A turbine blade vibration design method and system
By evaluating the turbulent interference factors and excitation frequency of the turbine blades, and conducting multiple iterative designs, the problem that the vibration design of turbine blades in the existing technology cannot meet the actual requirements was solved, and the structure was optimized and the service life was extended.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC HUNAN AVIATION POWERPLANT RES INST
- Filing Date
- 2026-03-06
- Publication Date
- 2026-05-29
AI Technical Summary
Existing turbine blade vibration design methods cannot fully meet design criteria when considering inlet airflow distortion, low-order engine excitation, and structural excitation sources. In particular, changes in the guide vane exit wake distribution and the influence of exhaust pipe bending lead to turbulent flow fields, affecting aerodynamic excitation and failing to fully meet the actual requirements of vibration design.
By obtaining multiple excitation frequency harmonics corresponding to the structural excitation source, the first vibration calculation iteration is performed to obtain the first blade structure, evaluate the flow field turbulence interference factors, and combine each excitation frequency harmonic to perform the second vibration design iteration to obtain the second blade structure. This avoids the dangerous point of aerodynamic excitation resonance exceeding the preset amplitude, ensuring that the blade structure meets the design criteria and actual requirements.
It achieves the design criteria requirements of turbine blade structure in traditional design methods, while avoiding the danger of aerodynamic excitation resonance exceeding the preset amplitude, ensuring that the blade structure can fully meet the actual requirements of vibration design, reducing vibration stress and improving service life.
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Figure CN122113743A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of turbine blade structure technology, and specifically relates to a turbine blade vibration design method and system. Background Technology
[0002] During the vibration design phase of turbine blades, resonance analysis of the blades is required. The vibration design of the blades is iterated by changing the blade profile, adjusting the number of excitation sources, or increasing damping, so that the blade structure meets the design criteria requirements.
[0003] Existing turbine blade vibration design typically considers inlet airflow distortion, low-order engine excitation, and structural excitation sources to iterate the blade's vibration design, thereby ensuring the blade structure meets design criteria. However, blades obtained through this iterative process are still susceptible to interference from other components. For example, when large and small blades coexist in the upstream guide vane cascade, or when the distance between the guide vane and the support plate is too small, the wake distribution at the guide vane exit will change. Alternatively, when the exhaust pipe has a significant bend, the resulting localized losses will affect the order and amplitude of pressure and aerodynamic forces, leading to turbulent flow and consequently impacting the aerodynamic excitation of the turbine blade, preventing the turbine blade from fully meeting the actual requirements of vibration design. Summary of the Invention
[0004] To address the aforementioned issues, this application provides a turbine blade vibration design method and system that meets the design criteria requirements of traditional design methods, avoids the generation of resonance hazards caused by structural excitation sources that result in aerodynamic excitation exceeding the preset amplitude, prevents impact on the aerodynamic excitation of the blade, and ensures that the blade structure fully meets the actual requirements of vibration design.
[0005] One method for designing turbine blade vibration includes the following steps: Obtain multiple excitation frequency harmonics corresponding to the structural excitation source; Based on the excitation frequency multiple which is less than a preset multiple, the first vibration calculation iteration obtains the first blade structure; Based on the first blade structure, the interfering factors that cause flow field turbulence are evaluated and obtained; Based on the aforementioned interference factors and in conjunction with each of the aforementioned excitation frequency harmonics, the second vibration design iteration yields the second blade structure.
[0006] Furthermore, the first vibration calculation iteration to obtain the first blade structure based on the excitation frequency harmonic, which is less than a preset multiple, includes the following steps: Select the excitation frequency, which is less than a preset multiple, corresponding to the structural excitation source; Based on the excitation frequency multiple which is less than a preset multiple, the first vibration calculation iteration is performed to obtain the first blade structure.
[0007] Furthermore, the assessment of interfering factors causing flow field turbulence based on the first blade structure includes the following steps: Based on the first blade structure, the flow channel components adjacent to the first blade structure are evaluated to obtain a first evaluation result; Based on the first evaluation results, the structural interference factors that cause flow field turbulence are identified.
[0008] Furthermore, the step of evaluating and acquiring the interfering factors causing flow field turbulence based on the first blade structure also includes the following steps: Based on the first blade structure, the exhaust pipe adjacent to the first blade structure is evaluated to obtain a second evaluation result; Based on the second evaluation results, the exhaust interference factors that cause flow field turbulence are obtained.
[0009] Furthermore, the second vibration design iteration to obtain the second blade structure based on the aforementioned interference factors and in combination with each of the aforementioned excitation frequency harmonics includes the following steps: Based on the aforementioned interference factors, select each of the excitation frequency harmonics corresponding to the structural excitation source; Based on each of the excitation frequency harmonics, the second vibration design iteration obtains the second blade structure.
[0010] Furthermore, the second vibration design iteration to obtain the second blade structure based on each of the excitation frequency harmonics includes the following steps: Based on each of the excitation frequency harmonics, the resonance hazard points of the first blade structure are assessed and obtained; Based on the aforementioned resonance hazard point, the second vibration design iteration yielded the second blade structure.
[0011] Furthermore, the second vibration design iteration to obtain the second blade structure based on the resonance hazard point includes the following steps: Based on the resonance hazard points, the aerodynamic excitation amplitude corresponding to each resonance hazard point is calculated and analyzed. Based on each of the aerodynamic excitation amplitudes, the second vibration design iteration obtains the second blade structure.
[0012] Furthermore, based on each of the aerodynamic excitation amplitudes, the second vibration design iteration obtains the second blade structure, including the following steps: If each of the aerodynamic excitation amplitudes is lower than the preset amplitude, the first blade structure is used as the second blade structure and output. If any of the aerodynamic excitation amplitudes is higher than the preset amplitude, the first blade structure will be iteratively transformed into the second blade structure through vibration design.
[0013] Furthermore, after obtaining the second blade structure through the second vibration design iteration, the following steps are included: Based on the second blade structure, the turbine blade vibration design method is repeated until the resonance hazard point is eliminated.
[0014] A turbine blade vibration design system based on the same concept, applying the turbine blade vibration design method described above, includes: The acquisition module is used to acquire multiple excitation frequency harmonics corresponding to the structural excitation source; The first analysis module is used to obtain the first blade structure through the first vibration calculation iteration based on the excitation frequency number which is less than a preset multiple; The judgment module is used to evaluate and acquire the interference factors that cause flow field turbulence based on the structure of the first blade; The second analysis module is used to obtain the second blade structure through a second vibration design iteration based on the interference factors and in combination with each of the excitation frequency harmonics.
[0015] Compared with the prior art, this application has the following advantages: The turbine blade vibration design method of this application obtains the interference factors that cause flow field turbulence by evaluating the first blade structure, thereby increasing the number of excitation frequency harmonics and incorporating them into the vibration calculation analysis to determine the corresponding resonance hazard points. This allows for further iterative acquisition of the second blade structure, ensuring that the second blade structure not only meets the design criteria requirements of traditional design methods but also avoids the generation of resonance hazard points caused by structural excitation sources with aerodynamic excitation exceeding the preset amplitude. This prevents the aerodynamic excitation of the blade from being affected, ensuring that the blade structure fully meets the actual requirements of vibration design.
[0016] The turbine blade vibration design system of this application has the same beneficial effects as the turbine blade vibration design method described above, because it applies the turbine blade vibration design method described above. Therefore, it will not be described again here.
[0017] Other features and advantages of this application will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the application. The objectives and other advantages of this application may be realized and obtained by means of the structures pointed out in the description, claims and drawings. Attached Figure Description
[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0019] Figure 1 A flowchart of a turbine blade vibration design method according to an embodiment of this application is shown; Figure 2 A logic block diagram of a turbine blade vibration design method according to an embodiment of this application is shown; Figure 3 The fatigue limit diagram of a turbine blade under high-order aerodynamic excitation using conventional design methods is shown. Figure 4 The fatigue limit diagram of a turbine blade subjected to high-order aerodynamic excitation is shown, which applies the turbine blade vibration design method of this application. Detailed Implementation
[0020] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0021] Reference Figure 1 and Figure 2 This application provides a turbine blade vibration design method, including the following steps: Multiple excitation frequency harmonics corresponding to the structural excitation source are obtained. Based on excitation frequency harmonics less than a preset multiple, the first vibration calculation iteration obtains the first blade structure. Based on the first blade structure, interference factors causing flow field turbulence are evaluated and obtained. Based on the interference factors, and in conjunction with each excitation frequency harmonic, the second vibration design iteration obtains the second blade structure.
[0022] Specifically, multiple excitation harmonics corresponding to the structural excitation source are obtained. Among these, the excitation harmonics corresponding to the structural excitation source but less than a preset multiple are selected for the first vibration calculation iteration, thereby calculating and obtaining the first blade structure. Using the first blade structure, characteristic structural assessments are conducted to identify interference factors that cause flow field turbulence, i.e., factors that may lead to non-uniform changes in the flow field. When interference factors are identified, all excitation harmonics except those corresponding to the structural excitation source but less than a preset multiple are included in the vibration calculation analysis. This identifies corresponding resonance hazard points, enabling a second vibration design iteration for the first blade structure, thereby designing and obtaining the second blade structure. The second blade structure obtained through this method not only meets the design criteria requirements of traditional design methods but also avoids the generation of resonance hazard points caused by aerodynamic excitation exceeding a preset amplitude due to the structural excitation source. This prevents interference with the blade's aerodynamic excitation, ensuring that the blade structure fully meets the actual requirements of vibration design.
[0023] In some specific embodiments of this application, the first blade structure is obtained through the first vibration calculation iteration based on an excitation frequency number less than a preset multiple, including the following steps: A vibration frequency harmonic of less than a preset multiple is selected corresponding to the vibration source of the structure. Based on the vibration frequency harmonic of less than the preset multiple, the first vibration calculation iteration is performed to obtain the structure of the first blade.
[0024] Specifically, the excitation frequency corresponding to the structural excitation source and less than a preset multiple is selected from multiple excitation frequency numbers. The first vibration calculation iteration is performed on the excitation frequency corresponding to the structural excitation source and less than the preset multiple to obtain the first blade structure, so that the first blade structure meets the design criteria requirements in the traditional design method.
[0025] In some specific embodiments of this application, based on the first blade structure, the evaluation of interfering factors that cause flow field turbulence includes the following steps: Based on the first blade structure, the flow channel components adjacent to the first blade structure are evaluated, and a first evaluation result is obtained. Based on the first evaluation result, the structural interference factors that cause flow field turbulence are identified.
[0026] Specifically, the flow channel components adjacent to the first blade structure are evaluated using the first blade structure to obtain a first evaluation result. Based on this first evaluation result, structures that may cause non-uniform changes in the flow field are identified. For example, the upstream guide vane cascade may contain both large and small blades, or the spacing between the support plate and the guide vane may be too small. This identifies structural interference factors that cause flow field turbulence. If structural interference factors causing flow field turbulence are found, then the existence of interference factors is confirmed.
[0027] In some specific embodiments of this application, the evaluation of interfering factors causing flow field turbulence, based on the first blade structure, further includes the following steps: Based on the first blade structure, the exhaust pipe adjacent to the first blade structure is evaluated to obtain a second evaluation result. Based on the second evaluation result, the exhaust interference factors that cause flow field turbulence are identified.
[0028] Specifically, the exhaust pipe adjacent to the first blade structure is evaluated using the first blade structure to obtain a second evaluation result. Based on the first evaluation result, the exhaust loss of the exhaust pipe is determined. For example, if the exhaust pipe has a large bend leading to significant exhaust loss, the exhaust interference factors causing flow field turbulence are identified. If exhaust interference factors causing flow field turbulence are found, then the existence of interference factors is confirmed.
[0029] In some specific embodiments of this application, based on interference factors and in combination with each excitation frequency harmonic, the second vibration design iteration obtains the second blade structure, including the following steps: Based on interference factors, each excitation frequency harmonic corresponding to the structural excitation source is selected. Based on each excitation frequency harmonic, the second vibration design iteration obtains the second blade structure.
[0030] Specifically, once interference factors are identified, all excitation frequency harmonics greater than a preset multiple, except for those corresponding to the structural excitation source and less than a preset multiple, are included in the vibration calculation analysis. This identifies the corresponding resonance hazard points, enabling a second vibration design iteration for the first blade structure, thereby designing and obtaining the second blade structure. This not only ensures that the blade structure meets the design criteria requirements of traditional design methods but also fully meets the actual requirements of vibration design.
[0031] Furthermore, if there are no interfering factors that cause flow field turbulence, the first blade structure is directly output.
[0032] It should be noted that, except for the excitation frequency harmonics corresponding to the structural excitation source that are less than the preset harmonics, all excitation frequency harmonics greater than the preset harmonics are included in the vibration calculation and analysis. In other words, all excitation frequency harmonics within the maximum harmonics corresponding to the structural excitation source are included in the vibration calculation and analysis.
[0033] In some specific embodiments of this application, the second vibration design iteration obtains the second blade structure based on each excitation frequency harmonic, including the following steps: Based on each excitation frequency harmonic, the resonance hazard points of the first blade structure are evaluated and obtained. Based on the resonance hazard points, the second vibration design iteration is used to obtain the second blade structure.
[0034] Specifically, by using each excitation harmonic, the corresponding blade excitation frequency and natural frequency are calculated, thus obtaining the frequency margin corresponding to each excitation harmonic. When the corresponding frequency margin is less than the required value, a resonance hazard point is identified in the first blade structure. Based on the identified resonance hazard point, a second vibration design iteration can be performed on the first blade structure to design and obtain the second blade structure. This not only ensures that the blade structure meets the design criteria requirements of traditional design methods but also fully meets the actual requirements of vibration design.
[0035] It should be noted that the excitation frequency harmonics are set in correspondence with the number of pitch diameters. Based on the excitation frequency harmonics that are less than the preset multiple corresponding to the structural excitation source, each excitation frequency harmonic that is greater than the preset multiple is included in the vibration calculation and analysis, which means that multiple pitch diameters are taken into consideration. This can improve the rationality of the vibration design iteration results and enable the blade structure to fully meet the actual requirements of vibration design.
[0036] Meanwhile, the excitation frequency multipliers less than the preset multiple are the excitation frequency multipliers of the low-order excitation (excitation frequency multipliers 1~3) and the excitation frequency multipliers corresponding to the structural excitation source.
[0037] In some specific embodiments of this application, the second blade structure is obtained through a second vibration design iteration based on resonance hazard points, including the following steps: Based on the resonance hazard points, the aerodynamic excitation amplitude corresponding to each resonance hazard point is calculated and analyzed. Based on each aerodynamic excitation amplitude, the second vibration design iteration is used to obtain the second blade structure.
[0038] Specifically, after identifying the existence of resonance hazard points, unsteady aerodynamic excitation calculations and analyses are performed on the first blade structure to obtain the aerodynamic excitation amplitude corresponding to each resonance hazard point. Using the aerodynamic excitation amplitude corresponding to each resonance hazard point, a second vibration design iteration can be performed on the first blade structure to design and obtain the second blade structure. This not only ensures that the blade structure meets the design criteria requirements of traditional design methods but also fully meets the actual requirements of vibration design.
[0039] Furthermore, if there is no resonance hazard, the first blade structure is directly output.
[0040] In some specific embodiments of this application, the second vibration design iteration obtains the second blade structure based on each aerodynamic excitation amplitude, including the following steps: If each aerodynamic excitation amplitude is lower than the preset amplitude, the first blade structure is used as the second blade structure and output. If any aerodynamic excitation amplitude is higher than the preset amplitude, the first blade structure is iteratively transformed into the second blade structure through vibration design.
[0041] Specifically, if the amplitude of each aerodynamic excitation is lower than the preset amplitude, a second vibration design iteration is unnecessary, and the first blade structure can be directly used as the second blade structure and output. However, if any aerodynamic excitation amplitude is higher than the preset amplitude, the first blade structure needs to be transformed into the second blade structure through a second vibration design iteration. This not only ensures that the blade structure meets the design criteria requirements of traditional design methods but also fully meets the actual requirements of vibration design.
[0042] In some specific embodiments of this application, after obtaining the second blade structure through the second vibration design iteration, the following steps are included: Based on the second blade structure, the turbine blade vibration design method is repeated until the resonance hazard point is eliminated.
[0043] Specifically, after obtaining the second blade structure through the second vibration design iteration, a new calculation and analysis is performed on the obtained second blade structure to determine whether resonance hazard points still exist. If resonance hazard points still exist, unsteady aerodynamic excitation calculation and analysis are conducted to obtain the aerodynamic excitation amplitude corresponding to each resonance hazard point. If aerodynamic excitation amplitudes higher than the preset amplitude still exist, a third vibration design iteration is performed on the second blade structure to obtain the third blade structure, and so on, until the blade no longer has resonance hazard points. This not only ensures that the blade structure meets the design criteria requirements of traditional design methods but also fully meets the actual requirements of vibration design.
[0044] This application also provides a turbine blade vibration design system, applying the turbine blade vibration design method described in any of the above specific embodiments, including: an acquisition module, a first analysis module, a judgment module, and a second analysis module. The acquisition module is used to acquire multiple excitation frequency harmonics corresponding to the structural excitation source. The first analysis module is used to perform a first vibration calculation iteration based on excitation frequency harmonics less than a preset multiple to obtain the first blade structure. The judgment module is used to evaluate and acquire interference factors that cause flow field turbulence based on the first blade structure. The second analysis module is used to perform a second vibration design iteration based on the interference factors and in conjunction with each excitation frequency harmonic to obtain the second blade structure.
[0045] Specifically, the acquisition module obtains multiple excitation harmonics corresponding to the structural excitation source. Among these, the excitation harmonics less than a preset multiple corresponding to the structural excitation source are selected and sent to the first analysis module for the first vibration calculation iteration, thereby calculating and obtaining the first blade structure. The judgment module identifies and evaluates the characteristic structures of the first blade structure block to obtain interference factors that may cause flow field turbulence or non-uniform changes. When interference factors are identified, all excitation harmonics except those less than the preset multiple multiple corresponding to the structural excitation source are sent to the second analysis module for vibration calculation analysis to determine the corresponding resonance hazard points. This allows for a second vibration design iteration for the first blade structure, thereby designing and obtaining the second blade structure. The obtained second blade structure not only meets the design criteria requirements of traditional design methods but also avoids the generation of resonance hazard points caused by aerodynamic excitation exceeding a preset amplitude due to the structural excitation source, thus preventing interference with the blade's aerodynamic excitation and ensuring that the blade structure fully meets the actual requirements of vibration design.
[0046] Experimental example: Reference Figure 3 and Figure 4 , Figure 3 This diagram illustrates the fatigue limit of turbine blades designed using traditional aerodynamic methods under high-order aerodynamic excitation. The irregularly shaped regions in the diagram represent the stress magnitude of the turbine blade during actual operation, and the diagonal lines represent the fatigue limit of the turbine blade material. Figure 4 The figure shows the fatigue limit of a turbine blade subjected to high-order aerodynamic excitation using the turbine blade vibration design method of this application. The irregularly shaped regions in the figure represent the stress magnitude of the turbine blade during actual operation, and the diagonal lines represent the fatigue limit of the turbine blade material. As can be seen from the figure, compared to traditional design methods, the turbine blade using the turbine blade vibration design method of this application has successfully optimized the resonance hazard point at the operating speed, and both vibration stress and steady-state stress have decreased. Combined with the fatigue limit of the turbine blade material, it can be concluded that the turbine blade using the turbine blade vibration design method of this application solves the resonance problem present in turbine blades designed using traditional methods.
[0047] Table 1. Comparison of parameters between turbine blades using the turbine blade vibration design method of this application and turbine blades using traditional design methods;
[0048] As shown in the table above, the turbine blade tip amplitude of the turbine blade using the turbine blade vibration design method of this application is reduced, reflecting the reduction in vibration stress experienced by the turbine blade using the turbine blade vibration design method of this application. The reduction in steady-state stress of the turbine blade using the turbine blade vibration design method of this application reflects the reduction in actual working stress of the turbine blade using the turbine blade vibration design method of this application at the operating speed, indicating that the service life of the turbine blade using the turbine blade vibration design method of this application is improved.
[0049] Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.
Claims
1. A method for designing turbine blade vibration, characterized in that, Includes the following steps: Obtain multiple excitation frequency harmonics corresponding to the structural excitation source; Based on the excitation frequency multiple which is less than a preset multiple, the first vibration calculation iteration obtains the first blade structure; Based on the first blade structure, the interfering factors that cause flow field turbulence are evaluated and obtained; Based on the aforementioned interference factors and in conjunction with each of the aforementioned excitation frequency harmonics, the second vibration design iteration yields the second blade structure.
2. The turbine blade vibration design method according to claim 1, characterized in that, The first vibration calculation iteration to obtain the first blade structure based on the excitation frequency number which is less than a preset multiple includes the following steps: Select the excitation frequency, which is less than a preset multiple, corresponding to the structural excitation source; Based on the excitation frequency multiple which is less than a preset multiple, the first vibration calculation iteration is performed to obtain the first blade structure.
3. The turbine blade vibration design method according to claim 1, characterized in that, The process of evaluating and identifying the interfering factors causing flow field turbulence based on the first blade structure includes the following steps: Based on the first blade structure, the flow channel components adjacent to the first blade structure are evaluated to obtain a first evaluation result; Based on the first evaluation results, the structural interference factors that cause flow field turbulence are identified.
4. The turbine blade vibration design method according to claim 3, characterized in that, The step of evaluating and acquiring the interfering factors that cause flow field turbulence based on the first blade structure further includes the following steps: Based on the first blade structure, the exhaust pipe adjacent to the first blade structure is evaluated to obtain a second evaluation result; Based on the second evaluation results, the exhaust interference factors that cause flow field turbulence are obtained.
5. The turbine blade vibration design method according to claim 1, characterized in that, The second vibration design iteration to obtain the second blade structure based on the aforementioned interference factors and in combination with each of the aforementioned excitation frequency harmonics includes the following steps: Based on the aforementioned interference factors, select each of the excitation frequency harmonics corresponding to the structural excitation source; Based on each of the excitation frequency harmonics, the second vibration design iteration obtains the second blade structure.
6. The turbine blade vibration design method according to claim 5, characterized in that, The second vibration design iteration to obtain the second blade structure based on each of the excitation frequency harmonics includes the following steps: Based on each of the excitation frequency harmonics, the resonance hazard points of the first blade structure are assessed and obtained; Based on the aforementioned resonance hazard point, the second vibration design iteration yielded the second blade structure.
7. The turbine blade vibration design method according to claim 6, characterized in that, The second vibration design iteration, based on the aforementioned resonance hazard point, to obtain the second blade structure includes the following steps: Based on the resonance hazard points, the aerodynamic excitation amplitude corresponding to each resonance hazard point is calculated and analyzed. Based on each of the aerodynamic excitation amplitudes, the second vibration design iteration obtains the second blade structure.
8. The turbine blade vibration design method according to claim 7, characterized in that, Based on each of the aerodynamic excitation amplitudes, the second vibration design iteration obtains the second blade structure, including the following steps: If each of the aerodynamic excitation amplitudes is lower than the preset amplitude, the first blade structure is used as the second blade structure and output. If any of the aerodynamic excitation amplitudes is higher than the preset amplitude, the first blade structure will be iteratively transformed into the second blade structure through vibration design.
9. The turbine blade vibration design method according to claim 6, characterized in that, After obtaining the second blade structure through the second vibration design iteration, the following steps are set: Based on the second blade structure, the turbine blade vibration design method is repeated until the resonance hazard point is eliminated.
10. A turbine blade vibration design system, employing the turbine blade vibration design method as described in any one of claims 1 to 9, characterized in that, include: The acquisition module is used to acquire multiple excitation frequency harmonics corresponding to the structural excitation source; The first analysis module is used to obtain the first blade structure by performing a first vibration calculation iteration based on the excitation frequency number which is less than a preset multiple. The judgment module is used to evaluate and acquire the interference factors that cause flow field turbulence based on the structure of the first blade; The second analysis module is used to obtain the second blade structure through a second vibration design iteration based on the interference factors and in combination with each of the excitation frequency harmonics.