阅读说明：本技术 导风板组件和空调器 (Air deflector assembly and air conditioner ) 是由 郜哲明 于 2019-11-29 设计创作，主要内容包括：本发明公开一种导风板组件和空调器,其中导风板组件包括导风板和机翼板,所述导风板具有导风面,导风面具有相对设置的第一边缘和第二边缘,所述第一边缘和所述第二边缘均沿所述导风板长度方向延伸,所述第一边缘和所述第二边缘所在平面为S<Sub>1</Sub>；所述机翼板通过连接件倾斜安装于所述导风面,所述机翼板具有前缘、后缘、腹面和背面,所述腹面和所述背面均连接所述前缘和所述后缘,所述前缘与所述导风面之间具有过风间隙,所述前缘与所述导风面之间的间距小于所述后缘与所述导风面之间的间距,所述前缘和所述后缘所在平面为S<Sub>2</Sub>,平面S<Sub>1</Sub>与平面S<Sub>2</Sub>夹角α不小于35°,且不大于55°。本发明的技术方案可以将气流轻柔化,实现无风感或者微风感效果。(The invention discloses an air guide plate assembly and an air conditioner, wherein the air guide plate assembly comprises an air guide plate and a wing plate, the air guide plate is provided with an air guide surface, the air guide surface is provided with a first edge and a second edge which are oppositely arranged, the first edge and the second edge both extend along the length direction of the air guide plate, and the plane where the first edge and the second edge are located is S 1 (ii) a The wing plate is obliquely arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a back surface, the ventral surface and the back surface are connected with the front edge and the rear edge, an air passing gap is formed between the front edge and the air guide surface, the distance between the front edge and the air guide surface is smaller than that between the rear edge and the air guide surface, and the plane where the front edge and the rear edge are located is S 2 Plane S 1 And plane S 2 The included angle α is not less than 35 degrees and not more than 55 degreesNo wind sense or slight wind sense effect exists.)

1. An air deflection assembly, comprising:

the air guide plate is provided with an air guide surface, the air guide surface is provided with a first edge and a second edge which are oppositely arranged, the first edge and the second edge both extend along the length direction of the air guide plate, and the plane where the first edge and the second edge are located is S₁；

The wing plate is obliquely arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a back surface, the ventral surface and the back surface are connected with the front edge and the rear edge, an air passing gap is formed between the front edge and the air guide surface, the distance between the front edge and the air guide surface is smaller than the distance between the rear edge and the air guide surface, and the plane where the front edge and the rear edge are located is S₂Plane S₁And plane S₂Included angle α is not less than 35 ° and not more than 55 °.

2. The air deflection assembly of claim 1, wherein the ventral surface is located between the dorsal surface and the air deflection surface.

3. The air deflection assembly of claim 1, wherein the back surface is positioned between the ventral surface and the air deflection surface.

4. The air deflection assembly of claim 3, wherein the wing panel has a chord length C and a span L, and wherein C/L is not less than 1.5 and not greater than 4.

5. The air deflection assembly of claim 4, wherein the distance between adjacent airfoils is D, and the span of the airfoils is L, and D is not less than 1.3L and not more than 2L.

6. The air deflection assembly of claim 5, wherein the wing panel has a wing head, the leading edge being located at the wing head, the wing head being radiused.

7. The air deflection assembly of claim 6, wherein the wing plate further comprises a wing tail, wherein the trailing edge is positioned on the wing tail, and wherein the wing tail is in a wedge configuration.

8. The air deflection assembly of claim 5, wherein said back surface has an arc length H corresponding to an airfoil section of said wing panel₁The arc length or the straight line length of the ventral surface corresponding to the airfoil section of the wing plate is H₂，H₁Greater than H₂。

9. An air deflection assembly according to any one of claims 1 to 8, wherein the distance between the leading edge and the maximum thickness of the wing panel is less than the distance between the trailing edge and the maximum thickness of the wing panel.

10. The air deflection assembly of claim 9, wherein the plurality of wing plates are spaced apart along the length of the air deflection.

11. The air deflection assembly of claim 10, wherein the connector is coupled to the back surface.

12. The air deflection assembly of claim 11, wherein the connector is configured as a tab that extends across the width of the air deflection.

13. An air deflection assembly according to any one of claims 1 to 8, wherein the rear face is convexly curved and the ventral face is planar or convexly curved.

14. An air conditioner having an air outlet, wherein the air outlet is provided with an air deflector assembly as claimed in any one of claims 1 to 13.

Technical Field

The invention relates to the technical field of air conditioners, in particular to an air deflector assembly and an air conditioner.

Background

In the air conditioner, the air deflector arranged at the air outlet mainly adopts an air deflector which forms a certain angle with the air supply flow, and the air supply direction is controlled by blocking and guiding.

However, when the air deflector is used for blowing air, the air flow velocity is high, cold air is easily blown directly, and discomfort and even cold of a user are caused.

The current no wind-sensing air conditioner mainly through set up the micropore on the aviation baffle, through stepping down the acceleration rate to the air current, makes the blowout of stranded air current from the micropore, forms the high-speed disturbance source in many places in the air outlet region, reaches the quick mixing of air outlet air current and environment air current, reaches and reduces air conditioner air-out distance, keeps sufficient refrigeration ability simultaneously.

Because the wind resistance of the existing microporous air deflector is large, when the wind quantity is large, the air deflector is limited by the air deflector, the airflow is difficult to flow out of the air deflector rapidly, the wind power waste is caused, and the requirement of no wind sense is difficult to achieve rapidly.

Disclosure of Invention

The invention mainly aims to provide an air deflector component, and aims to solve the technical problems of large wind resistance, no wind feeling effect and poor performance of the existing microporous air deflector.

To solve the above problem, the present invention provides an air deflector assembly, comprising:

the air guide plate is provided with an air guide surface, the air guide surface is provided with a first edge and a second edge which are oppositely arranged, the first edge and the second edge both extend along the length direction of the air guide plate, and the plane where the first edge and the second edge are located is S₁；

The wing plate is obliquely arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a back surface, the ventral surface and the back surface are connected with the front edge and the rear edge, an air passing gap is formed between the front edge and the air guide surface, the distance between the front edge and the air guide surface is smaller than the distance between the rear edge and the air guide surface, and the plane where the front edge and the rear edge are located is S₂Plane S₁And plane S₂Included angle α is not less than 35 ° and not more than 55 °.

In one embodiment, the ventral surface is located between the dorsal surface and the air guiding surface.

In one embodiment, the back surface is located between the ventral surface and the wind guide surface.

In one embodiment, the chord length of the wing plate is C, the wing span of the wing plate is L, and the value of C/L is not less than 1.5 and not more than 4.

In one embodiment, the distance between two adjacent wing plates is D, the wing span of the wing plates is L, and D is not less than 1.3L and not more than 2L.

In an embodiment, the wing panel has a nose at which the leading edge is located, the nose being radiused.

In one embodiment, the wing plate further has a wing tail, the trailing edge being located at the wing tail, the wing tail being arranged in a wedge shape.

In one embodiment, the arc length of the back surface corresponding to the airfoil section of the wing plate is H₁The arc length or the straight line length of the ventral surface corresponding to the airfoil section of the wing plate is H₂，H₁Greater than H₂。

In an embodiment, the distance of the leading edge from the maximum thickness of the wing panel is less than the distance of the trailing edge from the maximum thickness of the wing panel.

In one embodiment, the number of the wing plates is multiple, and the wing plates are arranged at intervals along the length direction of the air deflector.

In one embodiment, the connector is connected to the back side.

In an embodiment, the connecting member is disposed in a sheet shape, and the connecting member extends along the width direction of the air deflector.

In one embodiment, the back surface is a convex arc surface, and the ventral surface is a flat surface or a convex arc surface.

The invention also discloses an air conditioner which is provided with an air outlet, wherein an air guide plate assembly is arranged at the air outlet and comprises an air guide plate and a wing plate, the air guide plate is provided with an air guide surface, the air guide surface is provided with a first edge and a second edge which are oppositely arranged, the first edge and the second edge both extend along the length direction of the air guide plate, and the plane where the first edge and the second edge are located is S₁(ii) a The wing plate is obliquely arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a back surface, the ventral surface and the back surface are connected with the front edge and the rear edge, and the front edge and the guide surface are connectedThe wind guide surface is provided with a wind passing gap, the distance between the front edge and the wind guide surface is smaller than the distance between the rear edge and the wind guide surface, and the plane where the front edge and the rear edge are located is S₂Plane S₁And plane S₂Included angle α is not less than 35 ° and not more than 55 °.

According to the technical scheme, the wing plate is arranged on the air deflector, when airflow flows to the rear edge of the wing plate along the front edge of the wing plate, a vortex is formed at the rear edge of the wing plate, the radius of the formed vortex is gradually enlarged in the subsequent operation process, and the vortex speed is gradually reduced, so that rapid heat transfer can be realized, the airflow is softened lightly, and the effect of no wind sensation or slight wind sensation is realized.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

FIG. 1 is a schematic structural view (viewed along the direction of airflow) of an embodiment of an air deflector assembly according to the present invention;

fig. 2 is a schematic structural view of the air deflection assembly shown in fig. 1 from another perspective;

fig. 3 is a schematic structural view of another embodiment of the air deflection assembly in fig. 1;

FIG. 4 is a front view of the air deflection assembly of FIG. 2;

FIG. 5 is a cross-sectional view of the air deflection assembly of FIG. 4 taken along line A-A;

FIG. 6 is a comparison of the distance from the leading and trailing edges of the wing panel of FIG. 5 to the maximum thickness of the wing panel;

FIG. 7 is a comparison of the back arc length and ventral arc length of the wing plate of FIG. 6;

FIG. 8 is a perspective view of the wing plate of FIG. 1;

FIG. 9 is a schematic view of the flow field of the airflow from the leading edge to the trailing edge of the wing panel;

fig. 10a is a schematic view of the airflow field with the airflow flowing backwards from the leading edge of the wing plate, wherein α is 15 °;

fig. 10b is a schematic view of the airflow field with the airflow flowing backwards from the leading edge of the wing plate, wherein α is 25 °;

fig. 10c is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 35 °;

fig. 10d is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 45 °;

fig. 10e is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 55 °;

fig. 10f is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 60 °;

fig. 10g is a schematic view of the airflow field with the airflow flowing backwards from the leading edge of the wing plate, wherein α is 65 °;

FIG. 10h is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 70;

FIG. 11a is a plot of the profile of the flow vorticity for a flow flowing aft from the leading edge of the wing plate, where α is 15 °;

FIG. 11b is a plot of the profile of the flow vorticity for a flow flowing aft from the leading edge of the wing plate, where α is 25 °;

FIG. 11c is a plot of the profile of the flow vorticity for a flow flowing aft from the leading edge of the wing plate, where α is 35;

FIG. 11d is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 45;

FIG. 11e is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 55;

FIG. 11f is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 60;

FIG. 11g is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 65;

FIG. 11h is a plot of the flow vorticity contour profile for the flow aft from the leading edge of the wing plate, where α is 70;

FIG. 12 is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate; wherein C/L ═ 2;

FIG. 13 is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate; wherein C/L is 5;

FIG. 14 is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate; wherein C/L is 10;

FIG. 15 is a schematic flow diagram of the airflow at the trailing edge of the wing plate; wherein C/L is 3, 2, 1.5;

FIG. 16 is a schematic view of the vortex pattern, intersection X and non-wind zone W of the air flow passing through the air deflection assembly of the present invention;

FIG. 17 is a view of an airflow field when the airflow passes through a conventional air deflector of the prior art;

FIG. 18 is a flow field diagram of airflow over a plurality of airfoils of the subject application;

FIG. 19 is a schematic flow diagram of the airflow as it flows over the plurality of wing plates of the present application; wherein, because the D/L value is smaller, the vortexes generated by the two adjacent wing plates are converged;

FIG. 20 is a schematic flow diagram of the airflow as it flows over the plurality of wing plates of the present application; the D/L value is proper, and vortexes generated by two adjacent wing plates do not meet;

FIG. 21 is a flow field diagram of airflow 10 chord lengths behind the airfoils in this application.

The reference numbers illustrate:

reference numerals	Name (R)	Reference numerals	Name (R)
				10	Air deflector assembly	11	Air deflector
12	Wing plate	13	Connecting piece
				11a	Wind guide surface	11b	Leeward side
111	First edge	112	Second edge
				12c	Side surface		121	Leading edge
122	Trailing edge	12a	Ventral surface
				12b	Back side of the panel	X	Vortex air flow intersection zone
W	Area without wind	P	Air gap

The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

In addition, the descriptions related to "first", "second", etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.

The invention provides an air deflector assembly and an air conditioner comprising the same.

Referring to fig. 1 to 5 of the drawings,the air deflection assembly 10 includes an air deflection panel 11 and a wing panel 12. The air guide plate 11 has an air guide surface 11a, the air guide surface 11a has a first edge 111 and a second edge 112 which are oppositely arranged, the first edge 111 and the second edge 112 both extend along the length direction of the air guide plate 11, and the plane of the first edge 111 and the second edge 112 is S₁(ii) a The wing plate 12 is obliquely mounted on the air guide surface 11a through a connecting piece 13, the wing plate 12 has a front edge 121, a rear edge 122, a ventral surface 12a and a rear surface 12b, the ventral surface 12a and the rear surface 12b are both connected with the front edge 121 and the rear edge 122, an air passing gap P is formed between the front edge 121 and the air guide surface 11a, the distance between the front edge 121 and the air guide surface 11a is smaller than the distance between the rear edge 122 and the air guide surface 11a, and the plane where the front edge 121 and the rear edge 122 are located is S₂Plane S₁And plane S₂Included angle α is no less than 5 ° and no greater than 35 °.

The air guide plate 11 has a substantially square plate-like structure, and the air guide plate 11 further has a leeward surface 11b facing the air guide surface 11a (the leeward surface 11b also has an air guide function when it is at a certain angle). Of course, the wind guiding plate 11 may have a certain curvature, for example, the wind guiding surface 11a is a concave curved surface, and the leeward surface 11b is a convex curved surface. When the air guide surface 11a is a plane, the plane S₁Namely the air guide surface 11a, when the air guide surface 11a is a cambered surface, the plane S₁Not overlapping with the air guide surface 11 a.

Referring to fig. 6-8, wing panel 12, as its name implies, is constructed and operates in a manner similar to an aircraft wing.

The leading edge 121 of the wing panel 12 refers to the front edge of the wing panel 12 facing the wind, and the trailing edge 122 refers to the trailing edge of the wing panel 12 facing the wind, that is, when the wing panel 12 faces the wind, the airflow flows from the leading edge 121 to the trailing edge 122.

When the airflow passes through the wing plate 12, part of the airflow flows along the ventral surface 12a, and part of the airflow flows along the dorsal surface 12b, because the airflow path on the ventral surface 12a is smaller than that on the dorsal surface 12b, and the two airflows start from the front edge 121 and reach the rear edge 122 at the same time, the speed of the airflow on the dorsal surface 12b is greater than that on the ventral surface 12a, so that the pressure of the airflow on the dorsal surface 12b is greater than that on the ventral surface.

The wing panel 12 has a rounded tip (leading edge 121 at the tip) and a substantially tapered tail (trailing edge at the tail) at the wing 12.

Wing panel 12 has an airfoil section (taken from a section perpendicular to leading edge 121 and trailing edge 122) for which the back arc length H of wing panel 12₁(the length of the arc extending from the leading edge 121 to the trailing edge 122 along the rear surface 12 b) is greater than the straight length or arc length H of the ventral surface 12a of the wing plate 12₂. For this wing panel 12, the wing panel 12 itself also has two sides 12c between the ventral 12a and dorsal 12b, the span L (which can refer to the length of the leading edge 121, or the length of the trailing edge 122, for a uniform spacing between the two sides 12 c) when the spacing between the opposite sides 12c is the same. The chord length C is indicative of the perpendicular distance between the leading edge 121 and the trailing edge 122. Distance C of the leading edge 121 from the maximum thickness of the wing panel 12₁Less than the distance C of the trailing edge 122 from the maximum thickness of the wing panel 12₂. The back surface 12b may be a curved surface, and the ventral surface 12a may be a flat surface or a curved surface.

For the installation of the wing plate 12 and the air guiding plate 11, the wing plate 12 itself has a certain distance with the air guiding surface 11a to facilitate the air flow to pass through, the wing plate 12 and the air guiding plate 11 are connected by the connecting piece 13, on one hand, the connecting piece 13 may be a columnar structure, or a regular or irregular protrusion arranged on the air guiding surface 11a, or certainly a regular or irregular protrusion arranged on the surface of the wing plate 12, on the other hand, one end of the connecting piece 13 is connected to the air guiding surface 11a, and the other end thereof may be connected to the side surface, the back surface 12b, or the ventral surface 12a of the wing plate 12, on the other hand, the connecting piece 13 may also be a sheet structure, for example, the sheet structure extends along the air flow direction, on the one hand, the flow guiding function is achieved, on the other hand, the air flow resistance is reduced, on the other hand, a certain division function is also provided for the air flow passing through the air guiding surface 11a, and the formation of eddy is slowed down, and.

In the case of an air conditioner, the wind speed at the air outlet is approximately 0.5m/s to 4m/s, and in the case of 4m/s, after the wind is guided by a common plate-shaped air guide plate, the wind speed can be reduced to approximately 0 after a distance of about 5 m. After the air guide plate assembly, the wind speed can be reduced to 0 approximately after the distance of about 2m, the blown air flow and indoor air can fully exchange heat in the range of blowing out 2m from the air outlet to the air flow, and the wind speed is extremely low after 2m is opened.

Referring to fig. 9, when the airflow blows along the width direction of the wind deflector 11, a part of the airflow winds from the ventral surface 12a to the dorsal surface 12b, and at the same time, the airflow flows from the front edge 121 to the rear edge 122, so that a spiral vortex wake is formed by the part of the airflow relative to the wing plate. Namely, the air flow is originally straight when flowing through the air deflector 11, and can form a plurality of vortex-shaped wake flows after being guided by the multi-machine wing plate 12, so that the mass and heat transfer effects are enhanced, and the heat convection capability is improved; the stroke of the airflow is reduced on the premise of not reducing the heat exchange quantity; the effect of gentle wind feeling can be realized in a slightly far range by strong convection and strong heat exchange in a range close to the air outlet.

In addition to the above-described embodiments, the wing plate is attached to the air guide surface in an inclined manner, but the angle of inclination of the wing plate itself cannot be too large or too small. The inclination of the wing plate 12 will be discussed further in this embodiment.

The wing plate 12 is obliquely mounted on the air guide surface 11a with respect to the plane S₁In (1).

Theoretically, even if α is equal to 0, the vortex can be formed when the airflow flows from the front edge to the rear edge of the wing plate, but the vortex amount of the vortex is relatively small, the vortex strength is weak, in order to make the vortex effect relatively good, α can take 5 degrees, and the subsequent data can observe the vortex degree and the vortex amount when α changes from 15 degrees to 70 degrees.

Referring to fig. 10a to 10h, it can be seen that the vortex strength is weak when α is 15 °, the vortex condition changes significantly when α is 70 °, the wing tip vortex degree is weak, the wing tip vortex condition is relatively ideal when α is 15 ° to 70 °, and the value range of the adaptive attack angle α can be determined to be 15 ° to 70 ° according to numerical simulation

Referring to fig. 10a to 10h, the swirl strength is stronger in the range of α ° to α ° to 55 °, and the difference is that the influence range of the swirl wake is smaller when α ° to 15 ° and α ° to 25 °, which is not favorable for driving the rear air to rotate, the swirl condition is significantly changed when α ° to 70 °, the wing tip swirl degree is weak, and the wing tip swirl condition is ideal when α ° to α ° to 55 °.

The effect of α on vortex wake is not sufficiently judged by streamline distribution alone-vorticity is the physical quantity reflecting the strength of vortex, and the contour distribution of vorticity around the wing is shown in FIGS. 11a to 11 h.

The vortex core (solid portions on both sides of the wing plate in fig. 11a to 11 h) of the vortex wake is the largest when the incident angle α is 15 ° and the vortex core 28 is 25 °, but as the streamline distribution in fig. 10a to 10h is known, the wake influence range is relatively small because the incident angle α is small, so that the angle is suitable for a use situation where the air supply is far away and the heat exchange efficiency needs to be enhanced, α ° to α ° range is 55 °, the vortex distribution situation is close, and the incident angle α is larger, so that the capability of scattering the incoming flow is stronger, so that the effect of swirling the air flow into the wake is best when α ° is 55 °, α ° to α ° is suitable for the air supply short distance and the design requirement of soft feeling is strong, when the incident angle α is too large, the rising wing plate 12 blocks the air duct, the air flow influence on the inlet flow, and when the incident angle 364 ° is 60 ° and the vortex distribution is not small, so that the vortex distribution is no longer generated when 3670 ° is analyzed.

The streamline and velocity profiles obtained by numerical simulation calculations are shown in fig. 17 and 18. At the initial stage, the air flow speed guided out by the wing plate 12 and the air outlet speed of the common air outlet are both 4 m/s. It can be seen that the wake of the wing plate 12 forms a significant vortex, the local air velocity in front of the vortex is high (maximum 5.1m/s), this region is a strong mass and heat transfer region, and the air velocity rapidly decreases behind this region, reaching a softer air velocity range shortly beyond this region.

According to the technical scheme, the wing plate 12 is arranged on the air deflector 11, when airflow flows to the rear edge 122 of the wing plate 12 along the front edge 121 of the wing plate 12, a vortex is formed on the rear edge 122 of the wing plate 12, the radius of the formed vortex is gradually enlarged, and the vortex speed is gradually reduced in the subsequent operation process, so that rapid heat transfer can be realized, the airflow is softened lightly, and the effect of no wind feeling or slight wind feeling is realized. Referring to fig. 16, the air flow converges in the swirling air flow convergence region X, in which the air flow velocity is greatly reduced (the air flow velocity approaches 0), thereby forming a non-windy region W outside the convergence region X.

In the above embodiment, referring to fig. 1, fig. 2 and fig. 5, the number of the wing plates 12 may be one, and certainly, in order to achieve a better flow guiding effect, the number of the wing plates 12 is multiple, and the multiple wing plates 12 are arranged at intervals along the length direction of the air guiding plate 11. For example, the number of wing plates 12 may be 5 to 12.

In order to facilitate the arrangement of the wing plates 12 on the wind deflector 11, in another preferred embodiment, the length of the wind deflector 11 is S, the distance between two adjacent wing plates 12 is D, and the span of the wing plates 12 is L, wherein S is an integral multiple of the sum of D and L.

In wind guiding, the airflow is blown out along the width direction of the wind guiding plate 11, and when the airflow flows from the leading edge 121 to the trailing edge 122 along the back surface 12b and the ventral surface 12a, the airflow mainly at the trailing edge 122 and near the two side surfaces of the wing plate 12 forms vortices, so that, relatively speaking, if the span of the wing plate 12 is longer, the distance between two adjacent vortices is larger. With continued reference to fig. 12, 13, 14 and 15, in order to generate more swirl when the airflow blows through the air deflection assembly 10, in the present embodiment, the chord length of the wing plate 12 is C, the span of the wing plate 12 is L, and C/L > 1.

In fig. 12, C/L is 2, in fig. 13, C/L is 4, in fig. 14, C/L is 10, in fig. 15, C/L is 3, 2, 1.5 (C/L)₁＝3，C/L₂＝2，C/L₃1.5) it can be seen from the four figures that when C/L is 4, the two vortices at the trailing edge of the wing plate 12 (not yet flowing out of the wing plate) almost touch together, soContinuing to rise at C/L, the two vortices will interfere with each other, thereby affecting mass transfer and subsequent heat exchange. In this embodiment, 1.5. ltoreq. C/L. ltoreq.4.

When the air flow blows over two adjacent wing plates 12, the tips of the two adjacent wing plates 12 (the end of the trailing edge 122) form vortices, and as the vortices flow in a direction away from the wing plates 12, the radius of the vortices increases,

in the present embodiment, referring to fig. 21, if the distance between the two wings is too close, the vortices generated by two adjacent wingtips (two tips of the trailing edge 122 of the wing plate 12) are easy to interfere with each other. If the distance is too far away, more airflow does not flow through the wing tip, and the overall vortex effect is reduced. The best effect is that the vortices generated by two adjacent wingtips are close and do not intersect at a far point.

Therefore, the distance between two adjacent wing plates 12 is not small. In addition, if the distance between the two wing plates 12 is too large, the blown vortex air flow is relatively loose, which is not beneficial to mass transfer and heat exchange.

Please refer to FIG. 19, FIG. 20 and FIG. 21 (Q)₁For one of the swirling air streams, Q₂Another vortex air flow), the air flow lines are distributed in two cylindrical shapes within the range of 10 times of chord length behind the rear edge 11b (behind the wing) of the wing plate 11, and the range is the area with the fastest flow speed and the strongest forced convection heat exchange, so that the interference between the tail flow lines and the tail flow lines of the adjacent wings in the range is ensured as much as possible. It can be seen that the widest part of the streamlines is about 2 times the spanwise length, so it is best to ensure that the two wings are spaced 2 times the spanwise length. When the wing spacing is 1.3 times span, the wake will intersect 0.3m behind the wing, can obtain better gentle wind sense effect this moment, but the heat transfer ability can reduce to some extent, and the interval continues to reduce and can lead to heat transfer ability to continuously reduce. Therefore, according to different use scenes and design requirements, the relationship between the wing spacing and the span length is determined to be that D is more than or equal to 1.3L and less than or equal to 2L.

For the wing plate 12, the size should not be too large, nor too small, and if too large, the wind resistance would be larger, which would affect the air output; if too small, it may result in less swirl being formed at the trailing edge 122 of the wing plate 12. Considering the size of the air outlet of the air conditioner (the width of the air deflector is 60mm-120mm generally), considering the movement (opening and closing) of the air deflector, in order to prevent interference, the maximum chord length C of the wing plate 12 needs to be controlled within 80 mm. The chord length C of the wing 12 is small, which is not beneficial to the formation of the tip vortex of the wing with a large scale, so the limit minimum value is 20 mm. As the vortex is mainly generated at the wing tip, the overlong wingspan is not beneficial to the enhancement of the vortex, and the two wing tip vortexes which are too short interfere with each other and are not beneficial to the generation of the vortex. In addition, in a preferred embodiment, the wing panel 12 has a span L ranging in size from 10mm to 50mm, and more preferably, the span L ranges in size from 25mm to 40 mm.

For wing plates 12 with a span ranging from 25mm to 40mm, 1.5 ≦ C/L ≦ 4 is satisfied. The chord length of the wing plate 12 is not too long, so based on the ratio, the chord length C of the wing plate 12 can be further controlled to be between 40mm and 60 mm.

In the above embodiment, both the columnar connector 13 and the sheet-like connector 13 are described, and in the present embodiment, the connector 13 will be further described.

For the columnar connecting pieces 13 (an embodiment of the columnar connecting pieces 13 is not shown in the figure), after the airflow passes through the plurality of columnar connecting pieces 13, each columnar connecting piece forms a pair of vortex streets and then continuously propagates forwards, and the blown airflow has a karman vortex street effect, so that the airflow can be quickly mixed with indoor air, and the heat exchange mixed flow effect is further improved. Therefore, the columnar connector 13 is arranged at a position close to the leading edge 121, and the span between the vortex street and the vortex can be enlarged in space position to avoid mutual interference of the vortex street and the vortex. In addition, the area between two adjacent scrolls is less affected by the air flow (direct blowing of air) before the radii of the two adjacent scrolls are enlarged and meet, so that if the position where the cylindrical connecting member 13 connects the back surface 12b is located at the perpendicular bisector of the wingspan, the blank area between the two adjacent scrolls can be just compensated.

Referring to fig. 2 and 3, for the sheet-shaped connecting member 13, since the structure has a certain dividing effect on the airflow, so that the formation of the vortex can be greatly reduced (the vortex is formed in advance, which is not beneficial to the formation of the vortex at the rear edge 122 of the wing plate 12, and the vortex can disturb the vortex), the sheet-shaped connecting member 13 is disposed at a position close to the front edge 121, which can rectify the airflow, and the vortex phenomenon of the subsequent airflow is greatly reduced when the airflow flows through the wing plate 12. If the position of the sheet-like connection 13 is on the midperpendicular of the span, the radius and flow velocity of the vortex formed by the two tail tips of the trailing edge 122 of the wing plate 12 can be kept consistent, and the overall mass and heat transfer is more uniform.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.