Axial flow fan and ventilation equipment

Abstract

The utility model relates to an axial flow fan and ventilation equipment. The axial flow fan comprises a hub, a fan blade and a fan blade, the main wing blades are mounted on the hub; the aileron blade is arranged on one side of the suction surface of the main wing blade at an interval with the main wing blade, and the aileron blade is rotatably mounted on the hub around an aileron rotating shaft; and the main driving part is coaxially connected with the hub so as to drive the hub to drive the main wing blades and the auxiliary wing blades to rotate around a main wing rotating shaft. The aileron blade capable of rotating independent of the main wing blade is arranged on one side of the suction surface of the main wing blade of the axial flow fan, and the airflow direction on one side of the suction surface of the main wing blade can be guided through angle adjustment of the aileron blade, so that airflow can flow close to the suction surface of the main wing blade, the airflow separation phenomenon is eliminated, and the air volume is increased; and the vortex noise of the fan can be reduced by improving the fan performance. When the rotating speed of the fan changes, the aileron blades can adapt to different rotating speed changes by rotating at a proper angle, so that the performance of the fan at various rotating speeds is ensured.

Description

Technical Field

[0001] This disclosure relates to the field of axial flow fan technology, and in particular to an axial flow fan and ventilation equipment. Background Technology

[0002] Blades are a crucial component of axial flow fans, used in ventilation equipment, refrigerators, and various other devices requiring heat dissipation. In related technologies, airflow separation easily occurs at the leading edge of the blades in axial flow fans. As the degree of flow separation increases, the separation of airflow from the blades leads to a decrease in air volume, resulting in reduced fan performance and increased vortex noise. Utility Model Content

[0003] To overcome the problems existing in the related technologies, this disclosure provides an axial flow fan and ventilation equipment.

[0004] According to a first aspect of the present disclosure, an axial flow fan is provided, comprising: a hub; a main blade mounted on the hub; an auxiliary blade spaced apart from the main blade on the suction surface side of the main blade and rotatably mounted on the hub around an auxiliary blade rotation axis; and a main drive member coaxially connected to the hub to drive the hub to rotate the main blade and the auxiliary blade around the main blade rotation axis.

[0005] Optionally, the end of the aileron blade is provided with a shaft, which passes through the circumferential wall of the hub along the direction of the aileron rotation axis.

[0006] Optionally, a secondary drive member is provided on the inner side of the circumferential wall of the hub, and the secondary drive member is connected to the shaft to drive the shaft to rotate around the aileron rotation axis.

[0007] Optionally, the secondary drive member is connected to the shaft via a coupling structure, the coupling structure having a disconnection mode and an engagement mode. In the disconnection mode, the shaft is disengaged from the secondary drive member, and in the engagement mode, the shaft is connected to the secondary drive member.

[0008] Optionally, the coupling structure includes a telescopic member and a telescopic drive member. The telescopic member is movably disposed at the drive end of the auxiliary drive member in a direction close to or away from the shaft. The telescopic drive member is used to drive the telescopic member to move. In the disconnected mode, the telescopic member retracts to disengage from the shaft. In the engaged mode, the telescopic member extends to connect with the shaft.

[0009] Optionally, one end of the shaft is provided with a connector, and one end of the telescopic member is provided with a matching member. In the engagement mode, the connector and the matching member are engaged and plugged in.

[0010] Optionally, the telescopic member is provided with a rack, and the driving end of the telescopic drive member is connected to a cam, the protrusion of the cam being provided with mating teeth to engage with the rack.

[0011] Optionally, the main wing blade includes a leading edge and a trailing edge, and the aileron blade is located between the leading edge and the trailing edge of the main wing and is disposed close to the leading edge of the main wing.

[0012] Optionally, the aileron blade is configured to bend and extend from the inner end to the outer end of the main wing blade, and the bending direction is consistent with the bending direction of the leading edge of the main wing.

[0013] Optionally, the aileron blade includes an aileron leading edge and an aileron trailing edge, wherein the angle α between the line connecting the tip of the aileron leading edge near the outer end of the main wing blade and the center point of the aileron blade near the inner end of the main wing blade and the aileron rotation axis is not less than 10° and not greater than 35°.

[0014] Optionally, the main wing blade includes a leading edge and a trailing edge. In the fore-and-aft direction of the main wing blade, the distance between the leading edge of the main wing and the rotation center of the aileron blade is L1, and the chord length of the main wing blade is L2, wherein L1 / L2 is 0.2~0.3.

[0015] Optionally, the chord length of the main wing blade is L2, and the chord length of the aileron blade is L3, wherein L3 / L2 is 0.05~0.15.

[0016] Optionally, the minimum distance between the aileron rotation axis and the main wing blade is L4, and the chord length of the aileron blade is L3, wherein L4 / L3 is 0.8~1.2.

[0017] Optionally, the aileron blade includes an aileron leading edge and an aileron trailing edge, the minimum distance between the aileron leading edge and the main wing blade is L5, the minimum distance between the aileron trailing edge and the main wing blade is L6, and the chord length of the main wing blade is L2, wherein both L5 / L2 and L6 / L2 are not less than 0.03.

[0018] Optionally, the main wing blade includes a leading edge and a trailing edge. In the forward and backward direction of the main wing blade, the distance from the intersection of the pressure surface outflow tangent of the aileron blade and the chord of the main wing blade to the leading edge of the main wing is L7, and the chord length of the main wing blade is L2, wherein L7 / L2 is not greater than 2 / 3.

[0019] According to a second aspect of the present disclosure, a ventilation device is provided, including the axial flow fan provided in the present disclosure.

[0020] The technical solutions provided by the embodiments of this disclosure can include the following beneficial effects: A secondary blade, which can rotate independently of the main blade, is provided on the suction side of the main blade of the axial flow fan. By adjusting the angle of the secondary blade, the airflow direction on the suction side of the main blade can be guided, allowing the airflow to flow close to the suction surface of the main blade, eliminating airflow separation, increasing air volume, thereby improving fan performance, and reducing fan vortex noise. When the fan speed changes, the secondary blade can adapt to different speed changes by rotating at a suitable angle, thus ensuring fan performance at various speeds.

[0021] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0022] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure.

[0023] Figure 1 This is an assembly schematic diagram of an axial flow fan according to an exemplary embodiment;

[0024] Figure 2 This is a partial structural diagram of an axial flow fan according to an exemplary embodiment;

[0025] Figure 3 yes Figure 2 Enlarged view of part B in the image;

[0026] Figure 4 This is a schematic diagram of a main drive unit according to an exemplary embodiment;

[0027] Figure 5 This is a partial structural diagram of an axial flow fan according to an exemplary embodiment;

[0028] Figure 6 yes Figure 5 Enlarged view of section C in the image;

[0029] Figure 7 This is a schematic diagram illustrating a coupling structure in a disconnected mode according to an exemplary embodiment;

[0030] Figure 8 This is a schematic diagram illustrating a coupling structure in an engaged mode according to an exemplary embodiment;

[0031] Figure 9 This is a frontal projection view of an axial flow fan according to an exemplary embodiment;

[0032] Figure 10 It is along Figure 9 A schematic diagram of the cross section of the blade cascade of line A;

[0033] Figure 11 This is a schematic diagram of airflow in an axial flow fan in the prior art;

[0034] Figure 12 This is a schematic diagram of a cross-section of a cascade according to an exemplary embodiment;

[0035] Figure 13 This is a schematic diagram of a cross-section of a cascade according to an exemplary embodiment;

[0036] Figure 14 This is a flowchart illustrating a control method for an axial flow fan according to an exemplary embodiment;

[0037] Figure 15 This is a flowchart illustrating a control method for an axial flow fan according to an exemplary embodiment;

[0038] Figure 16 This is a flowchart illustrating a control method for an axial flow fan according to an exemplary embodiment;

[0039] Figure 17 This is a diagram illustrating the relationship between current and airflow for main airfoil blades of different diameters, according to an exemplary embodiment.

[0040] Explanation of reference numerals in the attached figures

[0041] 10-Hub, 20, 20'-Main wing blade, 21-Main wing leading edge, 22-Main wing trailing edge, 30-Aileron blade, 301-Shaft, 31-Aileron leading edge, 32-Aileron trailing edge, 311-Connector, 40-Main drive component, 401-Mounting slot, 41-Main shaft, 50-Secondary drive component, 501-Secondary drive component wiring harness, 60-Coupling structure, 601-Telescopic drive component wiring harness, 61-Telescopic component, 611-Matching component, 612-Rack, 62-Telescopic drive component, 621-Cam, 6211-Matching gear. Detailed Implementation

[0042] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this disclosure. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this disclosure as detailed in the appended claims.

[0043] It should be noted that all actions involving the acquisition of signals, information, or data in this disclosure are carried out in compliance with the relevant data protection laws and policies of the country where the location is situated, and with authorization from the owner of the relevant device.

[0044] Blades are a crucial component of axial flow fans, used in ventilation equipment, refrigerators, and various other devices requiring heat dissipation. In related technologies, airflow separation easily occurs at the leading edge of the blades in axial flow fans. As the degree of flow separation increases, the separation of airflow from the blades leads to a decrease in airflow volume, resulting in reduced fan performance and increased vortex noise. Furthermore, fan design is typically based on a rated speed, at which the fan exhibits high aerodynamic performance and minimal airflow separation from the blades. However, when the fan speed deviates significantly from the rated speed, the airflow angle changes, leading to severe airflow separation.

[0045] Therefore, embodiments of this disclosure provide an axial flow fan capable of reducing airflow separation at different speeds. (Refer to...) Figure 1 The axial flow fan includes a hub 10, main blades 20, aileron blades 30, and a main drive component 40. Both the main blades 20 and the aileron blades 30 are mounted on the hub 10. The main blades 20 can be fixed to the hub 10 so that they can rotate with the hub 10 around the main blade rotation axis, which is the axis of the hub 10. Figure 2 The axis is indicated by the dashed line. The aileron blade 30 is rotatably mounted on the hub 10 about an aileron rotation axis. The aileron rotation axis can be radial to the hub 10 or parallel to the surface of the main wing blade 20. The aileron rotation axis and the main wing rotation axis are not in the same direction, but they can intersect. (Refer to...) Figure 5 The three dashed lines in the diagram represent the aileron rotation axes of the three aileron blades 30. The aileron blades 30 are spaced apart from the main wing blade 20 on the suction side, so that the airflow direction on the suction side of the main wing blade 20 can be guided by adjusting the angle of the aileron blades 30 on the suction side. The main drive component 40 is coaxially connected to the hub 10, as shown... Figure 4 As shown, the main drive unit 40 is provided with a main shaft 41 for outputting driving power. The main shaft 41 passes through the shaft hole on the hub 10 for assembly connection. The main drive unit 40 can drive the hub 10 to drive the main wing blade 20 and the aileron blade 30 to rotate around the main wing rotation axis.

[0046] Through the above technical solution, an auxiliary blade 30 that can rotate independently of the main blade 20 is set on the suction side of the axial flow fan. By adjusting the angle of the auxiliary blade 30, the airflow direction on the suction side of the main blade 20 can be guided, allowing the airflow to flow close to the suction surface of the main blade 20, eliminating airflow separation, increasing air volume, thereby improving fan performance and reducing vortex noise. When the fan speed changes, the auxiliary blade 30 can adapt to different speed changes by rotating at an appropriate angle, thus ensuring fan performance at various speeds.

[0047] Reference Figure 10 and Figure 11 , Figure 11 In existing technology, the airflow direction when the main blade 20' is operating is such that the airflow is separated when it flows in, and the degree of separation continues to increase as it flows, resulting in a significant decrease in air volume. Figure 10 The axial flow fan in this embodiment has an auxiliary blade 30 on the suction side of the main blade 20. The auxiliary blade 30 guides the airflow direction so that the airflow can flow in close contact with the main blade 20, thereby avoiding airflow attenuation.

[0048] In this embodiment, the axial flow fan may include a secondary drive component 50. The secondary drive component 50 can independently control the rotation of the aileron blades 30 around the aileron rotation axis. In this embodiment, the secondary drive component 50 can rotate synchronously with the aileron blades 30 around the main wing rotation axis. In some embodiments, the secondary drive component 50 can be disposed between the main drive component 40 and the hub 10, so as to utilize the space between the main drive component 40 and the hub 10 to arrange the secondary drive component 50, while the hub 10 protects the secondary drive component 50. The secondary drive component 50 can cooperate with the main drive component 40 to adjust the relative angle of the aileron blades 30 with respect to the main wing blades 20. Since the secondary drive component 50 is disposed on the main drive component 40, the position of the secondary drive component 50 is fixed with the main drive component 40, while the positions of the main wing blades 20 and the aileron blades 30 will change with the driving of the main drive component 40. Therefore, the driving of the aileron blades 30 independently of the main wing blades 20 requires the main drive component 40 to coordinate the position of the secondary drive component 50 before driving through the secondary drive component 50. In one embodiment, both the main drive unit 40 and the auxiliary drive unit 50 can be in the form of motor drive.

[0049] like Figure 4 As shown, a mounting slot 401 can be provided on the main drive component 40. The auxiliary drive component 50 and the telescopic drive component 601, which will be described below, and other related structures can be arranged in the mounting slot 401 to protect these structures and prevent interference.

[0050] In this embodiment, the secondary drive component 50 is installed at a fixed position on the primary drive component 40 to prevent the secondary drive component 50 from moving together with the primary drive component 40 during operation, thus preventing damage to some connecting harnesses or other electrical components of the secondary drive component 50 due to rotation. The arrangement of the secondary drive component 50 in this embodiment allows the aileron blades 30 to be driven around their rotation axis by the secondary drive component 50 in conjunction with the primary drive component 40.

[0051] Reference Figure 5 and Figure 6A shaft 301 can be provided at the end of the aileron blade 30. The shaft 301 can pass through the circumferential wall of the hub 10 along the direction of the aileron rotation axis, that is, the direction of the aileron rotation axis is the axial direction of the shaft 301. The auxiliary drive 50 and the main drive 40 can adjust the rotation angle of the aileron blade 30 in coordination: the main drive 40 can drive the shaft 301 to be coaxial with the auxiliary drive 50, and after coaxiality, the auxiliary drive 50 can drive the shaft 301 to rotate around the aileron rotation axis, thereby driving the aileron blade 30 to rotate, so as to adjust the relative angle between the aileron blade 30 and the main wing blade 20. The auxiliary drive 50 can adjust the rotation angle of the aileron blade 30 on its own: the auxiliary drive 50 is mounted on the hub 10 so as to rotate synchronously with the hub 10 and the aileron blade 30 around the main wing rotation axis.

[0052] Reference Figure 2 and Figure 3 The secondary drive component 50 and the shaft 301 can be connected via a coupling structure 60, which has a disconnected mode and an engaged mode. In the disconnected mode, the shaft 301 is disengaged from the secondary drive component 50, and the two components do not interfere with each other. The rotation of the shaft 301, carrying the aileron blade 30, around the main wing's rotation axis does not affect the secondary drive component 50, and the rotation of the secondary drive component 50 around the aileron's rotation axis does not affect the aileron blade 30. In the engaged mode, the shaft 301 is connected to the secondary drive component 50, establishing a connection. Therefore, the secondary drive component 50 can drive the aileron blade 30 to rotate around the aileron's rotation axis. In this mode, the main drive component 40 stops working to avoid affecting the connection between the secondary drive component 50 and the shaft 301. Understandably, when the angle of the aileron blades 30 needs to be adjusted to adapt to a certain rotational speed of the main drive component 40, the main drive component 40 can be activated first to drive the shaft 301 into a position coaxial with the auxiliary drive component 50. The position can be detected by sensors. Then, the main drive component 40 stops operating, and the auxiliary drive component 50 is connected to the shaft 301 via the coupling structure 60. After the shaft 301 is connected to the auxiliary drive component 50, the auxiliary drive component 50 is operated to adjust the aileron blades 30 around the aileron rotation axis to the required position. After the aileron blades 30 are adjusted, the coupling structure 60 is switched to the disconnect mode, disengaging the shaft 301 from the auxiliary drive component 50. The aileron blades 30 remain in their current position. Then, the main drive component 40 is activated, and the aileron blades 30 and the main blades 20 rotate synchronously around the main blade rotation axis, allowing the fan to enter normal operating mode.

[0053] In one embodiment, reference is made to... Figure 3 , Figure 7 and Figure 8The coupling structure 60 may include a telescopic member 61 and a telescopic drive member 62. The telescopic member 61 is movably disposed at the drive end of the auxiliary drive member 50 in a direction approaching or away from the shaft 301. A raised key may be formed on the telescopic member 61, and a keyway for accommodating the raised key may be formed on the output shaft of the auxiliary drive member 50, allowing the telescopic member 61 to be fitted onto the outer periphery of the output shaft. Figure 7 and Figure 8 In the illustrated direction, the telescopic member 61 can move vertically along the plane of the drawing. The telescopic drive member 62 is used to drive the telescopic member 61 to move; in the disengaged mode, the telescopic member 61 retracts until it is disengaged from the shaft 301. Figure 7 The diagram shows the disconnected mode. In the engaged mode, the telescopic member 61 extends to connect with the shaft 301. Figure 8 What is shown is the engagement mode, compared to Figure 7 , Figure 8 The telescopic member 61 shown in the figure moves upward to move closer to the shaft 301.

[0054] In this embodiment of the present disclosure, one end of the shaft 301 may be provided with a connector 311, and one end of the telescopic member 61 may be provided with a matching member 611, as shown in the reference. Figure 3 As shown, in the engagement mode, the plug 311 and the matching part 611 are engaged and plugged in, so that the shaft 301 and the auxiliary drive part 50 can be linked.

[0055] In some embodiments, the extension and retraction of the telescopic member 61 can be driven by a linear motor. In some embodiments, refer to... Figure 3 , Figure 7 and Figure 8 The telescopic member 61 may be equipped with a rack 612, and the driving end of the telescopic drive member 62 is connected to a cam 621. The protrusion of the cam 621 may be equipped with a mating tooth 6211 to mesh with the rack 612. Figure 7 The disconnect mode shown has been switched to Figure 8 In the engagement mode shown, the telescopic drive 62 can drive the cam 621 to rotate clockwise in the direction shown in the figure, causing the mating teeth 6211 to drive the rack 612 to move upward, and the cam 621 to continue rotating until the mating teeth 6211 disengage from the rack 612, so as to prevent the cam 621 from affecting the rotation of the auxiliary drive 50 driving the telescopic member 61 together with the shaft 301 around the aileron rotation axis extending in the vertical direction along the figure. When it is necessary to... Figure 8 The shown engagement mode is switched to Figure 7In the disconnected mode, the telescopic drive 62 drives the cam 621 to rotate counterclockwise. When the meshing gear 6211 engages with the rack 612, the telescopic drive 61 moves downwards, disengaging from the shaft 301. Since the secondary drive 50 is not operational in the disconnected mode, the meshing gear 6211 and rack 612 do not need to disengage in this mode. The secondary drive 50 may be equipped with a secondary drive harness 501, and the telescopic drive 62 may be equipped with a telescopic drive harness 601. The harnesses are used to supply power to the corresponding drive components and to transmit signals to control the operation of the corresponding drive components. In one embodiment, both the secondary drive 50 and the telescopic drive 62 can be stepper motors.

[0056] Reference Figure 9 The main wing blade 20 includes a leading edge 21 and a trailing edge 22. The aileron blade 30 is located between the leading edge 21 and the trailing edge 22, and is positioned close to the leading edge 21. Airflow flows in from the leading edge 21 and out from the trailing edge 22. Positioning the aileron blade 30 close to the leading edge 21 can guide the airflow in the airflow inflow area, preventing the airflow from being too separated and thus unable to be guided or with poor guidance effect.

[0057] The aileron blade 30 is constructed to curve and extend from the inner end to the outer end of the main wing blade 20, with the curvature direction consistent with that of the leading edge 21 of the main wing. Here, the inner end refers to the end closer to the hub 10, i.e., the shorter blade root, while the outer end is the blade tip. Setting the aileron blade 30 to align with the curvature direction of the leading edge 21 of the main wing ensures that the aileron blade 30 guides the airflow in the same direction as the actual airflow, guaranteeing a smooth airflow.

[0058] Aileron blade 30 includes aileron leading edge 31 and aileron trailing edge 32, see reference Figure 9 The line connecting the tip of the aileron leading edge 31 near the outer end of the main wing blade 20 and the center point of the aileron blade 30 near the inner end of the main wing blade 20 (i.e. Figure 9 The dashed line closer to the left in the middle) and the aileron rotation axis (i.e. Figure 9 The angle α between the aileron blade 30 and the dotted line (closer to the right) should be no less than 10° and no more than 35° to avoid the aileron blade 30 bending too small and not matching the bending of the leading edge 21 of the main wing. At the same time, it should be avoided that the aileron blade 30 bending angle is too large, which would cause the end face near the blade tip to rotate too much during the rotation of the aileron rotation axis, resulting in a large deviation from the actual flow direction and affecting the flow guiding effect.

[0059] Figure 10 , Figure 12 and Figure 13 All along Figure 9 The diagram shows the result after sectioning along section line A. (Refer to...) Figure 12 In the front-to-back direction of the main wing blade 20, that is... Figure 12As shown in the diagram, in the direction from the leading edge 21 of the main wing to the trailing edge 22 of the main wing, the distance between the leading edge 21 of the main wing and the rotation center of the aileron blade 30 is L1, and the chord length of the main wing blade 20 is L2. The ratio of distance L1 to the chord length L2 of the main wing blade 20, L1 / L2, is 0.2 to 0.3, for example, 0.25, to ensure sufficient airflow guidance. If this ratio is too small, guidance will occur in areas where the airflow has not yet separated, resulting in design waste. If this ratio is too large, guidance will occur after the airflow separation is too great, affecting the guidance effect.

[0060] In this embodiment of the disclosure, the chord length of the aileron blade 30 is L3, wherein the ratio of the chord length L3 of the aileron blade 30 to the chord length L2 of the main blade 20, L3 / L2, is 0.05~0.15, for example, 0.1, to ensure sufficient airflow guidance effect, while avoiding excessive airflow drag due to the aileron blade 30 having an excessively large proportion.

[0061] Reference Figure 12 The minimum distance between the aileron rotation axis and the main wing blade 20 is L4. The ratio of distance L4 to the chord length L3 of the aileron blade 30, L4 / L3, is 0.8 to 1.2, for example, 1, to ensure that there is sufficient ventilation clearance between the aileron blade 30 and the main wing blade 20, while ensuring the guiding effect of the aileron blade 30 on the airflow.

[0062] Reference Figure 13 The aileron blade 30 includes an aileron leading edge 31 and an aileron trailing edge 32. Figure 13 The diagram shows aileron blades 30 in two positions. The solid line indicates the initial position, while the dashed line indicates the final position where they can rotate. The minimum distance between the aileron leading edge 31 and the main wing blade 20 is L5, and the minimum distance between the aileron trailing edge 32 and the main wing blade 20 is L6. Both L5 / L2 and L6 / L2 can be no less than 0.03 to ensure sufficient ventilation clearance for the aileron blades 30 at all angles. When the aileron blade 30 is in the final position, the distance between the aileron leading edge 31 and the main wing blade 20 is closest. Therefore, in this embodiment, the ratio of the distance L5 at this position to the chord length L2 of the main wing blade 20 can be set to no less than 0.03. When the aileron blade 30 is in the initial position, the distance between the aileron trailing edge 32 and the main wing blade 20 is closest. Therefore, in this embodiment, the ratio of the distance L6 at this position to the chord length L2 of the main wing blade 20 can be set to no less than 0.03.

[0063] Reference Figure 13 In the forward and backward direction of the main wing blade 20, the intersection of the outflow tangent of the pressure surface of the aileron blade 30 and the chord line of the main wing blade 20 (i.e., Figure 13The distance from the intersection of the two straight dashed lines in the middle to the leading edge 21 of the main wing is L7. The ratio of distance L7 to the chord length L2 of the main wing blade 20, L7 / L2, is not greater than 2 / 3, so as to ensure that the airflow flows along the surface of the main wing blade 20 in at least two-thirds of the area before the main wing blade 20, so as to avoid guiding the airflow too late and resulting in poor guiding effect.

[0064] According to a second aspect of the present disclosure, a control method for an axial flow fan is also provided. This control method is applied to the axial flow fan described above. The method can be applied to the performance optimization mode of the axial flow fan to select the optimal rotation angle of the aileron blades 30.

[0065] Specifically, refer to Figure 14 The control method includes the following steps.

[0066] In s103, the secondary drive unit 50 drives the aileron blade 30 to rotate around the aileron rotation axis from the initial position to the final position. The specific method and operation steps of the secondary drive unit 50 driving the aileron blade 30 are as described above and will not be repeated here. When the user selects the performance optimization mode, the main drive unit 40 can be operated first to bring the aileron blade 30 into a position suitable for adjustment by the secondary drive unit 50. Then, the secondary drive unit 50 drives the aileron blade 30 to rotate back to the initial position.

[0067] In step s104, after the aileron blade 30 rotates by a preset angle, the current rotation angle of the aileron blade 30 is obtained, and the main drive unit 40 is controlled to drive the main wing blade 20 and the aileron blade 30 to rotate around the main wing rotation axis at a preset speed for a predetermined time. The preset angle can be 1° to 3°, for example, 2°, to avoid insufficient optimization accuracy due to an excessively large angle, and to avoid excessive optimization time due to an excessively small angle. The preset angle, preset speed, and predetermined time remain constant throughout the optimization process. For example, after the aileron blade 30 rotates 2° for the first time, the secondary drive unit 50 stops, the main drive unit 40 operates for a predetermined time, and the current rotation angle of the aileron blade 30 is obtained as 2°; after the aileron blade 30 continues to rotate 2° for the second time, the secondary drive unit 50 stops, the main drive unit 40 operates for a predetermined time, and the current rotation angle of the aileron blade 30 is obtained as 4°, and so on, until the aileron blade 30 reaches the termination position.

[0068] In s105, the air volume value generated by the axial flow fan within each predetermined time period is obtained. For example, after the aileron blade 30 rotates 2° for the first time, the auxiliary drive 50 stops and the main drive 40 runs for a predetermined time, and the air volume value generated within that predetermined time period is obtained. After the aileron blade 30 rotates 2° for the second time, the auxiliary drive 50 stops and the main drive 40 runs for a predetermined time, and the air volume value generated within that predetermined time period is obtained again. This process is repeated to obtain the air volume value within the predetermined time period for each operation for subsequent comparison.

[0069] In step s106, the maximum airflow value is determined from multiple sets of airflow values ​​acquired when the aileron blade 30 is at different rotation angles, and the optimal rotation angle corresponding to the aileron blade 30 is determined based on the maximum airflow value. For example, when the aileron blade 30 is at rotation angles of 2°, 4°, and 6°, the airflow value generated by the axial flow fan running for a predetermined time at the corresponding angle is acquired. The maximum airflow value is determined by comparing multiple sets of acquired airflow values, thereby determining the rotation angle of the aileron blade 30 corresponding to the maximum airflow value. This angle is the optimal rotation angle, which can maximize the airflow. After the performance optimization mode is completed, the optimal rotation angle of the aileron blade 30 at the motor speed can be fed back to the user, allowing the user to adjust the aileron blade 30 to the optimal rotation angle based on the acquired results. When the speed of the main drive component 40 changes, the above steps can be repeated to perform the optimization mode again to find the optimal rotation angle of the aileron blade 30 that adapts to the current speed.

[0070] In this embodiment of the disclosure, the method may include: when the angle between the position of the aileron blade 30 after one or more rotations and the termination position is less than a preset angle, the next rotation of the aileron blade 30 is to rotate to the termination position. For example, when the preset angle is 2°, and the angle between the position of the aileron blade 30 after one or more rotations and the termination position is 1°, then the next rotation of the aileron blade 30 is the last rotation, and this rotation can directly rotate to the termination position, and the above-mentioned step of obtaining air volume is performed at the termination position.

[0071] In some embodiments, the guiding effect of the aileron blade 30 is considered to be the worst at its initial position, thus eliminating the need to measure the airflow value at the initial position of the aileron blade 30. However, in this embodiment, to ensure the accuracy of the measurement structure and to seek the optimal mode, [refer to the figure]. Figure 15 and Figure 16Before step s103, the control method may include: in step s101, with the aileron blade 30 in its initial position, controlling the main drive unit 40 to drive the main wing blade 20 and the aileron blade 30 to rotate around the main wing rotation axis at a preset speed for a predetermined time; and in step s102, acquiring the airflow value generated by the axial flow fan within the predetermined time. This step allows for the measurement of various positions of the aileron blade 30, thereby ensuring optimization accuracy.

[0072] In this embodiment of the disclosure, the predetermined duration is h, the number of revolutions of the main airfoil 20 is n, n is not less than 50 to ensure sufficient test cycles, and the rotational speed of the main drive component 40 is R. The predetermined duration h, the number of revolutions n, and the rotational speed R satisfy the following: This ensures sufficient operating time and a guaranteed number of revolutions, thereby guaranteeing more accurate values. The unit for rotational speed R is rpm, and the unit for the predetermined operating time h is seconds.

[0073] Reference Figure 16 S105 includes: in S1051, after the main wing blade 20 and the aileron blade 30 rotate around the main wing rotation axis for a predetermined period of time, obtaining the average input current of the main drive unit 40 within each predetermined period of time; and in S1052, obtaining the air volume value generated by the axial flow fan after each predetermined period of operation of the main drive unit 40, according to the relationship between current and air volume y, where the relationship between current x and air volume y is: Where k1 is 7550~7650, for example 7600; k2 is 23450~23550, for example 23500; k3 is 26100~26200, for example 26150; and b is 6000~6200, for example 6120. s106 includes: determining the maximum airflow value from the multiple sets of airflow values ​​obtained in s1052; and in s1061, determining the average input current corresponding to the maximum airflow value according to the relationship between current x and airflow y, to determine the optimal rotation angle of the aileron blade 30. Wherein, the relationship between current x and airflow y is based on... Figure 17 The relationship between current and air volume for main blades of different diameters is shown in the diagram. The relationship between current and air volume is basically the same for main blades of different diameters. Based on the data fitting, the relationship between current x and air volume y can be determined.

[0074] According to a third aspect of the present disclosure, a ventilation device is provided, including an axial flow fan provided according to the present disclosure, and having all the beneficial effects of the aforementioned axial flow fan, which will not be repeated here. The ventilation device in the embodiments of the present disclosure can be an outdoor unit of an air conditioner, a refrigerator, a drying device, or other equipment with ventilation requirements.

[0075] The ventilation device in this embodiment may have a processor and a memory. The processor executes instructions to implement the control method described above, and the memory stores the processor-executable instructions and the numerical values ​​obtained above, such as the rotation angle of the aileron blade 30, the airflow, and the input current. The memory may be implemented by any type of volatile or non-volatile storage device or a combination thereof, such as static random access memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic storage, flash memory, magnetic disk, or optical disk.

[0076] Those skilled in the art will also understand that the various steps listed in the embodiments of this application can be implemented by electronic hardware, computer software, or a combination of both. Whether such functionality is implemented through hardware or software depends on the specific application and the overall system design requirements. Those skilled in the art can implement the described functionality using various methods for each specific application, but such implementation should not be construed as exceeding the scope of protection of the embodiments of this application.

[0077] In the above detailed description, reference has been made to the accompanying drawings, which illustrate specific aspects of this disclosure by way of illustration. In this regard, terms indicating direction or positional relationship, such as “center,” “longitudinal,” “lateral,” “length,” “width,” “thickness,” “upper,” “lower,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” “outer,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential,” are used with reference to the orientation of the described figures. Since components of the described device can be positioned in multiple different orientations, directional terms are used for illustrative purposes and not for limitation. It should be understood that other aspects can be utilized and structural or logical changes can be made without departing from the concept of this disclosure. Therefore, the following detailed description should not be considered limiting.

[0078] It should be understood that, unless otherwise specifically indicated, features of various embodiments of this disclosure described herein can be combined with each other. As used herein, the term “and / or” includes any one of the relevant listed items and any combination of any two or more; similarly, “at least one of…” includes any one of the relevant listed items and any combination of any two or more.

[0079] It should be understood that, unless otherwise expressly specified and limited, the terms "joining," "attaching," "installing," "connecting," "linking," "fixing," etc., used in the embodiments of this disclosure should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms herein based on the specific circumstances.

[0080] Furthermore, the term "above" as used herein with respect to components, elements, or material layers formed or located "above" a surface may be used to indicate that the component, element, or material layer is "indirectly" positioned (e.g., placed, formed, deposited, etc.) on the surface such that one or more additional components, elements, or layers are arranged between the surface and the component, element, or material layer. However, the term "above" as used with respect to components, elements, or material layers formed or located "above" a surface may also optionally have a specific meaning: that the component, element, or material layer is "directly" positioned (e.g., placed, formed, deposited, etc.) on the surface, for example, in direct contact with the surface.

[0081] Although terms such as “first,” “second,” and “third” may be used herein to describe various components, parts, regions, layers, or sections, these components, parts, regions, layers, or sections are not limited to these terms. Rather, these terms are used only to distinguish one component, part, region, layer, or section from another. Therefore, without departing from the teachings of the examples described herein, the first component, part, region, layer, or section mentioned in the examples may also be referred to as the second component, part, region, layer, or section. Furthermore, the terms “first” and “second” are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as “first” or “second” may explicitly or implicitly include at least one of that feature. In the description herein, “a plurality” means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0082] It should be understood that spatial relative terms, such as “above,” “upper,” “below,” and “lower,” are used herein to describe the relationship between one element and another shown in the figures. In addition to the orientation depicted in the figures, these spatial relative terms are also intended to encompass different orientations of the device in use or operation. For example, if the device in the figures is flipped, an element described as “above” or “upper” relative to another element would be “below” or “lower” relative to that other element. Thus, depending on the spatial orientation of the device, the term “above” encompasses both above and below orientations. Devices may have other orientations (e.g., rotated 90 degrees or in other orientations), and the spatial relative terms used herein should be interpreted accordingly.

[0083] Furthermore, the term “exemplary” is used herein to mean serving as an example, instance, or illustration. Any aspect or design described herein as “exemplary” is not necessarily to be construed as advantageous compared to other aspects or designs. Rather, the use of the term “exemplary” is intended to present the concept in a concrete manner. As used herein, the term “or” is intended to mean an inclusive “or” rather than an exclusive “or.” That is, unless otherwise specified or clear from the context, “X applies A or B” is intended to mean any of the natural inclusive arrangements. That is, “X applies A or B” satisfies any of the foregoing instances if X applies A; X applies B; or both X applies A and B. Additionally, unless otherwise specified or clear from the context to refer to the singular form, the articles “a” and “an” as used in this application and the appended claims are generally understood to mean “one or more.”

[0084] Similarly, although this disclosure has been shown and described with respect to one or more implementations, equivalent variations and modifications will occur to those skilled in the art upon reading and understanding this specification and the accompanying drawings. This disclosure includes all such modifications and variations and is limited only by the scope of the claims. In particular, with respect to the various functions performed by the components described above (e.g., elements, resources, etc.), unless otherwise indicated, the terminology used to describe such components is intended to correspond to any component (functionally equivalent) that performs the specific function of the described component, even if structurally not equivalent to the disclosed structure. Furthermore, although specific features of this disclosure may have been disclosed with respect to only one of several implementations, such features may be combined with one or more other features of other implementations, as may be desired and advantageous to any given or particular application. Moreover, with regard to the terms “comprising,” “owning,” “having,” “having,” or variations thereof as used in the detailed description or claims, such terms are intended to be inclusive in a manner similar to the term “including.”

[0085] Other embodiments of this disclosure will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of this disclosure are indicated by the appended claims.

[0086] It should be understood that this disclosure is not limited to the precise structures described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this disclosure is limited only by the appended claims.

Claims

1. An axial flow fan characterised in that, The application relates to a propeller hub, comprising: a hub; a main wing blade installed on the hub; a winglet blade arranged on the suction surface side of the main wing blade and rotatably installed on the hub around a winglet rotation axis; a main driving element coaxially connected with the hub to drive the hub to rotate the main wing blade and the winglet blade around a main wing rotation axis.

2. The axial fan according to claim 1, characterized in that An axle rod is arranged at the end of the winglet blade and penetrates a circumferential wall of the hub along the direction of the winglet rotation axis.

3. The axial fan according to claim 2, characterized in that A winglet driving element is arranged on the inner side of the circumferential wall of the hub and connected with the axle rod to drive the axle rod to rotate around the winglet rotation axis.

4. The axial fan of claim 3, wherein The winglet driving element is connected with the axle rod through a shaft coupling structure, which has a disengaged mode and an engaged mode; in the disengaged mode, the axle rod is disengaged from the winglet driving element; in the engaged mode, the axle rod is connected with the winglet driving element.

5. The axial fan of claim 4, wherein The shaft coupling structure comprises a telescopic element and a telescopic driving element; the telescopic element is movably arranged on the driving end of the winglet driving element in the direction of approaching or moving away from the axle rod; the telescopic driving element is used for driving the telescopic element to move; in the disengaged mode, the telescopic element is retracted to be disengaged from the axle rod; in the engaged mode, the telescopic element is extended to be connected with the axle rod.

6. The axial fan of claim 5, wherein, One end of the axle rod is provided with a plug element, and one end of the telescopic element is provided with a matching element; in the engaged mode, the plug element is matched and plugged with the matching element.

7. The axial fan of claim 5, wherein A rack is arranged on the telescopic element, and the driving end of the telescopic driving element is connected with a cam; the protruding part of the cam is provided with a matching tooth to be engaged with the rack.

8. The axial fan of claim 1, wherein, The main wing blade comprises a main wing leading edge and a main wing trailing edge; the winglet blade is arranged between the main wing leading edge and the main wing trailing edge and close to the main wing leading edge.

9. The axial fan of claim 8, wherein, The winglet blade is configured to extend and bend from the inner end to the outer end of the main wing blade, and the bending direction is consistent with the bending direction of the main wing leading edge.

10. The axial fan of claim 9, wherein, The winglet blade comprises a winglet leading edge and a winglet trailing edge; the included angle a between the line connecting the wingtip of the winglet leading edge close to the outer end of the main wing blade and the center point of the winglet blade close to the inner end of the main wing blade and the winglet rotation axis is not less than 10 degrees and not more than 35 degrees.

11. The axial fan of claim 1, wherein The main wing blade comprises a main wing leading edge and a main wing trailing edge; in the front-rear direction of the main wing blade, the distance between the main wing leading edge and the rotation center of the winglet blade is L1, and the chord length of the main wing blade is L2; wherein, L1 / L2 is 0.2-0.

3.

12. The axial fan of claim 1, wherein, The chord length of the main wing blade is L2, and the chord length of the winglet blade is L3; wherein, L3 / L2 is 0.05-0.

15.

13. The axial fan of claim 1, wherein, The minimum distance between the winglet rotation axis and the main wing blade is L4, and the chord length of the winglet blade is L3; wherein, L4 / L3 is 0.8-1.

2.

14. The axial fan of claim 1, wherein, The winglet blade comprises a winglet leading edge and a winglet trailing edge; the minimum distance between the winglet leading edge and the main wing blade is L5, the minimum distance between the winglet trailing edge and the main wing blade is L6, and the chord length of the main wing blade is L2; wherein, L5 / L2 and L6 / L2 are both not less than 0.

03.

15. The axial fan of claim 1, wherein, The main wing blade includes a main wing leading edge and a main wing trailing edge, and a distance from an intersection point of a pressure surface outflow tangent of the aileron blade and a chord line of the main wing blade to the main wing leading edge is L7 in a front-rear direction of the main wing blade, and a chord length of the main wing blade is L2, wherein L7 / L2 is not greater than 2 / 3.

16. A ventilation device, characterized in that An axial flow fan comprising the axial flow fan according to any one of claims 1 to 15.

Images