Aero-engine complete machine vibration characteristic reproduction method and system based on component tester and strain energy distribution

Abstract

The invention relates to the technical field of rotor systems, in particular to an aero-engine complete machine vibration characteristic reproduction method and system based on a component tester and strain energy distribution, and the method comprises the steps: determining a similarity ratio relation between a fan rotor component tester and a complete machine fan section; carrying out finite element analysis on the fan section of the whole machine to obtain a strain energy ratio and prototype rigidity; performing finite element analysis on the fan part tester to obtain model rigidity; obtaining a rigidity similarity ratio according to the prototype rigidity and the model rigidity; according to the strain energy ratio, weighted distribution is carried out on the rigidity similarity ratio, and the overall rigidity similarity ratio is calculated; according to the similarity ratio relation, the overall rigidity similarity ratio and the mass similarity ratio, the inherent frequency similarity ratio is calculated; vibration test data of a fan rotor part tester are obtained, and the inherent frequency of the fan section in the whole aero-engine is predicted based on the inherent frequency similarity ratio. The engine vibration characteristic can be reproduced.

Description

Technical Field

[0001] This invention relates to the field of rotor system technology, and in particular to a method and system for reproducing the vibration characteristics of an aero-engine based on a component tester and strain energy distribution. Background Technology

[0002] As a core component of large rotating machinery, the rotor system's dynamic characteristics directly affect the equipment's operational safety and reliability. Aero engines, as a typical example, are crucial for design optimization and fault diagnosis when their overall vibration characteristics are studied. Due to the complexity of the overall structure and the high cost of testing, establishing component test chambers using similarity theory to reproduce the overall vibration characteristics has become an important research method. Dynamic similarity theory, by establishing the similarity relationship between the prototype and the model, enables scaled-down tests to reflect the dynamic behavior of the full-scale system, offering advantages such as reduced testing difficulty and shorter development cycles.

[0003] In existing technologies, dynamic similarity methods mainly reproduce vibration characteristics through size scaling or local simplification. Reference 1 ("Dynamic Similarity Design of High-Pressure Rotor Test Model for Aero-Engine") employs an optimization algorithm-based similarity method, using the prototype's natural frequency, critical speed, and modal confidence criteria as objective functions, and correcting model parameters through sub-problem approximation algorithms. However, in practical engineering, the high-pressure rotor of an aero-engine, as a core component, often has its full-speed-range vibration response difficult to obtain in advance due to the high cost and risk of whole-engine testing, resulting in a lack of reliable target benchmarks for optimization algorithms. Reference 2 ("Design Method of Equivalent Scaled-Down Test Specimen for Low-Pressure Gas Turbine Rotor Based on Dynamic Similarity") reduces the dependence on complex control equations through response surface optimization and does not require rigorous derivation of multi-parameter coupling similarity relationships, thus adapting to the distortion similarity design of multi-disc structures in low-pressure gas turbine rotors to some extent. However, this method ignores the contribution of blade stiffness to the overall bending stiffness of the rotor, resulting in stiffness deviation and insufficient prediction accuracy of the rotor system's vibration response. Furthermore, the prototype and model in Reference 2 have similar structures and the same number of support points, representing only size scaling and local structural simplification. Reference 3 ("Research on the Design Method of Dynamic Similarity Test Model of Gas Turbine Power Turbine Rotor") derives the dynamic similarity criterion based on the differential equation of rotor lateral vibration. This requires pre-establishing the control equations of the rotor system, resulting in a large computational burden in equation construction and similarity relationship derivation. Furthermore, this method uses a fixed geometric scaling factor when deriving similarity relationships, failing to fully consider the coupling effect of various parameters under distortion similarity, thus limiting the accuracy of vibration response prediction for distorted similarity of the rotor system. In addition, the prototype and model in Reference 3 have similar structures and the same number of support points, representing only a scaling down in size and simplification of local structures. Patent 4 ("A Dynamic Characteristics Similarity Design Method for a Fan Rotor Test Model") simplifies the low-pressure turbine rotor and couples it to the fan rotor via a gear coupling. It aims to optimize the test model parameters based on the modal characteristics of the fan rotor in the low-pressure rotor system to achieve modal matching. However, this method relies solely on finite element simulation to verify modal characteristics, without building an actual test apparatus, making it difficult to guarantee consistency with the actual fan rotor. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a method and system for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy allocation. This invention primarily utilizes the establishment of a dynamic distortion similarity relationship between the fan section rotor and the fan rotor component testing device to reproduce the vibration characteristics of the fan section within the entire engine. Targeting the fan section of a dual-rotor aero-engine, it eliminates the need for overall engine modeling, accurately reproducing the first-order pitch mode shape of the fan section through the component testing device. Furthermore, it reflects the vibration evolution across the entire speed range, better meeting the high-speed operating requirements of aero-engine fan rotors. Maintaining consistency between the fan rotor component testing device and the overall fan section structure reduces mass and stiffness deviations caused by simplification assumptions. A strain energy-weighted stiffness similarity ratio allocation method is proposed, calculating the strain energy proportion of each support point and the rotor body to allocate the stiffness similarity ratio, resulting in more accurate natural frequency prediction. This invention reduces the cost, risk, and difficulty of aero-engine vibration testing, and shortens the testing and development cycle.

[0005] The technical means employed in this invention are as follows: A method for reproducing the vibration characteristics of an aero-engine based on a component testing instrument and strain energy distribution includes the following steps: Establish a dynamic distortion similarity relationship for the rotor of the fan section of an aero-engine. The dynamic distortion similarity relationship includes the similarity ratio relationship between the fan rotor component tester and the fan section of the aero-engine. The similarity ratio relationship includes the relationship between the natural frequency similarity ratio, stiffness similarity ratio and mass similarity ratio. Finite element analysis was performed on the entire fan section to obtain the strain energy ratio and prototype stiffness of each support point and rotor. Finite element analysis was performed on the fan component tester to obtain the model stiffness of each support point and the rotor; The stiffness similarity ratio is obtained based on the prototype stiffness and the model stiffness. Based on the strain energy ratio, the stiffness similarity ratio is weighted and the overall stiffness similarity ratio is calculated. Based on the aforementioned similarity ratio relationship, and combining the overall stiffness similarity ratio and the mass similarity ratio, the natural frequency similarity ratio is calculated. The vibration test data of the fan rotor component tester is obtained, and the natural frequencies in the vibration test data are converted based on the natural frequency similarity ratio to predict the natural frequency of the fan section in the entire aero-engine.

[0006] Furthermore, the structure of the fan rotor component tester is consistent with that of the fan component in the complete machine, and the mass similarity ratio is 1.

[0007] Furthermore, the dynamic distortion similarity relationship is derived from the rotor system dynamic equations through equation analysis, and the specific relationship is as follows:

[0008] in, The natural frequency similarity ratio, For stiffness similarity ratio, This represents the quality similarity ratio.

[0009] Furthermore, the proportion of strain energy at each support point and rotor is obtained by dividing the strain energy at each support point and rotor by the total strain energy of the entire fan section. The formula for calculating the overall stiffness similarity ratio is:

[0010] in, For stiffness similarity ratio, This represents the total strain energy of the entire fan section. The strain energy at the first fulcrum. The strain energy at the second fulcrum. The strain energy of the rotor, The stiffness similarity ratio of the first support point. The stiffness similarity ratio of the second support point. The stiffness similarity ratio of the rotor is given. The total strain energy of the fan section of the whole machine is the sum of the strain energy of the first support point, the strain energy of the second support point, and the strain energy of the rotor.

[0011] Furthermore, the formula for calculating the strain energy at the first fulcrum is:

[0012] in, The coefficient of strain energy at the first fulcrum. Let the displacement of the first support point be the formula for calculating the strain energy of the second support point.

[0013] in, The coefficient of strain energy at the second fulcrum. The formula for calculating the strain energy of the rotor, where the displacement is at the second support point, is:

[0014] in, The coefficient of rotor strain energy. This represents the rotor displacement.

[0015] Furthermore, the stiffness similarity ratio is obtained by dividing the prototype stiffness by the model stiffness.

[0016] Furthermore, the dynamic equations of the rotor system are as follows:

[0017] in, For the quality of the rotor system, For the damping of the rotor system, For the stiffness of the rotor system, For the turntable eccentricity, For rotational speed, For the vibration displacement of the rotor system, The vibration velocity of the rotor system, This represents the acceleration of the rotor system.

[0018] This invention also provides a system for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution, used to implement the above-mentioned method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution, including: The prototype analysis module is used to perform finite element analysis on the entire fan section to obtain the strain energy ratio and prototype stiffness of each support point and rotor. The test equipment design and analysis module is used to perform finite element analysis on the fan component test equipment to obtain the model stiffness. The similarity ratio calculation module, which is communicatively connected to the prototype analysis module and the test instrument design analysis module, is used to: calculate the stiffness similarity ratio based on the prototype stiffness and the model stiffness; weight the stiffness similarity ratio based on the strain energy ratio to calculate the overall stiffness similarity ratio; and calculate the natural frequency similarity ratio based on the dynamic distortion similarity relationship, combined with the overall stiffness similarity ratio and the mass similarity ratio. The test execution and data acquisition module includes: a fan rotor component tester body, a drive system for the operation of the fan rotor component tester body, and a sensor system for acquiring vibration test data of the tester body in operation. The prediction module is communicatively connected to the similarity ratio calculation module and the test execution and data acquisition module. It is used to convert the natural frequencies in the vibration test data based on the natural frequency similarity ratio and predict the natural frequency of the fan section in the entire aero-engine.

[0019] Furthermore, the dynamic distortion similarity relationship is derived from the rotor system dynamic equations through equation analysis, and the specific relationship is as follows:

[0020] in, The natural frequency similarity ratio, For stiffness similarity ratio, This represents the quality similarity ratio.

[0021] Furthermore, the proportion of strain energy at each support point and rotor is obtained by dividing the strain energy at each support point and rotor by the total strain energy of the entire fan section. The formula for calculating the overall stiffness similarity ratio is:

[0022] in, For stiffness similarity ratio, This represents the total strain energy of the entire fan section. The strain energy at the first fulcrum. The strain energy at the second fulcrum. The strain energy of the rotor, The stiffness similarity ratio of the first support point. The stiffness similarity ratio of the second support point. The stiffness similarity ratio of the rotor is given. The total strain energy of the fan section of the whole machine is the sum of the strain energy of the first support point, the strain energy of the second support point, and the strain energy of the rotor.

[0023] Compared with the prior art, the present invention has the following advantages: 1. The strain energy-weighted stiffness similarity ratio allocation method provided by this invention uses the proportion of strain energy of each support point and rotor body as the allocation basis, and realizes high-precision and mechanistic allocation of the overall stiffness similarity ratio in the distortion similarity scenario where the stiffness of the support point and the stiffness of the rotor are not equal, which significantly improves the accuracy of dynamic characteristic prediction.

[0024] 2. The dynamic distortion similarity relationship provided by this invention, by clarifying the inherent physical constraints between the natural frequency similarity ratio, stiffness similarity ratio and mass similarity ratio, realizes the decoupling of complex whole machine vibration characteristics into independently controllable and matched similarity ratio parameters under non-uniform structural distortion conditions. This provides a rigorous theoretical framework and operable engineering path for the quantitative design of component testing equipment and the accurate prediction of vibration characteristics.

[0025] 3. The component testing device provided by this invention is designed to be consistent with the structural form of the fan section of the whole machine. This reduces the mass and stiffness deviations caused by traditional simplified models, and realizes the accurate reproduction of key vibration modes such as the first-order pitch mode of the fan section of the whole machine, ensuring the comprehensiveness and authenticity of the vibration characteristic reproduction.

[0026] Based on the above reasons, this invention can be widely applied in fields such as rotor systems. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 This is a schematic diagram of the dynamic similarity prediction method of the present invention.

[0029] Figure 2 This is a rotor model test apparatus for the fan section in an embodiment of the present invention.

[0030] Figure 3 The waterfall diagram shows the fan rotor model tester obtained in the embodiment of the present invention.

[0031] Figure 4 shows the first-order mode shape of the fan rotor model tester obtained in the embodiment of the present invention.

[0032] Figure 5 This is a schematic diagram of a simulation model of an aero-engine rotor system in an embodiment of the present invention.

[0033] Figure 6 This is a schematic diagram of the prototype and model with the greatest degree of distortion in the embodiments of the present invention. Detailed Implementation

[0034] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0035] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0036] like Figure 1 As shown, this invention provides a method for reproducing the vibration characteristics of an aero-engine based on a component testing instrument and strain energy distribution. The specific steps are as follows: S1. Establish the dynamic distortion similarity relationship of the rotor of the whole fan section of the aero-engine. The dynamic distortion similarity relationship includes the similarity ratio relationship between the fan rotor component test instrument and the whole fan section. The similarity ratio relationship includes the relationship between the natural frequency similarity ratio, stiffness similarity ratio and mass similarity ratio.

[0037] Considering the rotor system as a whole, its dynamic equations can be described by the following equations: (1) in, For the quality of the rotor system, For the damping of the rotor system, For the stiffness of the rotor system, For the turntable eccentricity, For rotational speed, For the vibration displacement of the rotor system, The vibration velocity of the rotor system, This represents the acceleration of the rotor system.

[0038] Using the equation analysis method, equation (2) can be transformed into the following similarity relationship: (2) in, The natural frequency similarity ratio, For stiffness similarity ratio, For quality similarity ratio, The similarity ratio of vibration displacement, For time similarity ratio, This represents the eccentricity similarity ratio.

[0039] Since rotational speed and time are reciprocals, their similarity relationship is as follows: (3) By combining the first and fourth terms of equation (2) with equation (3), we can obtain: (4) By combining the third and fourth terms of equation (2) and equation (4), we can obtain the similarity relationship of rotational speed. Since the rotational speed has the same dimension as the natural frequency, their similarity relationship is also the same: (5) Since the fan rotor component tester has the same structure as the fan section in the whole machine, the mass similarity ratio is 1.

[0040] S2. Perform finite element analysis on the entire fan section to obtain the strain energy ratio and prototype stiffness of each support point and rotor.

[0041] The proportion of strain energy at each support point and rotor is obtained by dividing the strain energy of each support point and rotor by the total strain energy of the entire fan section. The formula for calculating the strain energy at the first support point is:

[0042] in, The coefficient of strain energy at the first fulcrum. The formula for calculating the strain energy at the second support point is: where is the displacement of the first support point.

[0043] in, The coefficient of strain energy at the second fulcrum. The formula for calculating the strain energy of the rotor, where the displacement is at the second fulcrum, is:

[0044] in, The coefficient of rotor strain energy. This represents the rotor displacement.

[0045] S3. Perform finite element analysis on the fan component tester to obtain the model stiffness of each support point and the rotor.

[0046] S4. Obtain the stiffness similarity ratio based on the prototype stiffness and the model stiffness.

[0047] In a preferred embodiment of the present invention, the stiffness similarity ratio is obtained by dividing the prototype stiffness by the model stiffness.

[0048] S5. Based on the proportion of strain energy, the stiffness similarity ratio is weighted and the overall stiffness similarity ratio is calculated.

[0049] For widely used equation analysis and dimensional analysis methods, only when λ k1 , λ k2 , λ k3 λ can only be determined when they are equal. k However, in practical engineering, it is difficult to guarantee λ when designing similar scaled-down models. k1 , λ k2 , λ k3 Equal stiffness similarity leads to distortion similarity problems. To address this issue, this invention proposes a dynamic similarity method based on strain energy weighting. The dynamic characteristics of a rotor system are directly related to the distribution of strain energy. By incorporating strain energy into the allocation of the rotor system stiffness similarity ratio, a mechanism-considered distortion similarity prediction of the rotor system is achieved, improving the prediction accuracy of distortion similarity cases. The overall stiffness similarity ratio is calculated using the following formula:

[0050] in, For stiffness similarity ratio, This represents the total strain energy of the entire fan section. The strain energy at the first fulcrum. The strain energy at the second fulcrum. The strain energy of the rotor, The stiffness similarity ratio of the first support point. The stiffness similarity ratio of the second support point. This represents the rotor stiffness similarity ratio.

[0051] The total strain energy of the fan section of the whole machine is the sum of the strain energy of the first support point, the strain energy of the second support point, and the strain energy of the rotor.

[0052] S6. Based on the similarity ratio relationship, combined with the overall stiffness similarity ratio and mass similarity ratio, the natural frequency similarity ratio can be calculated by substituting into equation (5).

[0053] S7. Obtain vibration test data from the fan rotor component tester, convert the natural frequencies in the vibration test data based on the natural frequency similarity ratio, and predict the natural frequency of the fan section in the entire aero-engine.

[0054] Example 1 To fully verify the advantages and effects of the present invention, vibration tests were conducted on the fan rotor component tester, and the test results of the component tester were compared and verified with the vibration mode of the whole machine.

[0055] The fan section rotor model test apparatus has a three-stage disk, and its schematic diagram is shown below. Figure 2 As shown. The fan rotor is mounted on a large horizontal rotor test bench via a swing frame. The test bench housing is in a vacuum state. It is connected to the test bench drive system via an adapter shaft, and the rotational speed is 0-8000 rpm.

[0056] Experimental tests were conducted on the fan section rotor model to obtain its first-order vibration mode. A laser displacement sensor was used to collect the vibration response of the fan section rotor model, with a sampling frequency of 4096 Hz. Because the front of the second-stage disk is a conical surface, it is difficult to accurately receive the laser emitted by the laser displacement sensor, and all stages of the disk have tenon and slot structures, making measurement impossible. Therefore, two measuring points were selected between the second and third-stage disks. The obtained waterfall diagram is shown below. Figure 3 As shown, the first natural frequency of the fan rotor model test device is 40.6 Hz.

[0057] Figure 4 shows the elastic curves of the two measuring points of the fan section rotor model test device at the critical speed. The elastic curves are lines connecting the shaft center trajectories of different measuring points at each moment, reflecting the vibration state between different measuring points and more clearly depicting the mode shape. It can be seen that the elastic curves are all oblique lines and intersect, indicating that the first mode of the fan section rotor model test device is the pitch mode.

[0058] The vibration characteristics of the entire machine were analyzed, and a dynamic model of the rotor system was established. Its basic structure is as follows: Figure 5 As shown, the overall model was simplified as follows: the compressor and turbine blades were simplified to lumped mass points while maintaining mass and moment of inertia; the bearings were simplified to linear springs, and the rotor system was modeled using Solid185 elements in Ansys, with 136,529 nodes. The support stiffness of each support point is shown in Table 1.

[0059] Table 1 Support stiffness of each support point of the rotor system

[0060] Strain energy analysis was performed on the fan section model of the entire machine. The analysis revealed that the strain energy proportions of support point #1, support point #2, and the rotor were 62.5%, 29.3%, and 8.2%, respectively. k1 , λ k2 , λ k3 Given 1, 0.73, and 1 respectively, λ can be obtained from equation (6). k =0.92, and further calculated according to equation (5) λ ω =0.96. Modal analysis of the overall dynamic model yielded the first-order vibration mode of the fan section rotor, as shown below. Figure 6 As shown, the natural frequency is 37.3 Hz. (Through λ) ω The natural frequency of the entire machine, predicted by the fan rotor model test apparatus, is 39.0 Hz, with a prediction error of 4.5%. Compared with References 1, 2, and 3, the prediction results of this invention are closer to the prototype results, and the prediction error is significantly reduced. Therefore, this invention significantly improves the prediction accuracy of the vibration response of the rotor system.

[0061] It can be seen that the first mode of the fan section rotor in the whole machine is the pitch mode. Comparing the mode shapes of the fan rotor component tester (Figure 4), the results show that the fan section rotor model tester accurately predicted the first mode shape of the fan section in the whole machine, verifying the effectiveness of the invention in practical engineering applications.

[0062] Example 2 This embodiment includes a system for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution, used to implement the aforementioned method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution, including: The prototype analysis module is used to perform finite element analysis on the entire fan section to obtain the strain energy ratio and prototype stiffness of each support point and rotor.

[0063] The test equipment design and analysis module is used to perform finite element analysis on the fan component test equipment to obtain the stiffness of the test model.

[0064] The similarity ratio calculation module communicates with the prototype analysis module and the test instrument design analysis module. It is used to: calculate the stiffness similarity ratio based on the stiffness of the prototype and the stiffness of the test model; weight the stiffness similarity ratio according to the strain energy ratio to calculate the overall stiffness similarity ratio; and calculate the natural frequency similarity ratio based on the dynamic distortion similarity relationship, combined with the overall stiffness similarity ratio and the mass similarity ratio.

[0065] The test execution and data acquisition module includes: the fan rotor component tester body, the drive system for the operation of the fan rotor component tester body, and the sensor system for acquiring vibration test data of the tester body in operation.

[0066] The prediction module, which communicates with the similarity ratio calculation module and the test execution and data acquisition module, is used to convert the natural frequencies in the vibration test data based on the natural frequency similarity ratio, and predict the natural frequencies of the fan section in the entire aero-engine.

[0067] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention 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 or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for reproducing the vibration characteristics of an aero-engine based on a component testing instrument and strain energy distribution, characterized in that, Includes the following steps: Establish a dynamic distortion similarity relationship for the rotor of the fan section of an aero-engine. The dynamic distortion similarity relationship includes the similarity ratio relationship between the fan rotor component tester and the fan section of the aero-engine. The similarity ratio relationship includes the relationship between the natural frequency similarity ratio, stiffness similarity ratio and mass similarity ratio. Finite element analysis was performed on the entire fan section to obtain the strain energy ratio and prototype stiffness of each support point and rotor. Finite element analysis was performed on the fan component tester to obtain the model stiffness of each support point and the rotor; The stiffness similarity ratio is obtained based on the prototype stiffness and the model stiffness. Based on the strain energy ratio, the stiffness similarity ratio is weighted and the overall stiffness similarity ratio is calculated. Based on the aforementioned similarity ratio relationship, and combining the overall stiffness similarity ratio and the mass similarity ratio, the natural frequency similarity ratio is calculated. The vibration test data of the fan rotor component tester is obtained, and the natural frequencies in the vibration test data are converted based on the natural frequency similarity ratio to predict the natural frequency of the fan section in the entire aero-engine.

2. The method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution according to claim 1, characterized in that, The structure of the fan rotor component tester is consistent with that of the fan component in the whole machine, and the mass similarity ratio is 1.

3. The method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution according to claim 1, characterized in that, The dynamic distortion similarity relationship is derived from the rotor system dynamic equations through equation analysis, and the specific relationship is as follows: in, The natural frequency similarity ratio, For stiffness similarity ratio, This represents the quality similarity ratio.

4. The method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution according to claim 1, characterized in that, The strain energy ratio of each support point and rotor is obtained by dividing the strain energy of each support point and rotor by the total strain energy of the entire fan section. The formula for calculating the overall stiffness similarity ratio is: in, For stiffness similarity ratio, This represents the total strain energy of the entire fan section. The strain energy at the first fulcrum. The strain energy at the second fulcrum. The strain energy of the rotor, The stiffness similarity ratio of the first support point. The stiffness similarity ratio of the second support point. The stiffness similarity ratio of the rotor is given. The total strain energy of the fan section of the whole machine is the sum of the strain energy of the first support point, the strain energy of the second support point, and the strain energy of the rotor.

5. The method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution according to claim 4, characterized in that, The formula for calculating the strain energy at the first fulcrum is: in, The coefficient of strain energy at the first fulcrum. Let the displacement of the first support point be the formula for calculating the strain energy of the second support point. in, The coefficient of strain energy at the second fulcrum. The formula for calculating the strain energy of the rotor, where the displacement is at the second support point, is: in, The coefficient of rotor strain energy. This represents the rotor displacement.

6. The method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution according to claim 1, characterized in that, The stiffness similarity ratio is obtained by dividing the prototype stiffness by the model stiffness.

7. The method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution according to claim 1, characterized in that, The dynamic equations of the rotor system are as follows: in, For the quality of the rotor system, For the damping of the rotor system, For the stiffness of the rotor system, For the turntable eccentricity, For rotational speed, For the vibration displacement of the rotor system, The vibration velocity of the rotor system. This represents the acceleration of the rotor system.

8. A system for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution, used to implement the method for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution as described in any one of claims 1-7, characterized in that, include: The prototype analysis module is used to perform finite element analysis on the entire fan section to obtain the strain energy ratio and prototype stiffness of each support point and rotor. The test equipment design and analysis module is used to perform finite element analysis on the fan component test equipment to obtain the model stiffness. The similarity ratio calculation module is communicatively connected to the prototype analysis module and the test instrument design analysis module, and is used to: calculate the stiffness similarity ratio based on the prototype stiffness and the model stiffness; and to perform a weighted allocation of the stiffness similarity ratio based on the strain energy ratio, thereby calculating the overall stiffness similarity ratio. Based on the dynamic distortion similarity relationship, and combined with the overall stiffness similarity ratio and mass similarity ratio, the natural frequency similarity ratio is calculated. The test execution and data acquisition module includes: a fan rotor component tester body, a drive system for the operation of the fan rotor component tester body, and a sensor system for acquiring vibration test data of the tester body in operation. The prediction module is communicatively connected to the similarity ratio calculation module and the test execution and data acquisition module. It is used to convert the natural frequencies in the vibration test data based on the natural frequency similarity ratio and predict the natural frequency of the fan section in the entire aero-engine.

9. The system for reproducing the vibration characteristics of an aero-engine based on a component testing device and strain energy distribution according to claim 8, characterized in that, The dynamic distortion similarity relationship is derived from the rotor system dynamic equations through equation analysis, and the specific relationship is as follows: in, The natural frequency similarity ratio, For stiffness similarity ratio, This represents the quality similarity ratio.

10. The aero-engine whole-engine vibration characteristic reproduction system based on component testing equipment and strain energy distribution according to claim 8, characterized in that, The strain energy ratio of each support point and rotor is obtained by dividing the strain energy of each support point and rotor by the total strain energy of the entire fan section. The formula for calculating the overall stiffness similarity ratio is: in, For stiffness similarity ratio, This represents the total strain energy of the entire fan section. The strain energy at the first fulcrum. The strain energy at the second fulcrum. The strain energy of the rotor, The stiffness similarity ratio of the first support point. The stiffness similarity ratio of the second support point. The stiffness similarity ratio of the rotor is given. The total strain energy of the fan section of the whole machine is the sum of the strain energy of the first support point, the strain energy of the second support point, and the strain energy of the rotor.

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