Blade, impeller comprising same and range hood

Abstract

The utility model provides a blade, an impeller including the same and a range hood, the blade is arranged on the impeller, the blade comprises a blade body, the blade body comprises a first end facing the axis of the impeller and a second end deviating from the axis of the impeller, the blade body is provided with a mounting groove, and the first end and the second end face the axis of the impeller. The mounting groove is formed in the extension direction of the blade body, and a groove opening of the mounting groove faces the second end of the blade body; the blade body is provided with a mounting groove, the reinforcing rib is embedded in the mounting groove, the section of the mounting groove is provided with a bent section, the section of the reinforcing rib is provided with a bent edge corresponding to the bent section, and the bent section and the bent edge extend in the extending direction deviating from the blade body. The bending sections are matched with the bending edges, so that the reinforcing ribs are firmly connected with the blade body, the situation that the reinforcing ribs are separated from the blade body to damage the blade is prevented, blade trailing edge vortexes are reduced, and the aerodynamic performance is improved.

Description

Technical Field

[0001] This utility model relates to the field of impeller technology, and in particular to a blade and an impeller containing the blade, and a range hood. Background Technology

[0002] As the performance requirements of range hoods become increasingly stringent, researchers are conducting more in-depth studies on impellers. To design blade profiles, non-metallic materials have been introduced, improving upon straight metal blades to biomimetic airfoil blades. Existing blades, due to the presence of metal and non-metal materials of inconsistent weight, can experience blade damage during high-speed rotation due to centrifugal force, causing the heavier metal material to detach from the non-metallic material. Utility Model Content

[0003] The technical problem to be solved by this utility model is to overcome the defect that the blades are easily damaged when the blades include both metallic and non-metallic materials in the prior art, and to provide a blade and an impeller containing the blade, and a range hood.

[0004] The present invention solves the above-mentioned technical problems through the following technical solution:

[0005] A blade, the blade being disposed on an impeller, the blade comprising:

[0006] The blade body includes a first end facing the axis of the impeller and a second end facing away from the axis of the impeller. The blade body is provided with a mounting groove, which is provided along the extension direction of the blade body, and the opening of the mounting groove faces the second end of the blade body.

[0007] A reinforcing rib is embedded in the mounting groove, the mounting groove has a bent section in its cross-section, and the reinforcing rib has a bent edge in its cross-section corresponding to the bent section. The bent section and the bent edge extend in a direction away from the blade body.

[0008] In this design, reinforcing ribs are incorporated into the blade body to enhance the blade's structural strength and prevent damage during operation. The reinforcing ribs are positioned near the second end of the blade body, close to the airfoil trailing edge, to ensure structural strength at that location. The use of a bent section and a bent edge ensures a secure connection between the reinforcing ribs and the blade body, preventing the ribs from detaching and damaging the blade. Simultaneously, the shape of the airfoil trailing edge is maintained by the reinforcing ribs, reducing trailing edge vortices and improving aerodynamic performance during blade operation.

[0009] Preferably, the thickness of the reinforcing rib is 0.3-0.5 mm, and when the reinforcing rib is embedded in the mounting groove, the thickness of the first end section of the blade body is greater than the thickness of the second end section of the blade body.

[0010] In this scheme, the above settings ensure that the blade airfoil trailing edge is thin enough and the structure is strong enough, reducing the low-speed separation zone near the volute on the impeller outlet side and improving aerodynamic efficiency by nearly 2-3%.

[0011] Preferably, a first connecting part is provided in the mounting groove, and a second connecting part is provided on the reinforcing rib. When the reinforcing rib is embedded in the mounting groove, the first connecting part is connected to the second connecting part.

[0012] In this solution, by additionally setting a first connecting part and a second connecting part, the number of connection points between the blade body and the reinforcing rib is increased in addition to the limiting through the bending section and the bending edge, thereby improving the connection reliability between the blade body and the reinforcing rib.

[0013] Preferably, the first connecting portion consists of several protrusions disposed on the wall of the mounting groove, and the second connecting portion consists of several grooves disposed corresponding to the protrusions and located on the surface of the reinforcing rib facing the mounting groove.

[0014] In this solution, the above-mentioned settings are used to achieve a reliable connection between the reinforcing rib and the blade body.

[0015] Preferably, the groove extends through the reinforcing rib.

[0016] In this solution, the above-mentioned settings are used to further reduce the weight of the reinforcing ribs, thus reducing weight and ensuring the aerodynamic performance of the blades.

[0017] Preferably, along the extension direction of the blade body, the extension dimension of the reinforcing rib is smaller than the extension dimension of the blade body.

[0018] In this scheme, the above settings are used to further reduce the blade weight and prevent the situation where the blade weight is large and the aerodynamic efficiency is poor.

[0019] Preferably, the blade body is made of a non-metallic material, and the reinforcing rib is made of a metallic material.

[0020] In this solution, the above-mentioned settings are used to effectively enhance the structural strength of the blade body through the reinforcing ribs.

[0021] Preferably, the surface of the reinforcing rib facing the mounting groove and the surface of the mounting groove facing the reinforcing rib are roughened, and the blade body and the reinforcing rib are integrally injection molded.

[0022] In this solution, the surfaces of the reinforcing ribs facing the mounting groove and the mounting grooves facing the reinforcing ribs are roughened to create several tiny gaps when they come into contact, compared to a flush surface. These gaps allow injection molding material to penetrate during injection molding, filling the gaps and further increasing the number of connection points between the reinforcing ribs and the blade body, thereby improving the reliability of injection molding.

[0023] An impeller comprising blades as described above.

[0024] In this design, the impeller includes the aforementioned blades, eliminating the need to thicken the airfoil trailing edge of the blades. This reduces the low-speed separation zone of the impeller and improves aerodynamic efficiency by 2-3%. Furthermore, the service life of the impeller blades is correspondingly increased, and the reinforcing ribs are prevented from detaching from the blade body during operation, thus improving the reliability of the impeller.

[0025] A range hood, the range hood comprising the impeller as described above.

[0026] In this solution, the range hood includes the aforementioned impeller, thereby improving the overall aerodynamic efficiency of the range hood by 2-3% and extending its service life.

[0027] The positive and progressive effects of this utility model are as follows: By setting reinforcing ribs in the blade body, this utility model can improve the structural strength of the blade and prevent damage during operation. The reinforcing ribs are set near the second end of the blade body, that is, near the trailing edge of the blade airfoil, to ensure the structural strength at that point. The use of the bending section and the bending edge makes the reinforcing ribs firmly connected to the blade body, preventing the reinforcing ribs from detaching from the blade body and damaging the blade. At the same time, the shape of the trailing edge of the blade is guaranteed by the reinforcing ribs, so as to reduce the trailing edge vortex of the blade during operation and improve aerodynamic performance. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the impeller structure of a preferred embodiment of the present invention.

[0029] Figure 2 This is a schematic diagram of the blade structure of a preferred embodiment of the present invention.

[0030] Figure 3 This is a cross-sectional view of the reinforcing rib in a preferred embodiment of the present invention.

[0031] Figure 4 This is a perspective view of the reinforcing rib of a preferred embodiment of the present invention.

[0032] Figure 5 This diagram shows the positional relationship between the mounting groove and the blade body in a preferred embodiment of the present invention.

[0033] Explanation of reference numerals in the attached figures:

[0034] Leaf 1

[0035] Blade body 11

[0036] First end 111

[0037] Second end 112

[0038] Mounting slot 12

[0039] Bending section 121

[0040] Reinforcing rib 13

[0041] 131 bend edge

[0042] First connecting part 2

[0043] Second connecting part 3 Detailed Implementation

[0044] The present invention will be described more clearly and completely below with reference to the accompanying drawings, using a preferred embodiment.

[0045] This embodiment provides a blade 1, the specific structure of which is as follows: Figure 1 , Figure 2 , Figure 3 and Figure 5 As shown, blade 1 is disposed on the impeller, and blade 1 includes:

[0046] The blade body 11 includes a first end 111 facing the axis of the impeller and a second end 112 away from the axis of the impeller. The blade body 11 is provided with a mounting groove 12, which is provided along the extension direction of the blade body 11, and the opening of the mounting groove 12 faces the second end 112 of the blade body 11.

[0047] The reinforcing rib 13 is embedded in the mounting groove 12. The mounting groove 12 has a bent section 121 in its cross section. The reinforcing rib 13 has a bent edge 131 in its cross section corresponding to the bent section 121. The bent section 121 and the bent edge 131 extend in a direction away from the extension of the blade body 11.

[0048] Specifically, the blade body 11 has an arc-shaped cross-section. The first end 111 extends to the impeller hub, and the second end 112 extends to the impeller disk. A mounting groove 12 is provided in the area of ​​the blade body 11 near the second end 112, with the opening of the mounting groove 12 facing the second end 112. It is understood that the thickness of the second end 112 is less than the thickness of the first end 111, so that the airfoil trailing edge of the blade 1 can maintain its aerodynamic performance and reduce the low-speed separation zone. A reinforcing rib 13 is embedded in the mounting groove 12. The reinforcing rib 13 is connected to the blade body 11 through the mounting groove 12 to form a complete blade 1. The presence of the reinforcing rib 13 at the second end 112 enhances the structural strength of this end, preventing damage to the thinner second end 112 from airflow or centrifugal force during blade 1 operation, thus extending its service life.

[0049] In addition, in this embodiment, the cross-section of the mounting groove 12 is provided with a bent section 121, and the cross-section of the reinforcing rib 13 is provided with a bent edge 131. Taking the cross-section of the blade body 11 as an arc-shaped structure as an example, the bent section 121 is set away from the extension direction of the arc-shaped structure, that is, it forms a certain angle with the extension direction of the arc-shaped structure. This angle can be an acute angle, a right angle, or an obtuse angle. The bent edge 131 is similar. By using the cooperation of the bent section 121 and the bent edge 131, the reinforcing rib 13 is restricted from detaching from the blade body 11 along the direction of the second end 112, so that the reinforcing rib 13 is firmly connected to the blade body 11, preventing the reinforcing rib 13 from detaching from the blade body 11 and damaging the blade 1. At the same time, the airfoil trailing edge shape of the blade 1 is guaranteed by the reinforcing rib, so as to reduce the trailing edge vortex of the blade 1 during blade operation and improve aerodynamic performance.

[0050] In this embodiment, the thickness of the reinforcing rib 13 is 0.3-0.5mm. When the reinforcing rib 13 is embedded in the mounting groove 12, the cross-sectional thickness of the first end 111 of the blade body 11 is greater than the cross-sectional thickness of the second end 112 of the blade body 11.

[0051] Specifically, when the reinforcing rib 13 is embedded in the mounting groove 12, the blade 1 is in a complete shape. At this time, by limiting the thickness of the reinforcing rib 13, the thickness of the second end 112 section is still less than the thickness of the first end 111 section. Compared with increasing the thickness of the second end 112 to ensure its structural strength, setting the reinforcing rib 13 and mounting groove 12 can improve the structural strength of the second end 112 without increasing its thickness. At the same time, since the thickness remains unchanged, the low-speed separation zone near the volute on the impeller outlet side of the blade 1 is reduced accordingly, and the aerodynamic efficiency is improved by nearly 2 to 3%.

[0052] In this embodiment, a first connecting part 2 is provided in the mounting groove 12, and a second connecting part 3 is provided on the reinforcing rib 13. When the reinforcing rib 13 is embedded in the mounting groove 12, the first connecting part 2 and the second connecting part 3 are connected.

[0053] Specifically, in addition to the bending section 121 and the bending edge 131, this embodiment also provides a first connecting part 2 and a second connecting part 3. The first connecting part 2 and the second connecting part 3 are connected to increase the number of connection points when the blade body 11 and the reinforcing rib 13 are connected, in addition to being limited by the bending section 121 and the bending edge 131, thereby improving the connection reliability between the blade body 11 and the reinforcing rib 13. The first connecting part 2 and the second connecting part 3 can be selected from existing connection structures, such as snap-fit ​​structures, plug-in structures, etc., which will not be described in detail here.

[0054] like Figure 4 and Figure 5 As shown, in this embodiment, the first connecting part 2 consists of several protrusions, which are disposed on the groove wall of the mounting groove 12. The second connecting part 3 consists of several grooves, which are disposed corresponding to the protrusions and located on the surface of the reinforcing rib 13 facing the mounting groove 12.

[0055] Specifically, when the reinforcing rib 13 is embedded in the mounting groove 12, the bent edge 131 cooperates with the bent section 121, and several protrusions are provided on the groove wall of the mounting groove 12. Several grooves are provided on the surface of the reinforcing rib 13 facing the mounting groove 12. The protrusions extend into the grooves to restrict the position of the reinforcing rib 13 and prevent it from detaching from the blade body 11, thus achieving a reliable connection between the reinforcing rib 13 and the blade body 11. In addition, the cooperation between the protrusions and grooves also ensures the thickness of the second end 112, preventing the thickness from increasing and affecting the aerodynamic performance of the blade 1. It is understood that the protrusions are cylindrical structures and the grooves are cylindrical slots. In other embodiments, the protrusions and grooves may also be other shapes, which will not be elaborated on here.

[0056] Furthermore, in this embodiment, the groove penetrates the reinforcing rib 13. By setting the groove to penetrate the reinforcing rib 13, the weight of the reinforcing rib 13 itself is further reduced, i.e., weight reduction, to ensure the aerodynamic performance of the blade 1.

[0057] In this embodiment, the extension dimension of the reinforcing rib 13 along the extension direction of the blade body 11 is smaller than the extension dimension of the blade body 11. That is, the extension length of the reinforcing rib 13 is less than the extension length of the blade body 11 itself. The two ends of the blade body 11 are connected to the impeller hub and the impeller disk, respectively. Compared with the method of setting a frame and the frame extending to the hub and the impeller disk, this embodiment uses the reinforcing rib 13 to improve the structural strength of some thinner parts, which is more targeted and has a smaller extension dimension, so as to further reduce the weight of the blade 1 and prevent the situation where the blade 1 is heavy and the aerodynamic efficiency is poor.

[0058] In this embodiment, the blade body 11 is made of a non-metallic material, specifically plastic as used in the prior art, while the reinforcing rib 13 is made of a metallic material, such as aluminum or iron, to effectively enhance the structural strength of the blade body 11. It is understood that since the blade body 11 is the airfoil of the blade 1 section, using a non-metallic material is advantageous because it is easy to process, has lower cost, is lighter, and allows for multiple optimizations.

[0059] In this embodiment, the surface of the reinforcing rib 13 facing the mounting groove 12 and the surface of the mounting groove 12 facing the reinforcing rib 13 are roughened, and the blade body 11 and the reinforcing rib 13 are integrally injection molded.

[0060] Specifically, the roughening treatment can be the existing sanding treatment, or corrosion using a liquid with mild corrosive properties. The purpose is to make the surface of the reinforcing rib 13 facing the mounting groove 12 and the surface of the mounting groove 12 facing the reinforcing rib 13 rougher than a flat surface. In this way, when the two come into contact, several tiny gaps will be formed at the contact part, thereby integrally injection molding the blade body 11 and the reinforcing rib 13. During injection molding, injection molding material can be injected to fill the gaps and further increase the number of connection points between the reinforcing rib 13 and the blade body 11, thereby improving the strength and reliability of injection molding.

[0061] This embodiment also provides an impeller, which includes the blade 1 mentioned above. It eliminates the need to thicken the airfoil trailing edge of the blade 1, thereby reducing the low-speed separation zone of the impeller and improving the aerodynamic efficiency by 2-3%. In addition, the service life of the impeller blades is correspondingly increased, and the reinforcing rib 13 is prevented from detaching from the blade body 11 when the blade 1 is working. The reliability of the impeller is also correspondingly improved.

[0062] In addition, this embodiment also provides a range hood that includes the aforementioned impeller, thereby improving the overall aerodynamic efficiency of the range hood by 2-3% and extending its service life.

[0063] While specific embodiments of this utility model have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of this utility model is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of this utility model, but all such changes and modifications fall within the scope of protection of this utility model.

Claims

1. A blade, said blade being disposed on an impeller, characterized in that, The blade includes: The blade body includes a first end facing the axis of the impeller and a second end facing away from the axis of the impeller. The blade body is provided with a mounting groove, which is provided along the extension direction of the blade body, and the opening of the mounting groove faces the second end of the blade body. A reinforcing rib is embedded in the mounting groove, the mounting groove has a bent section in its cross-section, and the reinforcing rib has a bent edge in its cross-section corresponding to the bent section. The bent section and the bent edge extend in a direction away from the blade body.

2. The blade as described in claim 1, characterized in that, The thickness of the reinforcing rib is 0.3-0.5 mm. When the reinforcing rib is embedded in the mounting groove, the thickness of the first end section of the blade body is greater than the thickness of the second end section of the blade body.

3. The blade as described in claim 1, characterized in that, The mounting groove is provided with a first connecting part, and the reinforcing rib is provided with a second connecting part. When the reinforcing rib is embedded in the mounting groove, the first connecting part is connected to the second connecting part.

4. The blade as described in claim 3, characterized in that, The first connecting part consists of several protrusions disposed on the wall of the mounting groove, and the second connecting part consists of several grooves disposed corresponding to the protrusions and located on the surface of the reinforcing rib facing the mounting groove.

5. The blade as described in claim 4, characterized in that, The groove extends through the reinforcing rib.

6. The blade as described in claim 1, characterized in that, Along the extension direction of the blade body, the extension dimension of the reinforcing rib is smaller than the extension dimension of the blade body.

7. The blade as described in claim 1, characterized in that, The blade body is made of non-metallic material, while the reinforcing rib is made of metallic material.

8. The blade as described in claim 7, characterized in that, The surface of the reinforcing rib facing the mounting groove and the surface of the mounting groove facing the reinforcing rib are roughened, and the blade body and the reinforcing rib are integrally injection molded.

9. An impeller, characterized in that, The impeller comprises blades as described in any one of claims 1-8.

10. A range hood, characterized in that, The range hood includes the impeller as described in claim 9.

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