JP6099335B2 - Blower and hair dryer - Google Patents

Description

  The present invention relates to a blower, and more particularly, to a blower that rotates a propeller fan using a drive motor.

  Japanese Utility Model Laid-Open No. 05-088404 (Patent Document 1) and Japanese Patent Application Laid-Open No. 2010-125134 (Patent Document 2) disclose an invention relating to a hair dryer. A blower such as a hair dryer includes a drive motor and a propeller fan. The propeller fan is attached to the output shaft of the drive motor. The propeller fan rotates in response to rotational power from the drive motor, and generates an airflow that flows from the suction port toward the discharge port.

Japanese Utility Model Publication No. 05-088404 JP 2010-125134 A

  An object of this invention is to provide the air blower which can suppress that foreign materials, such as the hair or dust which were suck | inhaled with air from the suction inlet, are entangled with the output shaft of a drive motor.

  A blower device according to a first aspect of the present invention includes an air passage forming member including an inlet and an outlet, an output shaft, a drive motor provided inside the air passage forming member, and an output shaft. A propeller fan that includes a boss portion to be attached and a wing portion provided on an outer surface of the boss portion, and is disposed closer to the suction port than the drive motor, and the propeller fan extends from the drive motor. The airflow flowing from the upstream suction port toward the downstream discharge port is generated by rotating around a virtual rotation axis in response to the rotational power of the blade, and the wing portion is in the rotation direction of the propeller fan. A blade tip located at the most tip, a leading edge extending from the blade tip to the outer surface of the boss, and forming a leading edge of the blade in the rotational direction; and the boss External surface or The propeller fan extends outward in the rotational radial direction, and connects a trailing edge portion that forms a trailing edge of the wing portion in the rotational direction, and a wing tip portion and an outer end of the trailing edge portion. An outer peripheral edge portion that forms an outer peripheral edge of the wing portion in the rotational radius direction, and the most downstream position and the front edge portion in the wing portion in a direction parallel to the rotation axis When the height dimension between the base position of the blade and the blade is ha, and the height dimension between the most downstream position of the blade and the position of the blade tip is hb, the value of hb / ha is 1.5 or more.

  A blower device according to the second aspect of the present invention includes an air passage forming member including an inlet and an outlet, an output shaft, a drive motor provided inside the air passage forming member, and an output shaft. A propeller fan that includes a boss portion to be attached and a wing portion provided on an outer surface of the boss portion, and is disposed closer to the suction port than the drive motor, and the propeller fan extends from the drive motor. The airflow flowing from the upstream suction port toward the downstream discharge port is generated by rotating around a virtual rotation axis in response to the rotational power of the blade, and the wing portion is in the rotation direction of the propeller fan. A blade tip located at the most tip, a leading edge extending from the blade tip to the outer surface of the boss, and forming a leading edge of the blade in the rotational direction; and the boss External surface or The propeller fan extends outward in the rotational radial direction, and connects a trailing edge portion that forms a trailing edge of the wing portion in the rotational direction, and a wing tip portion and an outer end of the trailing edge portion. An outer peripheral edge portion forming an outer peripheral edge of the wing portion in the rotational radius direction, and the air passage forming member has an inner wall portion and a concave portion provided to be recessed from the inner wall portion. In the direction parallel to the rotational axis, the most downstream portion of the recess is located on the upstream side of the most downstream portion of the boss portion, and the blade of the wing portion The most upstream portion of the concave portion is located on the upstream side of the blade tip portion of the wing portion in the direction parallel to the rotation axis and located on the downstream side of the tip portion. .

  A blower device according to a third aspect of the present invention includes an air passage forming member including an inlet and an outlet, an output shaft, a drive motor provided inside the air passage forming member, and an output shaft. A propeller fan that includes a boss portion to be attached and a wing portion provided on an outer surface of the boss portion, and is disposed closer to the suction port than the drive motor, and the propeller fan extends from the drive motor. The airflow flowing from the upstream suction port toward the downstream discharge port is generated by rotating around a virtual rotation axis in response to the rotational power of the blade, and the wing portion is in the rotation direction of the propeller fan. A blade tip located at the most tip, a leading edge extending from the blade tip to the outer surface of the boss, and forming a leading edge of the blade in the rotational direction; and the boss External surface or The propeller fan extends outward in the rotational radial direction, and connects a trailing edge portion that forms a trailing edge of the wing portion in the rotational direction, and a wing tip portion and an outer end of the trailing edge portion. An outer peripheral edge portion that forms an outer peripheral edge of the wing portion in the rotational radius direction, and the air passage forming member is located on the downstream side of the first inner wall portion and the first inner wall portion. A second inner wall part having a narrower air passage area than the first inner wall part, and in the direction parallel to the rotation axis, the most upstream part of the second inner wall part is It is located on the upstream side of the most downstream portion of the boss portion, and is located on the downstream side of the blade tip portion of the blade portion.

  Preferably, the outer peripheral edge portion has a shape extending from the outer side toward the inner side in the rotational radius direction toward the blade tip portion.

  Preferably, when the propeller fan is rotating, a portion of the wing portion near the blade tip is elastically deformed by the action of centrifugal force, and a portion of the outer peripheral edge near the blade tip is Is rotating substantially along the circumferential direction.

  Preferably, the outer surface of the boss portion is continuous with the upstream end portion located on the most upstream side and the upstream end portion, and toward the outer side in the rotational radius direction of the propeller fan toward the downstream side. An upstream surface having a shape that extends, a downstream portion that is located downstream of the downstream end of the upstream surface, and a downstream surface that connects the downstream end of the upstream surface and the downstream portion, and The downstream surface has a shape extending along the parallel direction with respect to the rotation axis, or a shape extending toward the inner side of the rotation radial direction from the parallel direction toward the downstream portion.

  Preferably, the outer surface of the boss portion is located on the most upstream side, is continuous to the upstream end portion having a planar shape, and the outer edge of the upstream end portion, and is parallel to the rotation axis. An upstream surface having a shape extending along a direction, or a shape extending toward the inside in the rotational radial direction of the propeller fan as compared to the parallel direction toward the downstream side, and the downstream surface of the upstream surface. A downstream portion located downstream, and a downstream surface connecting the downstream end of the upstream surface and the downstream portion, and the downstream surface rotates more than the parallel direction toward the downstream portion. It has a shape extending inward in the radial direction.

  Preferably, the upstream surface has a substantially conical surface shape whose diameter increases toward the downstream side, and the downstream surface has a shape extending along the parallel direction with respect to the rotation axis.

Preferably, the inner angle of the boss portion at the upstream end is 50 ° or more.
Preferably, when the height dimension of the upstream surface in the direction parallel to the rotation axis is H and the height dimension of the downstream surface in the direction parallel to the rotation axis is h, h / The value of (H + h) is 1/5 or more.

  Preferably, the upstream surface has a substantially conical surface shape that increases in diameter toward the downstream side, and the downstream surface has a substantially conical surface shape that decreases in diameter toward the downstream side.

  Preferably, the outer surface of the boss portion is formed to be curved from the upstream surface toward the downstream surface.

  Preferably, the outer surface of the boss portion is formed to bend from the upstream surface toward the downstream surface.

  Preferably, it further includes a rectifying blade disposed on the downstream side of the propeller fan and having an upstream edge portion on the upstream side, and each of the trailing edge portion of the wing portion and the upstream edge portion of the rectifying blade is While looking at them from a direction perpendicular to the rotation axis in a state where they are opposed to each other, one of them is directed toward the other of these along the direction parallel to the rotation axis. A shape in which a gap is formed between them when they are virtually moved and brought into contact with each other, and / or they are viewed from the direction parallel to the rotation axis in a state where they are opposed to each other. Sometimes only some of these intersect.

  Preferably, when viewed from the direction perpendicular to the rotational axis, the innermost part of the trailing edge of the wing in the rotational radius direction and the trailing edge of the wing in the rotational radius direction A first imaginary straight line is formed so as to connect the outermost portion of the portion, and the innermost portion of the upstream edge portion of the rectifying blade in the rotational radius direction and the upstream edge of the rectifying blade in the rotational radius direction A second imaginary straight line is formed so as to connect the outermost part of the part, and an angle formed by the first imaginary straight line and the second imaginary straight line is not less than 10 ° and not more than 80 °.

  Preferably, when viewed from the direction parallel to the rotational axis, the innermost part of the trailing edge of the wing in the rotational radial direction and the trailing edge of the wing in the rotational radial direction A third imaginary straight line is formed so as to connect the outermost portion of the portion, and the innermost portion of the upstream edge portion of the rectifying blade in the rotational radius direction and the upstream edge of the rectifying blade in the rotational radius direction A fourth virtual straight line is formed so as to connect the outermost part of the part, and an angle formed by the third virtual straight line and the fourth virtual straight line is not less than 10 ° and not more than 90 °.

  Preferably, each of the trailing edge portion of the wing portion and the upstream edge portion of the rectifying wing is viewed from the direction perpendicular to the rotation axis in a state where they are opposed to each other. A shape in which a gap is formed between them when they are virtually moved toward the other of them along the direction parallel to the rotation axis and brought into contact with each other, and When these are viewed from the direction parallel to the rotation axis in a state where they are opposed to each other, only a part of them intersect.

  Preferably, if the number of the blades is M and the number of the rectifying blades is N, both M and N are prime numbers, and the relationship 2M ± 1 = N or 2N ± 1 = M is established. .

  Preferably, in the direction parallel to the rotation axis, the narrowest gap formed between the blade portion and the rectifying blade is 3 mm or less.

  Preferably, in the direction parallel to the rotation axis, the output shaft is located on the upstream side of the most downstream portion of the boss portion.

  ADVANTAGE OF THE INVENTION According to this invention, the air blower which can suppress that foreign materials, such as the hair or dust which were suck | inhaled with air from the suction inlet, entangled with the output shaft of a drive motor can be obtained.

It is sectional drawing which shows the air blower in the comparative example 1. It is sectional drawing which expands and shows the area | region enclosed by the II line | wire in FIG. It is a side view which shows the propeller fan used for the air blower in the comparative example 1. It is a top view which shows the propeller fan used for the air blower in the comparative example 1. It is sectional drawing which shows a mode when the propeller fan used for the air blower in the comparative example 1 is rotating. It is a figure which shows typically a mode that a part of air which was flowing along the outer surface of the boss | hub part used for the air blower in the comparative example 1 is sucked in the inside of a boss | hub part. It is a figure which shows typically a mode that a part of air which was flowing along the outer surface of the boss | hub part used for the air blower in the modification of the comparative example 1 is sucked in the inside of a boss | hub part. It is a figure which shows typically a mode that a part of air which was flowing along the outer surface of the boss | hub part used for the air blower in the other modification of the comparative example 1 is sucked in the inside of a boss | hub part. FIG. 3 is a cross-sectional view showing the air blower in the first embodiment. It is sectional drawing which expands and shows the area | region enclosed by the X-ray in FIG. FIG. 3 is a side view showing a propeller fan used in the air blower in the first embodiment. 2 is a plan view showing a propeller fan used in the blower in Embodiment 1. FIG. It is sectional drawing which shows a mode when the propeller fan used for the air blower in Embodiment 1 is rotating. It is a figure which shows typically a mode when the boss | hub part used for the air blower in Embodiment 1 is rotating. 6 is a diagram schematically showing a boss portion in a first modification of the first embodiment. FIG. It is a figure which shows typically the boss | hub part in the 2nd modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 3rd modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 4th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 5th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 6th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 7th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 8th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 9th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 10th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 11th modification of Embodiment 1. FIG. It is a figure which shows typically the boss | hub part in the 12th modification of Embodiment 1. FIG. FIG. 6 is a diagram schematically showing a boss portion used in Experimental example 1 related to the first embodiment. It is a figure which shows the conditions and result of Experimental example 1 regarding Embodiment 1, and has shown the relationship between the internal angle of an upstream edge part, and the number of the hair wound in the output shaft of a drive motor. It is a figure which shows the conditions and result of Experimental example 1 regarding Embodiment 1, and has shown the relationship between the value of h / (H + h) and the number of the hairs wound in the output shaft of a drive motor. It is a figure which shows typically the boss | hub part used for Experimental example 2 regarding Embodiment 1. FIG. It is a figure which shows the conditions and result of Experimental example 2 regarding Embodiment 1, and has shown the relationship between the value of h / (H + h) and the number of the hairs wound in the output shaft of a drive motor. Regarding Experimental Example 2 related to the first embodiment, the value of the inner angle of the upstream end when the average value of the number of entangled hairs is 2, and the h / (when the average value of the number of entangled hairs is two. It is a figure which shows the relationship with the value of H + h). It is a side view which shows the propeller fan used for the air blower in the comparative example 2. It is sectional drawing which shows a mode when the propeller fan used for the air blower in the comparative example 2 is rotating. FIG. 6 is a side view showing a propeller fan used in a blower device in a second embodiment. It is sectional drawing which shows a mode when the propeller fan used for the air blower in Embodiment 2 is rotating. It is a figure which shows the conditions and result of Experimental example 3 regarding Embodiment 2, and has shown the relationship between the value of hb / ha and the number of the hair caught in the output shaft of a drive motor. It is a figure which shows partially the air blower used for Experimental example 4 regarding Embodiment 2. FIG. It is a figure which shows the conditions and result of Experimental example 4 regarding Embodiment 2. FIG. It is a top view which shows the propeller fan used for the air blower in the comparative example 3. FIG. 10 is a plan view showing a propeller fan in a first modification example of the second embodiment. FIG. 11 is a plan view showing a state when the propeller fan in the first modification of the second embodiment is rotating. It is a figure which shows partially the air blower in the 2nd modification of Embodiment 2. FIG. It is a figure which shows partially the air blower in the 3rd modification of Embodiment 2. FIG. It is a top view which shows the propeller fan and rectifier blade in Embodiment 3 (The state where the propeller fan is not attached to the drive motor is shown). It is a top view which shows the propeller fan and rectifier blade in Embodiment 3 (The state where the propeller fan is attached to the drive motor is shown). It is a top view which expands and shows the area | region enclosed by the XKVII line | wire in FIG. It is a figure which shows the conditions and result of Experimental example 5 regarding Embodiment 3. FIG. FIG. 10 is a plan view schematically showing a propeller fan and a rectifying blade in a first modification of the third embodiment. FIG. 10 is a plan view schematically showing a propeller fan and a rectifying blade in a second modification example of the third embodiment. FIG. 10 is a plan view schematically showing a propeller fan and a rectifying blade in a third modification of the third embodiment. FIG. 10 is a plan view schematically showing a propeller fan and a rectifying blade in a fourth modification example of the third embodiment. FIG. 25 is a plan view schematically showing a propeller fan and a rectifying blade in a fifth modification example of the third embodiment. FIG. 25 is a plan view schematically showing a propeller fan and a rectifying blade in a sixth modification example of the third embodiment. FIG. 25 is a plan view schematically showing a propeller fan and a rectifying blade in a seventh modification example of the third embodiment. FIG. 29 is a plan view schematically showing a wing part of a propeller fan and an upstream edge part of a rectifying blade in an eighth modification example of the third embodiment. FIG. 25 is a plan view schematically showing a wing part of a propeller fan and an upstream edge part of a rectifying blade in a ninth modification example of the third embodiment. FIG. 29 is a plan view schematically showing a blade portion of a propeller fan and an upstream edge portion of a rectifying blade in a tenth modification example of the third embodiment. FIG. 25 is a plan view schematically showing a blade portion of a propeller fan and an upstream edge portion of a rectifying blade in an eleventh modification example of the third embodiment. FIG. 29 is a plan view schematically showing a blade portion of a propeller fan and an upstream edge portion of a rectifying blade in a twelfth modification of the third embodiment. FIG. 38 is a plan view schematically showing a blade portion of a propeller fan and an upstream edge portion of a rectifying blade in a thirteenth modification example of the third embodiment. FIG. 29 is a plan view schematically showing a blade portion of a propeller fan and an upstream edge portion of a rectifying blade in a fourteenth modified example of the third embodiment. FIG. 29 is a plan view schematically showing a blade portion of a propeller fan and an upstream edge portion of a rectifying blade in a fifteenth modification example of the third embodiment. FIG. 38 is a plan view schematically showing a blade portion of a propeller fan and an upstream edge portion of a rectifying blade in a sixteenth modification example of the third embodiment. 10 is a cross-sectional view showing a propeller fan and a rectifying blade in a fourth embodiment. FIG. 6 is an enlarged cross-sectional view showing a propeller fan and a rectifying blade in a fourth embodiment. It is a figure which shows the conditions and result of Experimental example 6 regarding Embodiment 4. FIG. FIG. 10 is a cross-sectional view showing a propeller fan and a rectifying blade in a first modification of the fourth embodiment. FIG. 10 is a cross-sectional view showing a propeller fan and a rectifying blade in a second modification of the fourth embodiment. FIG. 10 is a cross-sectional view showing a propeller fan and a rectifying blade in a third modification of the fourth embodiment. FIG. 10 is a cross-sectional view showing a propeller fan and a rectifying blade in a fourth modification of the fourth embodiment. FIG. 10 is a cross-sectional view showing a propeller fan and a rectifying blade in a fifth modification of the fourth embodiment. FIG. 25 is a side view schematically showing a blade portion and a rectifying blade of a propeller fan in a sixth modification example of the fourth embodiment. FIG. 25 is a side view schematically showing a blade portion and a rectifying blade of a propeller fan in a seventh modification example of the fourth embodiment. FIG. 29 is a side view schematically showing a wing part and a rectifying blade of a propeller fan in an eighth modification example of the fourth embodiment. FIG. 25 is a side view schematically showing a blade portion and a rectifying blade of a propeller fan in a ninth modification example of the fourth embodiment. FIG. 29 is a side view schematically showing a propeller fan blade and a rectifying blade in a tenth modification of the fourth embodiment. FIG. 29 is a side view schematically showing a blade portion and a rectifying blade of a propeller fan in an eleventh modification example of the fourth embodiment. FIG. 25 is a side view schematically showing a propeller fan blade portion and a rectifying blade in a twelfth modification of the fourth embodiment. FIG. 25 is a side view schematically showing a blade portion and a rectifying blade of a propeller fan in a thirteenth modification example of the fourth embodiment. FIG. 25 is a side view schematically showing a blade portion and a rectifying blade of a propeller fan in a fourteenth modification example of the fourth embodiment.

[Comparative Example 1]
Before explaining each embodiment and each experimental example based on this invention, the comparative example 1 regarding this invention is demonstrated. In the description of the comparative example, the same parts and corresponding parts are denoted by the same reference numerals, and the repeated description may not be repeated.

(Blower 100)
FIG. 1 is a cross-sectional view showing an air blower 100 in this comparative example. The blower 100 includes a main body 10 and a grip 20. The grip part 20 is a part gripped by the user. An operation unit 23 is provided on the surface of the grip unit 20. The tip 21 of the grip 20 is rotatably attached to the main body 10. A power cord 24 is provided at the rear end 22 of the grip 20.

  The main body 10 includes an outer case 11, an inner case 12, a drive motor 30, a propeller fan 50 </ b> Z, a rectifying blade 40 </ b> Z, and a heater 17. The outer case 11 and the inner case 12 each have a substantially cylindrical shape. The outer case 11 has an inlet opening 13 and an outlet opening 14. The inlet opening 13 communicates with the outlet opening 14, and an air passage is formed between the inlet opening 13 and the outlet opening 14.

  An inner case 12 as an air path forming member is disposed inside the outer case 11. The inner case 12 has a suction port 15 and a discharge port 16. In a state where the inner case 12 is disposed inside the outer case 11, the suction port 15 is located on the inlet opening 13 side of the outer case 11, and the discharge port 16 is located on the outlet opening 14 side of the outer case 11.

  The drive motor 30, the propeller fan 50 </ b> Z, and the rectifying blade 40 </ b> Z are provided inside the inner case 12. A motor support 44 (see FIG. 2) is provided inside the rectifying blade 40Z. The drive motor 30 is supported by the motor support portion 44. The drive motor 30 is arranged such that its output shaft 31 (see FIG. 2) is substantially parallel to the longitudinal direction of the main body 10.

  The propeller fan 50Z is attached to the drive motor 30. Propeller fan 50Z is disposed closer to suction port 15 than drive motor 30 is. The propeller fan 50Z is disposed such that the rotation axis of the propeller fan 50Z (see the rotation axis 80 in FIG. 2) is substantially parallel to the longitudinal direction of the main body portion 10. The drive motor 30 rotates the propeller fan 50 </ b> Z by being supplied with power through the power cord 24.

  The propeller fan 50Z receives the rotational power from the drive motor 30 and rotates around the rotation axis, and the airflow (air) flowing from the upstream inlet opening 13 and the suction port 15 toward the downstream discharge port 16 and the outlet opening 14 Flow). The heater 17 is disposed closer to the outlet opening 14 than the propeller fan 50Z.

  FIG. 2 is an enlarged cross-sectional view of a region surrounded by line II in FIG. For convenience of illustration, the cross-sectional view of FIG. 2 is illustrated such that the suction port 15 is located above the paper surface and the discharge port 16 is located below the paper surface. As described above, the drive motor 30, the propeller fan 50Z, and the rectifying blade 40Z are provided inside the inner case 12. A motor support 44 is provided inside the rectifying blade 40Z.

  The motor support 44 has a peripheral wall 44A, a bottom wall 44B, and a hole 44C. The peripheral wall 44A has a cylindrical shape. The central axis of the peripheral wall 44A and the central axis of the inner case 12 are located on substantially the same straight line. The bottom wall 44B has a disc shape and is provided so as to close the upstream end of the peripheral wall 44A. The hole 44C is provided at the center of the bottom wall 44B. When the drive motor 30 is fitted inside the peripheral wall 44A, the output shaft 31 of the drive motor 30 jumps out of the hole 44C toward the upstream side.

  The rectifying blade 40Z is disposed on the downstream side of the propeller fan 50Z. The rectifying blade 40 </ b> Z includes a plate-like portion 42. The plate-like portion 42 extends radially outward from the outer surface of the motor support portion 44 (circumferential wall 44A). The plate-like portions 42 are arranged at intervals in the circumferential direction so as not to reduce the flow rate of the airflow flowing from the suction port 15 toward the discharge port 16. The plate-like portion 42 has an upstream edge portion 43 on the upstream side. The upstream edge portion 43 of this comparative example has a planar shape and extends along a direction perpendicular to the rotation shaft 80 of the propeller fan 50Z.

(Propeller fan 50Z)
FIG. 3 is a side view showing the propeller fan 50Z. FIG. 4 is a plan view showing the propeller fan 50Z. Propeller fan 50Z is integrally manufactured as a resin molded product using a synthetic resin such as an AS (acrylonitrile-styrene) resin. Propeller fan 50Z receives rotational power from drive motor 30 (see FIG. 2) and rotates in the direction of arrow AR1 around rotating shaft 80 (see FIG. 3).

  As shown in FIGS. 2 to 4, the propeller fan 50 </ b> Z includes a boss portion 60 </ b> Z and seven wing portions 70 </ b> Z. The propeller fan 50Z in this comparative example has a rotationally symmetric shape. The rotational symmetry referred to here is a rotation angle of 2π / n radians (n is a positive integer and n = 7 in this comparative example) when the propeller fan 50Z is rotated around the rotation axis 80. This means that the same figure is repeated. When the propeller fan 50Z rotates one of the blade portions 70Z around the rotation shaft 80 at a rotation angle of 360/7 = about 51.4 (°), the other blade portion adjacent to the blade portion 70Z. It has the property of overlapping with 70Z.

(Boss 60Z)
The boss portion 60 </ b> Z rotates in the direction of the arrow AR <b> 1 about the virtual rotation shaft 80 by receiving the rotational power from the drive motor 30. Boss portion 60 </ b> Z includes an outer surface 61, an inner surface 68 and a bearing portion 69. The boss part 60Z has a rotationally symmetric shape as a whole, and the outer surface 61 of the boss part 60Z has a hemispherical shape as a whole. An upstream end 62 is formed at the most upstream position (vertex) of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan 50Z is rotating.

  A main flow surface 63 is formed at an intermediate position of the outer surface 61 in a direction parallel to the rotation shaft 80. The main flow surface 63 has a hemispherical shape continuous to the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan 50Z toward the downstream side. A downstream portion 67 is formed at the most downstream position of the outer surface 61. The downstream portion 67 is located at the downstream end of the main flow surface 63. When the downstream portion 67 is viewed in plan (see FIG. 4), the downstream portion 67 has a circular shape.

  The inner surface 68 of the boss portion 60Z is formed inside the outer surface 61. The bearing portion 69 has a cylindrical shape and is provided at the center position of the inner surface 68. The bearing portion 69 is a part that connects the propeller fan 50Z to the output shaft 31 (see FIG. 2) of the drive motor 30 (see FIG. 2).

(Wings 70Z)
The seven blade portions 70Z are provided on the outer surface 61 of the boss portion 60Z, and have a shape extending from the outer surface 61 toward the outer side in the rotational radius direction of the propeller fan 50Z. The seven wing portions 70Z have the same shape. The seven blade portions 70Z are arranged side by side at equal intervals in the rotation direction of the propeller fan 50Z (arrow AR1 direction).

  When the seven wing parts 70Z rotate in the direction of the arrow AR1 about the rotation shaft 80, the seven wing parts 70Z rotate integrally with the boss part 60Z. The seven blades 70Z rotate about the rotation shaft 80, thereby causing an air flow (from the upper side to the lower side in FIG. 3) to flow from the suction port 15 (see FIG. 2) toward the discharge port 16 (see FIG. 2). Airflow that flows toward the

  With reference to FIGS. 3 and 4, the wing part 70 </ b> Z has a wing tip part 71, a leading edge part 72, a root part 73, a trailing edge part 74, a wing trailing edge part 75, and an outer peripheral edge part 76. The blade tip 71 is located at the most tip (front side) in the rotation direction (arrow AR1 direction) of the propeller fan 50Z. The leading edge 72 extends from the blade tip 71 to the outer surface 61 of the boss 60Z, and forms the leading edge of the blade 70Z in the rotational direction. The front edge portion 72 of the present comparative example extends so as to be substantially along a direction perpendicular to the rotation shaft 80 of the propeller fan 50Z (see FIG. 3). The root portion 73 is formed (boundary) between the wing portion 70Z and the outer surface 61 of the boss portion 60Z.

  The trailing edge portion 74 extends from the outer surface 61 of the boss portion 60Z toward the outer side in the rotational radial direction, and forms the trailing edge of the blade portion 70Z in the rotational direction (arrow AR1 direction) of the propeller fan 50Z. When the propeller fan 50Z is viewed from a direction orthogonal to the rotation shaft 80 (in other words, when the propeller fan 50Z is viewed from the side), the rear edge portion 74 of this comparative example is connected to the rotation shaft 80 of the propeller fan 50Z. It extends along a direction perpendicular to the surface (see FIG. 3). The blade trailing edge 75 is formed at the outermost edge (outer edge) of the trailing edge 74 in the rotational radius direction. The outer peripheral edge 76 connects the blade tip 71 and the blade trailing edge 75, and forms the outer periphery of the blade 70Z in the rotational radius direction.

  More specifically, the wing portion 70Z has a sickle shape with the wing tip portion 71 as a tip. The wing portion 70 </ b> Z has a shape in which the width in the direction along the rotation direction between the front edge portion 72 and the rear edge portion 74 gradually decreases toward the inner side in the rotation radius direction. In other words, the wing portion 70 </ b> Z has a shape in which the width in the direction along the rotational direction between the front edge portion 72 and the rear edge portion 74 gradually increases toward the outside in the rotational radius direction.

  The leading edge 72 is located on the front side in the rotation direction (arrow AR1 direction) of the wing part 70Z, and forms the leading edge of the wing part 70Z in the rotation direction. When the propeller fan 50Z is viewed from a direction parallel to the rotation axis 80 (in other words, when the propeller fan 50Z is viewed in plan), the front edge portion 72 has a front end portion in the rotation direction of the root portion 73. As a starting point, it extends substantially linearly from the inner side in the rotational radius direction toward the outer side in the same direction. As described above, when the propeller fan 50Z is viewed from a direction orthogonal to the rotation shaft 80 (in other words, when the propeller fan 50Z is viewed from the side), the front edge portion 72 of this comparative example is the same as the propeller fan 50Z. It extends so as to be substantially along a direction perpendicular to the rotation shaft 80 (see FIG. 3).

  The blade tip 71 is positioned at the outermost tip (front side) of the blade 70Z in the rotational direction (arrow AR1 direction), and is positioned at the outermost side in the rotational radius direction of the leading edge 72. The blade tip portion 71 is a portion where the front edge portion 72 and the outer peripheral edge portion 76 are connected, and is a portion where the radius of curvature is minimized between the front edge portion 72 and the outer peripheral edge portion 76.

  The trailing edge portion 74 is located on the rear side in the rotation direction (arrow AR1 direction) of the wing portion 70Z, and forms the trailing edge of the wing portion 70Z in the rotation direction. When the propeller fan 50Z is viewed from a direction parallel to the rotation shaft 80 (in other words, when the propeller fan 50Z is viewed in plan), the rear edge portion 74 is the rear end portion in the rotation direction of the root portion 73. Starting from the inside in the radial direction of rotation and extending outward in the same direction. As described above, when the propeller fan 50Z is viewed from a direction orthogonal to the rotation shaft 80 (in other words, when the propeller fan 50Z is viewed from the side), the trailing edge portion 74 of this comparative example is the same as the propeller fan 50Z. It extends linearly along a direction perpendicular to the rotation shaft 80 (see FIG. 3).

  The blade trailing end 75 is located on the outermost side in the radial direction of rotation at the trailing edge 74. The blade trailing end portion 75 is a portion where the trailing edge portion 74 and the outer peripheral edge portion 76 are connected, and is a portion where the radius of curvature is minimized between the trailing edge portion 74 and the outer peripheral edge portion 76. In the propeller fan 50Z of this comparative example, the blade tip portion 71 and the blade trailing end portion 75 are located on substantially the same circle.

  The outer peripheral edge 76 extends along the rotation direction of the wing 70 </ b> Z (the circumferential direction around the rotation shaft 80), and is provided so as to connect between the wing tip 71 and the wing trailing edge 75. The outer peripheral edge portion 76 of this comparative example extends in an arc shape between the blade tip portion 71 and the blade trailing end portion 75 as a whole. In other words, when the propeller fan 50Z is viewed from a direction parallel to the rotation shaft 80 (in other words, when the propeller fan 50Z is viewed in plan), the rotation shaft 80 (upstream end portion 62) and the blade tip portion 71 are The dimension between them and the dimension between the rotary shaft 80 (upstream end 62) and the blade trailing end 75 are the same value.

  The blade tip 71, the leading edge 72, the root 73, the trailing edge 74, the blade trailing end 75, and the outer peripheral edge 76 form the periphery of the blade 70Z. The wing surface of the wing part 70Z is formed in the entire region inside the region surrounded by the periphery. The blade surface of the wing portion 70Z has a shape in which the leading edge portion 72 is located on the upstream side in the airflow direction and the trailing edge portion 74 is located on the downstream side in the airflow direction. In other words, the blade surface of the wing portion 70Z as a whole moves from the suction port 15 (see FIG. 2) side to the discharge port 16 (see FIG. 2) side as it goes from the front edge portion 72 to the rear edge portion 74. It is formed to be smoothly curved (see FIG. 3).

  When the propeller fan 50Z is rotating, a pressure surface is formed on the surface of the blade surface of the blade portion 70Z on the discharge port 16 side, and a suction surface is formed on the surface of the suction port 15 of the blade surface. When the propeller fan 50Z is rotating, the blade surface of the blade portion 70Z generates an airflow that flows from the suction port 15 toward the discharge port 16. When propeller fan 50Z is rotating, an air flow is generated on the blade surface, and a pressure distribution that is relatively large on the pressure surface and relatively small on the suction surface is generated.

  FIG. 5 is a cross-sectional view showing a state when the propeller fan 50Z is rotating. Propeller fan 50Z receives rotational power from drive motor 30 and rotates in the direction of arrow AR1, and generates an airflow (see arrow DR1) that flows from suction port 15 toward discharge port 16. As indicated by the arrow DR1, the airflow from the suction port 15 flows from the upstream side toward the downstream side along the blade surface of the blade portion 70Z and the outer surface 61 of the boss portion 60Z.

  As the wing portion 70Z rotates, a wing tip vortex is generated in the vicinity of the wing tip portion 71 (see FIGS. 3 and 4) of the wing portion 70Z (see arrow DR3). The blade tip vortex is generated so as to extend toward the rear side in the rotation direction (arrow AR1 direction) with the vicinity of the blade tip 71 as a tip.

  On the other hand, when the propeller fan 50Z is rotating, the air existing inside the boss portion 60Z is also rotated by the inner surface 68 of the boss portion 60Z. Centrifugal force is generated in the air existing inside the boss portion 60Z with rotation. A negative pressure is generated in the vicinity of the downstream portion 67 of the boss portion 60Z by the air in which the centrifugal force is generated and the air flowing through the space around the boss portion 60Z where the wing portion 70Z is not provided. In the vicinity of the downstream portion 67 of the boss portion 60Z, a vortex (see arrow DR2) is generated by the action of this negative pressure.

  As indicated by the arrow DR2, a part of the air (arrow DR1) flowing along the outer surface 61 is folded back around the downstream portion 67 of the boss portion 60Z under the action of this vortex, and toward the inner surface 68 side. It flows so as to be sucked into the boss 60Z.

  FIG. 6 is a diagram schematically illustrating a state in which a part of the air flowing along the outer surface 61 is sucked into the boss portion 60Z. As indicated by an arrow DR4 in FIG. 6, the outer surface 61 of the boss portion 60Z has a hemispherical shape as a whole, so that a part of the air flowing along the outer surface 61 is It flows around the downstream portion 67 of 60Z so as to be sucked into the boss portion 60Z.

  When the blower 100 (see FIG. 1) is used, foreign matter such as hair or dust may be sucked into the blower 100 together with air from the inlet opening 13 (see FIG. 1). Foreign matter such as hair is sucked into the boss portion 60Z by riding on the air flow indicated by the arrow DR4 (see FIG. 6). When foreign matters such as hair get entangled with the output shaft 31 of the drive motor 30, not only the air blowing efficiency is lowered, but foreign matters such as hair may induce a failure.

(Boss 60ZA)
Referring to FIG. 7, the same phenomenon as described above can occur in boss portion 60ZA. The outer surface 61 of the boss portion 60ZA has a cylindrical surface shape as a whole. The outer surface 61 of the boss portion 60ZA includes an upstream end portion 62, a main flow surface 63, and a downstream portion 67. The upstream end portion 62 is located on the most upstream side of the boss portion 60ZA and has a planar shape. The main flow surface 63 is continuous with the outer edge of the upstream end portion 62 and has a shape extending along a direction parallel to the rotation axis 80. The downstream portion 67 is located at the downstream end of the main flow surface 63.

  When the propeller fan is rotating, the air present inside the boss portion 60ZA is also rotated by the inner surface of the boss portion 60ZA. Centrifugal force is generated in the air existing inside the boss portion 60ZA as it rotates. A negative pressure is generated in the vicinity of the downstream portion 67 of the boss portion 60ZA by the air in which the centrifugal force is generated and the air flowing through the space around the boss portion 60ZA where the wing portion is not provided. In the vicinity of the downstream portion 67 of the boss portion 60ZA, a vortex is generated by the action of this negative pressure.

  As indicated by an arrow DR4, the outer surface 61 of the boss portion 60ZA has a cylindrical surface shape as a whole, so that part of the air flowing along the outer surface 61 is downstream of the boss portion 60ZA. It folds around 67 and flows so as to be sucked into the boss 60ZA. Foreign matter such as hair may be sucked into the boss portion 60ZA by the air flow indicated by the arrow DR4 and entangled with the output shaft 31 of the drive motor 30.

(Boss 60ZB)
Referring to FIG. 8, the same phenomenon as described above can occur in boss portion 60ZB. The outer surface 61 of the boss 60ZB has a conical shape as a whole. The outer surface 61 of the boss portion 60ZB includes an upstream end portion 62, a main flow surface 63, and a downstream portion 67. The upstream end portion 62 is located on the most upstream side of the boss portion 60ZB. The main flow surface 63 is continuous with the upstream end portion 62 and extends so as to increase in diameter toward the outer side in the rotational radial direction toward the downstream side. The downstream portion 67 is located at the downstream end of the main flow surface 63.

  When the propeller fan is rotating, the air present inside the boss 60ZB is also rotated by the inner surface of the boss 60ZB. Centrifugal force is generated in the air existing inside the boss portion 60ZB as it rotates. A negative pressure is generated in the vicinity of the downstream portion 67 of the boss portion 60ZB by the air in which the centrifugal force is generated and the air flowing through the space around the boss portion 60ZB where no wing portion is provided. In the vicinity of the downstream portion 67 of the boss portion 60ZB, a vortex is generated by the action of this negative pressure.

  As indicated by the arrow DR4, the outer surface 61 of the boss portion 60ZB has a conical shape as a whole, so that part of the air flowing along the outer surface 61 is downstream of the boss portion 60ZB. It folds around 67 and flows so as to be sucked into the boss 60ZB. Foreign matter such as hair may be sucked into the boss portion 60ZB on the air flow indicated by the arrow DR4 and entangled with the output shaft 31 of the drive motor 30.

[Embodiment]
Embodiments and experimental examples based on the present invention will be described below with reference to the drawings. In the description of each embodiment and each experimental example, when the number and amount are referred to, the scope of the present invention is not necessarily limited to the number and amount unless otherwise specified. In the description of each embodiment and each experimental example, the same parts and corresponding parts are denoted by the same reference numerals, and redundant description may not be repeated. Unless there is a restriction | limiting in particular, it is planned from the beginning to use suitably combining the structure shown in each embodiment, and the structure shown in each experiment example.

[Embodiment 1]
(Blower 200)
FIG. 9 is a cross-sectional view showing a blower device 200 in the present embodiment. The blower device 200 includes a main body 10 and a grip 20. The grip part 20 is a part gripped by the user. An operation unit 23 is provided on the surface of the grip unit 20. The tip 21 of the grip 20 is rotatably attached to the main body 10. A power cord 24 is provided at the rear end 22 of the grip 20.

  When using the air blower 200, the main-body part 10 and the holding part 20 form the shape of a substantially T shape or a substantially L shape as a whole. When the blower 200 is housed, the grip 20 can be rotated to a position along the main body 10. The air blower 200 can be easily accommodated by folding the grip 20.

  The main body 10 includes an outer case 11, an inner case 12, a drive motor 30, a propeller fan 50, rectifying blades 40, and a heater 17. The outer case 11 and the inner case 12 each have a substantially cylindrical shape. The outer case 11 has an inlet opening 13 and an outlet opening 14. The inlet opening 13 communicates with the outlet opening 14, and an air passage is formed between the inlet opening 13 and the outlet opening 14.

  An inner case 12 as an air path forming member is disposed inside the outer case 11. The inner case 12 has a suction port 15 and a discharge port 16. In a state where the inner case 12 is disposed inside the outer case 11, the suction port 15 is located on the inlet opening 13 side of the outer case 11, and the discharge port 16 is located on the outlet opening 14 side of the outer case 11.

  The drive motor 30, the propeller fan 50 and the rectifying blade 40 are provided inside the inner case 12. A motor support 44 (see FIG. 10) is provided inside the rectifying blade 40. The drive motor 30 is supported by the motor support portion 44. The drive motor 30 is arranged such that its output shaft 31 (see FIG. 10) is substantially parallel to the longitudinal direction of the main body 10.

  The propeller fan 50 is attached to the drive motor 30. The propeller fan 50 is disposed closer to the suction port 15 than the drive motor 30. Propeller fan 50 is arranged such that the rotation axis of propeller fan 50 (see rotation axis 80 in FIG. 10) is substantially parallel to the longitudinal direction of main body 10. The drive motor 30 rotates the propeller fan 50 by being supplied with power through the power cord 24.

  The propeller fan 50 receives the rotational power from the drive motor 30 and rotates around the rotation axis, and the airflow (air) flowing from the upstream side inlet opening 13 and the suction port 15 toward the downstream side discharge port 16 and the outlet opening 14. Flow). The heater 17 is disposed closer to the outlet opening 14 than the propeller fan 50.

  The operating state of the heater 17 is switched by operating the operation unit 23. When the heater 17 is in the ON state, warm air is blown out from the outlet opening 14. When the heater 17 is in the OFF state, cold air is blown out from the outlet opening 14. The operation state of the heater 17 may include a mode in which the ON state and the OFF state are periodically switched. As the temperature of the wind blown from the outlet opening 14 changes with time, the warmed scalp is tightened with cold air, the warmed hair is tightened, a cuticle is formed on the hair, etc. It becomes possible.

  FIG. 10 is an enlarged cross-sectional view of a region surrounded by X-rays in FIG. For convenience of illustration, the cross-sectional view of FIG. 10 is illustrated such that the suction port 15 is located above the paper surface and the discharge port 16 is located below the paper surface. As described above, the drive motor 30, the propeller fan 50, and the rectifying blade 40 are provided inside the inner case 12. A motor support 44 is provided inside the rectifying blade 40.

  The motor support portion 44 has a peripheral wall 44A, a bottom wall 44B, a hole 44C, and an annular wall 46. The peripheral wall 44A has a cylindrical shape. The central axis of the peripheral wall 44A and the central axis of the inner case 12 are located on substantially the same straight line. The bottom wall 44B has a disc shape and is provided so as to close the upstream end of the peripheral wall 44A. The hole 44C is provided at the center of the bottom wall 44B. When the drive motor 30 is fitted inside the peripheral wall 44A, the output shaft 31 of the drive motor 30 jumps out of the hole 44C toward the upstream side. The annular wall 46 is provided on the upstream surface of the bottom wall 44 </ b> B, and surrounds the output shaft 31 with a space from the output shaft 31.

  The rectifying blade 40 is disposed on the downstream side of the propeller fan 50. The rectifying blade 40 includes a plate-like portion 42. The plate-like portion 42 extends radially outward from the outer surface of the motor support portion 44 (circumferential wall 44A). The plate-like portions 42 are arranged at intervals in the circumferential direction so as not to reduce the flow rate of the airflow flowing from the suction port 15 toward the discharge port 16. The plate-like portion 42 has an upstream edge portion 43 on the upstream side. The upstream edge 43 of the present embodiment has a planar shape and extends along a direction perpendicular to the rotation shaft 80 of the propeller fan 50.

(Propeller fan 50)
FIG. 11 is a side view showing the propeller fan 50. FIG. 12 is a plan view showing the propeller fan 50. The propeller fan 50 is integrally manufactured as a resin molded product using a synthetic resin such as an AS (acrylonitrile-styrene) resin. The propeller fan 50 receives rotational power from the drive motor 30 (see FIG. 10) and rotates around the rotation shaft 80 (see FIG. 11) in the direction of the arrow AR1.

  As shown in FIGS. 10 to 12, the propeller fan 50 includes a boss portion 60 and three wing portions 70. Propeller fan 50 in the present embodiment has a rotationally symmetric shape. The rotational symmetry here refers to a rotation angle of 2π / n radians (where n is a positive integer and n = 3 in the present embodiment) when the propeller fan 50 is rotated about the rotation axis 80. Means that the same figure is repeated. When the propeller fan 50 rotates one of the blade portions 70 around the rotation shaft 80 at a rotation angle of 360/3 = 120 (°), the propeller fan 50 overlaps the other blade portions 70 adjacent to the blade portion 70. It has the property of

  Propeller fan 50 may be manufactured, for example, by twisting a single sheet metal, or may be manufactured from an integral thin-walled object formed with a curved surface. In these cases, the propeller fan may have a structure in which three blade portions 70 are joined to a separately formed boss portion 60. The propeller fan 50 may include a plurality of blade portions 70 other than three, or may include only one blade portion 70. When the propeller fan 50 includes only one wing portion 70, a weight as a balancer may be provided on the opposite side of the wing portion 70 with respect to the rotation shaft 80.

(Boss 60)
The boss 60 rotates in the direction of the arrow AR1 about the virtual rotation shaft 80 by receiving the rotational power from the drive motor 30. Boss portion 60 includes an outer surface 61, an inner surface 68 and a bearing portion 69. The boss part 60 has a rotationally symmetric shape as a whole.

  The outer surface 61 of the boss 60 includes an upstream end 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan 50 is rotating. The upstream surface 64 has a substantially conical shape continuous to the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan 50 toward the downstream side.

  The substantially conical surface shape referred to here means a surface shape in which the cross-sectional shape of the upstream surface 64 in the direction along the rotation axis 80 is a substantially straight line. The substantially conical surface includes a case where a portion of the upstream surface 64 near the upstream end 62 and a portion of the upstream surface 64 near the downstream end 65 are appropriately curved. The shape of the upstream surface 64 may be formed so as to be curved as a whole as long as it extends toward the outer side in the rotational radial direction of the propeller fan 50 toward the downstream side. A shape that is curved in a direction approaching the axis and a shape in which the conical surface is curved away from the axis are also included in the “substantially conical surface”.

  In other words, the outer surface 61 of the boss portion 60 may be formed to be curved from the upstream surface 64 toward the downstream surface 66, or formed to bend from the upstream surface 64 toward the downstream surface 66. It may be. The shape of the upstream surface 64 has a hemispherical shape continuous to the upstream end portion 62, and the diameter increases toward the outer side in the rotational radial direction of the propeller fan 50 toward the downstream side (downstream end 65 of the upstream surface 64). It may extend so that.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. When the downstream end 65 of the upstream surface 64 is viewed in plan (see FIG. 12), the downstream end 65 of the upstream surface 64 has a circular shape. The downstream portion 67 (see FIG. 11) is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of the present embodiment is located on the most downstream side of the outer surface 61 as a whole. The outer surface 61 may have another part further downstream of the downstream part 67.

  The downstream surface 66 is formed so as to connect the downstream end 65 and the downstream portion 67 of the upstream surface 64. The downstream surface 66 of the present embodiment has a cylindrical surface shape as a whole and extends along a direction parallel to the rotation axis 80. The inner surface 68 of the boss part 60 is formed inside the outer surface 61. The bearing portion 69 has a cylindrical shape and is provided at the center position of the inner surface 68. The bearing 69 is a part that connects the propeller fan 50 to the output shaft 31 (see FIG. 10) of the drive motor 30 (see FIG. 10).

  As shown in FIG. 10, when the propeller fan 50 is attached to the output shaft 31 of the drive motor 30, the bottom wall 44 </ b> B of the motor support 44 and the output shaft 31 are bosses in a direction parallel to the rotation shaft 80. It is located upstream of the most downstream portion (downstream portion 67) of the portion 60. In other words, the portion near the bottom wall 44 </ b> B of the motor support portion 44, the bottom wall 44 </ b> B and the output shaft 31 are arranged so as to be covered by the inner surface 68 of the boss portion 60.

(Wing part 70)
The three blade portions 70 are provided on the outer surface 61 of the boss portion 60 and have a shape extending from the outer surface 61 toward the outer side in the rotational radial direction of the propeller fan 50. The three wing parts 70 have the same shape. The three wing parts 70 are arranged at equal intervals in the rotation direction of the propeller fan 50 (in the direction of the arrow AR1).

  When the three wing parts 70 rotate in the direction of the arrow AR1 about the rotation shaft 80, the three wing parts 70 rotate integrally with the boss part 60. The three wing portions 70 rotate about the rotation shaft 80, whereby an air flow (from the upper side to the lower side in FIG. 11) flows from the suction port 15 (see FIG. 10) toward the discharge port 16 (see FIG. 10). Airflow that flows toward the

  Referring to FIGS. 11 and 12, the wing part 70 has a wing tip part 71, a leading edge part 72, a root part 73, a trailing edge part 74, a wing trailing edge part 75, and an outer peripheral edge part 76. The blade tip 71 is located at the most tip (front side) in the rotation direction of the propeller fan 50 (arrow AR1 direction). The leading edge 72 extends from the blade tip 71 to the outer surface 61 of the boss 60, and forms the leading edge of the blade 70 in the rotational direction. The front edge portion 72 of the present embodiment extends toward the front side in the rotational direction from the outer surface 61 of the boss portion 60 toward the outer side in the rotational radial direction (see FIG. 11). The root portion 73 is formed (boundary) between the wing portion 70 and the outer surface 61 of the boss portion 60.

  The rear edge portion 74 extends from the outer surface 61 of the boss portion 60 toward the outer side in the rotational radius direction, and forms the rear edge of the wing portion 70 in the rotation direction of the propeller fan 50 (arrow AR1 direction). The rear edge portion 74 of the present embodiment extends slightly forward in the rotational direction from the outer surface 61 of the boss portion 60 toward the outer side in the rotational radial direction (see FIG. 11). The blade trailing edge 75 is formed at the outermost edge (outer edge) of the trailing edge 74 in the rotational radius direction. The outer peripheral edge 76 connects the blade tip 71 and the blade rear end 75 and forms the outer periphery of the blade 70 in the rotational radius direction.

  More specifically, the wing part 70 has a sickle-like shape with the wing tip part 71 as a tip. The wing part 70 has a shape in which the width in the direction along the rotational direction between the front edge part 72 and the rear edge part 74 becomes relatively steep as it goes inward in the rotational radial direction. In other words, the wing portion 70 has a shape in which the width in the direction along the rotational direction between the front edge portion 72 and the rear edge portion 74 becomes relatively steep as it goes outward in the rotational radius direction.

  The leading edge 72 is located on the front side in the rotation direction (arrow AR1 direction) of the wing 70, and forms the leading edge of the wing 70 in the rotation direction. When the propeller fan 50 is viewed from a direction parallel to the rotation shaft 80 (in other words, when the propeller fan 50 is viewed in plan), the front edge portion 72 has a front end portion in the rotation direction of the root portion 73. As a starting point, it extends toward the front side in the rotational direction from the outer surface 61 of the boss 60 toward the outer side in the rotational radial direction. When the propeller fan 50 is viewed from a direction orthogonal to the rotation axis 80 (in other words, when the propeller fan 50 is viewed from the side), the front edge portion 72 of the present embodiment is the rotation of the root portion 73. Starting from the front end in the direction, it extends toward the upstream side in the airflow direction from the outer surface 61 of the boss 60 toward the outer side in the rotational radial direction (see FIG. 11).

  The blade tip 71 is located at the foremost end (front side) of the blade 70 in the rotational direction (arrow AR1 direction) and at the outermost side in the rotational radius direction of the leading edge 72. The blade tip portion 71 is a portion where the front edge portion 72 and the outer peripheral edge portion 76 are connected, and is a portion where the radius of curvature is minimized between the front edge portion 72 and the outer peripheral edge portion 76.

  The trailing edge portion 74 is located on the rear side in the rotation direction (arrow AR1 direction) of the wing portion 70, and forms the trailing edge of the wing portion 70 in the rotation direction. When the propeller fan 50 is viewed from a direction parallel to the rotation shaft 80 (in other words, when the propeller fan 50 is viewed in plan), the rear edge portion 74 is a rear end portion in the rotation direction of the root portion 73. Starting from the inside in the radial direction of rotation and extending outward in the same direction. When the propeller fan 50 is viewed from a direction orthogonal to the rotation axis 80 (in other words, when the propeller fan 50 is viewed from the side), the trailing edge portion 74 of the present embodiment is the rotation of the root portion 73. Starting from the rear end portion in the direction, it extends toward the upstream side in the direction in which the airflow flows from the outer surface 61 of the boss portion 60 toward the outside in the rotational radial direction (see FIG. 11).

  The blade trailing end 75 is located on the outermost side in the radial direction of rotation at the trailing edge 74. The blade trailing end portion 75 is a portion where the trailing edge portion 74 and the outer peripheral edge portion 76 are connected, and is a portion where the radius of curvature is minimized between the trailing edge portion 74 and the outer peripheral edge portion 76.

  The outer peripheral edge portion 76 extends along the rotation direction of the wing portion 70 (a circumferential direction around the rotation shaft 80), and is provided so as to connect between the wing tip portion 71 and the wing rear end portion 75. The outer peripheral edge portion 76 of the present embodiment as a whole extends in a substantially arc shape between the blade tip portion 71 and the blade trailing end portion 75. When the propeller fan 50 is viewed from a direction parallel to the rotation shaft 80 (in other words, when the propeller fan 50 is viewed in plan), the dimension between the rotation shaft 80 (upstream end portion 62) and the blade tip portion 71 is determined. Is smaller than the dimension between the rotating shaft 80 (upstream end 62) and the blade trailing end 75.

  The blade tip portion 71, the leading edge portion 72, the root portion 73, the trailing edge portion 74, the blade trailing edge portion 75, and the outer peripheral edge portion 76 form the periphery of the blade portion 70. The wing surface of the wing part 70 is formed in the entire region inside the region surrounded by the peripheral edge. The blade surface of the wing part 70 has a shape in which the front edge part 72 is located on the upstream side in the airflow direction and the rear edge part 74 is located on the downstream side in the airflow direction. In other words, the wing surface of the wing portion 70 as a whole moves from the suction port 15 (see FIG. 10) side to the discharge port 16 (see FIG. 10) side as it goes from the front edge portion 72 to the rear edge portion 74. It is formed to be smoothly curved (see FIG. 11).

  When the propeller fan 50 is rotating, a pressure surface is formed on the surface of the blade surface of the blade portion 70 on the discharge port 16 side, and a suction surface is formed on the surface of the suction port 15 of the blade surface. When the propeller fan 50 is rotating, the blade surface of the blade portion 70 generates an airflow that flows from the suction port 15 toward the discharge port 16. When the propeller fan 50 is rotating, a pressure distribution that is relatively large on the pressure surface and relatively small on the suction surface is generated as an air flow is generated on the blade surface.

(Function and effect)
FIG. 13 is a cross-sectional view showing a state when the propeller fan 50 is rotating. FIG. 14 is a diagram schematically illustrating a state when the boss portion 60 is rotating. Referring to FIGS. 13 and 14, propeller fan 50 receives rotational power from drive motor 30 (see FIG. 10) and rotates in the direction of arrow AR <b> 1, and from discharge port 15 (see FIG. 10) to discharge port 16 ( An airflow (see arrow DR5) that flows toward (see FIG. 10) is generated. As indicated by the arrow DR5, the airflow from the suction port 15 flows from the upstream side toward the downstream side along the blade surface of the blade portion 70 and the outer surface 61 of the boss portion 60.

  The air flowing through the space around the boss 60 where the wings 70 are not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side. On the other hand, the air flowing through the space around the boss 60 where the wings 70 are not provided does not flow along the downstream surface 66 of the outer surface 61 on the downstream side, and the centrifugal force from the outer surface 61 does not flow. In response to the action, it peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60 where the wing portion 70 is not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side (see arrow DR5).

  As the air flows in the direction of the arrow DR5, a vortex as indicated by the arrow DR6 is generated between the air flow and the downstream surface 66 of the boss portion 60. This vortex is generated when a part of the vortex is separated from the air flowing in the direction of the arrow DR5 and the part of the separated air is subjected to the centrifugal force from the outer surface 61. Most of the vortex occurs at a position upstream of the downstream portion 67 of the boss portion 60. The vortex does not fold around the downstream portion 67 of the boss portion 60 and does not flow so as to be sucked into the boss portion 60 toward the inner surface 68 side.

  When the air blower 200 (see FIG. 9) is used, foreign matter such as hair or dust may be sucked into the air blower 200 together with air from the inlet opening 13 (see FIG. 9). If the hair sucked from the inlet opening 13 (see FIG. 9) is growing hair, the hair stagnates on the spot without being entangled with the output shaft 31 of the drive motor 30. The hair can be easily pulled out from the inside of the blower 200 by being pulled upstream.

  When the hair sucked from the inlet opening 13 (see FIG. 9) is hair loss or the like, the foreign matter such as hair rides on the air flow indicated by the arrow DR5 (see FIGS. 13 and 14) as it is on the downstream side. Flowing. Foreign matter such as hair hardly entangles with the output shaft 31 of the drive motor 30. Therefore, according to the air blower 200 (refer FIG. 1) of this Embodiment, it can suppress effectively that a failure is induced by foreign materials, such as hair, without blowing efficiency falling.

  As described above (see FIG. 10), when the propeller fan 50 is attached to the output shaft 31 of the drive motor 30, the bottom wall 44B of the motor support portion 44 and the output shaft 31 are in the direction parallel to the rotation shaft 80. The boss portion 60 is located upstream of the most downstream portion (downstream portion 67). In other words, the portion near the bottom wall 44 </ b> B of the motor support portion 44, the bottom wall 44 </ b> B and the output shaft 31 are arranged so as to be covered by the inner surface 68 of the boss portion 60. It is further suppressed that foreign matters such as hair are entangled with the output shaft 31.

(First modification)
FIG. 15 is a diagram schematically showing a boss portion 60A in the first modification of the first embodiment. The outer surface 61 of the boss portion 60 </ b> A includes an upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical surface shape continuous to the upstream end portion 62 and extends toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60 </ b> A is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of the present modification has a conical surface shape as a whole, and extends toward the downstream portion 67 so as to decrease in diameter toward the inner side in the rotational radius direction rather than in a direction parallel to the rotation shaft 80. ing.

  In other words, the external shape of the portion including the downstream surface 66 of the boss portion 60 </ b> A has a substantially truncated cone shape that decreases in diameter toward the downstream portion 67. The shape of the truncated cone is a solid shape that is not a cone among solids obtained by bisecting the cone by a plane parallel to the bottom surface. The shape of the substantially truncated cone referred to here does not only mean the shape of a surface whose side surface shape (the shape of the downstream surface 66) is a substantially straight line, but also the portion of the downstream surface 66 near the downstream end 65 and Or the case where the part near the downstream part 67 of the downstream surface 66 is curving suitably is included. The shape of the downstream surface 66 of the present modification may be formed so as to be curved as a whole as long as the downstream surface 66 extends toward the inner side in the rotational radial direction toward the downstream side. The shape in which 66 is curved toward the rotation axis and the shape in which the downstream surface 66 is curved away from the rotation axis are also included in the “substantially truncated cone shape”.

  When the propeller fan is rotating, the airflow from the suction port flows as shown by an arrow DR5. Air flowing through a space around the boss portion 60A where no wing portion is provided flows along the upstream surface 64 of the outer surface 61 on the upstream side, and along the downstream surface 66 of the outer surface 61 on the downstream side. Does not flow, and peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing in the space around the boss portion 60A where the wing portion is not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side (see arrow DR5).

  As the air flows in the direction of the arrow DR5, a vortex as indicated by the arrow DR6 is generated between the air flow and the downstream surface 66 of the boss portion 60A. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60A. The vortex does not turn around the downstream portion 67 of the boss portion 60A and does not flow so as to be sucked into the boss portion 60A. Therefore, even when the boss portion 60A is used, the blowing efficiency is not lowered, and it is possible to effectively suppress the failure induced by foreign matters such as hair.

(Second modification)
FIG. 16 is a diagram schematically showing a boss 60B1 in the second modification of the first embodiment. The outer surface 61 of the boss portion 60B1 includes an upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical surface shape continuous to the upstream end portion 62 and extends toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60B1 is also formed so as to connect the downstream end 65 and the downstream portion 67 of the upstream surface 64. The downstream surface 66 of this modification has a first downstream surface 66A and a second downstream surface 66B. The first downstream surface 66A extends in a direction orthogonal to the rotation shaft 80. The second downstream surface 66B has a cylindrical surface shape continuous with the first downstream surface 66A and extends in a direction parallel to the rotation shaft 80. The entire downstream surface 66 extends toward the downstream portion 67 while being bent toward the inner side in the rotational radial direction rather than in a direction parallel to the rotational axis 80.

  When the propeller fan is rotating, the air flowing in the space where the wing portion around the boss portion 60B1 is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss 60 </ b> B <b> 1 where the wings are not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60B1. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60B1. The vortex does not turn around the downstream portion 67 of the boss portion 60B1, and does not flow so as to be sucked into the boss portion 60B1. Therefore, even when the boss portion 60B1 is used, it is possible to effectively suppress a failure induced by a foreign object such as hair without reducing the blowing efficiency.

(Third Modification)
FIG. 17 is a diagram schematically showing a boss portion 60B2 in the third modification example of the first embodiment. The outer surface 61 of the boss portion 60B2 includes an upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially hemispherical shape continuous to the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60B2 is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of the present modification has a substantially conical shape that is continuous with the downstream end 65 of the upstream surface 64, and as it goes toward the downstream portion 67, it is more in the radial direction of rotation than in the direction parallel to the rotational axis 80. It extends linearly so as to reduce its diameter toward the inside.

  When the propeller fan is rotating, the air flowing through the space around the boss portion 60B2 where the wing portion is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60B2 where the wing portion is not provided flows outside the outer surface 61 in the rotational radius direction on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60B2. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60B2. The vortex does not fold around the downstream portion 67 of the boss portion 60B2, and does not flow so as to be sucked into the boss portion 60B2. Therefore, even when the boss portion 60B2 is used, the air blowing efficiency is not lowered, and it is possible to effectively suppress the failure induced by foreign matters such as hair.

(Fourth modification)
FIG. 18 is a diagram schematically showing a boss portion 60B3 in the fourth modification example of the first embodiment. The outer surface 61 of the boss portion 60B3 includes an upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially hemispherical shape continuous to the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60B3 is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of this modification has a first downstream surface 66A and a second downstream surface 66B. The first downstream surface 66A extends in a direction orthogonal to the rotation shaft 80. The second downstream surface 66B has a cylindrical surface shape continuous with the first downstream surface 66A and extends in a direction parallel to the rotation shaft 80. The entire downstream surface 66 extends toward the downstream portion 67 while being bent toward the inner side in the rotational radial direction rather than in a direction parallel to the rotational axis 80.

  When the propeller fan is rotating, the air flowing through the space around the boss portion 60B3 where the wing portion is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60B3 where the wing portion is not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60B3. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60B3. The vortex does not fold around the downstream portion 67 of the boss portion 60B3 and does not flow so as to be sucked into the boss portion 60B3. Therefore, even when the boss portion 60B3 is used, the blowing efficiency is not lowered, and it is possible to effectively suppress the failure induced by foreign matters such as hair.

(5th modification)
FIG. 19 is a diagram schematically showing a boss portion 60B4 in the fifth modification example of the first embodiment. The outer surface 61 of the boss portion 60B4 includes an upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially hemispherical shape continuous to the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60B4 is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of the present modification extends in an arc shape toward the inner side in the rotational radial direction rather than the direction parallel to the rotational axis 80 as it goes toward the downstream portion 67. The downstream surface 66 of this modification has an arcuate shape that is recessed inwardly toward the downstream portion 67.

  When the propeller fan is rotating, the air flowing through the space around the boss portion 60B4 where the wing portion is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60B4 where the wing portion is not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60B4. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60B4. The vortex does not fold around the downstream portion 67 of the boss portion 60B4 and does not flow so as to be sucked into the boss portion 60B4. Therefore, even when the boss portion 60B4 is used, the blowing efficiency is not lowered, and it is possible to effectively suppress the failure induced by foreign matters such as hair.

(Sixth Modification)
FIG. 20 is a diagram schematically showing a boss portion 60C in the sixth modification example of the first embodiment. The outer surface 61 of the boss 60C includes an upstream end 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 is formed so as to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially hemispherical shape continuous to the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60 </ b> C is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of this modification has a first downstream surface 66A and a second downstream surface 66B. 66 A of 1st downstream surfaces are extended in circular arc shape toward the inner side of a rotation radial direction rather than the direction parallel to the rotating shaft 80 as it goes downstream. The first downstream surface 66A of this modification has an arc shape that protrudes outward as it goes downstream. The second downstream surface 66B extends in a direction parallel to the rotation shaft 80 starting from the downstream end of the first downstream surface 66A, and further downstream of the second downstream surface 66B than the direction parallel to the rotation shaft 80. It extends in the shape of an arc toward the inside. The downstream portion of the second downstream surface 66B of this modification has an arcuate shape that protrudes outward as it goes downstream.

  When the propeller fan is rotating, the air flowing through the space where the wing portion around the boss portion 60C is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing in the space around the boss portion 60 </ b> C where the wing portion is not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60C. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60C. This vortex does not fold around the downstream portion 67 of the boss portion 60C and does not flow so as to be sucked into the boss portion 60C. Therefore, even when the boss portion 60C is used, it is possible to effectively suppress a failure induced by foreign matters such as hair without reducing the blowing efficiency.

(Seventh Modification)
FIG. 21 is a diagram schematically showing a boss portion 60D1 in the seventh modification example of the first embodiment. The outer surface 61 of the boss 60D1 includes an upstream end 62, an outer edge 62T of the upstream end 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61 and has a planar shape. A rotation shaft 80 is formed so as to pass through the center of the upstream end portion 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical shape continuous to the outer edge 62T of the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan as it goes downstream.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60D1 is also formed so as to connect the downstream end 65 and the downstream portion 67 of the upstream surface 64. The downstream surface 66 of this modification has a first downstream surface 66A and a second downstream surface 66B. The first downstream surface 66A extends in a direction orthogonal to the rotation shaft 80. The second downstream surface 66B has a cylindrical surface shape continuous with the first downstream surface 66A and extends in a direction parallel to the rotation shaft 80. The entire downstream surface 66 extends toward the downstream portion 67 while being bent toward the inner side in the rotational radial direction rather than in a direction parallel to the rotational axis 80.

  When the propeller fan is rotating, the air flowing through the space around the boss portion 60D1 where the wing portion is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60D1 where the wing portion is not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60D1. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60D1. The vortex does not fold around the downstream portion 67 of the boss portion 60D1, and does not flow so as to be sucked into the boss portion 60D1. Therefore, even when the boss portion 60D1 is used, the blowing efficiency is not lowered, and it is possible to effectively suppress the failure induced by foreign matters such as hair.

(Eighth modification)
FIG. 22 is a diagram schematically showing a boss portion 60D2 in the eighth modification example of the first embodiment. The outer surface 61 of the boss 60D2 includes an upstream end 62, an outer edge 62T of the upstream end 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61 and has a planar shape. A rotation shaft 80 is formed so as to pass through the center of the upstream end portion 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical shape continuous to the outer edge 62T of the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan as it goes downstream.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60D2 is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of the present modification extends in an arc shape toward the inner side in the rotational radial direction rather than the direction parallel to the rotation shaft 80 as it goes downstream. The downstream surface 66 of this modification has an arcuate shape that protrudes outward as it goes downstream.

  When the propeller fan is rotating, the air flowing through the space where the wing portion around the boss portion 60D2 is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60D2 where the wing portion is not provided flows on the outer side in the radial direction of rotation than the outer surface 61 on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60D2. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60D2. The vortex does not fold around the downstream portion 67 of the boss portion 60D2, and does not flow so as to be sucked into the boss portion 60D2. Therefore, even when the boss portion 60D2 is used, the blowing efficiency is not lowered, and it is possible to effectively suppress the failure induced by foreign matters such as hair.

(Ninth Modification)
FIG. 23 is a diagram schematically showing a boss portion 60D3 in the ninth modification example of the first embodiment. The outer surface 61 of the boss portion 60D3 includes an upstream end portion 62, an outer edge 62T of the upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61 and has a planar shape. A rotation shaft 80 is formed so as to pass through the center of the upstream end portion 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical shape continuous to the outer edge 62T of the upstream end portion 62, and extends so as to increase in diameter toward the outer side in the rotational radial direction of the propeller fan as it goes downstream.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60D3 is also formed so as to connect the downstream end 65 and the downstream portion 67 of the upstream surface 64. The downstream surface 66 of the present modification extends in an arc shape toward the inner side in the rotational radial direction rather than the direction parallel to the rotation shaft 80 as it goes downstream. The downstream surface 66 of this modification has an arcuate shape that becomes concave toward the downstream side.

  When the propeller fan is rotating, the air flowing through the space around the boss portion 60D3 where the wing portion is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60D3 where the wing portion is not provided flows outside the outer surface 61 in the rotational radius direction on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60D3. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60D3. This vortex does not fold around the downstream portion 67 of the boss 60D3 and does not flow so as to be sucked into the boss 60D3. Therefore, even when the boss portion 60D3 is used, it is possible to effectively suppress a failure induced by a foreign object such as hair without reducing the blowing efficiency.

(10th modification)
FIG. 24 is a diagram schematically showing a boss portion 60E1 in the tenth modification example of the first embodiment. The outer surface 61 of the boss 60E1 includes an upstream end 62, an outer edge 62T of the upstream end 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61 and has a planar shape. A rotation shaft 80 is formed so as to pass through the center of the upstream end portion 62 when the propeller fan is rotating. The upstream surface 64 has a substantially cylindrical surface shape continuous with the outer edge 62 </ b> T of the upstream end portion 62, and extends along a direction parallel to the rotation shaft 80.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60E1 is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of the present modification has a substantially conical surface shape that is continuous with the downstream end 65 of the upstream surface 64, and the inner side in the rotational radial direction than the direction parallel to the rotational axis 80 as it goes downstream. It extends in a straight line so as to reduce its diameter.

  When the propeller fan is rotating, the air flowing through the space around the boss portion 60E1 where the wing portion is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60E1 where the wing portion is not provided flows outside the outer surface 61 in the rotational radius direction on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60E1. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60E1. The vortex does not fold around the downstream portion 67 of the boss portion 60E1, and does not flow so as to be sucked into the boss portion 60E1. Therefore, even when the boss portion 60E1 is used, the blowing efficiency is not lowered, and it is possible to effectively suppress the failure induced by foreign matters such as hair.

(Eleventh modification)
FIG. 25 is a diagram schematically showing a boss portion 60E2 in the eleventh modification example of the first embodiment. The outer surface 61 of the boss portion 60E2 includes an upstream end portion 62, an outer edge 62T of the upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61 and has a planar shape. A rotation shaft 80 is formed so as to pass through the center of the upstream end portion 62 when the propeller fan is rotating. The upstream surface 64 has a substantially cylindrical surface shape continuous to the outer edge 62T of the upstream end portion 62, and extends along a direction parallel to the rotation axis 80 toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60E2 is also formed so as to connect the downstream end 65 and the downstream portion 67 of the upstream surface 64. The downstream surface 66 of this modification has a first downstream surface 66A and a second downstream surface 66B. The first downstream surface 66A extends in a direction orthogonal to the rotation shaft 80. The second downstream surface 66B has a substantially conical surface shape continuous with the first downstream surface 66A, and contracts inward in the rotational radial direction rather than in a direction parallel to the rotation shaft 80 toward the downstream side. It extends linearly so as to have a diameter. The entire downstream surface 66 extends toward the downstream portion 67 while being bent toward the inner side in the rotational radial direction rather than in a direction parallel to the rotational axis 80.

  When the propeller fan is rotating, the air flowing through the space where the wing portion around the boss portion 60E2 is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60E2 where the wing portion is not provided flows outside the outer surface 61 in the rotational radius direction on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60E2. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60E2. The vortex does not fold around the downstream portion 67 of the boss portion 60E2, and does not flow so as to be sucked into the boss portion 60E2. Therefore, even when the boss portion 60E2 is used, the blowing efficiency is not lowered, and it is possible to effectively suppress a failure induced by foreign matters such as hair.

(Twelfth modification)
FIG. 26 is a diagram schematically showing a boss portion 60E3 in the twelfth modification of the first embodiment. The outer surface 61 of the boss portion 60E3 includes an upstream end portion 62, an outer edge 62T of the upstream end portion 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67. The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61 and has a planar shape. A rotation shaft 80 is formed so as to pass through the center of the upstream end portion 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical surface shape that is continuous with the outer edge 62T of the upstream end portion 62, and contracts inward in the rotational radial direction from the direction parallel to the rotation shaft 80 toward the downstream side. It extends linearly so as to have a diameter.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this modification is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60E3 is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of this modification has a first downstream surface 66A and a second downstream surface 66B. The first downstream surface 66A extends in a direction orthogonal to the rotation shaft 80. The second downstream surface 66B has a cylindrical surface shape continuous with the first downstream surface 66A and extends in a direction parallel to the rotation shaft 80. The entire downstream surface 66 extends toward the downstream portion 67 while being bent toward the inner side in the rotational radial direction rather than in a direction parallel to the rotational axis 80.

  When the propeller fan is rotating, the air flowing through the space around the boss portion 60E3 where the wing portion is not provided flows along the upstream surface 64 of the outer surface 61 on the upstream side and outside on the downstream side. It does not flow along the downstream surface 66 of the surface 61 but peels from the outer surface 61 in the vicinity of the downstream end 65 of the upstream surface 64. The air flowing through the space around the boss portion 60E3 where the wing portion is not provided flows on the outer side in the rotational radius direction than the outer surface 61 on the downstream side.

  A vortex is generated between the air flow and the downstream surface 66 of the boss 60E3. Most of the vortex is generated at a position upstream of the downstream portion 67 of the boss portion 60E3. The vortex does not turn around the downstream portion 67 of the boss portion 60E3 and does not flow so as to be sucked into the boss portion 60E3. Therefore, even when the boss portion 60E3 is used, it is possible to effectively suppress a failure induced by foreign matters such as hair without reducing the blowing efficiency.

[Experimental Example 1]
With reference to FIG. 27 to FIG. 29, Experimental Example 1 and its results relating to the above-described first embodiment (FIGS. 9 to 14) will be described. In this experimental example, a boss portion 60F as shown in FIG. 27 was used. Boss portion 60F has substantially the same shape as boss portion 60 (see FIG. 14) in the first embodiment. Specifically, the outer surface 61 of the boss 60F includes an upstream end 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67.

  The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 (not shown) is formed to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical surface shape continuous to the upstream end portion 62 and extends toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this experimental example is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60F is also formed so as to connect the downstream end 65 of the upstream surface 64 and the downstream portion 67. The downstream surface 66 of this experimental example has a cylindrical surface shape that is continuous with the downstream end 65 of the upstream surface 64, and extends in a direction parallel to the rotation axis 80.

  The upstream end 62 of the boss 60F has an inner angle θ1. The upstream surface 64 of the boss portion 60F has a height dimension H in a direction parallel to the rotation shaft 80 (not shown). The downstream surface 66 of the boss portion 60F has a height dimension h in a direction parallel to the rotation shaft 80 (not shown). The downstream surface 66 of the boss portion 60F has an outer diameter D1. In the present experimental example, the internal angle θ1 and the height dimension H were treated as variable values (see FIGS. 28 and 29). The height dimension h and the outer diameter D1 were treated as fixed values. The value of the height dimension h is 10 mm, and the value of the outer diameter D1 is 40 mm.

  The internal angle θ1 of the upstream end 62 was changed from 0 ° to 170 °, and the height dimension H of the upstream surface 64 was also changed accordingly. A propeller fan provided with a plurality of types of boss portions 60F having different inner angles θ1 was prepared, and the propeller fan was disposed in a cylindrical case together with a drive motor. While rotating the propeller fan, 1000 hairs were flowed from the upstream side toward the downstream side. For each propeller fan, the operation of running 1000 hairs was repeated 5 times, and the average value of the number of hairs wound around the output shaft of the drive motor was calculated.

  A line L1 in FIG. 28 shows the relationship between the internal angle θ1 and the number of hairs wound around the output shaft of the drive motor. The horizontal axis in FIG. 28 indicates the internal angle θ1 of the upstream end portion 62 of the boss portion 60F. The vertical axis | shaft of FIG. 28 has shown the average value of the number of the hair wound in the output shaft of a drive motor. This average value is an average value when the operation of flowing 1000 hairs is repeated 5 times.

  As shown by the line L1, it can be seen that as the value of the internal angle θ1 is increased from 10 °, the entanglement of the hair sharply decreases. When the internal angle θ1 is 50 ° or more, it can be seen that almost no entanglement of hair occurs. Therefore, it can be seen that the inner angle θ1 at the upstream end 62 of the boss 60F is preferably 50 ° or more.

  A line L2 in FIG. 29 shows the relationship between the value of h / (H + h) and the number of hairs caught on the output shaft of the drive motor. The horizontal axis in FIG. 29 indicates a value obtained by dividing the height dimension h of the downstream surface 66 by (height dimension H + height dimension h). This height dimension H is the height dimension H of the upstream surface 64 obtained when the internal angle θ1 of the upstream end portion 62 is changed from 0 ° to 170 °. The value of h / (H + h) is a ratio of the height dimension h of the downstream surface 66 occupying in the total height (H + h) of the boss portion 60F in a direction parallel to the rotation shaft 80 (not shown). The vertical axis | shaft of FIG. 29 has shown the average value of the number of the hair wound in the output shaft of a drive motor. This average value is an average value when the operation of flowing 1000 hairs is repeated 5 times.

  As shown by the line L2, it can be seen that as the value of h / (H + h) is increased from 0.05, the entanglement of hair sharply decreases. When h / (H + h) is 0.2 or more, it can be seen that almost no entanglement of hair occurs. Therefore, it can be seen that the value of h / (H + h) is preferably 0.2 (= 1/5) or more. In other words, it can be seen that the ratio of the height dimension h of the downstream surface 66 in the total height (H + h) of the boss portion 60F is preferably 1/5 or more.

  Even when the value of the internal angle θ1 is less than 50 °, the hair entrainment can be suppressed by securing the height dimension h of the downstream surface 66 to some extent. Even if the height dimension h of the downstream surface 66 is less than 1/5 of the total height, the inner angle θ1 has a certain value and the flow is separated from the outer surface 61. If it is, the entrainment of hair can be suppressed. Therefore, the feature of the internal angle θ1 and the feature of h / (H + h) may be applied independently to the boss portion 60F.

[Experiment 2]
With reference to FIG. 30 and FIG. 31, Experimental Example 2 and its results relating to the above-described first embodiment (FIGS. 9 to 14) will be described. In this experimental example, a boss portion 60G as shown in FIG. 30 was used. Boss portion 60G has substantially the same shape as boss portion 60 (see FIG. 14) in the first embodiment. Specifically, the outer surface 61 of the boss 60G includes an upstream end 62, an upstream surface 64, a downstream end 65 of the upstream surface 64, a downstream surface 66, and a downstream portion 67.

  The upstream end 62 is formed at the most upstream (vertical) position of the outer surface 61. A rotating shaft 80 (not shown) is formed to pass through the upstream end 62 when the propeller fan is rotating. The upstream surface 64 has a substantially conical surface shape continuous to the upstream end portion 62 and extends toward the outer side in the rotational radial direction of the propeller fan toward the downstream side.

  The downstream end 65 of the upstream surface 64 is formed at the most downstream position of the upstream surface 64. The downstream portion 67 is located further downstream than the downstream end 65 of the upstream surface 64. The downstream portion 67 of this experimental example is located on the most downstream side of the outer surface 61 as a whole. The downstream surface 66 of the boss portion 60G is also formed so as to connect the downstream end 65 and the downstream portion 67 of the upstream surface 64. The downstream surface 66 of this experimental example has a cylindrical surface shape that is continuous with the downstream end 65 of the upstream surface 64, and extends in a direction parallel to the rotation axis 80.

  The upstream end 62 of the boss 60G has an inner angle θ2. The upstream surface 64 of the boss portion 60G has a height dimension H in a direction parallel to the rotation shaft 80 (not shown). The downstream surface 66 of the boss 60G has a height dimension h in a direction parallel to the rotation shaft 80 (not shown). The downstream surface 66 of the boss 60G has an outer diameter D2. In this experimental example, the value of the internal angle θ2 was set to three types of 150 °, 98 °, and 60 ° (see FIG. 31). The value of the outer diameter D2 is 40 mm (fixed value).

  When the value of the internal angle θ2 is 150 °, the value of the height dimension H is 5.36 mm. When the value of the internal angle θ2 is 98 °, the value of the height dimension H is 17.39 mm. When the value of the internal angle θ2 is 60 °, the value of the height dimension H is 34.64 mm. The height dimension h was treated as a variable value (see FIG. 31).

  A propeller fan provided with three types of boss portions 60G having an internal angle θ2 of 150 °, 98 °, and 60 ° was prepared, and the propeller fan was disposed in a cylindrical case together with a drive motor. While rotating the propeller fan, 1000 hairs were flowed from the upstream side toward the downstream side. For each propeller fan, the operation of running 1000 hairs was repeated 5 times, and the average value of the number of hairs wound around the output shaft of the drive motor was calculated.

  A line L3 in FIG. 31 indicates the relationship between the value of h / (H + h) and the number of hairs caught on the output shaft of the drive motor when the value of the internal angle θ2 is 150 °. A line L4 in FIG. 31 shows the relationship between the value of h / (H + h) and the number of hairs caught on the output shaft of the drive motor when the value of the internal angle θ2 is 98 °. A line L5 in FIG. 31 indicates the relationship between the value of h / (H + h) and the number of hairs caught on the output shaft of the drive motor when the value of the internal angle θ2 is 60 °. The horizontal axis in FIG. 29 indicates a value obtained by dividing the height dimension h of the downstream surface 66 by (height dimension H + height dimension h). The vertical axis | shaft of FIG. 31 has shown the average value of the number of the hair wound in the output shaft of a drive motor. This average value is an average value when the operation of flowing 1000 hairs is repeated 5 times.

  As shown by the lines L3 to L5, it can be seen that as the value of h / (H + h) is increased from 0.05, the entanglement of hair sharply decreases. When h / (H + h) is 0.2 or more, it can be seen that almost no entanglement of hair occurs. Therefore, it can be seen that the value of h / (H + h) is preferably 0.2 (= 1/5) or more. In other words, it can be seen that the ratio of the height dimension h of the downstream surface 66 occupying in the total height (H + h) of the boss 60G is preferably 1/5 or more.

  On the other hand, as shown by lines L3 to L5, it can be seen that as the value of h / (H + h) is further increased, the number of entangled hairs slightly increases. With reference to the line L3, when the value of the internal angle θ2 is 150 °, the average value of the number of entangled hairs becomes 2 or more when the value of h / (H + h) exceeds 0.88. With reference to the line L4, when the value of the internal angle θ2 is 98 °, if the value of h / (H + h) exceeds 0.63, the average value of the number of entangled hairs becomes 2 or more. With reference to the line L5, when the value of the internal angle θ2 is 60 °, the average value of the number of entangled hairs becomes 2 or more when the value of h / (H + h) exceeds 0.37.

  FIG. 32 shows the relationship between the value of the internal angle θ2 when the average value of the number of entangled hairs is two and the value of h / (H + h) when the average value of the number of entangled hairs is two. It is a figure. As shown in FIG. 32, the value of the internal angle θ2 when the average value of the number of entangled hairs is 2, and the value of h / (H + h) when the average value of the number of entangled hairs is two. It can be seen that changes substantially linearly. The line L6 in FIG. 32 shows the value of the internal angle θ2 when the average value of the number of hairs to be wound is 2, and the value of h / (H + h) when the average value of the number of hairs to be wound is two. This is an approximate straight line showing the relationship. This approximate curve is represented by the formula “h / (H + h) = 0.0501 × inner angle θ2max + 0.0056”, and its determination coefficient is 0.989.

  Therefore, the ratio of the height dimension h of the downstream surface 66 occupying in the total height (H + h) of the boss portion 60G is preferably 1/5 or more, and it is desired to further suppress the entrainment of hair on the output shaft of the drive motor. In this case, it can be seen that it is more preferable that the maximum value of the internal angle θ2 is set so that the relationship represented by the expression “h / (H + h) = 0.0501 × internal angle θ2max + 0.0056” is satisfied.

[Comparative Example 2]
(Propeller fan 50Z1)
With reference to FIG. 33, the propeller fan 50Z1 in this comparative example is demonstrated. Propeller fan 50Z1 includes a boss portion 60Z1 and a wing portion 70Z1. Propeller fan 50Z1 has substantially the same shape as propeller fan 50Z (see FIGS. 3 and 5) in Comparative Example 1 described above.

  In a direction parallel to the rotation shaft 80, the blade portion 70Z1 of the propeller fan 50Z1 has a height dimension haz and a height dimension hbz. The height dimension haz is a position on the most downstream side in the wing part 70Z1 (a position of the rear edge part 74 in the wing part 70Z1) and a position of the root 72H of the front edge part 72 in the direction parallel to the rotation axis 80 It is a dimension between. The height dimension hbz is a dimension between the position on the most downstream side in the blade part 70Z1 and the position of the blade tip part 71 in the direction parallel to the rotation shaft 80.

  As described in the description of the first comparative example, the front edge portion 72 of this comparative example extends substantially along the direction perpendicular to the rotation shaft 80 of the propeller fan 50Z1. In the wing part 70Z1, the value of hbz / haz is 1.05.

  FIG. 34 is a cross-sectional view showing a state when propeller fan 50Z1 is rotating. Propeller fan 50Z1 receives the rotational power from drive motor 30 and rotates in the direction of arrow AR1, and generates an air flow (see arrow DR1) flowing from suction port 15 toward discharge port 16. As indicated by the arrow DR1, the airflow from the suction port 15 flows from the upstream side to the downstream side along the blade surface of the blade portion 70Z1 and the outer surface 61 of the boss portion 60Z1.

  As described in the description of Comparative Example 1 above, as the blade portion 70Z1 rotates, a blade tip vortex is generated in the vicinity of the blade tip portion 71 of the blade portion 70Z1 (see arrow DR3). The blade tip vortex is generated so as to extend toward the rear side in the rotation direction (arrow AR1 direction) with the vicinity of the blade tip 71 as a tip.

  The position of the blade tip portion 71 of the blade portion 70Z1 is close to the position of the downstream end (rear edge portion 74) of the blade portion 70Z1 (compared to the case of Embodiment 2 described later). Therefore, in propeller fan 50Z1, between the generation position of the blade tip vortex indicated by arrow DR3 and the generation position of the vortex generated near the downstream end (rear edge portion 74) of blade 70Z1 indicated by arrow DR2. The distance is getting shorter.

  In the propeller fan 50Z1, the width W10 of the air passage through which air from the suction port 15 can smoothly flow toward the discharge port 16 is narrow, and the incident angle θ10 of air with respect to the inner wall surface of the inner case 12 is also increased. Yes. The incident angle θ10 referred to here is an angle formed between the direction of air flow and the inner wall surface of the inner case 12 when the air from the suction port 15 contacts the inner wall surface of the inner case 12. It is.

  When the air from the suction port 15 comes into contact with the inner wall surface of the inner case 12, the outward flow in the rotational radius direction collides with the inner wall surface of the inner case 12 and is rebounded. The air that has flowed along the outer surface 61 flows so as to enter the inner side on the rebounded flow from the outside. Therefore, when the propeller fan 50Z1 provided with the wing portion 70Z1 is used, it is difficult to prevent foreign matters such as hair from being entangled with the output shaft 31 of the drive motor 30.

[Embodiment 2]
(Propeller fan 50H)
With reference to FIG. 35, propeller fan 50H in the present embodiment will be described. Propeller fan 50H includes boss portion 60H and wing portion 70H. Propeller fan 50H has substantially the same shape as propeller fan 50 (see FIG. 11) in the first embodiment.

  In a direction parallel to the rotation shaft 80, the blade portion 70H of the propeller fan 50H has a height dimension ha and a height dimension hb. The height ha is the position of the most downstream side of the wing 70H (the root of the trailing edge 74 in the wing 70H) and the position of the root 72H of the leading edge 72 in the direction parallel to the rotation axis 80. It is a dimension between. The height dimension hb is a dimension between the position on the most downstream side in the blade part 70 </ b> H and the position of the blade tip part 71 in the direction parallel to the rotation shaft 80.

  As described in the description of the first embodiment, when the propeller fan 50H is viewed from a direction orthogonal to the rotation shaft 80 (in other words, when the propeller fan 50H is viewed from the side), The front edge portion 72 extends from the front end portion in the rotational direction of the root portion 73 to the upstream side in the airflow direction from the outer surface 61 of the boss portion 60 toward the outer side in the rotational radial direction. Yes. In the wing portion 70H, the value of hb / ha is 2.20.

  FIG. 36 is a cross-sectional view showing a state when the propeller fan 50H is rotating. Propeller fan 50H receives rotational power from drive motor 30 and rotates in the direction of arrow AR1, and generates an airflow (see arrow DR1) that flows from suction port 15 toward discharge port 16. As indicated by the arrow DR1, the airflow from the suction port 15 flows from the upstream side toward the downstream side along the blade surface of the blade portion 70H and the outer surface 61 of the boss portion 60H.

  As described in the description of the first embodiment, the blade tip vortex is generated near the blade tip 71 of the blade 70H as the blade 70H rotates (see arrow DR3). The blade tip vortex is generated so as to extend toward the rear side in the rotation direction (arrow AR1 direction) with the vicinity of the blade tip 71 as a tip.

  Compared to the case of Comparative Example 2 described above, the position of the blade tip 71 of the blade 70H is far from the position of the downstream end of the blade 70H. Accordingly, in propeller fan 50H, the blade tip vortex generation position indicated by arrow DR3 and the vortex generation position generated near the downstream end (rear edge portion 74) of blade part 70H indicated by arrow DR6 are between. The distance is getting longer.

  In the propeller fan 50H, the width W11 of the air passage through which the air from the suction port 15 can smoothly flow toward the discharge port 16 is wider than the width W10 (see FIG. 34), and the inner case 12 The incident angle θ11 of air with respect to the inner wall surface is also smaller than the incident angle θ10 (see FIG. 34). The incident angle θ11 referred to here is an angle formed between the air flowing direction and the inner wall surface of the inner case 12 when the air from the suction port 15 contacts the inner wall surface of the inner case 12. It is.

  When the air from the suction port 15 comes into contact with the inner wall surface of the inner case 12, the flow toward the outside in the rotational radius direction is hardly repelled even if it comes into contact with the inner wall surface of the inner case 12. The air flowing along the outer surface 61 does not enter the inside, and the air in contact with the inner wall surface of the inner case 12 flows directly downstream. Therefore, when the propeller fan 50H provided with the wing portion 70H is used, it is possible to effectively suppress foreign matters such as hair from being entangled with the output shaft 31 of the drive motor 30.

[Experiment 3]
With reference to FIG. 37, Experimental Example 3 and its results relating to the above-described second embodiment (FIGS. 35 and 36) will be described. In the present experimental example, the value of the height dimension ha was set to 15 mm, and the value of the height dimension hb was changed from 15 mm to 35 mm. A propeller fan provided with a plurality of types of boss portions 60H (see FIG. 35) having different values of hb / ha was prepared, and the propeller fan was disposed in a cylindrical case together with a drive motor. While rotating the propeller fan, 1000 hairs were flowed from the upstream side toward the downstream side. For each propeller fan, the operation of running 1000 hairs was repeated 5 times, and the average value of the number of hairs wound around the output shaft of the drive motor was calculated.

  A line L10 in FIG. 37 shows the relationship between the value of hb / ha and the number of hairs caught on the output shaft of the drive motor. The horizontal axis in FIG. 37 indicates the value of hb / ha of the boss portion 60H. The vertical axis | shaft of FIG. 37 has shown the average value of the number of the hair wound in the output shaft of a drive motor. This average value is an average value when the operation of flowing 1000 hairs is repeated 5 times.

  As shown by the line L10, it can be seen that as the value of hb / ha is increased from 1.0, the entanglement of hair sharply decreases. When the value of hb / ha is 1.5 or more, it can be seen that almost no entanglement of hair occurs. Therefore, it can be seen that the value of hb / ha of the boss 60H is preferably 1.5 or more.

[Experimental Example 4]
With reference to FIGS. 38 and 39, Experimental Example 4 and its results relating to the above-described second embodiment (FIGS. 35 and 36) will be described. In this experimental example, the value of the minimum clearance CL (narrowest clearance) formed between the blade portion 70H and the rectifying blade 40 in the direction parallel to the rotating shaft 80 is from 0.5 mm to 9.5 mm. Changed.

  Plural types of propeller fans having different minimum clearance CL values were prepared, and the propeller fans were arranged in a cylindrical case together with a drive motor. While rotating the propeller fan, 1000 hairs were flowed from the upstream side toward the downstream side. For each propeller fan, the operation of running 1000 hairs was repeated 5 times, and the average value of the number of hairs wound around the output shaft of the drive motor was calculated. On the other hand, the air volume was also measured on the downstream side of the cylindrical case while rotating the propeller fan.

  A line L20 in FIG. 39 shows the relationship between the value of the minimum gap CL and the number of hairs caught on the output shaft of the drive motor. A line L21 in FIG. 39 shows the relationship between the value of the minimum gap CL and the air volume measured on the downstream side of the cylindrical case. Referring to line L20 and line L21, it can be seen that when the value of the minimum gap CL is larger than about 3 mm, the air volume at the same rotation speed decreases and the number of hairs involved increases. It can be seen that when the value of the minimum clearance CL is 3 mm or less (for example, 2.27 mm), the air volume at the same rotation speed does not decrease, and the number of hairs can be further suppressed.

[Comparative Example 3]
(Propeller fan 50Z2)
FIG. 40 is a plan view showing propeller fan 50Z2 of Comparative Example 3 relating to the above-described Embodiment 2 (see FIG. 35). Propeller fan 50Z2 includes boss portion 60Z2 and wing portion 70Z2. Propeller fan 50Z2 has substantially the same shape as propeller fan 50Z (see FIG. 4) in Comparative Example 1 described above.

  As described in the description of Comparative Example 1 above, the blade tip 71 and the blade trailing end 75 of this comparative example are located on substantially the same circle C10. The outer peripheral edge portion 76 extends in an arc shape along the rotation direction of the wing portion 70Z2 (the circumferential direction around the rotation shaft 80). When propeller fan 50Z2 is viewed from a direction parallel to rotation axis 80 (in other words, when propeller fan 50Z2 is viewed in plan), the dimension between rotation axis 80 (upstream end 62) and blade tip 71 And the dimension between the rotating shaft 80 (upstream end part 62) and the blade rear-end part 75 is the same value.

  In a state where propeller fan 50Z2 is stationary, blade tip 71 of blade portion 70Z2 is located on circle C10. On the other hand, when the propeller fan 50Z2 is rotating, a large moment (inertial force) acts on the blade surface on the blade tip portion 71 side of the blade portion 70Z2. The blade surface on the blade tip portion 71 side of the blade portion 70Z2 is elastically deformed so as to spread outward in the rotational radius direction. When propeller fan 50Z2 is formed of a resin molded product, the amount of elastic deformation is further increased. In order to prevent the blade tip 71 from interfering with the inner wall of the inner case 12, it is necessary to increase the inner diameter of the inner case 12.

(First modification)
FIG. 41 is a plan view showing propeller fan 50J in the first modification of the above-described second embodiment (see FIG. 35). Propeller fan 50J includes boss portion 60J and wing portion 70J. As described above, the value of hb / ha of the boss 60H (see FIG. 35) is preferably 1.5 or more. According to the said structure, the entrainment of hair hardly arises. On the other hand, when the value of hb / ha is increased, the amount of elastic deformation of the blade surface of the wing portion also increases when the propeller fan is rotating.

  As shown in FIG. 41, the outer peripheral edge portion 76 of the propeller fan 50J in the present modification has a shape that extends from the outer side to the inner side in the rotational radius direction as it goes to the blade tip portion 71. When propeller fan 50J is viewed from a direction parallel to rotating shaft 80 (in other words, when propeller fan 50J is viewed in plan), the dimension between rotating shaft 80 (upstream end 62) and blade tip 71 is determined. R1 is a value smaller than the dimension R2 between the rotating shaft 80 (upstream end portion 62) and the blade trailing end portion 75.

  Referring to FIG. 42, in a state where propeller fan 50J is stationary, blade tip 71 of blade portion 70J is not located on circle C10, but is located on the inner side in the radial direction of rotation than circle C10 (see FIG. 42). 42). On the other hand, when the propeller fan 50J is rotating, a large moment (inertial force) acts on the blade surface on the blade tip 71 side of the blade 70J. The blade surface on the blade tip portion 71 side of the blade portion 70J is elastically deformed so as to spread outward in the rotational radius direction (see arrow DR10). When propeller fan 50J is formed of a resin molded product, the amount of elastic deformation is further increased.

  In the propeller fan 50J of the present modification, the blade tip 71 is positioned in advance in the rotational radius direction. Even if the blade surface on the blade tip portion 71 side of the blade portion 70J is elastically deformed so as to spread outward in the rotational radius direction, interference with the inner wall of the inner case 12 is suppressed. When the propeller fan 50J is rotating at a predetermined rotational speed, the blade portion of the propeller fan 50J is rotated so that the portion of the outer peripheral edge portion 76 near the blade tip portion 71 rotates substantially along the circumferential direction (circle C10). 70J may be designed in advance. According to this configuration, high air blowing efficiency can be obtained in a range where the wing portion 70J does not interfere with the inner wall of the inner case 12.

(Second modification)
FIG. 43 is a cross-sectional view partially showing the blower device in the second modified example of the above-described second embodiment (see FIGS. 35 and 36). The air blower of the present modification includes an inner case 12A (air path forming member). Inner case 12A has inner wall part 12A1, and recessed part 12W provided so that it might be dented from inner wall part 12A1 toward the outside of the rotation radius direction of propeller fan 50J. The recess 12W has an annular shape, and the air path in the inner case 12A is wide at the recess 12W and narrow at the inner wall 12A1.

  In the direction parallel to the rotation axis 80, the most downstream portion 12W1 of the recess 12W is located upstream of the most downstream portion of the boss portion 60J (the downstream portion 67 in the boss portion 60J). In FIG. 43, for convenience, the position of the downstream portion 67 of the boss portion 60J in the direction parallel to the rotation shaft 80 is indicated using a line LL1.

  On the other hand, an extension line LL2 is obtained by virtually extending a tangent line formed at a portion of the blade surface of the blade portion 70J near the blade tip portion 71 toward the outer side in the rotational radius direction. In the inner case 12A of the present modification, in the direction parallel to the rotation shaft 80, the most downstream portion 12W1 of the recess 12W is located on the downstream side (the discharge port 16 side) from the extension line LL2. Furthermore, in the direction parallel to the rotation shaft 80, the most upstream portion 12W2 of the recess 12W is located upstream (on the suction port 15 side) of the extension line LL2.

  As the wing portion 70J rotates, a wing tip vortex is generated in the vicinity of the wing tip portion 71 of the wing portion 70J (see arrow DR3). The blade tip vortex is generated so as to extend toward the rear side in the rotation direction (arrow AR1 direction) with the vicinity of the blade tip 71 as a tip. By providing a portion (recess 12W) in which the air path spreads in the vicinity of the blade tip 71 in the inner case 12, the blade tip vortex enters the recess 12W by the action of centrifugal force, and the recess 12W is provided in the inner case 12. It occurs at a portion closer to the recess 12W than when not.

  Also in the air blower of the present modification, the blade tip vortex generation position indicated by the arrow DR3 and the vortex generation position generated near the downstream end (rear edge portion 74) of the blade portion 70J indicated by the arrow DR6. The distance between them is longer than that in the case of the above-described comparative example 2 (see FIG. 34). The width of the air passage through which air from the suction port 15 can smoothly flow toward the discharge port 16 is wider than the width W10 (see FIG. 34) of the second comparative example, and the air flow to the inner wall surface of the inner case 12A is large. The incident angle is also smaller than the incident angle θ10 (see FIG. 34) of Comparative Example 2.

  When the air from the suction port 15 contacts the inner wall surface of the inner case 12A, the flow toward the outside in the rotational radius direction is hardly repelled even if it contacts the inner wall surface of the inner case 12A. The air flowing along the outer surface 61 does not enter the inside, and the air in contact with the inner wall surface of the inner case 12A flows toward the downstream side as it is. Therefore, also in the air blower of this modified example, it is possible to effectively suppress foreign matters such as hair from being entangled with the output shaft 31 of the drive motor 30.

  In the inner case 12A of the present modification, the most downstream portion 12W1 of the recess 12W is located upstream of the most downstream portion of the boss portion 60J (the downstream portion 67 in the boss portion 60J), and is the most of the recess 12W. The downstream portion 12W1 is located on the downstream side (the discharge port 16 side) of the extension line LL2, and the most upstream portion 12W2 of the recess 12W is located on the upstream side (the suction port 15 side) of the extension line LL2. doing. Without being limited to this configuration, the inner case 12A of the present modification may be configured as follows.

  That is, in the direction parallel to the rotation shaft 80, the most downstream portion 12W1 of the recess 12W is located upstream of the most downstream portion of the boss portion 60J (the downstream portion 67 in the boss portion 60J). Further, the most downstream portion 12W1 of the recess 12W is located on the downstream side (discharge port 16 side) of the blade tip portion 71 of the blade portion 70J of the propeller fan 50J, and the most upstream portion 12W2 of the recess 12W is the propeller. The inner case 12A of the present modification may be configured so as to be located upstream of the blade tip portion 71 of the blade portion 70J of the fan 50J (on the suction port 15 side).

  Even in the inner case 12A having such a configuration, when the air from the suction port 15 comes into contact with the inner wall surface of the inner case 12A, the flow toward the outer side in the rotational radial direction is applied to the inner wall surface of the inner case 12A. Even if it touches, it is hardly repelled. The air flowing along the outer surface 61 does not enter the inside, and the air in contact with the inner wall surface of the inner case 12A flows toward the downstream side as it is. As a result, it is possible to effectively suppress foreign matters such as hair from being entangled with the output shaft 31 of the drive motor 30.

(Third Modification)
FIG. 44 is a cross-sectional view partially showing the blower device in the third modified example of the above-described second embodiment (see FIGS. 35 and 36). The air blower of this modification is provided with the inner case 12B (air path forming member). The inner case 12B has a first inner wall portion 12B1 and a second inner wall portion 12B2. The second inner wall portion 12B2 is located on the downstream side (discharge port 16 side) with respect to the first inner wall portion 12B1, and has a narrower air passage area than the first inner wall portion 12B1. A step is formed between the first inner wall portion 12B1 and the second inner wall portion 12B2, and the air passage in the inner case 12B is wide in the first inner wall portion 12B1 and narrowed in the second inner wall portion 12B2.

  In the direction parallel to the rotation axis 80, the most upstream portion 12BB of the second inner wall portion 12B2 is located upstream of the most downstream portion of the boss portion 60J (the downstream portion 67 in the boss portion 60J). To do. In FIG. 44, for convenience, the position of the downstream portion 67 of the boss portion 60J in the direction parallel to the rotation shaft 80 is indicated using a line LL1.

  On the other hand, an extension line LL2 is obtained by virtually extending a tangent line formed at a portion of the blade surface of the blade portion 70J near the blade tip portion 71 toward the outer side in the rotational radius direction. In the inner case 12B of the present modification, in the direction parallel to the rotation shaft 80, the most upstream portion 12BB of the second inner wall portion 12B2 is located on the downstream side (discharge port 16 side) with respect to the extension line LL2. ing.

  As the wing portion 70J rotates, a wing tip vortex is generated in the vicinity of the wing tip portion 71 of the wing portion 70J (see arrow DR3). The blade tip vortex is generated so as to extend toward the rear side in the rotation direction (arrow AR1 direction) with the vicinity of the blade tip 71 as a tip. By providing a portion (step between the first inner wall portion 12B1 and the second inner wall portion 12B2) where the air path spreads in the vicinity of the blade tip portion 71 in the inner case 12, the blade tip vortex is caused by the action of centrifugal force. It enters into the step between the first inner wall portion 12B1 and the second inner wall portion 12B2, and occurs at a portion closer to the first inner wall portion 12B1 than when the inner case 12 is not provided with a step.

  Also in the air blower of the present modification, the blade tip vortex generation position indicated by the arrow DR3 and the vortex generation position generated near the downstream end (rear edge portion 74) of the blade portion 70J indicated by the arrow DR6. The distance between them is longer than that in the case of the above-described comparative example 2 (see FIG. 34). The width of the air path through which air from the suction port 15 can smoothly flow toward the discharge port 16 is wider than the width W10 (see FIG. 34) of the second comparative example, and the air flow with respect to the inner wall surface of the inner case 12B. The incident angle is also smaller than the incident angle θ10 (see FIG. 34) of Comparative Example 2.

  When the air from the suction port 15 contacts the inner wall surface of the inner case 12B, the flow toward the outside in the rotational radius direction is hardly repelled even if it contacts the inner wall surface of the inner case 12B. The air flowing along the outer surface 61 does not enter the inside, and the air in contact with the inner wall surface of the inner case 12B flows directly downstream. Therefore, also in the air blower of this modified example, it is possible to effectively suppress foreign matters such as hair from being entangled with the output shaft 31 of the drive motor 30.

  In the inner case 12B of the present modification, the most upstream portion 12BB of the second inner wall portion 12B2 is located upstream of the most downstream portion of the boss portion 60J (the downstream portion 67 in the boss portion 60J), Further, the most upstream portion 12BB of the second inner wall portion 12B2 is located on the downstream side (the discharge port 16 side) of the extension line LL2. Without being limited to this configuration, the inner case 12B of the present modification may be configured as follows.

  That is, in the direction parallel to the rotation shaft 80, the most upstream portion 12BB of the second inner wall portion 12B2 is upstream of the most downstream portion of the boss portion 60J (the downstream portion 67 in the boss portion 60J). And the most upstream portion 12BB of the second inner wall portion 12B2 is located on the downstream side (discharge port 16 side) of the blade tip portion 71 of the blade portion 70J of the propeller fan 50J. The inner case 12B may be configured.

  Even in the inner case 12B having such a configuration, when the air from the suction port 15 comes into contact with the inner wall surface of the inner case 12B, the outward flow in the radial direction of the rotation is applied to the inner wall surface of the inner case 12B. Even if it touches, it is hardly repelled. The air flowing along the outer surface 61 does not enter the inside, and the air in contact with the inner wall surface of the inner case 12B flows directly downstream. As a result, it is possible to effectively suppress foreign matters such as hair from being entangled with the output shaft 31 of the drive motor 30.

[Embodiment 3]
FIG. 45 is a plan view showing propeller fan 50K and rectifying blade 40K in the present embodiment. FIG. 45 shows a state where the bearing 69 of the propeller fan 50K is attached to the output shaft 31 of the drive motor 30 (not shown). FIG. 46 is a plan view showing a state when the propeller fan 50K is attached to the drive motor 30 (not shown). 47 is an enlarged plan view showing a region surrounded by the XKVII line in FIG.

(Propeller fan 50K)
45 to 47, propeller fan 50K includes boss portion 60K and wing portion 70K, and has substantially the same shape as propeller fan 50 (see FIG. 12) in the first embodiment described above. . Propeller fan 50K is attached to output shaft 31 of the drive motor as shown by arrow DR50 in FIG.

  As shown in FIGS. 45 and 47, when propeller fan 50K is viewed from a direction parallel to rotation shaft 80 (not shown) (in other words, when propeller fan 50K is viewed in plan), reference line LA and A virtual straight line LB (third virtual straight line) is formed. The reference line LA is virtually obtained by connecting the innermost portion 79 of the trailing edge portion 74 of the blade portion 70K and the rotation shaft 80 (upstream end portion 62) in the rotational radius direction of the propeller fan 50K. Straight line.

  The imaginary straight line LB includes the innermost portion 79 of the trailing edge 74 of the blade portion 70K in the rotational radius direction of the propeller fan 50K and the trailing edge portion 74 of the blade portion 70K in the rotational radius direction of the propeller fan 50K. It is a straight line obtained virtually by connecting the outermost part (blade trailing end 75). An angle θA is formed between the reference line LA and the virtual straight line LB.

(Rectifier blade 40K)
As shown in FIG. 45, in the air blower of the present embodiment, five rectifying blades 40K are used. The plate-like portion 42 of the rectifying blade 40 </ b> K extends radially outward from the outer surface of the motor support portion 44. The five plate-like portions 42 are arranged at intervals in the circumferential direction so as not to reduce the flow rate of the airflow flowing from the suction port toward the discharge port. The plate-like portion 42 has an upstream edge portion 43 on the upstream side. The upstream edge 43 in the present embodiment has a planar shape and extends along a direction perpendicular to the rotation shaft 80 (not shown) of the propeller fan 50K.

  45 and 47, when the rectifying blade 40K is viewed from a direction parallel to the rotating shaft 80 (not shown) (in other words, when the rectifying blade 40K is viewed in plan), the reference line LC and A virtual straight line LD (fourth virtual straight line) is formed. The reference line LC is virtually obtained by connecting the innermost portion 47 of the upstream edge 43 of the rectifying blade 40K and the rotary shaft 80 (output shaft 31) in the rotational radius direction of the propeller fan 50K. It is a straight line.

  The virtual straight line LD has an innermost portion 47 of the upstream edge 43 of the rectifying blade 40K in the rotational radius direction of the propeller fan 50K, and an upstream edge 43 of the rectifying blade 40K in the rotational radius direction of the propeller fan 50K. It is a straight line obtained virtually by connecting the outermost portion 48 of them. An angle θB is formed between the reference line LC and the virtual straight line LD.

  With reference to FIG. 47, in the air blower of the present embodiment, the value of angle θA is 43 °, and the value of angle θB is −13 °. When the virtual straight lines LB and LD extend from the reference lines LA and LC so as to go forward in the rotational direction, the angles θA and θB are positive values. When the virtual straight lines LB and LD extend from the reference lines LA and LC so as to go to the rear side in the rotation direction, the angles θA and θB have negative values. In the air blower of the present embodiment, when the difference between the angle θA and the angle θB is θC, the angle difference θC = 43 − (− 13) = 56 (°).

  It is assumed that the angle difference θC = 0 °. In this case, the imaginary straight line LB formed along the trailing edge 74 of the wing part 70K and the imaginary straight line LD formed along the upstream edge part 43 of the rectifying blade 40K extend in the same direction. Has a shape. When these are viewed from a direction parallel to the rotary shaft 80 with the trailing edge 74 of the blade 70K and the upstream edge 43 of the rectifying blade 40K facing each other (in other words, the propeller fan 50K is viewed in plan view) In this case, the trailing edge portion 74 of the wing portion 70K and the upstream edge portion 43 of the rectifying blade 40K overlap almost or completely.

  When they are viewed in plan with the trailing edge 74 of the blade 70K and the upstream edge 43 of the rectifying blade 40K facing each other, they are completely overlapped with each other, and this occurs when the propeller fan 50K rotates. Noise increases. In the air blower of the present embodiment, since the angle difference θC = 56 °, generation of noise from the propeller fan 50K is effectively suppressed.

[Experimental Example 5]
Referring to FIG. 48, description will be given of Experimental Example 5 and the results relating to the above-described third embodiment (FIGS. 45 to 47). In the present experimental example, the angle θB (see FIG. 47) formed on the upstream edge 43 of the rectifying blade 40K in a state where the value of the angle θA (see FIG. 47) formed on the trailing edge 74 of the blade 70K is fixed. The value of (see) was changed. FIG. 48 is a diagram showing the relationship between the angle difference θC obtained at that time and the noise. As described above, the angle difference θC is a difference between the angle θA and the angle θB. In this experimental example, the value of the angle difference θC was changed from 0 ° to 120 ° by changing the value of the angle θB (see FIG. 47).

  A line L30 in FIG. 48 indicates that the virtual straight line LD formed at the upstream edge 43 of the rectifying blade 40K is directed to the rear side in the rotational direction from the virtual straight line LB formed at the rear edge 74 of the blade 70K. The relationship between the angle difference θC and the noise in the case of being present (case as shown in FIG. 47) is shown. A line L31 in FIG. 48 indicates that the virtual straight line LD formed at the upstream edge portion 43 of the rectifying blade 40K is more forward than the virtual straight line LB formed at the rear edge portion 74 of the blade portion 70K. The relationship between the angle difference θC and the noise in the case of being present is shown.

  Referring to the line L30 and the line L31, it can be seen that the noise decreases sharply as the value of the angle difference θC is increased from 0 °. It can be seen that when the value of the angle difference θC is 10 ° or more and 90 ° or less, the generation of noise is greatly suppressed. Therefore, the value of the angle difference θC, in other words, the angle formed between the virtual straight line LD formed at the upstream edge 43 of the rectifying blade 40K and the virtual straight line LB formed at the trailing edge 74 of the blade 70K is 10 °. It can be seen that the angle is preferably 90 ° or less.

  This is because when the airflow flows between the trailing edge 74 of the wing 70K and the upstream edge 43 of the rectifying blade 40K, the airflow is less likely to be disturbed, and the airflow is downstream along the rectifying wing 40K. This is because the so-called peak sound is less likely to occur when the trailing edge 74 of the wing 70K passes through the portion facing the upstream edge 43 of the rectifying blade 40K. Conceivable. In addition, when the value of the angle difference θC is 130 ° or more, the length of the rectifying blade 40K becomes longer, the time for the wing portion 70K and the rectifying blade 40K to overlap increases, and the noise reduction effect is slightly reduced. The result is obtained.

(First modification)
FIG. 49 is a plan view schematically showing propeller fan 50L1 and rectifying blade 40L1 in the first modification of the third embodiment. Propeller fan 50L1 has boss portion 60L1 and wing portion 70L1. When the propeller fan 50L1 is viewed in plan, the trailing edge portion 74 of the wing portion 70L1 has a substantially linear shape. A virtual straight line LB is formed on the trailing edge portion 74 of the wing portion 70L1 as in the third embodiment.

  When the straightening blade 40L1 is viewed in plan, the upstream edge 43 of the straightening blade 40L1 extends along the rotational radius direction. A virtual straight line LD is formed at the upstream edge 43 of the rectifying blade 40L1 as in the third embodiment. The upstream edge 43 (virtual straight line LD) of the rectifying blade 40L1 extends toward the rear side in the rotational direction from the rear edge 74 (virtual straight line LB) of the blade 70L1.

  Also in this modification, the value of the angle difference θC, in other words, the virtual straight line LD formed on the upstream edge 43 of the rectifying blade 40L1 and the virtual straight line LB formed on the trailing edge 74 of the blade 70L1 is formed. When the angle is 10 ° or more and 90 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50L1 is effectively suppressed. It becomes possible to do.

(Second modification)
FIG. 50 is a plan view schematically showing propeller fan 50L2 and rectifying blade 40L2 in the second modification of the third embodiment. Propeller fan 50L2 has boss portion 60L2 and wing portion 70L2. When the propeller fan 50L2 is viewed in plan, the rear edge portion 74 of the wing portion 70L2 has a substantially linear shape, and extends toward the front side in the rotation direction toward the outer peripheral side (the inner case 12 side). . A virtual straight line LB is formed on the trailing edge portion 74 of the wing portion 70L2 as in the third embodiment.

  When the rectifying blade 40L2 is viewed in plan, the upstream edge portion 43 of the rectifying blade 40L2 has a substantially linear shape, and extends toward the rear side in the rotation direction toward the outer peripheral side (the inner case 12 side). . A virtual straight line LD is formed at the upstream edge 43 of the rectifying blade 40L2 as in the third embodiment. The upstream edge 43 (virtual straight line LD) of the rectifying blade 40L2 extends toward the rear side in the rotational direction from the rear edge 74 (virtual straight line LB) of the blade 70L2.

  Also in this modification, the value of the angle difference θC, in other words, the virtual straight line LD formed on the upstream edge 43 of the rectifying blade 40L2 and the virtual straight line LB formed on the trailing edge 74 of the blade 70L2 is formed. When the angle is 10 ° or more and 90 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50L2 is effectively suppressed. It becomes possible to do.

(Third Modification)
FIG. 51 is a plan view schematically showing propeller fan 50L3 and rectifying blade 40L3 in the third modification of the third embodiment. Propeller fan 50L3 has boss portion 60L3 and wing portion 70L3. When the propeller fan 50L3 is viewed in plan, the rear edge portion 74 of the wing portion 70L3 has a substantially linear shape and extends along the rotational radius direction. A virtual straight line LB is formed on the trailing edge 74 of the wing 70L3, as in the third embodiment.

  When the flow straightening blade 40L3 is viewed in plan, the upstream edge 43 of the flow straightening blade 40L3 has an arc shape and extends toward the rear side in the rotation direction toward the outer peripheral side (the inner case 12 side). A virtual straight line LD is formed at the upstream edge 43 of the rectifying blade 40L3, as in the third embodiment. The upstream edge 43 (virtual straight line LD) of the rectifying blade 40L3 extends toward the rear side in the rotational direction from the rear edge 74 (virtual straight line LB) of the blade 70L3.

  Also in this modification, the value of the angle difference θC, in other words, the virtual straight line LD formed at the upstream edge 43 of the rectifying blade 40L3 and the virtual straight line LB formed at the trailing edge 74 of the blade 70L3. When the angle is 10 ° or more and 90 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50L3 is effectively suppressed. It becomes possible to do.

(Fourth modification)
FIG. 52 is a plan view schematically showing propeller fan 50L4 and rectifying blade 40L4 in the fourth modified example of the third embodiment. Propeller fan 50L4 has boss portion 60L4 and wing portion 70L4. When the propeller fan 50L4 is viewed in plan, the trailing edge portion 74 of the wing portion 70L4 has a curved shape, and a part in the rotational radius direction is formed to be recessed forward in the rotational direction. A virtual straight line LB is formed on the trailing edge 74 of the wing 70L4, as in the third embodiment.

  When the straightening blade 40L4 is viewed in plan, the upstream edge 43 of the straightening blade 40L4 has a linear shape, and extends toward the rear side in the rotational direction toward the outer peripheral side (the inner case 12 side). A virtual straight line LD is formed at the upstream edge 43 of the rectifying blade 40L4, as in the third embodiment. The upstream edge 43 (virtual straight line LD) of the rectifying blade 40L4 extends toward the rear side in the rotational direction from the rear edge 74 (virtual straight line LB) of the blade 70L4.

  Also in this modification, the value of the angle difference θC, in other words, the virtual straight line LD formed at the upstream edge 43 of the rectifying blade 40L4 and the virtual straight line LB formed at the trailing edge 74 of the blade 70L4. When the angle is 10 ° or more and 90 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50L4 is effectively suppressed. It becomes possible to do.

(5th modification)
FIG. 53 is a plan view schematically showing propeller fan 50L5 and rectifying blade 40L5 in the fifth modification of the third embodiment. Propeller fan 50L5 has boss portion 60L5 and wing portion 70L5. When the propeller fan 50L5 is viewed in plan, the trailing edge portion 74 of the wing portion 70L5 has a linear shape and extends along the rotational radius direction. A virtual straight line LB is formed on the trailing edge portion 74 of the wing portion 70L5, as in the third embodiment.

  When the flow straightening blade 40L5 is viewed in plan, the upstream edge 43 of the flow straightening blade 40L5 has a curved shape and extends toward the front side in the rotational direction toward the outer peripheral side (the inner case 12 side). A virtual straight line LD is formed at the upstream edge 43 of the rectifying blade 40L5, as in the third embodiment. The upstream edge 43 (virtual straight line LD) of the rectifying blade 40L5 extends toward the front side in the rotational direction from the rear edge 74 (virtual straight line LB) of the blade 70L5.

  Also in this modification, the value of the angle difference θC, in other words, the virtual straight line LD formed on the upstream edge 43 of the rectifying blade 40L5 and the virtual straight line LB formed on the trailing edge 74 of the blade 70L5 is formed. When the angle is not less than 10 ° and not more than 90 °, noise generated from the propeller fan 50L5 can be effectively suppressed.

(Sixth Modification)
FIG. 54 is a plan view schematically showing propeller fan 50L6 and rectifying blade 40L6 in the sixth modification of the third embodiment. Propeller fan 50L6 has boss portion 60L6 and wing portion 70L6. When the propeller fan 50L6 is viewed in plan, the rear edge portion 74 of the wing portion 70L6 has a linear shape and extends along the rotational radius direction. A virtual straight line LB is formed on the trailing edge 74 of the wing 70L6, as in the third embodiment.

  When the rectifying blade 40L6 is viewed in plan, the upstream edge 43 of the rectifying blade 40L6 has a linear shape and extends toward the front side in the rotational direction toward the outer peripheral side (the inner case 12 side). A virtual straight line LD is formed at the upstream edge 43 of the rectifying blade 40L6, as in the third embodiment. The upstream edge 43 (virtual straight line LD) of the rectifying blade 40L6 extends toward the front side in the rotational direction from the rear edge 74 (virtual straight line LB) of the blade 70L6.

  Also in this modification, the value of the angle difference θC, in other words, the virtual straight line LD formed at the upstream edge 43 of the rectifying blade 40L6 and the virtual straight line LB formed at the trailing edge 74 of the blade 70L6 is formed. When the angle is 10 ° or more and 90 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50L6 is effectively suppressed. It becomes possible to do.

(Seventh Modification)
FIG. 55 is a plan view schematically showing propeller fan 50L7 and rectifying blade 40L7 in the seventh modification of the third embodiment. Propeller fan 50L7 has boss portion 60L7 and wing portion 70L7. When the propeller fan 50L7 is viewed in plan, the trailing edge 74 of the wing 70L7 has a linear shape and extends along the rotational radius direction. A virtual straight line LB is formed on the trailing edge 74 of the wing 70L7, as in the third embodiment.

  When the straightening blade 40L7 is viewed in plan, the upstream edge portion 43 of the straightening blade 40L7 has a linear shape, and extends toward the rear side in the rotational direction toward the outer peripheral side (inner case 12 side). A virtual straight line LD is formed at the upstream edge 43 of the rectifying blade 40L7, as in the third embodiment. The upstream edge 43 (virtual straight line LD) of the rectifying blade 40L7 extends toward the rear side in the rotational direction from the rear edge 74 (virtual straight line LB) of the blade 70L7.

  Also in this modification, the value of the angle difference θC, in other words, the virtual straight line LD formed on the upstream edge 43 of the rectifying blade 40L7 and the virtual straight line LB formed on the trailing edge 74 of the blade 70L7 is formed. When the angle is not less than 10 ° and not more than 90 °, the so-called peak sound is hardly generated because the airflow can flow smoothly toward the downstream side, and as a result, the noise generated from the propeller fan 50L7 is effectively suppressed. It becomes possible to do.

(Eighth modification)
FIG. 56 is a plan view schematically showing a propeller fan blade portion 70M1 and a rectifying blade upstream edge portion 43 in an eighth modification of the third embodiment. When the wing portion 70M1 is viewed in plan, the rear edge portion 74 of the wing portion 70M1 has an arc shape and is curved convexly toward the rear side in the rotation direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a linear shape.

  Each of the trailing edge portion 74 of the wing portion 70M1 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they are opposed to each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(Ninth Modification)
FIG. 57 is a plan view schematically showing a propeller fan blade portion 70M2 and a rectifying blade upstream edge portion 43 in a ninth modification of the third embodiment. When the wing part 70M2 is viewed in plan, the rear edge part 74 of the wing part 70M2 has an arc shape and is curved in a concave shape toward the front side in the rotation direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a linear shape.

  Each of the trailing edge portion 74 of the wing portion 70M2 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they face each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(10th modification)
FIG. 58 is a plan view schematically showing a propeller fan blade portion 70M3 and a rectifying blade upstream edge portion 43 in a tenth modification example of the third embodiment. When the wing portion 70M3 is viewed in a plan view, the trailing edge portion 74 of the wing portion 70M3 has a curved shape, and a part in the rotational radius direction is formed to be recessed forward in the rotational direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a linear shape.

  Each of the trailing edge portion 74 of the wing portion 70M3 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they face each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(Eleventh modification)
FIG. 59 is a plan view schematically showing a propeller fan blade portion 70M4 and a rectifying blade upstream edge portion 43 in an eleventh modification of the third embodiment. When the wing portion 70M4 is viewed in plan, the rear edge portion 74 of the wing portion 70M4 has a curved shape, and a part in the rotational radius direction is formed so as to protrude toward the rear side in the rotational radius direction. Yes. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a curved shape and is curved in a convex shape toward the front side in the rotational direction.

  Each of the trailing edge portion 74 of the wing portion 70M4 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they face each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(Twelfth modification)
FIG. 60 is a plan view schematically showing a propeller fan blade 70M5 and a rectifying blade upstream edge 43 in a twelfth modification of the third embodiment. When the wing portion 70M5 is viewed in plan, the trailing edge portion 74 of the wing portion 70M5 has an arc shape and is curved in a convex shape toward the rear side in the rotation direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a curved shape and is curved in a convex shape toward the front side in the rotational direction.

  Each of the trailing edge portion 74 of the wing portion 70M5 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they are opposed to each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(13th modification)
FIG. 61 is a plan view schematically showing a propeller fan blade portion 70M6 and a rectifying blade upstream edge portion 43 in a thirteenth modification example of the third embodiment. When the wing portion 70M6 is viewed in plan, the trailing edge portion 74 of the wing portion 70M6 has a linear shape and extends along the rotational radius direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a curved shape and is curved in a convex shape toward the front side in the rotational direction.

  Each of the trailing edge portion 74 of the wing portion 70M6 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotary shaft 80 (not shown) in a state where they are opposed to each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(14th modification)
FIG. 62 is a plan view schematically showing a propeller fan blade portion 70M7 and a rectifying blade upstream edge portion 43 in a fourteenth modification of the third embodiment. When the wing portion 70M7 is viewed in plan, the rear edge portion 74 of the wing portion 70M7 has a linear shape and extends along the rotational radius direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a curved shape and is curved in a concave shape toward the rear side in the rotational direction.

  Each of the trailing edge portion 74 of the wing portion 70M7 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they face each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(15th modification)
FIG. 63 is a plan view schematically showing a propeller fan blade portion 70M8 and a rectifying blade upstream edge portion 43 in a fifteenth modification of the third embodiment. When the wing portion 70M8 is viewed in plan, the trailing edge portion 74 of the wing portion 70M8 has a curved shape, and a part in the rotational radius direction is formed to be recessed forward in the rotational direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has a linear shape.

  Each of the trailing edge portion 74 of the wing portion 70M8 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they face each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

(16th modification)
FIG. 64 is a plan view schematically showing a propeller fan blade portion 70M9 and a rectifying blade upstream edge portion 43 in a sixteenth modification of the third embodiment. When the wing portion 70M9 is viewed in plan, the rear edge portion 74 of the wing portion 70M9 has an arc shape and is curved in a concave shape toward the front side in the rotation direction. When the upstream edge 43 of the rectifying blade is viewed in plan, the upstream edge 43 has an arc shape and is curved in a concave shape toward the rear side in the rotation direction.

  Each of the trailing edge portion 74 of the wing portion 70M9 and the upstream edge portion 43 of the rectifying blade is viewed when viewed from a direction parallel to the rotating shaft 80 (not shown) in a state where they face each other. Only a part of the crossing. In the case of this modification as well, since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan can be effectively suppressed.

[Embodiment 4]
FIG. 65 is a cross-sectional view showing propeller fan 50N and rectifying blade 40N in the present embodiment. FIG. 66 is an enlarged cross-sectional view showing propeller fan 50N and rectifying blade 40N in the present embodiment.

(Propeller fan 50N)
65 and 66, propeller fan 50N includes boss portion 60N and wing portion 70N, and has substantially the same shape as propeller fan 50 (see FIG. 10) in the first embodiment described above. .

  As shown in FIG. 66, when propeller fan 50N is viewed from a direction perpendicular to rotating shaft 80 (not shown) (in other words, when propeller fan 50N is viewed from the side), reference line LP and virtual straight line LQ are displayed. (First virtual straight line) is formed. The reference line LP passes through the innermost portion 79 of the trailing edge 74 of the blade portion 70N in the rotational radial direction of the propeller fan 50N and extends in a direction perpendicular to the rotation axis 80 of the propeller fan 50N. Straight line.

  The imaginary straight line LQ has an innermost portion 79 of the trailing edge 74 of the wing 70N in the rotational radius direction of the propeller fan 50N and a rear edge 74 of the wing 70N in the rotational radius of the propeller fan 50N. It is a straight line obtained virtually by connecting the outermost part (blade trailing end 75). An angle θP is formed between the reference line LP and the virtual straight line LQ.

(Rectifier blade 40N)
As shown in FIG. 66, when the rectifying blade 40N is viewed from a direction perpendicular to the rotating shaft 80 (not shown) (in other words, when the rectifying blade 40N is viewed from the side), the reference line LR and the virtual straight line LS. (Second virtual straight line) is formed. The reference line LR passes through the innermost portion 47 of the upstream edge 43 of the rectifying blade 40N in the radial direction of rotation of the propeller fan 50N and extends in a direction perpendicular to the rotation axis 80 of the propeller fan 50N. Straight line.

  The virtual straight line LS includes the innermost portion 47 of the upstream edge 43 of the rectifying blade 40N in the rotational radius direction of the propeller fan 50N and the upstream edge 43 of the rectifying blade 40N in the rotational radius direction of the propeller fan 50N. It is a straight line obtained virtually by connecting the outermost portion 48 of them. An angle θQ (not shown. In the present embodiment, an angle θQ = 0 °) is formed between the reference line LR and the virtual straight line LS.

  In the air blower of the present embodiment, the value of the angle θP is 23 °, and the value of the angle θQ is 0 °. When the virtual straight lines LQ, LS extend from the reference lines LP, LR toward the upstream side (the side of the suction port 15) in the airflow direction, the angles θP, θQ are positive values. When the virtual straight lines LQ, LS extend from the reference lines LP, LR toward the downstream side (the discharge port 16 side) in the airflow direction, the angles θP, θQ are negative values. In the blower of the present embodiment, if the difference between the angle θP and the angle θQ is θT, the angle difference θT = 23−0 = 23 (°).

  It is assumed that the angle difference θT = 0 °. In this case, the imaginary straight line LQ formed along the trailing edge 74 of the wing part 70N and the imaginary straight line LS formed along the upstream edge part 43 of the rectifying blade 40N are in a parallel relationship and are identical to each other. The shape extends in the direction of. While looking at these from a direction perpendicular to the rotating shaft 80 with the trailing edge 74 of the blade 70N and the upstream edge 43 of the rectifying blade 40N facing each other (in other words, the propeller fan 50N is viewed from the side. However, when one of these is virtually moved along the direction parallel to the rotation axis 80 toward the other of these and brought into contact with each other (see arrow AR2 in FIG. 65), No gap is formed between them.

  On the other hand, in the air blower of the present embodiment, the angle difference θT = 23 °. While looking at these from a direction perpendicular to the rotating shaft 80 with the trailing edge 74 of the blade 70N and the upstream edge 43 of the rectifying blade 40N facing each other (in other words, the propeller fan 50N is viewed from the side. However, when one of these is virtually moved along the direction parallel to the rotation axis 80 toward the other of these and brought into contact with each other (see arrow AR2 in FIG. 65), A gap S (see FIG. 65) is formed between them. Therefore, in the air blower of the present embodiment, the generation of noise from the propeller fan 50N is effectively suppressed.

[Experimental Example 6]
With reference to FIG. 67, Experimental Example 6 and its results relating to the above-described fourth embodiment (FIGS. 65 and 66) will be described. In the present experimental example, the angle θQ (see FIG. 66) formed at the upstream edge 43 of the rectifying blade 40N in a state where the value of the angle θP (see FIG. 66) formed at the trailing edge 74 of the blade 70N is fixed. In FIG. 69, the values shown in FIGS. 69 to 71 were changed. FIG. 67 is a diagram showing the relationship between the angle difference θT obtained at that time and noise. As described above, the angle difference θT is a difference between the angle θP and the angle θQ. The gap between the blade portion 70N and the rectifying blade 40N is a fixed value of 2.27 mm at the narrowest portion.

  A line L40 in FIG. 67 indicates that the virtual straight line LS formed at the upstream edge 43 of the rectifying blade 40N is upstream of the virtual straight line LQ formed at the trailing edge 74 of the blade 70N in the airflow direction. The relationship between the angle difference θT and the noise in the case of facing (case as shown in FIGS. 70 and 72) is shown. A line L41 in FIG. 67 indicates that the virtual straight line LS formed at the upstream edge 43 of the rectifying blade 40N is downstream of the virtual straight line LQ formed at the trailing edge 74 of the blade 70N in the direction in which the airflow flows. The relationship between the angle difference θT and noise in the case of facing (cases as shown in FIGS. 66, 68, 69 and 71) is shown.

  Referring to line L40 and line L41, it can be seen that the noise decreases sharply as the value of angle difference θT is increased from 0 °. It can be seen that when the value of the angle difference θT is 10 ° or more and 80 ° or less, the generation of noise is greatly suppressed. Therefore, the value of the angle difference θT, in other words, the angle formed by the virtual straight line LS formed at the upstream edge 43 of the rectifying blade 40N and the virtual straight line LQ formed at the trailing edge 74 of the blade 70N is 10 °. It can be seen that the angle is preferably 80 ° or less.

  This is because when the airflow flows between the trailing edge 74 of the wing 70N and the upstream edge 43 of the rectifying blade 40N, the airflow is less likely to be disturbed, and the airflow is downstream along the rectifying wing 40N. This is because the so-called peak sound is less likely to occur when the trailing edge 74 of the wing 70N passes through the portion facing the upstream edge 43 of the rectifying wing 40N. Conceivable.

  When the upstream edge 43 of the rectifying blade 40N is not perpendicular to the rotating shaft 80 and the trailing edge 74 of the blade 70N is formed to be largely inclined, the value of the angle difference θT is 90 ° or more. There are cases where Although it is almost difficult to make such a shape, even if it is made, when the value of the angle difference θT exceeds 80 °, there is a portion where the distance between the rectifying blade 40N and the blade portion 70N is greatly separated. As a result, the swirl component cannot be recovered, loss occurs, and the noise reduction effect is somewhat reduced.

(First modification)
FIG. 68 is a cross-sectional view showing propeller fan 50P and rectifying blade 40P in the first modification of the fourth embodiment. Propeller fan 50P has boss portion 60P and wing portion 70P. When the propeller fan 50P is viewed from the side, the rear edge portion 74 of the wing portion 70P has a curved shape and is formed so as to protrude toward the downstream side in the direction in which the airflow flows toward the outside. A virtual straight line LQ is formed on the trailing edge portion 74 of the wing portion 70P, as in the fourth embodiment described above.

  When the rectifying blade 40 </ b> P is viewed from the side, the upstream edge 43 of the rectifying blade 40 </ b> P extends along a direction perpendicular to the rotation shaft 80. A virtual straight line LS is formed at the upstream edge 43 of the rectifying blade 40P, as in the fourth embodiment. The upstream edge portion 43 (virtual straight line LS) of the rectifying blade 40P extends from the rear edge portion 74 (virtual straight line LQ) of the blade portion 70P toward the downstream side in the airflow direction.

  Also in the case of this modification, the rear edge portion 74 of the blade portion 70P and the upstream edge portion 43 of the rectifying blade 40P face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, When propeller fan 50P is viewed from the side), when one of these is virtually moved along the direction parallel to rotation axis 80 toward the other of these, they are brought into contact with each other. A gap is formed between them.

  Also in this modification, the value of the angle difference θT, in other words, the virtual straight line LS formed at the upstream edge 43 of the rectifying blade 40P and the virtual straight line LQ formed at the trailing edge 74 of the blade 70P. When the angle is 10 ° or more and 80 ° or less, the air current can flow smoothly toward the downstream side, so that so-called peak sound is hardly generated, and as a result, noise generated from the propeller fan 50P is effectively suppressed. It becomes possible to do.

(Second modification)
FIG. 69 is a cross-sectional view showing propeller fan 50Q and rectifying blade 40Q in the second modification of the fourth embodiment. Propeller fan 50Q has a boss portion 60Q and a wing portion 70Q. When the propeller fan 50Q is viewed from the side, the trailing edge portion 74 of the wing portion 70Q has a linear shape and extends along a direction perpendicular to the rotation shaft 80. A virtual straight line LQ is formed on the trailing edge portion 74 of the wing portion 70Q, as in the fourth embodiment.

  When the rectifying blade 40Q is viewed from the side, the upstream edge portion 43 of the rectifying blade 40Q has a linear shape, and extends toward the downstream side in the direction in which the airflow flows toward the outside. A virtual straight line LS is formed at the upstream edge 43 of the rectifying blade 40Q, as in the fourth embodiment. The upstream edge portion 43 (virtual straight line LS) of the rectifying blade 40Q extends toward the downstream side in the airflow direction from the rear edge portion 74 (virtual straight line LQ) of the blade portion 70Q.

  Also in the case of this modified example, the rear edge portion 74 of the blade portion 70Q and the upstream edge portion 43 of the rectifying blade 40Q face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, When propeller fan 50Q is viewed from the side), when one of these is virtually moved toward the other of them along a direction parallel to rotation axis 80 and brought into contact with each other, these A gap is formed between them.

  Also in this modification, the value of the angle difference θT, in other words, the virtual straight line LS formed at the upstream edge 43 of the rectifying blade 40Q and the virtual straight line LQ formed at the trailing edge 74 of the blade 70Q. When the angle is 10 ° or more and 80 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50Q is effectively suppressed. It becomes possible to do.

(Third Modification)
FIG. 70 is a cross-sectional view showing propeller fan 50R and rectifying blade 40R in the third modification of the fourth embodiment. Propeller fan 50R has boss portion 60R and wing portion 70R. When the propeller fan 50R is viewed from the side, the rear edge portion 74 of the wing portion 70R has a linear shape and extends along a direction perpendicular to the rotation shaft 80. A virtual straight line LQ is formed on the trailing edge portion 74 of the wing portion 70R, as in the fourth embodiment.

  When the rectifying blade 40R is viewed from the side, the upstream edge 43 of the rectifying blade 40R has a linear shape, and extends toward the upstream side in the direction in which the airflow flows toward the outside. A virtual straight line LS is formed at the upstream edge 43 of the rectifying blade 40R, as in the fourth embodiment. The upstream edge portion 43 (virtual straight line LS) of the rectifying blade 40R extends toward the upstream side in the airflow direction from the rear edge portion 74 (virtual straight line LQ) of the blade portion 70R.

  Also in the case of this modification, the rear edge portion 74 of the blade portion 70R and the upstream edge portion 43 of the rectifying blade 40R face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, When one of these is virtually moved along the direction parallel to the rotation axis 80 toward the other of the propeller fan 50R and viewed from the side, A gap is formed between them.

  Also in this modification, the value of the angle difference θT, in other words, the virtual straight line LS formed at the upstream edge 43 of the rectifying blade 40R and the virtual straight line LQ formed at the trailing edge 74 of the blade 70R is formed. When the angle is 10 ° or more and 80 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50R is effectively suppressed. It becomes possible to do.

(Fourth modification)
FIG. 71 is a cross-sectional view showing propeller fan 50S and rectifying blade 40S in a fourth modification of the fourth embodiment. Propeller fan 50S has boss portion 60S and wing portion 70S. When the propeller fan 50S is viewed from the side, the trailing edge portion 74 of the wing portion 70S has a curved shape, and extends toward the upstream side in the direction in which the airflow flows toward the outside. A virtual straight line LQ is formed on the trailing edge portion 74 of the wing portion 70S, as in the fourth embodiment.

  When the rectifying blade 40S is viewed from the side, the upstream edge portion 43 of the rectifying blade 40S has a linear shape, and extends toward the downstream side in the direction in which the airflow flows toward the outside. A virtual straight line LS is formed at the upstream edge 43 of the rectifying blade 40S, as in the fourth embodiment. The upstream edge 43 (virtual straight line LS) of the rectifying blade 40S extends toward the downstream side of the airflow direction from the rear edge 74 (virtual straight line LQ) of the blade 70S.

  Also in the case of this modified example, the rear edge portion 74 of the blade portion 70S and the upstream edge portion 43 of the rectifying blade 40S face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, When one of these is virtually moved along the direction parallel to the rotation axis 80 toward the other of the propeller fan 50S and viewed from the side, A gap is formed between them.

  Also in this modification, the value of the angle difference θT, in other words, the virtual straight line LS formed at the upstream edge 43 of the rectifying blade 40S and the virtual straight line LQ formed at the trailing edge 74 of the blade 70S. When the angle is 10 ° or more and 80 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50S is effectively suppressed. It becomes possible to do.

(5th modification)
FIG. 72 is a cross-sectional view showing propeller fan 50T and rectifying blade 40T in the fifth modification example of the fourth embodiment. Propeller fan 50T has boss portion 60T and wing portion 70T. When the propeller fan 50T is viewed from the side, the trailing edge 74 of the wing portion 70T has a curved shape extending toward the downstream side in the direction in which the airflow flows, and on the upstream side in the direction in which the airflow flows toward the outside. It is formed to be recessed. A virtual straight line LQ is formed on the trailing edge portion 74 of the wing portion 70T, as in the fourth embodiment.

  When the rectifying blade 40T is viewed from the side, the upstream edge 43 of the rectifying blade 40T has a linear shape, and extends toward the upstream side in the direction in which the airflow flows toward the outside. A virtual straight line LS is formed at the upstream edge 43 of the rectifying blade 40T, as in the fourth embodiment. The upstream edge portion 43 (virtual straight line LS) of the rectifying blade 40T extends toward the upstream side in the airflow direction from the rear edge portion 74 (virtual straight line LQ) of the blade portion 70T.

  Also in the case of this modification, the rear edge portion 74 of the wing portion 70T and the upstream edge portion 43 of the rectifying blade 40T face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, When the propeller fan 50T is viewed from the side), when one of these is virtually moved toward the other of the propeller fans 50T in the direction parallel to the rotation axis 80 and brought into contact with each other, A gap is formed between them.

  Also in this modification, the value of the angle difference θT, in other words, the imaginary straight line LS formed at the upstream edge 43 of the rectifying blade 40T and the imaginary straight line LQ formed at the trailing edge 74 of the wing 70T. When the angle is 10 ° or more and 80 ° or less, the air current can flow smoothly toward the downstream side, so that a so-called peak sound is hardly generated, and as a result, the noise generated from the propeller fan 50T is effectively suppressed. It becomes possible to do.

(Sixth Modification)
FIG. 73 is a side view schematically showing a propeller fan blade portion 70U1 and a rectifying blade 40U1 according to a sixth modification of the fourth embodiment. When the wing portion 70U1 of the propeller fan is viewed from the side, the rear edge portion 74 of the wing portion 70U1 has an arc shape and is curved in a convex shape toward the downstream side in the direction in which the airflow flows. When the rectifying blade 40U1 is viewed from the side, the upstream edge 43 has a linear shape and extends along a direction perpendicular to the rotation shaft 80.

  Also in the case of this modified example, the rear edge portion 74 of the wing portion 70U1 and the upstream edge portion 43 of the rectifying blade 40U1 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(Seventh Modification)
FIG. 74 is a side view schematically showing a propeller fan blade portion 70U2 and a rectifying blade 40U2 according to a seventh modification of the fourth embodiment. When the wing portion 70U2 of the propeller fan is viewed from the side, the rear edge portion 74 of the wing portion 70U2 has an arc shape and is curved in a concave shape toward the upstream side in the direction in which the airflow flows. When the rectifying blade 40U2 is viewed from the side, the upstream edge portion 43 has a linear shape.

  Also in the case of this modified example, the rear edge portion 74 of the wing portion 70U2 and the upstream edge portion 43 of the rectifying blade 40U2 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(Eighth modification)
FIG. 75 is a side view schematically showing a propeller fan blade portion 70U3 and a rectifying blade 40U3 according to an eighth modification of the fourth embodiment. When the wing portion 70U3 of the propeller fan is viewed from the side, the trailing edge portion 74 of the wing portion 70U3 has a curved shape and is formed so as to protrude toward the downstream side in the direction in which the airflow flows toward the outside. In addition, a part in the rotational radius direction is formed to be recessed upstream in the direction in which the airflow flows. When the rectifying blade 40U3 is viewed from the side, the upstream edge portion 43 has a linear shape.

  Also in the case of this modified example, the rear edge portion 74 of the wing portion 70U3 and the upstream edge portion 43 of the rectifying blade 40U3 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(Ninth Modification)
FIG. 76 is a side view schematically showing a propeller fan blade 70U4 and a rectifying blade 40U4 according to a ninth modification of the fourth embodiment. When the wing portion 70U4 of the propeller fan is viewed from the side, the trailing edge portion 74 of the wing portion 70U4 has a curved shape, and a part of the rotational radial direction protrudes toward the downstream side in the airflow direction. Is formed. When the rectifying blade 40U4 is viewed from the side, the upstream edge portion 43 has an arc shape and is curved in a convex shape toward the upstream side in the direction in which the airflow flows.

  Also in the case of this modified example, the rear edge portion 74 of the wing portion 70U4 and the upstream edge portion 43 of the rectifying blade 40U4 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(10th modification)
FIG. 77 is a side view schematically showing a propeller fan blade 70U5 and a rectifying blade 40U5 according to a tenth modification of the fourth embodiment. When the wing portion 70U5 of the propeller fan is viewed from the side, the rear edge portion 74 of the wing portion 70U5 has an arc shape and is curved convexly toward the downstream side in the direction in which the airflow flows. . When the rectifying blade 40U5 is viewed from the side, the upstream edge portion 43 has an arc shape and is curved in a convex shape toward the upstream side in the direction in which the airflow flows.

  Also in the case of this modification, the rear edge portion 74 of the wing portion 70U5 and the upstream edge portion 43 of the rectifying blade 40U5 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(Eleventh modification)
FIG. 78 is a side view schematically showing a propeller fan blade portion 70U6 and a rectifying blade 40U6 according to an eleventh modification of the fourth embodiment. When the wing portion 70U6 of the propeller fan is viewed from the side, the rear edge portion 74 of the wing portion 70U6 has a linear shape and extends along a direction orthogonal to the rotation shaft 80. When the rectifying blade 40U6 is viewed from the side, the upstream edge 43 has an arc shape and is curved in a convex shape toward the upstream side in the direction in which the airflow flows.

  Also in the case of this modification, the rear edge portion 74 of the wing portion 70U6 and the upstream edge portion 43 of the rectifying blade 40U6 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(Twelfth modification)
FIG. 79 is a side view schematically showing a propeller fan blade portion 70U7 and a rectifying blade 40U7 according to a twelfth modification of the fourth embodiment. When the wing portion 70U7 of the propeller fan is viewed from the side, the rear edge portion 74 of the wing portion 70U7 has a linear shape and extends along a direction orthogonal to the rotation shaft 80. When the rectifying blade 40U7 is viewed from the side, the upstream edge portion 43 has an arc shape and is curved in a concave shape toward the downstream side in the direction in which the airflow flows.

  Also in the case of this modified example, the rear edge portion 74 of the wing portion 70U7 and the upstream edge portion 43 of the rectifying blade 40U7 are opposed to each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(13th modification)
FIG. 80 is a side view schematically showing a propeller fan blade 70U8 and a rectifying blade 40U8 according to a thirteenth modification of the fourth embodiment. When the wing portion 70U8 of the propeller fan is viewed from the side, the trailing edge portion 74 of the wing portion 70U8 has a curved shape, and a part in the rotational radial direction is formed to be recessed upstream in the direction in which the airflow flows. Has been. When the rectifying blade 40U8 is viewed from the side, the upstream edge portion 43 has a linear shape.

  Also in the case of this modified example, the rear edge portion 74 of the wing portion 70U8 and the upstream edge portion 43 of the rectifying blade 40U8 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(14th modification)
FIG. 81 is a side view schematically showing a propeller fan blade 70U9 and a rectifying blade 40U9 according to a fourteenth modification of the fourth embodiment. When the wing portion 70U9 of the propeller fan is viewed from the side, the rear edge portion 74 of the wing portion 70U9 has an arc shape and is curved in a concave shape toward the upstream side in the direction in which the airflow flows. When the rectifying blade 40U9 is viewed from the side, the upstream edge portion 43 has an arc shape and is curved in a concave shape toward the downstream side in the direction in which the airflow flows.

  Also in the case of this modified example, the rear edge portion 74 of the wing portion 70U9 and the upstream edge portion 43 of the rectifying blade 40U9 face each other while looking at them from a direction perpendicular to the rotation shaft 80 (in other words, While viewing the propeller fan in a side view, one of these is virtually moved along the direction parallel to the rotation axis 80 (the direction of the arrow AR2) toward the other of these to bring them into contact with each other Sometimes a gap S is formed between them. Since the airflow can flow smoothly toward the downstream side, so-called peak sound is hardly generated, and as a result, it is possible to effectively suppress noise generated from the propeller fan.

(Other variations)
In each of the above-described embodiments and modifications, the propeller fan and the rectifying blade used in the blower device may include only the features according to the above-described Embodiment 3 (including each modification). Only the features according to the fourth embodiment (including the respective modifications) may be provided, or both of these features may be provided. When the air blower has the characteristics of both the third and fourth embodiments, the generation of noise can be further reduced.

  Assuming that the number of blades used in the propeller fan is M and the number of rectifying blades is N, both M and N are prime numbers, and the relationship 2M ± 1 = N or 2N ± 1 = M is established. Good. For example, when the number M of wing parts is 3, the number N of rectifying wings is preferably 7. Other combinations include 7 and 13 sheets, 3 and 5 sheets, 5 and 11 sheets, and the like. When this relationship is established, the peak sound is less likely to be generated, and as a result, the noise generated from the propeller fan can be effectively suppressed.

  In each above-mentioned embodiment and each modification, the air blower may be provided with the ion generating part inside main part 10 (refer to Drawing 9). Moisture and gloss can be given to the hair and scalp by placing ions in the wind sent by the propeller fan. Furthermore, the generation of static electricity by ions may be suppressed, and damage to hair may be reduced.

  In each above-mentioned embodiment and each modification, the air blower may be provided with the light-emitting part. In this case, the light emitting unit is formed of a light source such as an LED (light emitting diode) disposed in the main body 10 (see FIG. 9) and a synthetic resin material having translucency such as acrylic that guides light from the light source. A light guide member.

  This light emission part can be utilized as a display means of the operation mode of the air blower as a hair dryer. For example, when a heater is used and hot air is blown out, the color is red. When a heater is not used and cold air is blown out, it is green. When the ion emitter is in operation and ions are released. The color can be changed according to the operating state, such as blue. In this case, a plurality of light sources corresponding to each color are mounted, and the control circuit controls the light emission of the plurality of light sources. It is possible to blink the light source by the control circuit, control the blinking interval, and change the light emission intensity, and it is also possible to set these light emission modes corresponding to various operation modes. .

  As mentioned above, although each embodiment and each experimental example based on this invention were demonstrated, each disclosed embodiment and each experimental example are illustrations in all points, and are not restrictive. The technical scope of the present invention is defined by the terms of the claims, and is intended to include any modifications within the scope and meaning equivalent to the terms of the claims.

  10 body part, 11 outer case, 12, 12A, 12B inner case (air channel forming member), 12A1 inner wall part, 12B1 first inner wall part, 12B2 second inner wall part, 12BB, 12W1, 12W2, 47, 48, 79 part , 12W recess, 13 inlet opening, 14 outlet opening, 15 suction port, 16 discharge port, 17 heater, 20 gripping part, 21 tip, 22 rear end, 23 operation part, 24 power cord, 30 drive motor, 31 output shaft, 40, 40K, 40L1, 40L2, 40L3, 40L4, 40L5, 40L6, 40L7, 40N, 40P, 40Q, 40R, 40S, 40T, 40U1, 40U2, 40U3, 40U4, 40U5, 40U6, 40U7, 40U8, 40U9, 40Z Wings, 42 Plate-shaped part, 43 Upstream edge part, 44 Motor support part, 44A circumference 44B Bottom wall, 44C hole, 46 annular wall, 50, 50H, 50J, 50K, 50L1, 50L2, 50L3, 50L4, 50L5, 50L6, 50L7, 50N, 50P, 50Q, 50R, 50S, 50T, 50Z, 50Z1, 50Z2 propeller fan, 60, 60A, 60B1, 60B2, 60B3, 60B4, 60C, 60D1, 60D2, 60D3, 60E1, 60E2, 60E3, 60F, 60G, 60H, 60J, 60K, 60L1, 60L2, 60L3, 60L4, 60L5 60L6, 60L7, 60N, 60P, 60Q, 60R, 60S, 60T, 60Z, 60Z1, 60Z2, 60ZA, 60ZB Boss portion, 61 outer surface, 62 upstream end, 62T outer edge, 63 main flow surface, 64 upstream surface, 65 downstream End 66 downstream surface 66 A 1st downstream surface, 66B 2nd downstream surface, 67 downstream part, 68 inner surface, 69 bearing part, 70, 70H, 70J, 70K, 70L1, 70L2, 70L3, 70L4, 70L5, 70L6, 70L7, 70M1, 70M2, 70M3, 70M4, 70M5, 70M6, 70M7, 70M8, 70M9, 70N, 70P, 70Q, 70R, 70S, 70T, 70U1, 70U2, 70U3, 70U4, 70U5, 70U6, 70U7, 70U8, 70U9, 70Z, 70Z1, 70Z2 Part, 71 blade tip, 72 leading edge, 72H root, 73 root, 74 trailing edge, 75 blade trailing edge, 76 outer peripheral edge, 80 rotating shaft, 100, 200 blower, AR1 arrow (rotating direction) ), AR2, DR1, DR2, DR3, DR4, DR5, DR6, DR10, R50 arrow, C10 circle, CL minimum gap, D1, D2 outer diameter, Hh, ha, haz, hb, hbz, R1, R2 dimensions, L1, L2, L3, L4, L5, L6, L10, L20, L21, L30 , L31, L40, L41, LL1 line, LA, LC, LP, LR reference line, LB virtual straight line (third virtual straight line), LD virtual straight line (fourth virtual straight line), LQ virtual straight line (first virtual straight line), LS virtual straight line (second virtual straight line), LL2 extension line, S gap, W10, W11 width, θ1, θ2 inner angle, θ10, θ11 incident angle, θA, θB, θP, θQ angles, θC, θT angular difference.

Claims (5)

An air passage forming member including a suction port and a discharge port;
A drive motor including an output shaft and provided inside the air passage forming member;
A propeller fan that includes a boss portion attached to the output shaft and a wing portion provided on an outer surface of the boss portion, and is disposed closer to the suction port than the drive motor,
The propeller fan generates airflow flowing from the upstream suction port toward the downstream discharge port by receiving rotation power from the drive motor and rotating around a virtual rotation axis,
The wing part is
A blade tip located at the most tip in the rotation direction of the propeller fan;
A leading edge extending from the blade tip to the outer surface of the boss, and forming a leading edge of the blade in the rotational direction;
A rear edge portion extending from the outer surface of the boss portion toward the outside in the rotational radial direction of the propeller fan, and forming a rear edge of the wing portion in the rotational direction;
An outer periphery that connects the blade tip and the outer edge of the trailing edge, and forms an outer periphery of the blade in the rotational radius direction;
The outer surface of the boss portion is
An upstream surface having a shape extending toward the outer side in the rotational radial direction of the propeller fan toward the downstream side;
A downstream portion located on the downstream side of the downstream end of the upstream surface;
A downstream surface connecting the downstream end of the upstream surface and the downstream portion, and
The downstream surface has a shape extending along a direction parallel to the rotation axis, or a shape extending toward the inside of the rotation radial direction from the parallel direction toward the downstream portion,
In the direction parallel to the rotation axis, comparing the height of the upstream surface and the downstream surface, the height of the upstream surface is higher than the height of the downstream surface,
A front edge root portion that is a root of the front edge portion is connected to the boss portion at the upstream surface, and a rear edge root portion that is a root of the rear edge portion is connected to the boss portion at the downstream surface, The edge root portion is provided on the inner side in the rotational radius direction than the rear edge root portion,
In the direction parallel to the rotation axis, the height between the base of the position of the position and the front edge of the most the downstream side in the wings and ha, most the downstream side in the wings If the height between the position and the position of the wing tip of the hb, the value of hb / ha is Ru der 1.5 or higher,
Blower device. The upstream surface has a substantially conical shape that increases in diameter toward the downstream side.
The air blower according to claim 1. The air passage forming member is
An inner wall,
A recess provided to be recessed from the inner wall,
In the direction parallel to the rotation axis, most said downstream portion of the recess, than most the downstream portion of the boss portion located on the upstream side, and the blade tip of the wings Located on the downstream side of the part,
In the direction parallel to the rotation axis, the most upstream portion of the recess is located on the upstream side of the blade tip of the blade.
The air blower according to claim 1 or 2 . The air passage forming member is
A first inner wall,
A second inner wall portion located on the downstream side of the first inner wall portion and having a narrow air passage area than the first inner wall portion, and
In the direction parallel to the rotation axis, the most the upstream portion of the second inner wall portion, than the most the downstream portion of the boss portion located on the upstream side, and of the wings Located on the downstream side of the blade tip,
The air blower according to claim 1 or 2 . The air blower according to claim 1 is provided.
Hair dryer.

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