CN116857114A - A kind of divided-bin splicing blade structure and design method - Google Patents

Abstract

The invention relates to the field of wind power generation blades, and in particular to a divided-bin splicing type blade structure and a design method. A divided and spliced blade structure includes a main beam, a leading edge shell, a trailing edge shell, a blade tip and a blade root. The main beam includes a windward side main beam and a leeward side main beam; the leading edge shell is installed on the main beam. On the leading edge side of the beam; the leading edge shell is a curved shell structure; it is a curved shell structure, installed on the trailing edge side of the main beam, forming a complete airfoil shape with the main beam and leading edge shell; the blade tip is a variable cross-section tip shell structure , the blade tip is installed at the first end of the main beam; the blade root is a cylindrical structure along the blade span, and the blade root is installed at the second end of the main beam. The segmented blade structure in the prior art is not very safe and impractical. As a structural integral component, the blade always has the risk of local failure expansion leading to an increase in the overall safety risk or even failure and destruction. Based on the above problems, there is an urgent need for a segmented blade. Chamber splicing blade structure and design method.

Description

A kind of divided-bin splicing blade structure and design method

Technical field

The invention relates to the field of wind power generation blades, and in particular to a split-bin splicing type blade structure and a design method.

Background technique

With the rapid development of the wind power industry, the design level of wind turbines is improving day by day, and wind turbine blades have been evolving in the direction of large-scale and lightweight. The difficulty of blade design, manufacturing, transportation, hoisting, and monitoring has increased significantly. The impact of direct factors caused by large-scale development is inevitable; while the impact of other factors can be alleviated through improvements in technical solutions. The most typical case in the industry is the idea of segmented blades, which is one of the more common technical solutions in current application technology.

Since the characteristic size of the blade in the spanwise direction is much larger than its characteristic size in the chordwise direction, the current segmented blade technology is segmented from the spanwise direction of the blade. According to the difference in segment position, it is subdivided into three categories: tip segment, mid-leaf segment and blade root segment. Among them, the blade tip segmentation has the disadvantage that it does not significantly alleviate the influence of blade large-scale processes and implementation factors, and is mostly used in technical modification work to improve blade power; the blade mid-section segmentation has the disadvantage that the connection position bears a large load and needs to be used In the form of mechanical connection, the local structure enhancement design is complex and difficult to implement, and it will change the natural frequency characteristics of the blade, which is prone to safety risks for the blade and even the entire machine. It is rarely used at this stage; the blade root is segmented, and the disadvantage is that for the blade The mitigation effect of large-scale process and implementation factors is not obvious. The connection position bears a large load, which is prone to safety risks of the blades and even the entire machine. The cost of regular monitoring and operation and maintenance is high, and there are few applications at this stage.

In addition, as a structural integral component, the blade always faces the risk of local failure expansion leading to an increase in overall safety risks or even failure and destruction. Based on the above problems, there is an urgent need for a split-bin spliced blade structure and design method, which can increase the safety and reliability of the blade structure.

Contents of the invention

The purpose of the present invention is to provide a split-blade splicing type blade structure and a design method to solve the problems in the prior art that the segmented blade structure is not very safe and is not practical.

In order to achieve the above objects, the present invention adopts the following technical solutions:

A divided-bin splicing type blade structure includes a main beam, a leading edge shell, a trailing edge shell, a blade tip and a blade root. The leading edge shell is installed on the first side end surface of the main beam; the front The edge shell is a curved shell structure; the trailing edge shell is a curved shell structure and is installed on the second side end surface of the main beam. The trailing edge shell is connected with the main beam and the front edge shell. forming a complete airfoil shape; the blade tip is a variable cross-section tip shell structure, and the blade tip is installed at the first end of the main beam; the blade root is a cylindrical structure along the blade span, and the blade root Installed on the second end of the main beam.

Optionally, a buffer connection device is also included. The buffer connection device is installed between the main beam on the windward side and the main beam on the leeward side. Through multiple sets of buffer connection devices, the main beams are formed into a fixed relative position. Variable cross-section beam structure.

Optionally, the buffer connection device includes a conformable bracket and a bracket foot. The conformable bracket is composed of a generalized spring damper system. There are two bracket feet. The shape is a bent plane, the first side of the bracket foot is connected to the inner surface of the main beam, and the second side of the bracket foot is fixedly connected to both ends of the conformable bracket respectively.

Optionally, the conformable bracket is composed of a spring damper system.

Optionally, the conformable bracket includes a cross beam and a cross connector. The intersection positions of the cross beam are rotationally connected through the cross connector. The cross connector is used to constrain the deformation of the cross beam. The cross beam The included angle changes with the support height.

Optionally, the leading edge housing and the trailing edge housing are divided into several sections along the blade span direction, each section corresponding to a set of buffer connection devices; each section of the leading edge housing or the trailing edge The shell is provided with a flange on the edge adjacent to the main beam, and the flange is fixedly connected to the third side of the bracket foot.

Optionally, the flange is connected to the third side of the bracket foot through a mechanical connector or assembly.

Optionally, the main beam and the blade root are connected by vacuum injection molding; the main beam and the blade tip are connected by adhesive bonding.

Optionally, a reinforcing structure is provided at the corner position of the flange to constrain the corner stiffness.

10. A design method for split-bin splicing blades, which is characterized by including:

S1. Establish a load calculation model based on the aerodynamic shape of the blade to calculate the envelope distribution of load components in each section of the blade span, as well as the circumferential position pressure distribution in each section of the blade span;

S2. Based on the envelope distribution results of the load components of each section and the blade root pitch diameter, use the traditional blade structure design method to design the initial structure of the traditional blade;

S3. Based on traditional blades, through stiffness equivalent conversion, design the main beam, blade root, blade tip, leading edge shell, and trailing edge shell of the blade structure;

S4. Calculate based on the pressure distribution results at the circumferential position within each section to obtain the aerodynamic load on the leading edge shell or trailing edge shell at each section position; combine the aerodynamic load and gravity load to calculate the total load along the blade waving direction of the corresponding section and The load component value projected in the oscillation direction is used to obtain the corresponding load component distribution;

S5. Set the load component threshold and divide the leading edge shell or trailing edge shell into several segments along the blade span direction. The integral value of the load component corresponding to each segment is not greater than the set load component threshold;

S6. Each blade leading edge shell or trailing edge shell corresponds to a set of buffer connection devices, and the conformal bracket of the blade structure is designed; the natural frequency of the conformable bracket is designed to be equal to the blade operating vibration frequency;

S7. Based on the integral value of the load component projected along the blade flapping direction of the combined load on each blade section's leading edge shell or trailing edge shell, design the connection method between the leading edge shell or trailing edge shell and the bracket foot; according to the corresponding buffer The conformable bracket of the connecting device bears the load value, and the connection method between the conformable bracket and the bracket foot is designed;

S8. Based on the relative position of the main beam in the spanwise area of the corresponding blade, design the angle between the bending planes of the bracket foot; according to the connection method between the bracket foot and the conformal bracket and the connection method between the bracket foot and the leading edge shell or the trailing edge shell, Design bracket foot structure;

S9. Based on the integral value of the load component projected along the blade flapping direction of the leading edge shell or trailing edge shell of each blade segment, as well as the mechanical connection design of the leading edge shell or trailing edge shell and the bracket foot, design each segment The flanging structure of the leading edge shell or trailing edge shell of each blade segment; the leading edge of each blade segment is designed based on the integral value of the load component projected along the blade oscillation direction of the combined load on the leading edge shell or trailing edge shell of each segment of the blade. Shell or trailing edge shell flange corner reinforcement structure;

S10. Assemble the split-bin spliced blades, and optimize the blade weight and cost according to the split-bin spliced blade structure.

The beneficial effects of the present invention are as follows:

1. A divided-bin splicing type blade structure of the present invention effectively realizes the function of blade divided-bin and segmented connection. Through the buffer connection device, each blade section is connected to form a complete aerodynamic shape, which reduces the manufacturing difficulty of the overall vacuum suction of the blade. Reduce the difficulty of design and construction of complete cross-section connections of blades, and reduce the difficulty of road transportation protection and on-site construction and hoisting.

2. A divided-bucket spliced blade structure of the present invention reduces the impact of the connection design on the natural frequency characteristics of the blades and reduces the impact of the blades on the dynamic performance of the entire machine by arranging the connection design with additional concentrated mass in the main load-bearing structure area. .

3. The invention's split-bin spliced blade structure effectively avoids the influence of load transmission in the non-main load-bearing structural area at the connection position, reduces the possibility of load transmission at the connection position causing failure of the new blade structure, and reduces the difficulty of blade design.

4. A divided-bin spliced blade structure of the present invention ensures the safety and reliability of the connection structure by separately designing the transmission paths for different components of load at the connection position, reduces the failure probability of the connection structure, and reduces the maintenance frequency and frequency during operation. cost.

5. The invention's divided-bin spliced blade structure can effectively absorb the vibration of the blade structure, reduce the fatigue load during unit operation, and improve the overall safety of the blade.

6. The invention's divided-bin splicing type blade structure effectively realizes the division of the blade structure area into bins, physically limits the expansion range of local defects or damage within this bin section, and avoids the accumulation of local damage that affects the overall blade safety. , improve the overall ability of the blade to resist damage.

7. The invention's compartment-splicing blade structure effectively converts blade maintenance work into partial compartment replacement work, saves on-site construction time and costs, improves construction quality in outdoor environments, and ensures the safety of construction workers.

8. A divided-bin splicing type blade structure of the present invention. By dividing the blade structure area into bins and segments, the same type of blades can share components and brackets at different spanwise positions, and different types of blades can share components and trailing edge shells at similar parts. body), effectively forming a material library for blade structural elements, and taking advantage of batch manufacturing to save blade mold investment, manpower and material resources, and shorten the manufacturing cycle and cost.

9. The invention's compartment spliced blade structure effectively distinguishes the main failure modes of the structural design of different compartments. Through the classification and screening of dominant influencing factors, it is easy to complete the iterative work of the simplified design method and achieve the depth of the local structure. Optimize and even meet the enhancement needs under special conditions.

Description of the drawings

The description and drawings that constitute a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the attached picture:

Figure 1 is a schematic structural diagram of an embodiment of a divided-bin splicing blade structure of the present invention.

Figure 2 is a schematic structural assembly diagram of an embodiment of a split-bin splicing blade structure of the present invention.

Figure 3 is a partial detailed view of the axial structure assembly of an embodiment of the split-bin splicing blade structure of the present invention.

Figure 4 is a partial detailed view of the radial structure assembly of an embodiment of the split-bin splicing blade structure of the present invention.

Figure 5 is a schematic structural assembly diagram of another embodiment of a divided-bin splicing blade structure of the present invention.

Figure 6 is a partial detailed view of the axial structure assembly of another embodiment of a divided-bin splicing blade structure of the present invention.

Figure 7 is a partial detailed view of the radial structure assembly of another embodiment of a split-bin spliced blade structure of the present invention.

Among them: 1-main beam, 11-main beam on the windward side, 12-main beam on the leeward side, 2-conforming bracket, 3-bracket foot, 31-bracket foot first side, 32-bracket foot second side, 33- The bracket is on the third side, 4-mechanical connector, 5-leading edge housing, 6-trailing edge housing, 7-blade root, 8-blade tip.

Detailed ways

The present invention will be described in detail below with reference to the accompanying drawings and embodiments. It should be noted that, as long as there is no conflict, the embodiments and features in the embodiments of this application can be combined with each other.

The following detailed description is an exemplary description and is intended to provide further detailed description of the present invention. Unless otherwise specified, all technical terms used in the present invention have the same meanings as commonly understood by those of ordinary skill in the art to which this application belongs. The terminology used in the present invention is for the purpose of describing specific embodiments only and is not intended to limit the exemplary embodiments according to the present invention.

An embodiment as shown in Figure 1 provides a split-bucket spliced blade structure, including a main beam 1, a leading edge shell 5, a trailing edge shell 6, a blade tip 8 and a blade root 7. The main beam 1 It includes a main beam 11 on the windward side and a main beam 12 on the leeward side. The main beam 11 on the windward side and the main beam 12 on the leeward side are arranged up and down respectively; the leading edge shell 5 is installed on the first side end face of the main beam 1; the leading edge shell 5 is Curved shell structure; the trailing edge shell 6 is a curved shell structure and is installed on the second side end surface of the main beam 1. The trailing edge shell 6, the main beam 1 and the leading edge shell 5 form a complete airfoil shape; the blade tip 8 It is a variable cross-section tip shell structure, and the blade tip 8 is installed on the first end of the main beam 1; the blade root 7 is a cylindrical structure along the blade span, and the blade root 7 is installed on the second end of the main beam 1.

Main beam 1, leading edge shell 5, trailing edge shell 6, blade tip 8 and blade root 7 form the aerodynamic shape of the complete blade. Main beam 1 and blade root 7 can be connected by vacuum injection molding; main beam 1 The blade tip 8 can be connected by adhesive bonding. The main beam 1 and the leading edge shell 5, and the main beam 1 and the trailing edge shell 6 can be connected by mechanical connectors 4. The main beam on the windward side is located above the fan blade. The main beam 1 on the leeward side is the main beam 1 located below the fan blade. The function of the main beam 1 is to transfer the load of the blade to the blade root 7.

The structural form of the blade root 7 can be a cylindrical structure with the axis direction along the span of the blade, connecting the blade and the pitch bearing or hub; its function is to transfer the load of the blade to the pitch bearing or hub.

The structure of the blade tip 8 can be a variable cross-section tip shell structure, which can be equipped with a blade tip 8 air-termination device; it functions as a complete blade aerodynamic shape and provides a lightning induction position at the far end of the blade. The blade tip 8 is installed on the third side of the main beam 1. One end can be connected by adhesive bonding.

The structural form of the front edge shell 5 can be a curved shell structure, which is arranged on the front edge side of the main beam 1. The front edge side is the side for installing the front edge shell 5, and is connected with the main beam 1 and the rear edge. The shell 6 forms a complete airfoil shape; its function is to ensure the aerodynamic shape and bear the load at the leading edge of the blade.

The structure of the trailing edge shell 6 is a curved shell structure, which is arranged on the trailing edge side of the main beam 1. The trailing edge side is the side for installing the trailing edge shell 6, and is connected with the main beam 1 and the front edge shell. 5 form a complete airfoil shape; its function is to ensure the aerodynamic shape and bear the load at the trailing edge of the blade.

As shown in Figures 2 to 7, as a preferred example, a buffer connection device is also included. The buffer connection device is installed between the main beam on the windward side and the main beam on the leeward side. The main beam 1 is composed of multiple sets of buffer connection devices. Variable cross-section beam structure with fixed relative positions.

As shown in Figure 2, Figure 3 and Figure 4, as a specific example, the buffer connection device can include a conformable bracket 2 and a bracket foot 3. There are two bracket feet 3, and the structural form is a bent plane. Structure, the cross-section is "L" shaped, connected to the inner surface of the main beam 1, the end of the conformal bracket 2, the flange of the leading edge shell 5 or the flange of the trailing edge shell 6; its function is to maintain the blade assembly shape and transmit Blade load, the first side 31 of the bracket foot is connected to the inner surface of the main beam 1. Specifically, adhesive bonding or screw assembly can be used to connect. The second side 32 of the bracket foot is fixedly connected to both ends of the conformable bracket 2. Specifically, it can be connected by adhesive bonding or screw assembly. The mechanical connector 4 connects or assembles the connection, and the mechanical connector 4 can be a rivet; it functions to constrain the degree of freedom of the connection structure and transmit the shear load.

As a specific example of the above embodiment, a reinforcing structure is provided at the corner position of the flange for constraining the corner stiffness, and the reinforcing structure may be a reinforcing rib.

As shown in Figures 2, 3 and 4, as a specific example, the conformable bracket 2 can be composed of a spring and damper system in a broad sense. The structural form is a generalized spring-damper system structure, with a spring part and a damping part. It can be connected in series or parallel; it functions to support the relative position of the main beam 1, transmit shear load, and absorb blade vibration.

As shown in Figures 5, 6 and 7, as another specific example, the conformable bracket 2 includes a cross beam and a cross connector. The intersection positions of the cross beams are connected through the cross connector, and the cross connector is used to constrain the deformation of the cross beam. , the angle between the cross beams can change with the support height, and serves to support the relative position of the main beam 1 and transmit the shear load.

Specifically, the cross-connecting member may be a rivet, the cross-connecting member may be a mechanical connecting member, and the cross-beam may be two cross-bar-shaped beams.

As a preferred example, the leading edge shell 5 and the trailing edge shell 6 are divided into several segments along the blade span direction, and each segment corresponds to a set of buffer connection devices; each segment of the leading edge shell 5 or the trailing edge shell 6 A flange is provided on the edge adjacent to the main beam 1, and the flange is fixedly connected to the third side 33 of the bracket foot. Specifically, the flange and the third side 33 of the bracket foot are connected or assembled through a mechanical connector 4, and the mechanical connector 4 can be a bolt or a rivet.

A design method for divided-bin splicing blades, including:

S1. Establish a load calculation model based on the aerodynamic shape of the blade to calculate the envelope distribution of load components in each section of the blade span, as well as the circumferential position pressure distribution in each section of the blade span;

S2. Based on the envelope distribution results of the load components of each section and the 7-node diameter of the blade root, use the traditional blade structure design method to design the initial structure of the traditional blade;

S3. Based on the main beam 1 and the inner and outer skins designed based on the traditional blade initial structure, the main beam 1 of the blade structure is designed through stiffness equivalent conversion; the blade root 7 is designed based on the traditional blade initial structure, and the blade is designed through stiffness equivalent conversion. The blade root 7 of the structure; the blade tip 8 designed based on the traditional blade initial structure. After stiffness equivalent conversion, the blade tip 8 of the blade structure is designed; the leading edge, near-leading edge core material and inner and outer skins are designed based on the traditional blade initial structure. After stiffness equivalent conversion, the leading edge shell 5 of the blade structure is designed; based on the traditional blade initial structure design of the trailing edge, near trailing edge core material, trailing edge beam and inner and outer skin, etc., through stiffness equivalent conversion, the blade structure is designed The trailing edge housing 6;

S4. According to the pressure distribution results at the circumferential position within each section, integrate along the surface of the blade leading edge shell 5 or trailing edge shell 6 to obtain the aerodynamic load on the leading edge shell 5 or trailing edge shell 6 at each section position; Combine aerodynamic loads and gravity loads, etc., calculate the load component values projected along the flapping and oscillation directions of the blades of the corresponding cross-section, and obtain the corresponding load component distribution;

S5. According to the load component distribution of the combined load on the leading edge shell 5 or the trailing edge shell 6 at each cross-sectional position projected along the blade flapping direction, integrate along the blade span direction to obtain the corresponding load component integral value; according to the settings For the load component threshold, divide the leading edge shell 5 or the trailing edge shell 6 into several segments along the blade span direction to ensure that the integral value of the load component corresponding to each segment is not greater than the set load component threshold;

S6. Each section of the blade leading edge shell 5 or trailing edge shell 6 corresponds to a set of buffer connection devices; in the corresponding blade span area, the shear web designed according to the traditional blade initial structure is equivalently converted in stiffness. Design the conformable bracket 2 of the blade structure; design the natural frequency of the conformable bracket 2 to be equal to the blade operating vibration frequency; calculate the load value of the corresponding conformable bracket 2;

S7. Design the mechanical structure of the leading edge shell 5 or trailing edge shell 6 and the bracket 3 based on the integral value of the load component projected along the blade flapping direction of the combined load on each blade segment. Connection; according to the load value of the conformable bracket 2 of the corresponding buffer connection device, design the mechanical connection of the conformable bracket 2 and the bracket foot 3; according to the deformation matching relationship between the main beam 1 and the corresponding splicing device, design the adhesive bonding or screws Assembly connection;

S8. Based on the relative position of the main beam 1 in the corresponding blade spanwise area, design the angle between the bending planes of the bracket foot 3; design the structure of the bracket foot 3 based on the connections related to the bracket foot 3 involved in the seventh step;

S9. According to the integral value of the load component projected along the blade flapping direction of the combined load on each blade section's leading edge shell 5 or trailing edge shell 6, as well as the mechanical relationship between the leading edge shell 5 or trailing edge shell 6 and the bracket foot 3 Connection design, design the flanging structure of the leading edge shell 5 or trailing edge shell 6 of each blade section; according to the load component projected along the blade oscillation direction according to the combined load of each blade leading edge shell 5 or trailing edge shell 6 Based on the integral value, design the flange corner reinforcement structure of the leading edge shell 5 or trailing edge shell 6 of each blade section;

S10. Assemble the split-bin spliced blades, and optimize the blade weight and cost according to the split-bin spliced blade structure.

Optimize blade weight and cost based on actual application.

It is known from common technical knowledge that the present invention can be implemented by other embodiments without departing from its spirit or essential characteristics. Therefore, the above-disclosed embodiments are in all respects illustrative and not exclusive. All changes within the scope of the present invention or within the scope equivalent to the present invention are included in the present invention.

Claims (10)

1. A divided-bin splicing blade structure, which is characterized by including: main beam(1); Leading edge housing (5), the leading edge housing (5) is installed on the first side end surface of the main beam (1); the leading edge housing (5) is a curved surface housing structure; The trailing edge shell (6) is a curved shell structure and is installed on the second side end surface of the main beam (1). The trailing edge shell (6) is connected with the main beam (1) and the front edge shell. The body (5) forms a complete airfoil shape; Blade tip (8), the blade tip (8) is a variable cross-section tip shell structure, and the blade tip (8) is installed on the first end of the main beam (1); Blade root (7), the blade root (7) is a cylindrical structure along the blade span, and the blade root (7) is installed on the second end of the main beam (1). 2. A compartment splicing type blade structure according to claim 1, characterized in that it also includes a buffer connection device, and multiple sets of the buffer connection devices are installed on the windward side main beam and the leeward side main beam. between. 3. A compartment splicing blade structure according to claim 2, characterized in that the buffer connection device includes a conformable bracket (2) and a bracket foot (3), and the bracket foot (3) has Two, the bracket foot (3) is a bending plane, the first side (31) of the bracket foot is connected to the inner surface of the main beam (1), and the second side (32) of the bracket foot is connected to the inner surface of the main beam (1). The two ends of the conformable bracket (2) are fixedly connected respectively. 4. A compartment splicing blade structure according to claim 3, characterized in that the conformable bracket (2) is composed of a spring damper system. 5. A compartment splicing type blade structure according to claim 3, characterized in that the conformable bracket (2) includes a cross beam and a cross connector, and the intersection position of the cross beam passes through the cross connector. Turn the connection. 6. A divided-bin splicing blade structure according to claim 3, characterized in that the leading edge housing (5) and the trailing edge housing (6) are divided into several sections along the blade span direction. , each section corresponds to a set of buffer connection devices; the front edge shell (5) or the trailing edge shell (6) of each section is provided with a flange on the edge adjacent to the main beam (1) , the flange is fixedly connected to the third side (33) of the bracket foot. 7. A compartment splicing type blade structure according to claim 6, characterized in that the flange and the third side (33) of the bracket foot are connected or assembled through a mechanical connector (4). 8. A compartment splicing type blade structure according to claim 1, characterized in that the main beam (1) and the blade root (7) are connected by vacuum injection molding; the main beam (1) Connect to the blade tip (8) by adhesive bonding. 9. A compartment splicing type blade structure according to claim 6, characterized in that a reinforcing structure is provided at the corner position of the flange for adjusting the corner stiffness. 10. A design method for split-bin splicing blades, which is characterized by including: S1. Establish a load calculation model based on the aerodynamic shape of the blade to calculate the envelope distribution of load components in each section of the blade span, as well as the circumferential position pressure distribution in each section of the blade span; S2. Based on the envelope distribution results of the load components of each section and the pitch circle diameter of the blade root (7), use the traditional blade structure design method to design the initial structure of the traditional blade; S3. Based on the traditional blade, through stiffness equivalent conversion, design the main beam (1), blade root (7), blade tip (8), leading edge shell (5), and trailing edge shell (6) of the blade structure; S4. Calculate based on the pressure distribution results at the circumferential position in each section to obtain the aerodynamic load on the leading edge shell (5) or trailing edge shell (6) at each section position; combine the aerodynamic load and gravity load to calculate the total load along the The corresponding load component distribution is obtained by projecting the load component values in the flapping direction and oscillation direction of the corresponding cross-section blade; S5. Set the load component threshold, divide the leading edge shell (5) or trailing edge shell (6) into several segments along the blade span direction, and the corresponding load component integral value of each segment is not greater than the set load component threshold; S6. Each blade leading edge shell (5) or trailing edge shell (6) corresponds to a set of buffer connection devices. Design the conformal bracket (2) of the blade structure; design the conformal bracket (2) to match the natural frequency of the blade. The operating vibration frequencies are equal; S7. Design the leading edge shell (5) or trailing edge shell (6) according to the integral value of the load component projected along the blade flapping direction of the combined load on each blade section. 6) The connection method with the bracket foot (3); according to the load value of the conformable bracket (2) of the corresponding buffer connection device, design the connection method between the conformable bracket (2) and the bracket foot (3); S8. Based on the relative position of the main beam (1) in the corresponding blade span area, design the angle between the bending planes of the bracket foot (3); according to the connection method between the bracket foot (3) and the conformal bracket (2) and the bracket foot (3) ) is connected to the leading edge shell (5) or the trailing edge shell (6), and the bracket foot (3) structure is designed; S9. According to the integral value of the load component projected along the blade flapping direction of the combined load on the leading edge shell (5) or trailing edge shell (6) of each blade section, and the leading edge shell (5) or trailing edge shell ( 6) Design the mechanical connection with the bracket foot (3), and design the flanging structure of the leading edge shell (5) or trailing edge shell (6) of each blade section; according to the leading edge shell (5) or trailing edge of each blade section Based on the integral value of the load component projected along the blade oscillation direction of the combined load on the casing (6), design the flange corner reinforcement structure of the leading edge casing (5) or trailing edge casing (6) of each blade segment; S10. Assemble the split-bin spliced blades, and optimize the blade weight and cost according to the split-bin spliced blade structure.