Rotor machining method

Abstract

The present application provides a rotor processing method, the rotor processing method comprising: providing a rotor, the rotor having a main shaft and a blade, an axial direction of the main shaft intersecting a span direction of the blade; processing the blade and forming a plurality of protrusions on a side of the blade along the axial direction, the plurality of protrusions being arranged along the span direction, and in a projection plane perpendicular to a chord direction of the blade, a normal projection area of the plurality of protrusions gradually decreases in a direction from a root of the blade toward a tip of the blade. The rotor processing method of the present application can improve the aerodynamic efficiency of the rotor.

Description

Technical Field

[0001] This invention relates to the field of rotor processing technology, and in particular to a rotor processing method. Background Technology

[0002] Rotors are core components in fields such as aircraft propulsion, wind power generation, industrial ventilation, and ship propulsion. A rotor consists of a main shaft and multiple blades arranged circumferentially along the main shaft. The main shaft drives the blades to rotate. When the main shaft rotates at high speed, a boundary layer forms on the blade surface, and flow separation occurs at the surface. This flow separation on the blade surface reduces rotor stability. Typically, flow separation on the blade surface is suppressed through turbulence to improve rotor stability. In existing technologies, turbulence structures are used to suppress flow separation. However, during rotor rotation, these structures generate significant drag on the rotor, leading to a decrease in aerodynamic efficiency. Summary of the Invention

[0003] This invention aims to at least solve one of the technical problems existing in the prior art. To this end, this invention proposes a rotor processing method that can improve the aerodynamic efficiency of rotors.

[0004] This invention provides a rotor manufacturing method, which includes: providing a rotor having a main shaft and blades, the axial direction of the main shaft intersecting the spanwise direction of the blades; manufacturing the blades and forming a plurality of protrusions on the side of the blades along the axial direction, the plurality of protrusions being arranged along the spanwise direction, and the orthographic projection area of ​​the plurality of protrusions gradually decreasing in the direction from the root of the blades toward the tip of the blades on a projection plane perpendicular to the chord direction of the blades.

[0005] The rotor processing method provided by the embodiments of the present invention has at least the following beneficial effects: By incorporating protrusions on the blades, these protrusions can turbulentize the air during rotor rotation and transition the laminar boundary layer on the blade surface to a turbulent boundary layer, thus suppressing flow separation on the blade surface. As the rotor rotates, the linear velocity of each part of the blade distributed along the root towards the tip gradually increases; that is, the protrusions near the blade tip have a higher linear velocity. In a projection plane perpendicular to the chord direction, the projected area of ​​multiple protrusions gradually decreases along the root towards the tip. This allows the disturbance intensity of each protrusion to the fluid to match its linear velocity, and reduces the difference in turbulence intensity of the turbulent boundary layer at each protrusion. This reduces the risk of excessively high turbulence in the turbulent boundary layer near the blade tip, which could lead to excessive friction between the blade and the fluid, thereby reducing the risk of excessive drag on the blade and ultimately improving the aerodynamic efficiency of the rotor.

[0006] In one embodiment of this implementation, multiple protrusions are located on the suction surface of the blades.

[0007] In one embodiment of this implementation, processing the blades includes: The printing process creates raised areas on the blades.

[0008] In one embodiment of this implementation, the axial dimensions of the plurality of protrusions gradually decrease along the direction from the root to the tip.

[0009] In one embodiment of this implementation, the distance between two adjacent protrusions gradually increases along the direction from the root to the tip.

[0010] In one embodiment of this implementation, on a projection plane perpendicular to the axial direction, the orthographic projection of the convex shape is a quadrilateral, and a pair of opposite corners of the quadrilateral are arranged along the chord direction.

[0011] In one embodiment of this implementation, the size of the plurality of protrusions gradually decreases in the spanwise direction along the direction from the root to the tip.

[0012] In one embodiment of this implementation, the distance between the protrusion and the leading edge of the blade is 4mm-9.6mm.

[0013] In one embodiment of this implementation, a hollow groove is formed on the side of the protrusion facing away from the blade.

[0014] In one embodiment of this implementation, the protrusion is a hexahedron, which forms a boss on the side of the blade along the axial direction, and the adjacent two sides of the boss transition smoothly.

[0015] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments, wherein: Figure 1 This is a schematic diagram of a rotor processing method according to one embodiment of the present invention; Figure 2 yes Figure 1 A schematic diagram of the blade structure; Figure 3 yes Figure 1 A schematic diagram of the propeller blade from another perspective.

[0017] Figure label: Blade 100; Root 11; Tip 12; Suction surface 13; Leading edge 14; Protrusion 20; Span 200; Chord 300; Axial 400. Detailed Implementation

[0018] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0019] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, front, back, left, right, etc., are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0020] In the description of this invention, "several" means one or more, "multiple" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. The use of "first" and "second" in the description is merely for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0021] In the description of this invention, unless otherwise explicitly defined, terms such as "set up," "install," and "connect" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this invention in conjunction with the specific content of the technical solution.

[0022] In the description of this invention, the terms "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0023] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

[0024] This invention provides a rotor manufacturing method; please refer to [link / reference]. Figure 1 , Figure 1 This is a schematic diagram of a rotor processing method according to one embodiment of the present invention. The rotor processing method includes: Step S100, a rotor is provided, the rotor having a main shaft and blades 100, the axial direction 400 of the main shaft intersecting the spanwise direction 200 of the blades 100.

[0025] Please refer to the following for details. Figures 2 to 3 , Figure 2 yes Figure 1 A schematic diagram of the structure of the blade 100; Figure 3 yes Figure 1 A schematic diagram of the structure of the blade 100 from another perspective. In this embodiment, the main shaft is cylindrical with its axis parallel to the axial direction 400. The rotor has multiple blades 100, which are arranged circumferentially on the outer circumferential surface of the main shaft. The blades 100 extend along the spanwise direction 200. The end of the blade 100 near the main shaft along the spanwise direction 200 forms a root 11, and the end of the blade 100 away from the main shaft along the spanwise direction 200 forms a tip 12.

[0026] In step S200, the blade 100 is processed, and a plurality of protrusions 20 are formed on the side of the blade 100 along the axial direction 400. The plurality of protrusions 20 are arranged along the spanwise direction 200. On the projection plane perpendicular to the chord direction 300 of the blade 100, along the direction from the root 11 of the blade 100 toward the tip 12 of the blade 100, the orthogonal projection area of ​​the plurality of protrusions 20 gradually decreases.

[0027] For details, please refer to Figures 2 to 3 The chord 300 intersects the axis 400 and the chord 300. The protrusion 20 can be installed on the rotor by means of bonding, welding and snap-fitting. The protrusion 20 can also be formed on the blade 100 by milling. Multiple protrusions 20 are arranged sequentially along the spanwise 200. The orthographic projections of multiple protrusions 20 in the plane perpendicular to the chord 300 are arranged in a queue along the spanwise 200. In the direction from the root 11 to the tip 12, the area of ​​the multiple orthographic projections in the queue formed by the multiple protrusions 20 decreases sequentially.

[0028] It should be understood that in some embodiments, span 200 is perpendicular to axis 400, and chord 300 is perpendicular to axis 400 and span 200.

[0029] It should be noted that in existing technologies, a turbulence-disrupting structure is typically installed on the rotor. The rotation of the rotor drives the turbulence-disrupting structure to disturb the fluid and form a turbulent boundary layer on the rotor surface to suppress flow separation. When the rotor rotates, the rotation radii of different parts of the rotor are different, resulting in different linear velocities. The parts of the rotor with higher linear velocities will drive the turbulence-disrupting structure to move relative to the fluid at a higher speed. This leads to an excessively high surface friction coefficient of the turbulent boundary layer formed on the surface of the parts with higher linear velocities. On the one hand, this results in uneven stress on different parts of the rotor, reducing the rotor's rotational stability and making the rotor prone to breakage and damage. On the other hand, it leads to excessively high overall drag on the rotor, reducing its aerodynamic efficiency.

[0030] Understandably, the spindle is mounted on a rotary drive and can rotate around an axis parallel to the axial direction 400 under the drive of the rotary drive, thereby driving the blade 100 to rotate around an axis parallel to the axial direction 400. The blade 100 can drive the protrusion 20 to rotate, so that the fluid can flow relative to the protrusion 20 along the incoming flow direction intersecting the chord direction 300, and the protrusion 20 will agitate the fluid. The projection plane perpendicular to the chord direction 300 is defined as the chord direction 300 plane, and the projection plane perpendicular to the incoming flow direction is defined as the flow direction plane. The projected area of ​​the protrusion 20 in the chord direction 300 plane is positively correlated with the projected area of ​​the protrusion 20 in the flow direction plane. Under the condition that the relative velocity between the protrusion 20 and the fluid remains constant, the larger the projected area of ​​the protrusion 20 in the flow direction plane, the greater the agitation intensity of the protrusion 20 on the fluid. Under the condition that the projected area of ​​the protrusion 20 in the flow direction plane remains constant, the greater the relative velocity between the protrusion 20 and the fluid, the greater the agitation intensity of the protrusion 20 on the fluid. In the chordal plane 300, along the direction from the root 11 to the tip 12, the projected area of ​​the multiple protrusions 20 gradually decreases, which makes the projected area of ​​the protrusions 20 in the flow plane negatively correlated with the rotation radius of the protrusions 20 at the position of the blade 100. This reduces the risk of excessively high surface friction coefficient of the turbulent boundary layer formed on the part of the blade 100 with a high linear velocity, and reduces the difference in friction force of the turbulent boundary layer on the various parts of the blade 100 distributed along the span 200, which is beneficial to improving the stability of the rotor during rotation.

[0031] The rotor processing method of the present invention provides a protrusion 20 on the blade 100. The protrusion 20 can disturb the air when the rotor rotates and cause the laminar boundary layer on the surface of the blade 100 to transition into a turbulent boundary layer, thereby suppressing flow separation on the surface of the blade 100. When the rotor rotates, the linear velocity of each part of the blade 100 distributed along the direction from the root 11 to the tip 12 gradually increases. That is, the linear velocity of the protrusion 20 near the tip of the blade 100 is larger. In the projection plane perpendicular to the chord 300, the orthographic projection area of ​​the multiple protrusions 20 gradually decreases along the direction from the root 11 to the tip 12. This allows the disturbance intensity of each protrusion 20 to the fluid to be matched with the linear velocity, and reduces the difference in turbulence intensity of the turbulent boundary layer at each protrusion 20. This reduces the risk of excessive turbulence of the turbulent boundary layer on the surface of the blade 100 near the tip, which would lead to excessive friction between the blade 100 and the fluid. This reduces the risk of excessive drag on the blade 100, thereby improving the aerodynamic efficiency of the rotor.

[0032] Please see Figures 1 to 3 In one embodiment of this implementation, a plurality of protrusions 20 are located on the suction surface 13 of the blade 100.

[0033] Specifically, one side surface of the blade 100 along the axial direction 400 is concave to form the pressure surface of the blade 100, while the other side surface of the blade 100 along the axial direction 400 is convex to form the suction surface 13 of the blade 100. This arrangement helps to further improve the stability of the rotor.

[0034] Please see Figures 1 to 3 In one embodiment of this implementation, processing the blade 100 includes: The protrusions 20 are formed on the blade 100 by a printing process.

[0035] Specifically, the blade 100 can be printed using pad printing and screen printing, and the ink can be adhered to the blade 100 to form the protrusions 20 on the blade 100.

[0036] It is understandable that by forming protrusions 20 on the blade 100 through printing, the pre-formed rotor can be post-processed to improve its aerodynamic efficiency, which is beneficial to improving the applicability and economy of rotor processing methods.

[0037] Please see Figures 1 to 3 In one embodiment of this implementation, the size of the plurality of protrusions 20 gradually decreases along the direction from the root 11 toward the tip 12 in the axial direction 400.

[0038] Specifically, the protrusion 20 protrudes relative to the suction surface 13 of the blade 100 along the axial direction 400. Along the direction from the root 11 to the tip 12, the distance b between the multiple protrusions 20 and the blade 100 along the axial direction 400 gradually decreases, so that the projected area of ​​the multiple protrusions 20 in the chordal plane 300 gradually decreases.

[0039] It is understandable that by adjusting the axial dimension b of the protrusion 20 to adjust the projected area of ​​the protrusion 20 in the chordal plane 300, it is possible to adjust the projected area of ​​the protrusion 20 in the chordal plane by adjusting the ink thickness printed on the blade 100, which helps to reduce manufacturing difficulty.

[0040] Please see Figures 1 to 3 In one embodiment of this implementation, the distance between two adjacent protrusions 20 gradually increases along the direction from the root 11 toward the tip 12.

[0041] Specifically, along the direction from the root 11 to the tip 12, the distance c between two adjacent protrusions 20 in the span 200 gradually increases.

[0042] Understandably, on the one hand, with the projected area of ​​the protrusions 20 in the flow plane remaining constant, the denser the arrangement of the multiple protrusions 20, the more protrusions 20 there are per unit size of the blade 100 along the spanwise direction 200, and the greater the disturbance intensity of the rotor on the fluid. Along the direction from the root 11 to the tip 12, the distance c between two adjacent protrusions 20 in the spanwise direction 200 gradually increases, enabling the disturbance capability of each part of the rotor to be matched with the linear velocity, thereby reducing the risk of excessively high surface friction coefficient of the turbulent boundary layer formed on the surface of the rotor with a higher linear velocity. On the other hand, by controlling the distance c between the multiple protrusions 20 and the projected area of ​​the protrusions 20 in the chordwise direction 300 plane, the disturbance capability of each part of the rotor can be adjusted in a coordinated manner, reducing the dimensional accuracy requirements of the protrusions 20, which is beneficial for reducing the accuracy requirements of the printing process.

[0043] Please see Figures 1 to 3 In one embodiment of this implementation, on a projection plane perpendicular to the axial direction 400, the orthographic projection of the protrusion 20 is a quadrilateral, and a pair of opposite corners of the quadrilateral are arranged along the chord direction 300.

[0044] Specifically, protrusion 20 is a rhomboid boss with a prismatic top surface. The orthographic projection of protrusion 20 in a plane perpendicular to the axial direction 40° is a rhombus. One set of diagonals of the rhombus is arranged along the chord direction 30°, and the other set of diagonals is arranged along the span direction 20°.

[0045] It is understandable that setting the protrusion 20 as a hexahedron and making its projection in a plane perpendicular to the axial direction 400 rhombus, with one set of diagonals of the rhombus arranged along the chord direction 300 and the other set of diagonals arranged along the spanwise direction 200, on the one hand, when the fluid passes through the protrusion 20, the fluid will pass through the front sharp corner of the rhombus and will deflect and flow around the front sharp corner along the spanwise direction 200. The fluid will also pass through the two front edges of the rhombus and form two flow vortices with opposite rotation directions. The two flow vortices form a pair of opposing vortices, and the vortex axis of the flow vortex is approximately parallel to the spanwise direction 200. On the other hand, it can form a Venturi channel between two adjacent protrusions 20, which is beneficial to improving the turbulence efficiency.

[0046] It should be noted that the ratio between the spanwise dimension of the protrusion 20 and the chordwise dimension of the protrusion 20 can be 1.5-3, so that the protrusion 20 can be adapted to slender blades 100 with large airflow velocity gradients in the spanwise direction 200. The ratio between the spanwise dimension of the protrusion 20 and the chordwise dimension of the protrusion 20 can be 1.5-2, so that the protrusion 20 can be adapted to wide-chord blades 100 with larger chordwise dimensions in the chordwise direction 300. In the direction from the root 11 to the tip 12, the dimension b of the protrusion 20 in the axial direction 400 can gradually decrease from 0.5 mm to 0.15 mm, which is beneficial for achieving adaptive turbulence with minimal drag across the entire spanwise direction 200 of the blade 100, and can improve the adaptability of the protrusion 20 to small rotors used as UAV propellers.

[0047] It should be understood that in some other embodiments, the protrusion 20 may be cylindrical, cuboid, or triangular.

[0048] Please see Figures 1 to 3 In one embodiment of this implementation, the size of the plurality of protrusions 20 gradually decreases in the spanwise direction 200 along the direction from the root 11 toward the tip 12.

[0049] Specifically, along the direction from the root 11 to the tip 12, the dimension a of the plurality of protrusions 20 in the span 200 gradually decreases, so that the projected area of ​​the plurality of protrusions 20 in the chord 300 plane gradually decreases.

[0050] It is understandable that by adjusting the spanwise dimension a of the protrusion 200 to adjust the projected area of ​​the protrusion 20 in the chordwise plane 300, the projected area of ​​the protrusion 20 in the chordwise plane can be adjusted while maintaining the same height of multiple protrusions 20, which is beneficial to improving the applicability of the rotor processing method.

[0051] Please see Figures 1 to 3 In one embodiment of this implementation, the distance between the protrusion 20 and the leading edge 14 of the blade 100 is 4mm-9.6mm.

[0052] Specifically, the distance d between the protrusion 20 and the leading edge 14 of the blade 100 can be 4mm, 5mm, 6.5mm, 8mm, and 9.6mm. It is understandable that when the distance d between the protrusion 20 and the leading edge 14 of the blade 100 is less than 4mm or greater than 9.6mm, the turbulence efficiency of the protrusion 20 will decrease. Setting the distance d between the protrusion 20 and the leading edge 14 of the blade 100 to 4mm-9.6mm is beneficial to improving the turbulence efficiency of the protrusion 20.

[0053] Please see Figures 1 to 3 In one embodiment of this implementation, a hollow groove is provided on the side of the protrusion 20 facing away from the blade 100.

[0054] Specifically, the hollow slot is located on the side of the protrusion 20 along the axial direction of 400°, facing away from the blade 100. Understandably, this arrangement reduces the weight of the protrusion 20, which helps to reduce the overall weight of the rotor.

[0055] Please see Figures 1 to 3 In one embodiment of this implementation, the protrusion 20 is a hexahedron, which forms a boss on the side of the blade 100 along the axial direction 400, and the adjacent two sides of the boss are smoothly transitioned.

[0056] Specifically, the two adjacent sides of the boss are connected by an arc surface. It can be understood that the smooth transition between the two adjacent sides of the boss can reduce the sharp structure on the protrusion 20, thereby reducing the risk of stress concentration on the protrusion 20. This can reduce the risk of shrinkage and cracking after the ink is formed on the protrusion 20, and thus improve the manufacturability of the protrusion 20 shape to better adapt to the printing process.

[0057] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments, and various changes can be made within the scope of knowledge possessed by those skilled in the art without departing from the spirit of the present invention. Furthermore, the embodiments of the present invention and the features thereof can be combined with each other unless otherwise specified.

Claims

1. A rotor processing method, characterized in that, include: A rotor is provided, the rotor having a main shaft and blades, the axial direction of the main shaft intersecting the spanwise direction of the blades; The blade is processed, and a plurality of protrusions are formed on the side of the blade along the axial direction. The plurality of protrusions are arranged along the spanwise direction. On the projection plane perpendicular to the chord direction of the blade, in the direction from the root of the blade toward the tip of the blade, the projected area of ​​the plurality of protrusions gradually decreases.

2. The rotor processing method according to claim 1, characterized in that, The plurality of protrusions are located on the suction surface of the blade.

3. The rotor processing method according to claim 1, characterized in that, The processing of the blade includes: The protrusions are formed on the blades using a printing process.

4. The rotor processing method according to claim 1, characterized in that, Along the direction from the root to the tip, the size of the plurality of protrusions gradually decreases in the axial direction.

5. The rotor processing method according to claim 1, characterized in that, Along the direction from the root to the tip, the distance between two adjacent protrusions gradually increases.

6. The rotor processing method according to claim 1, characterized in that, On a projection plane perpendicular to the axis, the orthographic projection of the protrusion is a quadrilateral, and a pair of opposite corners of the quadrilateral are arranged along the chord direction.

7. The rotor processing method according to claim 1, characterized in that, Along the direction from the root to the tip, the size of the plurality of protrusions gradually decreases in the spanwise direction.

8. The rotor processing method according to claim 1, characterized in that, The distance between the protrusion and the leading edge of the blade is 4mm-9.6mm.

9. The rotor processing method according to claim 1, characterized in that, The protrusion has a hollow groove on its side facing away from the blade.

10. The rotor processing method according to claim 3, characterized in that, The protrusion is a hexahedron, which forms a boss on the side of the blade along the axial direction, and the two adjacent sides of the boss transition smoothly.

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