JP2779285B2 - Multi-layer disk fan with wings - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a winged multi-layer disk fan capable of stably obtaining a sufficient air volume while maintaining quiet operation.

[0002]

2. Description of the Related Art Conventionally, as one form of a fan capable of quiet operation, there is a multi-layer disk fan with wings X described in Japanese Utility Model Laid-Open No. 54-89602.

As shown in FIGS. 25 and 26, such a multi-layer disk fan with wings X has a fan blade 101 driven by an electric motor 100 disposed substantially at one end of a fan casing 110. .

Then, the fan blade 101 is rotated by the driving of the electric motor 100 to generate an air flow, and the air can be sent out from the air outlet 140.

Further, as shown in FIG. 25, the fan blade 101 is formed by laminating a large number of thin circular disks 104 at predetermined intervals, so that by rotating the circular disks 104, the fan blades 101 are rotated. A circumferential shear force is generated on the surface. The force acts as a centrifugal force, and as a result, an air flow is generated, so that the fan can be operated quietly.

Further, in order to provide a predetermined space between the annular disks 104, to smoothly flow air from the inner peripheral side to the outer peripheral side, and to increase the fan air volume, as shown in FIGS.
A plurality of arc-shaped wings 105 which also function as spacers are interposed between the annular disks 104 at a required circumferential pitch.

[0007]

However, such a multi-layer disk fan with wings X still has the following problems to be solved.

That is, as is apparent from FIG. 26, all of the blades 105 have their outer circumferential ends (blades outlet end) at their annular disks.
104 to the outer edge. Therefore, an annular disk
At the outlet of 104, as shown in FIGS. 26 and 27, a large speed distortion occurs in the circumferential direction, and the speed distortion periodically changes the pressure near the tongue of the casing, so that so-called rotational noise is generated. Was.

In addition to the tongue, the outer peripheral edge of the circular disk 104 is disturbed in the process of equalizing the large velocity strain,
Turbulent noise was occurring.

Further, an air flow flowing between the annular disks 104, 104
Of the 106, the air behind the wing 105 separated, and the separated area 10
8 was formed, and a turbulent flow area 107 was generated on the outer peripheral edge of the disk due to the influence of the separation, and turbulent noise was generated.

On the other hand, as shown in FIG. 26, the wing 105 also has a tip in the inner circumferential direction (tip of the wing inlet) at the annular disk 10.
4 extends to the inner edge.

Therefore, as shown in the distribution 111 of the absolute value of the velocity on the blade surface in FIG. 26, the reduction ratio on the suction surface at the inner tip of the blade 105 is large. As shown in FIG.
Due to the large reduction ratio at the entrance between 104 and 104,
Separation occurred at the inner suction surface of the wing 105.
In addition, when there is a velocity distortion in the circumferential direction at the inlet of the annular disk, the inflow angle to the blade is not constant, which also causes separation. As a result, the turbulent noise at the inner periphery of the annular disk 104 is also increased.

An object of the present invention is to provide a multi-layered winged disk fan capable of solving the above-mentioned problems and increasing the air volume as much as possible while maintaining quiet operation. And

[0014]

SUMMARY OF THE INVENTION The present invention relates to a multi-layer winged disk fan formed by laminating a number of annular disks which are kept at a fixed distance from each other. The present invention relates to a multi-layer disk fan with blades, wherein the outer circumferential end of the blade is located inside the outer peripheral edge of the annular disk.

The present invention also provides a multi-layered winged disk fan formed by laminating a number of annular disks having a constant gap therebetween, with a number of blades interposed between the annular disks. The present invention relates to a multi-layered winged disk fan configured such that an inner circumferential end of a wing is located outside a predetermined distance from an inner peripheral edge of an annular disk.

According to the present invention, there is also provided a multi-layered winged disk fan formed by laminating a number of annular disks having a fixed gap therebetween, wherein a number of blades are interposed between the annular disks. The outer circumferential tip of the wing is configured so as to be located inside by a fixed distance from the outer peripheral edge of the annular disk, and the inner circumferential tip of the wing is located outside the inner peripheral edge of the annular disk by a fixed gap. The present invention relates to a multi-layered disk fan with wings configured to be located at a position as shown in FIG.

The gist of the present invention is to provide a multi-layer winged disk fan characterized by adding the following features to the various winged multi-layer disk fans described above. .

The distance S ₁ located inside the outer peripheral edge of the annular disk of the blade is a value represented by the following equation.

[0019]

(Equation 4)

The distance S ₂ located outside the inner peripheral edge of the annular disk of the blade is 0.025 <S ₂ / r ₂ <0.125 in relation to the radius r _{2 of the} inner edge of the blade of the annular disk.

In addition to the above features, the mounting direction of the wing is a rearward wing.

Lines L _{1 and} L ₂ connecting the innermost and outermost ends of the wing
And the trajectory R of the fluid obtained from the circumferential velocity and the radial velocity in the relative velocity of the fluid flowing between the annular disks, the angle θ formed at the inner tip of the wing, that is, the angle of attack is 20 ° ± 15 °
And

A line L formed by connecting the circumferential pitch angle α between the blades and the innermost and outermost ends of the blade with the center of the annular disk.
_3, the relationship between the angle of the L ₄ beta, is 0.5 <β / α <1 and.

The gap δ between the annular disks is a value represented by the following equation.

[0025]

(Equation 5)

The gap δ between the annular disks is a value represented by the following equation.

[0027]

(Equation 6)

[0028]

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view of a multi-layer disk fan with wings according to the present invention.

[0029] (Example 1) This example, with reference to FIGS, as described below, the outer end of the blade 25 by a distance S ₁ from the outer peripheral edge of the annular disc 24 inwardly The multi-layered disk fan A with wings is configured to be located at a position as shown in FIG. In this embodiment, the multi-layer disk fan A with wings is used as a hot air fan.

As shown in FIGS. 1 to 3, the fan casing 13 of the multi-layer disk fan A with wings has a substantially circular front wall 10 and a substantially circular rear wall.
Except for the lower end opening (warm air outlet) 40, the peripheral edges of 11 are connected by an annular peripheral wall 12.

In this embodiment, the fan casing 13 is fixed to a motor casing 15 via a support frame 14.

The fan casing 13 has an air inlet 10a in the front wall 10 and a fan blade 20 concentrically disposed inside the air inlet 10a.
Is the output shaft of the drive motor 21 disposed in the support frame 14.
Connected to 22.

Below the fan casing 13, a heater 39 composed of a nichrome wire or the like is provided.

In the above basic configuration, the present invention is characterized by the configuration of the fan blade 20 capable of quiet operation.

That is, as shown in FIGS. 2, 4 and 5,
The fan blade 20 is substantially formed by stacking a large number of thin annular disks 24 on a base disk 23 in a layered manner with a certain gap δ opened through a number of blades 25. doing.

The constant gap δ includes not only a case where the gaps δ are equal but also a case where they are not equal.

The annular disk 24 has a donut shape as shown in FIG. 3, and has an insertion hole 27 for inserting a connecting pin 26 described later at a constant circumferential pitch.

The constant circumferential pitch includes not only the case where the pitch is equal but also the case where the pitch is not equal.

On the other hand, as shown in FIG. 5, the wing 25 is formed of a thin arc-shaped piece, and has an insertion hole 28 for inserting the connecting pin 26 at the center thereof.

When assembling the fan blade 20 shown in FIG. 2, a number of annular disks 24 and blades 25 are placed on a base disk 23.
Are alternately stacked by inserting the connection pins 26 into the respective insertion holes 27 and 28, and then the insertion ends of the connection pins 26 are caulked on the surface of the final annular disk 24, thereby providing the fan blades. 20 can be assembled. Further, in this embodiment, best seen in FIG. 3, the outer tip portion 25a of all the blades 25, is positioned inside by a predetermined distance S ₁ from the outer periphery of the annular disc 24.

In this manner, when the fan blade 20 is rotated, the air flows from the central space C formed inside the multilayer annular disk 24 to the air flow path between the annular disks 24,24.
The gas flows radially to the outside of the fan blade 20 through 30, and then is discharged from the annular disk 24 to the outside. At this time, the turbulence 31 due to the separation behind the wings 25 generated between the annular disks 24, 24 can be suppressed by the influence of the viscosity due to the wall surface of the rotating annular disk 24. Can be reliably prevented.

Further, the velocity strain generated between the adjacent outer blade tips due to the wall shearing force of the annular disk 24 rotating for a fixed distance S ₁ to the outer peripheral edge is reduced as shown in FIG. It is almost uniform at the plate outlet. Therefore, pressure fluctuation near the tongue is eliminated, interference noise is reduced, and generation of turbulent noise due to speed distortion can be prevented.

Further, the flow inside the blade cascade periodically changes due to the influence of the outside of the disk such as the tongue and the blow-out part, which may cause a pressure drop or a stall.
Boundary conditions from the outer peripheral edge at the wing exit by positioned inside by a predetermined distance S ₁ of the annular disk 24 is stabilized, it can be operated to the angle of the fluid flowing out from the blade always remains constant stable.

By the way, the outer tip 25a of the wing 25 described above
Distance S ₁ to the outer periphery of the annular circular plate 24 from, according to the experiment by the present applicant carried out, it was found that it is preferable that the value represented by the following formula.

[0045]

(Equation 7)

[0046]

(Equation 8)

Where _: r1 _: wing outer tip radius (mm) Z: number of wings

[0048]

(Equation 9)

In the equation, u ₁ : the peripheral velocity of the annular disk 24 at the outer radius of the blade tip (m / s) = 2πr ₁ n / 60 n: the rotational speed of the annular disk 24 (rpm) A: dimensionless flow rate ( = Qδ / ν r _i ² ) q: Air flow rate between two annular disks (m ³ / s) δ: Gap between two annular disks (m) ν: Kinematic viscosity coefficient (m ² / s) r _i : Radius of annular disk inlet (m) R _: r ₁ / r _i

[0050]

(Equation 10)

The specific noise k _s is given by k _s = L _sp -10 log
This is the value obtained in QP ² .

[0052] However, Q: air volume [m ³ / s] P of the blower: blower of pressure head [mmAg] L _sp: sound pressure level of the blower [dB (A)]

[0053]

[Equation 11]

[0054] However, too much to take large S _1, because the chord length becomes shorter, the poor performance becomes less work by the wing, resulting in specific noise becomes large. As a result, there is an optimum range in the relational expression.

The operation when the winged multilayer disk fan A having the above configuration is used as a hot air fan will be described below with reference to FIGS.

First, when the user presses an operation switch (not shown), the fan drive motor 21 and the heater 39 operate.

The fan blade motor 20 is rotated by the drive of the fan drive motor 21 to suck air from outside through the air intake port 10 a into the fan casing 10, and the air is supplied to the multilayer disk 24 constituting the fan blade 20. , 24 through the gap between the inlet side and the back side with a substantially equal air volume distribution, then generate a downward air flow, after heating with the heater 39, blow out warm air from the warm air outlet 40 to the outside, Dry your hands.

[0058] Further, in the rotation of the fan blades 20, the outer end 25a of the blade 25, since is located inside from the outer peripheral edge 24a of the annular disk 24 by a predetermined distance S _1, in the vicinity of the tip of the blade 25, Turbulence caused by separation can be effectively suppressed, and since there is no exit speed distortion at the outer peripheral edge 24a of the annular disk 24, turbulence noise and interference noise can be reduced, and quiet operation is possible. Become.

(Embodiment 2) The winged multilayer disk fan A according to the present embodiment has substantially the same configuration as the winged multilayer disk fan A according to the first embodiment, as shown in FIG. doing. That is, the multi-layered disk fan A with wings is formed by laminating a number of annular disks 24 having a constant gap δ from each other. Therefore, in FIG. 8, the same configurations or members as those of the multi-layer disk fan with wings A according to the first embodiment are denoted by the same reference numerals.

However, in this embodiment, unlike the first embodiment,
As shown in FIG. 8, only on the inner peripheral side of the annular disks 24, 24,
The turbulence is prevented by the separation.

That is, only the inner circumferential ends 25b of the many blades 25 interposed between the annular disks 24, 24 are connected to the inner circumferential edge 24 of the annular disk 24.
from a certain distance S ₂ b are configured to be positioned outside.

In this way, the annular disk 24
The turbulent noise due to separation, which is likely to occur on the inner peripheral side of the ring, can be effectively suppressed, and even if there is a speed distortion in the circumferential direction at the entrance of the annular disk 24, a constant for homogenizing the velocity distribution between the distance S _2, inflow angle to the blade is constant, it is stable and quiet operation causing no separation.

By the way, the inner tip 25 _b of the wing 25 described above
Distance S ₂ to the inner peripheral edge 24b of the annular disc 24 from the, according to the experiment by the present applicant carried out, it was found that it is preferable that the value represented by the following formula.

[0064]

(Equation 12)

That is, the following table (Table 1) shows the inner tip of the wing 25.
In addition to showing the specific noise value k _s which is an experimental result measured by varying the distance S ₂ (mm) from 25b to the inner peripheral edge of the annular disk 24 and the blade inner tip radius r ₂ (mm), In FIG.
A graph is shown in which the above (S ₂ / r ₂ ) is plotted on the horizontal axis and the specific noise value k _s (dB (A)) is plotted on the vertical axis.

The specific noise k _s is calculated as in the first embodiment.
k _s = L _sp −10 log This is a value obtained by QP ² .

[0067]

[Table 1]

As is apparent from the above table and the graph shown in FIG. 9, when 0.025 <(S ₂ / r ₂ ) <0.125, the specific noise k _s is reduced, and particularly, 0.05 <(S ₂ / r ₂₎
It was found that when <0.10, the specific noise k _s was effectively reduced.

Regarding the noise, the tip radius r _{2 of the} inside of the blade
Respect, although preferably better to increase the distance S ₂ from the inner end portion 25b of the blade 25 to the inner periphery of the annular disc 24, the distance S ₂
If too take too large for the chord length of the wing 25 is shortened, the less work by the wings 25, performance is reduced, resulting in specific noise k _s is increased. As a result, the above-mentioned optimum range exists for S ₂ / r ₂ .

(Embodiment 3) The multi-layer disk fan A with wings according to the present embodiment also has substantially the same configuration as the multi-layer disk fan A with wings according to the first embodiment, as shown in FIG. doing. That is, the multi-layered disk fan A with wings is formed by laminating a number of annular disks 24 having a constant gap δ from each other. Therefore, in FIG. 8, the same configurations or members as those of the multi-layer disk fan with wings A according to the first embodiment are denoted by the same reference numerals.

However, in this embodiment, unlike the first embodiment,
As shown in FIG. 10, turbulence noise and rotation noise due to velocity distortion and separation are prevented not only on the inner peripheral edge side of the annular disks 24, 24 but also on the outer peripheral edge side.

[0072] That is, the constituting outward tip 25a of the plurality of vanes 25 which is interposed between the annular circular plates 24, 24 so as to be positioned inwardly by a distance S ₁ from the outer peripheral edge 24a of the annular disc 24, the inward tip 25b of the blade 25 is also configured so as to be located outside by a predetermined distance S ₂ from the inner peripheral edge 24b of the annular disc 24.

With this configuration, the annular disk
It is possible to effectively suppress turbulent noise and interference noise due to velocity distortion and separation, which are likely to occur on the inner and outer peripheral sides of the 25.

(Embodiment 4) This embodiment is directed to a multi-layered winged disk fan A having a large number of blades 25, and
Paying attention to the above mounting angle, the operation of the multi-layered disk fan A with wings is reduced.

Hereinafter, this embodiment will be described in detail with reference to FIGS. 2, 3, and 11 to 15.

As shown in FIGS. 2 and 3, in the winged multi-layer disk fan A, when the fan A is rotated, the air is blown by the fan blade 20 formed by laminating the annular disks 24 in multiple layers. From the central space C formed in the center, each annular disk 2
The air flows radially outward over the entire surface of the annular disk 24 through the air flow path formed between the air disks 4 and 24, and is then heated by the heater H. Then, the hot air outlet of the multi-layer disk fan A with wings is heated.
It will be released smoothly from 40 to the outside. Then, in such an air flow, the release of air to the outside is caused by the wing 25
Will be further promoted.

By the way, as shown in FIG. 11, each of the wings 25 has retreating wings whose outer end portions 25a are retracted in a direction opposite to the rotation direction of the annular disk 24.

The reason why the wing 25 is a swept wing is that when the wing 25 is a forward wing as shown in FIG. 15 or a radial wing as shown in FIG. Same as peripheral speed,
This is because the fluid flows with a higher tangential speed, but when the fluid comes out of the wing, the fluid is decelerated by the wall friction of the annular disk 24 to cause a loss.

On the other hand, as shown in FIG. 11, when the blade 25 is a swept-back blade, not only the centrifugal force generated by the shearing force between the annular disk 24 and the fluid, but also the work This is because air can be blown without causing turbulence as much as possible.

Further, the applicant of the present invention has set the retreat angle of the wing 25,
That is, the angle of attachment θ to the circular disk 24 is determined with respect to the trajectory R of the air flowing through the air flow path formed between the circular disks 24, 24.
It has been found that, when the value is set to a constant value, the quiet operation of the multi-layer disk fan A with wings can be effectively improved.

That is, the trajectory R of the air flowing between the annular disks 24, 24, the outer tip 25 a and the inner tip 25 b of the wing 25
It is experimentally possible to achieve a quiet operation while securing a sufficient air flow when the mounting angle θ between the line L connecting the and the inlet side of each annular disk 24 is set to 20 ° ± 15 °. all right.

The reason why the mounting angle θ is set to 20 ° ± 15 ° is as follows.
For the following reasons. That is, as shown in FIG.
When the maximum angle is larger than 35 °, turbulence is observed in the flow, such as the generation of vortices due to the separation of air on the suction surface k3, the blowing noise becomes extremely loud, the performance becomes unstable due to stall, and the noise becomes remarkable. growing. On the other hand, as shown in FIG. 13, when the mounting angle θ is smaller than the minimum angle of 5 °, the work by the wings hardly occurs, or conversely, the wings become the resistance to the flow of the wind, and the performance deteriorates. As a result, the specific noise increases.

The trajectory R of the air flowing through the air flow path is
It can be easily obtained in the following manner.

First, from the following equations (6) and (7), the circumferential velocity (relative velocity) of the air flowing between the annular disks 24 and 24 when the fan blade 20 of the multi-layered disk fan A with blades is rotated is shown. Vu-U) and the radial velocity _Vr are obtained.

[0085]

(Equation 13)

From the above equations (6) and (7), the annular disk 24
The position of the air after Δt seconds at the above point is x = x ₀ +
.DELTA.TV _r, is determined as _{y = y 0 + Δt (V} u · U).

Note that Δt ≒ 0.

Then, the trajectory R can be easily obtained by continuously connecting the positions thus obtained.

[0089] In the formula described above, A: dimensionless flow rate ^{_{(= qδ D / νr i 2}} ) V U: circumferential velocity of the air at any radius m / s V _r: radial velocity of the air at any radius m / s U: peripheral velocity of the disc at an arbitrary radius m / s δ: gap between two annular discs m q: air flow rate flowing between the two annular discs m ³ / s r: arbitrary radius m r _i : radius of the annular disc inlet m [nu: kinematic viscosity m ² / s μ: viscosity coefficient kgs / m
² Incidentally, in the following table (Table 2), shows a graph when taking a θ mounting angle (angle of attack) were measured at different respective specific noise value k _s on the vertical axis in FIG. 14.

[0090]

[Table 2]

As is clear from the above Table 2 and the graph shown in FIG. 14, the specific noise is reduced when 5 ° <θ <35 °, and especially when 10.5 ° <θ <27.5 °. We were able to effectively reduce the noise k _s.

As described above, this embodiment is different from the embodiment shown in FIG.
As shown in the figure, the wing 25 is a swept wing, and the angle of attack θ is
Although there is a feature characterized by 20 ° ± 15 °, the wing 25
The shape and arrangement of are not limited to those shown in FIG. 11, but may be, for example, a multilayer disk fan A having blades 25 as shown in FIGS. 17 and 18.

That is, FIG. 17 shows a completely linear shape of the wing 25, and FIG. 18 shows a slightly curved shape of the wing 25.

(Embodiment 5) In this embodiment, as shown in FIG. 19, the circumferential pitch angle α between the blades 25, 25 and the innermost end and outermost end of the blade central and connecting in forming the line L _{3 of}
The relationship between the angle beta of L _4, are 0.5 <β / α <1 and.

The circumferential pitch angle α between the wings 25, 25
Was set to 0.5 <β / α <1 for the following reason.

That is, when β / α is smaller than 0.5,
In other words, when the circumferential pitch angle between the wings 25, 25 is larger than β / 0.5, as shown in the following table (Table 3) and the graph of FIG. Is reduced, the velocity distortion between the outer tips of the blades 25 is increased, and turbulent noise / interference noise is increased. Also, β / α
If is larger than 1, that is, if the circumferential pitch angle between the blades 25, 25 is smaller than β, the passage of the airflow flowing between the blades 25, 25 is narrowed, and the passage pressure loss increases, This is because the air volume and pressure are extremely reduced. Therefore,
There is an optimal range.

[0097]

[Table 3]

(Embodiment 6) In this embodiment, in a multi-layered winged disk fan A having a large number of blades 25, the gap δ between the annular disks 24 is determined by the kinematic viscosity coefficient of air and the annular disk 24. The operation of the multi-layered disk fan with wings A is reduced by setting the relationship with the angular velocity of the blade to an appropriate ratio. That is, in a multi-layer disk fan without wings, Breiter et al.

[0099]

[Equation 14]

The present applicant conducted an experiment under the condition that the number of blades was set to Z ≧ 8, in order to examine the validity of the above expression in the multi-layer disk fan with wing A, and the experimental results shown in the graph of FIG. I got

As is clear from this graph, in the multilayer disk fan A with wings, δ / π (ν / ω) ^{1/2 is set} to 0.1.
By setting the specific noise value in the range of 8 to 4.0, preferably 1.2 to 3.0, the specific noise value could be significantly reduced.

As described above, the reason why the optimum gap δ between the annular disks 24, 24 is increased by attaching a large number of blades 25 to the annular disk 24 is that the blade 25 is It seems that the aerodynamic performance was improved to work more efficiently, and as a result, the specific noise k _s was reduced. If the gap δ is too large, the laminar flow effect of the disk is lost and the noise increases. Therefore, there is an optimal range.

(Embodiment 7) This embodiment focuses on the Reynolds number Re of air, and focuses on the annular disc in the multilayer disc fan A.
It is characterized in that the gap δ between 24, 24 is determined.

In a sirocco fan or the like, a vortex is likely to be generated in the fluid flow in the blade portion. However, in the multi-layer disc fan A, the turbulence of the vortex can be suppressed by stacking a large number of annular discs 24. it can.

However, as shown in FIG.
If the gap δ between the circular plates 24, 24 is too wide, a vortex or turbulence will occur between the circular disks 24, 24, and as shown in FIG. If it is too narrow, no vortex or turbulence occurs between the annular disks 24, 24, but almost no air can be blown due to flow path resistance.

The applicant of the present invention has considered the gap δ capable of ensuring a sufficient air flow while preventing the occurrence of the vortex and turbulence as much as possible. By setting the value within a certain range in relation to the Reynolds number Re, as shown in FIG. 22 (b), it was found that there was no eddy or turbulence and that the air could be sent with a sufficient air volume.

That is, the multilayer disc fan A generally has the following relationship between the gap δ and the Reynolds number Re in the multilayer disc fan A.

That is, the number of annular disks 24, 24 is B,
Assuming that the air volume is Q (m ³ / min), from FIG. 23, the inlet relative speed can be obtained by the following equation, assuming that air flows into the multilayer disk fan A in the radial direction.

[0109]

(Equation 15)

At the entrance, if the air is completely slipped in the circumferential direction,

[0111]

(Equation 16)

[0112]

[Equation 17]

From this, the Reynolds number Re and the annular disks 24,2
The relationship with the gap δ between 4 is obtained by the following equation.

[0114]

(Equation 18)

In the above formula, each symbol indicates the following.

Ω _m1 : Air inlet relative angular velocity ω _u1 : Air inlet peripheral angular velocity ω _1: Air inlet relative velocity ν _: Kinematic viscosity coefficient of air r _i: Inlet radius of annular disk FIG. 24 is a graph showing the result of an experiment performed by a person while changing the gap δ between the annular disks 24, 24 when the Reynolds number Re is in the range of 200 to 10,000.

From the graph shown in FIG. 24, it can be seen that it is desirable to set the relationship between the Reynolds number Re and the gap δ in the following range in order to effectively reduce the noise level.

[0118]

[Equation 19]

The present invention has been described in detail with reference to some embodiments. However, the present invention is not limited to the above-described embodiments, and the present invention is not limited to the embodiments. The multilayer disc fan can be suitably used in a heat exchanger, a heat exchanger, and other technical fields and applications that require a quiet air blower. The shape of the wing is not limited to the streamlined one shown in the figure, but may be a cut-and-raised flat wing, a streamlined flat wing, an arc flat wing, or the like. It can be converted to a column and arranged.

[0120]

According to the present invention, in a multi-layer disk fan with wings formed by laminating a number of annular disks which are kept at a constant distance from each other, a number of blades are interposed between the annular disks, and Since at least one of the inner end and the outer end of the wing is located outside or inside by a certain distance from the inner peripheral edge or the outer peripheral edge of the annular disk, the laminar flow effect of the disk causes separation at the tips of the inner and outer wings. The turbulence caused by the turbulent flow can be effectively suppressed, and since there is no outlet speed distortion at the outer peripheral edge of the annular disk, turbulent flow noise and interference noise can be reduced, so that quiet operation is possible.

Also, a swept wing may be adopted, a line connecting the innermost end and the outermost end of the wing, and a trajectory of the fluid obtained from the circumferential speed and the radial speed of the relative speed of the fluid between the disks. Is the angle formed on the entrance side of each disk, that is, the angle of attack is 20 ° ±
By setting the angle to 15 °, the air volume can be increased while maintaining quietness.

The ratio between the circumferential pitch angle between the blades and the angle formed by the line formed by connecting the innermost end and the outermost end of the blade to the center of the annular disk is 0.5 to 1. Thereby, it is possible to take an optimal airflow path, and it is possible to increase the blowing amount while maintaining quietness.

Further, there is an optimum operating range in relation to the gap between the annular disks, the rotational speed, and the flow velocity at the disk inlet. In addition, the turbulent noise caused by the separation is suppressed, and the outlet distortion at the outer periphery of the annular disk is suppressed, so that the turbulent noise and the interference noise can be reduced, and the quiet operation becomes possible.

[0124]

[Brief description of the drawings]

FIG. 1 is a perspective view of a winged multilayer disk fan according to a first embodiment when the winged multilayer disk fan according to the present invention is used as a hot air fan.

FIG. 2 is a sectional side view of the same.

FIG. 3 is a cross-sectional view taken along line II of FIG. 2;

FIG. 4 is a perspective view of an annular disk.

FIG. 5 is a perspective view of a wing.

FIG. 6 is an explanatory diagram showing a flow velocity of an air flow at an outer peripheral edge of an annular disk.

FIG. 7 is a graph showing a specific noise value of a multi-layer disk fan with wings.

FIG. 8 is a sectional front view of a multi-layer disk fan with blades according to Embodiment 2.

FIG. 9 is a graph showing a specific noise value of a multi-layered disk fan with blades.

FIG. 10 is a sectional front view of a winged multilayer disk fan according to Embodiment 3.

FIG. 11 is an explanatory diagram showing an appropriate rear angle of attack of a blade in the multi-layered disk fan with blades according to the fourth embodiment.

FIG. 12 is an explanatory diagram showing an inappropriate wing rear angle of attack.

FIG. 13 is an explanatory diagram showing an inappropriate wing rear angle of attack.

FIG. 14 is a graph showing the relationship between the angle of attack and the specific noise.

FIG. 15 is an explanatory diagram showing an inappropriate wing rear angle of attack.

FIG. 16 is an explanatory view of a multi-layered disk fan with blades having blades with no tilt angle.

FIG. 17 is an explanatory diagram of a modified example of a wing having a rear angle of attack.

FIG. 18 is an explanatory diagram of a modified example of a wing having a rear angle of attack.

FIG. 19 is an enlarged explanatory view of a main part of a multi-layer disk fan with wings according to a fifth embodiment.

FIG. 20 is a graph showing the relationship between the ratio of the circumferential pitch of the blades to the blade mounting angle and the specific noise.

FIG. 21 is a graph showing a relationship between a circumferential speed and the like and specific noise according to the sixth embodiment.

FIG. 22 is an explanatory diagram of an airflow flowing through a gap between annular disks according to the seventh embodiment.

FIG. 23 is an explanatory diagram showing a flow of an air flow.

FIG. 24 is a graph showing a relationship between Reynolds number and specific noise.

FIG. 25 is a cross-sectional side view of a conventional multilayer disk fan.

26 is a sectional view taken along line II-II in FIG.

FIG. 27 is an explanatory diagram showing a flow of an air flow on an annular disk.

FIG. 28 is an explanatory diagram showing a velocity distribution of an air flow between annular disks.

[Explanation of symbols]

 A Multi-layered disk fan with wings 20 Fan blades 24 Annular disk 25 blades

──────────────────────────────────────────────────続 き Continuation of the front page (56) References Japanese Utility Model Showa 50-3110 (JP, U) (58) Field surveyed (Int. Cl. ⁶ , DB name) F04D 17/08 F04D 29/28

Claims (9)

(57) [Claims] 1. An annular disk formed by laminating a number of annular disks (24) having a constant gap (δ) therebetween.
(24) In a multi-layered winged disk fan having a number of wings (25) interposed between (24), the tip of the wing (25) in the outer circumferential direction is an annular disk (24).
A multi-layer disk fan with wings, wherein the fan is configured to be located at a fixed distance (S ₁ ) inside the outer peripheral edge of the blade and the distance (S ₁ ) is a value represented by the following equation. (Equation 1) 2. An annular disk formed by laminating a number of annular disks (24) having a constant gap (δ) therebetween.
(24) In a multi-layered winged disk fan having a number of wings (25) interposed between (24), the outer circumferential end of the wing (25) is attached to the annular disk (2).
4) is located at a fixed distance (S ₁ ) inside the outer peripheral edge, and the inner circumferential end of the wing (25) is fixed at a fixed distance ( A multi-layer winged disk fan characterized by being configured to be located outside by only S ₂ ) and having a distance (S ₁ ) represented by the following formula: (Equation 1) 3. An annular disk formed by laminating a number of annular disks (24) having a constant gap (δ) therebetween.
(24) In a multi-layered winged disk fan having a number of wings (25) interposed between (24), the inner circumferential end of the wing (25) is connected to an annular disk (24).
Of a certain distance from the inner circumferential edge (S ₂₎ by a distance as well as configured to be positioned outside (S _2), in relation to the blade inner edge radius (r ₂₎ of the annular circular plate (24), 0.025 < A multi-layer disk fan with wings, wherein S ₂ / r ₂ <0.125. 4. An annular disk formed by laminating a number of annular disks (24) having a constant gap (δ) therebetween.
(24) In a multi-layered winged disk fan having a number of wings (25) interposed between (24), the outer circumferential end of the wing (25) is attached to an annular disk (2).
4) is located at a fixed distance (S ₁ ) inside the outer peripheral edge, and the inner circumferential end of the wing (25) is fixed at a fixed distance ( distance as well as configured to S ₂₎ only located outside the (S _2), in relation to the blade inner edge radius of the annular disc _{(24) (r 2),} 0.025 <S 2 / r 2 <0.
A multi-layer disk fan with wings, characterized by the fact that it is 125. 5. The multi-layer disk fan with wings according to claim 1, wherein the mounting direction of the wings (25) is a rearward wing. 6. A line (L) connecting the innermost and outermost ends of the wing (25).
And the trajectory of the fluid obtained from the circumferential velocity and the radial velocity of the relative velocity of the fluid flowing between the annular disks (24) and (24)
(R) is the angle of attack that is the angle made by the inner tip of the wing (25).
2. The method according to claim 1, wherein (θ) is set to 20 ° ± 15 °.
The multi-layer disk fan with wings according to any one of claims 1 to 4. 7. A circumferential pitch angle between the blades (25) (25) (α)
And the angle (β) formed by a line (L ₃ ) (L ₄ ) formed by connecting the innermost end and the outermost end of the wing (25) to the center of the annular disk (24),
7. The method according to claim 1, wherein 0.5 <.beta ./. Alpha. <1.
The multilayer disk fan with wings according to any one of claims 1 to 7. 8. The apparatus according to claim 1, wherein the gap (δ) between the annular disks (24) is a value represented by the following equation.
The multi-layer disk fan with wings according to any one of claims. (Equation 2) 9. A gap (δ) between the annular disks (24) and (24) has a value represented by the following equation.
The multi-layer disk fan with wings according to any one of claims. (Equation 3)