CN211650680U

CN211650680U - Air deflector assembly and air conditioner

Info

Publication number: CN211650680U
Application number: CN201922131460.9U
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 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 board pass through the connecting piece install in the wind-guiding surface, the wing board 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 trailing edge with have the air gap between the wind-guiding surface, the trailing edge for the leading edge is closer to the wind-guiding surface, the back corresponds the arc length of the airfoil section of wing board is H₁Said ventral surface corresponding to the arc length or straight line of the airfoil section of said wing panelLength H₂，H₁Greater than H₂And the ventral surface is positioned between the back surface and the air guide surface. The technical scheme of the utility model can realize the rapid heat transfer of air conditioner, 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;

the wing board, the wing board pass through the connecting piece install in the wind-guiding surface, the wing board 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 trailing edge with there is the air gap between the wind-guiding surface, the trailing edge for the leading edge is closer to the wind-guiding surface, the back corresponds the arc length of the airfoil section of wing board 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 H₂And the ventral surface is positioned between the back surface and the air guide surface.

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 distance between the leading edge and the maximum thickness of the wing plate is C₁The distance between the trailing edge and the maximum thickness position of the wing plate is C₂，C₁Less than C₂。

In an embodiment, the air guide surface has a first edge and a second edge that are arranged oppositely, the first edge and the second edge both extend along the length direction of the air guide plate, and a plane where the first edge and the second edge are located is S₁The plane of the front edge and the plane of the rear edge are S₂，S₁And S₂The included angle α is not less than 15 degrees and not more than 70 degrees

In one embodiment, α is not less than 35 ° and not more than 55 °.

In one embodiment, the chord length of the wing plate is C, the wing span of the wing plate is L, C is not less than 20mm and not more than 60mm, L is not less than 10mm and not more than 40mm, and the value of L/C is less than 1.

In one embodiment, the value of L/C is not less than 0.25 and not greater than 2/3.

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

In one embodiment, the air guide surface is arranged in a concave arc surface.

In an embodiment, the air guide plate assembly further includes at least one guide bracket, two ends of the guide bracket are connected to the air guide surface, a guide channel is formed by enclosing between an inner surface of the guide bracket and the air guide surface, the guide channel guides the air along a width direction of the air guide plate, and the plurality of wing plates are disposed in the guide channel.

In one embodiment, the middle part of the guide bracket is connected with the air guide surface through a support leg.

In an embodiment, the number of the guide supports is two, the two guide supports are arranged at intervals in the length direction of the air deflector, the plurality of wing plates include a first wing group and a second wing group, and the first wing group and the second wing group are arranged in the two guide channels.

The utility model discloses still disclose an air conditioner, have the air outlet, air outlet department installs at least one air deflection assembly, air deflection assemblyThe wind guide plate is provided with a wind guide surface; the wing board pass through the connecting piece install in the wind-guiding surface, the wing board 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 trailing edge with have the air gap between the wind-guiding surface, the trailing edge for the leading edge is closer to the wind-guiding surface, the back corresponds the arc length of the airfoil section of wing board 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 H₂And the ventral surface is positioned between the back surface and the air guide surface.

In one embodiment, the air conditioner is a wall-mounted air conditioner indoor unit.

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 view of an embodiment of an air deflection assembly according to the present invention;

FIG. 2 is a rear view of the air deflection assembly of FIG. 1;

FIG. 3 is another perspective view of the air deflection assembly of FIG. 1;

FIG. 4 is a front view of the air deflection assembly of FIG. 3;

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

FIG. 6 is a schematic view of the wing plate and the air deflector of FIG. 5;

FIG. 7 is a schematic structural view of the wing plate of FIG. 7;

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 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 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. 17 is a schematic structural view of an air guide plate assembly installed in a floor type air conditioner indoor unit, in which a plurality of air guide plate assemblies are installed at an air outlet of the floor type air conditioner indoor unit;

FIG. 18 is a view of the airflow field when the airflow passes through a conventional air deflector of the prior art;

FIG. 19 is a flow field diagram of airflow over a plurality of airfoils of the present application;

FIG. 20 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. 21 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. 22 is a flow field diagram of the air flow 10 chord lengths behind the airfoils of the present application;

fig. 23 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	111	First edge
				112	Second edge	12c	Side surface
121	Leading edge	122	Trailing edge
				12a	Ventral surface	12b	Back side of the panel
140	Flow guide channel	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 wall-mounted air conditioner indoor unit as a specific example (see fig. 17).

Referring to fig. 1 to 8, the air deflection assembly 10 includes an air deflection plate 11 and a wing plate 12, the air deflection plate 11 has an air deflection surface 11 a; the wing plate 12 is 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 ventral surface 12a and a rear surface 12b, the ventral surface 12a and the rear surface 12b are both connected to the front edge 121 and the rear edge 122, an air gap P is provided between the rear edge 122 and the air guide surface 11a, the rear edge 122 is closer to the air guide surface 11a than to the front edge 121, and the arc length of the rear surface 12b corresponding to the airfoil section of the wing plate 12 is H₁The ventral surface 12a has an arc length or a straight length H corresponding to the airfoil section of the wing plate 12₂(FIG. 7), H₁Greater than H₂And the ventral surface 12a is located between the rear surface 12b 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 edge 111 and a second edge 112 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. 7, 8 and 9, wing panel 12, as the name implies, is constructed and operates in a manner similar to 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.

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 tip 12.

Referring to fig. 5 to 8, for the wing plate 12, the wing plate 12 itself has two side surfaces 12c located between the ventral surface 12a and the dorsal surface 12b, and the span L refers to the distance between the two opposite side surfaces of the wing plate 12 (for a uniform distance between the two side surfaces 12 c). 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 is spaced from the air guiding surface 11a for the air flow to pass through. The wing plate 12 and the air guiding plate 11 are connected by a 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 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 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 in the part of the airflow relative to the wing plate 12. 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 embodiment, the wing plate 12 is attached to the air guide surface 11a, but the inclination angle of the wing plate 12 itself cannot be too large or too small. In the present embodiment, the inclination of the wing plate 12 will be further discussedThe theory is as follows. Defining the plane of the first edge 111 and the second edge 112 as S₁The plane of the leading edge 121 and the trailing edge 122 is S₂，S₁And S₂The included angle α is not less than 15 degrees and not more than 70 degrees, here, the wind guide surface 11a can be a plane or a cambered surface, when the wind guide surface 11a is a plane, the plane S is₁Namely 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. 10 to 13, the wing plate 12 is obliquely installed on the wind guide surface 11a with respect to the plane S₁In (1).

The following simulation experiment was conducted for the vortex case when α was varied between 15 ° and 70 °.

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 streamline and velocity profiles obtained by numerical simulation calculations are shown in fig. 18 and 19. 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.

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. 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 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. 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 the 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, so that the C/L continues to rise, and the two vortices will interfere with each other, thereby affecting the mass transfer and subsequent heat exchange. In this embodiment, 1.5. ltoreq. C/L. ltoreq.4.

In addition, referring to fig. 23, when C/L is greater than or equal to 1.5 and less than or equal to 4, and at the maximum wind speed (4m/s), the sound pressure level distribution of the surface of the wing is as shown in fig. 22, and the sound pressure level is about 38dB at the wind speed using the normal wind deflector, it can be seen that the use of the lifting wing does not significantly improve the collective sound pressure level of the whole wind deflector assembly. In FIG. 22, the sound pressure level distribution, Z, of the airfoil surface at a wind speed of 4m/s₁Maximum region 37dB, Z₂The area is a minimum of 26 dB.

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 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. 20, 21 and 22 (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, 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.

Further, referring to fig. 1 to 5, in a preferred embodiment, the air guiding plate assembly 10 further includes at least one air guiding bracket 14, two ends of the air guiding bracket 14 are connected to the air guiding surface 11a, a guiding channel 140 is formed between an inner surface of the air guiding bracket 14 and the air guiding surface 11a, the guiding channel 140 guides the air along a width direction of the air guiding plate 11, and the wing plates 12 are disposed in the guiding channel 140.

The guide bracket 14 is arranged to collect the airflow on the one hand, so that the airflow can flow to the wing plate 12 more smoothly; on the other hand, the air flow guiding device has a guiding function on the air flow, and reduces the formation of the vortex inside the air outlet.

In one embodiment, the middle of the air guide bracket 14 is connected to the air guide surface 11a through a leg 15. Therefore, on one hand, the flow guide support 14 can be strengthened, and on the other hand, the airflow flowing through the flow guide channel 140 can be divided into a plurality of areas, so that the formation of vortex is further reduced, and the wind resistance is reduced.

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.

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 plurality of wing plates are spaced apart along the length of the air deflection.

3. The air deflection assembly of claim 2, wherein the leading edge is spaced from the maximum thickness of the wing panel by a distance C₁The distance between the trailing edge and the maximum thickness position of the wing plate is C₂，C₁Less than C₂。

4. The air deflection assembly of claim 3, wherein the air deflection surface has a first edge and a second edge disposed opposite to each other, the first edge and the second edge both extending along the length of the air deflection plate, and the first edge and the second edge are in a plane S₁The plane of the front edge and the plane of the rear edge are S₂，S₁And S₂Included angle α is not less than 15 ° and not more than 70 °.

5. The air deflection assembly of claim 4, wherein α is not less than 35 ° and not more than 55 °.

6. The air deflection assembly of claim 4, wherein the wing panel has a chord length C and a span L, wherein C is not less than 20mm and not greater than 60mm, L is not less than 10mm and not greater than 40mm, and L/C has a value less than 1.

7. The air deflection assembly of claim 6, wherein the value of L/C is not less than 0.25 and not greater than 2/3.

8. The air deflection assembly of claim 6, wherein the distance between adjacent wing plates is D, D being not less than 1.3L and not more than 2L.

9. The air deflection assembly of claim 6, wherein the air deflection surface is concavely curved.

10. The air deflection assembly according to any one of claims 1 to 9, further comprising at least one air deflection bracket, wherein two ends of the air deflection bracket are connected to the air deflection surface, an air deflection channel is defined between an inner surface of the air deflection bracket and the air deflection surface, the air deflection channel guides air in a width direction of the air deflection plate, and a plurality of wing plates are disposed in the air deflection channel.

11. The air deflection assembly of claim 10, wherein the central portion of the deflection bracket is connected to the air deflection surface by a leg.

12. The air deflection assembly of claim 10, wherein the number of deflection brackets is two, the two deflection brackets are spaced apart along the length of the air deflection panel, and the plurality of wing panels includes a first wing group and a second wing group, the first wing group and the second wing group being disposed within the two deflection channels.

13. An air conditioner having an outlet, wherein at least one air deflection assembly as claimed in any one of claims 1 to 12 is mounted at the outlet.

14. The air conditioner of claim 13, wherein the air conditioner is a wall-mounted indoor air conditioner.