CN211476252U

CN211476252U - Air deflector assembly and air conditioner

Info

Publication number: CN211476252U
Application number: CN201922130653.2U
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: 2020-09-11
Anticipated expiration: 2029-11-29

Abstract

The utility model discloses an air deflector component and an air conditioner, wherein the air deflector component comprises an air deflector and a wing plate, and the air deflector is provided with an air guide surface; the wing plate passes through the connecting piece slope install in the wind-guiding surface, the wing plate has leading edge, trailing edge, ventral surface and back, the ventral surface with the back all is connected the leading edge with the trailing edge, the leading edge with there is the air gap between the wind-guiding surface, the leading edge with interval between the wind-guiding surface is less than the trailing edge with interval between the wind-guiding surface, the back is located the ventral surface with between the wind-guiding surface. 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.

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;

the wing plate is obliquely installed on the air guide surface through the 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 back surface is located between the ventral surface and the air guide surface.

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 angle of attack of the wing panel relative to 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 not less than 25 ° and not more than 40 °.

In one embodiment, the length of the wind deflector is S, the distance between two adjacent wing plates is D, and the span of the wing plates is L, where S is an integral multiple of the sum of D and L.

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 wing panel has a span L, L being no less than 10mm and no greater than 50 mm.

In one embodiment, L is not less than 25mm, and not greater than 40 mm.

In one embodiment, the chord length of the wing plate is C, which is not less than 20mm and not more than 80 mm.

In an embodiment, the chord length C is not less than 40mm, and not more than 60 mm.

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

In an embodiment, the connecting member is arranged in a column shape, and two ends of the axis of the column-shaped connecting member are respectively connected with the air guide surface and the back surface.

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 connection of the connector to the rear face is disposed proximate the front edge.

In one embodiment, the location where the connector connects to the rear face is at the midperpendicular of the span.

In one embodiment, the dorsal surface is a curved surface and the ventral surface is a planar surface.

The utility model also provides an air conditioner, which is provided with an air outlet, wherein an air deflector component is arranged at the air outlet and comprises an air deflector and a wing plate, and the air deflector is provided with an air guide surface; the wing plate passes through the connecting piece slope install in the wind-guiding surface, the wing plate has leading edge, trailing edge, ventral surface and back, the ventral surface with the back all is connected the leading edge with the trailing edge, the leading edge with there is the air gap between the wind-guiding surface, the leading edge with interval between the wind-guiding surface is less than the trailing edge with interval between the wind-guiding surface, the back is located the ventral surface with between the wind-guiding surface.

In one embodiment, the air conditioner is a split air conditioner or a unitary air conditioner.

In one embodiment, the air conditioner is a floor air conditioner indoor unit.

In one embodiment, the floor type air conditioner indoor unit has an air outlet, a plurality of air guide plate assemblies are installed at the air outlet, the air guide plate assemblies are arranged at intervals in the vertical direction, and two rows of wing plates adjacent to each other in the vertical direction are separated by the air guide plates.

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 an enlarged view of FIG. 2 at C;

FIG. 4 is a schematic view of the wing plate of FIG. 2 (viewed from the back side of the wing plate to the ventral side);

FIG. 5 is a schematic view of the wing panel of FIG. 1 from a further perspective;

FIG. 6 is a front view of FIG. 5;

FIG. 7 is a cross-sectional view of the air deflection assembly of FIG. 6 taken along line A-A;

FIG. 8 is a schematic view of the wind deflector being disposed at an angle to the wing plate;

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. 10 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. 11 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. 12 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. 13 is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate; wherein α is 70 °;

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 ═ 2;

FIG. 15 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. 16 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. 17 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. 18 is a schematic view of the vortex shape, intersection region X and non-wind zone W when the airflow passes through the air deflection assembly of the present invention;

fig. 19 is a schematic structural view of an air deflection assembly installed in a floor type air conditioning indoor unit, in which a plurality of air deflection assemblies are installed at an air outlet of the floor type air conditioning indoor unit;

FIG. 20 is a view of an airflow field when the airflow passes through a conventional air deflector of the prior art;

FIG. 21 is a flow field diagram of airflow over a plurality of airfoils of the present application;

FIG. 22 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 vortex directions generated by two adjacent wing plates are converged;

FIG. 23 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 the vortexes generated by the two adjacent wing plates do not meet.

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
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 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 an aviation baffle subassembly and has included the air conditioner of this aviation baffle subassembly, and this air conditioner can be split type air conditioner or integral air conditioner. Regarding the air conditioner, the following description will be made with respect to a split type air conditioner (floor type air conditioner indoor unit) as a specific embodiment.

Referring to fig. 1 to 5, the wind deflector assembly 10 includes a wind deflector 11 and a wing plate 12. The air deflector 11 is provided with an air guiding surface 11 a; the wing plate 12 is obliquely attached to the air guide surface 11a by a connector 13, the wing plate 12 has a front edge 121, a rear edge 122, a front surface 12a and a rear surface 12b, the front edge 121 and the rear edge 122 are connected to the front surface 12a and the rear surface 12b, an air gap P (see fig. 3 in detail) is provided between the front edge 121 and the air guide surface 11a, a distance between the front edge 121 and the air guide surface 11a is smaller than a distance between the rear edge 122 and the air guide surface 11a, and the rear surface 12b is located between the front surface 12a and the air guide surface 11 a.

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 itself has a certain distance with the air guiding surface 11a so as to facilitate the air flow to pass through, and 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 may be a regular or irregular protrusion arranged on the air guiding surface 11a, or of course, may be a regular or irregular protrusion arranged on the surface of the wing plate 12. On the other hand, the connector 13 may have one end connected to the air guide surface 11a and the other end 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 member 13 may also be a sheet-like structure, for example, the sheet-like structure extends along the airflow direction, so that on the one hand, the sheet-like structure can play a role in guiding the airflow, on the other hand, the sheet-like structure can also reduce the airflow resistance, and on the other hand, the sheet-like structure also has a certain dividing role in the airflow passing through the air guiding surface 11a, so as to slow down the formation of.

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 the indoor air can fully exchange heat in the range of blowing out 2m from the air outlet to the air flow, and almost no wind feeling exists 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 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. 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.

Referring to fig. 10 to 13, the swirl strength is stronger in the range of α -15 ° to α -55 °, except that the influence range of the swirl 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.

The vortex core length of the vortex wake is at a maximum when the angle of attack α is 15 ° and α is 25 °. However, as can be seen from the streamline distribution in fig. 10 to 13, 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 streamline and velocity profiles obtained by numerical simulation calculation are shown in fig. 20 and 21. The wind guiding speed of the wing plate 12 and the outlet speed of the common wind guiding 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.

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. 22 and 23, 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 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.

Referring to fig. 19, as to the installation manner of the air deflector assembly 10 on the air conditioner, specifically, taking a floor type air conditioner indoor unit as an example, the floor type air conditioner indoor unit has an air outlet, a plurality of air deflector assemblies 10 are installed at the air outlet, the plurality of air deflector assemblies 10 are arranged at intervals along the up-down direction, and two rows of wing plates 12 adjacent to each other in the up-down direction are separated by the air deflector 11.

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:

the air guide plate is provided with an air guide surface;

2. The air deflection assembly of claim 1, 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.

3. The air deflection assembly of claim 2, wherein the plurality of wing plates are spaced apart along the length of the air deflection.

4. The air deflection assembly of claim 3, wherein the wing panel has an angle of attack with respect to the air deflection panel of no less than 15 ° and no greater than 70 °.

5. The air deflection assembly of claim 4, 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 °.

6. The air deflection assembly of claim 4, wherein the length of the air deflection plate is S, the distance between two adjacent wing plates is D, and the span of the wing plates is L, wherein S is an integral multiple of the sum of D and L.

7. The air deflection assembly of claim 4, wherein the wing panel has a chord length C and a span L, and wherein C/L is greater than 1.

8. The air deflection assembly of claim 7, wherein C/L has a value of not less than 1.5 and not greater than 4.

9. 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.

10. The air deflection assembly of claim 8, wherein the wing panel has a span L, L being no less than 10mm and no greater than 50 mm.

11. The air deflection assembly of claim 10, wherein L is not less than 25mm and not greater than 40 mm.

12. The air deflection assembly of claim 11, wherein the wing panel has a chord length C that is not less than 20mm and not greater than 80 mm.

13. The air deflection assembly of claim 12, wherein the chord length C is not less than 40mm and not greater than 60 mm.

14. The air deflection assembly of claim 8, wherein the connector member is attached to the back surface.

15. The air deflection assembly of claim 14, wherein the connecting member is provided in a cylindrical shape, and two ends of the cylindrical connecting member on the axis are respectively connected to the air deflection surface and the back surface.

16. The air deflection assembly of claim 14, wherein the connecting member is configured in a sheet shape, and the connecting member extends along the width direction of the air deflection plate.

17. An air deflection assembly according to claim 15 or claim 16, wherein the junction of the connector member with the rear face is disposed adjacent the leading edge.

18. The air deflection assembly of claim 17, wherein the attachment member is attached to the rear face at a position that is at a perpendicular bisector of the span.

19. The air deflection assembly of any one of claims 1 to 16, wherein the back surface is a curved surface and the ventral surface is a flat surface.

20. 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 19.

21. The air conditioner of claim 20, wherein the air conditioner is a split type air conditioner or a unitary type air conditioner.

22. The air conditioner according to claim 21, wherein the air conditioner is a floor type air conditioner indoor unit.

23. The air conditioner as claimed in claim 22, wherein said indoor unit of floor air conditioner has an air outlet, said air outlet is provided with a plurality of said air guiding plate assemblies, said plurality of said air guiding plate assemblies are arranged along the up and down direction at intervals, and two rows of said wing plates adjacent to each other up and down direction are separated by said air guiding plate.