JP3304243B2 - Blast impeller - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a blower used for a ventilation blower, an air conditioner, or the like, and more particularly to a blower capable of reducing noise generated at a high static pressure and increasing efficiency. Regarding the impeller.

[0002]

2. Description of the Related Art In recent years, a ventilation impeller used for ventilation and air conditioning equipment and air conditioning equipment used in living and non-living spaces is a medium-to-low static pressure ventilating blower that does not require much static pressure. In addition, low-noise axial-flow impellers have been designed by various design techniques used as air conditioners. However, expanding the range of use of equipment performance and further expanding the range of applications are required, and ventilation and air conditioning equipment and air conditioning equipment with high static pressure and large air volume have been required. However, there is a problem in that there is an unstable region at high static pressure, the noise rises sharply, and the efficiency also falls sharply. Therefore, in the past, a mixed flow blow impeller has been used as a blow impeller having a higher static pressure than an axial flow impeller, but at a low static pressure, there is a problem that noise increases and efficiency is low, It could not meet all the needs of society that wanted to use low static pressure to high static pressure with large air volume and low noise. Therefore, there is a need for a blower impeller that has no instability during operation, has low noise, has a wide range of use in performance, is more efficient and consumes less power, and a design method and development of the blower impeller are required. .

Conventionally, this type of blower impeller generally has a configuration shown in FIGS. Hereinafter, the configuration will be described with reference to the drawings.

As shown in FIG. 1, a blade 1 of an axial impeller 101 is provided.
02 in the axial projection of the rotating shaft 103,
The blade 102 has a shape that is advanced in the rotation direction 104 of the blade 102, and has a shape that is uniformly inclined to the suction side 105 in a projection view projected on a plane including the rotation axis 103. A free vortex that keeps the work from the inner peripheral portion 106 of the blade 102 to the outer peripheral portion 107 of the blade 102 constant.
02 is designed with a flow distribution of forced vortex that makes the attachment angle Cθ ′ from the inner peripheral portion 106 to the outer peripheral portion 107 substantially constant, and the center line 109 of the wing section 108 of the wing 102 has a substantially circular arc shape and the wing section 108 Is given by Q ′ = D ′ / L ′, and the chord length L ′ and the warp D ′ are given by Q ′ = D ′ / L ′.
7, the warp rate Q ′ of the blade inner peripheral portion 106 is larger than that of the blade inner peripheral portion 106, and the mounting angle Cθ ′ of the blade inner peripheral portion 106 is larger than the blade outer peripheral portion 107 or the mounting angle Cθ ′ is The configuration is substantially constant from the portion 106 to the blade outer peripheral portion 107.

In the above configuration, a very large air flow and a high static pressure are required to reduce the size of the equipment and expand the range of use of the performance of the equipment. Are advanced in the rotation direction, and the suction side 105
It is necessary to rotate the axial flow impeller 101 having a shape inclined at a high speed. However, when the rotation speed increases, the relative speed w1 at the blade inlet increases, and the sound power E depends on the sound output E of the noise accompanied by the vortex emission by a sixth power.
Further, when the use range is expanded, since the lift range idealized in the design of the wing 102 becomes larger than the use range designed before and after the angle of attack 113 at which the minimum lift ratio is minimum, the angle of attack 113 is larger than a certain limit. That is, when the lift Cl reaches a maximum value and the angle of attack 113 further increases, the drag C R rather decreases, and a phenomenon in which the drag Cd rapidly increases occurs. This is because the boundary layer 114 along the upper surface of the wing separates at a large angle of attack 113, promotes the turbulent flow 110, and a phenomenon called stall occurs. At this time, first due to the stall near the bucket tip 111, the bucket tip 11
A backflow 112 first occurs on the suction side 105 of one. When the rotor blade tip 111 stalls, the turning angle of the relative flow decreases, but the axial flow speed decreases, so the outflow turning speed of the absolute flow increases. Therefore, as the backflow 112 spreads, the pressure near the discharge-side orifice increases, the backflow 112 develops near the suction-side tip, the flow is pushed to the hub side, and the axial flow velocity ratio on the hub side increases, so that the blade root However, the centrifugal effect does not work, so that the discharge pressure of the blower decreases as the flow rate decreases. When the backflow 112 on the suction side 105 spreads, the fluid in the inter-blade flow path pushed down to the hub side 115 causes the orifice side 116 to flow due to the action of centrifugal force.
, The axial velocity near the blade root begins to decrease,
A backflow 118 appears on the discharge side, and a flow 117 rises from the hub side 115 to the orifice side 116, and the discharge pressure increases. Such a phenomenon is called a surging phenomenon, and has caused the blower impeller 101 to become unstable. Also, after the occurrence of the surging phenomenon, there is a problem that the noise rapidly increases and the efficiency is low.

[0006]

In such a conventional blower impeller, when obtaining high static pressure and low noise by miniaturization, the noise rise due to high rotation of the moving blade is very large, and the range of use is large. However, there is a problem that the noise rises sharply and the efficiency is low due to an increase in the size, and there is a problem that a blade design method for solving all these problems has not been established.

SUMMARY OF THE INVENTION The present invention solves the above-mentioned problems, and it is possible to suppress an increase in noise due to a high rotation speed of a moving blade in order to obtain a high static pressure and a large air flow with a small size. A first object is to provide an established blower impeller.

A second object of the present invention is to provide a blower impeller capable of minimizing the occurrence of a surging phenomenon peculiar to an axial blower and expanding its use range, and having established a design method for the same.

A third object is to increase the static closing pressure at the same rotational speed.

[0010]

According to the present invention, there is provided a blower impeller for achieving the first and second objects.
Means comprises a plurality of moving blades on the outer periphery of the hub, and a motor for supporting the moving blades on a rotating shaft is provided.The shape of the moving blade is projected in the axial direction of the rotating shaft. The rotation axis is defined as the origin O, the point at which the hub inner blade chord projection line at the contact portion between the hub and the rotor blade is bisected is defined as the blade inner chord projection center point Pb, and the blade outer circumference of the rotor blade is A point dividing the chord projection line into two equal parts is defined as a blade outer periphery chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn. An intersection point where the circle intersects in the projection of the rotor blade is described. And the point at which the arc shown by the radius R is bisected as an arbitrary cross-section chord projection center point Pr, and in the projection view projected on a plane including the rotation axis, the blade inner chord projection center point Pb
And a straight line P connecting the wing outer circumference chord projection center point Pt, a fluid suction side from the straight line P is defined as a positive direction, and a fluid discharge side on the discharge side is defined as a negative direction. The arbitrary cross-section chord projection in which the point Pr is in the positive direction near the wing inner chord projection center point Pb, intersects the straight line P at an arbitrary position, and becomes a negative direction near the wing outer chord projection center point Pt. The locus of the center point Pr is S-shaped , or
A gauge passing on a straight line P near the wing outer peripheral chord projection center point Pt.
It is configured to draw a trace .

Further, in order to achieve the first object and the second object, the second means connects the origin O of the rotation axis and the projection center point Pb of the blade inner circumference to the structure of the first means. X for line segment
b, assuming that a line segment connecting the origin O and the blade inner chord projection center point Pt is Xt, when an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is a rotation direction of the moving blade. Is in the range of 30 ° to 60 °, and Aθ is larger than Aθt, where Aθ is an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb. Take a small value and set the projection center point P of the wing inner circumference chord
Assuming that a plane passing through b and perpendicular to the rotation axis is a reference plane A,
When the distance from the reference plane A to the arbitrary cross-section chord projection center point Pr is K, the radial distribution of K is Rb <R <
In the range of 0.46Rt, 0 <K <0.125Rt, and in the range of 0.46Rt <R <0.70Rt,
0.12Rt <K <0.17Rt, and 0.7
In the range of 0Rt <R <Rt, 0.16Rt <K <0.
Taking a range of 34 Rt, (Rt: blade outer radius, Rb:
A blade cross section formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O and cutting the cross section two-dimensionally, and the center line in the blade cross section is substantially arc-shaped. The chord length L and the warp D of the wing section are given by
= D / L, the outer peripheral warpage ratio Qt in the blade cross section of the outer peripheral portion of the blade takes a value in the range of 0.05 to 0.09, and the inner peripheral warp ratio Qt in the blade inner peripheral portion of the blade cross section. Is 0.0
The value is in the range of 3 to 0.06, and the warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion.

In order to achieve the first object and the second object, the third means connects the origin O of the rotation axis and the projection center point Pb of the blade inner circumference to the structure of the first means. X for line segment
b, assuming that a line segment connecting the origin O and the blade inner chord projection center point Pt is Xt, when an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is a rotation direction of the moving blade. Is in the range of 30 ° to 60 °, and Aθ is larger than Aθt, where Aθ is an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb. Take a small value and set the projection center point P of the wing inner circumference chord
Assuming that a plane passing through b and perpendicular to the rotation axis is a reference plane A,
When the distance from the reference plane A to the arbitrary cross-section chord projection center point Pr is K, the radial distribution of K is Rb <R <
In the range of 0.46Rt, 0 <K <0.125Rt, and in the range of 0.46Rt <R <0.70Rt,
0.12Rt <K <0.17Rt, and 0.7
In the range of 0Rt <R <Rt, 0.16Rt <K <0.
Taking a range of 34 Rt, (Rt: blade outer radius, Rb:
Blade inner circumference radius) and a blade section formed by cutting the cylindrical surface of the arbitrary radius R centered on the origin O and expanding the cross section two-dimensionally, perpendicular to the chord and the rotation axis. The angle formed by a straight line passing through the leading edge of the wing section and the cascade line is referred to as a mounting angle Cθ, and the outer peripheral mounting angle Cθt in the wing cross section of the outer peripheral portion of the wing is in a range of 20 ° to 35 °. The inner peripheral portion mounting angle Cθb in the blade cross section of the inner peripheral portion of the blade is in a range of 30 ° to 40 °.

In order to achieve the first object and the second object, the fourth means comprises a cylindrical surface having an arbitrary radius R centered on the origin O of the rotating shaft. In the blade cross section formed by expanding the cross section two-dimensionally, the center line of the blade in the blade cross section has a substantially arc shape, and the chord length Q of the blade cross section and the warp D are Q = D / L, the outer peripheral portion warpage rate Qt in the blade cross section of the outer peripheral portion of the blade is 0.0
The value in the range of 5 to 0.09 takes a value in the range of 0.03 to 0.06 in the inner peripheral portion warp rate Qt in the blade cross section of the inner peripheral portion of the wing, and the curvature of the inner peripheral portion is higher than the outer peripheral portion. The configuration is such that the rate Q is small.

In order to achieve the first object and the second object, the fifth means may include a cylinder having the arbitrary radius R centered on the origin O of the rotating shaft. A wing cross section formed by expanding the cross section in a two-dimensional manner, and a cascade line L that is a straight line that is perpendicular to the rotation axis and passes through the wing leading edge of the wing. When the distance between the edge and the leading edge of the wing adjacent to the wing is a pitch T, the chord ratio S is S =
L / T, and the chord ratio S is in the range of 0.6 to 1.0.

In order to achieve the first object and the second object, the sixth means comprises the second, third, fourth and fifth means.
In the means, the center axis is the same as the rotation axis of the moving blade having the outer diameter Dt, and the cross section on the suction port side is the radius Or and the center of the radius Or on a plane perpendicular to the center axis indicating the minimum inner diameter Dr. An arc-shaped ring extending to the suction port side by an angle Oθ, having an orifice integrally formed with a duct part having a straight section and a length of Lr, and the radius Or being 0.15 Dt.
0.4Dt, and the minimum inner diameter Dr is 1.02Dt.
1.03 Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.05 Dt to 0.10 Dt.

In order to achieve the first object and the second object, the seventh means comprises the second, third, fourth and fifth means.
Means, the center axis is the same as the rotation axis of the rotor blade having an outer diameter Dt, and the inlet and outlet sections have a radius Or.
The radius O on a plane perpendicular to the central axis indicating the minimum inner diameter Dr
r is an arc-shaped ring extending from the center to the suction port side by an angle Oθ, having a straight cross section, and having an orifice formed integrally with a duct portion having a length of Lr and having the radius O
r is 0.05 Dt to 0.2 Dt, and the minimum inner diameter D
r is 1.02 Dt to 1.03 Dt, and the angle Oθ
Is 30 ° to 90 °, and the length Lr is 0.01 Dt.
０．０0.02 Dt.

In order to achieve the first and second objects, an eighth means connects the origin O of the rotation axis and the projection center point Pb of the wing inner circumference to the structure of the first means. X for line segment
b, assuming that a line segment connecting the origin O and the blade inner chord projection center point Pt is Xt, when an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is the rotation of the moving blade. If the direction is a positive direction and it is in the range of 30 ° to 60 °, and if an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb is Aθ, Aθ is Aθ
Assuming that a plane that takes a value smaller than t and passes through the wing inner circumference chord projection center point Pb and is orthogonal to the rotation axis is a reference plane A, the arbitrary cross-section chord projection center point Pr from the reference plane A When the distance to K is K, the radial distribution of K is Rb
0 <K <0.14Rt in the range of <R <0.46Rt, and 0.13Rt <K <0.17Rt in the range of 0.46Rt <R <0.70Rt;
In the range of 0.70Rt <R <Rt, 0.16Rt <K
Taking a range of <0.265 Rt, (Rt: outer radius of blade, Rb: inner radius of blade), and cut at a cylindrical surface of an arbitrary radius R centered on the origin O, the cross section is two-dimensional. In the wing section that can be developed, the center line of the wing section in the wing section has a substantially arc shape, the chord length L and the sleigh D of the wing section, the warp rate Q is given by Q = D / L, and the wing outer periphery The outer peripheral warpage rate Qt in the blade cross section of the portion takes a value in the range of 0.05 to 0.09, and the inner peripheral warp rate Qt in the blade cross section of the inner peripheral part of the blade ranges from 0.03 to 0.06. And the warp rate Q of the inner peripheral portion is smaller than that of the outer peripheral portion.

In order to achieve the first and second objects, the ninth means connects the origin O of the rotation axis and the projection center point Pb of the blade inner circumference to the structure of the first means. X for line segment
b, assuming that a line segment connecting the origin O and the blade inner chord projection center point Pt is Xt, when an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is a rotation direction of the moving blade. Is in the range of 30 ° to 60 °, where Aθ is Aθ, where Aθ is an arbitrary angle formed by a line segment connecting the origin O and the center point Pr of arbitrary cross-section chord projection and the line segment Xb.
Assuming that a plane that takes a value smaller than t and passes through the wing inner circumference chord projection center point Pb and is orthogonal to the rotation axis is a reference plane A, the arbitrary cross-section chord projection center point Pr from the reference plane A When the distance to K is K, the radial distribution of K is Rb
0 <K <0.14Rt in the range of <R <0.46Rt, and 0.13Rt <K <0.17Rt in the range of 0.46Rt <R <0.70Rt;
In the range of 0.70Rt <R <Rt, 0.16Rt <K
Taking a range of <0.265 Rt, (Rt: outer circumference radius of the blade, Rb: inner circumference radius of the blade), and cutting at a cylindrical surface of the arbitrary radius R centered on the origin O, the cross section is two-dimensional. The angle formed between the chord and a cascade line, which is a straight line perpendicular to the rotation axis and passing through the blade leading edge of the wing cross section, is referred to as an attachment angle Cθ, and the wing cross section of the outer periphery of the wing is formed. The outer peripheral portion mounting angle Cθt is in the range of 20 ° to 35 °, the inner peripheral portion mounting angle Cθb in the blade cross section of the inner peripheral portion of the blade is in the range of 30 ° to 40 °, and Mounting angle Cθ
Is increased.

In order to achieve the first object and the second object, the tenth means comprises the configuration of the ninth means,
A wing section formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O of the rotation axis and expanding the section in two dimensions, the center line of the wing section in the wing section has a substantially arc shape. With the chord length L and the sled D of the cross section, the sled rate Q is given by Q = D / L,
The outer peripheral portion warpage rate Qt in the blade cross section of the outer peripheral portion of the blade is 0.
The value of the inner peripheral portion warp Qt in the blade cross section of the inner peripheral portion of the blade takes a value in the range of 0.03 to 0.06. The configuration is such that the rate Q is small.

In order to achieve the first object and the second object, the eleventh means includes a cylindrical surface having an arbitrary radius R centered on the origin O of the rotating shaft. And a chord length L in a wing cross section formed by expanding the cross section two-dimensionally, and the wing leading edge of the wing on a cascade line that is a straight line perpendicular to the rotation axis and passing through the wing leading edge of the wing. When the distance between the wing and the leading edge of the adjacent wing is pitch T, the chord ratio S is S
= L / T, and the chord ratio S is in the range of 0.6 to 1.0.

In order to achieve the first object and the second object, a twelfth means is provided in the eighth, ninth, tenth or eleventh means, wherein a moving blade having a central axis and an outer diameter Dt is provided. An arcuate ring extending from the center of a radius Or on a plane perpendicular to the central axis showing the minimum diameter Dr and having a cross section on the suction port side extending from the center of the suction port side to the suction port side by the angle Oθ. And has an orifice integrally formed with a duct portion having a straight section and a length of Lr, and the radius Or is 0.15.
Dt to 0.4 Dt, and the minimum inner diameter Dr is 1.02.
Dt to 1.03 Dt, and the angle Oθ is 30 ° to 9
0 °, and the length Lr is 0.05 Dt to 0.10 D
t.

In order to achieve the first object and the second object, a thirteenth means is provided in the eighth, ninth, tenth or eleventh means, in which An arc-shaped circle extending from the center of a radius Or on a plane perpendicular to the center axis showing the minimum inner diameter Dr and having a cross section on the suction port and the outlet side extending from the center of the suction port and the outlet side by an angle Oθ toward the suction port with the same rotation axis as the blade. An orifice formed by sandwiching a duct section having a length of Lr and having a straight section, the radius Or being 0.05 Dt to 0.2 Dt, and the minimum inner diameter Dr being 1.02 Dt. 1.03 Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.0
The configuration is 1Dt to 0.02Dt.

In order to achieve the first, second and third objects, a fourteenth means comprises a motor having a plurality of moving blades on the outer periphery of a hub and supporting the moving blades on a rotating shaft. The shape of the bucket blade is projected on the plane perpendicular to the rotation axis when the bucket blade is projected in the axial direction of the rotation axis. The point at which the projection line of the blade inner circumference chord at the contact portion between the hub and the rotor blade is bisected is the blade inner circumference chord projection center point Pb,
A point that bisects the blade outer peripheral chord projection line of the rotor blade is set as a blade outer peripheral chord projection center point Pt, and, in the projection, a circle having an arbitrary radius R centered on the origin O is drawn, The intersection point where the circle intersects in the projection of the bucket blade and the radius R
In the projection view projected on a plane including the rotation axis, a point at which the circular arc shown in FIG.
Considering a straight line P connecting the blade outer peripheral chord center point Pt to a blade on the fluid suction side of the straight line P and a negative direction on the discharge side, The chord projection center point Pr is the wing inner circumference chord projection center point Pb.
In the vicinity, the trajectory is in the positive direction, intersects the straight line P at an arbitrary position, and draws a locus passing on the straight line P near the wing outer peripheral chord projection center point Pt.

Further, in order to achieve the first, second and third objects, a fifteenth means is arranged such that the origin O of the rotation axis and the wing inner circumference chord projection center point Pb are added to the structure of the fourteenth means. Assuming that a connecting line segment is Xb and a connecting line between the origin O and the wing inner chord projection center point Pt is Xt, when an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is When the rotation direction of the blade is a positive direction and the angle is in the range of 30 ° to 60 °, and an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb is Aθ, Aθ
Takes a value smaller than Aθt, and assuming that a plane passing through the wing inner chord projection center point Pb and orthogonal to the rotation axis is a reference plane A, the arbitrary cross-section chord projection center point from the reference plane A When the distance to Pr is K, the radial distribution of K is 0 <K <0.12 in the range of Rb <R <0.46Rt.
5Rt, 0.46Rt <R <0.70Rt
Is in the range of 0.12Rt <K <0.17Rt, and in the range of 0.70Rt <R <Rt, it is 0.16Rt.
In the range of t <K <0.265Rt, (Rt: outer circumference radius of the blade, Rb: inner circumference radius of the blade), and cut at a cylindrical surface of an arbitrary radius R centered on the origin O, the cross section is cut. A blade section formed in a two-dimensional manner, the center line of the blade section is formed in an arc shape, the chord length L and the warp D of the blade section, and the warp rate Q is given by Q = D / L. Takes a value in the range of 0.05 to 0.09 in the cross section of the wing, and the warp ratio Qt of the inner periphery in the wing cross section of the inner periphery of the wing.
t takes a value in the range of 0.03 to 0.06, and the warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion.

In order to achieve the first, second, and third objects, the sixteenth means is characterized in that the configuration of the fourteenth means is such that the origin O of the rotation axis and the center point Pb of the wing inner circumference chord are projected. Assuming that a connecting line segment is Xb and a connecting line between the origin O and the wing inner chord projection center point Pt is Xt, when an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is When the rotation direction of the blade is a positive direction and the angle is in the range of 30 ° to 60 °, and an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb is Aθ, Aθ
Takes a value smaller than Aθt, and assuming that a plane passing through the wing inner chord projection center point Pb and orthogonal to the rotation axis is a reference plane A, the arbitrary cross-section chord projection center point from the reference plane A When the distance to Pr is K, the radial distribution of K is 0 <K <0.12 in the range of Rb <R <0.46Rt.
5Rt, 0.46Rt <R <0.70Rt
Is in the range of 0.12Rt <K <0.17Rt, and in the range of 0.70Rt <R <Rt, it is 0.16Rt.
A section of t <K <0.265Rt is taken, (Rt: outer circumference radius of the blade, Rb: inner circumference radius of the blade), and cut at a cylindrical surface of the arbitrary radius R centered on the origin O, and a cross section is formed. In a blade section formed by expanding the blade in two dimensions, an angle formed between a chord and a row of cascade lines that is perpendicular to the rotation axis and passes through a leading edge of the blade section is defined as a mounting angle Cθ, The outer peripheral portion mounting angle Cθt in the wing cross section is in the range of 20 ° to 35 °,
The inner peripheral portion mounting angle Cθb in the blade cross section of the inner peripheral portion of the blade is 3
The angle is in the range of 0 ° to 40 °, and the warp rate Q of the inner peripheral portion is smaller than that of the outer peripheral portion.

In order to achieve the first, second, and third objects, the seventeenth means is characterized in that the sixteenth means comprises a cylinder having an arbitrary radius R centered on the origin O of the rotating shaft. A wing cross section that can be cut in planes and expanded in two dimensions
The center line of the wing section in the wing section is substantially arc-shaped, and the chord length L and the slewing D of the wing section are given by Q = D / L. Qt takes a value in the range of 0.05 to 0.09, and the inner peripheral portion warp rate Qt in the blade section of the inner peripheral portion of the blade is 0.03 to 0.06.
And the warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion.

In order to achieve the first, second, and third objects, the eighteenth means may have a configuration in which the seventeenth means is formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O. And the chord length L
And, on a cascade line that is perpendicular to the rotation axis and passes through the wing leading edge of the wing, when the distance between the wing leading edge of the wing and the wing leading edge of an adjacent wing is a pitch T, The string ratio S is S = L /
T, the string ratio S is in the range of 0.6 to 1.0.

In order to achieve the first, second, and third objects, the nineteenth means may be configured so that the fifteenth, sixteenth, seventeenth, or eighteenth means has a dynamic axis having an outer diameter Dt. The rotation axis of the blade is the same, and the cross section on the suction port side has a radius of Or.
The radius O on a plane perpendicular to the central axis indicating the minimum inner diameter Dr
r is an arc-shaped ring extending from the center to the suction port side by an angle Oθ, and has an orifice integrally formed with a duct portion having a straight cross section and a length of Lr.
15Dt to 0.4Dt, and the minimum inner diameter Dr is 1.Dt.
02Dt to 1.03Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.05Dt to 0.1Dt.
0Dt.

In order to achieve the first, second, and third objects, a twentieth means is characterized in that the fifteenth, sixteenth, seventeenth, or eighteenth means has a dynamic shaft having a central axis and an outer diameter Dt. A circular arc extending from the center of a radius Or on a plane perpendicular to the central axis indicating the minimum inner diameter Dr with a cross section on the suction port and the outlet side extending from the center of the suction port to the suction port side by the same angle as the rotation axis of the blade blade. It has an orifice that is annular, has a straight cross section, and is formed integrally with a duct portion with a length of Lr.
The radius Or is 0.05 Dt to 0.2 Dt, the minimum inner diameter Dr is 1.02 Dt to 1.03 Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.01 Dt to 0.01 Dt. 0.02Dt.

[0030]

DESCRIPTION OF THE PREFERRED EMBODIMENTS According to the first aspect of the present invention, a locus of a chord center point of a moving blade is designed so as to show an S-shape in a projection view projected on a plane including a rotation axis. As a result, it is possible to suppress the rise in noise due to the high rotation of the moving blades to obtain high static pressure and large air flow with miniaturization, and minimize the occurrence of surging phenomena peculiar to axial blowers. , The use range can be enlarged.

Further, the second, third, fourth, fifth, sixth, seventh, eighth,
According to the configuration of the ninth, tenth, twelfth, or thirteenth means, the locus of the chord center point of the moving blade is in a projected shape projected on a plane including the rotation axis in a shape advanced in the rotating direction of the moving blade. Is an S shape or a specified shape, and the warp rate of the inner peripheral portion is smaller than the outer peripheral portion, the mounting angle of the inner peripheral portion is larger than the outer peripheral portion, and the range of the chord ratio is specified, and the orifice shape is Since the blades are designed by specifying dimensions and optimizing the level of factors, the rise in noise due to high rotation of the blades to achieve high static pressure and large airflow with small size is suppressed. It is possible to minimize the occurrence of a surging phenomenon peculiar to an axial blower, and to enlarge the range of use.

Further, according to the structure of the fourteenth means, in the projection view projected on the plane including the rotation axis, it is designed in a shape that specifies the locus of the chord center point of the moving blade,
It is possible to suppress the rise of noise due to high rotation of the moving blade to obtain high static pressure and large air volume by miniaturization, minimize the occurrence of surging phenomenon peculiar to axial blowers, and widen the range of use And the static shutoff pressure can be increased at the same rotational speed.

Further, with the configuration of the fifteenth, fifteenth, sixteenth, eighteenth, nineteenth and twentieth means, the moving blade has a shape advanced in the rotating direction of the moving blade, and in the projection view projected on a plane including the rotation axis, A shape that specifies the locus of the chord center point of the wing blade.The warpage rate of the inner circumference is smaller than the outer circumference, the mounting angle of the inner circumference is larger than the outer circumference, and the range of the chord ratio is specified. The blades are designed by specifying the dimensions of the orifice shape and optimizing the level of the factors, and by increasing the rotation speed of the blades to obtain high static pressure and large air flow with miniaturization. It is possible to suppress the rise of noise,
Minimize the occurrence of surging phenomena peculiar to axial blowers,
The working range can be increased, and the static shutoff pressure can be increased at the same rotation speed.

[0034]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described below with reference to FIGS.
This will be described with reference to FIG. As shown in the figure, hub 2
A plurality of moving blades 1 are provided on the outer periphery of the motor, and there is a motor 4 that supports the moving blades 1 on a rotating shaft 3. The moving blades 1 are projected in the axial direction of the rotating shaft 3 in the shape of the moving blades 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, the point at which the hub 2 and the blade 1 are bisected at the contact point between the blade inner circumference projection line 5 is defined as the blade inner circumference projection center point Pb, and the blade outer circumference of the blade 1 The point at which the chord projection line 6 is bisected is defined as the blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. In the projection view projected on a plane including the rotation axis 3, there is an intersection 7 that intersects with each other, and a point bisecting the arc 8 indicated by the intersection 7 and the radius R is defined as an arbitrary cross-section chord projection center point Pr. Consider a straight line P connecting the wing inner chord projection center point Pb and the wing outer chord projection center point Pt. A straight line P on the fluid suction side 9 is defined as a positive direction, and a straight line on the discharge side 10 is defined as a negative direction. , The center point Pr of arbitrary cross-section chord projection is located near the center point Pb of wing inner chord projection. There is in the positive direction, the straight line P at any location
, The trajectory 11 of the arbitrary cross-section chord projection center point Pr shows an S shape in the negative direction near the blade outer chord projection center point Pt.

With the above structure, the moving blade 1 is rotated by the motor 4, and requires a very large air volume and a high static pressure in order to reduce the size of the equipment and expand the range of use of the equipment performance. In order to obtain pressure and large air volume, the blade 1
Need to rotate at high speed. When the rotation speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade inlet increases, and the sound output E depends on the sound output E of the noise accompanied with the vortex emission by a sixth power, so that the noise rapidly increases. Show a tendency to.

As shown in FIGS. 6 and 7, at low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so that there is no problem in the conventional design method. 9, the flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the moving blade 1 by the action of the centrifugal force on the fluid. In the design of the blower, sufficient design cannot be performed. Therefore, by giving a radial shape by making the chord center point an S-shape, the inclined section 23 from the inner peripheral side to the outer peripheral side of the moving blade 1 is provided. In this inclined cross section 23, the shape becomes a substantially arc shape in the past, and the angle difference between the theoretical outlet flow 24 and the actual outlet flow 25 becomes large, but as shown in FIG. As shown in FIG. Exit stream 25 actually flowing and 24
And the angle difference between them becomes smaller, the vortex shedding decreases, and the efficiency increases.

For this reason, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and noise can be reduced as compared with the conventional case. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge.

As described above, according to the blower of the first embodiment of the present invention, the locus 11 of the chord center point of the moving blade 1 shows an S-shape in the projected view projected on the plane including the rotating shaft 3. In order to obtain high static pressure and large air flow by miniaturization, it is possible to suppress the rise of noise due to the high rotation speed of the moving blade 1, and a surging phenomenon peculiar to the axial blower is generated. And the range of use can be increased.

Next, a second embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of a hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ takes a value smaller than Aθt, and in a projection projected on a plane including the rotation axis 3, consider a straight line P connecting the wing inner chord projection center point Pb and the wing outer chord center point Pt,
An object on the fluid suction side 9 with respect to the straight line P is defined as a positive direction,
If the thing on the discharge side 10 is in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction, intersects the straight line P at any place, and becomes negative in the vicinity of the blade outer chord projection center point Pt, Assuming that the locus 11 of the arbitrary cross-section chord projection center point Pr shows an S shape and that a plane passing through the wing inner circumference chord projection center point Pb and orthogonal to the rotation axis 3 is a reference plane A, the reference plane A The distance to the arbitrary cross-section chord projection center point Pr is K
, The radial distribution of K is Rb <R <0.46Rt
Is in the range of 0 <K <0.125Rt.
In the range of 46Rt <R <0.70Rt, 0.12Rt
<K <0.17Rt, and 0.70Rt <R <
In the range of Rt, a range of 0.16Rt <K <0.34Rt is taken, (Rt: blade outer radius, Rb: blade inner radius), and a cylindrical surface having an arbitrary radius R centered on the origin O. Wing section 13 formed by cutting and expanding the section in two dimensions
The center line of the wing section 13 is formed into an arc shape 8, and the chord length L and the skew D of the wing section 13 are given by Q = D / L. Rate Qt
Takes a value in the range of 0.05 to 0.09, and the inner peripheral portion warpage rate Qt in the wing section 13 of the inner peripheral portion of the wing is 0.03 to 0.09.
6, the warp rate Q of the inner peripheral part is smaller than that of the outer peripheral part.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

An extremely large air flow and a high static pressure are required to reduce the size of the equipment and expand the range of use of the equipment performance.
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases.

Therefore, at the time of high rotation, compared with the time of low rotation,
The fluid in the boundary layer on the wing surface causes a flow from the inner circumference to the outer circumference, and the boundary layer becomes thicker near the outer circumference,
Since the stall is likely to occur, the surging phenomenon is likely to occur. For this reason, in the conventional design method, the warp rate of the inner peripheral portion is set to be larger than that of the outer peripheral portion.

However, as shown in FIG. 9, by providing the advance angle in the rotation direction, the concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that the stall at the leading edge can be delayed. The surging phenomenon is less likely to occur, noise at low static pressure can be reduced, and the warpage rate of the outer peripheral part can be made larger than that of the inner peripheral part. Can be increased.

When the rotational speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade entrance increases, and the acoustic output E of the noise accompanied with the vortex emission depends on the sixth power multiplier. Noise tends to rise sharply.

At low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so that there is no problem in the conventional design method. However, at high static pressure, the backflow 21 on the suction side 9 expands and centrifugation to the fluid occurs. Since the flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the moving blade 1 by the action of the force, in the design of the axial flow fan which is not aware of the radial shape as in the related art,
Since sufficient design cannot be performed, the shape of the rotating blade 1 at the inclined cross section 23 from the inner circumferential side to the outer circumferential side is determined by giving the chord center point an S-shape to give a radial shape. Conventionally, the inclined cross section 23 has a substantially arc shape, and the angle difference between the theoretical outlet flow 24 and the actual outlet flow 25 is large. However, as shown in FIG. It shows an S-shape, and the angular difference between the theoretical outlet flow 24 and the actual outlet flow 25 becomes smaller, so that vortex shedding is reduced and efficiency is increased.

For this reason, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and noise can be reduced. Even when the rotation speed is the same as the conventional one, a higher static pressure and a larger air volume can be obtained, and the noise can be reduced by reducing the vortex emission. Here, the specific noise level Ks (dB (A)) is represented by Ks = SPL
Defined as −10 · Log ((Ps + Pv) 2 · Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure).

As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or more.
It can be seen that the specific noise level Ks is smaller when the angle is less than ゜, but the optimum value is 30 ° or more and 60 ° or less from the viewpoint of strength.

Further, as shown in FIG. 11, when the outer peripheral portion warp rate Qt is not less than 0.05 and not more than 0.09, it becomes optimum.
As shown in FIG.
Optimum at 6 or less.

As described above, according to the air blower of the second embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed so as to show an S shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to high rotation of the moving blade 1 to obtain a high static pressure and a large air volume by miniaturization, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and reduce a use range. Can be bigger.

Next, a third embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIGS. 10, 13 and 14.
The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blades 1 are projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ is smaller than Aθt, and the straight line P
In the vicinity of the wing outer peripheral chord projection center point Pt, the trajectory 11 of the arbitrary cross-section chord projection center point Pr shows an S shape and is projected on a plane including the rotation axis 3. Chord projection center point Pb and wing outer periphery center point Pt
Considering the straight line P connecting the straight line P to the one on the fluid suction side 9 as the positive direction and the one on the discharge side 10 in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction. And a plane passing through the wing inner circumference chord projection center point Pb and orthogonal to the rotation axis 3 is defined as a reference plane A, the distance from the reference plane A to the arbitrary cross-section chord projection center point Pr is K , K in the radial direction are in the range of 0 <K <0.125Rt in the range of Rb <R <0.46Rt, and 0.46R
In the range of t <R <0.70Rt, 0.12Rt <K <
0.17Rt, in the range of 0.70Rt <R <Rt, 0.16Rt <K <0.34Rt, (Rt: blade outer radius, Rb: blade inner radius), and A wing cross section 13 formed by cutting a cylindrical surface of an arbitrary radius R centered on the origin O and expanding the cross section in two dimensions, passing through the leading edge of the wing cross section 13 perpendicular to the chord and the rotation axis 3. An angle between the straight line and the cascade line 18 is referred to as a mounting angle Cθ, and an outer peripheral portion mounting angle Cθt in the blade cross section 13 of the outer peripheral portion of the blade is 20 ° to 35 °.
、, and the inner peripheral portion mounting angle Cθb in the wing section 13 of the inner peripheral portion of the blade is in the range of 30 ° to 40 °.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

An extremely large air flow and a high static pressure are required to reduce the size of the equipment and expand the range of use of the equipment performance.
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur.

However, as shown in FIG. 9, by providing the advancing angle in the rotational direction, the concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that the stall at the leading edge can be delayed. It is possible to make the surging phenomenon less likely to occur and reduce noise at low static pressure.

The outer peripheral mounting angle Cθt is equal to the inner peripheral mounting angle C.
By making it smaller than θb, the work load on the outer peripheral portion can be reduced, and stall at the leading edge can be delayed.

Further, when the rotation speed is increased, the peripheral speed u increases, and the relative speed w1 at the blade inlet increases, and depends on the sound power E of the noise accompanied by the vortex emission by a sixth power multiplier. Noise tends to rise sharply.

At low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so that there is no problem in the conventional design method. The flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the bucket blade 1 by the action of the force.
Since sufficient design cannot be performed, the shape of the rotating blade 1 at the inclined cross section 23 from the inner circumferential side to the outer circumferential side is determined by giving the chord center point an S-shape to give a radial shape. Conventionally, the inclined cross section 23 has a substantially arc shape, and the angle difference between the theoretical outlet flow 24 and the actual outlet flow 25 is large. However, as shown in FIG. It shows an S-shape, and the angular difference between the theoretical outlet flow 24 and the actual outlet flow 25 becomes smaller, so that vortex shedding is reduced and efficiency is increased.

For this reason, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and noise can be reduced. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge.

Here, the specific noise level Ks (dB (A))
Is calculated as Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or less. It can be seen that the specific noise level Ks is small, but the optimum value is 30 ° or more and 60 ° or less from the problem of strength.

Further, as shown in FIG. 13, the optimum is obtained when the outer peripheral portion mounting angle Cθt is between 20 ° and 35 °, and as shown in FIG. 14, the optimal when the inner peripheral portion mounting angle Cθb is between 30 ° and 40 °. Becomes

As described above, according to the air blower of the third embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed so as to show an S shape, the outer peripheral mounting angle Cθt is smaller than the inner peripheral mounting angle Cθb, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to high rotation of the moving blade 1 to obtain a high static pressure and a large air volume by miniaturization, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and reduce a use range. Can be bigger.

Next, a fourth embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blades 1 are projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ is smaller than Aθt, and the straight line P
In the vicinity of the wing outer peripheral chord projection center point Pt, the trajectory 11 of the arbitrary cross-section chord projection center point Pr shows an S shape and is projected on a plane including the rotation axis 3. Chord projection center point Pb and wing outer periphery center point Pt
Considering the straight line P connecting the straight line P to the one on the fluid suction side 9 as the positive direction and the one on the discharge side 10 in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction. And a plane passing through the wing inner circumference chord projection center point Pb and orthogonal to the rotation axis 3 is defined as a reference plane A, the distance from the reference plane A to the arbitrary cross-section chord projection center point Pr is K , K in the radial direction are in the range of 0 <K <0.125Rt in the range of Rb <R <0.46Rt, and 0.46R
In the range of t <R <0.70Rt, 0.12Rt <K <
0.17Rt, in the range of 0.70Rt <R <Rt, 0.16Rt <K <0.34Rt, (Rt: blade outer radius, Rb: blade inner radius), and A wing cross section 13 formed by cutting a cylindrical surface of an arbitrary radius R centered on the origin O and expanding the cross section in two dimensions, passing through the leading edge of the wing cross section 13 perpendicular to the chord and the rotation axis 3. An angle between the straight line and the cascade line 18 is referred to as a mounting angle Cθ, and an outer peripheral portion mounting angle Cθt in the blade cross section 13 of the outer peripheral portion of the blade is 20 ° to 35 °.
、, and the inner peripheral portion mounting angle Cθb in the wing section 13 of the inner peripheral portion of the blade is in the range of 30 ° to 40 °.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω 2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

An extremely large air flow and a high static pressure are required to reduce the size of the equipment and to expand the range of use of the performance of the equipment.
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur.

For this reason, in the conventional design method, the warp ratio of the inner peripheral portion is set larger than that of the outer peripheral portion. However, as shown in FIG. 9, by providing the advancing angle in the rotation direction, the concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that the stall at the leading edge can be delayed, and the surging phenomenon can be prevented. In addition to reducing the noise at low static pressure, it is possible to increase the amount of work in the outer peripheral part because the outer peripheral part can have a larger warp rate than the inner peripheral part. Can be.

The outer peripheral portion mounting angle Cθt is equal to the inner peripheral portion mounting angle C
By making it smaller than θb, the work load on the outer peripheral portion can be reduced, and stall at the leading edge can be delayed.

When the rotational speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade inlet increases, and the acoustic output E of the noise accompanied with the vortex emission depends on the sixth power multiplier. Noise tends to rise sharply.

At low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so there is no problem in the conventional design method. However, at high static pressure, the backflow 21 on the suction side 9 expands and centrifugation to the fluid occurs. Since the flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the moving blade 1 by the action of the force, in the design of the axial flow fan which is not aware of the radial shape as in the related art,
Since sufficient design cannot be performed, the shape of the rotating blade 1 at the inclined cross section 23 from the inner circumferential side to the outer circumferential side is determined by giving the chord center point an S-shape to give a radial shape. Conventionally, the inclined cross section 23 has a substantially arc shape, and the angle difference between the theoretical outlet flow 24 and the actual outlet flow 25 is large. However, as shown in FIG. It shows an S-shape, and the angular difference between the theoretical outlet flow 24 and the actual outlet flow 25 has a small relationship, reducing vortex shedding and increasing efficiency.

For this reason, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced as compared with the conventional case, and the noise can be reduced. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge.

Here, the specific noise level Ks (dB (A))
Is calculated as Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or more. The following shows that the specific noise level Ks is small. However, from the problem of strength, the optimum value is 30 ° or more and 60 ° or less.

Further, as shown in FIG. 11, when the outer peripheral portion warp rate Qt is 0.05 or more and 0.09 or less, it becomes optimum.
As shown in FIG.
Optimum at 6 or less.

Further, as shown in FIG. 13, the optimum is obtained when the outer peripheral portion mounting angle Cθt is 20 ° or more and 35 ° or less, and as shown in FIG. 14, the optimal when the inner peripheral portion mounting angle Cθb is 30 ° or more and 40 ° or less. Becomes

As described above, according to the blower of the fourth embodiment of the present invention, the moving blade 1 has a shape advanced in the rotational direction, and is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed in a shape showing an S-shape, the outer peripheral part warpage rate Qt is made larger than the inner peripheral part warp rate Qb, the level of each factor is optimized, and the outer peripheral part mounting angle Cθt is It is smaller than the inner peripheral part mounting angle Cθb, and by optimizing the levels of the respective factors, it is possible to suppress an increase in noise due to a high rotation speed of the moving blade 1 in order to obtain a high static pressure and a large air flow with a small size. It is possible to minimize the occurrence of a surging phenomenon peculiar to the axial blower, and to enlarge the use range.

Next, a fifth embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, the configuration of the fourth embodiment has a wing cross section 13 formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O and expanding the cross section two-dimensionally. Length L,
A blade 15 adjacent to the blade leading edge 17 of the blade 14 on a cascade line 18 which is a straight line perpendicular to the rotation axis 3 and passing through the blade leading edge 17 of the blade 14.
When the pitch T is the distance from the wing leading edge 19, the chord ratio S
Is given by S = L / T, and the chord ratio S is in the range of 0.6 to 1.0.

According to the above configuration, when the chord length L does not change, the pitch T is reduced, that is, the number of blades is increased, so that the flow can easily follow the blade even at high static pressure, and the thickness of the boundary layer is reduced. However, when the number of blades is increased, the number of sound sources generated from the blades increases, so that the noise tends to increase when the static pressure is low. Therefore, in order to reduce noise while maintaining a balance between low static pressure and high static pressure, the stringing ratio S is limited.

Further, as shown in FIG. 15, the optimum value is obtained when the chord ratio S is 0.6 or more and 1.0 or less. As described above, according to the blower of the fifth embodiment of the present invention, the moving blade 1 has a shape advanced in the rotational direction, and the chord of the moving blade 1 is shown in a projection view projected on a plane including the rotating shaft 3. Locus 1 of the center point
1 is designed to have an S-shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, the chord ratio S is limited, the level of each factor is optimized, and the outer peripheral part mounting angle Cθt Is smaller than the inner peripheral portion mounting angle Cθb, and the level of each factor is optimized to suppress an increase in noise due to high rotation of the moving blade 1 in order to obtain a high static pressure and a large air flow with a small size. It is possible to minimize the occurrence of a surging phenomenon peculiar to an axial blower, and to enlarge a use range.

Next, a sixth embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the drawing, the rotor blade 1 having a central axis having an outer diameter Dt is added to the structure of the second, third, fourth and fifth embodiments.
And an arc-shaped ring extending from the center of the radius Or on a plane perpendicular to the central axis showing the minimum inner diameter Dr and having a cross section on the suction port side with a radius Or and extending by an angle Oθ to the suction port side. The orifice has an orifice integrally formed with a duct portion having a straight section and a length of Lr, and has a radius Or of 0.15 Dt.
0.4Dt, and the minimum inner diameter Dr is 1.02Dt.
1.03 Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.05 Dt to 0.10 Dt.

With the above configuration, the cross section on the suction port side is an arc-shaped circular pipe, and the outlet side is a duct, so that the flow along the blade at low static pressure becomes parallel to the central axis, and The flow is also less turbulent and noise is reduced.

As described above, according to the blower of the sixth embodiment of the present invention, the moving blade 1 has a shape advanced in the rotating direction, and is shown in the projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed in a shape showing an S shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, the chord ratio S is limited, and the level of each factor is optimized. The outer peripheral portion mounting angle Cθt is made smaller than the inner peripheral portion mounting angle Cθb, and the shape of the orifice is specified, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to an increase in the rotation speed of the rotor blades 1 for obtaining a large air volume, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and increase the range of use.

Next, a seventh embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIGS. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the drawing, the rotor blade 1 having the outer diameter Dt as the center axis is added to the structure of the second, third, fourth and fifth embodiments.
And an arc-shaped circle extending from the center of a radius Or on a plane perpendicular to the central axis showing the minimum inner diameter Dr and having a cross section on the suction port and the outlet side with a radius Or toward the suction port side by an angle Oθ. It is a ring, has a straight orifice, and has an orifice integrally formed by sandwiching a duct portion having a length of Lr, the radius Or is 0.05 Dt to 0.2 Dt, and the minimum inner diameter Dr is
Is 1.02 Dt to 1.03 Dt, and the angle Oθ is 30
{90}, and the length Lr is 0.01 Dt to 0.02.
Dt.

With the above configuration, the cross sections of the suction port side and the outlet side are arc-shaped circular pipes and are joined by ducts, so that at high static pressure, the backflow 21 on the suction side 9 expands and the action of centrifugal force on the fluid is exerted. As a result, the blade is inclined in the direction from the inner peripheral side to the outer peripheral side of the bucket blade 1, so that the outlet side obstructs the outlet flow of the fluid in the form of a duct portion, and the cause of turbulence can be eliminated.

As described above, according to the air blower of the seventh embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed in a shape showing an S shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, the chord ratio S is limited, and the level of each factor is optimized. In order to obtain a high static pressure and a large air volume by downsizing by making the outer part mounting angle Cθt smaller than the inner part mounting angle Cθb, specifying the shape of the orifice, and optimizing the level of each factor. It is possible to suppress an increase in noise due to the high rotation of the moving blade 1, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and increase the range of use.

Next, an eighth embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ takes a value smaller than Aθt, and in a projection projected on a plane including the rotation axis 3, consider a straight line P connecting the wing inner chord projection center point Pb and the wing outer chord center point Pt,
An object on the fluid suction side 9 with respect to the straight line P is defined as a positive direction,
If the thing on the discharge side 10 is in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction, intersects the straight line P at any place, and becomes negative in the vicinity of the blade outer chord projection center point Pt, Assuming that the locus 11 of the arbitrary cross-section chord projection center point Pr shows an S shape and that a plane passing through the wing inner circumference chord projection center point Pb and orthogonal to the rotation axis 3 is a reference plane A, the reference plane A The distance to the arbitrary cross-section chord projection center point Pr is K
, The radial distribution of K is Rb <R <0.46Rt
Is in the range of 0 <K <0.14Rt, and 0.4
In the range of 6Rt <R <0.70Rt, 0.13Rt <
K <0.17Rt, 0.70Rt <R <R
In the range of t, a range of 0.16Rt <K <0.265Rt is taken, (Rt: outer circumference radius of the blade, Rb: inner circumference radius of the blade) and an arbitrary radius R centered on the origin O. Wing cross section 13 formed by cutting and expanding the cross section in two dimensions
The center line of the wing section 13 is formed into an arc shape 8, and the chord length L and the skew D of the wing section 13 are given by Q = D / L. Rate Qt
Takes a value in the range of 0.05 to 0.09, and the inner peripheral portion warpage rate Qt in the wing section 13 of the inner peripheral portion of the wing is 0.03 to 0.09.
6, the warp rate Q of the inner peripheral part is smaller than that of the outer peripheral part.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.
A very large air flow and a high static pressure are required in order to reduce the size of the device and to expand the range of use of the device performance. There is a need. As the rotational speed increases, the angular velocity ω increases, and at the same time, the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur. For this reason, in the conventional design method, the warp rate of the inner peripheral portion is set to be larger than that of the outer peripheral portion.

However, as shown in FIG. 9, by providing the advancing angle in the rotation direction, concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that stall at the leading edge can be delayed. The surging phenomenon is less likely to occur, noise at low static pressure can be reduced, and the warpage rate of the outer peripheral part can be made larger than that of the inner peripheral part. Can be increased.

When the rotational speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade inlet increases, and the acoustic output E of the noise accompanied by the vortex discharge depends on the sixth power multiplier. Noise tends to rise sharply.

At low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so there is no problem in the conventional design method. However, at high static pressure, the backflow 21 on the suction side 9 expands and centrifugation to the fluid occurs. Since the flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the bucket blade 1 by the action of the force, in the design of the axial flow blower which is not aware of the radial shape as in the related art,
Since sufficient design cannot be performed, the shape of the rotating blade 1 at the inclined cross section 23 from the inner circumferential side to the outer circumferential side is determined by giving the chord center point an S-shape to give a radial shape. Conventionally, the inclined cross section 23 has a substantially arc shape, and the angle difference between the theoretical outlet flow 24 and the actual outlet flow 25 is large. However, as shown in FIG. It shows an S-shape, and the angular difference between the theoretical outlet flow 24 and the actual outlet flow 25 becomes smaller, so that vortex shedding is reduced and efficiency is increased.

For this reason, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced as compared with the conventional case, and the noise can be reduced. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge.

By specifying the radial distribution of K, the shape becomes more consistent with the flow at high static pressure, and noise can be reduced.

Here, the specific noise level Ks (dB (A))
Is calculated as Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or more. The following shows that the specific noise level Ks is small. However, from the problem of strength, the optimum value is 30 ° or more and 60 ° or less.

Further, as shown in FIG. 11, when the outer peripheral portion warp rate Qt is 0.05 or more and 0.09 or less, it becomes optimum.
As shown in FIG.
Optimum at 6 or less.

As described above, according to the air blower of the eighth embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed so as to show an S shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to high rotation of the moving blade 1 to obtain a high static pressure and a large air volume by miniaturization, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and reduce a use range. Can be bigger.

Next, a ninth embodiment of the present invention will be described with reference to FIGS.
This will be described with reference to FIGS. 10, 13, and 14. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of a hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ is smaller than Aθt, and the straight line P
In the vicinity of the wing outer peripheral chord projection center point Pt, the trajectory 11 of the arbitrary cross-section chord projection center point Pr shows an S shape and is projected on a plane including the rotation axis 3. Chord projection center point Pb and wing outer periphery center point Pt
Considering the straight line P connecting the straight line P to the one on the fluid suction side 9 as the positive direction and the one on the discharge side 10 in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction. And a plane passing through the wing inner circumference chord projection center point Pb and orthogonal to the rotation axis 3 is defined as a reference plane A, the distance from the reference plane A to the arbitrary cross-section chord projection center point Pr is K , K in the radial direction range of 0 <K <0.14Rt in the range of Rb <R <0.46Rt, and 0.46Rt
In the range of <R <0.70Rt, 0.13Rt <K <
0.17Rt, in the range of 0.70Rt <R <Rt, 0.16Rt <K <0.265Rt, (Rt: blade outer radius, Rb: blade inner radius),
In addition, a wing cross section 13 formed by cutting a cylindrical surface of an arbitrary radius R centered on the origin O and expanding the cross section two-dimensionally, the wing leading edge of the wing cross section 13 being perpendicular to the chord and the rotation axis 3 The angle formed with the cascade line 18 which is a straight line passing through the blade is referred to as an attachment angle Cθ.
5 °, and the inner peripheral portion mounting angle Cθb in the blade section 13 of the inner peripheral portion of the blade is in the range of 30 ° to 40 °.

With the above configuration, the moving blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω 2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

An extremely large air flow and a high static pressure are required in order to reduce the size of the equipment and to expand the range of use of the equipment performance.
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur.

However, as shown in FIG. 9, by providing the advancing angle in the rotation direction, the concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that the stall at the leading edge can be delayed. It is possible to make the surging phenomenon less likely to occur and reduce noise at low static pressure.

The outer peripheral mounting angle Cθt is equal to the inner peripheral mounting angle C.
By making it smaller than θb, the work load on the outer peripheral portion can be reduced, and stall at the leading edge can be delayed.

When the rotational speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade entrance increases, and the sound output E of the noise accompanied by the vortex emission depends on the sixth power multiplier. Noise tends to rise sharply.

At low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so that there is no problem in the conventional design method. The flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the bucket blade 1 by the action of the force.
Since sufficient design cannot be performed, the shape of the rotating blade 1 at the inclined cross section 23 from the inner circumferential side to the outer circumferential side is determined by giving the chord center point an S-shape to give a radial shape. Conventionally, the inclined cross section 23 has a substantially arc shape, and the angle difference between the theoretical outlet flow 24 and the actual outlet flow 25 is large. However, as shown in FIG. It shows an S-shape, and the angular difference between the theoretical outlet flow 24 and the actual outlet flow 25 becomes smaller, so that vortex shedding is reduced and efficiency is increased.

Therefore, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and noise can be reduced as compared with the conventional case. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge.

Here, the specific noise level Ks (dB (A))
Is calculated as Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or less. It can be seen that the specific noise level Ks is small, but the optimum value is 30 ° or more and 60 ° or less from the problem of strength.

Further, as shown in FIG. 13, the optimum is obtained when the outer peripheral portion mounting angle Cθt is between 20 ° and 35 °, and as shown in FIG. 14, the optimal when the inner peripheral portion mounting angle Cθb is between 30 ° and 40 °. Becomes

As described above, according to the air blower of the ninth embodiment of the present invention, the blade 1 is advanced in the rotation direction, and the blade shown in the projection view projected on the plane including the rotating shaft 3 The trajectory 11 of the chord center point of 1 is designed in a shape showing an S shape, the outer peripheral portion mounting angle Cθt is smaller than the inner peripheral portion mounting angle Cθb, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to high rotation of the moving blade 1 to obtain a high static pressure and a large air volume by miniaturization, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and reduce a use range. Can be bigger.

Next, a tenth embodiment of the present invention will be described with reference to FIG.
This will be described with reference to FIGS. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view, and the circle is projected onto the moving blade 1. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xt be the line segment connecting the origin O and the wing inner chord projection center point Pt, and let Aθt be the angle formed by the line segment Xb and the line segment Xt.
Is in the range of 30 ° to 60 ° with the rotation direction of the moving blade 1 as a positive direction, and Aθ is an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and a line segment Xb. ,
Aθ takes a value smaller than Aθt, intersects the straight line P at an arbitrary place, becomes a negative direction near the blade outer peripheral chord projection center point Pt, and the trajectory 11 of the arbitrary cross-section chord projection center point Pr shows an S shape, and In the projection view projected on a plane including the rotation axis 3, the wing inner chord projection center point Pb and the wing outer circumference center point P
Considering a straight line P connecting t, the fluid suction side 9
Is in the positive direction, and the object on the discharge side 10 is in the negative direction. If the arbitrary cross-section chord projection center point Pr is in the positive direction, and passes through the wing inner chord projection center point Pb,
Assuming that a plane perpendicular to the rotation axis 3 is a reference plane A, the reference plane A
When the distance from to the arbitrary cross-section chord projection center point Pr is K, the radial distribution of K is 0 <K <0.14Rt in the range of Rb <R <0.46Rt, and 0.46Rt.
In the range of <R <0.70Rt, 0.13Rt <K <
In the range of 0.17Rt, and in the range of 0.70Rt <R <Rt, the range of 0.16Rt <K <0.265Rt is taken (Rt: blade outer radius, Rb: blade inner radius).
In addition, a wing cross section 13 formed by cutting a cylindrical surface of an arbitrary radius R centered on the origin O and expanding the cross section two-dimensionally, the wing leading edge of the wing cross section 13 being perpendicular to the chord and the rotation axis 3 The angle formed with the cascade line 18 which is a straight line passing through the blade is referred to as an attachment angle Cθ.
5 °, and the inner peripheral portion mounting angle Cθb in the blade section 13 of the inner peripheral portion of the blade is in the range of 30 ° to 40 °.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

A very large air flow and a high static pressure are required to reduce the size of the equipment and to expand the range of use of the equipment performance.
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur.

For this reason, in the conventional design method, the warp ratio of the inner peripheral portion is set larger than that of the outer peripheral portion.

However, as shown in FIG. 9, by providing the advance angle in the rotation direction, the concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that the stall at the leading edge can be delayed. The surging phenomenon is less likely to occur, noise at low static pressure can be reduced, and the warpage rate of the outer peripheral part can be made larger than that of the inner peripheral part. Can be increased.

The outer peripheral mounting angle Cθt is equal to the inner peripheral mounting angle C.
By making it smaller than θb, the work load on the outer peripheral portion can be reduced, and stall at the leading edge can be delayed.

When the rotational speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade inlet increases, and the acoustic output E of the noise accompanied by the vortex discharge depends on the sixth power multiplier. Noise tends to rise sharply.

At a low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so that there is no problem in the conventional design method. The flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the bucket blade 1 by the action of the force.
Since sufficient design cannot be performed, the shape of the rotating blade 1 at the inclined cross section 23 from the inner circumferential side to the outer circumferential side is determined by giving the chord center point an S-shape to give a radial shape. Conventionally, the inclined cross section 23 has a substantially arc shape, and the angle difference between the theoretical outlet flow 24 and the actual outlet flow 25 is large. However, as shown in FIG. It shows an S-shape, and the angular difference between the theoretical outlet flow 24 and the actual outlet flow 25 has a small relationship, reducing vortex shedding and increasing efficiency.

Therefore, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and the noise can be reduced. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge.

Here, the specific noise level Ks (dB (A))
Is calculated as Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or more. The following shows that the specific noise level Ks is small. However, from the problem of strength, the optimum value is 30 ° or more and 60 ° or less.

Further, as shown in FIG. 11, when the outer peripheral portion warp ratio Qt is not less than 0.05 and not more than 0.09, it becomes optimum.
As shown in FIG.
Optimum at 6 or less.

Further, as shown in FIG. 13, the outer peripheral portion mounting angle Cθt is optimum when it is 20 ° or more and 35 ° or less, and as shown in FIG. 14, the inner peripheral portion mounting angle Cθb is optimum when it is 30 ° or more and 40 ° or less. Becomes

As described above, according to the air blower of the tenth embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point 1 is designed so as to show an S shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, the level of each factor is optimized, and the outer peripheral part mounting angle Cθt is reduced. It is smaller than the inner peripheral part mounting angle Cθb, and by optimizing the levels of the respective factors, it is possible to suppress an increase in noise due to high rotation of the moving blade 1 in order to obtain a high static pressure and a large air flow with a small size. It is possible to minimize the occurrence of a surging phenomenon peculiar to the axial blower, and to enlarge the range of use.

Next, an eleventh embodiment of the present invention will be described with reference to FIG.
This will be described with reference to FIGS. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, the configuration of the tenth embodiment is
Cutting at a cylindrical surface with an arbitrary radius R centered on the origin O,
Chord length L in wing section 13 formed by expanding the section in two dimensions
And the distance between the wing leading edge 17 of the adjacent wing 15 and the wing leading edge 19 of the adjacent wing 15 on the cascade line 18 which is a straight line perpendicular to the rotation axis 3 and passing through the wing leading edge 17 of the wing 14. Then, the string ratio S is given by S = L / T, and the string ratio S is 0.6 to 1.0.
Configuration.

According to the above configuration, when the chord length L does not change, the pitch T is reduced, that is, by increasing the number of blades, the flow can easily follow the blade even at high static pressure, and the thickness of the boundary layer is reduced. However, when the number of blades is increased, the number of sound sources generated from the blades increases, so that the noise tends to increase when the static pressure is low.

Therefore, the string ratio S was limited in order to reduce noise while maintaining a balance between low static pressure and high static pressure.

Further, as shown in FIG. 15, the optimum value is obtained when the chord ratio S is 0.6 or more and 1.0 or less. As described above, according to the air blower of the eleventh embodiment of the present invention, the moving blade 1 has a shape advancing in the rotation direction, and the chord of the moving blade 1 is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the center point is designed in a shape showing an S shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, the chord ratio S is limited, and the level of each factor is optimized. The angle of attachment Cθt is smaller than the angle of attachment Cθb of the inner circumference, and by optimizing the levels of the respective factors, noise reduction due to high rotation of the moving blade 1 to obtain high static pressure and a large air flow with a small size is achieved. It is possible to suppress the rise, minimize the occurrence of the surging phenomenon peculiar to the axial blower, and enlarge the use range.

Next, a twelfth embodiment of the present invention will be described with reference to FIG.
This will be described with reference to FIGS. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, the eighth, ninth, tenth, and first
In the configuration of the first embodiment, the center axis is the same as the rotation axis 3 of the rotor blade 1 having the outer diameter Dt, and the cross section on the suction port side has a radius Or.
The radius O on a plane perpendicular to the central axis indicating the minimum inner diameter Dr
a circular orifice extending from the center of r to the suction port side by an angle Oθ, having an orifice integrally formed with a duct portion having a straight section and a length of Lr, and having a radius Or of 0.15.
Dt to 0.4 Dt, and the minimum inner diameter Dr is 1.02 Dt.
1.03 Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.05 Dt to 0.10 Dt.

With the above configuration, the cross section on the suction port side is an arc-shaped circular tube, and the outlet side is a duct section, so that the flow along the blade at the time of low static pressure becomes parallel to the central axis. The flow is also less turbulent and noise is reduced.

As described above, according to the air blower of the twelfth embodiment of the present invention, the moving blade 1 has a shape advanced in the rotational direction, and the moving blade 1 The trajectory 11 of the chord center point of 1 is designed so as to show an S shape, the outer peripheral warp ratio Qt is made larger than the inner peripheral warp ratio Qb, the chord ratio S is limited, and the level of each factor is optimized. The outer peripheral portion mounting angle Cθt is made smaller than the inner peripheral portion mounting angle Cθb, and the shape of the orifice is specified, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to an increase in the rotation speed of the rotor blades 1 for obtaining a large air volume, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and increase the range of use.

Next, a thirteenth embodiment of the present invention will be described with reference to FIG.
This will be described with reference to FIGS. The first
The same parts as those of the embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in FIG.
In the configuration of the first embodiment, the center axis is the same as the rotation axis 3 of the rotor blade 1 having the outer diameter Dt, and the cross section of the suction port and the outlet side is a radius Or, and is on a plane perpendicular to the center axis indicating the minimum inner diameter Dr. A circular arc extending from the center of the radius Or to the suction port side by an angle Oθ, having an orifice integrally formed by sandwiching a duct portion having a linear cross section and a length of Lr,
The radius Or is 0.05 Dt to 0.2 Dt, the minimum inner diameter Dr is 1.02 Dt to 1.03 Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.01 Dt to 0.
02Dt.

With the above structure, the cross sections of the suction port side and the outlet side are arc-shaped circular pipes and are joined by ducts, so that the backflow 21 on the suction side 9 expands at high static pressure and the centrifugal force acts on the fluid. As a result, the blade is inclined in the direction from the inner peripheral side to the outer peripheral side of the bucket blade 1, so that the outlet side obstructs the outlet flow of the fluid in the form of a duct portion, and the cause of turbulence can be eliminated.

As described above, according to the air blower of the thirteenth embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed so as to show an S shape, the outer peripheral warp ratio Qt is made larger than the inner peripheral warp ratio Qb, the chord ratio S is limited, and the level of each factor is optimized. To obtain a high static pressure and a large air flow by miniaturization by making the outer peripheral mounting angle Cθt smaller than the inner peripheral mounting angle Cθb, specifying the shape of the orifice, and optimizing the level of each factor. It is possible to suppress an increase in noise due to high rotation of the moving blade 1, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and increase the range of use.

Next, a fourteenth embodiment of the present invention will be described with reference to FIG.
This will be described with reference to FIGS. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, there is a motor 4 provided with a plurality of moving blades 1 on the outer periphery of a hub 2 and supporting the moving blades 1 on a rotating shaft 3. When the rotor blades 1 are projected in the axial direction, the rotation axis 3 is set to the origin O in a projection view projected on a plane perpendicular to the rotation axis 3.
A point at which the wing inner chord projection line 5 at the contact portion between the hub 2 and the moving blade 1 is bisected is a wing inner chord projection center point Pb,
A point at which the blade outer peripheral chord projection line 6 of the rotor blade 1 is bisected is a blade outer peripheral chord projection center point Pt.
, A circle having an arbitrary radius R is drawn, and there is an intersection 7 at which the circle intersects in the projection of the moving blade 1, and a point bisecting the intersection 8 and the arc 8 indicated by the radius R is an arbitrary cross-section blade. In the projection view which is set as the chord projection center point Pr and is projected on a plane including the rotation axis 3, the wing inner circumference chord projection center point Pb
Considering a straight line P connecting the airfoil outer chord and the center point Pt of the blade, the one on the suction side 9 of the fluid from the straight line P is in the positive direction, and the one on the discharge side 10 is in the negative direction. The projection center point Pr is in the positive direction near the wing inner chord projection center point Pb, intersects the straight line P at an arbitrary location, and draws a locus 11 passing on the straight line P near the wing outer chord projection center point Pt. .

With the above configuration, the moving blade 1 is rotated by the motor 4, and requires a very large air flow and a high static pressure in order to reduce the size of the equipment and expand the range of use of the equipment performance. In order to obtain pressure and large air flow, the blade 1
Need to rotate at high speed. When the rotation speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade inlet increases, and the sound output E depends on the sound output E of the noise accompanied with the vortex emission by a sixth power, so that the noise rapidly increases. Show a tendency to.

As shown in FIGS. 6 and 7, the fluid has a flow direction 20 parallel to the axial direction at a low static pressure, so that there is no problem in the conventional design method. 9, the flow direction 22 is inclined in the direction from the inner peripheral side to the outer peripheral side of the moving blade 1 by the action of centrifugal force on the fluid. In the design of the blower, since sufficient design cannot be performed, the shape in the inclined section 26 from the inner peripheral side to the outer peripheral side of the moving blade 1 is given by specifying the chord center point to give a radial shape. Can be determined, and this inclined section 26
Therefore, the conventional outlet flow 2 has a substantially circular arc shape.
7, the angle difference between the actual outlet flow 28 and the actual outlet flow 28 is large. However, as shown in FIG.
And the angle difference between them becomes smaller, the vortex shedding decreases, and the efficiency increases.

Therefore, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and noise can be reduced as compared with the conventional case. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge. Also,
When the inclined cross-section 26 performed in the first to thirteenth embodiments has an S-shaped cross section, the work speed increases because the circumferential speed of the absolute speed increases, and when the shutoff static pressure is the same rotation, To rise.

As described above, according to the air blower of the fourteenth embodiment of the present invention, the locus 11 of the chord center point of the moving blade 1 is designed to have a specific shape in the projection projected on the plane including the rotation axis 3. As a result, it is possible to suppress an increase in noise due to high rotation of the moving blade 1 to obtain a high static pressure and a large air flow by miniaturization, and to minimize occurrence of a surging phenomenon peculiar to an axial blower. And the range of use can be increased.

Next, a fifteenth embodiment of the present invention will be described with reference to FIG.
7, FIG. 9 to FIG. 12, and FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ takes a value smaller than Aθt, and in a projection projected on a plane including the rotation axis 3, consider a straight line P connecting the wing inner chord projection center point Pb and the wing outer chord center point Pt,
An object on the fluid suction side 9 with respect to the straight line P is defined as a positive direction,
If the thing on the discharge side 10 is in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction, intersects the straight line P at any place, and on the straight line P near the blade outer chord projection center point Pt. Assuming that a plane that shows the passing locus 11 and passes through the wing inner circumference chord projection center point Pb and is orthogonal to the rotation axis 3 is a reference plane A, the distance from the reference plane A to the arbitrary cross section chord projection center point Pr is K , The radial distribution of K is Rb <R <0.
In the range of 46Rt, 0 <K <0.125Rt, and in the range of 0.46Rt <R <0.70Rt, the range of 0.
In the range of 12Rt <K <0.17Rt, 0.70R
In the range of t <R <Rt, 0.16Rt <K <0.26
In the range of 5Rt, (Rt: blade outer radius, Rb: blade inner radius), and an arbitrary radius R centered on the origin O
The blade section 13 is formed by cutting the cylindrical surface of the blade section and expanding the cross section two-dimensionally. The center line of the blade section 13 is formed in an arc shape, the chord length L and the warp D of the blade section 13, and the warp rate Q is , Q
= D / L, the outer peripheral warpage rate Qt of the outer peripheral part of the blade section 13 takes a value in the range of 0.05 to 0.09, and the inner peripheral warp rate Qt of the inner peripheral part of the blade section 13 Is 0.0
The value is in the range of 3 to 0.06, and the warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

A very large air flow and a high static pressure are required to reduce the size of the equipment and expand the range of use of the equipment performance. To obtain a small, high static pressure and a large air flow, the moving blade 1
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur. For this reason, in the conventional design method, the warp rate of the inner peripheral portion is set to be larger than that of the outer peripheral portion.

However, as shown in FIG. 9, by providing the advancing angle in the rotation direction, concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that stall at the leading edge can be delayed. The surging phenomenon is less likely to occur, the noise at low static pressure can be reduced, and the warp rate of the outer circumference can be made larger than that of the inner circumference. Can be increased.

When the rotational speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade entrance increases, and the acoustic output E of the noise accompanied by the vortex discharge depends on the sixth power. Noise tends to rise sharply.

At a low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so that there is no problem in the conventional design method. However, at a high static pressure, the backflow 21 on the suction side 9 expands, and the fluid is centrifuged to the fluid. Since the flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the moving blade 1 by the action of the force, in the design of the axial flow fan which is not aware of the radial shape as in the related art,
Since a sufficient design cannot be performed, the shape in the inclined cross section 26 from the inner peripheral side to the outer peripheral side of the moving blade 1 can be determined by giving the radial shape by specifying the chord center point. Conventionally, the inclined cross section 26 has a substantially arc shape, and has a theoretical outlet flow 27 and an actual outlet flow 28.
18, the angle difference between the theoretical outlet flow 27 and the actual outlet flow 28 becomes smaller, and the vortex shedding decreases, as shown in FIG. Efficiency increases.

Therefore, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and noise can be reduced as compared with the conventional case. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge. Also,
When the inclined cross-section 26 performed in the first to thirteenth embodiments has an S-shaped cross section, the work speed increases because the circumferential speed of the absolute speed increases, and when the shutoff static pressure is the same rotation, To rise.

Here, the specific noise level Ks (dB (A))
Is calculated as Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or more. The following shows that the specific noise level Ks is small. However, from the problem of strength, the optimum value is 30 ° or more and 60 ° or less.

Further, as shown in FIG. 11, when the outer peripheral portion warp ratio Qt is not less than 0.05 and not more than 0.09, it becomes optimum.
As shown in FIG.
Optimum at 6 or less.

As described above, according to the air blower of the fifteenth embodiment of the present invention, the blade 1 is advanced in the rotational direction, and the blade shown in the projection view projected on the plane including the rotary shaft 3 The trajectory 11 of the chord center point of 1 is designed so as to show an S shape, the outer peripheral portion warp rate Qt is made larger than the inner peripheral portion warp rate Qb, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to high rotation of the moving blade 1 to obtain a high static pressure and a large air volume by miniaturization, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and reduce a use range. Can be bigger.

Next, a sixteenth embodiment of the present invention will be described with reference to FIG.
7, FIG. 9, FIG. 9, FIG. 10, FIG. 13, FIG. 14, and FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ takes a value smaller than Aθt, and in a projection view projected on a plane including the rotation axis 3, consider a straight line P connecting the wing inner chord projection center point Pb and the wing outer periphery center point Pt,
An object on the fluid suction side 9 with respect to the straight line P is defined as a positive direction,
If the thing on the discharge side 10 is in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction, intersects the straight line P at any place, and on the straight line P near the blade outer chord projection center point Pt. Assuming that a plane that shows the passing locus 11 and passes through the wing inner circumference chord projection center point Pb and is orthogonal to the rotation axis 3 is a reference plane A, the distance from the reference plane A to the arbitrary cross section chord projection center point Pr is K , The radial distribution of K is Rb <R <0.
In the range of 46Rt, 0 <K <0.125Rt, and in the range of 0.46Rt <R <0.70Rt, the range of 0.
In the range of 12Rt <K <0.17Rt, 0.70R
In the range of t <R <Rt, 0.16Rt <K <0.26
In the range of 5Rt, (Rt: blade outer radius, Rb: blade inner radius), and an arbitrary radius R centered on the origin O
A blade section 13 formed by cutting the cylindrical surface of the blade section and expanding the section in a two-dimensional manner. The blade section line 18 is a straight line perpendicular to the chord and the rotation axis 3 and passing through the leading edge of the blade section 13. Angle is mounting angle Cθ
And the outer peripheral part mounting angle Cθ in the wing cross section 13 of the outer peripheral part of the blade
t is in the range of 20 ° to 35 °, and the blade cross section 1
3, the inner peripheral part mounting angle Cθb is in the range of 30 ° to 40 °, and the warp rate Q of the inner peripheral part is smaller than that of the outer peripheral part.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

A very large air flow and a high static pressure are required to reduce the size of the equipment and to expand the range of use of the equipment performance.
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur.

However, as shown in FIG. 9, by providing the advancing angle in the rotational direction, the concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that the stall at the leading edge can be delayed. It is possible to make the surging phenomenon less likely to occur and reduce noise at low static pressure.

When the outer peripheral mounting angle Cθt is equal to the inner peripheral mounting angle C
By making it smaller than θb, the work load on the outer peripheral portion can be reduced, and stall at the leading edge can be delayed.

When the rotational speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade entrance increases, and the acoustic output E of the noise accompanied by the vortex emission depends on the sixth power multiplier. Noise tends to rise sharply.

At low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so there is no problem in the conventional design method. However, at high static pressure, the backflow 21 on the suction side 9 expands and centrifugation to the fluid occurs. Since the flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the moving blade 1 by the action of the force, in the design of the axial flow fan which is not aware of the radial shape as in the related art,
Since a sufficient design cannot be performed, the shape in the inclined cross section 26 from the inner peripheral side to the outer peripheral side of the moving blade 1 can be determined by giving the radial shape by specifying the chord center point. Conventionally, the inclined cross section 26 has a substantially arc shape, and has a theoretical outlet flow 27 and an actual outlet flow 28.
18, the angle difference between the theoretical outlet flow 27 and the actual outlet flow 28 becomes smaller, and the vortex shedding decreases, as shown in FIG. Efficiency increases.

Therefore, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced and noise can be reduced as compared with the conventional case. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge. Also,
When the inclined cross-section 26 performed in the first to thirteenth embodiments has an S-shaped cross section, the work speed increases because the circumferential speed of the absolute speed increases, and when the shutoff static pressure is the same rotation, To rise.

Here, the specific noise level Ks (dB (A))
Is calculated as Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or less. It can be seen that the specific noise level Ks is small, but the optimum value is 30 ° or more and 60 ° or less from the problem of strength.

Also, as shown in FIG. 13, the outer peripheral portion mounting angle Cθt is optimal when it is 20 ° or more and 35 ° or less, and as shown in FIG. 14, the inner peripheral portion mounting angle Cθb is optimal when it is 30 ° or more and 40 ° or less. Becomes

As described above, according to the air blower of the sixteenth embodiment of the present invention, the moving blade 1 is advanced in the rotation direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of 1 is designed in a shape showing an S shape, the outer peripheral portion mounting angle Cθt is smaller than the inner peripheral portion mounting angle Cθb, and the level of each factor is optimized.
It is possible to suppress an increase in noise due to high rotation of the moving blade 1 to obtain a high static pressure and a large air volume by miniaturization, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and reduce a use range. Can be bigger.

Next, a seventeenth embodiment of the present invention will be described with reference to FIG.
7, FIG. 9, FIG. 9 to FIG. 14, and FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ takes a value smaller than Aθt, and in a projection view projected on a plane including the rotation axis 3, consider a straight line P connecting the wing inner chord projection center point Pb and the wing outer periphery center point Pt,
An object on the fluid suction side 9 with respect to the straight line P is defined as a positive direction,
If the thing on the discharge side 10 is in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction, intersects the straight line P at any place, and on the straight line P near the blade outer chord projection center point Pt. Assuming that a plane that shows the passing locus 11 and passes through the wing inner circumference chord projection center point Pb and is orthogonal to the rotation axis 3 is a reference plane A, the distance from the reference plane A to the arbitrary cross section chord projection center point Pr is K , The radial distribution of K is Rb <R <0.
In the range of 46Rt, 0 <K <0.125Rt, and in the range of 0.46Rt <R <0.70Rt, the range of 0.
In the range of 12Rt <K <0.17Rt, 0.70R
In the range of t <R <Rt, 0.16Rt <K <0.26
In the range of 5Rt, (Rt: blade outer radius, Rb: blade inner radius), and an arbitrary radius R centered on the origin O
A wing cross section 13 formed by cutting the cylindrical surface of the wing and expanding the cross section two-dimensionally has a substantially arc-shaped center line in the wing cross section 13 of the wing. Q is
Q = D / L, and the outer peripheral part warpage rate Qt in the blade section 13 of the outer peripheral part of the blade takes a value in the range of 0.05 to 0.09,
The inner peripheral portion warpage rate Qt of the inner peripheral portion of the blade section 13 at the blade cross section 13 is set to 0.1.
Taking a value in the range of 03 to 0.06, the warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion, and the cross section is two-dimensionally cut by a cylindrical surface having an arbitrary radius R centered on the origin O. The wing cross section 13 formed by the
The angle formed between the blade line 18 and a straight line passing through the leading edge 17 of the blade is referred to as a mounting angle Cθ, and the mounting angle Cθt of the outer peripheral portion in the blade cross section 13 of the outer peripheral portion of the blade is in the range of 20 ° to 35 °. The inner peripheral part mounting angle Cθb in the peripheral blade section 13 is 30 ° to 4 °.
The angle is in the range of 0 °, and the mounting angle Cθ of the inner peripheral portion is larger than that of the outer peripheral portion.

With the above configuration, the rotor blade 1 is rotated by the motor 4, and the centrifugal force f is given by f = m · r · ω2 when the mass is m, the radius of rotation is r, and the angular velocity is ω.

An extremely large air flow and a high static pressure are required to reduce the size of the equipment and expand the range of use of the equipment performance. To obtain a small, high static pressure and a large air flow, the moving blade 1
Need to rotate at high speed. When the rotation speed increases, the angular velocity ω
And the centrifugal force f also increases. Therefore, the fluid in the boundary layer on the wing surface flows from the inner circumference to the outer circumference at high rotation more than at low rotation, and the boundary layer becomes thicker near the outer circumference and stalls more easily. Phenomenon is likely to occur.

For this reason, in the conventional design method, the warp ratio of the inner peripheral portion is set larger than that of the outer peripheral portion.

However, as shown in FIG. 9, by providing the advancing angle in the rotation direction, concentration of the boundary layer at the outer peripheral portion of the leading edge can be prevented, so that stall at the leading edge can be delayed. The surging phenomenon is less likely to occur, the noise at low static pressure can be reduced, and the warp rate of the outer circumference can be made larger than that of the inner circumference. Can be increased.

The outer peripheral mounting angle Cθt is equal to the inner peripheral mounting angle C.
By making it smaller than θb, the work load on the outer peripheral portion can be reduced, and the stall at the leading edge can be delayed. Also, when the rotation speed is increased, the peripheral speed u increases, so that the relative speed w1 at the blade inlet is increased. Rises and depends on the sound power E of the noise accompanied by vortex shedding by a power of six, so that the noise tends to rise rapidly.

At low static pressure, the fluid has a flow direction 20 parallel to the axial direction, so there is no problem in the conventional design method. However, at high static pressure, the backflow 21 on the suction side 9 expands and centrifugation to the fluid occurs. Since the flow direction 22 is inclined from the inner peripheral side to the outer peripheral side of the blade due to the action of the force, a sufficient design cannot be performed with the conventional design of the axial flow blower which does not consider the radial shape. By giving the radial shape by specifying the chord center point, the shape of the inclined section 26 from the inner peripheral side to the outer peripheral side of the moving blade 1 can be determined. Conventionally, the outlet flow has a substantially arc shape, and the angle difference between the theoretical outlet flow 27 and the actual outlet flow 28 is large. However, as shown in FIG. Angle between 27 and actual outlet flow 28 Becomes small relationship, vortex shedding is reduced efficiency increases.

For this reason, even if the peripheral speed u is small, the static pressure can be increased, and even at a high static pressure, the number of revolutions can be reduced as compared with the conventional case, and the noise can be reduced. Also, when the number of revolutions is the same as that of the related art, a higher static pressure and a larger air volume can be obtained, and noise can be reduced by reducing eddy discharge. Also,
When the inclined cross-section 26 performed in the first to thirteenth embodiments has an S-shaped cross section, the work speed increases because the circumferential speed of the absolute speed increases, and when the shutoff static pressure is the same rotation, To rise.

Here, the specific noise level Ks (dB (A))
To Ks = SPL-10 · Log ((Ps + Pv) 2 ·
Q). (SPL: noise level, Q: air volume, Ps: static pressure, Pv: dynamic pressure) As shown in FIG. 10, the outer peripheral advance angle Aθt when the rotating direction of the moving blade 1 is the positive direction is 30 ° or more and 90 ° or more. The following shows that the specific noise level Ks is small. However, from the problem of strength, the optimum value is 30 ° or more and 60 ° or less.

Further, as shown in FIG. 11, the outer peripheral portion warp ratio Qt is optimum when the value is 0.05 or more and 0.09 or less, and FIG.
As shown in FIG.
Optimum at 6 or less.

Further, as shown in FIG. 13, the optimum is obtained when the outer peripheral portion mounting angle Cθt is between 20 ° and 35 °, and as shown in FIG. 14, the optimal when the inner peripheral portion mounting angle Cθb is between 30 ° and 40 °. Becomes

As described above, according to the air blower of the seventeenth embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade 1 is projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point 1 is designed in a specific shape, the outer peripheral warpage rate Qt is made larger than the inner peripheral warp rate Qb, the level of each factor is optimized, and the outer peripheral part installation angle C
θt is smaller than the inner peripheral portion mounting angle Cθb, and by optimizing the levels of the respective factors, noise rise due to high rotation of the moving blade 1 for obtaining high static pressure and large air flow by miniaturization is suppressed. It is possible to minimize the occurrence of a surging phenomenon peculiar to an axial blower, and to enlarge the range of use.

Next, an eighteenth embodiment of the present invention will be described with reference to FIG.
7, FIG. 9 to FIG. 15, and FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, a plurality of moving blades 1 are provided on the outer periphery of the hub 2, and the moving blade 1 is projected in the axial direction of the rotating shaft 3 of the moving blade 1 in the shape of the moving blade 1. sometimes,
In a projection projected on a plane perpendicular to the rotation axis 3,
The rotation axis 3 is defined as the origin O, and the point at which the hub inner chord projected line 5 is bisected at the contact portion between the hub 2 and the blade 1 is designated as the blade inner chord projection center point Pb. A point at which the chord projection line 6 is bisected is defined as a blade outer peripheral chord projection center point Pt, and a circle having an arbitrary radius R centered on the origin O is drawn in the projection view. , A point dividing the arc 8 indicated by the radius R with the intersection 7 into two equal parts is a arbitrarily-sectioned chord projection center point Pr, and a line segment connecting the origin O and the wing inner chord projection center point Pb. Let Xb be a line segment connecting the origin O and the wing inner circumference projection center point Pt, and let Xt be a line segment X
Assuming that the angle between b and the line segment Xt is Aθt, Aθt is in the range of 30 ° to 60 ° with the rotation direction of the bucket blade 1 being the positive direction, and connects the origin O and the arbitrary cross-section chord projection center point Pr. If an arbitrary angle formed by the line segment and the line segment Xb is Aθ, A
θ takes a value smaller than Aθt, and in a projection view projected on a plane including the rotation axis 3, consider a straight line P connecting the wing inner chord projection center point Pb and the wing outer periphery center point Pt,
An object on the fluid suction side 9 with respect to the straight line P is defined as a positive direction,
If the thing on the discharge side 10 is in the negative direction, the arbitrary cross-section chord projection center point Pr is in the positive direction, intersects the straight line P at any place, and on the straight line P near the blade outer chord projection center point Pt. Assuming that a plane that shows the passing locus 11 and passes through the wing inner circumference chord projection center point Pb and is orthogonal to the rotation axis 3 is a reference plane A, the distance from the reference plane A to the arbitrary cross section chord projection center point Pr is K , The radial distribution of K is Rb <R <0.
In the range of 46Rt, 0 <K <0.125Rt, and in the range of 0.46Rt <R <0.70Rt, the range of 0.
In the range of 12Rt <K <0.17Rt, 0.70R
In the range of t <R <Rt, 0.16Rt <K <0.26
In the range of 5Rt, (Rt: blade outer radius, Rb: blade inner radius), and an arbitrary radius R centered on the origin O
Wing section 13 formed by cutting the cylindrical surface of the wing and expanding the section in two dimensions. The center line of the wing section 13 of the wing has a substantially arc shape. Rate Q
Is given by Q = D / L, the outer peripheral warpage rate Qt in the blade cross section 13 of the blade outer peripheral portion takes a value in the range of 0.05 to 0.09, and the inner circumferential portion of the blade inner peripheral portion in the blade cross section 13 The warp rate Qt takes a value in the range of 0.03 to 0.06, and the warp rate Q of the inner peripheral portion is smaller than that of the outer peripheral portion. In the blade cross section 13 formed by expanding the cross section two-dimensionally, the angle formed between the chord and the cascade line 18 which is a straight line perpendicular to the rotation axis 3 and passing through the leading edge 17 of the blade 14 is defined as an attachment angle Cθ. The outer peripheral portion mounting angle Cθt in the blade cross section 13 of the outer peripheral portion of the blade is in the range of 20 ° to 35 °, and the inner peripheral portion mounting angle Cθb in the blade cross section 13 of the inner peripheral portion of the blade is in the range of 30 ° to 40 °. Yes, the mounting angle Cθ from the outer circumference to the inner circumference
And an arbitrary radius R centered on the origin O
On the wing row line 18 which is a straight line passing through the wing leading edge 17 of the wing 14 perpendicularly to the rotation axis 3 and a wing cross section 13 formed by expanding the cross section in a two-dimensional manner. When the pitch T is the distance between the wing leading edge 17 of the wing 14 and the wing leading edge 19 of the wing 15 adjacent to the wing, the chord ratio S is given by S = L / T. The configuration is in the range of 0.6 to 1.0.

With the above configuration, when the chord length L does not change, the pitch T is reduced, that is, the number of blades is increased, so that the flow can easily follow the blade even at high static pressure, and the thickness of the boundary layer is reduced. However, when the number of blades is increased, the number of sound sources generated from the blades increases, so that the noise tends to increase when the static pressure is low. Therefore, in order to reduce noise while maintaining a balance between low static pressure and high static pressure, the stringing ratio S is limited.

Also, as shown in FIG. 15, the optimum is obtained when the chord ratio S is 0.6 or more and 1.0 or less. As described above, according to the blower of the eighteenth embodiment of the present invention, the moving blade 1 has a shape advanced in the rotational direction, and the chord of the moving blade 1 is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the center point is designed in a specific shape, the outer peripheral portion warp ratio Qt is made larger than the inner peripheral portion warp ratio Qb, the chord ratio S is limited, the level of each factor is optimized, and the outer peripheral portion mounting angle is set. Cθt is smaller than the inner peripheral portion mounting angle Cθb, and the level of each factor is optimized to suppress noise rise due to high rotation of the moving blade 1 to obtain high static pressure and large air flow with downsizing. It is possible to minimize the occurrence of a surging phenomenon peculiar to an axial blower, and to enlarge the range of use.

Next, a nineteenth embodiment of the present invention will be described with reference to FIG.
7, FIG. 8 to FIG. 17, and FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the drawing, the configuration of the fifteenth, sixteenth, seventeenth, and eighteenth embodiments has the same central axis as the rotating shaft 3 of the moving blade 1 having the outer diameter Dt, and has a radial cross section on the suction port side. A circular arc extending from the center of a radius Or on a plane perpendicular to the central axis indicating the minimum inner diameter Dr at Or to the suction port side by an angle Oθ, and having a duct section having a linear cross section and a length of Lr. It has an orifice made in one piece and has a radius Or.
15Dt to 0.4Dt, and the minimum inner diameter Dr is 1.02
Dt to 1.03 Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.05 Dt to 0.10 Dt.

According to the above configuration, the cross section on the suction port side is an arc-shaped circular pipe, and the outlet side is a duct, so that the flow along the blade at low static pressure becomes parallel to the central axis, and The flow is also less turbulent and noise is reduced.

As described above, according to the air blower of the nineteenth embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of No. 1 is designed in a specific shape, the outer peripheral warp ratio Qt is made larger than the inner peripheral warp ratio Qb, the chord ratio S is limited, and the level of each factor is optimized. By making the part mounting angle Cθt smaller than the inner peripheral part mounting angle Cθb, specifying the shape of the orifice, and optimizing the level of each factor, the dynamics for obtaining high static pressure and large air flow with miniaturization are obtained. It is possible to suppress an increase in noise due to the high rotation speed of the blade 1, minimize the occurrence of a surging phenomenon peculiar to the axial blower, and increase the range of use.

Next, a twentieth embodiment of the present invention will be described with reference to FIG.
7, FIG. 9, FIG. 9 to FIG. 16, and FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description is omitted.

As shown in the figure, the configuration of the fifteenth, sixteenth, seventeenth, and eighteenth embodiments has the same central axis as the rotating shaft 3 of the moving blade 1 having the outer diameter Dt, and shows a cross section on the suction port and the outlet side. Is an arcuate ring extending from the center of the radius Or on a plane perpendicular to the central axis showing the minimum inner diameter Dr with the radius Or toward the suction port side by an angle Oθ, having a straight section and a length L
r having an orifice formed by sandwiching the duct portion, the radius Or is 0.05 Dt to 0.2 Dt, the minimum inner diameter Dr is 1.02 Dt to 1.03 Dt, and the angle O
is 30 ° to 90 °, and the length Lr is 0.01 Dt to
It is configured to be 0.02Dt.

With the above structure, the cross sections of the suction port side and the outlet side are arc-shaped circular pipes and joined by a duct portion, so that at high static pressure, the backflow 21 on the suction side 9 expands and the action of centrifugal force on the fluid is exerted. As a result, the blade is inclined in the direction from the inner peripheral side to the outer peripheral side of the bucket blade 1, so that the outlet side obstructs the outlet flow of the fluid in the form of a duct portion, and the cause of turbulence can be eliminated.

As described above, according to the air blower of the twentieth embodiment of the present invention, the moving blade 1 is advanced in the rotational direction, and the moving blade is shown in a projection view projected on a plane including the rotating shaft 3. The trajectory 11 of the chord center point of No. 1 is designed in a specific shape, the outer peripheral warp ratio Qt is made larger than the inner peripheral warp ratio Qb, the chord ratio S is limited, and the level of each factor is optimized. The blade for obtaining a high static pressure and a large air volume with a small size by making the part mounting angle Cθt smaller than the inner peripheral part mounting angle Cθb, specifying the shape of the orifice, and optimizing the level of each factor. It is possible to suppress an increase in noise due to the high rotation speed of the blade 1, minimize the occurrence of a surging phenomenon peculiar to an axial blower, and increase the range of use.

[0192]

As is clear from the embodiments as described above, according to the present invention, the blade shape of the moving blade 1 is projected on a plane including the rotation axis 3 of the moving blade 1 in the projection view. The locus 11 of the center point of the chord becomes a shape showing an S shape,
In addition, it is a shape advanced in the direction of rotation of the wing, and the warp rate of the inner peripheral part is smaller than the outer peripheral part, the mounting angle of the inner peripheral part is larger than the outer peripheral part, and the range of the chord ratio is specified, In addition, by specifying the dimensions of the orifice shape and optimizing the levels of these factors, it is possible to suppress the rise in noise due to the high rotation of the blower impeller to obtain high static pressure and a large air flow with miniaturization. It is possible to minimize the occurrence of the surging phenomenon peculiar to the blower, to increase the use range, and to reduce the use load of the motor 4, and by using this blower impeller,
It can be applied to a wide range of applications that could not be achieved with conventional ventilation ventilation equipment and air conditioning equipment.

[Brief description of the drawings]

FIG. 1 is an overall view of a blower impeller according to a first embodiment of the present invention.

FIG. 2 is a projection view of the main part.

FIG. 3 is a sectional view of a main part of the same.

FIG. 4 is a sectional view of an essential part of the same.

FIG. 5 is a sectional view of the main part.

FIG. 6 is a side sectional view of the main part.

FIG. 7 is a side sectional view of the main part.

FIG. 8 is a sectional view of the main part.

FIG. 9 is a projection view of the main part.

FIG. 10 shows a specific noise level K at the outer peripheral advance angle Aθt.
s performance characteristic diagram

FIG. 11 shows a specific noise level K at the outer peripheral portion warpage rate Qt.
s performance characteristic diagram

FIG. 12 shows a specific noise level k at the inner peripheral portion warpage rate Qb.
s performance characteristic diagram

FIG. 13 is a characteristic diagram of a specific noise level Ks at the outer peripheral portion mounting angle Cθt.

FIG. 14 is a performance characteristic diagram of a specific noise level Ks at the inner peripheral portion mounting angle Cθb.

FIG. 15 is a performance characteristic diagram of a specific noise level Ks at the same string ratio S.

FIG. 16 is a side sectional view of a blower impeller of the sixth embodiment.

FIG. 17 is a side sectional view of a blower impeller of the seventh embodiment.

FIG. 18 is a sectional view of a main part of another blower impeller of the first embodiment.

FIG. 19 is a projection view of a main part of a conventional blower impeller.

FIG. 20 is a sectional view of a main part of the same.

FIG. 21 is a sectional view of the main part.

FIG. 22 is a sectional view of the main part.

FIG. 23 is a side sectional view of the relevant part.

[Explanation of symbols]

 Reference Signs List 1 rotor blade 2 hub 3 rotation axis 4 motor 5 blade inner chord projection line 6 blade outer chord projection line 7 intersection 8 arc X straight line P straight line R radius Aθ advance angle Aθt outer circumference advance angle Pt blade outer chord projection center point Pb blade Inner chord projection center point Pr Arbitrary cross-section chord projection center point O Origin 9 Suction side 10 Discharge side 11 Trajectory 13 Wing cross section 14 Wing 15 Wing 16 Chord 17 Wing leading edge 18 Cascade line 19 Wing leading edge L Chord length T pitch Cθ Mounting angle u Peripheral speed c1 Inlet axial flow speed c2 Outlet axial flow speed w1 Relative speed w2 Relative speed 20 Flow direction 21 Backflow 22 Flow direction 23 Inclined section 24 Outlet flow 25 Outlet flow Dt Outer diameter Or Radius Dr Minimum inner diameter Oθ Angle Lr Length 26 Inclined cross section 27 Outlet flow 28 Outlet flow

Claims (20)

(57) [Claims] A plurality of rotor blades provided on an outer periphery of a hub;
A motor for supporting the moving blades with a rotating shaft is provided, and the shape of the moving blades is a projection projected in the axial direction of the rotating shaft. A point at which the projection line of the blade inner chord at the contact part is bisected is defined as a blade inner chord projection center point Pb, and a point at which the projection of the blade outer periphery chord of the moving blade is bisected is designated as a blade outer chord projection center point Pt. A circle having an arbitrary radius R centered on the origin O is drawn, and an intersection point where the circle intersects in the projection of the bucket blade and a point bisecting an arc indicated by the radius R are arbitrarily sectioned chords. The projection center point Pr is used as the projection center point Pb in the projection view projected on a plane including the rotation axis.
And a straight line P connecting the wing outer peripheral chord projection center point Pt, a line on the fluid suction side from the straight line P is defined as a positive direction, and a line on the discharge side is defined as a negative direction. The arbitrary cross-section chord projection, in which the point Pr is in the positive direction near the wing inner chord projection center point Pb, intersects the straight line P at an arbitrary position, and becomes a negative direction near the wing outer chord projection center point Pt. Whether the locus of the center point Pr shows an S shape , or
Or, in the vicinity of the wing outer peripheral chord projection center point Pt,
A blower impeller that draws a trajectory . 2. The origin O of the rotation axis and the projection center point Pb of the blade inner circumference chord.
Xb, the origin O and the wing inner chord projection center point P
Assuming that a line segment connecting t is Xt and an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is in a range of 30 ° to 60 ° with the rotation direction of the bucket blade being the positive direction. If an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb is Aθ,
Aθ takes a value smaller than Aθt, and when a plane passing through the wing inner chord projection center point Pb and perpendicular to the rotation axis is defined as a reference plane A, the arbitrary cross-section chord projection center point from the reference plane A When the distance to Pr is K,
The radial distribution of K is in the range of 0 <K <0.125Rt in the range of Rb <R <0.46Rt, and 0.46Rt <
In the range of R <0.70Rt, 0.12Rt <K <0.
17Rt, and in a range of 0.70Rt <R <Rt, a range of 0.16Rt <K <0.34Rt is taken;
(Rt: outer circumference radius of the blade, Rb: inner circumference radius of the blade), and a blade section formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O and expanding the section in two dimensions. The center line in the cross section of the wing has a substantially arc shape, and the chord length L and the deflection D of the wing cross section are given by Q = D / L.
The outer peripheral portion warpage rate Qt in the blade cross section of the outer peripheral portion of the blade is 0.
05 to 0.09, the inner peripheral part warpage rate Qt in the blade cross section of the inner peripheral part of the blade takes a value in the range of 0.03 to 0.06, and the inner peripheral part is more curved than the outer peripheral part. The blower impeller according to claim 1, wherein the rate Q is smaller. 3. The origin O of the rotation axis and the projection center point Pb of the inner wing chord.
Xb, the origin O and the wing inner chord projection center point P
Assuming that a line segment connecting t is Xt and an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is in a range of 30 ° to 60 ° with the rotation direction of the bucket blade being the positive direction. If an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb is Aθ,
Aθ takes a value smaller than Aθt, and when a plane passing through the wing inner chord projection center point Pb and perpendicular to the rotation axis is defined as a reference plane A, the arbitrary cross-section chord projection center point from the reference plane A When the distance to Pr is K,
The radial distribution of K is in the range of 0 <K <0.125Rt in the range of Rb <R <0.46Rt, and 0.46Rt <
In the range of R <0.70Rt, 0.12Rt <K <0.
17Rt, and in a range of 0.70Rt <R <Rt, a range of 0.16Rt <K <0.34Rt is taken;
(Rt: blade outer radius, Rb: blade inner radius), and a blade section formed by cutting the cylindrical surface of the arbitrary radius R centered on the origin O and expanding the section in two dimensions. The angle formed between the chord and a row of cascade lines that is perpendicular to the rotation axis and passes through the leading edge of the blade section is defined as a mounting angle Cθ, and an outer peripheral portion mounting angle Cθt in the blade cross section of the outer peripheral portion of the blade is 20 °. 2. The blower impeller according to claim 1, wherein the inner peripheral portion mounting angle Cθb in the blade cross section of the inner peripheral portion of the blade is in a range of 30 ° to 40 °. 4. An arbitrary radius R centered on the origin O of the rotation axis.
Is a wing cross section formed by expanding the cross section two-dimensionally, the center line of the wing in the wing cross section is substantially arc-shaped, and the chord length L and the warp D of the wing cross section Q Is Q = D
/ L, the outer peripheral part warpage rate Qt in the blade cross section of the outer peripheral part of the blade takes a value in the range of 0.05 to 0.09, and the inner peripheral part warp rate Qt in the blade cross section of the inner peripheral part of the blade is 0. .03-
4. The blower impeller according to claim 1, wherein the blower impeller takes a value in the range of 0.06, and the warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion. 5. A blade section formed by cutting the cylindrical surface having the arbitrary radius R centered on the origin O of the rotation axis and expanding the cross section two-dimensionally, and having a chord length L perpendicular to the rotation axis. On a cascade line that is a straight line passing through the wing leading edge of the wing, when a distance between the wing leading edge of the wing and the wing leading edge of an adjacent wing is a pitch T,
The string ratio S is given by S = L / T, and the string ratio S is 0.6 to
The blower impeller according to claim 1, 3 or 4, which has a range of 1.0. 6. A center of a radius Or on a plane perpendicular to a central axis having a cross section on the suction port side having a radius of Or and a minimum inner diameter Dr, wherein the center axis is the same as the rotation axis of the rotor blade having an outer diameter Dt. Is an arc-shaped ring extending from the opening to the suction port side by an angle Oθ, and has an orifice integrally formed with a duct portion having a straight section and a length of Lr, and the radius Or is 0.15 Dt.
0.4Dt, and the minimum inner diameter Dr is 1.02Dt.
6. The blower impeller according to claim 1, wherein the angle Oθ is 30 ° to 90 °, and the length Lr is 0.05 Dt to 0.10 Dt. 7. 7. A rotating shaft of a rotor blade having an outer peripheral diameter Dt having the same central axis as a rotating shaft of a rotor blade having a radius O
r is an arcuate ring extending from the center of a radius Or on a plane perpendicular to the central axis indicating the minimum inner diameter Dr toward the suction port side by an angle Oθ, and has a straight section and a length Lr. An orifice formed integrally with the pinch, the radius Or is 0.05 Dt to 0.2 Dt, the minimum inner diameter Dr is 1.02 Dt to 1.03 Dt, and the angle O
is 30 ° to 90 °, and the length Lr is 0.01D
6. The method according to claim 1, wherein t is 0.02 Dt.
The blower impeller described. 8. The origin O of the rotation axis and the projection center point Pb of the blade inner circumference.
Is defined as Xb, and a line connecting the origin O and the wing inner chord projection center point Pt is defined as Xt, where Aθt is an angle formed by the line Xb and the line Xt. When the rotation direction of the bucket blade is the positive direction, the angle is in the range of 30 ° to 60 °, and an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb is Aθ. , Aθ is smaller than Aθt, and if a plane passing through the wing inner circumference chord projection center point Pb and perpendicular to the rotation axis is defined as a reference plane A, the arbitrary cross-section chord projection from the reference plane A is performed. Assuming that the distance to the center point Pr is K, the radial distribution of K is 0 <K <0.14Rt in the range of Rb <R <0.46Rt, and 0.46Rt.
In the range of <R <0.70Rt, 0.13Rt <K <
In the range of 0.70Rt <R <Rt, the range of 0.16Rt <K <0.265Rt is taken, (Rt: blade outer radius, Rb: blade inner radius), and A wing section formed by cutting a cylindrical surface of an arbitrary radius R centered on the origin O and expanding the section in two dimensions, the center line of the wing section of the wing is substantially arc-shaped, Is given by Q = D / L with the chord length L and the warp D of the blade.
Takes a value in the range of 0.05 to 0.09, and the inner peripheral portion warp rate Qt in the blade cross section of the inner peripheral portion of the blade is 0.03 to 0.09.
The blower impeller according to claim 1, wherein a value of the range of 6 is set, and the warp rate Q of the inner peripheral portion is smaller than that of the outer peripheral portion. 9. The origin O of the rotation axis and the projection center point Pb of the inner wing chord.
Xb, the origin O and the wing inner chord projection center point P
Assuming that a line segment connecting t is Xt and an angle formed by the line segment Xb and the line segment Xt is Aθt, this Aθt is in a range of 30 ° to 60 ° with the rotation direction of the bucket blade being the positive direction. If an arbitrary angle formed by a line segment connecting the origin O and the arbitrary cross-section chord projection center point Pr and the line segment Xb is Aθ, Aθ takes a value smaller than Aθt, and Assuming that a plane passing through the projection center point Pb and perpendicular to the rotation axis is a reference plane A, when a distance from the reference plane A to the arbitrary cross-section chord projection center point Pr is K, a radial distribution of K is When Rb <R <0.46Rt, 0 <K <0.14Rt, and 0.46Rt
In the range of <R <0.70Rt, 0.13Rt <K <
In the range of 0.70Rt <R <Rt, the range of 0.16Rt <K <0.265Rt is taken, (Rt: blade outer radius, Rb: blade inner radius), and A wing section formed by cutting the cylindrical surface of the arbitrary radius R centered on the origin O and expanding the section in two dimensions, the wing leading edge of the wing section perpendicular to the chord and the rotation axis. The angle formed with the cascade line, which is a straight line, is referred to as an attachment angle Cθ, and the outer peripheral portion attachment angle Cθt in the blade cross section of the outer peripheral portion of the blade is in a range of 20 ° to 35 °. The blower impeller according to claim 1, wherein the inner peripheral portion mounting angle Cθb is in a range of 30 ° to 40 °, and the inner peripheral portion mounting angle Cθ is larger than the outer peripheral portion. 10. A wing section formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O of the rotation axis and expanding the section in two dimensions, wherein the center line of the wing section is substantially a circular arc. With the chord length L and the sled D of the wing cross section, the warp rate Q is Q =
Given by D / L, the outer peripheral part warpage rate Qt in the blade cross section of the outer peripheral part of the blade takes a value in the range of 0.05 to 0.09, and the inner peripheral part warp rate Qt in the wing cross section of the inner peripheral part of the blade is 0.03
The blower impeller according to claim 1 or 9, wherein the blower impeller has a value in the range of -0.06 and the warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion. 11. A blade section formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O of the rotation axis and expanding the cross section in two dimensions, and a chord length L and a blade section perpendicular to the rotation axis. On a cascade line that is a straight line passing through the leading edge of the wing, when the distance between the leading edge of the wing and the leading edge of the wing adjacent to the wing is a pitch T, the chord ratio S is S = L / T, and the chord ratio S is 0.6 to
The blower impeller according to claim 1, 9 or 10, which has a range of 1.0. 12. The center axis of which is the same as the rotation axis of the rotor blade having an outer diameter Dt, and whose center on a plane Or whose cross section on the suction port side is a radius Or and is perpendicular to the center axis indicating the minimum inner diameter Dr. Is an arc-shaped ring extending from the side to the suction port side by an angle Oθ, and has an orifice integrally formed with a duct portion having a straight section and a length of Lr, and the radius Or is 0.15D.
t to 0.4 Dt, and the minimum inner diameter Dr is 1.02 D
t to 1.03 Dt, and the angle Oθ is 30 ° to 90 °.
長, and the length Lr is 0.05 Dt to 0.10 Dt.
The blower impeller according to claim 1, 8, 9, 10, or 11, wherein 13. A central axis having the same axis as the rotating axis of the rotor blade having an outer peripheral diameter Dt, and having a radius Or on a plane perpendicular to the central axis whose cross section on the inlet and outlet sides has the radius Or and the minimum inner diameter Dr. Is an arc-shaped ring extending from the center to the suction port side by an angle Oθ, has an orifice integrally formed by sandwiching a duct section having a linear cross section and a length of Lr. 05Dt to 0.2Dt, the minimum inner diameter Dr is 1.02Dt to 1.03Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.01
The blower impeller according to claim 1, 8, 9, 10, or 11, wherein Dt is 0.02Dt. 14. A plurality of rotor blades are provided on the outer periphery of the hub,
A motor for supporting the moving blades with a rotating shaft is provided, and the shape of the moving blade is projected on a plane perpendicular to the rotating shaft when the moving blade is projected in the axial direction of the rotating shaft. , The rotation axis is defined as the origin O, the point at which the hub and the rotor blade contact each other, and the point at which the blade inner circumference projection line is bisected is defined as the blade inner circumference projection center point Pb, and the blade of the rotor blade is The point at which the outer chord projection line is bisected is the wing outer chord projection center point P
t, and in the projection, a circle having an arbitrary radius R centered on the origin O is drawn, and an intersection point where the circle intersects in the projection of the bucket blade and an arc indicated by the radius R are bisected. Is defined as an arbitrary cross-section chord projection center point Pr, and a straight line P connecting the wing inner chord projection center point Pb and the wing outer chord center point Pt in a projection view projected on a plane including the rotation axis. In consideration of the above, if the one on the suction side of the fluid with respect to the straight line P is in the positive direction, and the one on the discharge side is in the negative direction, the arbitrary cross-section chord projection center point Pr is equal to the wing inner chord projection center. A blower impeller that is in the positive direction near point Pb, intersects with the straight line P at an arbitrary position, and draws a locus passing on the straight line P near the blade outer peripheral chord projection center point Pt. 15. The origin O of the rotation axis and the projection center point P of the wing inner circumference chord.
Assuming that a line connecting Xb is Xb and a line connecting the origin O and the wing inner chord projection center point Pt is Xt, when an angle formed by the line Xb and the line Xt is Aθt, Aθt is The rotation direction of the moving blade is in the range of 30 ° to 60 ° with the rotation direction being the positive direction, and the origin O and the arbitrary cross-section chord projection center point Pr
Is defined as Aθ, and Aθ has a value smaller than Aθt, and passes through the wing inner chord projection center point Pb and is orthogonal to the rotation axis. Let K be the distance from the reference plane A to the arbitrary cross-section chord projection center point Pr, the radial distribution of K is 0 <K <in the range of Rb <R <0.46Rt. 0.125Rt range, 0.46Rt
In the range of t <R <0.70Rt, 0.12Rt <K <
In the range of 0.70Rt <R <Rt, the range of 0.16Rt <K <0.265Rt is taken, (Rt: blade outer radius, Rb: blade inner radius), and A wing section obtained by cutting a cylindrical surface having an arbitrary radius R centered on the origin O and expanding the section in two dimensions, the center line in the wing section has an arc shape, and the chord length of the wing section The warp rate Q is given by Q = D / L with L and warp D, and the outer circumferential warp rate Qt in the blade cross section of the outer circumferential portion of the blade is 0.05.
The value of the inner peripheral portion warp Qt in the blade cross section of the inner peripheral portion of the blade takes a value of 0.03 to 0.06. The blower impeller according to claim 14, wherein Q is reduced. 16. The origin O of the rotation axis and the projection center point P of the blade inner circumference chord.
Assuming that a line connecting Xb is Xb and a line connecting the origin O and the wing inner chord projection center point Pt is Xt, when an angle formed by the line Xb and the line Xt is Aθt, Aθt is The rotation direction of the moving blade is in the range of 30 ° to 60 ° with the rotation direction being the positive direction, and the origin O and the arbitrary cross-section chord projection center point Pr
Is defined as Aθ, and Aθ has a value smaller than Aθt, and passes through the wing inner chord projection center point Pb and is orthogonal to the rotation axis. Let K be the distance from the reference plane A to the arbitrary cross-section chord projection center point Pr, the radial distribution of K is 0 <K <in the range of Rb <R <0.46Rt. 0.125Rt range, 0.46Rt
In the range of t <R <0.70Rt, 0.12Rt <K <
In the range of 0.70Rt <R <Rt, the range of 0.16Rt <K <0.265Rt is taken, (Rt: blade outer radius, Rb: blade inner radius), and A wing section formed by cutting the cylindrical surface of the arbitrary radius R centered on the origin O and expanding the section in two dimensions, the wing leading edge of the wing section perpendicular to the chord and the rotation axis. The angle formed with the cascade line, which is a straight line, is referred to as an attachment angle Cθ, and the outer peripheral portion attachment angle Cθt in the blade cross section of the outer peripheral portion of the blade is in a range of 20 ° to 35 °. 15. The blower impeller according to claim 14, wherein the inner peripheral portion mounting angle C [theta] b is in a range of 30 [deg.] To 40 [deg.], And the warp rate Q of the inner peripheral portion is smaller than that of the outer peripheral portion. 17. A wing section obtained by cutting a cylindrical surface having an arbitrary radius R centered on the origin O of the rotation axis and expanding the section in two dimensions, wherein the center line of the wing section is substantially a circular arc. With the chord length L and the sled D of the wing cross section, the warp rate Q is Q =
Given by D / L, the outer peripheral part warpage rate Qt in the blade cross section of the outer peripheral part of the blade takes a value in the range of 0.05 to 0.09, and the inner peripheral part warp rate Qt in the wing cross section of the inner peripheral part of the blade is 0.03
17. The blower impeller according to claim 14 or 16, wherein a value in a range of -0.06 is set, and a warp ratio Q of the inner peripheral portion is smaller than that of the outer peripheral portion. 18. A blade section formed by cutting a cylindrical surface having an arbitrary radius R centered on the origin O of the rotation axis and expanding the cross section in two dimensions, and a chord length L and a blade section perpendicular to the rotation axis. On a cascade line that is a straight line passing through the leading edge of the wing, when the distance between the leading edge of the wing and the leading edge of the wing adjacent to the wing is a pitch T, the chord ratio S is S = L / T, and the chord ratio S is 0.6 to
The blower impeller according to claim 14, 16 or 17, which has a range of 1.0. 19. A center of a radius Or on a plane perpendicular to the center axis whose cross section on the suction port side is the radius Or and has the minimum inner diameter Dr, wherein the center axis is the same as the rotation axis of the rotor blade having the outer diameter Dt. Is an arc-shaped ring extending from the side to the suction port side by an angle Oθ, and has an orifice integrally formed with a duct portion having a straight section and a length Lr, and the radius Or is 0.15D.
t to 0.4 Dt, and the minimum inner diameter Dr is 1.02 D
t to 1.03 Dt, and the angle Oθ is 30 ° to 90 °.
長, and the length Lr is 0.05 Dt to 0.10 Dt.
The blower impeller according to claim 14, 15, 16, 17, or 18. 20. A central axis having the same axis as a rotating axis of a rotor blade having an outer diameter Dt, and a cross section on the inlet and outlet sides having a radius of Or and a radius Or on a plane perpendicular to the central axis indicating the minimum inner diameter Dr. Is an arc-shaped ring extending from the center to the suction port side by an angle Oθ, has an orifice integrally formed by sandwiching a duct section having a linear cross section and a length of Lr. 05Dt to 0.2Dt, the minimum inner diameter Dr is 1.02Dt to 1.03Dt, the angle Oθ is 30 ° to 90 °, and the length Lr is 0.01
Dt to 0.02 Dt.
The blower impeller according to 7 or 18.