A method and system for strength design of turbine blades

Abstract

This application discloses a turbine blade strength design method and system, belonging to the field of blade strength design technology. The turbine blade strength design method includes the following steps: establishing a blade airfoil model, wherein the center of the stacking axis of the blade in the airfoil model coincides with the centroid of the blade; determining and obtaining the execution tolerance of the blade based on the airfoil model; establishing a tolerance influence assessment calculation model based on the execution tolerance; and optimizing the blade airfoil model based on the tolerance influence assessment calculation model. This improves the accuracy of determining and obtaining the execution tolerance, and enables theoretical analysis of the execution tolerance of the blade airfoil during forward design. It avoids the problem that the execution tolerance influence exceeds the reserve coefficient required by the blade design criteria during actual production, reduces the risk of fatigue fracture of the blade, improves the actual life of the blade, and ensures that the strength of the turbine blade meets the actual requirements of strength design and engineering production.

Description

Technical Field

[0001] This application belongs to the field of blade strength design technology, and specifically relates to a turbine blade strength design method and system. Background Technology

[0002] During the strength design phase of turbine blades, it is necessary to perform strength simulation calculations and analyses on the blades to ensure that the blade strength meets the requirements of strength, life, and vibration reserve coefficient specified in the blade design guidelines.

[0003] In existing turbine blade strength design, theoretical models of the blade are generally used as the calculation and analysis object, and the reserve coefficient specified in the blade design criteria is used to evaluate whether the blade strength design meets the requirements. The selection of the blade profile tolerance is based on existing finished products and relevant standards. However, turbine blades designed using this method lack theoretical analysis of the blade profile tolerance during forward design. In actual production, the designed tolerance of some blade profiles can easily exceed the reserve coefficient required by the blade design criteria, making the blades highly susceptible to fatigue fracture. This results in the actual blade life being lower than the theoretical life designed in the past, and the turbine blade strength failing to fully meet the actual requirements of strength design and engineering production. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a turbine blade strength design method and system, which has the beneficial effects of reducing the probability of fatigue fracture in the blade, increasing the actual lifespan of the blade, and ensuring that the strength of the turbine blade meets the actual requirements of strength design and engineering production.

[0005] One method for designing the strength of a turbine blade includes the following steps: Establish a blade profile model, wherein the center of the stacking axis of the blade in the blade profile model is set to coincide with the centroid of the blade; Based on the blade profile model, determine the execution tolerance of the blade for which the blade profile model is obtained; Based on the aforementioned performance tolerance, a tolerance impact assessment calculation model is established; Based on the tolerance impact assessment calculation model, the blade shape model is optimized.

[0006] Further, determining the execution tolerance of the blade based on the blade profile model includes the following steps: Based on the blade profile model, obtain the static strength of the blade of the blade profile model; Based on the static strength of the blade, the execution tolerance of the blade for obtaining the blade profile model is determined.

[0007] Further, determining the execution tolerance of the blade based on the blade static strength to obtain the blade profile model includes the following steps: Obtain blade design guidelines; The static strength of the blade is evaluated based on the blade design criteria.

[0008] Furthermore, after evaluating the static strength of the blade based on the blade design criteria, the following steps are set: When the static strength of the blade meets the blade design criteria, determine the execution tolerance of the blade for obtaining the blade airfoil model; Alternatively, when the static strength of the blade violates the blade design criteria, the blade profile model is re-established.

[0009] Furthermore, the step of establishing a tolerance impact assessment calculation model based on the performance tolerance includes the following steps: Obtain the deviation value between the installation angle and position degree of the tolerance being performed; Based on the deviation between the mounting angle and the position degree, a first tolerance extreme value for the mounting angle and a second tolerance extreme value for the position degree along the lever arm direction of the centroid of the blade in the blade airfoil model are determined. Based on the first tolerance extreme value and the second tolerance extreme value, a tolerance impact assessment calculation model is established.

[0010] Furthermore, the lever arm direction of the center of mass of the blade in the blade airfoil model is perpendicular to the rotation axis of the impeller of the blade airfoil model; The lever arm direction of the center of mass of the blade in the blade profile model is also perpendicular to the stacking axis of the blade in the blade profile model.

[0011] Furthermore, optimizing the blade profile model based on the tolerance impact assessment calculation model includes the following steps: Obtain the blade evaluation requirements; The static strength of the blade is evaluated based on the tolerance impact assessment calculation model and the blade evaluation requirements. Based on the static strength of the blade, the blade shape model is optimized.

[0012] Furthermore, after evaluating the static strength of the blade based on the tolerance impact assessment calculation model and the blade evaluation requirements, the following steps are included: When the static strength of the blade is qualified, the blade shape model is output; Alternatively, if the static strength of the blade fails to meet the requirements, the execution tolerance of the blade in the blade profile model is reassessed.

[0013] Furthermore, when the static strength of the blade violates the blade evaluation requirements, and the execution tolerance of the blade for obtaining the blade profile model is reassessed, the following steps are set: If the execution tolerance of the blade in the blade profile model is less than a preset value, the blade profile model is rebuilt.

[0014] A turbine blade strength design system based on the same concept, applying the turbine blade strength design method described above, includes: A construction module is used to build a blade profile model and drive the center of the stacking axis of the blade in the blade profile model to coincide with the centroid of the blade. The first evaluation module is used to determine the execution tolerance of the blade that obtained the blade profile model based on the blade profile model. The processing module is used to establish a tolerance impact assessment calculation model based on the execution tolerance; The second evaluation module is used to optimize the blade shape model based on the tolerance influence evaluation calculation model.

[0015] Compared with the prior art, this application has the following advantages: The turbine blade strength design method of this application, when establishing the blade airfoil model based on blade design criteria, ensures that the center of the stacking axis of the blade in the airfoil model coincides with the center of mass of the blade. This avoids the generation or increase of bending stress, thereby improving the accuracy of obtaining the execution tolerance of the blade for the airfoil model. Simultaneously, by sequentially optimizing the blade airfoil model using a tolerance influence assessment calculation model established based on the execution tolerance, and then using the tolerance influence assessment calculation model as a basis, the tolerance influence assessment calculation model can be incorporated into the strength calculation analysis. This achieves theoretical analysis of the execution tolerance of the blade airfoil during forward design, thus avoiding the problem that the execution tolerance of the blade airfoil design exceeds the reserve coefficient required by the blade design criteria during actual production. This reduces the probability of fatigue fracture of the blade, thereby improving the actual life of the blade and ensuring that the strength of the turbine blade meets the actual requirements of strength design and engineering production.

[0016] The turbine blade strength design system of this application has the same beneficial effects as the turbine blade strength design method described above, since it applies the turbine blade strength 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 strength design method according to an embodiment of this application is shown; Figure 2 A logic block diagram of a turbine blade strength design method according to an embodiment of this application is shown; Figure 3a Equivalent stress distribution diagram for a theoretical model of a turbine blade using traditional design methods; Figure 3b The equivalent stress distribution diagram of an actual turbine blade component using traditional design methods; Figure 4a Equivalent stress distribution diagram of the theoretical model of a turbine blade for which the turbine blade strength design method of the present application is applied; Figure 4b The equivalent stress distribution diagram of the actual part of the turbine blade for which the turbine blade strength design method of the present application embodiment is applied. 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 strength design method, including the following steps: A blade profile model is established, where the center of the blade's stacking axis coincides with the blade's centroid. Based on the blade profile model, the execution tolerance of the blade is determined. Based on the execution tolerance, a tolerance impact assessment calculation model is established. Based on the tolerance impact assessment calculation model, the blade profile model is optimized.

[0022] Specifically, the turbine blade profile is designed to establish a blade profile model. During model creation, the center of the blade's stacking axis is aligned with the blade's center of mass to prevent the generation or increase of bending stress, thereby improving the accuracy of determining the blade's performance tolerances. Then, based on the established blade profile model, the performance tolerances are initially determined and obtained. After obtaining the performance tolerances, a tolerance impact assessment calculation model is established. This model is then used to optimize the blade profile model, incorporating it into the strength calculation analysis. This allows for the theoretical analysis of the blade profile's performance tolerances during forward design. This avoids the problem that the performance tolerance of the blade profile design in actual production exceeds the reserve coefficient required in the blade design criteria, thereby reducing the probability of fatigue fracture of the blade and improving the actual life of the blade, so that the strength of the turbine blade can meet the actual requirements of strength design and engineering production.

[0023] It should be noted that the center point O of the stacking axis of the blade in the airfoil model is the reference point for the execution tolerance of the blade in the airfoil model. The execution tolerance of the blade in the airfoil model reflects the deviation of the turbine blade from the center point O of the stacking axis of the blade in the actual manufacturing process. The greater the offset distance of the centroid of the blade in the airfoil model, the greater the bending stress of the blade. By aligning the center of the stacking axis of the blade in the airfoil model with the centroid of the blade, the theoretical position of the centroid offset of the blade in the airfoil model can be directly reflected through the execution tolerance of the blade. This facilitates the control of the centroid deviation of the blade in the airfoil model by controlling the positional degree of the execution tolerance, thus controlling the bending stress of the blade and preventing its generation or increase. This improves the accuracy of the judgment of the execution tolerance of the blade in the airfoil model.

[0024] In some specific embodiments of this application, determining the execution tolerance of the blade based on the blade profile model includes the following steps: Based on the blade profile model, obtain the static strength of the blade. Based on the static strength, determine the execution tolerance of the obtained blade profile model.

[0025] Specifically, after establishing the blade profile model, strength and life calculations are performed on the model to obtain its static strength. Based on this static strength, and combined with experience from mature models, relevant standards, and process requirements, the execution tolerances of the blade profile model are preliminarily determined and obtained.

[0026] In some specific embodiments of this application, determining the execution tolerance of the blade based on the blade static strength includes the following steps: Obtain blade design criteria. Based on the blade design criteria, evaluate the blade's static strength.

[0027] Specifically, after establishing the blade profile model, strength and life calculation analysis are carried out on the blade profile model, and the static strength of the blade profile model is designed iteratively according to the blade design criteria. This is to evaluate whether the static strength of the blade profile model meets the requirements of the blade design criteria, and to ensure that the strength design of the turbine blade can meet the reserve coefficient requirements specified in the blade design criteria.

[0028] In some specific embodiments of this application, after evaluating the static strength of the blade based on blade design criteria, the following steps are set: If the blade's static strength meets the blade design criteria, determine the execution tolerance of the blade's airfoil model. Alternatively, if the blade's static strength violates the blade design criteria, rebuild the blade airfoil model.

[0029] Specifically, when the static strength of the blade profile model meets the requirements of the blade design criteria, subsequent steps are initiated. Based on experience from mature models, relevant standards, and process requirements, the execution tolerance of the blade profile model is initially determined and obtained. However, if the static strength violates the blade design criteria, the process returns to the step of establishing the blade profile model. The blade profile model is re-established after parameter adjustments, and strength and life calculations are performed again on the re-established model until the static strength of the obtained blade profile model meets the requirements of the blade design criteria. This iterative process ensures that the strength design of the turbine blade meets the reserve coefficient requirements specified in the blade design criteria.

[0030] In some specific embodiments of this application, a tolerance impact assessment calculation model is established based on the performance tolerance, including the following steps: Obtain the deviation between the mounting angle and positional tolerance. Based on the deviation, determine the first tolerance extreme value of the mounting angle and the second tolerance extreme value of the positional tolerance along the lever arm direction of the blade's center of mass in the blade airfoil model. Based on the first and second tolerance extreme values, establish a tolerance impact assessment calculation model.

[0031] Specifically, the deviation between the installation angle and the positional tolerance is a value that needs to be specified in the execution tolerance of the blade profile model. After determining and obtaining the execution tolerance of the blade profile model, the deviation between the installation angle and the positional tolerance is obtained based on the execution tolerance of the blade profile model. Based on the deviation between the installation angle and the positional tolerance, the first tolerance extreme value of the installation angle and the second tolerance extreme value of the positional tolerance along the lever arm direction of the center of mass of the blade profile model can be determined. Through the first and second tolerance extreme values, a tolerance influence assessment calculation model can be established accordingly, thus incorporating the tolerance influence assessment calculation model into the scope of strength calculation analysis, thereby realizing the theoretical analysis of the execution tolerance of the blade profile during forward design.

[0032] Furthermore, by combining and arranging the first and second tolerance extreme values, four tolerance impact assessment calculation models can be established accordingly. These models represent the tolerance impact assessment calculation model established by the maximum value of the first and second tolerance extreme values, the tolerance impact assessment calculation model established by the maximum value of the first and second tolerance extreme values, the tolerance impact assessment calculation model established by the minimum value of the first and second tolerance extreme values, and the tolerance impact assessment calculation model established by the minimum value of the first and second tolerance extreme values. This increases the number of tolerance impact assessment calculation models included in the strength calculation analysis, thereby ensuring the accuracy of the theoretical analysis of the blade profile tolerances during forward design.

[0033] In some specific embodiments of this application, the lever arm direction of the center of mass of the blade in the blade airfoil model is perpendicular to the rotation axis of the impeller of the blade airfoil model. The lever arm direction of the center of mass of the blade in the blade airfoil model is also perpendicular to the stacking axis of the blade in the blade airfoil model.

[0034] Specifically, the rotation axis of the impeller in the blade profile model is the same as the rotation axis of the turbine blade during operation. The stacking axis of the blade in the blade profile model is the line connecting the feature points obtained on each feature section of the blade profile model according to the construction rules of the blade design criteria. These feature points are either the position where the center of the stacking axis coincides with the centroid of the blade, or the line connecting the centers of the largest inscribed circles of the blade, etc. Furthermore, the stacking axis of the blade in the blade profile model is perpendicular to each feature section. The lever arm direction of the centroid of the blade in the blade profile model is perpendicular to the rotation axis of the impeller. Simultaneously, the lever arm direction of the centroid of the blade in the blade profile model is also perpendicular to the stacking axis of the blade. The larger the value of the lever arm direction of the centroid of the blade in the blade profile model, the larger the lever arm of the centroid of the blade in the blade profile model.

[0035] In some specific embodiments of this application, the blade profile model is optimized based on the tolerance impact assessment calculation model, including the following steps: Obtain the blade evaluation requirements. Based on the tolerance impact assessment calculation model and the blade evaluation requirements, evaluate the static strength of the blade. Based on the static strength of the blade, optimize the blade profile model.

[0036] Specifically, after establishing four tolerance impact assessment calculation models, strength and life calculation analyses are performed on these models. Blade evaluation requirements are obtained, and based on the four tolerance impact assessment calculation models and the blade evaluation requirements, the static strength of the blade is evaluated. Then, based on the evaluation results of the blade's static strength, the blade profile model is optimized to ensure that the strength design of the turbine blade meets the actual requirements of engineering production.

[0037] In some specific embodiments of this application, after evaluating the static strength of the blade based on the tolerance impact assessment calculation model and blade evaluation requirements, the following steps are set: If the blade's static strength is qualified, output the blade profile model. Alternatively, if the blade's static strength is not qualified, re-evaluate and obtain the blade's execution tolerance for the blade profile model.

[0038] Specifically, after the four tolerance impact assessment calculation models have undergone strength and life calculation analysis and design iteration, if all four tolerance impact assessment calculation models meet the requirements of blade evaluation, the blade profile model is deemed to have qualified static strength, and the blade profile model can be output. However, if any tolerance impact assessment calculation model fails to meet the requirements of blade evaluation, the blade profile model is deemed to have unqualified static strength. Therefore, it is necessary to re-evaluate and obtain the blade's execution tolerance for the blade profile model, thereby optimizing the blade profile model. By incorporating the tolerance impact assessment calculation models into the scope of strength calculation analysis, theoretical analysis of the blade profile's execution tolerance during forward design is achieved, ensuring that the turbine blade's strength meets the actual requirements of strength design and engineering production.

[0039] In some specific embodiments of this application, when the static strength of the blade violates the blade evaluation requirements, the following steps are set when re-evaluating the execution tolerance of the blade to obtain the blade profile model: If the execution tolerance of the blade in the blade profile model is less than the preset value, the blade profile model is rebuilt.

[0040] Specifically, when the static strength of the blade profile model is deemed unqualified, the executed tolerance value of the blade profile model needs to be reduced, and the executed tolerance value needs to be reassessed until the static strength of the blade profile model is deemed qualified. However, if the executed tolerance value of the blade profile model decreases below a preset value, the step of establishing the blade profile model needs to be returned to and the model re-established until the static strength of the blade profile model is deemed qualified. The prerequisite for re-establishing the blade profile model is that even when the executed tolerance value is adjusted to the minimum tolerance value achievable by the manufacturing unit, the static strength of the blade profile model is still deemed unqualified; or, in other words, the maximum executed tolerance achievable by the tolerance impact assessment calculation model for the blade's static strength requirements is less than the minimum tolerance value achievable by the manufacturing unit.

[0041] This application also provides a turbine blade strength design system, applying the turbine blade strength design method of any of the above specific embodiments, including: a construction module, a first evaluation module, a processing module, and a second evaluation module. The construction module is used to establish a blade profile model and drive the center of the stacking axis of the blade in the blade profile model to coincide with the centroid of the blade. The first evaluation module is used to determine and obtain the execution tolerance of the blade in the blade profile model based on the blade profile model. The processing module is used to establish a tolerance influence assessment calculation model based on the execution tolerance. The second evaluation module is used to optimize the blade profile model based on the tolerance influence assessment calculation model.

[0042] Specifically, the turbine blade profile is designed using a construction module to establish a blade profile model. During this process, the construction module ensures that the center of the blade's stacking axis coincides with the blade's center of mass to prevent the generation or increase of bending stress, thereby improving the accuracy of determining the blade's performance tolerance. Then, based on the established blade profile model, a first evaluation module initially determines and obtains the blade's performance tolerance. After obtaining the performance tolerance, a processing module establishes a tolerance impact assessment calculation model based on the performance tolerance. Finally, a second evaluation module optimizes the blade profile model based on the tolerance impact assessment calculation model, thus incorporating the tolerance impact assessment calculation model into the strength calculation analysis, thereby achieving theoretical analysis of the blade's performance tolerance during forward design. This avoids the problem that the performance tolerance of the blade profile design in actual production exceeds the reserve coefficient required in the blade design criteria, thereby reducing the probability of fatigue fracture of the blade and improving the actual life of the blade, so that the strength of the turbine blade can meet the actual requirements of strength design and engineering production.

[0043] Experimental example: Reference Figure 3a , Figure 3b , Figure 4a and Figure 4b ,in, Figure 3a The equivalent stress distribution diagram is shown for a theoretical model of a turbine blade using traditional design methods. Figure 3b This is an equivalent stress distribution diagram for an actual turbine blade component designed using traditional methods. Figure 4a This is an equivalent stress distribution diagram of the theoretical model of a turbine blade for which the turbine blade strength design method of this application is applied. Figure 4b The equivalent stress distribution diagram of the actual part of the turbine blade for which the turbine blade strength design method of the present application embodiment is applied.

[0044] Depend on Figure 3a and Figure 3b It is evident that the equivalent stress distribution of the theoretical model of turbine blades using traditional design methods differs significantly from that of the actual parts. The location and magnitude of the maximum stress in the actual parts also differ from the calculation results of the theoretical model. Furthermore, the center of the stacking axis of the blades using traditional design methods is not aligned with the centroid of the blades, resulting in a significant impact of tolerances on the strength of the turbine blades.

[0045] Depend on Figure 4a and Figure 4bIt is evident that the equivalent stress distribution of the turbine blade theoretical model using the turbine blade strength design method of this application differs little from the equivalent stress distribution of the actual part. The location and magnitude of the maximum stress in the actual part are essentially the same as the calculation results of the theoretical model, and the deviation is within an acceptable range. Furthermore, the turbine blade strength design method of this application sets the center of the blade's stacking axis to coincide with the blade's center of mass, which can reduce the impact of performance tolerances on the strength of the turbine blade.

[0046] 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 the strength of turbine blades, characterized in that, Includes the following steps: Establish a blade profile model, wherein the center of the stacking axis of the blade in the blade profile model is set to coincide with the centroid of the blade; Based on the blade profile model, determine the execution tolerance of the blade for which the blade profile model is obtained; Based on the aforementioned performance tolerance, a tolerance impact assessment calculation model is established; Based on the tolerance impact assessment calculation model, the blade shape model is optimized.

2. The turbine blade strength design method according to claim 1, characterized in that, The step of determining the execution tolerance of the blade based on the blade profile model includes the following steps: Based on the blade profile model, obtain the static strength of the blade of the blade profile model; Based on the static strength of the blade, the execution tolerance of the blade for obtaining the blade profile model is determined.

3. The turbine blade strength design method according to claim 2, characterized in that, The step of determining the execution tolerance of the blade based on the blade static strength and obtaining the blade airfoil model includes the following steps: Obtain blade design guidelines; The static strength of the blade is evaluated based on the blade design criteria.

4. The turbine blade strength design method according to claim 3, characterized in that, Based on the blade design criteria, after evaluating the static strength of the blade, the following steps are set: When the static strength of the blade meets the blade design criteria, determine the execution tolerance of the blade for obtaining the blade airfoil model; Alternatively, when the static strength of the blade violates the blade design criteria, the blade profile model is re-established.

5. The turbine blade strength design method according to claim 1, characterized in that, The step of establishing a tolerance impact assessment calculation model based on the performance tolerance includes the following steps: Obtain the deviation value between the installation angle and position degree of the tolerance being performed; Based on the deviation between the mounting angle and the position degree, a first tolerance extreme value for the mounting angle and a second tolerance extreme value for the position degree along the lever arm direction of the centroid of the blade in the blade airfoil model are determined. Based on the first tolerance extreme value and the second tolerance extreme value, a tolerance impact assessment calculation model is established.

6. The turbine blade strength design method according to claim 5, characterized in that, The lever arm of the center of mass of the blade in the blade airfoil model is perpendicular to the rotation axis of the impeller of the blade airfoil model. The lever arm direction of the center of mass of the blade in the blade profile model is also perpendicular to the stacking axis of the blade in the blade profile model.

7. The turbine blade strength design method according to claim 1, characterized in that, The optimization of the blade profile model based on the tolerance impact assessment calculation model includes the following steps: Obtain the blade evaluation requirements; The static strength of the blade is evaluated based on the tolerance impact assessment calculation model and the blade evaluation requirements. Based on the static strength of the blade, the blade shape model is optimized.

8. The turbine blade strength design method according to claim 7, characterized in that, Based on the tolerance impact assessment calculation model and the blade evaluation requirements, after assessing the static strength of the blade, the following steps are set: When the static strength of the blade is qualified, the blade shape model is output; Alternatively, if the static strength of the blade fails to meet the requirements, the execution tolerance of the blade in the blade profile model is reassessed.

9. The turbine blade strength design method according to claim 8, characterized in that, When the static strength of the blade violates the blade evaluation requirements, and the execution tolerance of the blade airfoil model is re-evaluated, the following steps are set: If the execution tolerance of the blade in the blade profile model is less than a preset value, the blade profile model is rebuilt.

10. A turbine blade strength design system, employing the turbine blade strength design method as described in any one of claims 1 to 9, characterized in that, include: A construction module is used to build a blade profile model and drive the center of the stacking axis of the blade in the blade profile model to coincide with the centroid of the blade. The first evaluation module is used to determine the execution tolerance of the blade that obtained the blade profile model based on the blade profile model. The processing module is used to establish a tolerance impact assessment calculation model based on the execution tolerance; The second evaluation module is used to optimize the blade shape model based on the tolerance influence evaluation calculation model.

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