JP3203308B2 - Axial blower - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an axial blower used for an outdoor unit of an air conditioner, a ventilation device, and the like.

[0002]

2. Description of the Related Art FIG. 14 shows a wing portion of a conventional axial blower.
It is explanatory drawing which shows the state of the airflow around one blade among several blades in a no-load state. FIG. 15 is an explanatory diagram showing the state of the airflow around the wing under the load of FIG. 14.
In the figure, 1 is a blade, 1s is a cross section of the blade 1 cut in a cylindrical state concentric with the rotation axis, 1n is a negative pressure surface, 1p is a pressure surface, 1
f is the leading edge of the wing 1, 1 b is the trailing edge of the wing 1, 1 h is the chord of the section 1 s of the pressure surface 1 p of the wing 1, 2 is the boss, 2 j is the rotation axis, 3 w is the relative inflow, 4w mainstream flow, 7r is separation turbulence, α ₀ and α ₁ are angles of attack between the direction of the relative inflow 3w and the chord line 1h, and R is a rotation direction.

The axial blower has a configuration in which a plurality of blades 1 shown in FIG. The main flow 4w is relatively moved from the leading edge 1f to the trailing edge 1b of the blade 1f by rotating the blade 1 in the R direction about the rotation axis 2j.
Flows in the direction of 14, when operating the axial-flow fan in a state of no load, since a small angle of attack alpha ₀ relative incoming flows 3w relative chord line 1h, the main flow 4w wings 1
Flows smoothly along the negative pressure surface 1n. However, under the condition that a load such as an outdoor unit of an air conditioner is arranged on the upstream side of the axial blower, the airflow decreases even if the rotational speed of the axial blower is the same, and as shown in FIG. angle of attack alpha ₁ formed by the relative incoming flows 3w viewed from chord line 1h and wings 1 increases. In the case of such a flow, the direction of the main flow 4w is
Can not follow the negative pressure surface 1n, and the separation 7r
Are generated from the leading edge 1f of the suction surface 1n of the blade 1 to the suction surface 1n side. The separation turbulence 7r collides with the suction surface 1n of the blade 1 to increase the pressure fluctuation, thereby causing a phenomenon that noise is generated.

FIG. 16 is a diagram showing a utility model utility model disclosed in Japanese Utility Model Publication No. 58-4239.
No. 8 is a plan view of a wing portion of the axial flow fan, and FIG. 17 is a cross-sectional view of the wing portion. In the figure, 11 is a blade, 11n is a suction surface, 14w is a mainstream flow, and 16 is a blade 11
15r, a triangular protrusion protruding from the negative pressure surface 11n
Is a vortex generated at the rear of the projection 16.

FIG. 18 shows a triangular projection 16 shown in FIG.
FIG. 4 is an explanatory diagram of a mainstream flow 14w around a circle. As shown in FIG. 18, the direction of each projection 16 is arranged with one vertex facing upstream with respect to the direction of the mainstream flow 14 w,
A vortex 15r is generated on the rear surface of the protrusion 16, and the force of the vortex 15r sprayed on the negative pressure surface 11n of the blade 11 is given, thereby suppressing the deterioration of the blowing performance.

[0006]

In the conventional axial blower shown in FIG. 16 in which a large number of triangular projections are provided on the suction surface of the blade, vortices are generated on both sides of the downstream side of the triangular projections. However, the direction of the vortex at both ends is opposite to each other, so they are offset and weakened where the flow collides, and the force that stabilizes the boundary layer on the suction surface of the blade Decrease. Also, the size of the vortex could not be increased due to the proximity of the vortex, and the region where the flow sprayed on the wing surface occurred was limited only after the protrusion. For this reason, there is a problem that the noise suppression effect cannot be obtained unless many projections are provided. Further, providing many projections on the wing surface has a problem that the cost is high and the productivity is low.

SUMMARY OF THE INVENTION The present invention has been made to solve the above problems, and an object of the present invention is to provide a low-noise axial-flow blower in which an increase in noise due to turbulence generated from a leading edge of a blade is suppressed. And

[0008]

According to a first aspect of the present invention, there is provided an axial blower having a steering angle with respect to a relative inflow near a leading edge of a suction surface of a plurality of blades provided on an outer periphery of a boss. The boundary layer stabilizing blade is provided such that the outer peripheral side surface of the boss of the boundary layer stabilizing blade having the above faces the upstream side of the relative inflow flow, and the outer peripheral side surface faces the downstream side of the relative inflow flow.

An axial blower according to a second aspect of the present invention comprises:
On the suction surface of the plurality of blades provided on the outer periphery of the boss portion, the outer peripheral side surface of the boss of the boundary layer stabilizing blades having a steering angle with respect to the relative inflow flows is directed to the upstream side, and the outer peripheral side surface of the blade is Boundary layer stabilizers are provided so as to face the downstream side of the relative inflow.

An axial blower according to a third aspect of the present invention comprises :
Their Re respectively is obtained by placing one or a plurality of boundary layer stability wings bosses near the outer periphery of the suction surface of the blade.

An axial blower according to a fourth aspect of the present invention comprises:
On the suction surface of each wing provided on the outer periphery of the boss ,
The upstream height of the relative inflow is lower than the downstream height
One or a plurality of well-formed boundary layer stabilizing wings are provided .

An axial blower according to a fifth aspect of the present invention comprises:
Boundary layer stabilizing blades are installed at a slant downstream in the relative inflow direction.
Is placed .

[0013]

[0014]

BEST MODE FOR CARRYING OUT THE INVENTION

Embodiment 1 FIG. FIG. 1 shows Embodiment 1 of the present invention.
It is a top view which shows the structure of the wing | blade part of the axial flow blower of FIG. FIG.
Is an explanatory diagram showing a steering angle. FIG. 3 is an explanatory diagram showing the situation of the flow around the wing. Only one wing is shown. In the figure, 21 is the wing, 21f is the leading edge of the wing, 21b
Is the trailing edge of the wing, 21q is the outer edge of the wing, 22 is the boss, 2
2j is the rotation axis, 21p is the pressure surface of the wing 21, 21n is the wing 2
Reference numeral 1 denotes a negative pressure surface, 26 denotes a boundary layer stabilizing blade, 26f denotes a surface of the boundary layer stabilizing blade 26 on the boss 22 side, 26b denotes a surface of the boundary layer stabilizing blade 26 on the blade outer periphery 21q side, and 26h denotes a boundary facing the boss portion 22. The chord line of the inner side surface 21f of the layer stabilizing blade 21, 23w is a relative inflow, 24w is a main flow, and 25r is a boundary layer stabilizing blade 26.
The vortex, R, generated behind the outer surface 26b of the boss is a boundary layer stabilizer having a steering angle with respect to the relative inflow to the suction surface of each blade in the rotational direction. The boundary layer stabilizing blade is arranged such that the side surface on the outer peripheral side of the blade faces the downstream side of the relative inflow.

The axial blower includes a plurality of blades 21 and a boss 22.
By rotating in the R direction about the rotation axis 22j, a flow is generated in the direction from the leading edge 21f of the blade to the trailing edge 21b. The large flow around the axial blower as viewed from the rotating blades 21 is referred to as a main flow 24w, and the airflow of the portion flowing into the axial blower therein is referred to as a relative inflow 23w.
In FIG. 2, the inner side surface 26f of the boundary layer stabilizing blade 26 is installed at a steering angle β formed by the relative inflow 23w and the boundary layer stabilizing blade 26h. In this configuration, as shown in FIG. 3, in the portion of the boundary layer stabilizing blade 26, the outer surface 26 b side has a lower static pressure than the inner surface 26 f side, and collides with the boundary layer stabilizing blade 26 to cause the boundary layer stabilizing blade 26. The air flow that has passed over the vortex becomes a flow that is swept in the direction of spraying on the negative pressure surface 21n of the wing 21, and the vortex 2
5r is generated and flows to the trailing edge 21b. This vortex 25r
Presses the main flow 24w flowing in the direction from the leading edge 21f to the trailing edge 21b of the blade 21 to the suction surface 21n of the blade 21 to stabilize the boundary layer.

[0016] forcing the main flow on the negative pressure surface 21n of the blade 21 as shown in FIG big angle of attack alpha ₁ relative to the wing 1 of the chord line 1h shown in FIG. 15, even when the relative incoming flows 3w has flowed 3 24w And the peeling turbulence 7r in FIG.
It works to control. The vortex 25r generated in the boundary layer stabilizing wing 26 is a single vortex, and is not weakened by the vortex colliding with the vortex as in the conventional example shown in FIG. Inner surface 26f and outer surface 2
The static pressure difference of the blade 6b is also superimposed and gives a force to wind in, so that it becomes a strong vortex, and a large force to blow against the suction surface 21n of the blade 21 is obtained. The chord of the blade 1 of the conventional axial flow blower shown in FIG. large peeling at the leading edge 1f of the blade 1 in the angle of attack alpha ₁ relative incoming flows generated when a flow disturbance 7r is suppressed to the line 1h, the noise is reduced.

In this type of axial blower, as the load increases, the angle of attack of the relative inflow 23w increases, and separation from the front edge 21f of the axial blower starts to occur.
Therefore, when the boundary layer stabilizing blades 26 are arranged near the leading edge 21f of the suction surface 21n of each blade 21, the vortex generated by the boundary layer stabilizing blades 26 can directly suppress the separation turbulence generated from the leading edge 21f. , The main flow 24w is forced to follow the negative pressure surface 21n side, and the effect of reducing noise is increased.

Since the rotational speed of the blade 21 of the axial blower is smaller on the outer periphery of the boss 22 than on the outer periphery 21q of the boss 22, the angle of attack of the relative inflow 23w tends to be larger on the boss 22 side. Therefore, the separation turbulence is likely to occur from the outer peripheral side of the boss 22. Therefore, by disposing the boundary layer stabilizing wings 26 on the outer peripheral side of the boss 22 of the suction surface 21n of each wing 21, the separation turbulence is directly suppressed and the noise is reduced. Increase.

Although the illustrated boundary layer stabilizing blade 26 has been described as having a curved plate shape protruding toward the outer periphery, the same effect can be obtained by forming the boundary layer stabilizing blade into a flat plate shape 36 as shown in FIG. With a curved plate shape, the direction of the inflow relative to the rotating boundary layer stabilizing blades 26 is substantially the same in each part of the boundary layer stabilizing blades 26, and the turbulence of the airflow is reduced. The flat plate shape has the advantage that the turbulence of the air flow is slightly increased but the workability is improved.

Embodiment 2 Embodiment 1 FIG. In the above, one boundary layer stabilizing blade 26 is provided for each of the plurality of blades 21. However, in the case where the blades become large due to the size of the blades and the capacity of the axial flow blower, etc., FIG. By providing a plurality of boundary layer stabilizing wings 26c and 26d in this manner, an axial blower with similarly reduced noise can be obtained even when the capacity is large. As shown in FIG. 5, when the wing rotates,
Vortices 25r are generated on the outer surface behind each of the boundary layer stabilizing wings 26c and 26d, and the turbulence is suppressed over the entire surface of the wings, thereby suppressing an increase in noise.

Embodiment 3 FIG. FIG. 7 is an explanatory view showing the configuration of the axial blower of FIG. 1, and FIG. Only one wing is shown. In the figure, the wing 21 and the boss 22 are the same as those in the first embodiment.
-Embodiment 2. 45r is a vortex, 46
Is the boundary layer stable wing, and 46f is the boss 22 of the boundary layer stable wing 46
A surface 46b is a surface on the blade outer periphery 21q side of the boundary layer stable blade 46. The shape of the upper side of the boundary layer stabilizing blade 46 is such that the upstream height of the relative inflow is lower than the downstream height,
It is arranged on the suction surface 21 of the blade 21.

As shown in FIG. 7, the height of the boundary layer stabilizing blades 46 increases from the upstream side to the downstream side, so that the surface 46b on the blade outer peripheral side and the surface 46f on the boss outer peripheral side of the boundary layer stabilizing blades 46. And the static pressure difference gradually increases. For this reason, a stable vortex can be obtained by gradually increasing the force that causes the vortex 45r to collide with the boundary layer stabilizing wing 46 and become involved.

The central axis of the generated vortex flow 45r also moves away from the wing surface toward the downstream similarly to the inclination of the boundary layer stabilizing wing, so that the vortex grows largely without being restricted by the wing surface 21n, and the strong vortex flow 45r Can be obtained. For this reason, the force for pressing the main flow 24w shown in FIG. 3 against the blade suction surface 21n is also stably strong, the turbulence is unlikely to occur from the blade leading edge 21f, and the pressure fluctuation on the blade surface is reduced, thereby reducing the pressure. A noise axial blower can be obtained.

Embodiment 4 FIG. And FIG. 9 is a cross-sectional view of the blade.
FIG. 10 is an explanatory diagram showing the velocity vector of the airflow on the boundary layer stable wing. Only one wing is shown. In the figure, the wing 21 portion and the boss 22 portion are the same as those in the above-described embodiment, and 56 is a boundary layer stabilizing wing arranged in an inclined manner, 56
f is a surface of the boundary layer stabilizing blade 56 on the boss 22 side, 56b is a surface of the boundary layer stabilizing blade 56 on the blade outer periphery 21q side, 53w is a relative inflow flow, 53g is a relative inflow flow 53 of the boundary layer stabilization blade 56.
A velocity component of w, 53e is a vertical velocity component of 53g with respect to the surface 56f of the boundary layer stable wing 56, and 53k is a horizontal velocity component of 53g with respect to the surface 56f of the boundary layer stable wing 56. The boundary layer stabilizing blades 56 are arranged at an angle downstream of the relative inflow 53w.

As shown in FIG. 10, the velocity component 5 when the relative inflow 53w flows into the inclined boundary layer stabilizer 56
3g can be decomposed into a component 53e perpendicular to the surface 56f of the boundary layer stabilizing blade 56 and a component 53k parallel to the boundary layer stabilizing blade 56.
A speed component 53k is generated in a direction over the sixth vehicle.

By inclining the boundary layer stabilizing blades 56 to the downstream side of the relative inflow flow 53w, the relative inflow flow 53w colliding with the boundary layer stabilizing blades 56 can easily get over the boundary layer stabilizing blades 56, The vortex 53r generated on the back side of the layer stabilizing blade 56 becomes a strong vortex, and the negative pressure surface 2 of the blade 21
It acts to strongly suppress the separation turbulence generated in 1n. Therefore, the pressure fluctuation of the negative pressure surface of the wing 21 is suppressed,
Noise reduction can be realized more effectively.

As shown in FIG. 11, the space between the boundary layer stabilizing wings 56 and the blade surface 21n in FIG. 9 is filled to form the boundary layer stabilizing wings 66, so that the airflow in this space is reduced. Disturbance is eliminated, and the effect of the inclined arrangement increases.

Embodiment 5 Embodiment 5 FIG. In the above, the height of the upstream side of the boundary layer stabilizing blade is lower than the height of the downstream side, and the steering wheel has a steering angle with respect to the relative inflow and is arranged in an inclined manner. FIG. 12 is a plan view of the configuration, and FIG. 13 is a perspective view. In the figure, the wing 21 portion and the boss 22 portion are the same as those of the other embodiments described above, 76 is a boundary layer stabilizing wing arranged in an inclined manner, and 73w is a relative inflow. Boundary layer stabilizing wing 76
Are arranged with a steering angle β with respect to the direction of the relative inflow 73w and an inclination angle θ with respect to the direction of the rotation axis.

With this configuration, since the height of the boundary layer stabilizing wings 21 is low and inclined, the relative inflow 73 w colliding with the boundary layer stabilizing wings 76 can easily get over the boundary layer stabilizing wings 76, and The vortex generated on the back side of the layer stabilizing wing 76 does not become too large in the vicinity of the leading edge 21f, but gradually increases from the leading edge 21f toward the trailing edge 21b. Separation turbulence does not easily occur in the vicinity of the portion, and it acts to press against the negative pressure surface 21n of the blade 21 as it approaches the trailing edge portion 21b, which has the effect of reducing noise.

[0030]

Effects of the Invention axial blower according to claim 1 of the present invention, prior to the suction side of the blade of Taso respectively provided in the boss portion outer periphery
On the edge , the boundary layer stabilizing wing with a steering angle to the relative inflow flow faces the outer peripheral side of the boss toward the upstream side of the relative inflow flow,
Since the boundary layer stabilizing blade is provided so that the side surface on the blade outer circumferential side is directed to the downstream side of the relative inflow, the load on the axial blower increases, and the separation turbulence generated on the blade is suppressed even when the angle of attack increases, Noise can be reduced.

An axial blower according to a second aspect of the present invention comprises:
A plurality of boundary layer stabilizing wings with a steering angle to the relative inflow are provided on the suction surface of each wing provided on the outer periphery of the boss, so even if the wing area is large, the separation turbulence that occurs on the wings It is suppressed and noise can be reduced.

An axial blower according to a third aspect of the present invention comprises :
It to the boss near the outer periphery of the suction surface of the blade of respectively the boundary layer stability wings
Because of the arrangement, it is possible to suppress the occurrence of direct peeling turbulence and reduce noise.

An axial blower according to a fourth aspect of the present invention comprises:
On the suction surface of each wing provided on the outer periphery of the boss ,
The upstream height of the relative inflow is lower than the downstream height
The stable boundary wing is formed ,
The generated vortex can be generated stably and strongly, and noise can be significantly suppressed .

An axial blower according to a fifth aspect of the present invention comprises:
The boundary layer stabilization wing is inclined downstream in the relative inflow direction.
Since the arranged, can be generated stably <br/> strong vortices without deteriorating the blowing performance, it can be remarkably suppressed noise.

[0035]

[Brief description of the drawings]

FIG. 1 shows an axial blower according to a first embodiment of the present invention. It is a top view which shows the structure of.

FIG. 2 is an explanatory diagram showing the bending angle of the boundary layer stabilizer of FIG.

FIG. 3 is an explanatory diagram showing a state of a flow around a wing in FIG. 1;

FIG. 4 is a configuration diagram when the boundary layer stabilizing wing has a flat plate shape.

FIG. 5 is a configuration diagram in which a plurality of boundary layer stabilizing wings are provided in the configuration of FIG. 1;

FIG. 6 is a third embodiment of an axial blower according to the present invention. It is a top view which shows the structure of.

FIG. 7 is an explanatory diagram of a vortex generation state of a boundary layer stabilizing wing having a changed height.

FIG. 8 is a fourth embodiment of the axial blower according to the present invention. It is a top view which shows the structure of.

FIG. 9 is a sectional view of FIG.

FIG. 10 is an explanatory diagram showing a velocity vector of an airflow on a boundary layer stable wing.

FIG. 11 is a cross-sectional view in which a space between a boundary layer stabilizing wing and a wing surface that are arranged in an inclined manner is filled.

Fig. 12 is an axial blower according to a fifth embodiment of the present invention. It is a top view which shows the structure of.

FIG. 13 is a perspective view of FIG.

FIG. 14 is an explanatory diagram showing a state of airflow of a conventional axial blower.

FIG. 15 is an explanatory diagram showing a state of airflow of a conventional axial blower.

FIG. 16 is a plan view showing a configuration of a conventional axial blower.

FIG. 17 is a partial cross-sectional view showing a state of airflow of the axial blower of FIG.

FIG. 18 is an explanatory diagram showing a state of airflow around a protrusion provided on the wing of FIG. 16;

[Explanation of symbols]

1 blade, 1f leading edge, 1b trailing edge, 1q blade outer periphery, 1p pressure surface, 1n suction surface, 1h chord line, 1s
Wing cross section, 2 boss, 2j rotation axis, 3w relative inflow, 4w main flow, 7r separation turbulence, 11 blades,
11n suction surface, 13w relative inflow, 15r vortex,
16 Projection, 21 blades, 21f leading edge, 21b trailing edge, 21q blade outer periphery, 21p pressure surface, 21n
Suction surface, 26h chord line of boundary layer stabilizing wing, 22 boss, 22j rotation axis, 23w relative inflow, 24w
Main flow, 25r vortex, 26 boundary layer stabilizing wing, 26f
Surface of the boundary layer stabilizing blade 26 on the boss 22 side, 26b Surface of the boundary layer stabilizing blade 26 on the blade outer periphery 21q side, 26c Boundary layer stabilizing blade, 26d Boundary layer stabilizing blade, 26h Boundary layer stabilizing chord line, 36 Boundary layer stabilizing Wing, 43w relative inflow, 45
r vortex, 46 boundary layer stabilizer, 46f boundary layer stabilizer 4
6, the surface of the boss 22 side, 46b the surface of the boundary layer stabilizing blade 46 on the blade outer periphery 21q side, 53w relative inflow, 53g velocity vector of the relative inflow at the boundary layer stabilizing blade, 53e relative inflow to the boundary layer stabilizing blade Vertical component of velocity vector, 53k parallel component of velocity vector of inflow relative to boundary layer stabilizer, 56 boundary layer stabilizer, 56f
Surface of the boundary layer stabilizing wing 56 on the boss 22 side, 56b surface of the boundary layer stabilizing wing 56 on the blade outer periphery 21q side, 66 boundary layer stabilizing wing,
76w relative inflow, 76 boundary layer stabilizer, α angle of attack, α ₀ angle of attack, α ₁ angle of attack, β steering angle, θ tilt angle, R rotation direction.

──────────────────────────────────────────────────続 き Continuation of the front page (72) Inventor Ken Morishita 2-3-2 Marunouchi, Chiyoda-ku, Tokyo Inside Mitsubishi Electric Corporation (56) References JP-A-62-284999 (JP, A) JP-A Sho 57-191495 (JP, A) Japanese Utility Model Showa 60-137200 (JP, U) Japanese Utility Model Showa 54-34107 (JP, U) Japanese Utility Model Showa 52-115905 (JP, U) (58) Fields surveyed (Int. Cl. ⁷ , DB name) F04D 29/38

Claims (5)

(57) [Claims] 1. A axial-flow fan having a plurality of vanes provided in the boss and the boss portion periphery, the leading edge side of the suction surface of each blade, lifting Chi the steering angle with respect to the relative incoming flows ,
An axial-flow blower having a boundary layer stabilizing blade provided such that a side surface on an outer peripheral side of a boss faces an upstream side of a relative inflow flow and a side surface on an outer peripheral side of a blade faces a downstream side of the relative inflow flow. 2. The axial blower according to claim 1, wherein a plurality of boundary layer stabilizing blades are provided on a suction surface of each blade. 3. A boundary layer stability wing claim 1 or, characterized in that arranged on the suction surface of the boss near the outer periphery of each blade
An axial blower according to claim 2 . 4. The boundary layer stabilizing wing is provided with a relative inflow flow on the upper side.
The axial flow blower according to any one of claims 1 to 3 , wherein the height on the upstream side is formed lower than the height on the downstream side . 5. The boundary layer stabilizing wing is located downstream of the relative inflow.
The axial flow blower according to any one of claims 1 to 4 , wherein the axial flow blower is arranged at an angle.