Combined material blade and design method thereof

Abstract

The invention provides a combined material blade and a design method thereof, and the design method comprises the steps: S1, carrying out the analysis of the vibration characteristics of the blade, and determining the inherent frequency order and vibration mode of possible dangerous resonance; s2, determining the direction in which the frequency needs to be adjusted; s3, according to the characteristics of the available material, analyzing the geometric position of the material needing to be locally replaced and the trend of blade frequency change possibly caused by material replacement, and determining a blade material for replacement; s4, carrying out detailed inherent frequency checking on the structure of the combined material blade formed by adopting the determined replacement material; and S5, designing a material combination scheme and a blade structure scheme which meet the frequency requirement. The structure frequency adjustment can be realized under the condition that the pneumatic airfoil is not changed, so that the optimal pneumatic performance design is ensured, and the working efficiency of parts is improved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a composite material blade and its design method. Background Technology

[0002] Aircraft engine blades are the main working parts of aircraft engines. Blades are usually components with a certain airfoil, arranged evenly along the circumference in the main flow channel of the impeller, used to convert gas energy or guide the direction of airflow.

[0003] Aero-engine blades are subjected to complex alternating vibration stresses during operation. If the magnitude of the vibration stress exceeds the corresponding fatigue limit, fatigue cracks will appear in the blades within their design life, often leading to fatigue fracture within a short period, severely impacting the safety of the aero-engine. Therefore, during the product design phase, frequency tuning design is necessary to avoid dangerous resonance points from the main operating speed range, preventing the blades from exceeding vibration stress limits due to resonance, thereby avoiding blade fracture due to high-cycle fatigue.

[0004] Except for some blades with internal cavities, most blades of aero engines are solid blades. The frequency tuning design of blades is generally achieved by adjusting blade size, mass distribution, etc. The initial airfoil of the blade is designed for optimal aerodynamic performance. If frequency tuning is carried out only from the perspective of structural optimization, it will inevitably lead to the aerodynamic airfoil deviating from the optimal solution, thereby causing performance loss. In the design, the contradiction between performance and safety requirements is often encountered.

[0005] In view of this, the inventors of this application have designed a composite material blade and its design method to overcome the aforementioned technical problems. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the defect in the design of existing aero-engine blades where it is often difficult to balance performance and safety requirements, and to provide a composite material blade and its design method.

[0007] The present invention solves the above-mentioned technical problems through the following technical solution:

[0008] This invention provides a design method for composite material blades, characterized by the following steps: S1, conducting blade vibration characteristic analysis to determine the natural frequency order and mode shape that may cause dangerous resonance; S2, determining the direction in which the frequency needs to be adjusted; S3, based on the characteristics of available materials, analyzing the geometric location of materials that need to be replaced locally, and the trend of blade frequency changes that may result from the replacement materials, and determining the replacement blade material; S4, conducting detailed natural frequency verification on the structure of the composite material blade formed using the determined replacement materials; S5, designing a material combination scheme and blade structure scheme that meet the frequency requirements.

[0009] According to one or more embodiments of the present invention, the vibration modes of the blade include: bending vibration mode, torsional vibration mode, chordal vibration mode, and composite vibration mode.

[0010] According to one or more embodiments of the present invention, the relationship between the natural frequency of the blade structure and the elastic modulus and density of the blade material is as follows: Where ω is the natural frequency; E is the elastic modulus of the blade material; is the density of the blade material; k is a coefficient; in step S3, let a be the original blade material and b be the replacement blade material; E a ρ represents the elastic modulus of the original blade material. a E represents the density of the original blade material. b ρ represents the elastic modulus of the replacement blade material. b This indicates the density of the replacement blade material; if it is necessary to increase the blade frequency, then... If it is necessary to reduce the blade frequency, then

[0011] The present invention also provides a composite material blade, characterized in that the composite material blade is designed using the composite material blade design method described above, the composite material includes at least two different materials, the blade structures of the various different materials are interconnected to form the whole blade, the connection between the various different materials has a transition area, and the various different materials permeate each other in the transition area.

[0012] According to one or more embodiments of the present invention, the composite material includes a first material and a second material, the blade structure of the first material and the blade structure of the second material are interconnected to form an integral blade, and the connection between the first material and the second material has a transition region in which the first material and the second material permeate each other.

[0013] According to one or more embodiments of the present invention, the material of the upper structure of the composite material blade body is a first material, and the material of the lower part of the composite material blade body and the tenon structure is a second material.

[0014] According to one or more embodiments of the present invention, the material on the left side of the composite material blade in the axial direction is a first material, and the material on the right side of the composite material blade in the axial direction is a second material.

[0015] According to one or more embodiments of the present invention, the material at the root bending mode nodal line of the composite material blade is a first material, and the material at the remaining positions of the composite material blade is a second material.

[0016] According to one or more embodiments of the present invention, the material at the mid-axial nodal line position of the composite material blade is a first material, and the material at the remaining positions of the composite material blade is a second material.

[0017] According to one or more embodiments of the present invention, the composite material blade is a guide blade, the material of the upper structure and the upper outer ring structure of the guide blade is a first material, and the material of the lower part of the guide blade and the lower inner ring structure is a second material.

[0018] According to one or more embodiments of the present invention, the composite material includes three different materials and a third material; the upper part of the blade of the composite material is the first material, the middle part of the blade of the composite material is the second material, and the lower part of the blade of the composite material and the tenon structure are the third material.

[0019] According to one or more embodiments of the present invention, the composite material blade is manufactured by additive manufacturing or welding.

[0020] The positive and progressive effects of this invention are as follows:

[0021] The composite material blade and its design method of the present invention have at least the following advantages:

[0022] The composite material blade and its design method of the present invention can achieve structural frequency adjustment while keeping the aerodynamic airfoil unchanged, thereby ensuring optimal aerodynamic performance design and improving component working efficiency.

[0023] This invention combines the vibration characteristics of blade structures with existing processing and manufacturing capabilities, and utilizes different material combinations to provide a composite material blade design method. By designing and manufacturing blades using this invention's design method, it is possible to change the specific order resonant frequency of the blade structure by altering its local stiffness and weight, thereby achieving the goal of avoiding the main operating speed range by changing the natural frequency.

[0024] The composite material blade of this invention can simultaneously meet the vibration fatigue design requirements while ensuring the optimal aerodynamic performance of the blade airfoil, thus solving the problem of balancing transmission aerodynamic performance and safety requirements, and making a beneficial contribution to improving engine efficiency. Attached Figure Description

[0025] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features, wherein:

[0026] Figure 1a This is a schematic diagram of the bending mode in a typical compressor blade vibration mode.

[0027] Figure 1bThis is a schematic diagram of the torsional vibration mode in a typical compressor blade.

[0028] Figure 1c This is a schematic diagram of the chordal vibration mode in a typical compressor blade.

[0029] Figure 1d This is a schematic diagram of a composite vibration mode in a typical compressor blade.

[0030] Figure 2 This is a schematic diagram of the rotor blade vibration characteristic analysis results in step S1 of embodiment 1 of the composite material blade design method of the present invention.

[0031] Figure 3a This is a schematic diagram of the material distribution in the first scheme of the composite material blade design method of the present invention.

[0032] Figure 3b This is a schematic diagram of the frequency analysis results of the first scheme in step S4 of embodiment 1 of the composite material blade design method of the present invention.

[0033] Figure 4a This is a schematic diagram of the material distribution in the second scheme of the composite material blade design method of the present invention, in embodiment 1.

[0034] Figure 4b This is a schematic diagram of the frequency analysis results of the second scheme in step S4 of embodiment 1 of the composite material blade design method of the present invention.

[0035] Figure 5 This is a schematic diagram of the rotor blade vibration characteristic analysis results in step S1 of embodiment 2 of the composite material blade design method of the present invention.

[0036] Figure 6a This is a schematic diagram of the material distribution in the first scheme of the combined material blade design method embodiment 2 of the present invention.

[0037] Figure 6b This is a schematic diagram of the frequency analysis results of the first scheme in step S4 of embodiment 2 of the composite material blade design method of the present invention.

[0038] Figure 7a This is a schematic diagram of the material distribution in the second scheme of the combined material blade design method of the present invention, in embodiment 2.

[0039] Figure 7b This is a schematic diagram of the frequency analysis results of the second scheme in step S4 of embodiment 2 of the composite material blade design method of the present invention.

[0040] Figure 8 This is a schematic diagram of the blade structure of one embodiment of the composite material blade of the present invention.

[0041] Figure 9yes Figure 8 Enlarged schematic diagram of part A.

[0042] Figure 10 This is a schematic diagram of the blade structure of another embodiment of the composite material blade of the present invention.

[0043] Figure 11 This is a schematic diagram of the blade structure of another embodiment of the composite material blade of the present invention.

[0044] Figure 12 This is a schematic diagram of the blade structure of another embodiment of the composite material blade of the present invention. Detailed Implementation

[0045] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0046] Embodiments of the invention will now be described in detail with reference to the accompanying drawings. Preferred embodiments of the invention will now be described in detail, examples of which are illustrated in the drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts. Furthermore, although the terminology used herein is selected from commonly known and used terminology, some terms mentioned in this specification may have been chosen by the applicant at his or her discretion, and their detailed meanings are explained in the relevant sections of the description herein. Moreover, the invention should be understood not only by the actual terms used, but also by the meaning implied by each term.

[0047] This invention provides a method for designing composite material blades, characterized in that the design method includes the following steps:

[0048] Step S1: Conduct blade vibration characteristic analysis to determine the natural frequency order and mode shape that may cause dangerous resonance;

[0049] Step S2: Determine the direction in which the frequency needs to be adjusted;

[0050] Step S3: Based on the characteristics of available materials, analyze the geometric location where materials need to be replaced locally, and the trend of blade frequency change that may result from material replacement, and determine the blade material to be replaced.

[0051] Step S4: Conduct a detailed verification of the natural frequencies of the composite material blades formed using the determined replacement materials;

[0052] Step S5: Design a material combination scheme and blade structure scheme that meet the frequency requirements.

[0053] The composite material blades, after the design is completed, are then manufactured and processed using additive manufacturing or welding methods. Preferably, the processed composite material blades have a transition region 300 at the junction of different materials, in which the different materials interpenetrate, such as... Figure 9 As shown, this ensures a secure connection of the cross-sections.

[0054] It should be noted that the composite material is a raw material composed of two or more materials, each of which retains its original properties, and the various materials are tightly connected through interfaces; the frequency refers to the number of times the blade structure undergoes periodic vibration per unit time when resonance occurs.

[0055] It should be noted that step S2 requires determining the direction of frequency adjustment based on the complexity of the design, including increasing or decreasing the frequency.

[0056] It should be noted that step S3 requires analyzing the geometric location of the material to be replaced locally, and the trend of blade frequency change that may result from the replacement of the material, based on the elastic modulus and density of the available material.

[0057] It should be noted that step S4 involves a detailed verification of the natural frequency of the blade structure formed by the initially determined beneficial combination of materials.

[0058] It should be noted that the material combination scheme and blade structure scheme that meet the frequency requirements in step S5 include several typical schemes, the structures of which are as follows: Figure 8 , Figure 10 , Figure 11 and Figure 12 As shown.

[0059] The present invention relates to a composite material blade design method. By combining the vibration characteristics of the blade structure, different materials are used to design the blade. By changing the local stiffness and weight of the blade structure, the specific order resonant frequency of the blade is changed, so as to achieve the target value of the specific order frequency of the blade, thereby achieving the purpose of avoiding the main operating speed range of the natural frequency.

[0060] like Figures 1a to 1d As shown, in a preferred embodiment of the composite material blade design method of the present invention, the vibration modes of the blade include: bending vibration mode, torsional vibration mode, chordal vibration mode, and composite vibration mode.

[0061] It should be noted that, Figures 1a to 1d This is a schematic diagram of a typical compressor blade vibration mode, with bending vibration modes as follows: Figure 1a As shown, the torsional vibration mode is as follows Figure 1b As shown, the chordal vibration mode is as follows Figure 1c As shown, the composite vibration mode is as follows Figure 1d As shown.

[0062] As a preferred embodiment of the composite material blade design method of the present invention, the relationship between the natural frequency of the blade structure and the elastic modulus and density of the blade material is as follows:

[0063] Where ω is the natural frequency; E is the elastic modulus of the blade material; ρ is the density of the blade material; and k is a coefficient.

[0064] In step S3, let a be the original blade material and b be the replacement blade material; E a ρ represents the elastic modulus of the original blade material. a E represents the density of the original blade material. b This indicates the elastic modulus of the replacement blade material. b Indicates the density of the replacement blade material;

[0065] If it is necessary to increase the blade frequency, then If it is necessary to reduce the blade frequency, then

[0066] It should be noted that engine blades are generally cantilever beam structures, based on the relationship between the structure's natural frequency and the elastic modulus and density of its material. If the blade frequency needs to be increased, the new replacement material E / needs to be larger than the original material; if the frequency needs to be reduced, the opposite is true.

[0067] It should be noted that the frequency is not only positively correlated with the magnitude of E / , but also related to the material distribution.

[0068] The present invention provides two specific embodiments of a composite material blade design method, as described below:

[0069] Example 1

[0070] According to step S1, the vibration characteristic analysis results of a typical rotor blade show that its natural frequency at which dangerous resonance may occur is f1, which is a first-order bending mode shape, as shown in the figure. Figure 2 As shown in the blade Campbell diagram, the frequency margin is 2.2% under 19E harmonic excitation.

[0071] According to step S2, analysis shows that, with the excitation frequency unchanged, the dangerous resonance point can be avoided by reducing the frequency of the bending mode.

[0072] Following step S3, an attempt was made to reduce the first-order bending frequency of the blade by decreasing the material elastic modulus at the nodal line of the bending mode shape at the blade root. Two blade frequency verifications were conducted for two combined material blade configuration schemes. The two schemes have the same structural form, differing only in the proportion of material components. The material distribution of the first scheme is as follows: Figure 3a As shown, the material distribution of the second scheme is as follows: Figure 4aAs shown, the material includes a first material 100 and a second material 200, and the elastic modulus of the second material 200 is lower than that of the first material 100.

[0073] Preferably, the first material 100 can be titanium alloy TC4, which has an elastic modulus of 109 and a density of 4.2; the second material 200 can be aluminum alloy 2A16, which has an elastic modulus of 76 and a density of 2.75.

[0074] As can be seen from the above calculations, the frequency is not only positively correlated with the magnitude of E / ρ, but also related to the material distribution. Following step S4, the verification results for the first scheme are as follows: Figure 3b As shown in the Campbell diagram of the blades, the verification results for the second scheme described above are as follows: Figure 4b The blade is shown in the Campbell diagram.

[0075] The analysis results above show that the first scheme has a better frequency modulation effect. Therefore, unless there are other restrictions, in step S5, the blade configuration determined by the first combination material scheme can be selected to design the blade structure.

[0076] After the design is completed, blade processing will be carried out according to the final determined blade material combination configuration.

[0077] Example 2

[0078] According to step S1, the vibration characteristic analysis results of a typical rotor blade show that its natural frequency at which dangerous resonance may occur is f2, which is a first-order torsional mode shape, as shown in the figure. Figure 5 As shown in the blade Campbell diagram, the frequency margin is 1.9% under 32E frequency doubling excitation.

[0079] According to step S2, analysis shows that, with the excitation frequency unchanged, the dangerous resonance point can be avoided by reducing the frequency of the torsional mode.

[0080] Following step S3, an attempt was made to reduce the first-order torsional frequency of the blade by decreasing the material elastic modulus at the mid-node position along the blade's axial direction. Frequency verification was conducted for two blade configurations with combined materials. The two schemes have the same structural form, differing only in the proportion of material components. The material distribution of the first scheme is as follows... Figure 6a As shown, the material distribution of the second scheme is as follows: Figure 7a As shown, the material includes a first material 100 and a second material 200, and the elastic modulus of the second material 200 is lower than that of the first material 100.

[0081] Preferably, the first material 100 can be titanium alloy TC4, which has an elastic modulus of 109 and a density of 4.2; the second material 200 can be aluminum alloy 2A16, which has an elastic modulus of 76 and a density of 2.75.

[0082] As can be seen from the above calculations, the frequency is not only positively correlated with the magnitude of E / ρ, but also related to the material distribution.

[0083] According to step S4, the verification result of the first scheme is as follows: Figure 6b As shown in the Campbell diagram of the blades, the verification results for the second scheme described above are as follows: Figure 7b The blade is shown in the Campbell diagram.

[0084] The analysis results above show that the first scheme has a better frequency modulation effect. Therefore, unless there are other restrictions, in step S5, the blade configuration determined by the first combination material scheme can be selected to design the blade structure.

[0085] After the design is completed, blade processing will be carried out according to the final determined blade material combination configuration.

[0086] In the existing engine blade design process, when a blade designed according to the optimal aerodynamic performance requirements is found to have resonance problems after vibration characteristic evaluation, frequency tuning design is required. However, for a solid blade model, frequency tuning can only adjust the blade's external dimensions, which often leads to a reduction in aerodynamic performance.

[0087] The present invention provides a composite material blade design method that achieves structural frequency adjustment while keeping the aerodynamic airfoil unchanged, thereby ensuring optimal aerodynamic performance design and improving component working efficiency.

[0088] like Figures 8-12 As shown, the present invention also provides a composite material blade, which is designed using the composite material blade design method described above. The composite material includes at least two different materials, and the blade structures of the various different materials are interconnected to form the whole blade. The connection between the various different materials has a transition area, and the various different materials permeate each other in the transition area.

[0089] It should be noted that the blade structures of various different materials are interconnected to form the whole blade, and there are transition areas at the joints of the different materials. In these transition areas, the different materials should be able to permeate each other to improve the reliability of the working performance.

[0090] like Figures 8-12 As shown, in a preferred embodiment of the composite material blade of the present invention, the composite material includes a first material 100 and a second material 200. The blade structure of the first material 100 and the blade structure of the second material 200 are connected to each other to form the whole blade. The connection between the first material 100 and the second material 200 has a transition region 300, in which different materials permeate each other.

[0091] Preferably, the first material 100 and the second material 200 can be metal or non-metal, depending on the application requirements and processing maturity. The two materials permeate each other in the transition area 300 so as to form a firm connection. They can be manufactured by methods including but not limited to welding, additive manufacturing, etc.

[0092] like Figure 9 As shown, Figure 8 The enlarged structural diagram of part A of the transition area 300 between the two materials shows that there is a transition area 300 between the material of the upper structure of the blade and the material of the lower part of the blade and the tenon structure. In the transition area 300, the two materials permeate each other to ensure effective connection.

[0093] like Figure 8 As shown, in a preferred embodiment of the composite material blade of the present invention, the material of the upper structure of the composite material blade body is the first material 100, and the material of the lower part of the composite material blade body and the tenon structure is the second material 200.

[0094] like Figure 11 As shown, in a preferred embodiment of the composite material blade of the present invention, the material on the left side of the composite material blade in the axial direction is the first material 100, and the material on the right side of the composite material blade in the axial direction is the second material 200.

[0095] like Figure 3a and Figure 4a As shown, in a preferred embodiment of the composite material blade of the present invention, the material at the bending vibration mode nodal line position at the root of the composite material blade is the first material 100, and the material at the remaining positions of the composite material blade is the second material 200.

[0096] like Figure 7a As shown, in a preferred embodiment of the composite material blade of the present invention, the material at the mid-axial nodal line position of the composite material blade is the first material 100, and the material at the remaining positions of the composite material blade is the second material 200.

[0097] like Figure 10 As shown, in a preferred embodiment of the composite material blade of the present invention, the composite material blade is a guide blade, the material of the upper structure and the upper outer ring structure of the guide blade is a first material 100, and the material of the lower part of the guide blade and the lower inner ring structure is a second material 200.

[0098] like Figure 12 As shown, in a preferred embodiment of the composite material blade of the present invention, the composite material includes three different materials and also includes a third material;

[0099] The upper part of the blade body of the composite material blade is made of the first material 100, the middle part of the blade body of the composite material blade is made of the second material 200, and the lower part of the blade body and the tenon structure of the composite material blade are made of the third material.

[0100] In a preferred embodiment of the composite material blade of the present invention, the composite material blade is manufactured by additive manufacturing or welding.

[0101] In summary, the composite material blade and its design method of the present invention can achieve structural frequency adjustment while keeping the aerodynamic airfoil unchanged, thereby ensuring optimal aerodynamic performance design and improving component working efficiency.

[0102] This invention combines the vibration characteristics of blade structures with existing processing and manufacturing capabilities, and utilizes different material combinations to provide a composite material blade design method. By designing and manufacturing blades using this invention's design method, it is possible to change the specific order resonant frequency of the blade structure by altering its local stiffness and weight, thereby achieving the goal of avoiding the main operating speed range by changing the natural frequency.

[0103] The composite material blade of this invention can simultaneously meet the vibration fatigue design requirements while ensuring the optimal aerodynamic performance of the blade airfoil, thus solving the problem of balancing transmission aerodynamic performance and safety requirements, and making a beneficial contribution to improving engine efficiency.

[0104] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A method for designing composite material blades, characterized in that, The design method includes the following steps: S1. Conduct blade vibration characteristic analysis to determine the natural frequency order and mode shape that may cause dangerous resonance; S2. Determine the direction in which the frequency needs to be adjusted; S3. Based on the characteristics of available materials, analyze the geometric location where materials need to be replaced locally, and the trend of blade frequency change that may result from material replacement, and determine the blade material to be replaced. S4. For the structure of composite material blades formed using the determined replacement materials, conduct detailed verification of the natural frequencies; S5. Design a material combination scheme and blade structure scheme that meet the frequency requirements.

2. The composite material blade design method as described in claim 1, characterized in that, The vibration modes of the blades include: bending vibration mode, torsional vibration mode, chordal vibration mode, and composite vibration mode.

3. The composite material blade design method as described in claim 1, characterized in that, The relationship between the natural frequency of the blade structure and the elastic modulus and density of the blade material is as follows: Where ω is the natural frequency; E is the elastic modulus of the blade material; ρ is the density of the blade material; and k is a coefficient. In step S3, let a be the original blade material and b be the replacement blade material; E a ρ represents the elastic modulus of the original blade material. a E represents the density of the original blade material. b ρ represents the elastic modulus of the replacement blade material. b Indicates the density of the replacement blade material; If it is necessary to increase the blade frequency, then If it is necessary to reduce the blade frequency, then 4. A composite material blade, characterized in that, The composite material blade is designed using the composite material blade design method as described in any one of claims 1-3. The composite material includes at least two different materials. The blade structures of the various different materials are interconnected to form the whole blade. There is a transition area at the connection of the various different materials, and the various different materials permeate each other in the transition area.

5. The composite material blade as described in claim 4, characterized in that, The composite material includes a first material and a second material. The blade structure of the first material and the blade structure of the second material are connected to each other to form the whole blade. The connection between the first material and the second material has a transition region in which the first material and the second material permeate each other.

6. The composite material blade as described in claim 5, characterized in that, The material of the upper structure of the composite material blade body is the first material, and the material of the lower part of the composite material blade body and the tenon structure is the second material.

7. The composite material blade as described in claim 5, characterized in that, The material on the left side of the composite material blade in the axial direction is the first material, and the material on the right side of the composite material blade in the axial direction is the second material.

8. The composite material blade as described in claim 5, characterized in that, The material at the root bending mode nodal line of the composite material blade is the first material, and the material at the remaining positions of the composite material blade is the second material.

9. The composite material blade as described in claim 5, characterized in that, The material at the mid-axis nodal line of the composite material blade is the first material, and the material at the remaining positions of the composite material blade is the second material.

10. The composite material blade as described in claim 5, characterized in that, The composite material blade is a guide blade, the material of the upper structure and the upper outer ring structure of the guide blade is a first material, and the material of the lower part of the guide blade and the lower inner ring structure is a second material.

11. The composite material blade as described in claim 5, characterized in that, The composite material includes three different materials, and also includes a third material; The upper part of the blade body of the composite material blade is the first material, the middle part of the blade body of the composite material blade is the second material, and the lower part of the blade body and the tenon structure of the composite material blade are the third material.

12. The composite material blade as described in claim 5, characterized in that, The composite material blades are manufactured using additive manufacturing or welding methods.

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