CN111076396B - Air deflector assembly and air conditioner - Google Patents
Air deflector assembly and air conditioner Download PDFInfo
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- CN111076396B CN111076396B CN201911217643.0A CN201911217643A CN111076396B CN 111076396 B CN111076396 B CN 111076396B CN 201911217643 A CN201911217643 A CN 201911217643A CN 111076396 B CN111076396 B CN 111076396B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F13/00—Details common to, or for air-conditioning, air-humidification, ventilation or use of air currents for screening
- F24F13/08—Air-flow control members, e.g. louvres, grilles, flaps or guide plates
- F24F13/081—Air-flow control members, e.g. louvres, grilles, flaps or guide plates for guiding air around a curve
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
- F24F1/00—Room units for air-conditioning, e.g. separate or self-contained units or units receiving primary air from a central station
- F24F1/0007—Indoor units, e.g. fan coil units
- F24F1/0011—Indoor units, e.g. fan coil units characterised by air outlets
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Air-Flow Control Members (AREA)
Abstract
The application discloses an air deflector assembly and an air conditioner, wherein the air deflector assembly comprises an air deflector and a plurality of wing groups, the air deflector is provided with an air deflector surface, and a first edge and a second edge which are positioned on two opposite sides of the air deflector surface, and the first edge and the second edge both extend along the length direction of the air deflector; the plurality of wing groups are arranged at intervals along the length direction of the air deflector, each wing group comprises a plurality of wing plates which are laterally stacked on the air guiding surface, the front edge of each wing plate faces towards the first edge, and the rear edge of each wing plate faces towards the second edge. 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
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, and a first edge and a second edge which are positioned on two opposite sides of the air deflector surface, wherein the first edge and the second edge extend along the length direction of the air deflector;
the plurality of wing groups are arranged at intervals along the length direction of the air deflector, each wing group comprises a plurality of wing plates which are laterally stacked on the air deflector, the front edge of each wing plate faces towards the first edge, and the rear edge of each wing plate faces towards the second edge.
In an embodiment, the number of laminated wing panels in each of the wing groups is 2 to 5.
In an embodiment, the wing plate has a back surface and a web surface, and in the same wing group, the web surface of each wing plate is disposed toward the same end in the length direction of the wind deflector.
In one embodiment, the leading edges of the plurality of wing panels extend along the same straight line in the same wing group.
In one embodiment, the chord length of the wing panels in the stacking direction is gradually reduced in the same wing group.
In an embodiment, in the same wing group, an angle of attack of the wing plate with respect to the width direction of the wind deflector is α, and the α gradually decreases in the stacking direction of the wing plates.
In an embodiment, the α is not less than 15 °, and not greater than 70 °.
In an embodiment, the angle of attack of the two adjacent wing panels is between 5 ° and 30 °.
In an embodiment, the arc length of the back surface of each wing plate corresponding to the wing section of the wing plate is H 1 The arc length or the straight line length of the web surface of the wing plate corresponding to the wing section of the wing plate is H 2 ， H 1 Greater than H 2 。
In an embodiment, in the same wing panel, the distance between the leading edge and the maximum thickness of the wing panel is smaller than the distance between the trailing edge and the maximum thickness of the wing panel.
In an embodiment, the air deflector has opposite ends located in a length direction of the air deflector, the plurality of wing groups include a first wing group and a second wing group, web surfaces of wing plates in the first wing group are all arranged towards one end of the air deflector, web surfaces of wing plates in the second wing group are all arranged towards the other end of the air deflector, and wing plates in the first wing group and wing plates in the second wing group are alternately arranged in the length direction of the air deflector.
In an embodiment, in the two adjacent wing groups with the web surfaces opposite to each other, a distance between the two front edges of the two wing plates of the same layer is greater than a distance between the two rear edges.
The application also discloses an air conditioner, which is provided with an air outlet, wherein an air deflector assembly is arranged at the air outlet, the air deflector assembly comprises an air deflector and a plurality of wing groups, the air deflector is provided with an air deflector surface, and a first edge and a second edge which are positioned on two opposite sides of the air deflector surface, and the first edge and the second edge extend along the length direction of the air deflector; the plurality of wing groups are arranged at intervals along the length direction of the air deflector, each wing group comprises a plurality of wing plates which are laterally stacked on the air guiding surface, the front edge of each wing plate faces towards the first edge, and the rear edge of each wing plate faces towards the second edge.
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 top plan view of the air deflection assembly of FIG. 1;
FIG. 3 is a rear view of the air deflection assembly of FIG. 1;
fig. 4 is a perspective view of the wing plate of the air deflection assembly of fig. 1;
FIG. 5 is a graph of arc length comparison of the ventral and dorsal surfaces of the wing panel of FIG. 4;
FIG. 6 is a graph comparing distances from the leading and trailing edges of the wing panel of FIG. 5 to the maximum thickness of the wing panel;
FIG. 7 is a schematic flow field illustration of airflow from the leading edge to the trailing edge of the wing plate;
FIG. 8a 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. 8b 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. 8c 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. 8d 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. 8e 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. 8f 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. 8g 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. 8h 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. 9a 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. 9b is a graph showing the flow vorticity contour of an airflow flowing backward from the front edge of the wing plate; wherein α=25°;
FIG. 9c is a graph showing the flow vorticity contour profile of the airflow flowing backward from the front edge of the wing plate; wherein α=35°;
FIG. 9d is a graph of the flow vorticity contour of the airflow flowing backward from the leading edge of the wing plate; wherein α=45°;
FIG. 9e is a graph showing the flow vorticity contour profile of a flow flowing backward from the leading edge of the wing plate; wherein α=55°;
FIG. 9f is a graph of the flow vorticity contour of an airflow flowing backward from the leading edge of the wing panel; wherein α=60°;
FIG. 9g is a graph showing the flow vorticity contour surface of the airflow flowing backward from the front edge of the wing plate; wherein α=65°;
FIG. 9h 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. 10 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. 11 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. 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=10;
FIG. 13 is a schematic flow diagram of an airflow at the trailing edge of a wing panel; wherein C/l=3, 2, 1.5;
FIG. 14 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. 15 is a schematic flow diagram of an airflow through a plurality of engine flaps of the present application; where the D/L values are appropriate, the vortices produced by adjacent wing panels do not meet.
Reference numerals illustrate:
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 to 5, the wind guiding assembly includes a wind guiding plate 11 and a plurality of wing groups 12', the wind guiding plate 11 has a wind guiding surface 11a, and a first edge 111 and a second edge 112 located at opposite sides of the wind guiding surface 11a, and the first edge 111 and the second edge 112 extend along a length direction of the wind guiding plate 11. The plurality of wing groups 12 'are arranged at intervals along the length direction of the air deflector 11, each wing group 12' comprises a plurality of wing plates 12 laterally stacked on the air deflector surface 11a, a front edge 121 of each wing plate 12 is arranged towards the first edge 111, and a rear edge 122 of each wing plate 12 is arranged towards the second edge 112.
The number of wing panels 12 in the wing group 12' may be 2 to 5, for example 2. The wing set 12' includes a first wing plate and a second wing plate, the first wing plate is mounted on the wind guiding surface 11a, the first wing plate has a first front edge, a first rear edge, a first web surface, a first back surface, and two first side surfaces, the first side surfaces connect the first web surface and the first back surface, one of the first side surfaces connects the wind guiding surface 11a, and the first front edge is located between the first edge 111 and the first rear edge; the second wing plate is provided with a second front edge, a second rear edge, a second web surface, a second back surface and two second side surfaces, the second side surfaces are connected with the second web surface and the second back surface, and the second front edge is positioned between the first edge and the second rear edge; the second wing plate is mounted on the other first side surface of the first wing plate through one of the second side surfaces. The leading edges of the two wing panels stacked together may extend along the same straight line.
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 which extend in the longitudinal direction thereof and are provided opposite to each other, and the air guide plate 11 further has a leeward surface 11b (the leeward surface 11b also has an air guide function when a certain angle is provided) opposite to the air guide surface 11 a. Of course, the air deflector 11 may have a certain arc, for example, the air deflector 11a may be a concave arc surface and the leeward surface 11b may be a convex arc surface. The wind-guiding surface 11a and the leeward surface 11b may be both planar.
Referring to fig. 4 to 7, the wing panel 12 has a structure similar to that of an aircraft, as the name implies. 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. For this airfoil section, the back arc length of the wing panel 12 (along the back from the leading edge 12112b extends to the trailing edge 122) is greater than the linear or arcuate length of the ventral surface 12a of the wing panel 12. For the wing panel 12, the wing panel 12 itself also has two sides 12c between the ventral 12a and dorsal 12b sides, with the span L referring to the spacing between the opposite sides of the wing panel 12 (for uniform spacing between the sides 12 c). The chord length C refers to the linear distance between the leading edge 121 and the trailing edge 122. Distance L of the leading edge 121 from the maximum thickness of the wing panel 12 1 Less than the distance L at the maximum thickness of the trailing edge 122 from 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 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 2.5m, 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 almost no wind sensation exists outside 2 m.
Referring to fig. 7, when the airflow is blown along the width direction of the wind deflector 11, part of the airflow forms a spiral wake with respect to the wing because part of the airflow passes from the ventral surface 12a to the dorsal surface 12b and part of the airflow passes 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 a plurality of wing plates 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.
While the stacked wing panels 12 may provide more swirling airflow, the manner in which the wing panels 12 are stacked is also taught. For example, if the two wing plates 12 are stacked in opposite directions (the ventral surfaces are opposite), the air at the bottom layer interferes with each other, and the swirling effect is reduced. In view of this, in the present embodiment, the wing plates 12 have a back surface 12b and a ventral surface 12a, and in the same wing group 12', the ventral surface 12a of each wing plate 12 is disposed toward the same end in the longitudinal direction of the wind deflector 11.
In an embodiment, in the same wing group 12', the chord length of the wing plates 12 is gradually reduced in the stacking direction, and the attack angle of the wing plates 12 with respect to the width direction of the wind deflector 11 is α, and the α is gradually reduced in the stacking direction of the wing plates 12. It is mainly considered here that the bottom wing plate 12 is for forming a large vortex quantity, and the airflow resistance around the bottom wing plate 12 is relatively large while forming a large vortex quantity, the chord length of the wing plate 12 is gradually reduced in the stacking direction, and the attack angle α is also gradually reduced, so that the airflow above the bottom wing plate 12 can be fully utilized, and the bottom wing plate 12 is also assisted in delivering a vortex airflow.
Further, since the plurality of stacked wing plates 12 are offset in the above manner, the wing plates 12 positioned at the non-bottom layer can generate two vortices, and thus a preferable vortex air flow can be obtained.
Further, on the basis of the above embodiment, the wind deflector 11 has opposite ends located in the length direction thereof, the plurality of wing groups 12' include a first wing group and a second wing group, the ventral surfaces 12a of the wing plates 12 in the first wing group are each disposed toward one end of the wind deflector 11, the ventral surfaces 12a of the wing plates 12 in the second wing group are each disposed toward the other end of the wind deflector 11, and the wing plates 12 in the first wing group and the wing plates 12 in the second wing group are alternately disposed in the length direction of the wind deflector 11. Here, in the two wing groups 12' alternately arranged (the ventral surfaces 12a are opposite), on the one hand, the flow rate of the air flow passing between the two wing plates 12 can be locally increased, thereby increasing the swirling effect.
In the two adjacent wing groups 12' with the ventral surfaces 12a opposite to each other, the distance between the front edges 121 of the two wing plates 12 of the same layer is greater than the distance between the rear edges. However, the angle between the opposite wing plates 12 of the ventral surface 12a should not be too large or too small. The included angle is too large, so that the vortex quantity of vortex is influenced; the included angle is too small, which is unfavorable for the increase of vortex. In the present embodiment, among the adjacent two wing panels 12 opposing the ventral surface 12a, the included angle of the two wing panels 12 is not less than 10 ° and not more than 165 °. Preferably, the included angle is between 45 and 75 degrees. Here, the angle is an angle formed by chord planes of the two wing plates 12.
Regarding the problem of the angle of attack of the wing plate 12 itself, a simulation experiment will be performed with the wing plate 12 at various angles, in which, in view of the difficulty in measuring the single-side vorticity, a double-side vortex situation is simulated in the simulation experiment.
Referring to fig. 8a to 9h, 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. 8a to 8h, 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. 9a to 9 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. 9a to 9 h) of the vortex wake are the largest in length. However, as can be seen from the streamline distribution in fig. 8a to 8h, 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.
And obtaining streamline and speed distribution through numerical simulation calculation. The speed of the air guide of the wing plate 12 and the speed of the air guide outlet of the common wing plate are both 4m/s. The wake of the wing plate 12 forms an obvious vortex, the local airflow speed in the front of the vortex is larger (the maximum is 5.1 m/s), the area is a strong mass transfer heat transfer area, the airflow speed behind the area is rapidly reduced, and a softer wind speed range can be quickly reached in a slightly far range.
According to the technical scheme, the wing plates 12 are arranged on the air deflector 11, when air flows along the front edge 121 of the wing plates 12 to the rear edge 122 of the wing plates 12, vortex is formed at the rear edge 122 of the wing plates 12, the radius of the vortex is gradually enlarged, and the vortex speed is gradually reduced in the subsequent operation process, so that rapid heat transfer can be realized, the air flow is gentle, and no-wind effect or a slight-wind effect is realized.
In the above embodiment, referring to fig. 1, 2 and 3, 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 wind 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. 10, 11, 12 and 13, 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. 10, C/l=2, C/l=4 in fig. 11, C/l=10 in fig. 12, and C/l=3, 2, and 1.5 in fig. 13, it can be seen from these three figures that when C/l=4, the two vortices at the rear edge of the wing plate almost 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.
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. 14 and 15, if the two wings are too close together, the vortices generated by the adjacent two 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 vortex generated by two adjacent wing tips is just close at a far distance and does not want to 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. 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.
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 60-120 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.
In the present embodiment, the wing panel 12 has a span L ranging from 10mm to 50mm, preferably 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 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 (9)
1. An air deflection assembly, comprising:
the air deflector is provided with an air deflector surface, and a first edge and a second edge which are positioned on two opposite sides of the air deflector surface, wherein the first edge and the second edge extend along the length direction of the air deflector;
the plurality of wing groups are arranged at intervals along the length direction of the air deflector, each wing group comprises a plurality of wing plates which are laterally stacked on the air deflector, the front edge of each wing plate is arranged towards the first edge, and the rear edge of each wing plate is arranged towards the second edge;
in the same wing group, the attack angle of the wing plate relative to the width direction of the air deflector is alpha, and the alpha is gradually reduced in the stacking direction of the wing plates; the alpha is not less than 15 DEG and not more than 70 DEG;
the arc length of the back surface of each wing plate corresponding to the wing section of the wing plate is H 1 The arc length or the straight line length of the web surface of the wing plate corresponding to the wing section of the wing plate is H 2 ，H 1 Greater than H 2 ；
In the same wing panel, the distance between the front edge and the maximum thickness of the wing panel is smaller than the distance between the rear edge and the maximum thickness of the wing panel.
2. The air deflection assembly of claim 1, wherein the number of stacked wing plates in each of the wing groups is from 2 to 5.
3. The air deflection assembly of claim 1, wherein the wing panels have a back side and a ventral side, and wherein the ventral side of each wing panel is disposed toward the same end of the length of the air deflection in the same set of wings.
4. The air deflection assembly of claim 3, wherein the leading edges of a plurality of said wing panels extend along a common line in the same set of wings.
5. The air deflection assembly of claim 1, wherein adjacent ones of the wing plates have an angle of attack that varies from 5 ° to 30 °.
6. The air deflection assembly of claim 1, wherein the distance between the leading edge and the maximum thickness of the wing panel is less than the distance between the trailing edge and the maximum thickness of the wing panel in the same wing panel.
7. The air deflection assembly of claim 6, wherein the air deflection has opposite ends in a length direction thereof, wherein the plurality of wing groups includes a first wing group and a second wing group, wherein a ventral surface of the wing plates in the first wing group is disposed toward one end of the air deflection, wherein a ventral surface of the wing plates in the second wing group is disposed toward the other end of the air deflection, and wherein the wing plates in the first wing group and the wing plates in the second wing group are alternately disposed in the length direction of the air deflection.
8. The air deflection assembly of claim 7, wherein the pitch between the leading edges of two wing panels of a common layer is greater than the pitch between the trailing edges of two wing panels of an adjacent pair of wing groups disposed opposite the ventral surface.
9. 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 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911217643.0A CN111076396B (en) | 2019-11-29 | 2019-11-29 | Air deflector assembly and air conditioner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN111076396A (en) | 2020-04-28 |
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