TW201804087A - Propeller fan and fluid feeding device - Google Patents

Abstract

In the present invention, the cross-sectional shape (S11) of a blade part is defined by a circular arc having an arbitrary radius and passing through a front-edge section and a back-edge section, a chord line (BC11) connecting the front-edge section and the back-edge section in the cross-sectional shape is defined, and a base line (BL11) parallel to the chord line is defined. A convex surface section (NC11), which has a surface shape that curves in a convex shape in a central axis direction, and a concave surface section (NV11), which is positioned between the convex surface section and the front-edge section and has a surface shape that curves in a concave shape in the central axis direction, are formed on the negative-pressure-surface side of the cross-sectional shape of the blade part. The convex surface section (NC11) has an apex (NC11c), which is a portion at which the distance from the base line to the convex surface section in the chord line direction changes from gradually increasing to gradually decreasing from the front-edge-section side toward the back-edge-section side. The apex is formed at a position at which the distance (NC11x) in the chord line direction from the front-edge section to the apex is no greater than 1/3 of the entire length (LL11) of the chord line.

Description

Propeller fan and fluid conveying device

This disclosure relates to propeller fans and fluid delivery devices. This application claims priority based on Japanese Patent Application No. 2016-147339 filed on July 27, 2016. The entire contents of this Japanese patent application are incorporated herein by reference.

Propeller fans are used in fluid delivery devices such as air conditioners. In the case where the propeller fan is used as a fluid conveying device of an air conditioner, the propeller fan is arranged in, for example, an outdoor unit. Japanese Patent No. 3803184 (Patent Document 1) discloses a propeller fan (also referred to as an axial flow fan) having a specific structure. According to the propeller fan, the boundary layer turbulence generated by the airfoil can be reduced. As a result, the propeller fan can be reduced. The eddy current after the vicinity of the trailing edge is reduced to reduce the noise of the air supply. Japanese Patent Application Laid-Open No. 2011-236860 (Patent Document 2) also discloses a propeller fan having a specific structure. According to this propeller fan, since the radial direction of inflow from the outer periphery of the wing can flow in from the outer peripheral side linear portion and the hub side The convex portion promotes the inflow and optimizes the flow state around the natural wing. Therefore, the effects of improving fan efficiency and reducing noise can be fully exerted, and power consumption during the air conditioner can be reduced. [Prior Art Document] [Patent Document] [Patent Document 1] Japanese Patent No. 3803184 [Patent Document 2] Japanese Patent Laid-Open No. 2011-236860

Recently, the awareness of global environmental protection has gradually increased, and high-level energy conservation is urgently expected. The propeller fan disclosed in Japanese Patent No. 3803184 (Patent Document 1) or Japanese Patent Laid-Open No. 2011-236860 (Patent Document 2) has room for improvement from the viewpoint of energy saving. For example, the propeller fan disclosed in Japanese Patent No. 3803184 (Patent Document 1), even if the boundary layer turbulence generated by the airfoil can be temporarily reduced, the boundary layer turbulence cannot be eliminated. For example, in the case of an air conditioner, a heat exchanger is arranged upstream of the propeller fan. In most cases, a propeller fan is sought to overcome the pressure loss of several resistance bodies, but for this requirement, the boundary layer turbulence generated by the airfoil is a fluid property and is not simply a disappearance. Even if the turbulence in the boundary layer can be temporarily disappeared, it is not permanent. The turbulence in the boundary layer will be immediately regenerated due to several opportunities. If the turbulence in the boundary layer disappears, occurs, disappears again, and reappears, there may be a possibility that the noise may become larger when the generation and disappearance of the turbulence in the boundary layer are repeated. That is, in the improvement aimed at reducing the boundary layer turbulence generated by the airfoil, it is difficult to obtain a result that can sufficiently meet the requirements for energy saving. The present inventors have focused on the following improvement issues: change the concept, for example, reduce the boundary layer turbulence generated by the airfoil to a certain degree, and effectively manage the boundary layer turbulence so that the boundary layer turbulence exists It is stable, thereby suppressing noise in the presence of boundary layer turbulence. Moreover, the propeller fan disclosed in Japanese Patent Laid-Open No. 2011-236860 (Patent Document 2) can temporarily reduce the deviation between the position of the wing-end vortex generated from the outer periphery of the wing and the shape of the concave wing surface, and it is not necessary Can make the wing-end vortex itself disappear. Even if the radial inflow from the outer periphery of the wing can be temporarily promoted, it is not sufficient. As described above, for example, in the case of an air conditioner, a heat exchanger is disposed upstream of the propeller fan. In most cases, a propeller fan is sought to overcome the pressure loss of several resistance bodies. Even if the above-mentioned offset can be temporarily disappeared, it is not permanent. Deviations can recur immediately due to several opportunities. As the above-mentioned offset disappears, occurs, disappears, and reappears, when the occurrence and disappearance of the offset are repeated, there is also a possibility that the flow state around the wing may deteriorate. That is, even if it is an improvement aimed at reducing the above-mentioned offset caused by the airfoil, it is difficult to obtain a result that can sufficiently meet the requirements for energy saving. The present inventors have focused on the following improvement issues: change the concept, for example, reduce the above-mentioned offset generated by the airfoil to a certain degree, and effectively manage and stabilize the offset in a state where the offset exists, thereby Make the flow around the wing good in the presence of offset. The present invention is an explorer in view of the above-mentioned facts, and an object thereof is to provide a propeller fan which can further improve the quietness, improve the air supply efficiency of the fan, and seeks to save energy, and a fluid conveying device provided with the propeller fan. [Technical means for solving the problem] A propeller fan according to a first aspect of the present invention includes a rotation shaft portion that rotates around an imaginary center axis and a wing portion that has a rotation radius direction from the rotation shaft portion side. A shape extending outward and forming a positive pressure surface and a negative pressure surface on the front and rear surfaces respectively by being rotated; and the wing portion includes: a wing front end portion located at the forefront of the rotation direction; a front edge portion forming the rotation direction The leading edge of the wing portion; the trailing edge portion that forms the trailing edge of the wing portion in the rotation direction; and the outer peripheral edge portion that connects the leading end portion of the wing with the outer side end of the trailing edge portion to form the wing portion in the turning radius direction The outer peripheral edge; and if the wing portion is cut by an arc of an arbitrary radius of the leading edge portion and the trailing edge portion with the position of the center axis as the center, the first cross-sectional shape of the wing portion is defined as The line segment connecting the position of the leading edge portion and the position of the trailing edge portion of the first cross-sectional shape of the wing portion is defined as a first chord line, and extends from the wing portion in the direction of the central axis. When the first cross-sectional shape is directed away from the positive pressure surface side, a first reference line is defined by drawing a straight line parallel to the first chord line, and then on the negative pressure surface side of the first cross-sectional shape of the wing portion Formed: a first convex surface portion having a surface shape curved in a convex shape in the direction of the central axis; and a first concave surface portion located between the first convex surface portion and the leading edge portion and having the center And the first convex surface portion has a first apex portion that extends from the leading edge portion side toward the trailing edge portion side in the first chord line direction. The distance from the first reference line to the first convex surface portion is gradually changed from gradually increasing to a gradually decreasing portion; and the distance between the first top portion formed in the direction of the first chord line from the front edge portion to the first top portion is The position of the first chord line is less than 1/3 of the total length. In the propeller fan, the first concave surface portion may include a first bottom portion, which is connected to the first chord line direction from the front edge portion side toward the rear edge portion side, and the first The distance from the reference line to the first concave surface portion is gradually reduced from increasing to an increasing portion; and the distance between the first bottom portion formed in the direction of the first chord line from the front edge portion to the first bottom portion is the first portion 1 chord line at a position of 5% or more and 15% or less of the total length. The propeller fan may be configured as follows: a second concave surface portion is formed on the positive pressure surface side of the first cross-sectional shape of the wing portion, and has a surface shape curved into a concave shape in the central axis direction; And a second convex surface portion, which is located between the second concave surface portion and the leading edge portion, and has a surface shape curved in a convex shape in the direction of the central axis; the second concave surface portion includes a second bottom portion, The distance from the first reference line to the second concave surface portion is gradually changed from an increasing portion to a decreasing portion in the direction of the first chord line from the front edge portion side to the rear edge portion side; and the second portion The bottom portion is formed at a position where the distance in the direction of the first chord line from the front edge portion to the second bottom portion is 1/3 or less of the total length of the first chord line. In the propeller fan, if the total length of the outer peripheral edge portion is specified as LA, a starting point is defined at an arbitrary position on the outer peripheral edge portion, and a distance from the front end portion of the wing to the outer peripheral edge portion of the starting point is defined. It is defined as LB, and the distance from the central portion of the trailing edge portion to the outer end of the trailing edge portion on the trailing edge portion is defined as DA, on the trailing edge portion and the central portion of the trailing edge portion and the The end point is defined at an arbitrary position between the outer ends of the trailing edge portion, and the distance from the central portion of the trailing edge portion to the trailing edge portion of the end point is defined as DB, then by satisfying LB / LA = DB The relationship between the starting point and the ending point of the / DA relationship cuts the wing straight and defines the second cross-sectional shape of the wing. If the position of the outer peripheral edge portion connecting the second cross-sectional shape of the wing and the rear The line segment of the edge position is defined as the second chord line, and is drawn parallel to the second chord line from the second cross-sectional shape of the wing part toward the position away from the positive pressure surface in the center axis direction. A second reference line is defined as a straight line, and a third convex surface portion having a surface shape curved into a convex shape in the central axis direction is formed on the negative pressure surface side of the second cross-sectional shape of the wing portion; and A third concave surface portion is located between the third convex surface portion and the outer peripheral edge portion, and has a surface shape bent into a concave shape in the direction of the central axis; and the third convex surface portion has a third top portion, which is The distance from the second reference line to the third convex surface portion is gradually changed from a gradually increasing portion to a gradually decreasing portion in the direction of the second chord line from the outer peripheral edge portion toward the rear edge portion; The top portion is formed at a position where the distance in the direction of the second chord line from the outer peripheral edge portion to the third top portion is 1/3 or less of the total length of the second chord line. In the propeller fan, the third concave surface portion may include a third bottom portion, which is connected to the second chord line direction from the outer peripheral edge portion toward the rear edge portion, and the second The distance from the reference line to the third concave surface portion is gradually decreased to gradually increase; and the distance between the third bottom portion formed in the direction of the second chord line from the outer peripheral edge portion to the third bottom portion is the first portion. 2-wing chords 5% to 15% of the total length. The propeller fan may be configured as follows: a fourth concave surface portion is formed on the positive pressure surface side of the second cross-sectional shape of the wing portion, and has a surface shape curved into a concave shape in the central axis direction; And a fourth convex surface portion, which is located between the fourth concave surface portion and the outer peripheral edge portion, and has a surface shape curved in a convex shape in the direction of the central axis; and the fourth concave surface portion has a fourth bottom portion, The distance from the second reference line to the fourth concave surface portion is gradually changed from an increasing portion to a decreasing portion in the direction of the second chord line from the outer peripheral edge portion toward the rear edge portion; and The bottom portion 4 is formed at a position where the distance in the direction of the second chord line from the outer peripheral edge portion to the fourth bottom portion is 1/3 or less of the total length of the second chord line. A propeller fan according to a second aspect of the present invention includes a rotation shaft portion that rotates around an imaginary center axis, and a wing portion that has a shape extending from the rotation shaft portion side toward the outside in the direction of the rotation radius, and A positive pressure surface and a negative pressure surface are respectively formed on the positive and negative surfaces by rotation; and the wing portion includes: a front end portion of the wing, which is located at the forefront of the rotation direction; a leading edge portion, which forms the leading edge of the wing portion in the rotation direction; An edge portion that forms the trailing edge of the wing portion in the rotation direction; and an outer peripheral edge portion that connects the leading end portion of the wing with the outer end of the trailing edge portion to form the outer peripheral edge of the wing portion in the radius of rotation direction; and The total length of the outer peripheral edge portion is defined as LA, the starting point is defined at any position on the outer peripheral edge portion, the distance from the front end portion of the wing to the outer peripheral edge portion of the starting point is specified as LB, and the central portion of the rear edge portion to The distance on the trailing edge portion of the trailing edge portion on the trailing edge portion is defined as DA, and is on the trailing edge portion and the central portion of the trailing edge portion and the trailing edge portion of the trailing edge portion. The end point is defined at an arbitrary position between the ends, and the distance from the central portion of the trailing edge portion to the trailing edge portion of the end point is defined as DB. By passing the starting point and the relationship satisfying the relationship of LB / LA = DB / DA, The straight line at the end point cuts the wing portion to define the cross-sectional shape of the wing portion. If a line segment connecting the position of the outer peripheral edge portion and the position of the trailing edge portion of the cross-sectional shape of the wing portion is specified as a chord line, And in the direction of the central axis, draw a straight line parallel to the chord line from the cross-sectional shape of the wing part to a position away from the positive pressure surface side to define a reference line. The negative pressure surface side is formed with a convex surface portion having a surface shape curved in a convex shape in the central axis direction, and a concave surface portion located between the convex surface portion and the outer peripheral edge portion in the central axis direction. And the convex surface portion has: a top portion, which is in the chord line direction as it goes from the outer peripheral edge portion side to the rear edge portion side, the reference The distance from the convex surface portion gradually increases to a gradually decreasing portion; and the top portion is formed in a direction in which the chord line direction from the outer peripheral edge portion to the top portion is less than 1/3 of the full length of the chord line position. A propeller fan according to a third aspect of the present invention includes: a rotating shaft portion that rotates around an imaginary central axis; and a wing portion that has a shape extending from the side of the rotating shaft portion to the outside in the direction of the rotation radius, and A positive pressure surface and a negative pressure surface are respectively formed on the positive and negative surfaces by rotation; and the wing portion includes: a front end portion of the wing, which is located at the forefront of the rotation direction; a leading edge portion, which forms the leading edge of the wing portion in the rotation direction; An edge portion that forms the trailing edge of the wing portion in the rotation direction; and an outer peripheral edge portion that connects the leading end portion of the wing with the outer side end of the trailing edge portion to form the outer peripheral edge of the wing portion in the radius of rotation direction; and The wing portion is cut by an arbitrary position on the outer peripheral edge portion and a plane of the central axis to define a cross-sectional shape of the wing portion, and a portion between the wing portion and the rotary shaft portion in the cross-sectional shape of the wing portion is defined. It is defined as a connection portion, and a line segment connecting the position of the outer peripheral edge portion of the cross-sectional shape of the wing portion and the position of the connection portion is defined as a chord line, and in the above Draw a straight line parallel to the chord line in the axial direction from the cross-sectional shape of the wing portion to a position away from the positive pressure surface side, and define a reference line on the negative pressure surface side of the cross-sectional shape of the wing portion. Formed: a convex surface portion having a surface shape curved in a convex shape in the central axis direction; and a concave surface portion located between the convex surface portion and the outer peripheral edge portion and having a concave shape in the central axis direction. And the convex portion has: a top portion, which is in the chord line direction as the distance from the reference line to the convex portion changes from the outer peripheral edge side to the rear edge portion side, gradually increasing to The decreasing portion; and the top portion is formed at a position where the distance in the chord line direction from the outer peripheral edge portion to the top portion is less than 1/3 of the full length of the chord line. A fluid transfer device according to an aspect of the present invention includes the above-mentioned propeller fan. [Effects of the Invention] According to the above-mentioned propeller fan, it is possible to further improve the quietness, improve the air supply efficiency of the fan, and achieve energy saving.

For implementation, The following description is made with reference to the drawings. There may be cases where the same parts and equivalent parts are labeled with the same reference number without repeated description. [Embodiment 1] (Fluid transport device 100) Fig. 1 is a perspective view showing a fluid transport device 100 according to a first embodiment. The fluid transfer device 100 is an outdoor unit such as an air conditioner, With frame 110, Vent 120 (blowing outlet), And propeller fan 101. The vent 120 is provided so as to penetrate the front panel of the frame 110 in the thickness direction. The propeller fan 101 is disposed inside the housing 110, By driving with a motor not shown, The airflow flowing through the vent 120 is formed. Within the frame body 110, A heat exchanger (not shown) is provided. Air is supplied by the propeller fan 101, The airflow is exhausted through the vent 120. With this, The heat exchanger can effectively perform heat exchange. (Propeller Fan 101) FIG. 2 is a plan view showing a propeller fan 101 according to the first embodiment. The propeller fan 101 includes a rotation shaft portion 10 and a plurality of wing portions 20. The rotating shaft portion 10 is a portion for connecting the propeller fan 101 to an output shaft of a drive motor (not shown). The rotation shaft portion 10 receives a driving force from a driving motor, On the other hand, it rotates around the imaginary center axis AX. The wing portion 20 has a shape extending from the rotation shaft portion 10 side toward the outside in the rotation radius direction. In this embodiment, The three wing portions 20 are arranged at equal intervals so as to be spaced apart from each other in the direction of rotation, Each of the three wing portions 20 has the same shape. As the rotation shaft portion 10 rotates about the central axis AX, The three wing portions 20 also rotate around the central axis AX integrally with the rotation shaft portion 10. as shown in picture 2, The wing portion 20 includes the medial end 21, Front edge 22, Wing tip 23, Outer periphery 24, Outer end 25, Trailing edge 26, And medial end 27, And on the inside of these, A wing plate having a thickness is formed. In other words, Around a thick wing, Sequentially form the inner end 21, Front edge 22, Wing tip 23, Outer periphery 24, Outer end 25, Trailing edge 26, And medial end 27. The wing plate of the wing portion 20 is a portion mainly responsible for the original function of the wing portion 20 that sends fluid (generates airflow) in the direction of the central axis AX. As the wings 20 rotate, One of the main surfaces of the wing plates of the wing portion 20 forms a positive pressure surface 20P, The other main surface of the wing plate of the wing portion 20 forms a negative pressure surface 20N. The positive pressure surface 20P is formed on the ejection side of the wing portion 20 in the direction of the central axis AX, The negative pressure surface 20S is formed on the suction side of the wing portion 20 in the direction of the central axis AX. The wing portion 20 generates an air current flowing from the negative pressure surface 20S side (suction side) toward the positive pressure surface 20P side (ejection side). When the wing portion 20 is viewed in plan as shown in FIG. 2, The outer shape of the wing portion 20 passes the leading edge portion 22, Wing tip 23, Outer periphery 24, Outer end 25, The smooth curve of the trailing edge portion 26 reaching the inner end 27 is formed. The inner end 21 of the wing portion 20 is formed between the front edge portion 22 and the rear edge portion 26 connected to each other. The inboard end 21 is provided, for example, at a position closest to the outer surface of the rotation shaft portion 10 between the front edge portion 22 and the rear edge portion 26 in the above-mentioned curve defining the outer shape of the wing portion 20. The inboard end 21 of the wing portion 20 coincides with the inboard end 27 of the other wing portion 20 adjacent to the wing portion 20. The leading edge portion 22 of the wing portion 20 is a portion of the wing portion 20 forming the leading edge in the rotation direction, When the situation of the propeller fan 101 is viewed from the center axis AX direction, The leading edge portion 22 starts from the inner end 21, It extends in a substantially arc shape from the inner side toward the outer side in the radial direction of rotation. The leading edge portion 22 moves from the inside to the outside in the radial direction of rotation, One side is curved into a concave shape, and the other side smoothly extends toward the front side of the rotation direction of the propeller fan 101. The trailing edge portion 26 of the wing portion 20 is a portion of the trailing edge of the wing portion 20 forming the rotation direction, When the situation of the propeller fan 101 is viewed from the center axis AX direction, The trailing edge portion 26 starts from the inner end 27, It extends in a substantially arc shape from the inner side toward the outer side in the radial direction of rotation. The trailing edge portion 26 is directed outward from the inside of the radius of rotation, One side is curved to be convex, and the other side smoothly extends toward the front side of the propeller fan 101 in the rotation direction. The wing tip portion 23 is the most forward position of the wing portion 20 in the rotation direction, And It is attached to the outermost portion of the leading edge portion 22 in the rotation radius direction. The outer peripheral edge portion 24 extends in a substantially arc shape in the circumferential direction. The outer peripheral edge portion 24 connects the front end portion 23 of the wing with the outer end 25 of the trailing edge portion 26, The outer periphery of the wing portion 20 in the radial direction of rotation is formed. When the situation of the propeller fan 101 of this embodiment is viewed from the center axis AX direction, The wing portion 20 has a wing tip portion 23 as a front end, Sharpened into a sickle-like shape. The propeller fan 101 including the above-mentioned rotating shaft portion 10 and wing portion 20 is configured to have a diameter of, for example, 466 mm. Here, Prescribed arc CR11, CR12, CR13 is an arc having an arbitrary radius around the position of the central axis AX and passing through the leading edge portion 22 and the trailing edge portion 26. Arc CR11, CR12, In CR13, the center of the arc is the position of the central axis AX. The arc CR11 has a radius of 100 mm (diameter of 200 mm), The arc CR12 has a radius of 150 mm (diameter of 300 mm), The arc CR13 has a radius of 200 mm (diameter of 400 mm). By using the arc CR11, CR12, The cross-sectional shape of the wing part 20 obtained by CR13 imaginarily cutting the wing part 20 is defined as the cross-sectional shape S11, S12, S13. Regarding the cross-sectional shape S11, Refer to Figure 3, Figure 4 illustrates, Regarding the cross-sectional shape S12, Refer to Figure 5, Figure 6 illustrates, Regarding the cross-sectional shape S13, Refer to Figure 7, This is illustrated in FIG. 8. (Sectional shape S11) FIG. 3 is a cross-sectional view of the arrow along the line III-III in FIG. 2, A cross-sectional shape S11 (first cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 with the arc CR11 shown in FIG. 2 is shown. FIG. 4 is a cross-sectional view showing an area surrounded by an IV line in FIG. 3 in an enlarged manner. As shown in Figures 3 and 4, A line segment connecting the position of the front edge portion 22 and the position of the rear edge portion 26 of the cross-sectional shape S11 (first cross-sectional shape) of the wing portion 20 is defined as a chord line BC11 (first chord line). A position away from the cross-sectional shape S11 of the wing portion 20 toward the positive pressure surface 20P side in the direction of the central axis AX, A straight line parallel to the chord line BC11 is drawn and a reference line BL11 (a first reference line) is defined. (About the surface shape of the negative pressure surface 20N) In the propeller fan 101 of this embodiment, Formed on the negative pressure surface 20N side of the cross-sectional shape S11 of the wing portion 20: Convex surface NC11 (the first convex surface), It has a surface shape curved into a convex shape in the direction of the central axis AX; And concave surface NV11 (the first concave surface), It is located between the convex portion NC11 and the leading edge portion 22 and has a surface shape that is curved in a concave shape in the direction of the central axis AX. (About the position of the top part NC11c of the convex part NC11 formed on the negative pressure surface 20N) The convex part NC11 (1st convex part) has the top part NC11c (1st top part) (refer FIG. 4). The top NC11c is separated from the above-mentioned reference line BL11 by a distance NC11y (the distance referred to here refers to the distance in the projection plane formed by projecting the cross-sectional shape S11 on a plane parallel to the central axis AX, That is, the distance in the direction orthogonal to the reference line BL11, Same below.) The top NC11c is part of the convex surface NC11, And tied in the direction of the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the reference line BL11 to the convex portion NC11 is gradually changed from a gradually increasing portion to a decreasing portion. The top NC11c having such characteristics is formed at a position where the distance NC11x in the direction of the chord line BC11 of the leading edge portion 22 to the top NC11c is 1/3 or less (about 33%) of the total length LL11 of the chord line BC11. As a better constitution, The top NC11c is formed at a position where the distance NC11x in the direction of the chord line BC11 from the leading edge portion 22 to the top NC11c is 20% or more and 30% or less of the full length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure. (About the position of the bottom NV11c of the concave portion NV11 formed on the negative pressure surface 20N) The concave portion NV11 (first concave portion) has a bottom NV11c (first bottom) (see FIG. 4). The bottom NV11c is separated from the reference line BL11 by a distance NV11y. The bottom NV11c is part of the concave surface NV11, And tied in the direction of the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the above-mentioned reference line BL11 to the concave surface NV11 changes from decreasing to increasing. As a better constitution, The bottom NV11c is formed at a position where the distance NV11x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom NV11c is 5% to 15% of the total length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure, The bottom NV11c is formed at a position where the distance NV11x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom NV11c is 10% of the full length LL11 of the chord line BC11. (About the concave surface NV12 formed on the negative pressure surface 20N, Convex surface NC12) Referring to FIG. 3 and FIG. 4, In the propeller fan 101 of this embodiment, As a better form, On the negative pressure surface 20N, In addition to the above-mentioned concave surface NV11 and convex surface NC11, Further, a concave surface portion NV12 and a convex surface portion NC12 are formed. in particular, Formed on the negative pressure surface 20N side of the cross-sectional shape S11 of the wing portion 20 is: Convex face NC12, It has a surface shape curved into a convex shape in the direction of the central axis AX; And concave surface NV12, It is located between the convex surface NC12 and the convex surface NC11 (the first convex surface), And it has a surface shape curved into a concave shape in the direction of the central axis AX. (Regarding the position of the bottom NV12c of the concave portion NV12 formed on the negative pressure surface 20N) The concave portion NV12 has a bottom NV12c (third bottom) (see FIG. 4). The bottom NV12c is separated from the reference line BL11 by a distance NV12y. The bottom NV12c is part of the concave surface NV12, And tied in the direction of the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the above-mentioned reference line BL11 to the concave surface NV12 changes from decreasing to increasing. As a better constitution, The bottom NV12c is formed at a position where the distance NV12x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom NV12c is 40% or more and 50% or less of the total length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure. (About the position of the top part NC12c of the convex surface part NC12 formed on the negative pressure surface 20N) The convex surface part NC12 has the top part NC12c (3rd top part) (refer FIG. 4). The top NC12c is separated from the reference line BL11 by a distance NC12y. The top NC12c is part of the convex surface NC12, Tied to the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the above-mentioned reference line BL11 to the convex portion NC12 is gradually changed from a gradually increasing portion to a decreasing portion. As a better constitution, The top NC12c is formed at a position where the distance NC12x in the direction of the chord line BC11 from the leading edge portion 22 to the top NC12c is 60% or more and 70% or less of the total length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure. (About the surface shape of the positive pressure surface 20P) In the propeller fan 101 of this embodiment, Formed on the positive pressure surface 20P side of the cross-sectional shape S11 of the wing portion 20: Concave surface PV11 (second concave surface), It has a surface shape curved into a concave shape in the direction of the central axis AX; And convex surface PC11 (second convex surface), It is located between the concave surface portion PV11 and the front edge portion 22 and has a surface shape curved in a convex shape in the direction of the central axis AX. (Regarding the position of the bottom PV11c of the concave surface PV11 formed on the positive pressure surface 20P) The concave surface PV11 (second concave surface) has a bottom PV11c (second bottom) (see FIG. 4). The bottom PV11c is separated from the reference line BL11 by a distance PV11y. The bottom PV11c is part of the concave surface PV11, Tied to the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the above-mentioned reference line BL11 to the concave portion PV11 is gradually changed from a gradually increasing portion to a gradually decreasing portion. As a better constitution, The bottom PV11c is formed at a position where the distance PV11x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom PV11c is 1/3 or less (about 33%) of the full length LL11 of the chord line BC11. As a further preferable structure, The bottom PV11c is formed at a position where the distance PV11x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom PV11c is 20% or more and 30% or less of the total length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure. (Regarding the position of the top PC11c of the convex surface PC11 formed on the positive pressure surface 20P) The convex surface PC11 (second convex surface) has a top PC11c (second top) (see FIG. 4). The top PC11c is separated from the reference line BL11 by a distance PC11y. The top PC11c is a part of the convex surface PC11, Tied to the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the above-mentioned reference line BL11 to the convex surface PC11 changes from decreasing to increasing. As a better constitution, The top PC11c is formed at a position where the distance PC11x in the direction of the chord line BC11 of the leading edge portion 22 to the top PC11c is 5% or more and 15% or less of the total length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure, The top PC11c is formed at a position where the distance PC11x in the direction of the chord line BC11 of the leading edge portion 22 to the top PC11c is 10% of the full length LL11 of the chord line BC11. (About the convex surface PC12 formed on the positive pressure surface 20P, Concave surface PV12) Referring to FIGS. 3 and 4, In the propeller fan 101 of this embodiment, As a better form, On the positive pressure surface 20P, In addition to the above-mentioned convex surface PC11 and concave surface PV11, Further, a convex surface PC12 and a concave surface PV12 are formed. in particular, Formed on the positive pressure surface 20P side of the cross-sectional shape S11 of the wing portion 20: Concave face PV12, It has a surface shape curved into a concave shape in the direction of the central axis AX; And convex face PC12, It is located between the concave surface portion PV12 and the concave surface portion PV11 (the second concave surface portion) and has a surface shape curved in a convex shape in the direction of the central axis AX. (Regarding the position of the top PC12c of the convex surface PC12 formed on the positive pressure surface 20P) The convex surface PC12 has the top PC12c (4th top) (refer FIG. 4). The top PC12c is separated from the reference line BL11 by a distance PC12y. The top PC12c is part of the convex surface PC12, Tied to the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the above-mentioned reference line BL11 to the convex surface PC12 changes from decreasing to increasing. As a better constitution, The top PC12c is formed at a position where the distance PC12x in the direction of the chord line BC11 of the leading edge portion 22 to the top PC12c is 40% or more and 50% or less of the total length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure. (Regarding the position of the bottom PV12c of the concave surface PV12 formed on the positive pressure surface 20P) The concave surface PV12 has a bottom PV12c (fourth bottom) (see FIG. 4). The bottom PV12c is separated from the reference line BL11 by a distance PV12y. The bottom PV12c is part of the concave surface PV12, Tied to the chord line BC11, As it goes from the leading edge portion 22 side to the trailing edge portion 26 side, The distance from the above-mentioned reference line BL11 to the concave surface portion PV12 is gradually changed from a gradually increasing portion to a gradually decreasing portion. As a better constitution, The bottom PV12c is formed at a position where the distance PV12x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom PV12c is 60% or more and 70% or less of the total length LL11 of the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure. (Sectional shape S12) FIG. 5 is a sectional view of the arrow along the VV line in FIG. 2, A cross-sectional shape S12 (other first cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 using the arc CR12 shown in FIG. 2 is shown. FIG. 6 is a cross-sectional view showing an area surrounded by a line VI in FIG. 5 in an enlarged manner. As shown in Figures 5 and 6, The cross-sectional shape S12 (other first cross-sectional shape) of the wing portion 20 is the same as the cross-sectional shape S11 described above, On the negative pressure surface 20N, NV11 (first concave surface) is formed, Convex surface NC11 (first convex surface), Concave face NV12, And convex face NC12, On the positive pressure surface 20P, A convex surface PC11 (second convex surface) is formed, Concave surface PV11 (second concave surface), Convex PC12, And concave surface PV12. With regard to each of these components related to the cross-sectional shape S12, Since the cross-sectional shape S12 is substantially the same as the cross-sectional shape S11, Therefore, the repeated explanation is not repeated. As a better constitution, In the cross-sectional shape S12 (the other first cross-sectional shape), The surface shape NR (FIG. 6) of the positive pressure surface 20P between the leading edge portion 22 and the top PC11c (second top) of the convex portion PC11 (second convex portion) is formed along the chord line BC11. The propeller fan 101 of this embodiment is provided with this structure. This structure can also be applied to the above-mentioned cross-sectional shape S11 (first cross-sectional shape), And / or the following cross-sectional shape S13 (and further other first cross-sectional shapes). (Sectional shape S13) FIG. 7 is a cross-sectional view of an arrow along the line VII-VII in FIG. 2, The cross-sectional shape S13 (and other first cross-sectional shapes) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by the arc CR13 shown in FIG. FIG. 8 is an enlarged sectional view showing an area surrounded by a line VIII in FIG. 7. As shown in Figures 7 and 8, The cross-sectional shape S13 (and other first cross-sectional shapes) of the wing portion 20 is the same as the cross-sectional shape S11 described above, On the negative pressure surface 20N, At least a concave portion NV11 (first concave portion) and a convex portion NC11 (first convex portion) are formed, On the positive pressure surface 20P, At least a convex surface PC11 (second convex surface) and a concave surface PV11 (second concave surface) are formed. In addition, A concave surface NV12 and a convex surface NC12 may be further formed on the negative pressure surface 20N. In addition, A convex portion PC12 and a concave portion PV12 may be further formed on the positive pressure surface 20P. With regard to each of these components related to the cross-sectional shape S13, Since the cross-sectional shape S13 is substantially the same as the cross-sectional shape S11, Therefore, the repeated explanation is not repeated. (Action and Effect) FIG. 9 is a plan view for explaining the action and effect of the propeller fan 101 according to the first embodiment. As shown in Figure 9, The propeller fan 101 rotates in the direction of the arrow AR and generates airflow. The airflow flows into the airfoil surface by passing near the front edge portion 22 of the airfoil portion 20. Here, The air passing through the vicinity of the front edge portion 22 of the wing portion 20 passes through the airfoil surface in a generally circumferential direction from the front edge portion 22 (in a substantially arc shape), And flows out from the trailing edge portion 26. (Concave surface NV11) FIG. 10 is a diagram for explaining the function and effect of the cross-sectional shape S11 of the propeller fan 101 (wing portion 20) according to the first embodiment. As shown in Figure 10, 20N on the negative pressure surface of the propeller fan 101, A concave portion NV11 (first concave portion) is formed at a specific position. According to this constitution, The boundary layer turbulence generated immediately downstream of the edge portion 22 immediately before the negative pressure surface 20N is particularly generated in the concave portion of the concave portion NV11 (near the bottom NV11c). This is evident in the following situations: The bottom NV11c is formed at a position where the distance NV11x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom NV11c is 5% or more and 15% or less of the total length LL11 of the chord line BC11. This is particularly noticeable in the following situations: The bottom NV11c is formed at a position where the distance NV11x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom NV11c is 10% of the full length LL11 of the chord line BC11. on the other hand, The main flow passing on the wing surface of the wing portion 20 does not flow into the concave portion of the concave portion NV11, That is, it circulates through the upper surface of the boundary layer turbulence. therefore, The boundary layer turbulence in the concave portion of the concave portion NV11 is fixed in the concave portion, Thereby, propagation (enlargement) from the concave portion to the outside is suppressed. With this, The boundary layer turbulence can be kept small and effectively stabilized. Since almost no boundary layer turbulence disappears, produce, Disappear again, The occurrence and disappearance of turbulence in the boundary layer are repeated, Therefore, noise can be further suppressed in the state where the boundary layer turbulence exists. (Comparative Example) FIG. 11 is a diagram showing a cross-sectional shape SZ of a propeller fan (wing portion) of a comparative example. In the cross-sectional shape SZ of the wing, On the negative pressure surface 20N, A concave surface ZV and a convex surface ZC are formed. however, The bottom ZVc of the concave surface ZV or the top ZCc of the convex surface ZC is compared with the configuration of the propeller fan in the first embodiment. Either is formed near the trailing edge portion 26. therefore, The boundary layer turbulence in the concave portion of the concave portion ZV is difficult to be fixed in the concave portion, The propagation (enlargement) from the concave portion to the outside cannot be sufficiently suppressed. therefore, Compared with the propeller fan 101 of the first embodiment, the propeller fan shown in FIG. It is difficult to achieve noise suppression or energy saving. (Concave surface PV11) Referring again to FIG. 10, As mentioned above, On the positive pressure surface 20P of the propeller fan 101, A convex portion PC11 (second convex portion) and a concave portion PV11 (second concave portion) are formed at specific positions. According to this constitution, Vortex can be efficiently generated on the concave portion PV11 (concave portion) located downstream of the convex portion PC11, The eddy current is stably secured in the concave surface portion PV11. In the case of the wings shown in Figure 11, It has a wing shape having the largest thickness at the portion closer to the leading edge portion 22 (the position corresponding to the concave portion PV11 of the first embodiment). According to wings with this shape, A large lift force can be sufficiently generated at a position closer to the leading edge portion 22, But as a consequence of this, The frictional resistance caused by the friction between the wind and the airfoil increases. In contrast, According to the propeller fan 101 of this embodiment, A concave surface PV11 is formed at this part, And use the convex part PC11 to make it generate vortex stably, This can prevent wind and airfoil from directly rubbing against each other, In addition, the wall thickness of the portion having the largest thickness in the case of the wing portion shown in FIG. 11 can be greatly reduced. also, In the propeller fan 101 of this embodiment, The wing shape is formed by the vortex that stays inside the concave surface NV12 or the concave surface PV11, etc. (when the vortex is attached to the thin-walled wing, it has a wing shape as a whole), So despite being thin and lightweight, But the lift is roughly equal to the thick-walled wing, Since the frictional resistance is reduced as described above, Therefore, the design can also be used to make the lift-to-drag ratio exceed that of thick-walled wings. As mentioned above, The bottom portion NV12c of the concave portion NV12 is preferably formed at a position where the distance NV12x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom NV12c is 40% to 50% of the total length LL11 of the chord line BC11. The top NC12c of the convex portion NC12 is preferably formed at a position where the distance NC12x from the leading edge portion 22 to the wing chord line BC11 of the top NC12c is 60% or more and 70% or less of the total length LL11 of the wing chord BC11. Furthermore, The top PC12c of the convex portion PC12 is preferably formed at a position where the distance PC12x in the direction of the chord line BC11 of the leading edge portion 22 to the top PC12c is 40% or more and 50% or less of the total length LL11 of the chord line BC11. The bottom PV12c of the concave portion PV12 is preferably formed at a position where the distance PV12x in the direction of the chord line BC11 of the leading edge portion 22 to the bottom PV12c is 60% or more and 70% or less of the total length LL11 of the chord line BC11. The following designs are preferred for these systems: By placing them as evenly as possible, While reducing friction resistance with a lighter weight, One side contains the generated vortex to form a better wing shape. Referring to FIG. 12, As mentioned above, The surface shape NR (FIG. 6) of the positive pressure surface 20P between the leading edge portion 22 and the top portion PC11c (second top portion) of the convex portion PC11 (second convex portion) is preferably formed along the chord line BC11. The flow flowing from the leading edge portion 22 side flows along the surface shape NR (arrow DR), Can define the direction of flow, result, A vortex can be stably generated at a position downstream of the surface shape NR. (About strength assurance and weight reduction) According to the propeller fan 101 of this embodiment, The following secondary effects can also be expected. which is, Even if the thickness of the wings of the propeller fan 101 is reduced, You can also use the lift that rivals thick-walled wings, And Although thin-walled, it has higher strength, result, Significant weight reduction of fans can be achieved. in particular, In a normal propeller fan, If the entire wing portion is formed into a thick wall shape to increase the lift, According to the shape of the thick-walled wing, a large lift can be reliably obtained and the strength can be improved. But as a disadvantage, Increased weight of wings or fans, The required driving torque becomes larger, Or the cost of materials increases. When a large centrifugal force is applied due to high-speed rotation, etc., There is also a possibility that a large stress acts on the root of the leading edge of the wing and the blade expands or breaks outward. According to the propeller fan 101 of this embodiment, Has such as airfoil twice, Or two or more curved shapes, This takes the shape of undulating airfoils. therefore, Can increase the strength per unit thickness, It also reduces the possibility of damage during high-speed rotation. therefore, According to the propeller fan 101 of this embodiment, Almost no increase in material costs, Instead, we can reduce material costs by reducing weight. In addition to strength or lift, It is also possible to improve the air supply performance or air supply efficiency. According to the fluid conveying device 100 provided with the propeller fan 101 having such characteristics, Can help save energy, And people with high product value who can improve the quietness can be expected. [Embodiment 2] FIG. 13 is a plan view showing a propeller fan 102 according to Embodiment 2. The propeller fan 101 according to the first embodiment is different from the propeller fan 102 according to the second embodiment in the following points. Prescribed straight line CR21, CR22, CR23. The total length of the outer peripheral edge portion 24 is defined as LA, The starting point P1 is specified at an arbitrary position on the outer peripheral edge portion 24, The distance from the wing tip portion 23 to the peripheral edge portion 24 outside the starting point P1 is defined as LB. Furthermore, The distance from the central portion 26C of the trailing edge portion 26 to the trailing edge portion 26 behind the outer edge 25 of the trailing edge portion 26 is defined as DA, An end point P2 is defined on the trailing edge portion 26 and at any position between the central portion 26C of the trailing edge portion 26 and the outer end 25 of the trailing edge portion 26, The distance from the central portion 26C of the trailing edge portion 26 to the trailing edge portion 26 behind the end point P2 is defined as DB. Straight CR21, CR22, CR23 is a straight line passing through the starting point (P1) and the ending point (P2) that satisfy the relationship of LB / LA = DB / DA. These straight lines CR21, CR22, CR23 is substantially along the flow line of the air flowing in from the outer peripheral edge portion 24 and flowing toward the trailing edge portion 26. By using the straight line CR21, CR22, The cross-sectional shape of the wing portion 20 obtained by CR23 imaginarily cutting the wing portion 20 is defined as the cross-sectional shape S21, S22, S23. Regarding the cross-sectional shape S21, Refer to Figure 14, Figure 15 illustrates, Regarding the cross-sectional shape S22, Refer to Figure 16, Figure 17 illustrates, Regarding the cross-sectional shape S23, Refer to Figure 18, FIG. 19 is described. (Sectional shape S21) FIG. 14 is a sectional view of the arrow along the line XIV-XIV in FIG. 13, A cross-sectional shape S21 (second cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 using the straight line CR21 shown in FIG. 13 is shown. FIG. 15 is an enlarged cross-sectional view showing an area surrounded by the XV line in FIG. 14. As shown in Figures 14 and 15, A line segment connecting the position of the peripheral edge portion 24 and the position of the trailing edge portion 26 outside the sectional shape S21 (second sectional shape) of the wing portion 20 is defined as a chord line BC21 (second chord line). A position away from the cross-sectional shape S21 of the wing portion 20 toward the positive pressure surface 20P side in the direction of the central axis AX, A straight line parallel to the chord line BC21 is drawn and a reference line BL21 (a second reference line) is defined. (About the surface shape of the negative pressure surface 20N) In the propeller fan 102 of this embodiment, Formed on the negative pressure surface 20N side of the cross-sectional shape S21 of the wing portion 20: Convex surface NC21 (third convex surface), It has a surface shape curved into a convex shape in the direction of the central axis AX; And concave surface NV21 (third concave surface), It is located between the convex portion NC21 and the outer peripheral edge portion 24 and has a surface shape that is curved in a concave shape in the direction of the central axis AX. (About the position of the top part NC21c of the convex part NC21 formed on the negative pressure surface 20N) The convex part NC21 (3rd convex part) has the top part NC21c (3rd top part) (refer FIG. 15). The top NC21c is separated from the above-mentioned reference line BL21 by a distance NC21y (the distance referred to here refers to the distance in the projection plane formed by projecting the cross-sectional shape S21 on a plane parallel to the central axis AX, That is, the distance in a direction orthogonal to the reference line BL21. Same below.) The top NC21c is a part of the convex surface NC21, Tied to the chord line BC21, As it goes from the outer peripheral edge portion 24 side to the rear edge portion 26 side, The distance from the above-mentioned reference line BL21 to the convex portion NC21 is gradually changed from a gradually increasing portion to a decreasing portion. The top NC21c having such a feature is formed at a position where the distance NC21x from the outer peripheral edge portion 24 to the top chord line BC21 of the top NC21c is 1/3 or less (about 33%) of the total length LL21 of the chord line BC21. As a better constitution, The top NC21c is formed at a position where the distance NC21x of the chord line BC21 in the direction of the chord line BC21 from the outer peripheral edge portion 24 to the top NC21c is 20% or more and 30% or less of the total length LL21 of the chord line BC21. The propeller fan 102 of this embodiment is provided with this structure. (Regarding the position of the bottom NV21c of the concave portion NV21 formed on the negative pressure surface 20N) The concave portion NV21 (third concave portion) has a bottom NV21c (third bottom) (see FIG. 15). The bottom NV21c is separated from the reference line BL21 by a distance NV21y. The bottom NV21c is part of the concave surface NV21, Tied to the chord line BC21, As it goes from the outer peripheral edge portion 24 side to the rear edge portion 26 side, The distance from the above-mentioned reference line BL21 to the concave portion NV21 is changed from gradually decreasing to gradually increasing. As a better constitution, The bottom NV21c is formed at a position where the distance NV21x in the chord line BC21 direction of the chord line BC21 from the outer peripheral edge portion 24 to the bottom NV21c is 5% or more and 15% or less. The propeller fan 102 of this embodiment is provided with this structure, The bottom NV21c is formed at a position where the distance between the outer peripheral edge portion 24 and the chord line BC21 of the bottom NV21c in the direction of the chord line BC21 is 10% of the total length of the chord line BC21. As a better form, On the negative pressure surface 20N, It is the same as the case of the propeller fan 101 in Embodiment 1. In addition to the above-mentioned concave surface NV21 and convex surface NC21, Other concave portions (corresponding to FIG. 3, The concave surface of the concave surface NV12 shown in Fig. 4) and other convex surfaces (corresponding to Fig. 3, The convex surface of the convex surface NC12 shown in FIG. 4). Regarding such configuration, The same configuration as that described in the first embodiment can be applied to these. (About the surface shape of the positive pressure surface 20P) In the propeller fan 102 of this embodiment, Formed on the positive pressure surface 20P side of the sectional shape S21 of the wing portion 20: Concavity PV21 (4th concavity), It has a surface shape curved into a concave shape in the direction of the central axis AX; And convex surface PC21 (the fourth convex surface), It is located between the concave surface portion PV21 and the outer peripheral edge portion 24 and has a surface shape curved in a convex shape in the direction of the central axis AX. (Regarding the position of the bottom PV21c of the concave surface PV21 formed on the positive pressure surface 20P) The concave surface PV21 (the fourth concave surface) has a bottom PV21c (the fourth bottom) (see FIG. 15). The bottom PV21c is separated from the reference line BL21 by a distance PV21y. This bottom PV21c is part of the concave surface PV21, Tied to the chord line BC21, As it goes from the outer peripheral edge portion 24 side to the rear edge portion 26 side, The distance from the above-mentioned reference line BL21 to the concave portion PV21 is gradually changed from a gradually increasing portion to a gradually decreasing portion. As a better constitution, The bottom PV21c is formed at a position where the distance PV21x in the chord line BC21 direction of the chord line BC21 from the outer peripheral edge portion 24 to the bottom PV21c is 1/3 or less (about 33% or less) of the total length of the chord line BC21. As a further preferable structure, The bottom PV21c is formed at a position where the distance PV21x in the chord line BC21 direction from the outer peripheral edge portion 24 to the bottom PV21c is 20% or more and 30% or less of the full length LL21 of the chord line BC21. The propeller fan 102 of this embodiment is provided with this structure. (About the position of the top PC21c of the convex surface PC21 formed on the positive pressure surface 20P) The convex surface PC21 (4th convex surface) has the top PC21c (4th top) (refer FIG. 15). The top PC21c is separated from the reference line BL21 by a distance PC21y. The top PC21c is a part of the convex surface PC21, Tied to the chord line BC21, As it goes from the outer peripheral edge portion 24 side to the rear edge portion 26 side, The distance from the above-mentioned reference line BL21 to the convex surface PC21 changes from decreasing to increasing. As a better constitution, The top PC21c is formed at a position where the distance PC21x in the chord line BC21 direction from the outer peripheral edge portion 24 to the top PC21c is 5% or more and 15% or less of the total length LL21 of the chord line BC21. The propeller fan 102 of this embodiment is provided with this structure, The top PC21c is formed at a position where the distance PC21x in the chord line BC21 direction from the outer peripheral edge portion 24 to the top PC21c is 10% of the full length LL21 of the chord line BC21. As a better form, On the positive pressure surface 20P, It is the same as the case of the propeller fan 101 in Embodiment 1. In addition to the above-mentioned concave surface PV21 and convex surface PC21, Other concave portions (corresponding to FIG. 3, Concave surface PV12 shown in Figure 4) and convex surface (corresponding to Figure 3, (Convex surface of convex surface PC12 shown in FIG. 4). Regarding such configuration, The same configuration as that described in the first embodiment can be applied to these. (Sectional shape S22) FIG. 16 is an arrow sectional view taken along the line XVI-XVI in FIG. 13, A cross-sectional shape S22 (other second cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the straight line CR22 shown in FIG. 13 is shown. FIG. 17 is a cross-sectional view enlargedly showing a region surrounded by a line XVII in FIG. 16. As shown in Figure 16 and Figure 17, The cross-sectional shape S22 (the other second cross-sectional shape) of the wing portion 20 is the same as the cross-sectional shape S21 described above, On the negative pressure surface 20N, At least a concave portion NV21 (third concave portion) and a convex portion NC21 (third convex portion) are formed, On the positive pressure surface 20P, At least a convex surface PC21 (fourth convex surface) and a concave surface PV21 (fourth concave surface) are formed. With regard to each of these configurations and preferable configurations related to the cross-sectional shape S22, Since the cross-sectional shape S22 is substantially the same as the cross-sectional shape S21, Therefore, the repeated explanation is not repeated. As a better constitution, In the cross-sectional shape S22 (the other second cross-sectional shape), The surface shape of the positive pressure surface 20P (refer to the surface shape NR shown in FIG. 6) between the outer peripheral edge portion 24 and the top portion PC21c (the fourth top portion) of the convex portion PC21 (the fourth convex portion) follows the chord line BC21 Way of forming. This structure can also be applied to the above-mentioned cross-sectional shape S21 (second cross-sectional shape), And / or the following cross-sectional shape S23 (and further another second cross-sectional shape). (Sectional shape S23) FIG. 18 is a sectional view of the arrow along the line XVIII-XVIII in FIG. 13, A cross-sectional shape S23 (and other second cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 using the straight line CR23 shown in FIG. 13 is shown. FIG. 19 is a cross-sectional view showing an area surrounded by a line XIX in FIG. 18 in an enlarged manner. As shown in Figure 18 and Figure 19, The cross-sectional shape S23 (and other second cross-sectional shapes) of the wing portion 20 is the same as the cross-sectional shape S21 described above, On the negative pressure surface 20N, At least a concave portion NV21 (third concave portion) and a convex portion NC21 (third convex portion) are formed, On the positive pressure surface 20P, At least a convex surface PC21 (fourth convex surface) and a concave surface PV21 (fourth concave surface) are formed. With regard to each of these structures and preferable structures related to the cross-sectional shape S23, Since the cross-sectional shape S23 is substantially the same as the cross-sectional shape S21, Therefore, the repeated explanation is not repeated. (Actions and Effects) With reference to FIGS. 13 to 15 and the like, The propeller fan 102 rotates and generates airflow. The airflow flows into the airfoil surface through the vicinity of the outer peripheral edge portion 24 of the airfoil portion 20. Here, The air passing through the vicinity of the outer peripheral edge portion 24 of the wing portion 20 follows the straight line passing through the starting point (P1) and the end point (P2) satisfying the relationship of LB / LA = DB / DA from the outer peripheral portion 24 (actually a curved line ) (Approximately circular arc) through the airfoil, It flows out from the trailing edge portion 26. (Concave surface NV21) On the negative pressure surface 20N of the propeller fan 102, A concave portion NV21 (third concave portion) is formed at a specific position. According to this constitution, The boundary layer turbulence generated on the immediately downstream side of the peripheral edge portion 24 outside the negative pressure surface 20N, Especially, it occurs in the concave part of the concave surface part NV21 (near the bottom part NV21c). This is significant in the following situations: The bottom NV21c is formed at a position where the distance between the outer peripheral edge portion 24 and the chord line BC21 of the bottom NV21c is 5% or more and 15% or less of the total length LL21 of the chord line BC21. This is particularly significant in the following situations: The bottom NV21c is formed at a position where the distance NV21x from the outer peripheral edge portion 24 to the chord line BC21 of the bottom NV21c is 10% of the total length LL21 of the chord line BC21. on the other hand, The main flow passing on the wing surface of the wing portion 20 does not flow into the concave portion of the concave surface portion NV21, That is, it circulates through the upper surface of the boundary layer turbulence. therefore, The boundary layer in the concave portion of the concave portion NV21 is turbulently fixed in the concave portion, Thereby, propagation (enlargement) from the concave portion to the outside is suppressed. With this, The boundary layer turbulence can be kept small and effectively stabilized. Since almost no boundary layer turbulence disappears, produce, Disappear again, Recurrence of the occurrence and disappearance of turbulence in the boundary layer occurs again, Therefore, noise can be further suppressed in the state where the boundary layer turbulence exists. (Concave surface PV21) Referring to FIGS. 13 to 15 and the like, As mentioned above, On the positive pressure surface 20P of the propeller fan 102, A convex portion PC21 (fourth convex portion) and a concave portion PV21 (fourth concave portion) are formed at specific positions. According to this constitution, Vortex can be effectively generated on the concave surface PV21 (concave part) located downstream of the convex surface PC21, The eddy current is stably secured in the concave surface portion PV21. If the wing portion 20 has a wing shape having the largest thickness at a portion close to the outer peripheral edge portion 24 (equivalent to the position of the concave portion PV21 of the second embodiment), A large lift force can be sufficiently generated at a position close to the outer peripheral edge portion 24, But as a consequence of this, The frictional resistance caused by the friction between the wind and the airfoil increases. In contrast, According to the propeller fan 102 of this embodiment, A concave surface PV21 is formed at this part, And use the convex part PC21 to make it generate vortex stably, This can prevent wind and airfoil from directly rubbing against each other, In addition, the wall thickness of the portion that becomes the maximum thickness in the case described above can be significantly reduced. also, In the propeller fan 102 of this embodiment, As a better form, On the negative pressure surface 20N or the positive pressure surface 20P, It is the same as the case of the propeller fan 101 in Embodiment 1. Further, other concave portions and other convex portions may be formed. The shape of the wing is formed by the vortex that stays inside the other concave surface or other concave surface, etc. (when the vortex is attached to the thin-walled wing, it has a wing shape as a whole), So despite being thin and lightweight, But the lift is roughly equal to the thick-walled wing, Since the frictional resistance is reduced as described above, Therefore, the design can also be used to make the lift-to-drag ratio exceed that of thick-walled wings. Regarding the 20N side of the negative pressure surface, The bottom of the other concave portion is preferably formed at a position where the distance from the outer peripheral edge portion 24 to the chord line BC21 of the bottom is 40% or more and 50% or less of the full length LL21 of the chord line BC21. The top of the other convex surface portion is preferably formed at a position where the distance from the outer peripheral edge portion 24 to the chord line BC21 of the top is 60% or more and 70% or less of the full length LL21 of the chord line BC21. On the 20P side of the positive pressure surface, The top of the other convex portion is preferably formed at a position where the distance from the outer peripheral edge portion 24 to the chord line BC21 of the top is 40% to 50% of the full length LL21 of the chord line BC21. The bottom of the other concave surface portion is preferably formed at a position where the distance from the outer peripheral edge portion 24 to the chord line BC21 of the bottom is 60% to 70% of the full length LL21 of the chord line BC21. The following designs are preferred for these systems: By placing them as evenly as possible, While reducing friction resistance with a lighter weight, One side contains the generated vortex to form a better wing shape. As mentioned above, The surface shape of the positive pressure surface 20P (refer to the surface shape NR shown in FIG. 6) between the outer peripheral edge portion 24 and the top portion PC21c (the fourth top portion) of the convex portion PC21 (the fourth convex portion) preferably follows the chord The line BC21 is formed. The flow flowing from the outer peripheral edge portion 24 side flows along the surface shape NR (see arrow DR shown in FIG. 6), Can define the direction of flow, result, A vortex can be stably generated at a position downstream of the surface shape NR. (About strength assurance and weight reduction) According to the propeller fan 102 of this embodiment, The following secondary effects can also be expected. which is, Even if the thickness of the wings of the propeller fan 102 is reduced, You can also use the lift that rivals thick-walled wings, And Although thin-walled, it has higher strength, result, Significant weight reduction of fans can be achieved. in particular, In a normal propeller fan, If the entire wing portion is formed into a thick wall shape to increase the lift, According to the shape of the thick-walled wing, a large lift can be reliably obtained and the strength can be improved. But as a disadvantage, Increased weight of wings or fans, The required driving torque becomes larger, Or the cost of materials increases. When a large centrifugal force is applied due to high-speed rotation, etc., There is also a possibility that a large stress acts on the root of the leading edge of the wing and the blade expands or breaks outward. According to the propeller fan 102 of this embodiment, Has such as airfoil twice, Or two or more curved shapes, This takes the shape of undulating airfoils. therefore, Can increase the strength per unit thickness, It also reduces the possibility of damage during high-speed rotation. therefore, According to the propeller fan 102 of this embodiment, Almost no increase in material costs, Instead, we can reduce material costs by reducing weight. In addition to strength or lift, It is also possible to improve the air supply performance or air supply efficiency. According to the fluid conveying device provided with the propeller fan 102 having such characteristics, Can help save energy, And people with high product value who can improve the quietness can be expected. [Modification of Embodiment 2] The above-described configuration described in Embodiment 2 can be implemented in combination with the above-described configuration described in Embodiment 1. It may be implemented separately from the above-described configuration described as the first embodiment. According to Embodiment 1, 2 of the propeller fan, In addition to promoting the inflow of air from the leading edge portion 22, The inflow of air from the outer peripheral edge portion 24 is also promoted. Since the air flow around the propeller fan can be optimized, Therefore, the overall characteristics of the fan can be greatly improved. Furthermore, By setting the shape of the airfoil to be curved twice or more in two directions, It can also greatly increase the strength. [Embodiment 3] Fig. 20 is a plan view showing a propeller fan 103 according to Embodiment 3. The propeller fan 101 according to the first embodiment is different from the propeller fan 103 according to the third embodiment in the following points. The plane CR31 passing through an arbitrary position (Q1) on the outer peripheral edge portion 24 and the central axis AX is defined. CR32, CR33. By using plane CR31, CR32, The cross-sectional shape of the wing portion 20 obtained by CR33 imaginarily cutting the wing portion 20 is defined as the cross-sectional shape S31, S32, S33. Regarding the cross-sectional shape S31, Refer to Figure 21, Figure 22 illustrates, Regarding the cross-sectional shape S32, Refer to Figure 23, Figure 24 illustrates, Regarding the cross-sectional shape S33, Refer to Figure 25, FIG. 26 is described. (Sectional shape S31) FIG. 21 is a sectional view of the arrow along the line XXI-XXI in FIG. 20, A cross-sectional shape S31 (third cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the plane CR31 shown in FIG. 20 is shown. FIG. 22 is a cross-sectional view enlargedly showing a region surrounded by a line XXII in FIG. 21. As shown in Figure 20, A portion between the wing portion 20 and the rotation shaft portion 10 in the cross-sectional shape S31 (third cross-sectional shape) of the wing portion 20 is defined as the connection portion 28 (FIG. 20). The connecting portion 28 is located on a cylindrical surface of the outer surface of the predetermined rotation shaft portion 10, And the part located in the center of the wing part 20 in the direction of the central axis AX (refer to FIG. 23, Figure 25). A line segment connecting the position of the outer peripheral edge portion 24 of the cross-sectional shape S31 of the wing portion 20 and the position of the connecting portion 28 is defined as a chord line BC31 (third chord line). A position away from the cross-sectional shape S31 of the wing portion 20 toward the positive pressure surface 20P in the direction of the central axis AX, A straight line parallel to the chord line BC31 is drawn and a reference line BL31 (third reference line) is defined. (About the surface shape of the negative pressure surface 20N) In the propeller fan 103 of this embodiment, Formed on the negative pressure surface 20N side of the cross-sectional shape S31 of the wing portion 20: Convex surface NC31 (5th convex surface), It has a surface shape curved into a convex shape in the direction of the central axis AX; And concave surface NV31 (5th concave surface), It is located between the convex surface portion NC31 and the outer peripheral edge portion 24 and has a surface shape that is curved in a concave shape in the direction of the central axis AX. (About the position of the top part NC31c of the convex part NC31 formed on the negative pressure surface 20N) The convex part NC31 (5th convex part) has the top NC31c (5th top) (refer FIG. 22). The top NC31c is separated from the above-mentioned reference line BL31 by a distance NC31y (the distance referred to here refers to the distance in the projection plane formed by projecting the cross-sectional shape S31 on a plane parallel to the central axis AX That is, the distance in a direction orthogonal to the reference line BL31. Same below.) The top NC31c is part of the convex surface NC31, Tied to the chord line BC31, As it goes from the outer peripheral edge portion 24 side to the connecting portion 28 side, The distance from the above-mentioned reference line BL31 to the convex portion NC31 is gradually changed from a gradually increasing portion to a decreasing portion. The top NC31c having such characteristics is formed at a position where the distance NC31x in the direction of the chord line BC31 from the outer peripheral edge portion 24 to the top NC31c is 1/3 or less (about 33%) of the full length LL31 of the chord line BC31. As a better constitution, The top NC31c is formed at a position where the distance NC31x in the chord line BC31 direction from the outer peripheral edge portion 24 to the top NC31c is 20% or more and 30% or less of the full length LL31 of the chord line BC31. The propeller fan 103 of this embodiment is provided with this structure. (Regarding the position of the bottom NV31c of the concave portion NV31 formed on the negative pressure surface 20N) The concave portion NV31 (the fifth concave portion) has a bottom NV31c (the fifth bottom) (see FIG. 22). The bottom NV31c is separated from the reference line BL31 by a distance NV31y. The bottom NV31c is part of the concave surface NV31, Tied to the chord line BC31, As it goes from the outer peripheral edge portion 24 side to the connecting portion 28 side, The distance from the above-mentioned reference line BL31 to the concave surface NV31 changes from decreasing to increasing. As a better constitution, The bottom NV31c is formed at a position where the distance NV31x in the chord line BC31 direction of the chord line BC31 from the outer peripheral edge portion 24 to the bottom NV31c is 5% or more and 15% or less. The propeller fan 103 of this embodiment is provided with this structure, The bottom NV31c is formed at a position where the distance NV31x in the chord line BC31 direction from the outer peripheral edge portion 24 to the bottom NV31c is 10% of the full length LL31 of the chord line BC31. As a better form, On the negative pressure surface 20N, It is the same as the case of the propeller fan 101 in Embodiment 1. In addition to the above-mentioned concave surface NV31 and convex surface NC31, Other concave portions (corresponding to FIG. 3, The concave surface of the concave surface NV12 shown in Fig. 4) and other convex surfaces (corresponding to Fig. 3, The convex surface of the convex surface NC12 shown in FIG. 4). Regarding such configuration, The same configuration as that described in the first embodiment can be applied to these. (About the surface shape of the positive pressure surface 20P) In the propeller fan 103 of this embodiment, Formed on the positive pressure surface 20P side of the sectional shape S31 of the wing portion 20: Concave surface PV31 (sixth concave surface), It has a surface shape curved into a concave shape in the direction of the central axis AX; And convex surface PC31 (sixth convex surface), It is located between the concave surface portion PV31 and the outer peripheral edge portion 24 and has a surface shape curved in a convex shape in the direction of the central axis AX. (Regarding the position of the bottom PV31c of the concave surface PV31 formed on the positive pressure surface 20P) The concave surface PV31 (the sixth concave surface) has a bottom PV31c (the sixth bottom) (see FIG. 22). The bottom PV31c is separated from the reference line BL31 by a distance PV31y. The bottom PV31c is a part of the concave surface PV31, Tied to the chord line BC31, As it goes from the outer peripheral edge portion 24 side to the connecting portion 28 side, The distance from the above-mentioned reference line BL31 to the concave portion PV31 is gradually changed from a gradually increasing portion to a gradually decreasing portion. As a better constitution, The bottom PV31c is formed at a position where the distance PV31x in the chord line BC31 direction of the chord line BC31 from the outer peripheral edge portion 24 to the bottom PV31c is 1/3 or less (about 33% or less) of the full length of the chord line BC31. As a further preferable structure, The bottom PV31c is formed at a position where the distance PV31x in the chord line BC31 direction from the outer peripheral edge portion 24 to the bottom PV31c is 20% or more and 30% or less of the full length LL31 of the chord line BC31. The propeller fan 103 of this embodiment is provided with this structure. (About the position of the top PC31c of the convex surface PC31 formed on the positive pressure surface 20P) The convex surface PC31 (6th convex surface) has the top PC31c (6th top) (refer FIG. 22). The top PC31c is separated from the reference line BL31 by a distance PC31y. The top PC31c is a part of the convex surface PC31, Tied to the chord line BC31, As it goes from the outer peripheral edge portion 24 side to the connecting portion 28 side, The distance from the above-mentioned reference line BL31 to the convex surface PC31 is gradually changed from a decreasing portion to an increasing portion. As a better constitution, The top PC31c is formed at a position where the distance PC31x in the chord line BC31 direction from the outer peripheral edge portion 24 to the top PC31c is 5% or more and 15% or less of the full length LL31 of the chord line BC31. The propeller fan 103 of this embodiment is provided with this structure, The top PC31c is formed at a position where the distance PC31x in the chord line BC31 direction from the outer peripheral edge portion 24 to the top PC31c is 10% of the full length LL31 of the chord line BC31. As a better form, On the positive pressure surface 20P, It is the same as the case of the propeller fan 101 in Embodiment 1. In addition to the above-mentioned concave surface PV31 and convex surface PC31, Other concave portions (corresponding to FIG. 3, Concave surface PV12 shown in Figure 4) and convex surface (corresponding to Figure 3, (Convex surface of convex surface PC12 shown in FIG. 4). Regarding such configuration, The same configuration as that described in the first embodiment can be applied to these. (Sectional shape S32) FIG. 23 is a sectional view of the arrow along the line XXIII-XXIII in FIG. 20, A cross-sectional shape S32 (other third cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 using the plane CR32 shown in FIG. FIG. 24 is a cross-sectional view enlargedly showing a region surrounded by a line XXIV in FIG. 23. As shown in Figures 23 and 24, The cross-sectional shape S32 (other third cross-sectional shape) of the wing portion 20 is the same as the cross-sectional shape S31 described above, On the negative pressure surface 20N, At least a concave portion NV31 (the fifth concave portion) and a convex portion NC31 (the fifth convex portion) are formed, On the positive pressure surface 20P, At least a convex surface PC31 (sixth convex surface) and a concave surface PV31 (sixth concave surface) are formed. With regard to each of these structures and preferable structures related to the cross-sectional shape S32, Since the cross-sectional shape S32 is substantially the same as the cross-sectional shape S31, Therefore, the repeated explanation is not repeated. As a better constitution, In the cross-sectional shape S32 (the other third cross-sectional shape), The surface shape of the positive pressure surface 20P (refer to the surface shape NR shown in FIG. 6) between the outer peripheral edge portion 24 and the top portion PC31c (the sixth top portion) of the convex portion PC31 (the sixth convex portion) follows the chord line BC31. Way of forming. This structure can also be applied to the above-mentioned cross-sectional shape S31 (third cross-sectional shape), And / or the following cross-sectional shape S33 (and further the third cross-sectional shape). (Sectional shape S33) FIG. 25 is an arrow sectional view taken along the line XXV-XXV in FIG. 20, A cross-sectional shape S33 (and other third cross-sectional shape) of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the plane CR33 shown in FIG. 20 is shown. FIG. 26 is a cross-sectional view enlargedly showing a region surrounded by a line XXVI in FIG. 25. As shown in Figure 25 and Figure 26, The cross-sectional shape S33 (and other third cross-sectional shapes) of the wing portion 20 is the same as the cross-sectional shape S31 described above, On the negative pressure surface 20N, At least a concave portion NV31 (the fifth concave portion) and a convex portion NC31 (the fifth convex portion) are formed, On the positive pressure surface 20P, At least a convex surface PC31 (sixth convex surface) and a concave surface PV31 (sixth concave surface) are formed. With regard to each of these structures and preferable structures related to the cross-sectional shape S33, Since the cross-sectional shape S33 is substantially the same as the cross-sectional shape S31, Therefore, the repeated explanation is not repeated. (Actions and Effects) With reference to FIGS. 20 to 22 and the like, The propeller fan 103 rotates and generates airflow. The airflow flows into the airfoil surface by passing near the outer peripheral edge portion 24 of the airfoil portion 20. Here, The air passing through the vicinity of the outer peripheral edge portion 24 of the wing portion 20 follows the straight line passing through the starting point (P1) and the end point (P2) satisfying the relationship of LB / LA = DB / DA from the outer peripheral portion 24 (actually a curved line ) (Approximately circular arc) through the airfoil, And flows out from the trailing edge portion 26. When viewed only near the outer peripheral edge portion 24, Then, the state of the airflow passing through the vicinity of the outer peripheral portion 24 of the wing portion 20 and the direction of the rotation radius, That is, the state where an arbitrary position on the outer peripheral edge portion 24 is connected in a straight line to the direction of the center axis AX is substantially the same, Which can be approximated, Even for propeller fans adopting this idea, The same functions and effects as those of the second embodiment can also be obtained. [Modification of Embodiment 3] The above-described configuration described in Embodiment 3 can be implemented in combination with the above-described configuration described in Embodiment 1. It may be implemented separately from the above-described configuration described as the first embodiment. The above-described configuration described as the third embodiment can be implemented in combination with the above-described configuration described as the second embodiment. It may be implemented separately from the above-described configuration described as the second embodiment. The above-mentioned configuration described as the third embodiment can be the same as that of the first embodiment. The above-mentioned composition described in combination is implemented, Can also be used as Embodiment 1, The above-mentioned configuration described in 2 is implemented separately. [Experimental Example 1] As an experimental example of the first embodiment, Prepare propeller fan for air-conditioning outdoor unit. The propeller fan has a diameter of 466 mm, As a representative size of the structure of the first embodiment, In the center of the leading edge portion 22, The chord length C is 228 mm, The thickness tmax is 4. 8 mm, t / c is 2. 1%. Similarly, as an experimental example of the second embodiment, a propeller fan for an air-conditioning outdoor unit is prepared. The propeller fan has a diameter of 466 mm, as a representative size of the configuration of Embodiment 2, immediately adjacent to the outside of the front end of the wing, the chord length C is 425 mm, and the thickness tmax is 3. 44 mm, t / c is 0. 8%. In the configuration shown in FIG. 11 (the configuration of Patent Document 1), the value of t / c is about 5 to 12%. However, in the propeller fan based on Embodiments 1 and 2, the limit can be significantly exceeded. [Experimental Example 2] A vibration measuring device as shown in Fig. 27 was prepared. A wind tunnel having a box-like shape is mounted on the mounting table, and a propeller fan having a configuration including both Embodiments 1 and 2 is stored and driven as an "embodiment". The measurement position F4 is located at the upper part of the front when viewed from the propeller fan, the measurement position F8 is located at the right side when viewed from the propeller fan, and the measurement position F9 is located at the back when viewed from the propeller fan. As a "comparative example", a propeller fan having the configuration shown in FIG. 11 (the configuration of Patent Document 1) was used. Referring to FIGS. 28 to 30, the vibration value [µm] when the number of rotations of the fan is increased or decreased is measured at each of the measurement positions F4, F8, and F9. It can be seen that the measurement results are compared with the comparative examples. Small vibration. Therefore, according to the configuration of the example, it is considered that the vibration can be reduced compared to the configuration of the comparative example. [Experimental Example 3] Referring to Fig. 31, as in the case of Experimental Example 2 described above, the "Examples" and "Comparative Examples" were measured for PQ characteristics. The fans were rotated in the air-conditioning outdoor unit at a rotation number of 500 rpm. The quadratic curve of the solid line shown in FIG. 31 is the normal operation curve, and the quadratic curve of the dotted line is the operation curve during frosting. In the case of the comparative example, the air flow Q and the static pressure P are each 25. 8 m ³ / min, 10.3 Pa, 23.5 m in frost ³ / min, 13.5 Pa. On the other hand, in the case of the comparative example, the air volume Q and the static pressure P are each 27.5 m in normal time. ³ / min, 11.4 Pa, 24.5 m in frosting ³ / min, 14.5 Pa. If the comparison shows the value of P × Q as the output of the air supply device, the structure of the embodiment is increased by 18% in comparison with the structure of the comparative example in normal time, and the structure of the embodiment is increased compared with the structure of the comparative example in frost formation. 12%. Referring to Fig. 32, the relationship between the number of rotations and the air volume was measured for "Example" and "Comparative Example" in the same manner. It can be seen that the configuration of the example is approximately 6.5% higher than that of the comparative example. Referring to Fig. 33, the relationship between the air volume and power consumption was measured for "Example" and "Comparative Example" in the same manner. It can be seen that regarding the power consumption, the configuration of the embodiment is particularly advantageous because the air volume is small. The embodiments and experimental examples have been described above, but the above disclosure is illustrative in all respects, and is not restrictive. The technical scope of the present invention is disclosed through the scope of patent application, and is intended to include all changes within the meaning and scope equivalent to the scope of patent application. [Industrial Applicability] The propeller fan disclosed in this disclosure can be used for various fluid conveying devices such as air-conditioning outdoor units, hair dryers, curl dryers, pet hair dryers, garden blowers, and electric fans.

10‧‧‧Rotating shaft
20‧‧‧wing
20N‧‧‧Negative pressure surface
20P‧‧‧Positive pressure surface
20S‧‧‧Negative pressure surface
21‧‧‧ medial end
22‧‧‧ leading edge
23‧‧‧wing front
24‧‧‧outer periphery
25‧‧‧outer end
26‧‧‧back edge
26C‧‧‧Central Department
27‧‧‧ medial end
28‧‧‧Connecting Department
100‧‧‧ fluid conveying device
101‧‧‧ Propeller Fan
102‧‧‧ Propeller fan
103‧‧‧ Propeller fan
110‧‧‧Frame
120‧‧‧Vent
AR‧‧‧Arrow
AX‧‧‧Center axis
BC11‧‧‧wing chord line
BC21‧‧‧wing chord line
BC31‧‧‧wing chord line
BL11‧‧‧Baseline
BL21‧‧‧Baseline
BL31‧‧‧Baseline
CR11‧‧‧Circle
CR12‧‧‧Circle
CR13‧‧‧Circle
CR21‧‧‧Straight
CR22‧‧‧Straight
CR23‧‧‧Straight
CR31‧‧‧plane
CR32‧‧‧plane
CR33‧‧‧Plane
DA‧‧‧Distance
DB‧‧‧Distance
DR‧‧‧ Arrow
F4‧‧‧Measurement position
F8‧‧‧Measurement position
F9‧‧‧Measurement position
III-III‧‧‧line
IV‧‧‧line
LA‧‧‧ Full length
LB‧‧‧Distance
LL11‧‧‧ full length
LL21‧‧‧ full length
LL31‧‧‧ full length
NC11‧‧‧ convex face
NC11c‧‧‧Top
NC11x‧‧‧Distance
NC11y‧‧‧Distance
NC12‧‧‧ convex face
NC12c‧‧‧Top
NC12x‧‧‧distance
NC12y‧‧‧Distance
NC21‧‧‧ convex face
NC21c‧‧‧Top
NC21x‧‧‧distance
NC21y‧‧‧Distance
NC31‧‧‧ convex face
NC31c‧‧‧Top
NC31x‧‧‧distance
NC31y‧‧‧Distance
NR‧‧‧Surface shape
NV11‧‧‧ Concave face
NV11c‧‧‧ bottom
NV11x‧‧‧Distance
NV11y‧‧‧Distance
NV12‧‧‧ Concave face
NV12c‧‧‧ bottom
NV12x‧‧‧Distance
NV12y‧‧‧Distance
NV21‧‧‧ Concave face
NV21c‧‧‧ bottom
NV21x‧‧‧Distance
NV21y‧‧‧Distance
NV31‧‧‧Concave face
NV31c‧‧‧ bottom
NV31x‧‧‧Distance
NV31y‧‧‧Distance
P‧‧‧static pressure
P1‧‧‧point
P2‧‧‧point
PC11‧‧‧ convex face
PC11c‧‧‧Top
PC11x‧‧‧Distance
PC11y‧‧‧Distance
PC12‧‧‧ convex face
PC12c‧‧‧Top
PC12x‧‧‧ Distance
PC12y‧‧‧Distance
PC21‧‧‧ convex face
PC21c‧‧‧Top
PC21x‧‧‧Distance
PC21y‧‧‧Distance
PC31‧‧‧Convex face
PC31c‧‧‧Top
PC31x‧‧‧ Distance
PC31y‧‧‧Distance
PV11‧‧‧Concave face
PV11c‧‧‧ bottom
PV11x‧‧‧distance
PV11y‧‧‧Distance
PV12‧‧‧Concave face
PV12c‧‧‧ bottom
PV12x‧‧‧distance
PV12y‧‧‧Distance
PV21‧‧‧Concave face
PV21c‧‧‧ bottom
PV21x‧‧‧distance
PV21y‧‧‧Distance
PV31‧‧‧Concave face
PV31c‧‧‧ bottom
PV31x‧‧‧distance
PV31y‧‧‧Distance
Q‧‧‧Air volume
Q1‧‧‧anywhere
S11‧‧‧ Section Shape
S12‧‧‧ Section shape
S13‧‧‧ Section shape
S21‧‧‧ Section shape
S22‧‧‧ Section shape
S23‧‧‧ Section shape
S31‧‧‧ Section shape
S32‧‧‧ Section shape
S33‧‧‧ Section shape
SZ‧‧‧ Section Shape
VV‧‧‧line
VI‧‧‧line
Line VII-VII‧‧‧
Line VIII‧‧‧
XIV-XIV‧‧‧line
XIX‧‧‧line
XV‧‧‧line
XVI-XVI‧‧‧line
XVII‧‧‧line
XVIII-XVIII‧‧‧line
XXI-XXI‧‧‧line
XXII‧‧‧line
XXIV‧‧‧line
XXIII-XXIII‧‧‧line
XXV-XXV‧‧‧line
XXVI‧‧‧line
ZC‧‧‧ convex face
ZCc‧‧‧Top
ZV‧‧‧ Concave face
ZVc‧‧‧ bottom

FIG. 1 is a perspective view showing a fluid transfer device 100 according to the first embodiment. Fig. 2 is a plan view showing a propeller fan 101 according to the first embodiment. FIG. 3 is an arrow sectional view taken along the line III-III in FIG. 2, and shows the cross-sectional shape S11 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the arc CR11 shown in FIG. 2 ( 1st cross-sectional shape). FIG. 4 is a cross-sectional view showing an area surrounded by an IV line in FIG. 3 in an enlarged manner. FIG. 5 is a cross-sectional view of the arrow along the VV line in FIG. 2, showing a cross-sectional shape S12 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the arc CR12 shown in FIG. 2 (other sections 1 cross-sectional shape). FIG. 6 is a cross-sectional view showing an area surrounded by a line VI in FIG. 5 in an enlarged manner. FIG. 7 is an arrow sectional view taken along the line VII-VII in FIG. 2, and shows a sectional shape S13 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the circular arc CR13 shown in FIG. 2 ( And other first cross-sectional shapes). FIG. 8 is an enlarged sectional view showing an area surrounded by a line VIII in FIG. 7. FIG. 9 is a plan view for explaining the function and effect of the propeller fan 101 according to the first embodiment. FIG. 10 is a diagram for explaining the function and effect of the cross-sectional shape S11 of the propeller fan 101 (wing portion 20) according to the first embodiment. FIG. 11 is a diagram showing a cross-sectional shape SZ of a propeller fan (wing portion) of a comparative example. FIG. 12 is a diagram for explaining the function and effect of the cross-sectional shape S12 of the propeller fan 101 (wing portion 20) according to the first embodiment. FIG. 13 is a plan view showing a propeller fan 102 according to the second embodiment. FIG. 14 is an arrow cross-sectional view taken along the line XIV-XIV in FIG. 13, and shows a cross-sectional shape S21 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the straight line CR21 shown in FIG. 2 cross-sectional shape). FIG. 15 is an enlarged cross-sectional view showing an area surrounded by the XV line in FIG. 14. FIG. 16 is an arrow cross-sectional view taken along the line XVI-XVI in FIG. 13 and shows the cross-sectional shape S22 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the straight line CR22 shown in FIG. 13 (other 2nd cross-sectional shape). FIG. 17 is a cross-sectional view enlargedly showing a region surrounded by a line XVII in FIG. 16. FIG. 18 is an arrow cross-sectional view taken along the line XVIII-XVIII in FIG. 13 and shows the cross-sectional shape S23 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the straight line CR23 shown in FIG. 13 (and further Other second cross-sectional shapes). FIG. 19 is a cross-sectional view showing an area surrounded by a line XIX in FIG. 18 in an enlarged manner. Fig. 20 is a plan view showing a propeller fan 103 according to the third embodiment. FIG. 21 is an arrow sectional view taken along the line XXI-XXI in FIG. 20, and shows a cross-sectional shape S31 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 using the plane CR31 shown in FIG. 20 (No. 3 cross-sectional shape). FIG. 22 is a cross-sectional view enlargedly showing a region surrounded by a line XXII in FIG. 21. FIG. 23 is a cross-sectional view of the arrow along the line XXIII-XXIII in FIG. 20, and shows a cross-sectional shape S22 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 using the plane CR32 shown in FIG. 20 (others 3rd cross-sectional shape). FIG. 24 is a cross-sectional view enlargedly showing a region surrounded by a line XXIV in FIG. 23. FIG. 25 is an arrow cross-sectional view taken along the line XXV-XXV in FIG. 20, and shows the cross-sectional shape S33 of the wing portion 20 obtained by imaginarily cutting the wing portion 20 by using the plane CR33 shown in FIG. 20 (and further Other third cross-sectional shapes). FIG. 26 is a cross-sectional view enlargedly showing a region surrounded by a line XXVI in FIG. 25. FIG. 27 is a perspective view for explaining a vibration measuring device of Experimental Example 2. FIG. FIG. 28 is a diagram showing the relationship between the number of rotations and the vibration at the measurement position F4 in Experimental Example 2. FIG. FIG. 29 is a graph showing the relationship between the number of rotations and the vibration at the measurement position F8 in Experimental Example 2. FIG. FIG. 30 is a diagram showing the relationship between the number of rotations and the vibration at the measurement position F9 in Experimental Example 2. FIG. FIG. 31 is a graph showing P-Q characteristics for Experimental Example 3 and for Examples and Comparative Examples. FIG. 32 is a graph showing the relationship between the number of rotations and the air volume for the example and the comparative example regarding experimental example 3. FIG. FIG. 33 is a graph showing the relationship between the air volume and the power consumption for the example and the comparative example in relation to experimental example 3. FIG.

20N‧‧‧Negative pressure surface

20P‧‧‧Positive pressure surface

22‧‧‧ leading edge

AX‧‧‧Center axis

BC11‧‧‧wing chord line

BL11‧‧‧Baseline

LL11‧‧‧ full length

NC11‧‧‧ convex face

NC11c‧‧‧Top

NC11x‧‧‧Distance

NC11y‧‧‧Distance

NC12‧‧‧ convex face

NC12c‧‧‧Top

NC12x‧‧‧distance

NC12y‧‧‧Distance

NV11‧‧‧ Concave face

NV11c‧‧‧ bottom

NV11x‧‧‧Distance

NV11y‧‧‧Distance

NV12‧‧‧ Concave face

NV12c‧‧‧ bottom

NV12x‧‧‧Distance

NV12y‧‧‧Distance

PC11‧‧‧ convex face

PC11c‧‧‧Top

PC11x‧‧‧Distance

PC11y‧‧‧Distance

PC12‧‧‧ convex face

PC12c‧‧‧Top

PC12x‧‧‧ Distance

PC12y‧‧‧Distance

PV11‧‧‧Concave face

PV11c‧‧‧ bottom

PV11x‧‧‧distance

PV11y‧‧‧Distance

PV12‧‧‧Concave face

PV12c‧‧‧ bottom

PV12x‧‧‧distance

PV12y‧‧‧Distance

S11‧‧‧ Section Shape

Claims (9)

A propeller fan includes: a rotation shaft portion that rotates around an imaginary center axis; and a wing portion that has a shape that extends from the rotation shaft portion side toward the outside in the direction of the rotation radius, and is rotated positively by rotation. The back surface forms a positive pressure surface and a negative pressure surface, respectively; and the wing portion includes: a front end portion of the wing, which is located at the forefront of the rotation direction; a front edge portion, which forms the front edge of the wing portion in the rotation direction; a rear edge portion, which forms The trailing edge of the wing portion in the rotation direction; and an outer peripheral edge portion that connects the front end portion of the wing and the outer end of the trailing edge portion to form the outer peripheral edge of the wing portion in the radial direction of rotation; and Position the center and cut the wing portion by an arc of any radius of the leading edge portion and the trailing edge portion to define the first cross-sectional shape of the wing portion, and connect the front of the first cross-sectional shape of the wing portion to the front portion. The line segment between the position of the edge portion and the position of the trailing edge portion is defined as a first chord line, and is away from the positive pressure surface side from the first cross-sectional shape of the wing portion in the center axis direction. A position is defined by drawing a straight line parallel to the first chord line to define a first reference line, and a first convex surface portion is formed on the negative pressure surface side of the first cross-sectional shape of the wing portion at the center A surface shape curved into a convex shape in the axial direction; and a first concave surface portion located between the first convex surface portion and the leading edge portion and having a surface shape curved into a concave shape in the central axis direction; and The first convex portion has a first top portion, which is located in the first chord line direction from the front edge portion side to the rear edge portion side, and the distance from the first reference line to the first convex portion is Increasingly changing to gradually decreasing portion; and the distance between the first top portion formed in the direction of the first chord line from the front edge portion to the first top portion is less than 1/3 of the total length of the first chord line s position. For example, the propeller fan of claim 1, wherein the first concave surface portion has a first bottom portion, which is connected to the first chord line direction from the front edge portion side toward the rear edge portion side, and the first reference The distance from the line to the first concave surface portion is gradually reduced to a gradually increasing portion; and the distance from the front edge portion to the first chord line direction of the first bottom portion is the first The chord line is at least 5% to 15% of the total length. The propeller fan according to claim 1 or 2, wherein a second concave surface portion is formed on the positive pressure surface side of the first cross-sectional shape of the wing portion, and has a surface shape curved in a concave shape in the direction of the central axis. And a second convex surface portion, which is located between the second concave surface portion and the leading edge portion, and has a surface shape that is curved in a convex shape in the direction of the central axis; The distance from the first reference line to the second concave surface portion is gradually changed from an increasing portion to a decreasing portion in the direction of the first chord line from the leading edge portion toward the trailing edge portion; and The second bottom portion is formed at a position where the distance in the direction of the first chord line from the front edge portion to the second bottom portion is 1/3 or less of the total length of the first chord line. For the propeller fan of claim 1 or 2, in which if the full length of the outer peripheral portion is specified as LA, a starting point is specified at an arbitrary position on the outer peripheral portion, and the front end portion of the wing is extended to the outer peripheral portion of the starting point. The distance is specified as LB, and the distance from the central portion of the trailing edge portion to the outer end of the trailing edge portion on the trailing edge portion is defined as DA, on the trailing edge portion and the central portion of the trailing edge portion and The end point is defined at an arbitrary position between the outer ends of the trailing edge portion, and the distance from the central portion of the trailing edge portion to the trailing edge portion of the trailing point is defined as DB, by satisfying LB / LA = In the relationship between the starting point and the ending point of the DB / DA relationship, the wing portion is cut in a straight line to define the second cross-sectional shape of the wing portion. If the position of the outer peripheral edge portion connecting the second cross-sectional shape of the wing portion and the The line segment at the position of the trailing edge portion is defined as a second chord line, and is drawn from the second cross-sectional shape of the wing portion away from the positive pressure side in the direction of the central axis, and is drawn from the second chord line. Parallel And a second reference line is defined, a third convex surface portion having a surface shape curved in a convex shape in the direction of the central axis is formed on the negative pressure surface side of the second cross-sectional shape of the wing portion; and A third concave surface portion is located between the third convex surface portion and the outer peripheral edge portion, and has a surface shape bent into a concave shape in the direction of the central axis; and the third convex surface portion has a third top portion, which is The distance from the second reference line to the third convex surface portion is gradually changed from a gradually increasing portion to a gradually decreasing portion in the direction of the second chord line from the outer peripheral edge portion toward the rear edge portion; The top portion is formed at a position where the distance in the direction of the second chord line from the outer peripheral edge portion to the third top portion is 1/3 or less of the total length of the second chord line. The propeller fan according to claim 4, wherein the third concave surface portion has a third bottom portion, which is connected to the second chord line direction from the outer peripheral edge portion side toward the rear edge portion side, and the second reference The distance from the line to the third concave surface portion is gradually reduced to an increasing portion; and the distance between the third bottom portion formed in the direction of the second chord line from the outer peripheral edge portion to the third bottom portion is the second portion The chord line is at least 5% to 15% of the total length. The propeller fan according to claim 4, wherein a fourth concave surface portion is formed on the positive pressure surface side of the second cross-sectional shape of the wing portion, and has a surface shape curved into a concave shape in the direction of the central axis; and A fourth convex surface portion is located between the fourth concave surface portion and the outer peripheral edge portion, and has a surface shape curved in a convex shape in the direction of the central axis; and the fourth concave surface portion has a fourth bottom portion, which is The distance from the second reference line to the fourth concave surface portion is gradually changed from an increasing portion to a decreasing portion in the direction of the second chord line from the outer peripheral edge side to the rear edge portion side; and the fourth The bottom portion is formed at a position where the distance in the direction of the second chord line from the outer peripheral edge portion to the fourth bottom portion is 1/3 or less of the total length of the second chord line. A propeller fan includes: a rotation shaft portion that rotates around an imaginary center axis; and a wing portion that has a shape that extends from the rotation shaft portion side toward the outside in the direction of the rotation radius, and is rotated positively by rotation. The back surface forms a positive pressure surface and a negative pressure surface, respectively; and the wing portion includes: a front end portion of the wing, which is located at the forefront of the rotation direction; a front edge portion, which forms the front edge of the wing portion in the rotation direction; a rear edge portion, which forms The trailing edge of the wing portion in the rotation direction; and an outer peripheral edge portion connecting the front end portion of the wing and the outer end of the trailing edge portion to form the outer peripheral edge of the wing portion in the radius of rotation direction; It is defined as LA, a starting point is defined at an arbitrary position on the outer peripheral edge portion, a distance from the front end portion of the wing to the outer peripheral edge portion of the starting point is specified as LB, and a central portion of the trailing edge portion to the rear edge portion is defined. The distance on the trailing edge portion of the outer end is defined as DA, and the distance between the central portion of the trailing edge portion and the outer end of the trailing edge portion is arbitrary on the trailing edge portion. Set a predetermined end point, and set the distance from the central portion of the trailing edge portion to the trailing edge portion of the end point as DB, by passing the above starting point and the ending point by satisfying the relationship of LB / LA = DB / DA The wing portion is cut straight to define the cross-sectional shape of the wing portion. If a line segment connecting the position of the outer peripheral edge portion and the position of the trailing edge portion of the cross-sectional shape of the wing portion is defined as a chord line, and Draw a straight line parallel to the chord line from the cross-sectional shape of the wing portion toward the side away from the positive pressure surface in the central axis direction to define a reference line, and then the negative pressure surface of the cross-sectional shape of the wing portion Formed on the side are a convex surface portion having a surface shape curved in a convex shape in the direction of the central axis, and a concave surface portion located between the convex surface portion and the outer peripheral edge portion and having a concave shape in the central axis direction. And the convex portion has: a top portion, which is in the chord line direction from the outer peripheral edge portion side to the rear edge portion side, the reference line to the convex portion Increasing distance from the transition portion to the portion of decreasing; and said top tether is formed in the outer peripheral edge portion to the entire length of the chord line of the above position of 1/3 of the distance direction of the chord line of said top. A propeller fan includes: a rotation shaft portion that rotates around an imaginary center axis; and a wing portion that has a shape that extends from the rotation shaft portion side toward the outside in the direction of the rotation radius, and is rotated positively by rotation. The back surface forms a positive pressure surface and a negative pressure surface, respectively; and the wing portion includes: a front end portion of the wing, which is located at the forefront of the rotation direction; a front edge portion, which forms the front edge of the wing portion in the rotation direction; It forms the trailing edge of the wing portion in the rotation direction; and an outer peripheral edge portion that connects the front end portion of the wing and the outer end of the trailing edge portion to form the outer peripheral edge of the wing portion in the radial direction of rotation; and if it passes through the outer periphery The wing portion is cut at an arbitrary position on the edge and the plane of the central axis to define the cross-sectional shape of the wing portion, and a portion between the wing portion and the rotary shaft portion of the wing portion in the cross-sectional shape is defined as a connection The line segment connecting the position of the outer peripheral edge portion of the cross-sectional shape of the wing portion and the position of the connecting portion is defined as a chord line and is on the central axis. A straight line parallel to the chord line is drawn upward from the cross-sectional shape of the wing portion to a position away from the positive pressure surface side, and a reference line is defined. Then, the negative pressure surface side of the cross-sectional shape of the wing portion is formed. : A convex surface portion having a surface shape curved in a convex shape in the direction of the central axis; and a concave surface portion located between the convex surface portion and the outer peripheral edge portion and having a surface curved in a concave shape in the central axis direction Shape; and the convex portion has: a top portion, which is in the chord line direction as the distance from the reference line to the convex portion changes from increasing to decreasing gradually from the outer peripheral edge side to the trailing edge portion side. And the top portion is formed at a position where the distance in the chord line direction from the outer peripheral edge portion to the top portion is less than 1/3 of the full length of the chord line. A fluid conveying device having a propeller fan as claimed in claim 1 or 2.