CN110749077B - Air deflector assembly and air conditioner - Google Patents
Air deflector assembly and air conditioner Download PDFInfo
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- CN110749077B CN110749077B CN201911218985.4A CN201911218985A CN110749077B CN 110749077 B CN110749077 B CN 110749077B CN 201911218985 A CN201911218985 A CN 201911218985A CN 110749077 B CN110749077 B CN 110749077B
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- front edge
- wing plate
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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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- 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 an air conditioner wing plate, wherein the air deflector is provided with an air deflector surface; the wing plate is installed in the air guide surface through the connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a rear surface, the ventral surface and the rear surface are both 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 rear surface is located between the ventral surface and the air guide surface. The technical scheme of the application can realize rapid heat transfer of the air conditioner, soften the air flow 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 guide plate is provided with an air guide surface;
the wing plate is installed on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a rear surface, the ventral surface and the rear 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 rear surface is located between the ventral surface and the air guide surface.
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 leading edge is spaced a distance C from the maximum thickness of the wing panel 1 The distance between the trailing edge and the maximum thickness of the wing plate is C 2 ，C 1 Less than C 2 。
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 wing plate has a wing head and a wing tail, the leading edge is located at the wing head, the trailing edge is located at the wing tail, the wing head is arranged in a rounded shape, and the wing tail is arranged in a wedge shape.
In an embodiment, the air guiding surface has 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 guiding plate, and the plane where the first edge and the second edge are located is S 1 The plane of the front edge and the rear edge is S 2 ，S 1 And S is equal to 2 The included angle alpha is not less than 15 DEG and not more than 70 DEG
In one embodiment, α is not less than 35 ° and not greater than 55 °.
In an embodiment, the chord length of the wing panel is C, the wing span of the wing panel is L, and the value of C/L is not less than 1.5 and not more than 4.
In an embodiment, the distance between two adjacent wing plates is D, where D is not less than 1.3L and not more than 2L.
In an embodiment, the connection piece connects the back face and the air guiding face, and a connection point of the connection piece and the back face is closer to the front edge than to the rear edge.
The application also discloses an air conditioner, which is provided with an air outlet, wherein at least one air deflector assembly is arranged at the air outlet, the air deflector assembly comprises an air deflector and an air deflector plate, and the air deflector is provided with an air deflector surface; the wing plate is installed in the air guide surface through the connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a rear surface, the ventral surface and the rear surface are both 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 rear surface is located between the ventral surface and the air guide surface.
In one embodiment, the air conditioner is a wall-mounted air conditioner indoor unit.
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 rear view of the air deflection assembly of FIG. 3;
FIG. 5 is a cross-sectional view of the air deflection assembly of FIG. 4 taken along line A-A;
FIG. 6 is a schematic view of distances from the leading edge and the trailing edge of the wing panel of FIG. 5 to the thickest of the wing panel, respectively;
FIG. 7 is a graph showing the comparison of the camber line length of the rear surface and the camber line length of the ventral surface of the wing plate of FIG. 5;
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 schematic view of a structure in which an air deflection assembly is installed in a floor type air conditioning indoor unit, in which a plurality of air deflection assemblies are installed at an air outlet of the floor type air conditioning indoor unit;
FIG. 17 is a flow field diagram of air flow as it flows through a conventional air deflector of the prior art;
FIG. 18 is a flow field diagram of an airflow through a plurality of engine wings in accordance with the present application;
FIG. 19 is a schematic flow diagram of an airflow through a plurality of engine compartment flaps of the present application; wherein, because the D/L value is smaller, the vortex generated by two adjacent wing plates is intersected;
FIG. 20 is a schematic flow diagram of an airflow through a plurality of engine wings in the present application; the D/L value is proper, and vortex generated by two adjacent wing plates does not meet;
FIG. 21 is a flow field diagram of the airflow flowing 10 chords behind the wing panel of the present application;
FIG. 22 is a view of a sound pressure level distribution of a surface of a wing panel.
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, and the air conditioner can be a split type air conditioner or an integral type air conditioner. Regarding the air conditioner, the following description will be made with reference to a specific embodiment of an indoor unit of a wall-mounted air conditioner.
Referring to fig. 1 to 8, the air deflection assembly 10 includes an air deflection 11 and wing plates 12, the air deflection 11 having an air deflection surface 11a; the wing plate 12 is mounted on the wind 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 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 wind guiding surface 11a, the distance between the front edge 121 and the wind guiding surface 11a is smaller than the distance between the rear edge 122 and the wind guiding surface 11a, and the rear surface 12b is located between the ventral surface 12a and the wind guiding surface 11 a.
The air guide plate 11 has a substantially square plate-like structure, and the air guide plate 11 itself has a first edge 111 and a second edge 112 which extend in the longitudinal direction thereof and are provided so as to be opposed 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 formed) opposed to the air guide surface 11 a. Of course, the air deflector 11 may have a certain curvature, for example, the air guiding surface 11a may have a certain concave curvature, and the leeward surface 11b may also have a certain curvature.
Referring to fig. 7-10, the wing panel 12, as the name implies, is structured and constructed in a manner similar to an aircraft wing.
Referring to fig. 7, a front edge 121 of the wing panel 12 refers to a front edge of the wing panel 12 when facing into the wind, and a rear edge 122 refers to a rear edge of the wing panel 12 when facing into the wind, that is, when the wing panel 12 is facing into the wind, airflow flows from the front edge 121 to the rear 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 the airflow flows along the flow path (corresponding to H 2 ) Is smaller than the flow path of the air flow on the back surface 12b (corresponding to H 1 ) And two areThe flow starts from the leading edge 121 and reaches the trailing edge 122, so that the velocity of the flow at the back face 12b is greater than the velocity of the flow at the ventral face 12a, and so that the pressure of the flow received by the back face 12b is less than the pressure of the flow received by the ventral face 12 a.
The nose of the wing panel 12 (the leading edge 121 is located at the nose) is rounded, and the tail of the wing panel 12 (the trailing edge is located at the tail) is substantially wedge-shaped.
For this wing panel 12, the wing panel 12 itself also has two sides 12c between the ventral 12a and dorsal 12b sides 12c, with a uniform spacing between the sides 12c, with the span L being the length of the leading or trailing edge. Referring to fig. 6, the chord length C refers to the vertical 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 Less than the distance C between the trailing edge 122 and the maximum thickness of the wing panel 12 2 . For the back face 12b, it is a cambered face, and for the ventral face 12a, it may be a flat face or a cambered face.
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 0 approximately after passing through a distance of about 2m (changing along with the different angles of attack alpha), 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.
With continued reference to fig. 9, when the air flow is blown in the width direction of the air deflector 11, a part of the air flow is wound from the ventral surface 12a to the dorsal surface 12b, and at the same time, a part of the air flow forms a spiral wake with respect to the wing plate 12 because the air flow flows 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.
The inclination angle of the wing plate itself cannot be too large or too small. The tilting of the wing panel 12 will be further discussed in this embodiment. Defining the plane of the first edge 111 and the second edge 112 as S 1 The plane of the leading edge 121 and the trailing edge 122 is S 2 ，S 1 And S is equal to 2 The included angle alpha is not less than 15 deg. and not more than 70 deg.. Here, the air guiding surface 11a may be a plane or an arc surface, and when the air guiding surface 11a is a plane, the plane S is 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. 5, the wing plate 12 is mounted on the air guiding surface 11a with an inclination with respect to the plane S 1 A kind of electronic device.
It can be seen that the swirl strength is weak when α=15°, the swirl is significantly changed when α=70°, and the degree of tip swirl 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. 17 and 18 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.
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 5, 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.
In addition, referring to FIG. 22, when C/L is less than or equal to 1.5 and less than or equal to 4, the sound pressure level distribution condition of the surface of the wing is as shown in FIG. 22 at the maximum wind speed (4 m/s), the sound pressure level of the normal wind deflector is about 38dB at the wind speed, and therefore the total sound pressure level of the whole wind deflector assembly can not be obviously improved by using the lifting wing. In FIG. 22, 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. 20 and 21, 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 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. 21 (Q) 1 For one of the vortex flows, Q 2 For another vortex airflow), the airflow streamline is in two cylindrical distributions within 10 times chord length after the trailing edge 122 (behind the wing) of the wing plate 12, and the area with the fastest flow speed and the strongest forced convection heat exchange is in the range, so that the tail streamline and the side tail streamline are required to be 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.
Referring to fig. 1 and 3, the cylindrical connecting member 13 and the sheet-like connecting member 13 are both described in the above embodiment, and the connecting member 13 will be further described in this embodiment.
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 3, 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.
In addition, referring to fig. 3 and 5, there may be various connection points between the connecting member 13 and the back surface 12b, for example, the connecting member 13 may be connected to the center of the back surface 12b, or may be located near the front edge 121, or may be located near the rear edge 122. Considering that when the airflow hits the wing tip of the wing panel 12, since the mass of the wing tip portion is relatively large (compared to the wing tail), the inertia is also large, and the lift force generated on the wing panel 12 when the airflow hits the wing tip changes with the change of the airflow velocity, and the airflow velocity is an unstable factor, in order to make the whole wing panel 12 not susceptible to the airflow attack and shake, in this embodiment, the connection portion between the connection piece 13 and the back surface 12b is closer to the front edge than the rear edge 122.
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 guide plate is provided with an air guide surface;
the wing plate is arranged on the air guide surface through a connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a rear surface, the ventral surface and the rear surface are both 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 rear surface is positioned between the ventral surface and the air guide surface;
the distance between the front edge and the maximum thickness of the wing plate is C 1 The distance between the trailing edge and the maximum thickness of the wing plate is C 2 ，C 1 Less than C 2 ；
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 air guide 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 guide plate, and the plane where the first edge and the second edge are positioned is S 1 The plane of the front edge and the rear edge is S 2 ，S 1 And S is equal to 2 The included angle alpha is not less than 15 deg. and not more than 70 deg..
2. 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.
3. The air deflection assembly of claim 1, wherein the wing panels have a nose and a tail, wherein the leading edge is located at the nose and the trailing edge is located at the tail, wherein the nose is rounded and wherein the tail is wedge-shaped.
4. The air deflection assembly of claim 1, wherein α is not less than 35 ° and not greater than 55 °.
5. 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 not less than 1.5 and not greater than 4.
6. The air deflection assembly of claim 3, wherein the spacing between adjacent ones of the wing plates is D, D being no less than 1.3L and no greater than 2L.
7. The air deflection assembly of claim 3, wherein the connector connects the rear face and the air deflection face, and wherein the connector is connected to the rear face closer to the front edge than to the rear edge.
8. An air conditioner having an air outlet, wherein at least one air deflection assembly according to any one of claims 1 to 7 is mounted at said air outlet.
9. The air conditioner of claim 8, wherein the air conditioner is a wall-mounted air conditioner indoor unit.
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| CN201911218985.4A CN110749077B (en) | 2019-11-29 | 2019-11-29 | Air deflector assembly and air conditioner |
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| CN201911218985.4A CN110749077B (en) | 2019-11-29 | 2019-11-29 | Air deflector assembly and air conditioner |
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| CN110749077B true CN110749077B (en) | 2023-09-12 |
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| CN110749076B (en) * | 2019-11-29 | 2024-03-29 | 广东美的制冷设备有限公司 | Air deflector assembly and air conditioner |
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| CN110749077A (en) | 2020-02-04 |
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