阅读说明：本技术 百叶组件、导风组件和空调器 (Louver component, air guide component and air conditioner ) 是由 郜哲明 于 2019-11-29 设计创作，主要内容包括：本发明公开一种百叶组件、导风组件和空调器,百叶组件包括：叶片和机翼板,所述机翼板通过连接件安装于所述叶片的至少一个表面,所述机翼板具有前缘、后缘、腹面和背面,所述腹面和所述背面均连接所述前缘和所述后缘,所述腹面朝向所述叶片的表面设置,所述腹面与所述叶片的表面间隔设置。本发明的技术方案通过在叶片上设置机翼板,气流沿着机翼板的前缘流向机翼板的后缘时,在机翼板后缘形成涡旋,形成的涡旋在后续运行过程中,涡旋半径逐渐扩大,涡旋速度逐渐降低,从而可以实现迅速传热,将气流轻柔化,实现无风感或者微风感效果。(The invention discloses a shutter assembly, an air guide assembly and an air conditioner, wherein the shutter assembly comprises: blade and wing board, the wing board pass through the connecting piece install in at least one surface of blade, the wing board has leading edge, trailing edge, ventral surface and back, the ventral surface with the back is all connected the leading edge with the trailing edge, the ventral surface orientation the surface setting of blade, the ventral surface with the surface interval setting of blade. According to the technical scheme, the wing plates are arranged on the blades, when airflow flows to the rear edge of the wing plates along the front edges of the wing plates, vortexes are formed at the rear edges of the wing plates, the radius of the vortexes is gradually enlarged in the subsequent operation process of the formed vortexes, the vortex speed is gradually reduced, and therefore rapid heat transfer can be achieved, the airflow is softened lightly, and the effect of no wind sensation or slight wind sensation is achieved.)

1. A shutter assembly, comprising:

a blade;

the wing board, the wing board pass through the connecting piece install in at least one surface of blade, the wing board has leading edge, trailing edge, ventral surface and back, the ventral surface with the back is all connected the leading edge with the trailing edge, the ventral surface orientation the surface setting of blade, the ventral surface with the surface interval setting of blade.

2. The shutter assembly of claim 1, wherein the back surface has an arc length H corresponding to an airfoil section of the wing plate₁The arc length or the straight line length of the ventral surface corresponding to the airfoil section of the wing plate is H₂，H₁Greater than H₂。

3. The shutter assembly of claim 2, wherein the distance from the leading edge to the maximum thickness of the wing plate is less than the distance from the trailing edge to the maximum thickness of the wing plate.

4. The shutter assembly of claim 3, wherein a spacing between the leading edge and a surface of the vane is less than a spacing between the trailing edge and a surface of the vane.

5. The shutter assembly of claim 3, wherein the angle of attack of the slats relative to the surface of the blade is not less than 15 ° and not more than 70 °.

6. The shutter assembly of claim 5, wherein the angle of attack of the slats with respect to the blades is not less than 25 ° and not more than 55 °.

7. The shutter assembly of claim 6, wherein the strake has a chord length C and a span L, and wherein C/L is greater than 1.

8. The shutter assembly of claim 7, wherein C/L has a value of not less than 1.5 and not greater than 4.

9. A shutter assembly as claimed in any one of claims 1 to 8, wherein the vanes are flexible members.

10. A shutter assembly according to any one of claims 1 to 8, wherein the vanes have opposite surfaces, each of said surfaces having the wing plate mounted thereon.

11. An air guide assembly comprising a connecting rod, and further comprising the louver assembly as claimed in any one of claims 1 to 10, wherein the louver has a first connecting pin, and the first connecting pin is connected to the connecting rod.

12. The air guide assembly as claimed in claim 11, wherein the connecting leg is rotatably connected to the connecting rod.

13. An air conditioner with an air supply duct, characterized by further comprising the air guide assembly as claimed in claim 11 or 12, wherein the connecting rod is installed in the air duct, and the louver further has a second connecting pin connected with the side wall of the air duct.

14. The air conditioner according to claim 13, wherein said second connecting pin is rotatably connected to said air duct side wall.

Technical Field

The invention relates to the technical field of air conditioners, in particular to a louver 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.

In order to solve the above problem, the utility model provides a louver subassembly, include:

a blade;

the wing board, the wing board pass through the connecting piece install in at least one surface of blade, the wing board has leading edge, trailing edge, ventral surface and back, the ventral surface with the back is all connected the leading edge with the trailing edge, the ventral surface orientation the surface setting of blade, the ventral surface with the surface interval setting of blade.

In one embodiment, the arc length of the back surface corresponding to the airfoil section of the wing plate is H₁The arc length or the straight line length of the ventral surface corresponding to the airfoil section of the wing plate is H₂，H₁Greater than H₂。

In an embodiment, 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 spacing between the leading edge and the surface of the blade is smaller than the spacing between the trailing edge and the surface of the blade.

In an embodiment, the angle of attack of the wing plate with respect to the surface of the blade is not less than 15 ° and not more than 70 °.

In an embodiment, the angle of attack of the wing plate with respect to the blade is not less than 25 ° and not more than 55 °.

In one embodiment, the chord length of the wing plate is C, the span of the wing plate is L, and the value of C/L is more than 1.

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

In one embodiment, the blade is a flexible member.

In one embodiment, the blade has two opposing surfaces, each of which has the wing plate mounted thereon.

The invention also discloses an air guide assembly, which comprises a connecting rod and a shutter assembly, wherein the shutter assembly comprises a blade and a wing plate, the wing plate is arranged on at least one surface of the blade through a connecting piece, the wing plate is provided with a front edge, a rear edge, an abdominal surface and a back surface, the abdominal surface and the back surface are both connected with the front edge and the rear edge, the abdominal surface faces the surface of the blade, and the abdominal surface and the surface of the blade are arranged at intervals; the shutter is provided with a first connecting pin, and the first connecting pin is connected with the connecting rod.

In one embodiment, the connecting foot is rotatably connected with the connecting rod.

The invention also discloses an air conditioner which is provided with an air supply duct and also comprises an air guide assembly, wherein the air guide assembly comprises a connecting rod and a shutter assembly, the shutter assembly comprises a blade and a wing plate, the wing plate is arranged on at least one surface of the blade through a connecting piece, the wing plate is provided with a front edge, a rear edge, a ventral surface and a back surface, the ventral surface and the back surface are both connected with the front edge and the rear edge, the ventral surface faces the surface of the blade, and the ventral surface and the surface of the blade are arranged at intervals; the shutter is provided with a first connecting pin which is connected with the connecting rod; the connecting rod is installed in the air duct, the louver is further provided with a second connecting foot, and the second connecting foot is connected with the side wall of the air duct.

In one embodiment, the second connecting pin is rotatably connected with the side wall of the air duct.

According to the technical scheme, the wing plates are arranged on the blades, when airflow flows to the rear edge of the wing plates along the front edges of the wing plates, vortexes are formed at the rear edges of the wing plates, the radius of the vortexes is gradually enlarged in the subsequent operation process of the formed vortexes, the vortex speed is gradually reduced, and therefore rapid heat transfer can be achieved, the airflow is softened lightly, and the effect of no wind sensation or slight wind sensation is achieved.

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

fig. 2 is a schematic structural view of the wind guide assembly shown in fig. 1 from another perspective;

fig. 3 is a schematic structural view of the wind guide assembly shown in fig. 1 from another perspective;

FIG. 4 is a rear view of FIG. 1;

FIG. 5 is a perspective view of the wing plate of FIG. 1;

FIG. 6 is a comparison of the back arc length and ventral arc length of the wing plate of FIG. 5;

FIG. 7 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. 8 is a schematic view of the flow field of the airflow from the leading edge to the trailing edge of the wing panel;

fig. 9a 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. 9b is a schematic view of the airflow field with the airflow flowing backwards from the leading edge of the wing plate, wherein α is 25 °;

fig. 9c 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. 9d 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. 9e 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. 9f 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. 9g 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. 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. 10a 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. 10b 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. 10c is a graph of the profile of the flow vorticity contour for a flow flowing aft from the leading edge of the wing plate, wherein α is 35;

FIG. 10d 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. 10e 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. 10f 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. 10g 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 65;

FIG. 10h 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. 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 ═ 2;

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 5;

FIG. 13 is a schematic view of the airflow field with the airflow flowing aft from the leading edge of the wing plate; wherein C/L is 10;

FIG. 14 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. 15 is a view of an airflow field when the airflow passes through a conventional air deflector of the prior art;

FIG. 16 is a flow field diagram of airflow over a plurality of airfoils of the present application;

FIG. 17 is a schematic flow diagram of the air stream as it flows over the plurality of airfoils of the present application; wherein, because the D/L value is smaller, the vortex directions generated by two adjacent wing plates are converged;

FIG. 18 is a schematic flow diagram of the air stream as it flows over the plurality of airfoils 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:

reference numerals	Name (R)	Reference numerals	Name (R)
				10	Blade assembly	11	Blade
12	Wing plate	13	Connecting piece
				11a	Surface of	121	Leading edge
122	Trailing edge	12a	Ventral surface
				12b	Back side of the panel	141	First connecting pin
142	Second connecting pin	21	Connecting rod
				20	Air guide assembly

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 a blade assembly and an air conditioner comprising the same. Regarding the air conditioner, the following description will be made with respect to a split type air conditioner (floor type air conditioner indoor unit) as a specific embodiment.

Referring to fig. 1 to 5, the louver assembly 10 includes blades 11 and wing plates 12; the wing plate 12 is attached to at least one surface 11a of the blade 11 by a connecting member 13, the wing plate 12 has a front edge 121, a rear edge 122, a ventral surface 12a and a rear surface 12b, the ventral surface 12a and the rear surface 12b both connect the front edge 121 and the rear edge 122, the ventral surface 12a is disposed toward the surface 11a of the blade 11, and the ventral surface 12a is disposed at a distance from the surface 11a of the blade 11.

The blade 11 may be of a rigid sheet-like structure or of a flexible sheet-like structure. The blade has two surfaces 11a, and a wing plate 12 may be provided on one surface 11a, or a wing plate 12 may be provided on both surfaces 11 a.

Referring to fig. 6-9, 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 of wing panel 12 (extending from leading edge 121 along back 12b toThe arc length of the trailing edge 122) is greater than the straight or arc length of the ventral surface 12a of the wing plate 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.

For the installation of the wing plate 12 and the blade 11, the wing plate 12 itself is spaced from the surface 11a to facilitate the passage of the air flow, and the wing plate 12 and the blade 11 are connected by a connecting member 13, wherein the connecting member 13 may be a columnar structure, a regular or irregular protrusion disposed on the surface 11a, or a regular or irregular protrusion disposed on the surface of the wing plate 12. In another aspect, the connecting member 13 may be connected to the surface 11a at one end and to the side, back, or ventral surface 12b, 12a of the wing plate 12 at the other end. On the other hand, the connecting element 13 may also be a sheet-like structure, for example, the sheet-like structure extends along the airflow direction, which may play a role in guiding the airflow, on the other hand, may reduce the airflow resistance, and on the other hand, may also play a role in dividing the airflow passing through the surface 11a, and thus may slow down the formation of the vortex.

In the case of an air conditioner, the wind speed at the outlet is approximately 0.5m/s to 4m/s, and in the case of 4m/s, the wind speed can be reduced to approximately 0 after a distance of about 5m after the wind is guided by the normal plate-shaped blades. And behind this application blade subassembly, behind the distance about 2m, the wind speed can reduce to 0 roughly, blows off the within range of 2m at the air outlet to the air current, and the air current that blows off and indoor air are abundant to be heat exchanged, and outside 2m is opened, and nearly no wind feels.

Referring to fig. 9, when the airflow passes along the width direction of the blade 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. Namely, the air flow is originally straight when flowing through the blades 11, and can form a plurality of vortex-shaped wake flows after being guided by the multi-machine wing plate 12, so that the mass and heat transfer effects are enhanced, and the heat convection capacity is improved; the stroke of the airflow is reduced on the premise of not reducing the heat exchange quantity; the effect of gentle wind feeling can be realized in a slightly far range by strong convection and strong heat exchange in a range close to the air outlet.

In order to verify the eddy current generation condition of the wing plate under each attack angle, the attack angle in the range of 5-80 degrees is tested through simulation experiment design.

Referring to fig. 9a to 10h, it can be seen that the vortex strength is still weak when α is 15 °, the vortex condition is significantly changed when α is 70 °, the wing tip vortex degree is very 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. 9a to 9h, 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 profile of the isosurface distribution of vorticity around the wing is shown in fig. 10a to 10 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. 10a to 10 h) of the vortex wake is the largest, but according to the streamline distribution in fig. 9a to 9h, since the angle of attack α is small, the wake influence range is relatively small, and therefore the angle is suitable for a use situation where the distance is far away and the heat exchange efficiency needs to be enhanced, α ° to α ° range, the vorticity distribution is close, and the angle of attack α is large, the capability of scattering the incoming flow is strong, so when α is 55 °, the effect of converting the air flow into the vortex wake is best, α ° to α ° angle is suitable for short distance air supply and the design requirement of the feeling of soft is strong, when α is too large, the rising wing plate 12 blocks the air duct, the incoming flow affects the intake flow, and when 364 ° is 60 °, the vortex wake distribution is reduced, and therefore the comprehensive vortex distribution 3670 ° is no longer generated.

The streamline and velocity profiles obtained by numerical simulation calculations are shown in fig. 15 and 16. The wind guiding speed of the wing plate 12 and the outlet speed of the common wind guiding are both 4 m/s. It can be seen that the wake of the wing plate 12 forms a significant vortex, the local air velocity in front of the vortex is high (maximum 5.1m/s), this region is a strong mass and heat transfer region, and the air velocity rapidly decreases behind this region, reaching a softer air velocity range shortly beyond this region.

According to the technical scheme, the wing plate 12 is arranged on the blade 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.

When guiding wind, the airflow flowing from the leading edge 121 to the trailing edge 122 along the back surface 12b and the ventral surface 12a, mainly the airflow at the trailing edge 122 and near the two sides of the wing plate 12 will form vortex, so that, relatively speaking, if the span of the wing plate 12 is longer, the distance between two adjacent vortices is larger. With continued reference to fig. 11, 12, 13 and 14, in order to generate more swirl when the airflow is blown through the blade 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. 11, C/L is 2, C/L is 4 in fig. 12, C/L is 10 in fig. 13, and C/L is 3, 2, 1.5 in fig. 14, 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. 17 and 18, 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.

In the above embodiment, both the columnar connector 13 and the sheet-like connector 13 are described, and in the present embodiment, the connector 13 will be further described.

For the columnar connecting pieces 13 (an embodiment of the columnar connecting pieces 13 is not shown in the figure), after the airflow passes through the plurality of columnar connecting pieces 13, each columnar connecting piece forms a pair of vortex streets and then continuously propagates forwards, and the blown airflow has a karman vortex street effect, so that the airflow can be quickly mixed with indoor air, and the heat exchange mixed flow effect is further improved. Therefore, the columnar connector 13 is arranged at a position close to the leading edge 121, and the span between the vortex street and the vortex can be enlarged in space position to avoid mutual interference of the vortex street and the vortex. In addition, the area between two adjacent scrolls is less affected by the air flow (direct blowing of air) before the radii of the two adjacent scrolls are enlarged and meet, so that if the position where the cylindrical connecting member 13 connects the back surface 12b is located at the perpendicular bisector of the wingspan, the blank area between the two adjacent scrolls can be just compensated.

Referring to fig. 1 and 4, as for the sheet-shaped connecting member 13, since the structure has a certain dividing effect on the airflow, so that the formation of the vortex can be greatly reduced (the vortex is formed in advance, which is not beneficial to the formation of the vortex at the rear edge 122 of the wing plate 12, and the vortex can disturb the vortex), the sheet-shaped connecting member 13 is disposed near the front edge 121, which can rectify the airflow, and the vortex phenomenon of the subsequent airflow can be greatly reduced when the airflow flows through the wing plate 12. If the position of the sheet-like connection 13 is on the midperpendicular of the span, the radius and flow velocity of the vortex formed by the two tail tips of the trailing edge 122 of the wing plate 12 can be kept consistent, and the overall mass and heat transfer is more uniform.

Referring to fig. 1 to 4, the blade 10 may be connected to a connecting rod 21 to form an air guiding assembly 20, the air guiding assembly 20 has a connecting rod 21, the louver 11 has a first connecting pin 111, and the first connecting pin 111 is connected to the connecting rod 21.

The air guide assembly can be installed in a wall-mounted air conditioner indoor unit or a floor air conditioner indoor unit, the air conditioner is provided with an air supply duct, the connecting rod 21 is installed in the air duct, the blades 11 are further provided with second connecting pins 112, the second connecting pins 112 are connected with the side wall (for example, connected with a volute) of the air duct, and the connecting rod 21 is driven to move manually or by a motor, so that the blades 11 can be driven to rotate, and air supply at different angles is realized. For the flexible blades of the louver assembly 10, the second connecting angle 112 may be fixedly connected (not rotated) with the volute, and wind guiding at different angles is realized by means of deformation of the blades themselves. When the louver assembly 10 is a hard blade 11, the second connecting pin 112 is required to be rotatably connected with the side wall of the air duct.

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.