CN111156680B

CN111156680B - Air deflector assembly and air conditioner

Info

Publication number: CN111156680B
Application number: CN201911219134.1A
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: 2023-09-12
Anticipated expiration: 2039-11-29
Also published as: CN111156680A

Abstract

The application discloses an air deflector assembly and an air conditioner, wherein the air deflector assembly comprises an air deflector and an air conditioner wing plate, the air deflector is provided with an air deflector surface, the air deflector surface is provided with a first edge and a second edge which are oppositely arranged, the first edge and the second edge both extend along the length direction of the air deflector, and the plane where the first edge and the second edge are positioned is S ₁ The method comprises the steps of carrying out a first treatment on the surface of the The wing plate is obliquely arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a web surface and a back surface, the web surface and the back surface are connected with the front edge and the rear edge, an air passing gap is formed between the front edge and the air guide surface, the distance between the front edge and the air guide surface is smaller than the distance between the rear edge and the air guide surface, and the plane where the front edge and the rear edge are located is S ₂ Plane S ₁ And plane S ₂ The included angle alpha is not greater than 35 deg.. The technical scheme of the application can realize rapid heat transfer, soften the airflow and realize the effect of no or slight wind sense.

Description

Air deflector assembly and air conditioner

Technical Field

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

Background

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

However, when the air deflector delivers air, the air flow speed is high, and cold air is easy to blow directly, so that discomfort and even cold of users are caused.

The current no wind sense air conditioner is mainly through setting up the micropore on the aviation baffle, through carrying out the step-down acceleration to the air current, makes stranded air current follow micropore blowout, forms many high-speed disturbance sources in the air outlet region, reaches the quick mixing of air outlet air current and environment air current, reaches the reduction air conditioner air-out distance, keeps sufficient refrigerating capacity simultaneously.

Because the wind resistance of the existing microporous air deflector is large, when the air quantity is large, the air flow is limited by the air deflector, and is difficult to flow out of the air deflector rapidly, so that the wind power is wasted, and the requirement of no wind sensation is difficult to be met rapidly.

Disclosure of Invention

The application mainly aims to provide an air deflector assembly, which aims to solve the technical problems of large wind resistance, poor wind sensation-free effect and the like of the conventional microporous air deflector.

In order to solve the above-mentioned problem, the utility model provides an air deflection assembly, include:

the air deflector is provided with an air deflector surface, the air deflector surface is provided with a first edge and a second edge which are oppositely arranged, the first edge and the second edge extend along the length direction of the air deflector, and the plane where the first edge and the second edge are located is S ₁ ；

The wing plate is obliquely arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a web surface and a back surface, the web surface and the back surface are connected with the front edge and the rear edge, an air passing gap is arranged between the front edge and the air guide surface, the distance between the front edge and the air guide surface is larger than the distance between the rear edge and the air guide surface, and the plane where the front edge and the rear edge are located is S ₂ Plane S ₁ And plane S ₂ The included angle alpha is not less than 5 degrees and not more than 35 degrees.

In one embodiment, plane S ₁ And plane S ₂ The included angle alpha is not less than 15 DEG and not more than 25 DEG

In one embodiment, the back surface has an arc length H corresponding to the airfoil section of the wing panel ₁ The arc length or the straight line length of the ventral surface corresponding to the airfoil section of the wing plate is H ₂ ，H ₁ Greater than H ₂ 。

In an embodiment, the ventral surface is located between the dorsal surface and the wind-guiding surface.

In one embodiment, the wing panel has a nose, the leading edge is located at the nose, and the nose is rounded.

In an embodiment, the wing plate further has a tail, the trailing edge is located at the tail, and the tail is disposed in a wedge shape.

In an embodiment, the chord length of the wing panel is C, the span of the wing panel is L, and the value of C/L is greater than 1.

In one embodiment, the value of C/L is not less than 1.5 and not greater than 4.

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

In an embodiment, the 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.

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

In one embodiment, the connector connects the back surface.

In one embodiment, the connecting piece is arranged in a sheet shape, and the connecting piece extends along the width direction of the air deflector.

In an embodiment, the back surface is a convex arc surface, and the web surface is a plane or a convex arc surface.

The application also discloses an air conditioner, which is provided with an air outlet, wherein the air outlet is provided with an air deflector assembly, the air deflector assembly comprises an air deflector and an air deflector plate, the air deflector is provided with an air deflector surface, the air deflector surface is provided with a first edge and a second edge which are oppositely arranged, the first edge and the second edge extend along the length direction of the air deflector, and the plane where the first edge and the second edge are positioned is S ₁ The method comprises the steps of carrying out a first treatment on the surface of the The wing plate is obliquely arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a web surface and a back surface, the web surface and the back surface are connected with the front edge and the rear edge, an air passing gap is formed between the front edge and the air guide surface, the distance between the front edge and the air guide surface is smaller than the distance between the rear edge and the air guide surface, and the plane where the front edge and the rear edge are located is S ₂ Plane S ₁ And plane S ₂ The included angle alpha is not less than 5 degrees and not more than 35 degrees.

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

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of an embodiment of an air deflection assembly of the present application;

FIG. 2 is a schematic view of the air deflection assembly of FIG. 1 from another perspective;

FIG. 3 is a further view of the air deflection assembly of FIG. 1;

FIG. 4 is a top view of the air deflection assembly of FIG. 1;

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

FIG. 6 is a graph comparing distances from the leading and trailing edges of the wing panels to the maximum thickness of the wing panels in the air deflection assembly of FIG. 5;

FIG. 7 is a graph comparing the ventral chord and the dorsal chord of the wing panel of FIG. 6;

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

FIG. 9 is a flow field schematic of an airflow from a leading edge to a trailing edge of an engine wing;

FIG. 10a is a schematic view of an airflow flow field where the airflow flows rearward from the front edge of the engine wing plate; wherein α=15°;

FIG. 10b is a schematic view of an airflow flow field where the airflow flows rearward from the front edge of the engine wing plate; wherein α=25°;

FIG. 10c is a schematic view of an airflow flow field where the airflow flows rearward from the front edge of the wing panel; wherein α=35°;

FIG. 10d is a schematic view of an airflow flow field where the airflow flows rearward from the front edge of the wing plate; wherein α=45°;

FIG. 10e is a schematic view of an airflow flow field where the airflow flows rearward from the front edge of the engine wing plate; wherein α=55°;

FIG. 10f is a schematic view of an airflow flow field where the airflow flows rearward from the front edge of the engine wing plate; wherein α=60°;

FIG. 10g is a schematic view of an airflow flow field where the airflow flows rearward from the front edge of the engine wing plate; wherein α=65°;

FIG. 10h is a graph showing the flow vorticity contour surface of the airflow flowing backward from the front edge of the wing plate; wherein α=70°;

FIG. 11a is a graph showing the flow vorticity contour profile of a flow flowing backward from the leading edge of the wing plate; wherein α=15°;

FIG. 11b is a graph showing the flow vorticity contour profile of a flow flowing backward from the leading edge of the wing plate; wherein α=25°;

FIG. 11c is a graph showing the flow vorticity contour profile of a flow flowing backward from the leading edge of the wing panel; wherein α=35°;

FIG. 11d is a graph showing the flow vorticity contour profile of a flow flowing backward from the leading edge of the wing plate; wherein α=45°;

FIG. 11e is a graph showing the flow vorticity contour profile of a flow flowing backward from the leading edge of the wing panel; wherein α=55°;

FIG. 11f is a graph showing the flow vorticity contour profile of a flow flowing backward from the leading edge of the wing panel; wherein α=60°;

FIG. 11g is a graph showing the flow vorticity contour surface of an airflow flowing backward from the front edge of the wing plate; wherein α=65°;

FIG. 11h is a graph showing the flow vorticity contour surface of the airflow flowing backward from the front edge of the wing plate; wherein α=70°;

FIG. 12 is a schematic view of an airflow flow field in which the airflow flows rearward from the front edge of the engine wing plate; wherein C/l=2;

FIG. 13 is a schematic view of an airflow flow field in which the airflow flows rearward from the front edge of the engine wing plate; wherein C/l=5;

FIG. 14 is a schematic view of an airflow flow field in which the airflow flows rearward from the front edge of the engine wing plate; wherein C/l=10;

FIG. 15 is a schematic flow diagram of an airflow at the trailing edge of a wing panel; wherein C/l=3, 2, 1.5;

FIG. 16 is a flow field diagram of air flow as it flows through a conventional air deflector of the prior art;

FIG. 17 is a flow field diagram of an airflow through a plurality of engine wings in accordance with the present application;

FIG. 18 is a schematic flow diagram of an airflow through a plurality of engine wings in the present application; wherein, because the D/L value is smaller, the vortex generated by two adjacent wing plates is intersected;

FIG. 19 is a schematic flow diagram of an airflow through a plurality of engine compartment flaps of the present application; the D/L value is proper, and vortex generated by two adjacent wing plates does not meet;

FIG. 20 is a flow field diagram of the airflow flowing 10 chords behind the wing panel of the present application;

FIG. 21 is a view of a sound pressure level distribution of a surface of a wing panel.

Reference numerals illustrate:

reference numerals	Name of the name	Reference numerals	Name of the name
				10	Air deflector assembly	11	Air deflector
12	Wing plate of machine	13	Connecting piece
				11a	Air guiding surface	11b	Leeward surface
111	A first edge	112	Second edge
				12c	Side surface	121	Leading edge
122	Trailing edge	12a	Ventral surface
				12b	Back surface	P	Overwind gap

The achievement of the objects, functional features and advantages of the present application will be further described with reference to the accompanying drawings, in conjunction with the embodiments.

Detailed Description

The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present application are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.

Furthermore, the description of "first," "second," etc. in this disclosure is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present application.

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

Referring to fig. 1-5, an air deflection assembly 10 includes an air deflection 11 and a wing panel 12. The air deflector 11 has an air guiding surface 11a, the air guiding surface 11a has a first edge 111 and a second edge 112 which are oppositely arranged, the first edge 111 and the second edge 112 extend along the length direction of the air deflector 11, and the plane where the first edge 111 and the second edge 112 are located is S ₁ The method comprises the steps of carrying out a first treatment on the surface of the The wing plate 12 is obliquely mounted on the air guiding surface 11a through a connecting piece 13, the wing plate 12 is provided with a front edge 121, a rear edge 122, a ventral surface 12a and a rear surface 12b, the ventral surface 12a and the rear surface 12b are both connected with the front edge 121 and the rear edge 122, an air passing gap P is formed between the front edge 121 and the air guiding surface 11a, the distance between the front edge 121 and the air guiding surface 11a is larger than the distance between the rear edge 122 and the air guiding surface 11a, and the plane where the front edge 121 and the rear edge 122 are located is S ₂ Plane S ₁ And plane S ₂ The included angle alpha is not less than 5 degrees and not more than 35 degrees.

The air guide plate 11 has a substantially square plate-like structure, and the air guide plate 11 further has a leeward surface 11b (leeward surface) opposite to the air guide surface 11a11b also have a wind guiding function at a certain angle). Of course, the air deflector 11 may have a certain arc, for example, the air guiding surface 11a is a concave arc surface, and the leeward surface 11b is a convex arc surface. When the air guiding surface 11a is a plane, the plane S ₁ Namely, the wind guiding surface 11a, when the wind guiding surface 11a is an arc surface, the plane S ₁ Is not overlapped with the wind guiding surface 11 a.

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

The leading edge 121 of the wing panel 12 refers to the front edge of the wing panel 12 when it is exposed to the wind, and the trailing edge 122 refers to the trailing edge of the wing panel 12 when it is exposed to the wind, i.e. the wing panel 12 when it is exposed to the wind, the airflow flows from the leading edge 121 to the trailing edge 122.

When the airflow passes through the wing plate 12, a part of the airflow flows along the ventral surface 12a and a part of the airflow flows along the rear surface 12b, and since the flow path of the airflow at the ventral surface 12a is smaller than that of the airflow at the rear 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 at the rear surface 12b is higher than that of the airflow at the ventral surface 12a, and thus the airflow pressure received by the rear surface 12b is smaller than that received by the ventral surface.

In addition, the nose (leading edge 121 is located at the nose) of the wing panel 12 is rounded, and the tail (trailing edge is located at the tail) of the wing panel 12 is substantially wedge-shaped.

The wing panel 12 has a wing section (taken by a section perpendicular to the leading edge 121 and the trailing edge 122) for which the back arc length H of the wing panel 12 ₁ The arcuate length (extending from the leading edge 121 along the back face 12b to the trailing edge 122) is greater than the linear or arcuate length H of the ventral face 12a of the wing panel 12 ₂ . For this wing panel 12, the wing panel 12 itself also has two sides 12c between the ventral 12a and dorsal 12b sides, the span L (for uniform spacing between the sides 12c this may refer to the length of the leading edge 121, or the length of the trailing edge 122) when the spacing between the opposing sides 12c is the same. The chord length C refers to 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 12 ₁ Is smaller than what is neededDistance C of the trailing edge 122 from the maximum thickness of the wing panel 12 ₂ . The back surface 12b may be a curved surface, and the web surface 12a may be a flat surface or a curved surface.

For the installation of the wing plate 12 and the wind deflector 11, the wing plate 12 is spaced from the wind guiding surface 11a to facilitate the air flow. The wing plate 12 and the wind deflector 11 are connected by a connecting member 13, and on the one hand, the connecting member 13 may have a columnar structure, may be a regular or irregular protrusion provided on the wind guiding surface 11a, or may be a regular or irregular protrusion provided on the surface of the wing plate 12. In a further aspect, the connector 13 may be connected to the wind-guiding surface 11a at one end and to the side, back or ventral surface 12b, 12a of the wing panel 12 at the other end. On the other hand, the connecting piece 13 may also be a sheet-like structure, for example, the sheet-like structure extends along the direction of the air flow, which on the one hand can play a role in guiding the air flow, on the other hand can reduce the resistance of the air flow, and on the other hand, has a certain division effect on the air flow passing through the air guiding surface 11a, and slows down the formation of vortex. The angle of attack α at the time of mounting the wing plate 12 on the wind deflector 11 will be discussed in detail later.

For an air conditioner, the wind speed of an air outlet is approximately 0.5 m/s-4 m/s, and for example, the wind speed can be reduced to approximately 0 after the air is guided by a common plate-shaped air guide plate and passes a distance of about 5 m. After passing through the air deflector assembly, the air speed can be reduced to be approximately 0 after passing through the distance of about 2m, the blown air flow and indoor air exchange heat fully within the range from the air outlet to the air flow blowing out by 2m, and the air speed is extremely low outside 2 m.

Referring to fig. 9, when the air flow blows across the width of the air deflector 11, a portion of the air flow forms a spiral wake with respect to the wing plate because the air flow passes from the ventral surface 12a to the dorsal surface 12b and from the leading edge 121 to the trailing edge 122. That is, the airflow is straight when flowing through the air deflector 11, and a plurality of vortex wake flows can be formed after being guided by the multi-machine wing plate 12, so that the mass and heat transfer effect is enhanced, and the convection heat exchange capacity is improved; the travel of the air flow is reduced on the premise of not reducing the heat exchange quantity; strong convection and strong heat exchange are realized in a range close to the air outlet, and the effect of soft wind sensation can be realized in a slightly far range.

In the above embodiment, the wing plate 12 is mounted on the air guide surface 11a in an inclined manner, but the inclination angle of the wing plate 12 itself cannot be too large or too small. The tilting of the wing panel 12 will be further discussed in this embodiment.

The wing plate 12 is mounted on the air guiding surface 11a in an inclined manner with respect to the plane S ₁ A kind of electronic device.

In theory, even if α=0, the airflow can form a vortex in the process of flowing from the front edge to the rear edge of the wing panel, but the vortex is relatively small in vortex quantity and weak in vortex strength. For a relatively good swirling effect α may be taken to be 5 °. Subsequent data will observe the degree of swirl and the amount of vorticity as alpha varies from 15 deg. to 70 deg..

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

Referring to fig. 10a to 10h, the vortex strength is strong in the range of α=15° to α=55°, except that the influence range of the vortex wake is small when α=15° and α=25° is not beneficial to the rotation of the rear air. The vortex situation changes significantly when α=70°, with weak wingtip vortex. The wingtip vortex situation is ideal when α=25° to α=55°.

But merely by virtue of the streamline distribution is not sufficient to judge the effect of alpha on vortex wake. The vorticity is a physical quantity reflecting the intensity of vortex, and the distribution of the equivalent surface of the vorticity around the wing is shown in fig. 11a to 11 h.

When the angles of attack α=15° and α=25°, the vortex cores (solid portions on both sides of the wing plate in fig. 11a to 11 h) of the vortex wake are the largest in length. However, as can be seen from the streamline distribution in fig. 10a to 10h, the wake flow influence range is relatively small due to the small attack angle α, so that the angle is suitable for the use situations of long-distance air supply and heat exchange efficiency enhancement. In the range of α=35° to α=55°, the vortex flow distribution is similar, and the larger the angle of attack α is, the stronger the ability to break up the incoming flow, so that it is considered that the effect of fluidizing the gas into the vortex wake is best when α=55°. The angle of attack of α=35° to α=55° is suitable for the design requirement of shorter distance air supply and soft wind feeling. When the attack angle α is too large, the raised wing plate 12 blocks the wind channel to affect the incoming wind volume, and when α=60° the vortex flow distribution range is reduced, and when α=70° the vortex flow distribution is already small, so comprehensive analysis considers that α >70 ° no vortex wake can be generated any more.

The obtained streamline and velocity distribution are shown in fig. 16 and 17 through numerical simulation calculation. At the beginning, the air flow velocity led out by the wing plate 12 and the air outlet velocity of the common air outlet are both 4m/s. The wake of the wing panel 12 can be seen to form a significant vortex with a local airflow velocity in front of the vortex being relatively high (at maximum 5.1 m/s), which is a strong mass transfer heat transfer zone, and behind which the airflow velocity is rapidly reduced, a relatively gentle range of wind speeds being rapidly reached in a slightly remote range.

In the above embodiment, referring to fig. 1 to 4, the number of the wing plates 12 may be one, and of course, in order to achieve better flow guiding effect, the number of the wing plates 12 is plural, and the plural wing plates 12 are arranged at intervals along the length direction of the air deflector 11. For example, the number of wing panels 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, where S is an integer multiple of the sum of D and L.

When the air is blown out along the width direction of the air guide plate 11 during air guiding, and when the air flows from the front edge 121 to the rear edge 122 along the back surface 12b and the ventral surface 12a, the air flow mainly forms vortex on the rear edge 122 and near the two side surfaces of the wing plate 12, so that, relatively speaking, if the wing span of the wing plate 12 is longer, the distance between the two adjacent vortices is larger. With continued reference to fig. 12, 13, 14 and 15, in order to generate more swirl in the air flow passing through the air deflection assembly 10, in this embodiment the chord length of the wing panel 12 is C and the span of the wing panel 12 is L, C/L > 1.

In fig. 12, C/l=2, C/l=4 in fig. 13, C/l=10 in fig. 14, C/l=3, 2, 1.5 (C/L ₁ ＝3，C/L ₂ ＝2，C/L ₃ As can be seen from these four figures, when C/l=4, the two vortices at the trailing edge of the wing plate 12 (which have not yet flowed out of the wing plate) almost come into contact together, so that C/L continues to rise, and the two vortices interfere with each other, thereby affecting mass transfer and subsequent heat exchange. In this example, 1.5.ltoreq.C/L.ltoreq.4.

When alpha=25°,1.5 is less than or equal to C/L is less than or equal to 4, and at the maximum wind speed (4 m/s), the sound pressure level distribution condition of the surface of the wing is as shown in fig. 21, and the sound pressure level of the normal wind deflector is about 38dB at the wind speed, so that the full sound pressure level of the whole wind deflector assembly can not be obviously improved by using the lifting wing. In FIG. 21, the sound pressure level distribution, Z, of the airfoil surface at a wind speed of 4m/s ₁ Region maximum 37dB, Z ₂ The area is a minimum of 26dB.

As the airflow blows across the adjacent two wing panels 12, the tips of the tails (the ends of the trailing edges 122) of the adjacent two wing panels 12 will both form vortices, the radii of which will become increasingly larger as the vortices flow away from the wing panels 12,

in this embodiment, referring to fig. 18 and 19, if the two wings are too close together, the vortices generated by the adjacent wing tips (the two tips of the trailing edge 122 of the wing plate 12) are prone to interference. If too far apart, more airflow does not flow past the tips, reducing the overall swirling effect. The best effect is that the vortices generated by two adjacent wingtips are just close in distance and do not intersect.

Therefore, the interval between the adjacent two wing plates 12 is not necessarily too small. In addition, if the space between the two wing plates 12 is too large, the blown swirling airflow is relatively loose, which is unfavorable for mass transfer and heat exchange.

Please refer to fig. 18, 19 and 20 (Q ₁ For one of the vortex flows, Q ₂ Another swirling airflow) within 10 chord lengths of the trailing edge 122 of the wing panel 12 (aft of the wing)The lines are in two cylindrical distribution, and the area with the fastest flow speed and the strongest forced convection heat exchange is arranged in the range, so that the tail streamline and the side wing tail streamline in the range are prevented from interfering as much as possible. It can be seen that the widest part of the streamline is about 2 times the span length, so that it is preferable to ensure that the wing-to-wing spacing is 2 times the span length. When the wing spacing is 1.3 times of the wing span, wake flows are intersected at the position 0.3m behind the wing, and at the moment, a better soft wind effect can be obtained, but the heat exchange capacity is reduced, and the continuous reduction of the spacing can lead to continuous reduction of the heat exchange capacity. Therefore, according to different use scenes and design requirements, the relation between the wing spacing and the span length is determined to be 1.3L-D-2L.

The size of the wing panel 12 should not be too large or too small, and if too large, the wind resistance is large, and the air output is affected; if too small, the swirling effect formed by the rear edge 122 of the wing panel 12 is poor. Considering the size of the air outlet of the air conditioner (the width of the air deflector is generally 60mm-120 mm), considering the movement (on and off) of the air deflector, the chord length Cmax of the wing plate 12 is required to be controlled within 80mm for preventing interference. The chord length C of the wing panel 12 is small, which is disadvantageous for formation of large-scale wingtip vortex, and therefore the limit minimum value is 20mm. Because the vortex is mainly generated on the wing tip, the too long wing span is not beneficial to the enhancement of the vortex, and the too short two wing tip vortices interfere and are also not beneficial to the generation of the vortex. Additionally, in a preferred embodiment, the wing panel 12 has a span L dimension in the range of 10mm to 50mm, and preferably a span dimension in the range of 25mm to 40mm.

For wing panels 12 having a span in the range 25mm to 40mm, 1.5C/L4 is required. The chord length of the wing panel 12 is also not too long, so that the chord length C of the wing panel 12 can be further controlled between 40mm and 60mm on the basis of the ratio.

The above embodiments have been described with respect to both the post-like connector 13 and the sheet-like connector 13, and in this embodiment, the connector 13 will be further described.

For the columnar connectors 13 (the embodiment of the columnar connectors 13 is not shown in the figure), after the air flows pass through the columnar connectors 13, each columnar connector forms a pair of vortex streets, and then continues to propagate forward, and the blown air flow has a karman vortex street effect, so that the air can be quickly mixed with indoor air, and the heat exchange mixed flow effect is further improved. Therefore, the columnar connector 13 is provided at a position close to the leading edge 121, and the space between the vortex street and the vortex can be widened to avoid interference between the vortex street and the vortex. In addition, the area between the adjacent two vortices is less affected by the air flow (air blow-through) before the radius of the adjacent two vortices expands and meets, so if the location where the cylindrical connecting piece 13 connects the back surface 12b is located at the perpendicular bisector of the span, the blank space between the adjacent two vortices can be exactly compensated.

Referring to fig. 2 and 5, for the sheet-like connection member 13, since the structure has a certain division effect on the airflow, the vortex formation (the formation of vortex in advance is unfavorable for the formation of vortex at the rear edge 122 of the wing plate 12, and the vortex may be rushed to vortex) can be greatly reduced, so that the sheet-like connection member 13 is disposed at a position close to the front edge 121, which can play a role in rectifying the airflow, and the vortex phenomenon of the subsequent airflow is greatly reduced when the airflow flows through the wing plate 12. If the position of the sheet-like connection 13 is on the midspan of the span, the radius and flow rate of the vortex formed by the two trailing tips of the trailing edge 122 of the wing panel 12 can be maintained uniform and the overall mass and heat transfer more uniform.

The foregoing description is only of the preferred embodiments of the present application and is not intended to limit the scope of the application, and all equivalent structural changes made by the description of the present application and the accompanying drawings or direct/indirect application in other related technical fields are included in the scope of the application.

Claims

1. An air deflection assembly, comprising:

A wing plate passing throughThe connecting piece is obliquely arranged on the air guide surface, the wing plate is provided with a front edge, a rear edge, a web surface and a back surface, the web surface and the back surface are connected with the front edge and the rear edge, an air passing gap is arranged between the front edge and the air guide surface, the distance between the front edge and the air guide surface is larger than the distance between the rear edge and the air guide surface, and the plane where the front edge and the rear edge are located is S ₂ Plane S ₁ And plane S ₂ The included angle alpha is not more than 35 degrees;

the arc length of the back surface corresponding to the airfoil section of the wing plate is H ₁ The arc length or the straight line length of the ventral surface corresponding to the airfoil section of the wing plate is H ₂ ，H ₁ Greater than H ₂ ；

The distance between the leading edge and the maximum thickness of the wing panel is less than the distance between the trailing edge and the maximum thickness of the wing panel.

2. The air deflection assembly of claim 1 wherein the plane S ₁ And plane S ₂ The included angle alpha is not less than 15 deg. and not more than 25 deg..

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

4. The air deflection assembly of claim 1, wherein the wing panels have wing tips, wherein the leading edges are located at the wing tips, and wherein the wing tips are rounded.

5. The air deflection assembly of claim 1, wherein the wing panels further have wing tails, wherein the trailing edges are located at the wing tails, and wherein the wing tails are disposed in a wedge-like configuration.

6. The air deflection assembly of claim 1, wherein the wing panels have a chord length C, and wherein the wing panels have a span L, and wherein the value of C/L is greater than 1.

7. The air deflection assembly of claim 6, wherein the C/L has a value of not less than 1.5 and not greater than 4.

8. The air deflection assembly of claim 7, wherein the spacing between adjacent ones of the wing panels is D, wherein the wing panels have a span of L, and wherein D is not less than 1.3L and not greater than 2L.

9. The air deflection assembly of claim 1, wherein the number of wing panels is a plurality, and wherein the plurality of wing panels are spaced apart along the length of the air deflection.

10. The air deflection assembly of claim 9, wherein the connector is coupled to the rear face.

11. The air deflection assembly of claim 10, wherein the connector members are arranged in a sheet-like configuration, and wherein the connector members extend in a width direction of the air deflection.

12. The air deflection assembly of any one of claims 1 to 7, wherein the rear face is a convex curved surface and the ventral face is a planar or convex curved surface.

13. An air conditioner having an air outlet, wherein the air outlet is provided with the air deflection assembly of any one of claims 1 to 12.