to the first embodiment.
- FIG. 10 is a cross-sectional view for comparing the propeller fan according to the comparative example with the propeller fan according to the first embodiment in the I-I cross section.
- FIG. 11 is an air volume-input (input power) curve diagram.
- FIG. 12 is an air volume-rotational speed curve diagram.
- FIG. 13 is an air volume-static pressure curve diagram.
- FIG. 14 is a side view showing one of the propeller fan blades according to the second embodiment.
- FIG. 1 is a schematic view showing an outdoor unit having a propeller fan according to a first embodiment.
- the outdoor unit 1 of the first embodiment is an outdoor unit of an air conditioner.
- the outdoor unit 1 has a housing 6, and a compressor 3 for compressing a refrigerant and a propeller fan connected to the compressor 3 in the housing 6 for blowing the heat to the heat exchanger 4 and the heat exchanger 4 in which the refrigerant flows. 5 accommodates.
- the housing 6 has an inlet 7 for taking in the outside air, and an outlet 8 for discharging the air in the housing 6.
- the suction port 7 is provided on the side surface 6 a and the back surface 6 c of the housing 6.
- the outlet 8 is provided on the front surface 6 b of the housing 6.
- the heat exchanger 4 is disposed across the back surface 6 c opposite to the front surface 6 b of the housing 6 from the side surface 6 a.
- the propeller fan 5 is disposed to face the outlet 8 and is rotationally driven by a fan motor (not shown).
- the direction of the wind discharged from the outlet 8 by rotation of the propeller fan 5 is referred to as the positive pressure side, and the direction of the wind opposite thereto is referred to as the negative pressure side.
- FIG. 2 is a schematic plan view of the propeller fan according to the first embodiment as viewed from the pressure side.
- FIG. 3 is a plan view of one of the propeller fan blades according to the first embodiment as viewed from the pressure side.
- FIG. 4 is a schematic plan view of the propeller fan according to the first embodiment as viewed from the suction side.
- FIG. 5 is a plan view of one of the propeller fan blades according to the first embodiment as viewed from the suction side.
- FIG. 6 is a perspective view of the propeller fan according to the first embodiment.
- FIG. 7 is a side view of the propeller fan according to the first embodiment.
- FIG. 8 is a side view showing one of the propeller fan blades according to the first embodiment.
- the propeller fan 5 includes a hub 11 formed in a cylindrical shape (or a polygonal column) in appearance and a hub 11 provided around a central axis of the hub 11.
- a plurality of wings 12 are provided on the side surface 11a (see FIGS. 6 and 7), and the hub 11 and the plurality of wings 12 are integrally molded using, for example, a resin material as a molding material.
- the wing 12 has a front edge 12-2 which is the front in the rotational direction of the wing 12 and a rear edge 12-1 which is the rear in the rotational direction of the wing 12.
- the front edge 12-2 is curved and formed so as to be concave toward the rear edge 12-1 located on the opposite side of the front edge 12-2. Wings are also called wings.
- the hub 11 is a boss (not shown) in which the shaft (not shown) of the fan motor is fitted at the position of the central axis O of the hub 11 at the end of the suction side (see FIGS. 4 and 7) of the propeller fan 5. Is provided.
- the hub 11 rotates about the central axis O of the hub 11 as the fan motor rotates in the direction of “R” shown in FIGS. 2, 4 and 6-8.
- the propeller fan 5 has an inner periphery 12 a of the wing 12 located within a circle of radius r 1 of the central axis O and a circle of radius r 1 of the central axis O It has an outer peripheral portion 12b of the wing 12 located outside and within the circumference of a circle of radius R1 of the central axis O.
- the wing area of the radially outer peripheral portion 12 b of the hub 11 is wider than the inner peripheral portion 12 a connected to the hub 11.
- the propeller fan 5 has wing elements 12-11, 12-12 and 12-13 on the inner peripheral portion 12 a of each of the blades 12.
- the wing element 12-11 is an example of a first wing element
- the wing element 12-12 is an example of a second wing element.
- the wing area of wing elements 12-11, 12-12, 12-13 can be changed in design suitably, the wing area of wing element 12-11 is wing element 12-12, 12-13. It may be the largest compared to the wing area of
- the propeller fan 5 has a hole 12-21 between the wing elements 12-11 and 12-12 of the inner peripheral portion 12 a of each wing 12
- a hole 12-22 is provided between 12-12 and 12-13.
- the hole 12-21 is provided in contact with the boundary between the inner circumferential portion 12a and the outer circumferential portion 12b (the position of the radius r1 from the central axis O).
- the holes 12-21 and 12-22 are air flow channels.
- each wing 12 is connected to the hub 11 so that the base 12-11a of the wing element 12-11 and the base 12-12a of the wing element 12-12 form a hole 12-21 in the inner circumferential portion 12a. It is done. Further, each wing 12 is connected to the hub 11 so that the base 12-12a of the wing element 12-12 and the base 12-13a of the wing element 12-13 form a hole 12-22 in the inner circumferential portion 12a. It is done.
- the outer peripheral portion 12b is continuous with the wing elements 12-11, 12-12, 12-13, and the inner peripheral portion 12a and the outer peripheral portion 12b form a single wing surface.
- the three wing elements 12-11, 12-12 and 12-13 branch on the way from the outer peripheral portion 12 b of the wing 12 to the inner peripheral portion 12 a.
- the holes 12-21 between the wing elements 12-1 and 12-12 and the holes 12-22 between the wing elements 12-12 and 12-13 are flow paths of the air flow passing through the propeller fan 5, respectively. .
- the wing element 12-11 of the wing 12 is connected to the hub 11 with the base 12-11a as a connecting portion.
- the wing element 12-12 of the wing 12 is connected to the hub 11 with the base 12-12a as a connection portion.
- the wing element 12-13 of the wing 12 is connected to the hub 11 with the base 12-13a as a connection portion.
- the wing 12 is a wing element in which a wing element 12-12 located on the upstream side (front edge side) in the rotational direction (“R” direction in the figure) with respect to the hub 11 is located on the downstream side (rear edge side) It is connected to the positive pressure side than 12-11.
- the hole 12-21 of the wing 12 is located between the wing element 12-12 and the wing element 12-11 with respect to the central axis O direction and the circumferential direction.
- the wing 12 is a wing element having a wing element 12-13 located on the upstream side (front edge side) in the rotational direction (the “R” direction in the figure) with respect to the hub 11 located on the downstream side (rear edge side). It is connected to the positive pressure side than 12-12.
- the hole 12-22 of the wing 12 is located between the wing element 12-13 and the wing element 12-12 with respect to the central axis O direction and the circumferential direction.
- the number of blade elements 12-11, 12-12 and 12-13 and holes 12-21 and 12-22 included in the wing 12 in the first embodiment is not limited to those illustrated in FIGS. 2 to 8, One hole may be provided for two blade elements, or four or more blade elements may have (number of blade elements minus 1) holes.
- the wing element 12-11 has a leading edge 12-11-2 on the upstream side (leading edge side) in the rotational direction (the “R” direction in the figure), and the rotational direction A trailing edge 12-11-1 is provided on the downstream side (rear edge side) of the “R” direction in the drawing.
- the wing element 12-12 has a front edge 12-12-2 on the upstream side (leading edge side) in the rotational direction (the "R” direction in the figure), and in the rotational direction (the "R” direction in the figure)
- a trailing edge 12-12-1 is provided on the downstream side (rear edge side).
- the wing element 12-13 has a leading edge 12-13-2 on the upstream side (leading edge side) in the rotational direction ("R" direction in the figure), and in the rotational direction ("R” direction in the figure)
- a trailing edge 12-13-1 is provided on the downstream side (rear edge side).
- the wing element 12-11 has a base portion 12-11 A and an extension portion 12-11 B divided by a boundary C 1.
- the boundary C1 has a positional relationship substantially parallel to the front edge 12-12-2 of the wing element 12-12. Further, as shown in FIGS. 7 and 8, the boundary C1 is a branch of wing element 12-11 and wing element 12-12, one end of which branches off on the way from the outer peripheral portion 12b of the wing 12 to the inner peripheral portion 12a. The other end corresponds to the pressure-side end of the base 12-13a.
- the extended part 12-11B is the base of the wing element 12-11 to the hole 12-21 side which exists between the wing element 12-11 and the wing element 12-12. It is a portion further extending from the portion 12-11A to the downstream side of the air flow.
- the extending portion 12-11B has a triangular shape or a convex shape with the boundary C1 as a base and the both ends of the boundary C1 as vertices of the base angle.
- the extending portion 12-11B has a triangular shape or a convex shape. From this, a part of the hole 12-21 is shielded against the air flow along the wing element 12-11 near the branch point 12p of the wing element 12-11 and the wing element 12-12, and the hole The remaining unshielded portion 12-21 is exposed to the air flow along the wing element 12-11 near the side face 11 a of the hub 11.
- the extension portion 12-11B has a portion in which the vicinity of the branch point 12p of the wing element 12-11 and the wing element 12-12 overlaps the wing element 12-12 in the rotational direction (the “R” direction in the figure).
- the vicinity of the base 12-11a of the wing element 12-11 has a portion which does not overlap with the wing element 12-12 in the rotational direction (the “R” direction in the drawing).
- the wing element 12-11 is an extension 12-11B that overlaps the wing element 12-12 in the rotational direction (the "R” direction in the figure) at least near the branch point 12p of the wing element 12-11 and the wing element 12-12. Have.
- the extending portion 12-11B starts from one end of the boundary C1 in the vicinity of the branch point 12p of the wing element 12-11 and the wing element 12-12 as a starting point, and its height gradually increases toward the pressure side of the hub 11 with respect to the boundary C1.
- the height increases to the point where the pressure is highest on the pressure side of the hub 11 with respect to the boundary C1
- the height decreases on the pressure side of the hub 11 with respect to the boundary C1 and reaches the other end on the boundary C1. It is a shape.
- the extension portion 12-11B has a shape in which the height gradually increases toward the pressure side of the hub 11 with respect to the boundary C1 in the vicinity of the branch point 12p of the wing element 12-11 and the wing element 12-12.
- the extension portion 12-11B is a hole 12 that passes the air flow along the wing surface of the wing element 12-11 and the wing element 12-12 at the branch point 12p of the wing element 12-11 and the wing element 12-12. It has a part shaped to escape to -21. Therefore, the outer end of the extension portion 12-11B is located at the branch point 12p, so that the air conditioner is operated at high load or at high rotation, from the hole portion 12-21 to the wing element 12-12.
- the extension portion 12-11B branches at least the wing element 12-11 and the wing element 12-12. Even if it overlaps only with the wing element 12-12 in the rotational direction ("R" direction in the figure) near the portion, the wind speed of the inner peripheral portion is increased by increasing the number of blades on the inner peripheral side. Thus, it is possible to suppress the occurrence of an abnormal operating condition such as air flow disturbance or surging phenomenon caused by the difference in the wind velocity of the inner circumferential portion, and to increase the air volume. This becomes more pronounced when the wing element 12-12 has the same extension as the extension 12-11B.
- FIG. 9 is a cross-sectional view schematically illustrating an II cross section of the propeller fan according to the first embodiment.
- the II cross section is a cross section when the blade 12 of the propeller fan 5 is cut along the cutting line II in the plan view of the propeller fan 5 of FIG. 2 and viewed from the outer peripheral portion 12 b side .
- the wing 12 has wing elements 12-11, 12-12, 12-13.
- the wing elements 12-11, 12-12, 12-13 are arranged in the order of the wing elements 12-11, 12-12, 12-13 from the upstream side (leading edge side) in the rotational direction (the "R" direction in the figure). And partially overlap when viewed in the rotational direction ("R" direction in the figure).
- the wing 12 rotates in the direction of rotation with the leading edge 12-12-2 of the wing element 12-12 on the trailing edge 12-11-1 side of the wing element 12-11. It has an extending portion 12-11B which partially overlaps when viewed in the “R” direction in the drawing.
- the extension 12-11B partially overlaps with the front edge 12-12-2 of the wing element 12-12 in the rotational direction (the “R” direction in the figure)
- the axial direction of the hub 11 is
- the highest height in the positive pressure direction from the boundary C1 is H1.
- the pitch angles ⁇ , ⁇ and ⁇ of the wing elements 12-11, 12-12 and 12-13 with respect to the central axis O of the hub 11 can be changed as appropriate, but the pitch angle ⁇ of the wing element 12-11 is , And may be maximum as compared to the pitch angles ⁇ and ⁇ of the wing elements 12-12 and 12-13.
- the wing elements 12-11, 12-12 and 12-13 do not overlap in the central axis O direction on the side surface 11 a of the hub 11.
- the wing elements 12-11, 12-12 and 12-13 are connected to the side surface 11 a of the hub 11 at the side surface 11 a of the hub 11 so as not to overlap each other in the central axis O direction.
- the wing elements 12-11, 12-12 and 12-13 may overlap in the central axis O direction of the hub 11. That is, the wing elements 12-11, 12-12 and 12-13 are arranged on the side surface 11 a of the hub 11 so that the bases 12-11 a, 12-12 a and 12-13 a are aligned substantially in a straight line on the side surface 11 a of the hub 11 It may be connected.
- the extended portion 12-11B partially overlaps the wing element 12-12 in the rotational direction (the “R” direction in the figure).
- a part of the front edge 12-12-2 of the wing element 12-12 overlaps the rotational orbit around the hub 11 of the extension 12-11B. That is, the leading edge portion of the wing element 12-12 along the air flow A2 in which the extending portion 12-11B flows from the upstream side to the downstream side in the rotation direction (the “R” direction in the drawing) as the wing 12 rotates. Overlap with part of 12-12-2.
- the airflows A1 and A2 flowing from the upstream side to the downstream side in the rotational direction (the “R” direction in the drawing) along with the rotation of the wing 12 are both of the wing surfaces of the wing elements 12-11 and 12-12. It flows along the wing surface from the upstream side to the downstream side. That is, the air flow A2 flowing along the wing surface of the wing element 12-11 continues to flow into the wing element 12-without flowing into the hole 12-21 existing between the wing element 12-11 and the wing element 12-12. There is no loss of air volume because it flows along the 12 wing surfaces.
- the wing elements 12-12 and 12-13 are arranged so as to overlap with the rotational orbit around the hub 11 of the wing elements 12-11 and 12-12.
- the wing elements 12-12 and 12-13 are arranged so as to overlap the rotational orbit about the hub 11 of the wing elements 12-11 and 12-12 as a center of rotation, so that the wing surface of the wing 12 12 An air stream flowing along the position can be affected by the next row of wing elements 12-12, 12-13.
- FIG. 10 is a cross-sectional view for comparing the propeller fan according to the comparative example with the propeller fan according to the first embodiment in the I-I cross section.
- FIG. 10 is a cross-sectional view of a propeller fan blade 12Z according to a comparative example as viewed along the same II cross section (not shown) as the I-I cross section of the propeller fan 5 according to the first embodiment in FIG. Show vision.
- the wing 12Z has wing elements 12Z-11, 12Z-12, 12Z-13.
- the wing elements 12Z-11, 12Z-12, and 12Z-13 are arranged in the order of the wing elements 12Z-11, 12Z-12, and 12Z-13 from the upstream side (leading edge side) in the rotational direction (the "R" direction in the figure). And do not overlap when viewed in the rotational direction ("R" direction in the figure).
- the wing 12Z rotates in the rotational direction with the leading edge 12Z-12-2 of the wing element 12Z-12 on the side of the trailing edge 12Z-11-1 of the wing element 12Z-11. There is no part that partially overlaps (in the "R" direction in the figure).
- the distance between the trailing edge 12Z-11-1 of the wing element 12Z-11 and the leading edge 12Z-12-2 of the wing element 12Z-12 is H01 at the widest portion in the axial direction of the hub 11.
- the air flow A01 flowing from the upstream side to the downstream side in the rotation direction (the “R” direction in the drawing) with the rotation of the wing 12Z is the wing element 12Z-11, Since the air flow A02 is sandwiched between 12Z-12, the air flows along the downstream wing surface of the wing element 12Z-11, 12Z-12.
- the air flow A02 flowing from the upstream side to the downstream side in the rotational direction (the “R” direction in the drawing) along with the rotation of the wing 12Z is directly along the wing surface of the wing elements 12Z-11, 12Z-12, After along the wing surface on the downstream side of wing element 12Z-11, not along the wing surface of wing element 12Z-12, to hole 12Z-21 existing between wing element 12Z-11 and wing element 12Z-12 Flow into. Therefore, the air flow A02 flowing into the hole 12Z-21 existing between the wing element 12Z-11 and the wing element 12Z-12 is a loss of air volume as compared with the first embodiment.
- FIG. 11 is an air volume-input (input power) curve diagram.
- FIG. 12 is an air volume-rotational speed curve diagram.
- FIG. 13 is an air volume-static pressure curve diagram.
- FIG. 11 and FIG. 12 show the preconditions in comparing the static pressure of the propeller fan of the first embodiment and the propeller fan of the comparative example.
- FIG. 11 shows that the input (input power) is W1 [W] when the air volume of the propeller fan is Q01 [m 3 / h] and the input (input power) when the air volume of the propeller fan is Q 02 [m 3 / h] Indicates that W2 [W].
- Fig. 12 shows that the rotational speed is RF1 [W] when the air volume of the propeller fan is Q01 [m 3 / h] and the rotational speed is RF 2 [W] when the air volume of the propeller fan is Q 02 [m 3 / h] Indicates that there is. That is, Example 1 and a comparative example show that an input (input electric power) and rotation speed are the same, if the air volume is the same.
- the static pressure is P1 [Pa] when the air volume of the propeller fan is Q01 [m 3 / h], whereas in the first embodiment, the air volume of the propeller fan is When Q is Q01 [m 3 / h], the static pressure is higher than P1 [Pa], and the static pressure is higher than P1.
- the static pressure is P2 [Pa] when the air volume of the propeller fan is Q02 [m 3 / h], whereas in the first embodiment, the airflow of the propeller fan is Q 02 [m 3 / h] In this case, the static pressure is higher than P2 [Pa], and the static pressure is higher than P2.
- the air volume of the propeller fan 5 according to the conventional example is Q01 [m 3 / h]
- the propeller fan according to the first embodiment is Q11 [m 3 / h].
- the air volume is increasing from Q01 [m 3 / h] to Q11 [m 3 / h].
- the air volume of the propeller fan 5 according to the conventional example is Q02 [m 3 / h]
- the propeller fan according to the first embodiment is Q12 [m 3 / h]
- the air volume is increasing from Q02 [m 3 / h] to Q 12 [m 3 / h].
- the same air volume as that of the conventional example can be secured. That is, according to Example 1, it can be said from FIG. 13 that the air volume of the propeller fan 5 can be increased.
- the wing 12 is shaped to branch to the wing elements 12-11, 12-12 and 12-13 as it extends from the outer peripheral portion 12 b to the inner peripheral portion 12 a.
- the wing elements 12-11, 12-12, 12-13 are connected in a row around the hub 11 with their respective bases 12-11a, 12-12a, 12-13a.
- the wing element 12-11 has a triangular or convex extension near the branch point 12p of the wing element 12-11, 12-12 on the side of the trailing edge 12-11-1 on the downstream side in the rotational direction of the hub 11 It has 12-11B.
- the extension portion 12-11B suppresses the deflection of the air flow due to the centrifugal force caused by the rotation of the propeller fan 5, the occurrence of the surging phenomenon can be prevented. Further, by arranging the wing elements 12-12 and 12-13 so as to overlap with the rotational orbit around the hub 11 of the wing elements 12-11 and 12-12, the wing separated from the extension portion 12-11B The air flow flowing along the position of the surface is affected by the next row of wing elements 12-12. Thus, the force of the wing 12 can be exerted even on the air flow that has not been able to exert the force of the wing 12 conventionally, and the air volume of the propeller fan 5 can be increased. That is, according to the first embodiment, it is possible to increase the air volume of the propeller fan while suppressing the occurrence of the surging phenomenon.
- Example 1 the wing element 12-11 has the extended portion 12-11B at the rear edge 12-11-1.
- the present invention is not limited thereto.
- the wing element 12-11 does not have the extension 12-11B at the rear edge 12-11-1, and the wing element 12-12 extends at the rear edge 12-12-1.
- the wing element 12-11 has the extension 12-11B at the rear edge 12-11-1, and the wing element 12-12 is the same as the extension 12-11B at the rear edge 12-12-1. It may have a stretched portion of
- the wing element 12-11 has the extension 12-11B at the rear edge 12-11-1.
- the present invention is not limited to this, and the wing element 12-12 may have an extension portion similar to the extension portion 12-11B at the front edge portion 12-12-2.
- wing element 12-11 has extension 12-11B at the trailing edge 12-11-1, and wing element 12-12 is similar to extension 12-11B at the front edge 12-12-2. It may have a stretched portion of
- wing element 12-12 has an extension at trailing edge 12-12-1 similar to extension 12-11B, and wing element 12-13 extends to leading edge 12-13-2. It may have the same stretched portion as the portion 12-11B.
- wing element 12-11 has an extension 12-11B at the trailing edge 12-11-1
- wing element 12-12 is similar to extension 12-11B at the front edge 12-12-2
- the wing element 12-12 has an extension similar to the extension 12-11B at the trailing edge 12-12-1
- the wing element 12-13 has the leading edge 12
- the same extension part as the extension part 12-11B may be provided at -13-2.
- FIG. 14 is a side view showing one of the propeller fan blades according to the second embodiment.
- the wing element 12A-11 of the wing 12A of the propeller fan 5A according to the second embodiment is connected to the hub 11 with the base 12A-11a as a connection portion.
- the wing 12A has a substantially trapezoidal shape in which the extended portions 12A-11B of the wing element 12A-11 have the boundary C1 as a base and the boundary C1 as a base.
- the height of the extension 12A-11B gradually increases toward the pressure side of the hub 11 with respect to the boundary C1.
- the height of the hub 11 with respect to the pressure side of the boundary C1 is substantially constant until the connection point with the hub 11 is reached.
- the extended portions 12A-11B of the second embodiment like the extended portions 12-11B of the first embodiment, have the hub 11 with respect to the boundary C1 in the vicinity of the branch point 12p of the wing element 12A-11 and the wing element 12-12.
- the height gradually increases toward the positive pressure side of the In other words, the whole of the front edge 12-12-2 of the wing element 12-12 overlaps the rotational orbit around the hub 11 of the extension 12A-11B. Therefore, the outer end of the extension 12A-11B is located at the branch point 12p, so that the air conditioner is operated at high load or at high rotation from the hole 12A-21 to the wing element 12-12.
Abstract
Description
図1は、実施例1にかかるプロペラファンを有する室外機を示す模式図である。図1に示すように、実施例1の室外機1は、空気調和機の室外機である。室外機1は、筐体6を有し、筐体6内に、冷媒を圧縮する圧縮機3、圧縮機3に連結されて冷媒が流れる熱交換器4、熱交換器4に送風するプロペラファン5を収容する。
図2は、実施例1にかかるプロペラファンを正圧側から見た概略的な平面図である。図3は、実施例1にかかるプロペラファンの翼のうちの1枚を正圧側から見た平面図である。図4は、実施例1にかかるプロペラファンを負圧側から見た概略的な平面図である。図5は、実施例1にかかるプロペラファンの翼のうちの1枚を負圧側から見た平面図である。図6は、実施例1にかかるプロペラファンを示す斜視図である。図7は、実施例1にかかるプロペラファンを示す側面図である。図8は、実施例1にかかるプロペラファンの翼のうちの1枚を示す側面図である。
さらに、図9を参照して、隣接する翼素12-11と翼素12-12との位置関係について説明する。図9は、実施例1にかかるプロペラファンのI-I断面の概略を示す断面図である。ここで、I-I断面とは、図2のプロペラファン5の平面図における切断線I-Iに沿ってプロペラファン5の翼12を切断し、外周部12b側から見た場合の断面である。
図10は、比較例にかかるプロペラファンを実施例1にかかるプロペラファンとI-I断面において比較するための断面図である。図10は、比較例にかかるプロペラファンの翼12Zを、図2における実施例1にかかるプロペラファン5のI-I断面と同様のI-I断面(不図示)に沿って見た場合の断面視を示す。
図11~図13を参照して、実施例1と比較例のプロペラファンの静圧の変化を説明する。図11は、風量-入力(投入電力)曲線図である。図12は、風量-回転数曲線図である。図13は、風量-静圧曲線図である。図11および図12は、実施例1と比較例のプロペラファンの静圧を比較する際の前提条件を示す。
(1)実施例1では、翼素12-11が後縁部12-11-1に延伸部12-11Bを有するとした。しかし、これに限られず、翼素12-11が後縁部12-11-1に延伸部12-11Bを有さず、翼素12-12が後縁部12-12-1に延伸部12-11Bと同様の延伸部を有してもよい。または、翼素12-11が後縁部12-11-1に延伸部12-11Bを有し、かつ、翼素12-12が後縁部12-12-1に延伸部12-11Bと同様の延伸部を有するとしてもよい。
3 圧縮機
4 熱交換器
5、5A プロペラファン
6 筐体
6a 側面
6b 前面
6c 背面
7 吸込み口
8 吹出し口
11 ハブ
11a 側面
12、12A 翼
12a 内周部
12b 外周部
12p 分岐点
12-11、12-12、12-13、12A-11 翼素
12-21、12A-21、12-22 孔部
12-11a、12A-11a、12-12a、12-13a 基部
12-11A 基体部
12-11B、12A-11B 延伸部
12-1、12-11-1、12-12-1、12-13-1 後縁部
12-2、12-11-2、12-12-2、12-13-2 前縁部
Claims (4)
- 中心軸の周りに側面を有するハブと、前記側面に設けられた複数の翼と、を備え、
前記翼は、前記ハブに接続されている基部から外周までの部分のうち前記基部側に位置する内周部および前記外周側に位置する外周部を含み、前記外周部から前記内周部へ至る途中で分岐した複数の翼素を有し、
前記複数の翼素は、前記中心軸を回転中心とする回転の下流側の後縁部と、該回転の上流側の前縁部とを有し、前記中心軸に対してそれぞれのピッチ角で前記側面に接続され、隣接する該翼素間それぞれに気流の流路となる孔部を形成し、
前記複数の翼素は、前記外周部から前記内周部へ至る途中の分岐点で分岐した前記回転の上流側の第1の翼素と前記第1の翼素の前記回転の下流側に隣接する第2の翼素とを含み、前記分岐点から前記側面に至る前記第1の翼素の前記後縁部に前記第1の翼素の一部である延伸部を有し、
前記延伸部の前記中心軸を回転中心とする回転軌道には、前記第2の翼素の前縁部の少なくとも一部が重なる、プロペラファン。 - 前記延伸部の前記中心軸を回転中心とする回転軌道には、前記第2の翼素の前縁部の全部が重なる、請求項1に記載のプロペラファン。
- 前記複数の翼素は、前記中心軸に対して互いに異なる方向の前記側面の位置に接続されている、請求項1に記載のプロペラファン。
- 前記延伸部は、前記分岐点において、前記翼素の翼面に沿って流れる気流を前記流路へ逃がす形状の部分を有する、請求項1に記載のプロペラファン。
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CN201880077041.7A CN111417786B (zh) | 2017-12-05 | 2018-12-05 | 螺旋桨式风扇 |
AU2018381395A AU2018381395B2 (en) | 2017-12-05 | 2018-12-05 | Propeller fan |
EP18885012.7A EP3722615A4 (en) | 2017-12-05 | 2018-12-05 | PROPELLER FAN |
US16/769,988 US11187237B2 (en) | 2017-12-05 | 2018-12-05 | Propeller fan |
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JP2017233659A JP6583397B2 (ja) | 2017-12-05 | 2017-12-05 | プロペラファン |
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US (1) | US11187237B2 (ja) |
EP (1) | EP3722615A4 (ja) |
JP (1) | JP6583397B2 (ja) |
CN (1) | CN111417786B (ja) |
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CN111417786A (zh) | 2020-07-14 |
AU2018381395A1 (en) | 2020-06-18 |
US20210199122A1 (en) | 2021-07-01 |
JP2019100278A (ja) | 2019-06-24 |
AU2018381395B2 (en) | 2021-09-23 |
CN111417786B (zh) | 2021-10-08 |
JP6583397B2 (ja) | 2019-10-02 |
EP3722615A4 (en) | 2021-09-08 |
EP3722615A1 (en) | 2020-10-14 |
US11187237B2 (en) | 2021-11-30 |
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