A leading edge reinforced continuous fiber composite blade

Abstract

The utility model discloses a front edge reinforced continuous fiber composite material paddle of paddle structure design and composite material application technical field, including paddle matrix, front edge reinforced layer and interlock structure, the utility model discloses a interlock structure is arranged to the front edge of continuous fiber reinforced thermosetting resin paddle, and adopts injection molding and covers thermoplastic material, realizes the reliable connection of protective layer and matrix, and the impact resistance and structural stability of paddle front edge are significantly promoted, and the service life of paddle is prolonged.

Description

Technical Field

[0001] This utility model relates to the field of blade structure design and composite material application technology, specifically a leading-edge reinforced continuous fiber composite blade. Background Technology

[0002] As the core component of a power unit, the blades often operate in complex and harsh environments. They must withstand the centrifugal force generated by high-speed rotation, the continuous scouring of airflow or water flow, and are also susceptible to the impact of foreign objects such as sand, water droplets, and debris. The leading edge of the blade, as the direct windward / waterward surface, is a high-risk area for damage.

[0003] Traditional blades are mainly made of aluminum alloy matrix or single composite material. Aluminum alloy blades have defects such as poor fatigue resistance and easy corrosion. Moreover, the leading edge protection is mostly made of metal protective cover bonding method. After long-term use, damage such as debonding and pitting is prone to occur. Although single thermosetting composite material blades have the advantages of being lightweight and high strength, they have insufficient impact resistance. After the leading edge is impacted, cracks or even structural failure are easily generated, which seriously affects the service life and operational safety of the blade. Utility Model Content

[0004] The purpose of this section is to outline some aspects of the embodiments of this utility model and to briefly introduce some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be used to limit the scope of this utility model.

[0005] In view of the problems existing in the above and / or the existing leading-edge reinforced continuous fiber composite blade, the present invention is proposed.

[0006] Therefore, the purpose of this invention is to provide a leading-edge reinforced continuous fiber composite blade. By setting an interlocking structure at the leading edge of the continuous fiber reinforced thermosetting resin blade and using injection molding to coat thermoplastic material, a reliable connection between the protective layer and the substrate is achieved, which significantly improves the impact resistance and structural stability of the blade leading edge and extends the service life of the blade.

[0007] To solve the above-mentioned technical problems, according to one aspect of the present invention, the present invention provides the following technical solution:

[0008] A leading-edge reinforced continuous fiber composite blade, comprising:

[0009] The blade base has a trailing edge at the bottom and a leading edge at the top, with a connecting groove provided at the front end of the leading edge.

[0010] A leading edge reinforcement layer is encapsulated inside the connecting groove by insert injection molding;

[0011] The interlocking structure includes a first concave-convex structure located on the outer wall of the connecting groove and a second concave-convex structure located on the outer wall of the leading edge reinforcing layer, wherein the first concave-convex structure and the second concave-convex structure interlock with each other.

[0012] As a preferred embodiment of the leading edge reinforced continuous fiber composite blade of the present invention, the first concave-convex structure includes a first protrusion and a first groove, and the first protrusion and the first groove are multiple and arranged alternately on the outer wall of the connecting groove; the second concave-convex structure includes a second groove and a second protrusion, and the second groove and the second protrusion are multiple and arranged alternately on the outer wall of the leading edge reinforcement layer.

[0013] In a preferred embodiment of the leading-edge reinforced continuous fiber composite blade of this utility model, when the first protrusion and the first groove are arranged in a serrated, alternating pattern on the outer wall of the connecting groove, the second groove and the second protrusion are arranged in a serrated, alternating pattern on the outer wall of the leading-edge reinforcing layer. At this time, the first protrusion and the second protrusion are serrated protrusions, and the first groove and the second groove are corresponding serrated grooves. When the leading-edge reinforcing layer is injection molded to cover the inside of the connecting groove, the first protrusion covers the inside of the second groove, and the second protrusion covers the inside of the first groove.

[0014] In a preferred embodiment of the leading-edge reinforced continuous fiber composite blade of this utility model, when the first protrusion and the first groove are arranged in a dovetail-shaped alternating pattern on the outer wall of the connecting groove, the second groove and the second protrusion are arranged in a dovetail-shaped alternating pattern on the outer wall of the leading-edge reinforcing layer. At this time, the first protrusion and the second protrusion are dovetail-shaped protrusions, and the first groove and the second groove are corresponding dovetail-shaped grooves. When the leading-edge reinforcing layer is injection molded to cover the inside of the connecting groove, the first protrusion covers the inside of the second groove, and the second protrusion covers the inside of the first groove.

[0015] In a preferred embodiment of the leading-edge reinforced continuous fiber composite blade of this utility model, when the first protrusion and the first groove are arranged in a trapezoidal alternating pattern on the outer wall of the connecting groove, the second groove and the second protrusion are arranged in a trapezoidal alternating pattern on the outer wall of the leading-edge reinforcing layer. At this time, the first protrusion and the second protrusion are trapezoidal protrusions, and the first groove and the second groove are corresponding trapezoidal grooves. When the leading-edge reinforcing layer is injection molded to cover the inside of the connecting groove, the first protrusion covers the inside of the second groove, and the second protrusion covers the inside of the first groove.

[0016] As a preferred embodiment of the leading edge reinforced continuous fiber composite blade of this utility model, the blade matrix has a curved transition section at the tail end, the curved transition section has a connecting section at the tail end, the connecting section has a connecting hole on its side wall, and the blade trailing edge, the blade leading edge, the curved transition section and the connecting section are continuous fiber reinforced thermosetting resin composite material structures, which are made by composite molding of continuous fibers and thermosetting resin.

[0017] As a preferred embodiment of the leading edge reinforced continuous fiber composite blade of the present invention, the top of the leading edge reinforcing layer has an outer edge of the reinforcing layer, the outer edge of the reinforcing layer is flush with the leading edge of the blade, the interior of the leading edge reinforcing layer has a boss connecting groove, and the interior of the blade leading edge has a connecting boss at the middle position. When the leading edge reinforcing layer is injection molded to cover the interior of the connecting groove, the connecting boss is wrapped inside the boss connecting groove.

[0018] As a preferred embodiment of the leading edge reinforced continuous fiber composite blade of this utility model, the height of the first protrusion and the second protrusion is 0.5-3mm, the width of the first protrusion and the second protrusion is 1-5mm, the distance between two adjacent first protrusions is 1-5mm, and the distance between two adjacent second protrusions is 1-5mm.

[0019] As a preferred embodiment of the leading-edge reinforced continuous fiber composite blade of this utility model, the thickness of the leading-edge reinforcing layer is 1-5mm, and the outer surface of the leading-edge reinforcing layer smoothly transitions with the upper and lower surfaces of the blade substrate to form a continuous curved surface that conforms to the aerodynamic shape.

[0020] As a preferred embodiment of the leading edge reinforced continuous fiber composite blade of the present invention, the continuous fiber laying direction of the blade matrix includes 0° laying along the blade spanning direction and 90° laying perpendicular to the spanning direction, and the fiber volume fraction is 50%-70%.

[0021] Compared with existing technologies, the blade matrix formed by continuous fiber and thermosetting resin composite provides a stable mechanical load-bearing foundation for the blade. The fiber laying method can be optimized according to the stress requirements of the blade, ensuring structural strength and stiffness. By setting an interlocking structure between the blade leading edge and the leading edge reinforcement layer, the contact area and bonding force with the leading edge reinforcement layer are increased through mechanical interlocking, avoiding the debonding problem that is prone to occur in traditional coating structures. When thermoplastic material is coated onto the leading edge surface by injection molding, the thermoplastic material fully fills the gaps between the interlocking structure in the molten state. After cooling and solidification, it forms a firm mechanical interlock with the interlocking structure, making the leading edge reinforcement layer and the blade matrix an integrated structure. The thermoplastic material itself has excellent impact toughness, which can effectively absorb the energy generated by the impact of foreign objects and reduce the transmission of impact load to the blade matrix, thereby significantly improving the impact resistance and wear resistance of the blade leading edge and extending the service life of the blade under complex working conditions. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this utility model, the present utility model will be described in detail below with reference to the accompanying drawings and detailed embodiments. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Among them:

[0023] Figure 1 This is a structural diagram of a continuous fiber composite blade with leading edge reinforcement according to the present invention.

[0024] Figure 2 This is a cross-sectional structural diagram of the leading edge reinforcement layer of a continuous fiber composite blade according to the present invention.

[0025] Figure 3 This is a structural diagram of the blade matrix of a continuous fiber composite blade with leading edge reinforcement according to the present invention. Detailed Implementation

[0026] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0027] Secondly, this utility model is described in detail with reference to the schematic diagrams. When describing the embodiments of this utility model, for ease of explanation, the cross-sectional views showing the device structure may be partially enlarged, not according to the usual proportions. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of this utility model. In addition, actual manufacturing should include the three-dimensional spatial dimensions of length, width, and depth.

[0028] To make the objectives, technical solutions, and advantages of this utility model clearer, the embodiments of this utility model will be described in further detail below with reference to the accompanying drawings.

[0029] This invention provides a leading-edge reinforced continuous fiber composite blade. By setting an interlocking structure at the leading edge of the continuous fiber reinforced thermosetting resin blade and using injection molding to coat thermoplastic material, a reliable connection between the protective layer and the substrate is achieved, which significantly improves the impact resistance and structural stability of the blade leading edge and extends the service life of the blade.

[0030] Example 1

[0031] Figure 1-3 The diagram shown is a structural schematic of one embodiment of a leading-edge reinforced continuous fiber composite blade according to this invention. Please refer to [link / reference]. Figures 1-3 The blade of this embodiment, which is a leading-edge reinforced continuous fiber composite material, includes a blade substrate 100, a leading-edge reinforcing layer 200, and an interlocking structure 300.

[0032] The blade substrate 100 has a trailing edge 110 at the bottom and a leading edge 120 at the top. The tail end of the blade substrate 100 has a curved transition section 130, and the tail end of the curved transition section 130 has a connecting section 140. The side wall of the connecting section 140 has a connecting hole 140a. The trailing edge 110, the leading edge 120, the curved transition section 130, and the connecting section 140 are continuous fiber reinforced thermosetting resin composite material structures, which are made by composite molding of continuous fibers and thermosetting resin. A connecting groove 120a is provided at the front end of the top of the leading edge 120, and a connecting boss 120b is provided in the middle of the interior of the leading edge 120. The continuous fibers of the blade substrate 100 are selected from at least one of glass fiber, carbon fiber, aramid fiber, or basalt fiber. The thermosetting resin of the blade substrate 100 is selected from at least one of epoxy resin, phenolic resin, unsaturated polyester resin, or bismaleimide resin.

[0033] The leading edge reinforcement layer 200 has the same shape and size as the connecting groove 120a. The bottom of the leading edge reinforcement layer 200 has a boss connecting groove 220, which has the same shape as the connecting boss 120b. The leading edge reinforcement layer 200 is embedded inside the connecting groove 120a, and the connecting boss 120b is embedded inside the boss connecting groove 220. The leading edge reinforcement layer 200 is a thermoplastic material layer, which is injection molded into the connecting groove 120a through inserts. The top of the leading edge reinforcement layer 200 is flush with the top of the blade leading edge 120. The leading edge reinforcement layer 200 is injection molded into the front end of the blade leading edge 120 and fills the connecting groove 120a. The thermoplastic material is selected from at least one of polycarbonate, ultra-high molecular weight polyethylene, nylon, or polyphenylene sulfide.

[0034] The interlocking structure 300 includes a first convex-concave structure 310 located on the outer wall of the connecting groove 120a and a second convex-concave structure 320 located on the outer wall of the leading edge reinforcement layer 200. The first convex-concave structure 310 and the second convex-concave structure 320 interlock with each other. The first convex-concave structure 310 includes a first protrusion 310a and a first groove 310b, and there are multiple first protrusions 310a and first grooves 310b arranged alternately on the outer wall of the connecting groove 120a. The second convex-concave structure 320 includes a second groove 320a and a second protrusion 320b, and there are multiple second grooves 320a and second protrusions 320b arranged alternately on the outer wall of the leading edge reinforcement layer 200. The wall has a first protrusion 310a corresponding to a second groove 320a, with each first protrusion 310a embedded inside the corresponding second groove 320a. Similarly, each second protrusion 320b corresponds to a first groove 310b, with each second protrusion 320b embedded inside the corresponding first groove 310b. Not shown in the figures, the first and second concave-convex structures 310 and 320 employ a mechanical interlocking structure with a concave-convex shape, including a dovetail structure, a dovetail groove structure, or a trapezoidal groove structure with alternating protrusions and grooves. In this embodiment, a dovetail groove structure is used as an example. When the first protrusion 310a... When the second groove 320a is a dovetail slot insert, the second groove 320a is a dovetail slot corresponding to its shape and size. Similarly, when the second protrusion 320b is a dovetail slot insert, the first groove 310b is a dovetail slot corresponding to its shape and size. Not shown in the figure, the first protrusion 310a and the first groove 310b are formed either integrally with a mold or through post-processing: when the blade base 100 is integrally formed with a mold, corresponding concave and convex structures are provided in the leading edge area of ​​the blade forming mold, so that the first protrusion 310a and the first groove 310b structures are formed simultaneously during the forming process of the blade base 100; while in post-processing, the first protrusion 310a and the first groove 310b structures are formed simultaneously through milling and grinding. The first protrusion 310a and the first groove 310b are machined inside the formed connecting groove 120a by cutting or laser cutting. The leading edge reinforcement layer 200 is injection molded onto the front end of the blade leading edge 120 and fills the connecting groove 120a. During injection molding, the thermoplastic material cooperates with the first protrusion 310a and the first groove 310b to form the second groove 320a and the second protrusion 320b. At this time, the first protrusion 310a is embedded in the second groove 320a and the second protrusion 320b is embedded in the first groove 310b to form a tight bond, so that the leading edge reinforcement layer 200 and the blade substrate 100 become an integrated structure.

[0035] The height of the first protrusion 310a and the second protrusion 320b is 0.5-3mm, and the width of the first protrusion 310a and the second protrusion 320b is 1-5mm. The distance between two adjacent first protrusions 310a is 1-5mm, and the distance between two adjacent second protrusions 320b is 1-5mm. The thickness of the leading edge reinforcing layer 200 is 1-5mm. This ensures effective mechanical engagement with the leading edge reinforcing layer without affecting the structural strength of the blade substrate. The outer surface of the leading edge reinforcing layer 200 smoothly transitions with the upper and lower surfaces of the blade substrate 100, forming a continuous curve that conforms to the aerodynamic shape. The surface can form a continuous curved surface that conforms to the aerodynamic shape, avoiding airflow / water flow turbulence. The continuous fiber laying direction of the blade substrate 100 includes 0° laying along the blade span direction and 90° laying perpendicular to the span direction, with a fiber volume fraction of 50%-70%, ensuring that the blade substrate has excellent mechanical load-bearing performance. Not shown in the figure, the injection molding parameters of the leading edge reinforcement layer 200 are: injection temperature 180-320℃, injection pressure 0.5-5MPa, and holding time 1-10min, ensuring that the thermoplastic material fully fills the gaps of the interlocking structure and forms a tight bond.

[0036] Compared with the prior art, this application has the following advantages:

[0037] 1. Significantly improved impact resistance: Through the synergistic effect of the thermoplastic material reinforcement layer and the interlocking structure, the high toughness of the thermoplastic material can effectively absorb impact energy, while the interlocking structure avoids the peeling failure of the reinforcement layer. According to the test, the impact resistance of the blade leading edge of this application is more than 40% higher than that of traditional single composite material blades, and it can withstand the high-speed impact of sand and gravel with a particle size of less than 5mm.

[0038] 2. High structural stability: The mechanical interlocking and injection molding composite connection method improves the bonding strength between the leading edge reinforcement layer and the blade substrate by more than 60% compared with traditional bonding or coating. It is not easy to debond or fall off in harsh environments such as high temperature, high humidity and vibration, and the structural stability is significantly enhanced.

[0039] 3. Flexible and efficient molding: The interlocking structure can be molded in one piece or processed in the post-processing stage to adapt to different production needs. Insert injection molding can realize the rapid molding of the reinforcing layer, which can improve production efficiency by more than 30% and the product size accuracy can be controlled.

[0040] 4. Excellent aerodynamic performance: The outer surface of the leading edge reinforcement layer smoothly transitions to the blade substrate, maintaining the optimized aerodynamic shape of the blade and avoiding airflow / water flow turbulence caused by the protrusion of the protective structure, ensuring that the dynamic performance of the blade is not affected.

[0041] 5. Wide range of applications: The types of continuous fiber, thermosetting resin and thermoplastic materials can be flexibly selected according to different blade application scenarios, which can meet the blade requirements of various power devices such as aviation, ships, and drones, making it highly practical.

[0042] Example 2

[0043] In this embodiment, when the blade substrate 100 and the leading edge reinforcement layer 200 are used as UAV rotor blades, the blade substrate 100 is made of carbon fiber and epoxy resin composite, the carbon fiber volume fraction is 60%, and the carbon fiber is laid in an alternating superposition of 0° laying along the blade spanning direction and 90° laying perpendicular to the spanning direction. It is then hot-pressed by a mold at a molding temperature of 150°, a pressure of 3MPa, and a holding time of 2h.

[0044] The first protrusion 310a and the first groove 310b are integrally formed in the connecting groove 120a by mold, and are continuously distributed along the elongation direction of the blade leading edge. They have a dovetail structure, with the protrusion 21 having a height of 1mm, a width of 2mm, and a spacing of 2mm between adjacent protrusions.

[0045] The leading edge reinforcement layer 200 is made of polycarbonate material and is wrapped around the leading edge of the blade and the surface of the interlocking structure by insert injection molding. The injection temperature is 260℃, the injection pressure is 2MPa, the holding time is 3min, the thickness of the reinforcement layer is 2mm, and the outer surface is smoothly transitioned with the upper and lower surfaces of the blade substrate to form a continuous aerodynamic curved surface.

[0046] The drone rotor blades underwent impact testing. After being impacted by 3mm diameter sand and gravel at a wind speed of 80m / s, the leading edge showed no cracks or debonding. The impact resistance was improved by 45% compared to traditional carbon fiber blades, and the service life was extended by more than 2 times.

[0047] Example 3

[0048] In this embodiment, when the blade substrate 100 and the leading edge reinforcing layer 200 are used as ship propulsion blades, the blade substrate 100 is made of glass fiber and unsaturated polyester resin composite, the glass fiber volume fraction is 55%, the glass fiber is laid mainly at 0° along the blade span direction, supplemented by 45° oblique laying, and is formed by vacuum introduction.

[0049] The first protrusion 310a and the first groove 310b are formed by post-processing. A dovetail groove structure is machined on the leading edge of the formed blade by milling. The protrusion 21 has a height of 2mm, a width of 3mm, and a spacing of 3mm between adjacent protrusions.

[0050] The leading edge reinforcement layer 200 is made of ultra-high molecular weight polyethylene material and is encapsulated by insert injection molding. The injection temperature of the leading edge reinforcement layer is 200℃, the injection pressure is 3MPa, the holding time is 5min, the thickness of the reinforcement layer is 3mm, and the outer surface is polished to smoothly transition with the blade substrate, forming a continuous aerodynamic curved surface.

[0051] The propeller blades of this ship underwent impact testing. After being impacted by 5mm diameter silt at a water flow velocity of 10m / s, the leading edge showed no cracks or debonding. The impact resistance was improved by 45% compared to traditional fiberglass blades, and the service life was extended by more than 2.5 times.

[0052] Although the present invention has been described above with reference to embodiments, various modifications can be made and components can be replaced with equivalents without departing from the scope of the present invention. In particular, as long as there is no structural conflict, the features in the embodiments disclosed in this invention can be combined with each other in any way. The lack of an exhaustive description of these combinations in this specification is merely for the sake of brevity and resource conservation. Therefore, the present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A leading-edge reinforced continuous fiber composite blade, characterized in that, include: The blade base (100) has a blade trailing edge (110) at the bottom and a blade leading edge (120) at the top. A connecting groove (120a) is provided at the front end of the blade leading edge (120). A leading edge reinforcement layer (200) is encapsulated inside the connecting groove (120a) by insert injection molding; The interlocking structure (300) includes a first concave-convex structure (310) located on the outer wall of the connecting groove (120a) and a second concave-convex structure (320) located on the outer wall of the leading edge reinforcement layer (200), wherein the first concave-convex structure (310) and the second concave-convex structure (320) engage with each other.

2. The blade of a continuous fiber composite material with leading edge reinforcement according to claim 1, characterized in that, The first concave-convex structure (310) includes a first protrusion (310a) and a first groove (310b). The first protrusion (310a) and the first groove (310b) are multiple and are arranged alternately on the outer wall of the connecting groove (120a). The second concave-convex structure (320) includes a second groove (320a) and a second protrusion (320b). The second groove (320a) and the second protrusion (320b) are multiple and are arranged alternately on the outer wall of the leading edge reinforcement layer (200).

3. The blade of a continuous fiber composite material with leading edge reinforcement according to claim 2, characterized in that, When the first protrusion (310a) and the first groove (310b) are arranged in a serrated, alternating pattern on the outer wall of the connecting groove (120a), the second groove (320a) and the second protrusion (320b) are arranged in a serrated, alternating pattern on the outer wall of the leading edge reinforcement layer (200). At this time, the first protrusion (310a) and the second protrusion (320b) are serrated protrusions, and the first groove (310b) and the second groove (320a) are corresponding serrated grooves. When the leading edge reinforcement layer (200) is injection molded and encapsulated inside the connecting groove (120a), the first protrusion (310a) is encapsulated inside the second groove (320a), and the second protrusion (320b) is encapsulated inside the first groove (310b).

4. The leading-edge reinforced continuous fiber composite blade according to claim 2, characterized in that, When the first protrusion (310a) and the first groove (310b) are arranged in a dovetail-like alternating pattern on the outer wall of the connecting groove (120a), the second groove (320a) and the second protrusion (320b) are arranged in a dovetail-like alternating pattern on the outer wall of the leading edge reinforcement layer (200). At this time, the first protrusion (310a) and the second protrusion (320b) are dovetail-shaped protrusions, and the first groove (310b) and the second groove (320a) are corresponding dovetail-shaped grooves. When the leading edge reinforcement layer (200) is injection molded and covered inside the connecting groove (120a), the first protrusion (310a) is covered inside the second groove (320a), and the second protrusion (320b) is covered inside the first groove (310b).

5. The leading-edge reinforced continuous fiber composite blade according to claim 2, characterized in that, When the first protrusion (310a) and the first groove (310b) are arranged in a trapezoidal structure with alternating concave and convex shapes on the outer wall of the connecting groove (120a), the second groove (320a) and the second protrusion (320b) are arranged in a trapezoidal structure with alternating concave and convex shapes on the outer wall of the leading edge reinforcement layer (200). At this time, the first protrusion (310a) and the second protrusion (320b) are trapezoidal protrusions, and the first groove (310b) and the second groove (320a) are corresponding trapezoidal grooves. When the leading edge reinforcement layer (200) is injection molded and covered inside the connecting groove (120a), the first protrusion (310a) is covered inside the second groove (320a), and the second protrusion (320b) is covered inside the first groove (310b).

6. The leading-edge reinforced continuous fiber composite blade according to claim 1, characterized in that, The blade substrate (100) has a curved transition section (130) at its tail end, and the curved transition section (130) has a connecting section (140) at its tail end. The connecting section (140) has a connecting hole (140a) on its side wall. The trailing edge (110), the leading edge (120), the curved transition section (130), and the connecting section (140) are continuous fiber reinforced thermosetting resin composite material structures, which are made by composite molding of continuous fibers and thermosetting resin.

7. The leading-edge reinforced continuous fiber composite blade according to claim 1, characterized in that, The top of the leading edge reinforcement layer (200) has an outer edge (210) of the reinforcement layer, which is flush with the leading edge (120) of the blade. The leading edge reinforcement layer (200) has a boss connecting groove (220) inside, and a connecting boss (120b) is located in the middle of the leading edge (120) of the blade. When the leading edge reinforcement layer (200) is injection molded and covered inside the connecting groove (120a), the connecting boss (120b) is wrapped inside the boss connecting groove (220).

8. The leading-edge reinforced continuous fiber composite blade according to claim 2, characterized in that, The height of the first protrusion (310a) and the second protrusion (320b) is 0.5-3mm, the width of the first protrusion (310a) and the second protrusion (320b) is 1-5mm, the distance between two adjacent first protrusions (310a) is 1-5mm, and the distance between two adjacent second protrusions (320b) is 1-5mm.

9. The leading-edge reinforced continuous fiber composite blade according to claim 1, characterized in that, The thickness of the leading edge reinforcement layer (200) is 1-5 mm. The outer surface of the leading edge reinforcement layer (200) smoothly transitions with the upper and lower surfaces of the blade substrate (100) to form a continuous curved surface that conforms to the aerodynamic shape.

10. The leading-edge reinforced continuous fiber composite blade according to claim 1, characterized in that, The continuous fiber laying direction of the blade substrate (100) includes 0° laying along the blade span direction and 90° laying perpendicular to the span direction.

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