CN111076396A - Air deflector assembly and air conditioner - Google Patents
Air deflector assembly and air conditioner Download PDFInfo
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- CN111076396A CN111076396A CN201911217643.0A CN201911217643A CN111076396A CN 111076396 A CN111076396 A CN 111076396A CN 201911217643 A CN201911217643 A CN 201911217643A CN 111076396 A CN111076396 A CN 111076396A
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- wing
- edge
- air
- plate
- air deflection
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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
Abstract
The invention 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 guide surface, a first edge and a second edge, the first edge and the second edge are positioned on two opposite side edges of the air guide surface, and the first edge and the second edge both extend along the length direction of the air deflector; the wing groups are arranged at intervals along the length direction of the air guide plate, each wing group comprises a plurality of wing plates which are laterally stacked on the air guide surface, the front edge of each wing plate faces the first edge, and the rear edge of each wing plate faces the second edge. The technical scheme of the invention can realize rapid heat transfer, light and soft airflow and realize the effect of no wind feeling or slight wind feeling.
Description
Technical Field
The invention 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 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.
Disclosure of Invention
The invention mainly aims to provide an air deflector component, and aims to solve the technical problems of large wind resistance, no wind feeling effect and poor performance of the existing microporous air deflector.
To solve the above problem, the present invention provides an air deflector assembly, comprising:
the air guide plate is provided with an air guide surface, a first edge and a second edge, wherein the first edge and the second edge are positioned on two opposite side edges of the air guide surface, and the first edge and the second edge both extend along the length direction of the air guide plate;
the wing sets are arranged at intervals along the length direction of the air guide plate, each wing set comprises a plurality of wing plates which are laterally stacked on the air guide surface, the front edge of each wing plate faces the first edge, and the rear edge of each wing plate faces the second edge.
In one embodiment, the number of stacked wing panels in each of said wing sets is 2 to 5.
In one embodiment, the wing plates have a back surface and a ventral surface, and the ventral surface of each wing plate is arranged towards the same end of the air deflector in the length direction in the same wing group.
In one embodiment, the leading edges of the wing panels extend along a common line in the same wing group.
In one embodiment, the chord length of the wing panel is tapered in the stacking direction in the same wing group.
In an embodiment, in the same wing group, an attack angle of the wing plate relative to the width direction of the air deflector is α, and the angle α is gradually reduced in the stacking direction of the wing plates.
In one embodiment, the α is not less than 15 ° and not more than 70 °.
In one embodiment, the difference between the angles of attack of the two adjacent wing plates is between 5 ° and 30 °.
In one embodiment, the arc length of the back surface of each wing plate corresponding to the wing section of the wing plate is H1The ventral surface of the wing plate has an arc length or a straight length H corresponding to the airfoil section of the wing plate2， H1Greater than H2。
In an embodiment, in the same wing panel, the distance of the leading edge from the maximum thickness of the wing panel is less than the distance of the trailing edge from the maximum thickness of the wing panel.
In an embodiment, the air deflector has two opposite ends located in the length direction of the air deflector, the plurality of wing groups include a first wing group and a second wing group, ventral surfaces of wing plates in the first wing group are all arranged towards one end of the air deflector, ventral surfaces of wing plates in the second wing group are all arranged towards the other end of the air deflector, and the wing plates in the first wing group and the wing plates in the second wing group are alternately arranged in the length direction of the air deflector.
In one embodiment, in two adjacent wing sets with the opposite ventral surfaces, the distance between the two leading edges of the two wing plates in the same layer is greater than the distance between the two trailing edges.
The invention 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 guide surface, a first edge and a second edge, the first edge and the second edge are positioned at two opposite side edges of the air guide surface, and the first edge and the second edge both extend along the length direction of the air deflector; the wing groups are arranged at intervals along the length direction of the air guide plate, each wing group comprises a plurality of wing plates which are laterally stacked on the air guide surface, the front edge of each wing plate faces the first edge, and the rear edge of each wing plate faces the second edge.
According to the technical scheme, the wing plate is arranged on the air deflector, when airflow flows to the rear edge of the wing plate along the front edge of the wing plate, a vortex is formed at the rear edge of the wing plate, the radius of the formed vortex is gradually enlarged in the subsequent operation process, and the vortex speed is gradually reduced, so that rapid heat transfer can be realized, the airflow is softened lightly, and the effect of no wind sensation or slight wind sensation is realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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 view of an embodiment of an air deflection assembly according to the present invention;
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 a wing panel of the air deflection assembly of FIG. 1;
FIG. 5 is a graph comparing the arc length of the ventral and dorsal faces of the wing plate of FIG. 4;
FIG. 6 is a comparison of the distance 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 view of the flow field of the airflow from the leading edge to the trailing edge of the wing panel;
fig. 8a is a schematic view of the airflow field with the airflow flowing backwards from the leading edge of the wing plate, wherein α is 15 °;
FIG. 8b is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 25;
fig. 8c is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 35 °;
fig. 8d is a schematic view of the airflow field with the airflow flowing backwards from the leading edge of the wing plate, wherein α is 45 °;
fig. 8e is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 55 °;
fig. 8f is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate, where α is 60 °;
fig. 8g is a schematic view of the airflow field with the airflow flowing backwards from the leading edge of the wing plate, wherein α is 65 °;
FIG. 8h is a plot of the flow vorticity contour profile for the flow aft from the leading edge of the wing plate, where α is 70;
FIG. 9a is a plot of the profile of the flow vorticity for a flow flowing aft from the leading edge of the wing plate, where α is 15 °;
FIG. 9b is a plot of the profile of the flow vorticity for a flow flowing aft from the leading edge of the wing plate, where α is 25 °;
FIG. 9c is a graph of the profile of the contour of the vorticity of the air flowing aft from the leading edge of the wing plate, wherein α is 35;
FIG. 9d is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 45;
FIG. 9e is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 55;
FIG. 9f is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 60;
FIG. 9g is a plot of the profile of the flow vorticity contour for the flow aft from the leading edge of the wing plate, where α is 65;
FIG. 9h is a plot of the profile of the flow vorticity for the flow aft from the leading edge of the wing plate, where α is 70;
FIG. 10 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. 11 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. 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 is 10;
FIG. 13 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. 14 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. 15 is a schematic flow diagram of the airflow as it flows over the plurality of wing plates of the present application; the D/L value is proper, and the vortexes generated by the two adjacent wing plates do not meet.
The reference numbers illustrate:
the implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, 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 movement situation, etc. in a specific posture (as shown in the drawing), 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 implicitly 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, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
The invention 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 sets 12', the wind guiding plate 11 has a wind guiding surface 11a, and a first edge 111 and a second edge 112 located on two opposite sides of the wind guiding surface 11a, and both the first edge 111 and the second edge 112 extend along a length direction of the wind guiding plate 11. A plurality of wing groups 12 'are arranged at intervals along the length direction of the air guiding plate 11, each wing group 12' includes a plurality of wing plates 12 laterally stacked on the air guiding surface 11a, a leading edge 121 of each wing plate 12 is disposed toward the first edge 111, and a trailing edge 122 of each wing plate 12 is disposed toward the second edge 112.
The number of wing plates 12 in the wing set 12' may be 2-5, and 2 will be exemplified here. 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 leading edge, a first trailing edge, a first ventral surface, a first dorsal surface and two first side surfaces, the first side surfaces connect the first ventral surface and the first dorsal surface, one of the first side surfaces connects the wind guiding surface 11a, and the first leading edge is located between the first edge 111 and the first trailing edge; the second wing panel has a second leading edge, a second trailing edge, a second ventral surface, a second dorsal surface and two second lateral surfaces, the second lateral surface connecting the second ventral surface and the second dorsal surface, the second leading edge being located between the first edge and the second trailing edge 112; the second wing panel is mounted to the other first side of the first wing panel by one of the second sides. The leading edges of two wings stacked together may extend along the same 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 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 is a concave curved surface, and the leeward surface 11b is a convex curved surface. The air guide surface 11a and the leeward surface 11b may be both flat surfaces.
Referring to fig. 4-7, wing panel 12 is configured, as the name implies, like a wing of an aircraft. The leading edge 121 of the wing panel 12 refers to the front edge of the wing panel 12 facing the wind, and the trailing edge 122 refers to the trailing edge of the wing panel 12 facing the wind, that is, when the wing panel 12 faces the wind, the airflow flows from the leading edge 121 to the trailing edge 122. For this airfoil section, the arc length of the back face of wing panel 12 (the arc length extending from leading edge 121 along back face 12b to trailing edge 122) is greater than the straight or arc length of ventral face 12a of wing panel 12. For the wing panel 12, the wing panel 12 itself also has two side surfaces 12c between the ventral surface 12a and the dorsal surface 12b, with the span L referring to the spacing between the opposite side surfaces of the wing panel 12 (for a uniform spacing between the two side surfaces 12 c). The chord length C is indicative of the straight distance between the leading edge 121 and the trailing edge 122. Distance L between the leading edge 121 and the maximum thickness of the wing panel 121Less than the distance L between the trailing edge 122 and the maximum thickness of the wing panel 122. The back surface 12b may be a curved surface, and the ventral surface 12a may be a flat surface or a curved surface.
In the case of an air conditioner, the wind speed at the air outlet is approximately 0.5m/s to 4m/s, and in the case of 4m/s, after the wind is guided by a common plate-shaped air guide plate, the wind speed can be reduced to approximately 0 after a distance of about 5 m. After the air guide plate assembly is used, the wind speed can be reduced to 0 approximately after the distance of about 2.5m, the blown air flow and indoor air can fully exchange heat in the range from the air outlet to the air flow blowing out of 2m, and almost no wind sensation exists after the air outlet is opened for 2 m.
Referring to fig. 7, when the airflow blows along the width direction of the wind deflector 11, a part of the airflow winds from the ventral surface 12a to the dorsal surface 12b, and at the same time, the airflow flows from the leading edge 121 to the trailing edge 122, so that a spiral vortex wake is formed in the part of the airflow relative to the wing. That is, the air flow is straight when passing through the air deflector 11, and can form a plurality of vortex-shaped wake flows after being guided by the plurality of wing plates 12, thereby enhancing the mass and heat transfer effect and improving the heat convection capability; the stroke of the airflow is reduced on the premise of not reducing the heat exchange quantity; the effect of gentle wind feeling can be realized in a slightly far range by strong convection and strong heat exchange in a range close to the air outlet.
While the stacked airfoils 12 provide more swirl flow, the manner in which the airfoils 12 are stacked is also taught. For example, if the two airfoils 12 are stacked in opposite orientations (with the ventral surfaces facing opposite directions), the air in the bottom layer interferes with each other, thereby reducing the swirling effect. In view of this, in the present embodiment, the wing plate 12 has 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 length direction of the air deflector 11.
In one embodiment, in the same wing group 12', the chord length of the wing panel 12 is gradually reduced in the stacking direction, the angle of attack of the wing panel 12 with respect to the width direction of the air deflector 11 is α, and the angle of attack α is gradually reduced in the stacking direction of the wing panel 12. here, mainly considering that the bottom wing panel 12 is used for forming a large vortex volume, while the airflow resistance around the bottom wing panel 12 is relatively large while the large vortex volume is formed, the chord length of the wing panel 12 is gradually reduced in the stacking direction, and the angle of attack α is also gradually reduced, so that the airflow above the lowest wing panel 12 can be fully utilized, and the function of assisting the bottom wing panel 12 to send out vortex airflow is also realized.
In addition, since the plurality of laminated wing plates 12 are offset in the above manner, the wing plates 12 located on the non-bottom layer can generate two vortices, thereby obtaining a good vortex flow.
On the basis of the above embodiment, further, the air deflector 11 has two opposite ends located in the length direction thereof, the plurality of wing groups 12' include a first wing group and a second wing group, ventral surfaces 12a of wing plates 12 in the first wing group are all arranged toward one end of the air deflector 11, ventral surfaces 12a of wing plates 12 in the second wing group are all arranged toward the other end of the air deflector 11, and the wing plates 12 in the first wing group and the wing plates 12 in the second wing group are alternately arranged in the length direction of the air deflector 11. In this case, in the two wing groups 12' arranged alternately (with the ventral surfaces 12a facing each other), on the one hand the flow velocity of the air flow passing between the two wing groups 12 can be increased locally, so that the swirl effect is increased.
In two adjacent wing sets 12' with the opposite ventral surfaces 12a, the distance between the two leading edges 121 of the two wing plates 12 in the same layer is greater than the distance between the two trailing edges. However, the angle between the two wing plates 12 opposite to the ventral surface 12a should not be too large or too small. The included angle is too large, so that the vortex amount of vortex is influenced; the included angle is too small, which is not beneficial to the increase of vortex. In the present embodiment, the included angle between two wing plates 12 of two adjacent wing plates 12 opposite to each other with the ventral surface 12a is not less than 10 ° and not more than 165 °. Preferably, the included angle is 45-75 degrees. The angle is the angle formed by the chord planes of the wing plates 12.
Regarding the problem of the attack angle of the wing plate 12 itself, the following will be described as a simulation experiment of the wing plate 12 at various angles, in which the double-sided vortex is simulated in the simulation experiment in consideration of difficulty in measuring the single-sided vortex amount.
Referring to fig. 8a to 9h, it can be seen that the vortex strength is weak when α is 15 °, the vortex condition changes significantly when α is 70 °, the wing tip vortex degree is weak, the wing tip vortex condition is relatively ideal when α is 15 ° to 70 °, and the value range of the adaptive attack angle α can be determined to be 15 ° to 70 ° according to numerical simulation
Referring to fig. 8a to 8h, the swirl strength is stronger in the range of α ° to α ° to 55 °, and the difference is that the influence range of the swirl wake is smaller when α ° to 15 ° and α ° to 25 °, which is not favorable for driving the rear air to rotate, the swirl condition is significantly changed when α ° to 70 °, the wing tip swirl degree is weak, and the wing tip swirl condition is ideal when α ° to α ° to 55 °.
The effect of α on vortex wake is not sufficiently judged by streamline distribution alone-vorticity is the physical quantity reflecting the strength of vortex, and the contour distribution of vorticity around the wing is shown in FIGS. 9a to 9 h.
When the angle of attack α is 15 ° and α is 25 °, the length of the vortex core (solid portions on both sides of the wing plate in fig. 9a to 9 h) of the vortex wake is the largest, but according to the streamline distribution in fig. 8a to 8h, since the angle of attack α is small, the wake influence range is relatively small, and therefore the angle is suitable for the use situation where the air supply is far away and the heat exchange efficiency needs to be enhanced, α ° to α ° range is 55 °, the vortex distribution situation is close, and the larger angle of attack α is, the capability of scattering the incoming flow is stronger, so when α is 55 °, the effect of swirling the air flow into the wake flow is best, α ° to α ° angle is suitable for the air supply with short distance and the design requirement of soft feeling is satisfied, when α is too large, the rising wing plate 12 blocks the air duct, the air flow influence on the inlet flow, and when the angle of attack 364 ° is 60 °, the vortex distribution is not small, and therefore the vortex distribution is no longer generated when 3670 ° is analyzed.
And obtaining the streamline and speed distribution through numerical simulation calculation. The wind guiding speed of the wing plate 12 and the outlet speed of the common wind guiding are both 4 m/s. The wake of the wing plate 12 forms a significant vortex, the local air flow velocity at the front of the vortex is high (maximum 5.1m/s), the region is a strong mass and heat transfer region, the air flow velocity is rapidly reduced at the rear of the region, and a softer air velocity range can be quickly reached at a slightly far range.
According to the technical scheme, the wing plate 12 is arranged on the air deflector 11, when airflow flows to the rear edge 122 of the wing plate 12 along the front edge 121 of the wing plate 12, a vortex is formed on the rear edge 122 of the wing plate 12, the radius of the formed 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 airflow is softened lightly, and the effect of no wind feeling or slight wind feeling is realized.
In the above embodiment, referring to fig. 1, fig. 2 and fig. 3, 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. 10, 11, 12 and 13, in order to generate more swirl when the airflow blows through the air deflector 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. 10, C/L is 2, C/L is 4 in fig. 11, C/L is 10 in fig. 12, and C/L is 3, 2, 1.5 in fig. 13, it can be seen from these three figures that when C/L is 4, the two vortices at the trailing edge of the wing plate almost contact together, so C/L continues to rise, and the two vortices will interfere with each other, thereby affecting mass transfer and subsequent heat exchange. In the embodiment, C/L is more than or equal to 1.5 and less than or equal to 4.
When the air flow blows over two adjacent wing plates 12, the tips of the two adjacent wing plates 12 (the end of the trailing edge 122) form vortices, and as the vortices flow in a direction away from the wing plates 12, the radius of the vortices increases,
in the present embodiment, referring to fig. 14 and 15, if the distance between the two wings is too close, the vortices generated by two adjacent wing tips (two tips of the trailing edge 122 of the wing plate 12) are easy to interfere with each other. If the distance is too far away, more airflow does not flow through the wing tip, and the overall vortex effect is reduced. The best effect is that the vortices generated by two adjacent wingtips are just close at a distance and do not want to intersect.
Therefore, the distance between two adjacent wing plates 12 is not small. In addition, if the distance between the two wing plates 12 is too large, the blown vortex air flow is relatively loose, which is not beneficial to mass transfer and heat exchange. The distance between two adjacent wing plates 12 is D, and D is more than or equal to 1.3L and less than or equal to 2L.
For the wing plate 12, the size should not be too large, nor too small, and if too large, the wind resistance would be larger, which would affect the air output; if too small, it may result in less swirl being formed at the trailing edge 122 of the wing plate 12. Considering the size of the air outlet of the air conditioner (the width of the air deflector is 60-120mm generally), considering the movement (opening and closing) of the air deflector, in order to prevent interference, the maximum chord length C of the wing plate 12 needs to be controlled within 80 mm. The chord length C of the wing 12 is small, which is not beneficial to the formation of the tip vortex of the wing with a large scale, so the limit minimum value is 20 mm. As the vortex is mainly generated at the wing tip, the overlong wingspan is not beneficial to the enhancement of the vortex, and the two wing tip vortexes which are too short interfere with each other and are not beneficial to the generation of the vortex.
In the present embodiment, the wing panel 12 has a span L in the range of 10mm to 50mm, preferably in the range of 25mm to 40 mm.
For wing plates 12 with a span ranging from 25mm to 40mm, 1.5 ≦ C/L ≦ 4 is satisfied. The chord length of the wing plate 12 is not too long, so based on the ratio, the chord length C of the wing plate 12 can be further controlled to be between 40mm and 60 mm.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (13)
1. An air deflection assembly, comprising:
the air guide plate is provided with an air guide surface, a first edge and a second edge, wherein the first edge and the second edge are positioned on two opposite side edges of the air guide surface, and the first edge and the second edge both extend along the length direction of the air guide plate;
the wing sets are arranged at intervals along the length direction of the air guide plate, each wing set comprises a plurality of wing plates which are laterally stacked on the air guide surface, the front edge of each wing plate faces the first edge, and the rear edge of each wing plate faces the second edge.
2. The air deflection assembly of claim 1, wherein the number of stacked airfoils per wing set is from 2 to 5.
3. The air deflection assembly of claim 1, wherein the wing panel has a back surface and a ventral surface, the ventral surface of each wing panel being disposed toward the same end of the air deflection assembly in the same set of wings.
4. The air deflection assembly of claim 3, wherein the leading edges of a plurality of said airfoils in a common set of said airfoils extend along a common line.
5. The air deflection assembly of claim 3, wherein the chord length of the airfoils in the same airfoil group decreases in the stacking direction.
6. The air deflection assembly of claim 5, wherein the wing panel has an angle of attack of α with respect to the width of the air deflection panel in the same set of wings, and wherein the angle of attack of α decreases in the stacking direction of the wing panels.
7. The air deflection assembly of claim 6, wherein the α is not less than 15 ° and not more than 70 °.
8. The air deflection assembly of claim 6, wherein the difference in the angles of attack of adjacent strakes is between 5 ° and 30 °.
9. An air deflection assembly according to any one of claims 3 to 8, wherein the arc length of the rear face of each wing plate corresponding to the aerofoil section of the wing plate is H1The ventral surface of the wing plate has an arc length or a straight length H corresponding to the airfoil section of the wing plate2，H1Greater than H2。
10. The air deflection assembly of claim 9, wherein the leading edge is spaced less from the maximum thickness of the wing panel than the trailing edge in the same wing panel.
11. The air deflection assembly of claim 10, wherein the air deflection plate has opposite ends along the length thereof, and wherein the plurality of wing sets includes a first wing set and a second wing set, wherein the ventral surfaces of the wing plates of the first wing set are both disposed toward one end of the air deflection plate, the ventral surfaces of the wing plates of the second wing set are both disposed toward the other end of the air deflection plate, and the wing plates of the first wing set and the wing plates of the second wing set are alternately disposed along the length of the air deflection plate.
12. The air deflection assembly of claim 11, wherein the leading edges of two airfoils of the same layer are spaced farther apart than the trailing edges of two adjacent airfoil groups of the opposite ventral surface.
13. An air conditioner having an outlet, wherein the air deflection assembly of any one of claims 1 to 12 is mounted at the outlet.
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)
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| CN111076396B (en) | 2023-09-12 |
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