CN211650679U

CN211650679U - Air deflector assembly and air conditioner

Info

Publication number: CN211650679U
Application number: CN201922131123.XU
Authority: CN
Inventors: 郜哲明
Original assignee: GD Midea Air Conditioning Equipment Co Ltd
Current assignee: GD Midea Air Conditioning Equipment Co Ltd
Priority date: 2019-11-29
Filing date: 2019-11-29
Publication date: 2020-10-09
Anticipated expiration: 2029-11-29

Abstract

The utility model discloses an air deflector assembly and air conditioner, wherein air deflector assembly includes aviation baffle, water conservancy diversion support and wing board, the aviation baffle has the wind guide surface, and lie in the first edge and the second edge on the relative both sides limit of the wind guide surface, the first edge all extends along the length direction of aviation baffle with the second edge; the guide support is arranged on the air guide surface, a guide channel for guiding air along the width direction of the air guide plate is formed by enclosing between the guide support and the air guide plate, the guide support is provided with a guide plate opposite to the air guide plate, and the guide plate is provided with a guide surface facing the air guide surface; the wing plate is provided with a front edge, a rear edge, a ventral surface, a back surface and two side surfaces, wherein the ventral surface and the back surface are connected with the front edge and the rear edge, and the side surfaces are connected with the back surface and the ventral surface. The technical scheme of the utility model can realize transmitting heat rapidly, with the gentle change of air current, realize no wind sense or breeze sense effect.

Description

Air deflector assembly and air conditioner

Technical Field

The utility model relates to an air conditioner technical field, in particular to aviation baffle subassembly and 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.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an air deflection assembly aims at solving current micropore aviation baffle windage big partially, and no wind feels the effect and still just not good technical problem.

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, a first edge and a second edge, wherein the first edge and the second edge are positioned on two opposite side edges of the air guide surface, and the first edge and the second edge both extend along the length direction of the air guide plate;

the guide support is arranged on the air guide surface, a guide channel for guiding air along the width direction of the air guide plate is formed by enclosing between the guide support and the air guide plate, the guide support is provided with a guide plate opposite to the air guide plate, and the guide plate is provided with a guide surface facing the air guide surface;

a wing panel having a leading edge, a trailing edge, a ventral surface, a dorsal surface and two side surfaces, the ventral surface and the dorsal surface both connecting the leading edge and the trailing edge, the side surfaces connecting the dorsal surface and the ventral surface;

wherein a part of the wing plates are arranged on the air guide surface through the side surface, and the other part of the wing plates are arranged on the flow guide surface through the side surface;

a leading edge of the wing panel is disposed toward the first edge and a trailing edge of the wing panel is disposed toward the second edge.

In one embodiment, the number of the wing plates is multiple, the wing plates are arranged at intervals along the length direction of the air guide plate, and the side surface of the wing plate mounted on the air guide surface is attached to the air guide surface; the side surface of the wing plate arranged on the flow guide surface is attached and connected with the flow guide surface.

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 air deflector has two opposite ends located in the length direction thereof, the wing plates include a first wing group and a second wing group, ventral surfaces of the wing plates in the first wing group are all arranged towards one end of the air deflector, ventral surfaces of the wing plates in the second wing group are all arranged towards the other end of the air deflector, and the wing plates in the first wing group and the wing plates in the second wing group are alternately arranged in the length direction of the air deflector; the first wing group and the second wing group are arranged on the air guide surface and/or the flow guide surface.

In one embodiment, in two adjacent wing plates with the opposite ventral surfaces, the distance between the two leading edges is larger than the distance between the two trailing edges.

In one embodiment, a chord length of the wing plate located on the air guide surface is larger than a chord length of the wing plate located on the air guide surface.

In one embodiment, the included angle between two wing plates of two adjacent wing plates with opposite ventral surfaces is not less than 10 ° and not more than 165 °.

In one embodiment, an attack angle of the wing plate with respect to a width direction of the air deflector is not less than 15 ° and not more than 70 °.

In one embodiment, the angle of attack of the wing panel relative to the wind deflector is no less than 25 ° and no greater than 55 °.

In one embodiment, the chord length of the wing plate is C, the span of the wing plate is L, and the value of C/L is more than 1.

In one embodiment, the value of C/L is not less than 1.5 and not greater 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 one embodiment, the dorsal surface is a curved surface and the ventral surface is a flat or curved surface.

The utility model also discloses an air conditioner, which is provided with an air outlet, and an air deflector component is arranged at the air outlet; the air deflector assembly comprises an air deflector, a guide bracket and a wing plate. The air guide plate is provided with an air guide surface, a first edge and a second edge, wherein the first edge and the second edge are positioned on two opposite side edges of the air guide surface, and both the first edge and the second edge extend along the length direction of the air guide plate; the guide support is arranged on the air guide surface, a guide channel for guiding air along the width direction of the air guide plate is formed by enclosing between the guide support and the air guide plate, the guide support is provided with a guide plate opposite to the air guide plate, and the guide plate is provided with a guide surface facing the air guide surface; the wing plate is provided with a front edge, a rear edge, a ventral surface, a back surface and two side surfaces, wherein the ventral surface and the back surface are connected with the front edge and the rear edge, and the side surfaces are connected with the back surface and the ventral surface; wherein a part of the wing plates are arranged on the air guide surface through the side surface, and the other part of the wing plates are arranged on the flow guide surface through the side surface; a leading edge of the wing panel is disposed toward the first edge and a trailing edge of the wing panel is disposed toward the second edge.

The technical scheme of the utility model through set up the wing board on the aviation baffle, the air current forms the vortex along the trailing edge of the leading edge flow direction wing board of wing board at the wing board trailing edge, and the vortex of formation enlarges gradually at follow-up operation in-process, and the vortex speed reduces gradually to can realize transmitting heat rapidly, with the air current gentle change, realize no wind sense or breeze sense effect.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be 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 diagram (observed along the airflow direction) of an embodiment of an air deflection 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 front view of FIG. 2;

FIG. 4 is a top view of FIG. 2;

FIG. 5 is a rear view of FIG. 1;

fig. 6 is a perspective view of a wing plate of the air deflection assembly of fig. 1;

FIG. 7 is a graph comparing the ventral arc length and dorsal arc length of the wing plate of FIG. 6;

FIG. 8 is a comparison of the distance from the leading and trailing edges of the wing panel of FIG. 7 to the maximum thickness of the wing panel;

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 aft 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 aft 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; wherein 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; wherein 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; wherein 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; wherein α is 60 °;

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

FIG. 10h is a plot of the flow vorticity contour profile of the air flowing aft from the leading edge of the wing plate; wherein α is 70 °;

FIG. 11a is a plot of the contour profile of the vorticity of the air flowing aft from the leading edge of the wing plate; wherein α is 15 °;

FIG. 11b is a plot of the flow vorticity contour profile of the air flowing aft from the leading edge of the wing plate; wherein α is 25 °;

FIG. 11c is a plot of the contour profile of the vorticity of the air flowing aft from the leading edge of the wing plate; wherein α is 35 °;

FIG. 11d is a plot of the contour profile of the vorticity of the air flowing aft from the leading edge of the wing plate; wherein α is 45 °;

FIG. 11e is a plot of the flow vorticity contour profile of the air flowing aft from the leading edge of the wing plate; wherein α is 55 °;

FIG. 11f is a plot of the flow vorticity contour profile of the air flowing aft from the leading edge of the wing plate; wherein α is 60 °;

FIG. 11g is a plot of the flow vorticity contour profile of the air flowing aft from the leading edge of the wing plate; wherein α is 65 °;

FIG. 11h is a plot of the flow vorticity contour profile of the air flowing aft from the leading edge of the wing plate; wherein 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 view of an airflow field when the airflow passes through a conventional air deflector of the prior art;

FIG. 17 is a flow field diagram of airflow over a plurality of airfoils of the subject application;

FIG. 18 is a schematic flow diagram of the air stream as it flows over the plurality of airfoils of the present application; wherein, because the D/L value is smaller, the vortexes generated by the two adjacent wing plates are converged;

FIG. 19 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. 20 is a flow field diagram of the air flow 10 chord lengths behind the airfoils of the present application;

fig. 21 is a wing plate surface sound pressure level distribution diagram.

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
				14	Flow guide bracket	11a	Wind guide surface
11b	Leeward side		12c					Side surface
				121	Leading edge	122	Trailing edge
12a	Ventral surface	12b	Back side of the panel
				140	Flow guide channel	141	Flow guide surface
14a	Flow guide plate

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

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

It should be noted that all the directional indicators (such as upper, lower, 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 motion situation, etc. in a specific posture (as shown in the drawings), 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 implicit ly 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, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

The utility model discloses the reality has provided a aviation baffle subassembly and has included the air conditioner of this aviation baffle subassembly.

Referring to fig. 1 to 6, the air guiding plate assembly 10 includes an air guiding plate 11, an air guiding bracket 14 and a wing plate 12, wherein the air guiding plate 11 has an air guiding surface 11a, and a first edge 111 and a second edge 112 located at two opposite sides of the air guiding surface 11a, and both the first edge 111 and the second edge 112 extend along a length direction of the air guiding plate 11; the guide bracket 14 is mounted on the air guide surface 11a, a guide channel 140 guiding air along the width direction of the air guide plate 11 is formed by the guide bracket 14 and the air guide plate 11, the guide bracket 14 has a guide plate 14a opposite to the air guide plate 11, and the guide plate 14a has a guide surface 141 facing the air guide surface 11 a; the wing plate 12 has a front edge 121, a rear edge 122, a ventral surface 12a, a dorsal surface 12b, and two side surfaces 12c, wherein the ventral surface 12a and the dorsal surface 12b both connect the front edge 121 and the rear edge 122, and the side surfaces 12c connect the dorsal surface 12b and the ventral surface 12 a.

Wherein a part of the wing plate 12 is attached to the air guide surface 11a through the side surface 12c, and another part of the wing plate 12 is attached to the guide surface 141 through the side surface 12 c; the leading edge 121 of the wing panel 12 is disposed toward the first edge 111 and the trailing edge 122 of the wing panel 12 is disposed toward the second edge 112.

The air guide plate 11 has a substantially square plate-like structure, and the air guide plate 11 itself has a first side and a second side extending in the longitudinal direction thereof and disposed to face each other, and the air guide plate 11 also has a leeward surface 11b facing the air guide surface 11a (the leeward surface 11b has an air guide function when it is at a certain angle). Of course, the wind guide plate 11 may have a certain curvature, for example, the wind guide surface 11a may have a certain concave curvature, and the leeward surface 11b may have a certain curvature.

Referring to fig. 6-8, wing panel 12 is configured, as the name implies, like a wing of an aircraft. 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. For this airfoil section, the arc length of the back face of wing panel 12 (the arc length extending from leading edge 121 along back face 12b to trailing edge 122) is greater than the straight or arc length of ventral face 12a of wing panel 12. For the wing panel 12, the wing panel 12 itself also has two side surfaces 12c between the ventral surface 12a and the dorsal surface 12b, with the span L referring to the spacing between the opposite side surfaces of the wing panel 12 (for a uniform spacing between the two side surfaces 12 c). The chord length C is indicative of the straight distance between the leading edge 121 and the trailing edge 122. Distance L between the leading edge 121 and the maximum thickness of the wing panel 12₁Less than the distance L between the trailing edge 122 and 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 and the air guiding plate 11 may be connected by a connecting piece 13, or may be directly connected by the side surface 12 c.

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 is used, the wind speed can be reduced to 0 approximately after the distance of about 2.5m, the blown air flow and indoor air can fully exchange heat in the range from the air outlet to the air flow blowing out of 2m, and almost no wind sensation exists after the air outlet is opened for 2 m.

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 leading edge 121 to the trailing edge 122, so that a spiral vortex wake is formed in the part of the airflow relative to the wing. That is, the air flow is straight when passing through the air deflector 11, and can form a plurality of vortex-shaped wake flows after being guided by the plurality of wing plates 12, thereby enhancing the mass and heat transfer effect and improving the heat convection capability; 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.

For the guide bracket 14, on the one hand, the air flow has a collecting effect, so that the air flow can flow to the wing plate 12 more smoothly; on the other hand, the air conditioner has a guiding function on air flow, and reduces the formation of internal vortex of the air outlet of the air conditioner.

Further, in another preferred embodiment, the number of the guide brackets 14 is two, two guide brackets 14 are arranged at intervals in the length direction of the air deflector 11, and the plurality of wing plates 12 include a first wing group and a second wing group, and the first wing group and the second wing group are arranged in two guide channels 140.

In one embodiment, the ventral surface 12a of one wing panel 12 is disposed towards the dorsal surface 12b of the other wing panel 12 in any two adjacent wing panels 12. That is, the ventral surfaces 12a of all the wing plates 12 face the same direction. Therefore, when the vortex air flow is blown out from the air outlet of the air conditioner, the vortex air flow cannot interfere with each other to influence the mass transfer or heat transfer, so that the mass transfer or heat transfer effect is better.

Different from the previous embodiment, the air deflector 11 has two opposite ends located in the length direction thereof, the wing plates 12 include a first wing group (not shown) and a second wing group (not shown), ventral surfaces 12a of the wing plates 12 in the first wing group are all arranged towards one end of the air deflector 11, ventral surfaces 12a of the wing plates 12 in the second wing group are all arranged towards the other end of the air deflector 11, and the wing plates 12 in the first wing group and the wing plates 12 in the second wing group are alternately arranged in the length direction of the air deflector 11; the first wing group and the second wing group are disposed on the wind guide surface 11a and/or the flow guide surface 141.

In two adjacent wing plates 12 with the ventral surfaces 12a facing each other, the distance between the two leading edges 121 is greater than the distance between the two trailing edges 122.

Since the wing plates 12 are mounted against the air deflector 11, each wing plate 12 forms a swirling air flow only on its side remote from the air deflector 11. In the two wing sets arranged alternately (ventral faces facing each other), on the one hand the flow velocity of the air flow passing between the two wing plates 12 is locally increased, thereby increasing the swirling effect.

In addition, the included angle between the two wing plates 12 (opposite to the ventral surface 12 a) should not be too large or too small. The included angle is too large, so that the vortex amount of vortex is influenced; the included angle is too small, which is not beneficial to the increase of vortex. In the present embodiment, the included angle between two wing plates 12 of two adjacent wing plates 12 opposite to each other with the ventral surface 12a is not less than 10 ° and not more than 165 °. Preferably, the included angle is 45-75 degrees. The angle is the angle formed by the chord planes of the wing plates 12.

Further, in order to generate the vortex air flow by both the wing plate 12 of the air guiding surface 11a and the wing plate 12 of the guiding surface 141, the distance between the two wing plates is relatively short, which may cause the vortex air flow generated by the upper wing plate 12 and the lower wing plate 12 to be poor. In the present embodiment, in order to avoid this, the chord length of the wing plate 12 located on the air guide surface 11a is larger than the chord length of the wing plate 12 located on the guide surface 141. In this way, the wing plate 12 positioned on the air guide surface 11a is used as a main wing plate, and the wing plate 12 positioned on the guide surface 141 is used as an auxiliary wing plate, so that the main wing plate can form vortex air flow with larger vortex effect, vortex radius, vortex speed and vortex quantity; the auxiliary wing plate can guide the airflow which is not utilized yet by the main wing plate out to form a small vortex, thereby forming a supplement to the vortex formed by the main wing plate.

Regarding the problem of the attack angle of the wing plate, the following contents are that the wing plate is used for simulation experiments under various different angles, wherein the condition of double-sided vortex is simulated in the simulation experiments in consideration of the difficulty in measuring the single-sided vortex.

Referring to fig. 10a to 11h, it can be seen that the vortex strength is weak when α is 15 °, and the vortex condition is significantly changed when α is 70 °, and the wing tip vortex degree is weak. The wing tip vortex condition is relatively ideal when the alpha is between 15 and 70 degrees, and the value range of the proper attack angle alpha can be judged to be between 15 and 70 degrees according to numerical simulation

Referring to fig. 10a to 10h, the vortex intensity is stronger in the range of α -15 ° to α -55 °, except that the influence range of the vortex wake is smaller when α -15 ° and α -25 °, which is not favorable for driving the rear air to rotate. When alpha is 70 degrees, the vortex condition is obviously changed, and the wing tip vortex degree is very weak. Tip vortices are preferred when α is 25 ° to 55 °.

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

When the angle of attack α is 15 ° and α is 25 °, the length of the vortex core of the vortex wake (in fig. 11a to 11h, the solid portions on both sides of the wing plate) is the largest. However, as can be seen from the streamline distribution in fig. 10a to 10h, since the incidence angle α is small, the wake flow influence range is relatively small, and thus the angle is suitable for use situations where air blowing is performed at a relatively long distance and heat exchange efficiency needs to be enhanced. The swirl distribution is close in the range of α 35 ° to α 55 °, and the greater the angle of attack α, the greater the ability to break up the incoming flow, so that the effect of converting the air into a swirl wake is considered to be the best when α is 55 °. The attack angle of alpha is 35 degrees to 55 degrees, which is suitable for the design requirements of short distance air supply and soft wind feeling. When the attack angle alpha is too large, the vertical wing plates 12 block the air duct to influence the incoming air flow, the vortex amount distribution range is reduced when the angle alpha is 60 degrees, and the vortex amount distribution is very small when the angle alpha is 70 degrees, so that the comprehensive analysis shows that vortex wake flow can not be generated when the angle alpha is more than 70 degrees.

The technical scheme of the utility model through set up wing board 12 on aviation baffle 11, the air current forms the vortex along wing board 12 trailing edge 122 when wing board 12's leading edge 121 flow direction wing board 12's trailing edge 122, and the vortex of formation enlarges gradually at wing board 12 trailing edge 122, and the vortex radius reduces gradually at follow-up operation in-process, and vortex speed to can realize passing heat rapidly, with the air current gentle change, realize no wind sense or breeze sense effect.

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 a vortex, so that the distance between two adjacent vortices is relatively larger if the span of the wing plate 12 is longer. With continued reference to fig. 14, 15, 16 and 17, 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. 14, C/L is 2, C/L is 4 in fig. 15, C/L is 10 in fig. 16, and C/L is 3, 2, 1.5 in fig. 17, it can be seen from these three figures that when C/L is 4, the two vortices at the trailing edge of the wing plate almost contact together, so C/L continues to rise, and the two vortices will interfere with each other, thereby affecting mass transfer and subsequent heat exchange. In the embodiment, C/L is more than or equal to 1.5 and less than or equal to 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. 18 and fig. 19, if the distance between the two wings is too close, the vortices generated by the 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 just close at a distance and do not want to intersect.

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. The distance between two adjacent wing plates 12 is D, and 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 60-120mm 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 the present embodiment, the wing panel 12 has a span L in the range of 10mm to 50mm, preferably in the range of 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, as for the sheet-shaped connecting member 13, since the structure has a certain dividing effect on the airflow, 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), so that the sheet-shaped connecting member 13 is arranged at a position close to the front edge 121, which can perform a rectifying effect on the airflow, and when the airflow flows through the wing plate 12, the vortex phenomenon of the subsequent airflow is greatly reduced. 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 only is the preferred embodiment of the present invention, not limiting the scope of the present invention, all the equivalent structure changes made by the contents of the specification and the drawings under the inventive concept of the present invention, or the direct/indirect application in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An air deflection assembly, comprising:

2. The air guide plate assembly of claim 1, wherein the number of the wing plates is multiple, the wing plates are arranged at intervals along the length direction of the air guide plate, and the side surface of the wing plate mounted on the air guide surface is in fit connection with the air guide surface; the side surface of the wing plate arranged on the flow guide surface is attached and connected with the flow guide surface.

3. The air deflection board assembly of claim 1Element, characterized in that the arc length of said back face corresponding to the airfoil section of said wing panel 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。

4. The air deflection assembly of claim 3, wherein the distance from the leading edge to the maximum thickness of the wing panel is less than the distance from the trailing edge to the maximum thickness of the wing panel.

5. The air deflection assembly of claim 4, wherein the air deflection plate has opposite ends along the length thereof, and the plurality of wing plates includes a first wing group and a second wing group, wherein the ventral surfaces of the wing plates in the first wing group are both disposed toward one end of the air deflection plate, the ventral surfaces of the wing plates in the second wing group are both disposed toward the other end of the air deflection plate, and the wing plates in the first wing group and the wing plates in the second wing group are alternately disposed along the length of the air deflection plate; the first wing group and the second wing group are arranged on the air guide surface and/or the flow guide surface.

6. The air deflection assembly of claim 5, wherein said web surfaces are disposed opposite each other and adjacent wing panels are disposed with said leading edges spaced apart from each other by a distance greater than a distance between said trailing edges.

7. The air deflection assembly of claim 5, wherein a chord length of the airfoil plate at the air deflection surface is greater than a chord length of the airfoil plate at the flow deflection surface.

8. The air deflection assembly of claim 7, wherein the web faces of adjacent wing plates are oriented at an angle of not less than 10 ° and not more than 165 °.

9. The air deflection assembly according to any one of claims 1 to 8, wherein the incidence angle of the wing plate with respect to the width direction of the air deflection plate is not less than 15 ° and not more than 70 °.

10. The air deflection assembly of claim 8, wherein the wing panel has an angle of attack with respect to the air deflection panel of no less than 25 ° and no greater than 55 °.

11. The air deflection assembly of claim 8, wherein the wing panel has a chord length C and a span L, and wherein C/L is greater than 1.

12. The air deflection assembly of claim 10, wherein C/L has a value of not less than 1.5 and not greater than 4.

13. The air deflection assembly of claim 8, wherein the distance between adjacent airfoils is D, and the wing span of the airfoils is L, and D is not less than 1.3L and not more than 2L.

14. An air deflection assembly according to any one of claims 1 to 8, wherein the rear face is cambered and the ventral face is flat or cambered.

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