WO2022113217A1 - ターボファン及び空気調和機 - Google Patents
ターボファン及び空気調和機 Download PDFInfo
- Publication number
- WO2022113217A1 WO2022113217A1 PCT/JP2020/043872 JP2020043872W WO2022113217A1 WO 2022113217 A1 WO2022113217 A1 WO 2022113217A1 JP 2020043872 W JP2020043872 W JP 2020043872W WO 2022113217 A1 WO2022113217 A1 WO 2022113217A1
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- WIPO (PCT)
- Prior art keywords
- point
- blade
- rotation
- main plate
- leading edge
- Prior art date
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- 230000007423 decrease Effects 0.000 claims description 11
- 238000005452 bending Methods 0.000 claims description 6
- 230000000052 comparative effect Effects 0.000 description 11
- 238000009423 ventilation Methods 0.000 description 10
- 230000002093 peripheral effect Effects 0.000 description 6
- 238000000926 separation method Methods 0.000 description 5
- 230000006866 deterioration Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 238000007664 blowing Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000007787 solid 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
- F04D29/28—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
- F04D29/28—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
- F04D29/282—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers the leading edge of each vane being substantially parallel to the rotation axis
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
-
- 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
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
- F24F1/0007—Indoor units, e.g. fan coil units
- F24F1/0018—Indoor units, e.g. fan coil units characterised by fans
- F24F1/0022—Centrifugal or radial fans
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/713—Shape curved inflexed
Definitions
- This disclosure relates to a turbofan having a swept blade and an air conditioner.
- the turbofan has a configuration in which the air flow sucked in the axial direction is turned in the radial direction by centrifugal force and blown out. For this reason, the sucked air flow becomes a flow biased toward the main plate side due to inertia, and the work by the blades is not sufficient for the air flow on the shroud side facing the main plate. Further, if the air flow on the shroud side is separated, the pressure resistance increases and the efficiency of the fan is lowered. Further, when a high-speed air flow is blown out, the air flow collides with a structure such as a heat exchanger provided outside the turbofan, which causes an increase in pressure loss or deterioration of noise. In particular, in an air conditioner, the above problem is remarkable when the specific speed is relatively increased. The specific speed is the rotational speed required to generate a unit flow rate of air flow.
- the leading edge and the trailing edge of the blade are concave in the airflow direction, or the blade is curved to reduce the wing loading and suppress peeling, resulting in low noise and high efficiency. Has been realized.
- Patent Document 1 has a shape in which the trailing edge of the blade is concave in the direction along the air flow, that is, in the direction along the camber line which is the center line in the thickness direction of the blade. For this reason, the net diameter of the blade is reduced, resulting in a decrease in air blowing performance such as an increase in pressure or a decrease in air volume.
- the present disclosure has been made in order to solve the above problems, and an object of the present disclosure is to provide a turbofan and an air conditioner that suppresses deterioration of ventilation performance and deviation of speed distribution.
- the turbo fan according to the present disclosure includes a main plate having a hub to which a rotating shaft is connected, a shroud arranged so as to face the main plate, and a plurality of blades arranged between the main plate and the shroud.
- Each of the plurality of blades has a front edge and a trailing edge located farther from the rotation axis than the front edge, and the front edge is ahead of the trailing edge in the rotational direction.
- the first point is the joint point between the front edge and the main plate, and the second point is the intersection of the front edge and the virtual plane perpendicular to the rotation axis passing through the outermost periphery of the shroud.
- the first curve drawn by projecting the front edge onto a plane perpendicular to the rotation axis is the first point and the first curve in a top view seen from the axial direction of the rotation axis.
- the virtual straight line passing through the two points has a first variation point with respect to the coordinate system whose horizontal axis is the horizontal axis and the rotation direction side is positive, and the first curve is the first variation. It has a portion that is convex in the counter-rotational direction at a portion closer to the first point than the point, and a portion that is convex in the rotation direction at a portion closer to the second point than the first variation point.
- the first point is located in front of the second point in the direction of rotation, and a second curve drawn by projecting the trailing edge onto a plane perpendicular to the axis of rotation is formed.
- a third view of the top view from the axial direction of the axis of rotation, along an arc centered on the axis of rotation, with the trailing edge projected onto a cylindrical surface coaxial with the axis of rotation.
- the curve is formed so as to be convex in the rotation direction, and the joint point between the third curve and the shroud is in the rotation direction rather than the joint point between the third curve and the main plate. It is located behind.
- the region where the distance between the leading edge of the blade and the rotating shaft is decreasing is expanded, and the leading edge on the main plate side precedes the leading edge on the shroud side in the rotational direction. Therefore, it is possible to prevent a decrease in the suction efficiency of the air flow and improve the ventilation performance. Further, since the trailing edge of the blade is convex in the rotation direction and the trailing edge on the shroud side is located behind the trailing edge on the main plate side in the rotation direction, the deviation of the velocity distribution at the blade outlet is suppressed. be able to.
- FIG. It is a schematic perspective view of the turbofan which concerns on Embodiment 1.
- FIG. It is a perspective view of the main plate and the main part of the blade of the turbofan which concerns on Embodiment 1.
- FIG. It is a perspective view which looked at the main part of the main plate and the blade of the turbofan which concerns on Embodiment 1 from the direction different from FIG.
- It is a top view of the vane of the turbofan which concerns on Embodiment 1 as seen from the axial direction of the rotation axis.
- It is an enlarged view of the main part of FIG. It is a schematic diagram which projected the trailing edge line of the blade of the turbofan which concerns on Embodiment 1 on the virtual cylindrical plane about the rotation axis.
- FIG. 8 is a top view of the blades of the turbofan according to the fourth embodiment as viewed from the axial direction of the rotating shaft. It is a graph which shows the relationship between the height of the leading edge of the blade of the turbofan which concerns on Embodiment 5, and the entrance angle. It is a schematic diagram which shows the inside of the air conditioner which concerns on Embodiment 6.
- FIG. 1 is a schematic perspective view of the turbofan 100 according to the first embodiment.
- the turbofan 100 includes a main plate 2 provided with a hub 1, an annular shroud 3 arranged facing the main plate 2, and a plurality of blades 4 arranged between the main plate 2 and the shroud 3.
- the hub 1 is provided in the center of the main plate 2 and is connected to the rotation shaft RS.
- the XY plane is a plane perpendicular to the axis of rotation RS and is a plane perpendicular to the Z direction.
- the shroud 3 is arranged in the Z direction with a distance from the main plate 2.
- the turbofan 100 is rotationally driven in the rotation direction RD about the rotation axis RS by a motor (not shown).
- the turbofan 100 is driven by rotation to suck the air flow A1 in the axial direction of the rotation shaft RS, and blows out the air flow A1 to the outside in the radial direction by the centrifugal force generated by the rotation.
- Hub 1 has a circular shape projected along the rotation axis RS. That is, the hub 1 is circular when viewed in the axial direction of the rotation axis RS.
- the hub 1 is formed in a truncated cone shape that rises in a mountain shape from the main plate 2 side toward the shroud 3 side.
- the shaft 201a of the motor 201 is connected to the hub 1.
- the shape of the hub 1 is not limited to the above shape, and may be another shape.
- the hub 1 may be provided with a hole through which air passes for cooling the motor 201.
- the main plate 2 has a hub 1.
- the main plate 2 rotates together with the hub 1 by being driven by a motor.
- a plurality of blades 4 are connected to the main plate 2.
- the main plate 2 is formed in a disk shape.
- the shape of the main plate 2 is not limited to a disk shape.
- the main plate 2 may be formed in a mountain shape around the hub 1, for example.
- the outer edge shape of the main plate 2 is not limited to a circular shape having a constant outer diameter, but may be a polygon shape having a variable outer diameter.
- the shroud 3 forms a wind guide wall for guiding the air on the side of the turbofan 100 that sucks in the air.
- the shroud 3 is maintained at a distance from the main plate 2 by a plurality of blades 4.
- the shroud 3 has a trumpet-shaped shape that changes in diameter.
- the shroud 3 is formed so that the opening diameter increases from the air inlet to the outlet of the turbofan 100.
- the shroud 3 is formed in a mountain shape from the outer side in the radial direction toward the center side.
- the plurality of blades 4 are arranged between the main plate 2 and the shroud 3 and are connected to the main plate 2 and the shroud 3.
- the plurality of blades 4 rotate together with the main plate 2 to send out the air inside the turbofan 100 to the outer peripheral side.
- the plurality of blades 4 have a leading edge 41 and a trailing edge 42 located farther from the rotation axis RS than the leading edge 41.
- the leading edge 41 of the plurality of blades 4 is located in front of the trailing edge 42 in the rotation direction RD. That is, the plurality of blades 4 are receding blades.
- the plurality of blades 4 are arranged at predetermined intervals on the circumference centered on the rotation axis RS. The spacing between the plurality of blades 4 may or may not be equal.
- the blade 4 has an outer surface 4a and an inner surface 4b which is the back surface of the outer surface 4a.
- the inner surface 4b is located closer to the rotation axis RS than the outer surface 4a.
- the outer surface 4a is a positive pressure surface that receives a pressure higher than the air pressure
- the inner surface 4b is a negative pressure surface that receives a pressure lower than the air pressure.
- the blade 4 has a shape in which the thickness gradually decreases from the position where the thickness becomes the maximum on the camber line to the front edge side or the trailing edge side along the camber line.
- the camber line is a center line in the thickness direction of the blade 4.
- the blade 4 has a general wing shape in a plane perpendicular to the axis of rotation RS, that is, a plane parallel to the XY plane.
- the change in thickness along the camber line of the blade 4 does not change monotonically, but there may be a region where the change in thickness fluctuates in the middle.
- FIG. 2 is a perspective view of a main part of the main plate 2 and the blade 4 of the turbofan 100 according to the first embodiment.
- FIG. 3 is a perspective view of the main parts of the main plate 2 and the blades 4 of the turbofan 100 according to the first embodiment as viewed from a direction different from that of FIG. 2 and 3 show a state in which the shroud 3 is removed.
- FIG. 4 is a top view of the blade 4 of the turbofan 100 according to the first embodiment as viewed from the axial direction of the rotating shaft RS.
- the arrow A indicates the observation direction of the main plate 2 and the main part of the blade 4 of the turbofan 100 in FIG. 2
- the arrow B indicates the main part of the main plate 2 and the blade 4 of the turbofan 100 in FIG. Indicates the observation direction of.
- the blade 4 has, for example, a shape in which the camber line, which is the center line in the thickness direction of the plane perpendicular to the rotation axis RS, is convex in the rotation direction RD.
- the shape of the plane perpendicular to the rotation axis RS of the blade 4 and the cross section parallel to the XY plane is a general blade shape.
- the center line in the thickness direction of the blade 4 in the cross section where the blade 4 is in contact with the main plate 2 is defined as the camber line LC1.
- the leading edge 41 of the camber line LC1 in the cross section in contact with the main plate 2 is defined as a point P11. That is, the point P11 is a point where the leading edge 41 and the main plate 2 are in contact with each other, and is an example of the first point.
- the trailing edge 42 of the camber line LC1 in the cross section in contact with the main plate 2 is defined as a point P21.
- the center line in the thickness direction of the blade 4 in the cross section of the surface perpendicular to the rotation axis RS at the position at the height of the outermost peripheral portion of the shroud 3 is the camber line LC2.
- the leading edge 41 of the camber line LC2 at the height position of the outermost peripheral portion of the shroud 3 is defined as a point P12. That is, the point P12 is an intersection of the leading edge 41 and the plane perpendicular to the rotation axis RS passing through the outermost peripheral portion of the shroud 3, and is an example of the second point.
- the trailing edge 42 of the camber line LC2 at the height position of the outermost peripheral portion of the shroud 3 is defined as a point P22.
- the point farthest from the main plate 2 is defined as the point P12a.
- the locus drawn by the leading edge 41 from the point P11 to the point P12a is defined as the leading edge line L1.
- the locus drawn by the trailing edge 42 from the point P21 to the point P22 is defined as the trailing edge line L2.
- FIG. 5 is an enlarged view of a main part of FIG.
- the line drawn by projecting the leading edge line L1 onto a plane perpendicular to the rotation axis RS is defined as the first curve L21.
- the front edge 41 of the blade 4 is a top view seen from the axial direction of the rotation axis RS, and the first curve L21 is the first variation with respect to the coordinate system with the first straight line L11 as the horizontal axis. It is a shape having a curved point P13.
- the first curve L21 with the front edge 41 of the blade 4 viewed from above has a convex shape between the point P11 and the first inflection point P13 in the counter-rotation direction, and the first inflection point from the point P12. Between P13, an S-shaped curve having a convex shape in the rotation direction RD is drawn.
- the coordinate component of the point P11 is P11 (R11, ⁇ 11), and the coordinate component of the point P12 is P12 (R12, ⁇ 12).
- the distance R is the distance from the rotation axis RS to an arbitrary point.
- the angle ⁇ is an angle with the anti-rotation direction as a positive with respect to an arbitrary virtual straight line passing through the rotation axis RS.
- the first curve L21 is a curve that satisfies R11 ⁇ R12 and ⁇ 11 ⁇ 12. That is, in the leading edge line L1, the point P11 on the main plate 2 side is located on the inner side in the radial direction in which the distance from the rotation axis RS is shorter than the point P12a on the shroud 3 side. Further, in the leading edge line L1, the point P11 on the main plate 2 side is located in front of the point P12a on the shroud 3 side in the rotation direction RD.
- the leading edge 41 on the main plate 2 side is located in front of the rotation direction RD, the air flow on the main plate 2 side is not disturbed by the blades 4 on the shroud 3 side, and the air flow is on the main plate 2 side. It is effectively sucked from the blade 4 of the.
- the trailing edge line L2 passes from the point P21 on the main plate 2 side to the point P23 in front of the point P21 on the main plate 2 side in the rotation direction RD, and moves from the point P23 to the rear in the rotation direction RD.
- the shape is such that it reaches the point P22 on the shroud 3 side.
- the point P23 is a point located on the trailing edge line L2 most in front of the rotation direction RD.
- the trailing edge line L2 draws a second curve L22 when projected on a plane perpendicular to the axis of rotation RS.
- the second curve L22 traces a locus along an arc centered on the rotation axis RS in a top view seen from the axial direction of the rotation axis RS.
- FIG. 6 is a schematic diagram in which the trailing edge line L2 of the blade 4 of the turbofan 100 according to the first embodiment is projected onto a virtual cylindrical surface C centered on the rotation axis RS.
- the trailing edge line L2 of the blade 4 draws a third curve L23 when projected onto a virtual cylindrical surface C centered on the rotation axis RS.
- the third curve L23 draws a convex U-shape toward the front in the rotation direction RD from P21, which is a joint point with the main plate 2, on the virtual cylindrical surface C centered on the rotation axis RS, and the shroud 3 Follow the trajectory leading to P22, which is the junction with.
- the distance R from the rotation axis RS and the angle ⁇ with which an arbitrary virtual curve passing through the rotation axis RS is a reference and the anti-rotation direction is positive are used.
- the point P21 on the main plate 2 side is located in front of the point P22 on the shroud 3 side in the rotation direction RD. That is, the point P21 which is the junction point between the third curve L23 and the main plate 2 is located in front of the point P22 which is the junction point between the third curve L23 and the shroud 3 in the rotation direction RD. ..
- the second curve L22 is a curve that satisfies ⁇ 21 ⁇ 22, where P21 (R21, ⁇ 21) is the coordinate component of the point P21 and (R22, ⁇ 22) is the coordinate component of P22 in the polar coordinate system.
- the trailing edge line L2 Since the trailing edge line L2 has the above configuration, the air flow concentrated on the main plate 2 side is dispersed from the main plate 2 side to the shroud 3 side in the process toward the outlet side along the rotating blade 4. Therefore, the wind speed distribution of the air flow on the outer surface 4a of the blade 4 is made uniform.
- the second curve L22 may be along an arc centered on the rotation axis RS, and for example, a fine saw-shaped serration may be provided on the trailing edge 42 of the blade 4. Even if the radial position of the trailing edge 42, i.e., the second curve L22, is not on a perfect arc about the axis of rotation RS, it does not affect the effect obtained by the second curve L22. If the second curve L22 does not deviate excessively from the arc centered on the rotation axis RS, the outer diameter of the blade 4 does not fluctuate, so that the ventilation performance can be maintained.
- the change in the position of the trailing edge 42 in the rotation direction RD from the point P21 to the point P23, or the change from the point P23 to the point P22 does not necessarily have to be monotonous. As long as the positional relationship between the points P21, the point P22, and the point P23 is within the range satisfying the above-mentioned positional relationship, there may be a portion of the trailing edge 42 in which the direction of change is opposite.
- the leading edge line L1 draws an S-shape convex in the counter-rotation direction on the main plate 2 side.
- leading edge 41 on the main plate 2 side has a shape that precedes the leading edge 41 on the shroud 3 side in the rotation direction RD. As a result, the air flow is effectively sucked by the blades 4 on the main plate 2 side without being disturbed by the blades 4 on the shroud 3 side.
- the efficiently sucked air flow is dispersed from the main plate 2 side to the shroud 3 side as it goes toward the outlet side along the blade 4 due to the shape of the trailing edge line L2, and the wind speed distribution becomes more uniform. To. As a result, it is possible to prevent the flow without causing the negative pressure surface peeling on the shroud 3 side or the bias of the velocity distribution at the outlet of the blade 4, and adversely affect the fan efficiency and noise.
- the leading edge 41 is the rotation axis of the main plate 2 side where the air flow is concentrated, as compared with other regions.
- the area located on the inner diameter side with respect to RS is limited.
- the case where the leading edge line L1 is not S-shaped convex in the counter-rotation direction on the main plate 2 side is, for example, when the locus of the leading edge 41 of the blade 4 is linear in the top view, or the main plate 2 side. This is a case of an S-shape that is convex in the rotation direction RD and is convex in the counter-rotation direction on the shroud 3 side.
- the amount of air sucked on the main plate 2 side is also limited. Further, if the position of the leading edge 41 in the rotation direction RD is the same on the main plate 2 side and the shroud 3 side, the air flow is disturbed by the blade 4 on the shroud 3 side, and the air effectively reaches the main plate 2 side. I can't breathe in the flow.
- the leading edge line L1 of the blade 4 has an S-shaped shape that is convex in the counter-rotation direction in the top view, so that the leading edge 41 of the blade 4 is linear.
- the range of the region where the leading edge 41 is located on the inner diameter side of the other regions on the main plate 2 side can be expanded. As a result, the air flow is effectively sucked into the main plate 2 side where the flow is concentrated due to inertia, and the ventilation performance of the turbofan is improved.
- the configuration is such that the air flow concentrated on the main plate 2 side can be efficiently sucked, there is a possibility that the negative pressure surface is peeled off on the shroud 3 side or the velocity distribution is biased at the outlet of the blade 4.
- the entire blade 4 in order to increase the surface area of the blade 4 and improve the ventilation characteristics and the noise characteristics, for example, it is conceivable to bend the entire blade 4 in an uneven shape in the direction of the rotation axis.
- the cross-sectional shape of the blade 4 from the front edge side to the trailing edge side is substantially the same in the axial direction of the rotating shaft RS, the air flowing into the blade 4 flows into the blade 4.
- the flow is biased in the axial direction of the rotation axis RS, or there is a possibility that the air flow having three-dimensionality does not follow the cross section of the blade 4.
- the air flow flowing into the blade 4 and concentrating on the main plate 2 side flows toward the outlet side along the blade 4 due to the shape of the trailing edge line L2, and the outlet On the side, it is dispersed from the main plate 2 side to the shroud 3 side. Therefore, the wind speed distribution of the air flow that has flowed unevenly toward the main plate 2 side due to the influence of inertia is made more uniform, and the air flow is separated on the negative pressure surface on the shroud 3 side or the air flow speed at the outlet of the turbofan 100. Noise deterioration due to uneven distribution is suppressed.
- the first curve L21 when the leading edge 41 is viewed from the axial direction of the rotation axis RS is opposite. It has an S-shape that is convex in the direction of rotation.
- the region where the distance from the rotation axis RS to the leading edge 41 is smaller than the distance between the rotation axis RS and the first straight line L11 increases on the main plate 2 side. Therefore, the air flow concentrated on the main plate 2 side of the leading edge 41 due to inertia is effectively sucked in, and the blowing characteristics are improved.
- the main plate 2 side of the leading edge 41 has a shape located in front of the leading edge 41 on the shroud 3 side in the rotation direction RD.
- the air flow can be effectively sucked by the blade 4 on the main plate 2 side without being disturbed by the blade 4 on the shroud 3 side.
- the second curve L22 viewed from above is on an arc centered on the rotation axis RS
- the third curve L23 viewed from the cylindrical surface C is convex in the rotation direction RD.
- the shape is such that the main plate 2 side is located in front of the shroud 3 side in the rotation direction RD.
- the air flow promoted to be biased toward the main plate 2 side on the front edge 41 side is uniformly dispersed from the main plate 2 side to the shroud 3 side, and the air flow is separated or blown out on the negative pressure surface on the shroud 3 side.
- Noise deterioration due to bias of velocity distribution at the exit is prevented. Therefore, the decrease in the specific blown air in the turbofan 100 and the bias of the velocity distribution at the outlet of the blade 4 are suppressed.
- the air flow is less likely to be turbulent at the leading edge due to the three-dimensional nature of the suction flow, that is, the axial component of the air flow. Therefore, the air flow can flow smoothly toward the trailing edge, and the decrease in the suction efficiency of the air flow in the turbofan 100 and the bias of the velocity distribution at the outlet of the blade 4 can be further suppressed.
- FIG. 7 is a top view of the blade 4 of the turbofan 100 according to the second embodiment as viewed from the axial direction of the rotating shaft RS.
- the configuration of the blade 4 is different from that of the first embodiment, and the other configurations are the same as those of the first embodiment. It is attached.
- the camber line LC1 on the main plate 2 side and the camber line LC2 on the shroud 3 side are points in the top view seen from the axial direction of the rotating shaft RS.
- P14 it is a configuration that intersects with each other.
- the camber line LC1 on the main plate 2 side is a center line in the thickness direction of the blade 4 on the surface where the blade 4 is in contact with the main plate 2.
- the camber line LC2 on the shroud 3 side is a center line in the thickness direction of the blade 4 on a virtual plane perpendicular to the rotation axis RS passing through the outermost peripheral portion of the shroud 3 of the blade 4.
- the negative pressure surface of the blade 4 is, that is, the inner surface 4b of the blade 4.
- the inner surface 4b seen from the suction port side of the blade 4 is a region of the blade 4 mainly located on the shroud 3 side.
- turbofan 100 since the area of the negative pressure surface of the blade 4 seen from the suction port side increases, an air flow flows to the negative pressure surface side of the blade 4 on the shroud 3 side. It will be easier. As a result, the separation of the air flow from the negative pressure surface of the blade 4 on the shroud 3 side is suppressed more effectively, and the fan efficiency and the fan noise can be improved.
- FIG. 8 is a top view of the blade 4 of the turbofan 100 according to the third embodiment as viewed from the axial direction of the rotating shaft RS.
- the configuration of the blade 4 is different from that of the first embodiment, and the other configurations are the same as those of the first embodiment. It is attached.
- the first inflection point P13 at the leading edge line L1 is closer to the point P11 than the point P12 in the linear distance in the top view seen from the axial direction of the rotation axis RS. That is, the distance between the first inflection point P13 and the point 11 is shorter than the distance between the first inflection point P13 and the point P12.
- FIG. 9 is a meridional view showing a main part of the blade 4 of the turbofan 100 according to the third embodiment.
- the meridional view is a view showing a plane when a rotating solid formed by rotating the blade 4 is cut by a plane including the rotation axis RS.
- the angle ⁇ 3 formed by the normal of the leading edge 41 on the shroud 3 side and the rotation axis RS is the normal of the leading edge 41 on the main plate 2 side and the rotation axis RS. It is larger than the angle ⁇ 2 between the two.
- the blade 4 according to the third embodiment has a configuration in which the first inflection point P13 is arranged at a position closer to the point P11 than the point P12 in the top view seen from the axial direction of the rotation axis RS. be.
- the angle ⁇ 3 formed by the normal line of the leading edge 41 and the rotation axis RS on the shroud 3 side is larger than the angle ⁇ 2 formed by the normal line of the leading edge 41 and the rotation axis RS on the main plate 2 side.
- the air flow A11 on the main plate 2 side, the air flow A12 on the shroud 3 side, and the air flow A13 between the main plate 2 and the shroud 3 are in the normal direction of the leading edge 41 of the blade 4, respectively. Will flow in from. Therefore, on the shroud 3 side, the air flow A12 that flows diagonally with respect to the cross section of the blade 4 can be adjusted so that the normal direction of the leading edge 41 of the blade 4 is the inflow direction of the air flow A12. ..
- the normal direction of the leading edge 41 of the blade 4 can be adjusted according to the inflow direction of air, so that the flow loss can be suppressed and the fan efficiency can be suppressed. And reduction of fan noise can be realized.
- FIG. 10 is a top view of the blade 4 of the turbofan 100 according to the fourth embodiment as viewed from the axial direction of the rotating shaft RS.
- the configuration of the blade 4 is different from that of the first embodiment, and the other configurations are the same as those of the first embodiment. It is attached.
- the bending direction of the camber line in the cross section perpendicular to the rotation axis RS changes. It is configured to have an inflection point P15.
- the chord which is a straight line passing through the leading edge 41 and the trailing edge 42 in a certain cross section of the blade 4, is defined as a second straight line L12.
- a straight line L12 with respect to a cross section of the blade 4 passing through the point P11 is shown as an example.
- a straight line perpendicular to the second straight line L12 is defined as a third straight line L13.
- the vane 4 changes the bending direction of the camber line LC1 in the cross section perpendicular to the rotation axis RS at the second inflection point P15 with respect to the coordinate system.
- the blade 4 has a configuration in which the bending direction of the camber wire changes at the second inflection point P15 from the cross section on the main plate 2 side to the cross section of the first inflection point P13.
- the blade 4 may have a configuration having a second inflection point P15 at all positions from the main plate 2 side to the height of the first inflection point P13.
- the vicinity of the leading edge of the cross section of the blade 4 is convex in the counter-rotation direction, and the configuration is reversed.
- the camber wire on the main plate 2 side of the blade 4 has a shape that is reversely curved so as to be convex in the counter-rotation direction, so that the inlet angle of the cross-sectional shape of the blade 4 matches the inflow velocity of the air flow. ..
- the inlet angle is the negative pressure surface of the blade 4 among the angles formed by the tangent line at the front edge 41 of the virtual circle passing through the front edge 41 with the rotation axis RS as the origin and the tangent line at the front edge 41 of the camber line of the blade 4. It means the angle on the opposite rotation direction side.
- the leading edge 41 on the main plate 2 side of the blade 4 has a smaller inner diameter, which is the distance from the rotation axis RS, than the leading edge 41 on the shroud 3 side, the leading edge 41 on the main plate 2 side is the leading edge 41 on the shroud 3 side. It is closer to hub 1 than 41. Further, at the leading edge 41 on the main plate 2 side of the blade 4, the air flow is affected by the viscosity of the main plate 2, and the radial component of the air inflow velocity tends to decrease. By properly designing the inlet angle, the collision loss between the air flow and the blade 4 at the leading edge 41 of the blade 4 or the separation of the air flow at the leading edge 41 is effectively suppressed, and the fan efficiency is improved. , Fan noise is reduced.
- the bending direction of the camber line of the blade 4 changes.
- FIG. 11 is a graph showing the relationship between the height of the leading edge 41 of the blade 4 of the turbofan 100 according to the fifth embodiment and the entrance angle.
- the configuration of the blade 4 is different from that of the first embodiment, and the other configurations are the same as those in the first embodiment. It is attached.
- the blade 4 has a configuration in which the angle of the inlet angle on the counter-rotation direction side gradually decreases when the height of the leading edge 41 of the blade 4 becomes larger than the first inflection point P13. be.
- the height of the leading edge 41 of the blade 4 is the vertical distance from the main plate 2 to the leading edge 41 of the blade 4, and is the distance in the + Z direction when the intersection of the main plate 2 and the rotation axis RS is the origin. ..
- the entrance angle is formed by the tangent line at the leading edge 41 of the circle passing through the leading edge 41 of the blade 4 with the rotation axis RS as the origin and the tangent line at the leading edge 41 of the camber line of the blade 4.
- the blade 4 has an entrance angle of a cross section perpendicular to the axis of rotation RS from the cross section of the blade 4 having the first turning point P13 of the leading edge line L1 as the leading edge 41 to the cross section of the blade 4 on the shroud 3 side. Is a configuration that gradually shrinks.
- the air flow at the leading edge 41 is easily affected by the hub 1 and the main plate 2 on the main plate 2 side where the inner diameter of the blade 4 is reduced. Further, the air flow at the leading edge 41 is not affected by the hub 1 and the main plate 2 toward the shroud 3 side, and the inflow angle of air with respect to the cross section of the blade 4 tends to decrease.
- the entrance angle of the blade 4 becomes larger. It is a configuration that gradually decreases. Therefore, the collision loss of the air flow with respect to the blade 4 and the peeling of the leading edge are suppressed, and the fan efficiency can be improved and the fan noise can be reduced.
- FIG. 12 is a schematic view showing the inside of the air conditioner 200 according to the sixth embodiment.
- the sixth embodiment is an air conditioner 200 provided with the turbofan 100 according to any one of the first to fifth embodiments, and is the same as or equivalent to the first to fifth embodiments. It is marked with a sign.
- the air conditioner 200 is equipped with a turbofan 100 having a blade 4 and a motor 201 connected to the turbofan 100 via a shaft 201a.
- a heat exchanger 202 is arranged on the blowout side of the turbofan 100.
- a bell mouth 203 is provided on the suction side of the turbofan 100.
- the air flow is sucked into the air conditioner 200 from the suction port 205.
- the air flow passes through the bell mouth 203, the turbofan 100, and the heat exchanger 202, and then is blown out from the outlet 204 to the outside of the air conditioner 200.
- the velocity distribution of the air flow blown out from the turbofan 100 is uniform at the outlet, the velocity distribution of the air flow flowing into the heat exchanger 202 is also uniform. As a result, the pressure loss of the air flow when passing through the heat exchanger 202 can be reduced and the heat exchange performance can be improved, which contributes to the performance improvement and energy saving of the air conditioner 200 as a whole.
- the turbofan 100 according to the embodiment and the turbofan according to the comparative example have a configuration in which blades 4 have blades having a diameter of 480 [mm], and each of them is mounted on an air conditioner for an experiment.
- the turbofan 100 according to the embodiment and the turbofan according to the comparative example mounted on the air conditioner were driven at a predetermined rotation speed.
- the air volume, motor input, and noise level were measured under the condition that the differential pressure between the suction port 205 and the outlet 204 of the air conditioner was zero.
- the noise level was measured at a position 1 m away from the suction port 205 in the direction perpendicular to the suction surface under the condition that the differential pressure between the suction port 205 and the outlet 204 of the air conditioner was zero.
- FIG. 13 is a graph showing the relationship between the rotation speed and the air volume in the turbofan 100 according to the examples and the comparative examples.
- FIG. 14 is a graph showing the relationship between the inputs to the air volume in the turbofan 100 according to the examples and the comparative examples.
- FIG. 15 is a graph showing the relationship between the noise level and the air volume in the turbofan 100 according to the examples and the comparative examples.
- fan A shows a turbofan according to a comparative example
- fan B shows a turbofan 100 according to an embodiment.
- turbofan 100 according to the embodiment can simultaneously improve the ventilation performance, reduce the input, and reduce the noise.
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Abstract
Description
<ターボファン100の構成>
図1は、実施の形態1に係るターボファン100の概略斜視図である。ターボファン100は、ハブ1を備えた主板2と、主板2と対向して配置された環状のシュラウド3と、主板2とシュラウド3との間に配置された複数の羽根4と、を備える。ハブ1は、主板2の中央に設けられており、回転軸RSが接続される。
図2は、実施の形態1に係るターボファン100の主板2及び羽根4の要部の斜視図である。図3は、実施の形態1に係るターボファン100の主板2及び羽根4の要部を、図2と異なる方向から見た斜視図である。図2及び図3は、シュラウド3が取り外された状態を示している。図4は、実施の形態1に係るターボファン100の羽根4を、回転軸RSの軸方向から見た上面図である。図4において、矢印Aは、図2におけるターボファン100の主板2及び羽根4の要部の観察方向を示しており、矢印Bは、図3におけるターボファン100の主板2及び羽根4の要部の観察方向を示している。
図5は、図4の要部を拡大した図である。図5において、点P11と点P12とを通る第1の直線L11が横軸であり、第1の直線L11に垂直で、羽根4の回転方向RD側、すなわち、圧力面側が正である座標系を考える。前縁ラインL1を回転軸RSに垂直な平面に投影して描かれた線は、第1の曲線L21と定義する。
羽根4の後縁42は、後縁ラインL2が、主板2側の点P21から主板2側の点P21よりも回転方向RDの前方の点P23を通り、点P23から回転方向RDの後方に移動してシュラウド3側の点P22に到達する形状になっている。点P23は、後縁ラインL2で最も回転方向RDの前方に位置する点である。
図7は、実施の形態2に係るターボファン100の羽根4を回転軸RSの軸方向から見た上面図である。実施の形態2は、羽根4の構成が、実施の形態1と相違しており、その他の構成は実施の形態1と同様であるため、説明を省略し、同様あるいは相当部分には同じ符号を付している。
図8は、実施の形態3に係るターボファン100の羽根4を回転軸RSの軸方向から見た上面視である。実施の形態3は、羽根4の構成が、実施の形態1と相違しており、その他の構成は実施の形態1と同様であるため、説明を省略し、同様あるいは相当部分には同じ符号を付している。
図10は、実施の形態4に係るターボファン100の羽根4を回転軸RSの軸方向から見た上面視である。実施の形態4は、羽根4の構成が、実施の形態1と相違しており、その他の構成は実施の形態1と同様であるため、説明を省略し、同様あるいは相当部分には同じ符号を付している。
図11は、実施の形態5に係るターボファン100の羽根4の前縁41の高さと入口角との関係を示すグラフである。実施の形態5は、羽根4の構成が、実施の形態1と相違しており、その他の構成は実施の形態1と同様であるため、説明を省略し、同様あるいは相当部分には同じ符号を付している。
図12は、実施の形態6に係る空気調和機200の内部を示す概略図である。実施の形態6は、実施の形態1~5のいずれかに記載のターボファン100を備えた空気調和機200であり、実施の形態1~5と同様あるいは相当部分についての説明を省略し、同じ符号を付している。
続いて、実施例に係るターボファン100の性能評価について説明する。性能評価は、実施例に係るターボファン100と、比較例に係る一般的な構成のターボファンとの比較実験に基づき行った。
Claims (7)
- 回転軸が接続されるハブを備えた主板と、前記主板と対向して配置されたシュラウドと、前記主板と前記シュラウドとの間に配置された複数の羽根と、を有し、
前記複数の羽根のそれぞれは、前縁と、前記前縁よりも前記回転軸から離れて位置する後縁とを有し、前記前縁が前記後縁よりも回転方向の前方に位置しており、
前記前縁と前記主板との接合点を第1の点とし、前記前縁と前記シュラウドの最外周部を通る前記回転軸と垂直な仮想の平面との交点を第2の点とした場合、
前記前縁を前記回転軸に垂直な平面に投影して描かれた第1の曲線が、
前記回転軸の軸方向から見た上面視で、前記第1の点と前記第2の点とを通る仮想の直線が横軸であり前記回転方向側が正である座標系に対して、第1の変曲点を有し、
前記第1の曲線は、前記第1の変曲点より前記第1の点に近い部分で反回転方向に凸である部分と、前記第1の変曲点より前記第2の点に近い部分で前記回転方向に凸である部分と、を有し、
前記第1の点は前記第2の点よりも前記回転方向の前方に位置しており、
前記後縁を前記回転軸に垂直な平面に投影して描かれた第2の曲線が、前記回転軸の軸方向から見た上面視で、前記回転軸を中心とした円弧に沿っており、
前記後縁を前記回転軸と同軸上の円筒面上に投影して描かれた第3の曲線が、前記回転方向に凸であるように形成されており、
前記第3の曲線と前記シュラウドとの接合点は、前記第3の曲線と前記主板との接合点よりも、前記回転方向の後方に位置している
ターボファン。 - 前記第1の変曲点は、第1の曲線に単一に存在する
請求項1に記載のターボファン。 - 前記複数の羽根のそれぞれは、
前記主板と接する面における、前記複数の羽根のそれぞれの厚さ方向の中心線と、
前記シュラウドの前記最外周部を通る前記回転軸と垂直な仮想の平面における、前記複数の羽根のそれぞれの厚さ方向の中心線と、が、
前記回転軸の方向から見た上面視で、交差している
請求項1又は2に記載のターボファン。 - 前記回転軸の軸方向から見た上面視において、前記第1の変曲点と前記第2の点との距離よりも、前記第1の変曲点と前記第1の点との距離が短い
請求項1~3のいずれか一項に記載のターボファン。 - 前記第1の点を通り前記回転軸に垂直な平面における前記羽根の断面から、前記第1の変曲点を通り前記回転軸に垂直な平面における前記羽根の断面までの間の少なくとも一部において、
前記羽根の厚さ方向の中心線の湾曲方向が、
前記回転軸に垂直な平面における前記羽根の断面において前記前縁と前記後縁とを通る第1の直線と、それに垂直な第2の直線と、によって定義される座標系において、第2の変曲点を有する、
請求項1~4のいずれか一項に記載のターボファン。 - 前記回転軸に垂直な平面における前記羽根の断面において、
前記回転軸を原点とし前記前縁を通る円の前記前縁における接線と、前記羽根の厚さ方向における中心線の前記前縁における接線と、のなす角である入口角のうち、前記羽根の前記反回転方向側の角度が、
前記第1の変曲点を通り前記回転軸に垂直な平面における前記羽根の断面から、前記羽根と前記シュラウドとが接する面に至るまで、漸次減少する、
請求項1~5のいずれか一項に記載のターボファン。 - 請求項1~6のいずれか一項に記載のターボファンを搭載し、
前記ターボファンの吹き出し出口側に熱交換器を備えた
空気調和機。
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GB2306240.9A GB2615910A (en) | 2020-11-25 | 2020-11-25 | Turbofan and air conditioner |
AU2020478845A AU2020478845B2 (en) | 2020-11-25 | 2020-11-25 | Turbofan and air-conditioning apparatus |
US18/028,768 US20230332615A1 (en) | 2020-11-25 | 2020-11-25 | Turbofan and air-conditioning apparatus |
JP2021552910A JP7003337B1 (ja) | 2020-11-25 | 2020-11-25 | ターボファン及び空気調和機 |
PCT/JP2020/043872 WO2022113217A1 (ja) | 2020-11-25 | 2020-11-25 | ターボファン及び空気調和機 |
CN202080106107.8A CN116507808A (zh) | 2020-11-25 | 2020-11-25 | 涡轮风扇以及空调机 |
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