A method and device for testing performance of a rotor system excited by a vibration table

Abstract

The application discloses a kind of vibration table excitation's rotor system performance test method and device, belong to rotating machinery performance test technical field.Test method steps include: to the rotor system to be measured is resonant search;To rotor system is vibrated, static / dynamic force loading;In the performance parameter of load state measurement rotor system;It is calculated and peeled off the relative motion influence of the rotor to be measured and displacement sensor support, corrects rotor radial error movement value;Establish the performance state matrix of each working condition of rotor system;Form rotor system service suggestion parameter;Test device is mainly by electric exciter, electric exciter top end fixedly connected with motor, motor output end is connected with rotor system.This method and device to the active excitation and load loading of rotor system steady / unsteady working condition, can realize the rapid synchronous test of load state swing error, thermal elongation, static stiffness and the like, and provide guidance for the improvement optimization and service parameter setting of rotor system.

Description

Technical Field

[0001] This invention belongs to the field of rotating machinery performance testing technology, specifically relating to a method and apparatus for testing the performance of a rotor system excited by a vibration table. Background Technology

[0002] Rotor systems are widely used in aviation, aerospace, and high-end machine tool equipment, serving as core functional components to ensure high-performance operation of equipment. During the service operation of precision rotor systems, the rotors are subjected to both internal and external loads, exacerbating issues such as rotational errors, thermal expansion, and stress deformation, severely impacting their performance and even causing equipment failure. Therefore, comprehensive and systematic testing and analysis of rotor systems under complex operating conditions is essential.

[0003] Currently, a series of studies have been conducted both domestically and internationally on performance testing devices and methods for rotor systems. However, these studies generally focus on precision performance testing under no-load conditions or macroscopic operating state testing under load conditions. They cannot comprehensively simulate the loading conditions of the rotor system and test the rotor's precision performance under load. For example, in 2024, Xu Fangcheng et al. from Dalian University of Technology disclosed a stability testing system and method for a sliding bearing rotor system under impact load in patent CN119618650A. This system can apply multiple types and frequencies of impact loads through a vibration acceleration platform and identify the system's resonant frequency, modal characteristics, and potential failure modes. In 2025, Zeng Liping et al. from East China Jiaotong University disclosed a power transmission rotor vibration test bench with simulated multi-source excitation in patent CN119714762A, which can monitor the rotor's operating state under various excitation conditions. However, these inventions primarily focus on the macroscopic operating state of the rotor system and have not yet achieved performance testing of the rotor system's precision aspects, such as rotational error and thermal error, under load. In 2023, Wang Yunzhi et al. from Taiderex (Zhejiang) Precision Technology Co., Ltd. disclosed a machine tool spindle rotation error detection device in patent CN117428571A, which is used to improve the high-precision measurement of rotation error data in the spindle rotor system. In 2018, Ding Zhe et al. from Northeastern University disclosed a thermal analysis test bench for a disc-shaft connected rotor system and its thermal deformation measurement method in patent CN109342053B, which measures the thermal deformation of the rotor system. In 2022, Gao Jinhai et al. from Beijing University of Aeronautics and Astronautics disclosed a test device and method for testing the dynamic stiffness of the rotor support structure of an aero-engine in patent CN116929732A, which is used to improve the accuracy of dynamic stiffness testing of the rotor support structure of an aero-engine. However, the above inventions can only be tested under the no-load condition of the rotor system, and cannot actively stimulate and identify the unsteady working conditions of the rotor system, and cannot comprehensively assess the load performance level of the rotor system.

[0004] Therefore, there is an urgent need to propose a testing method and device that can actively stimulate stable or unstable operating conditions of the rotor system and achieve synchronous testing of accuracy such as rotational error, thermal elongation, and stiffness under load. Summary of the Invention

[0005] This invention provides a method and apparatus for testing the performance of a rotor system excited by a vibration table. It enables rapid and synchronous testing of properties such as rotational error, thermal elongation, and static stiffness under multiple operating conditions through active excitation and load loading of the rotor system in both stable and unstable conditions, providing guidance for the improvement, optimization, and service parameter setting of the rotor system.

[0006] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a method for testing the performance of a rotor system excited by a vibration table, comprising the following steps:

[0007] S1. Perform resonance search on the rotor system under test;

[0008] S2. Apply vibration and static / dynamic force loading to the rotor system;

[0009] S3. Measure the performance parameters of the rotor system under load;

[0010] S4. Calculate and isolate the relative motion influence between the rotor under test and the displacement sensor support, and correct the rotor radial error motion value.

[0011] S5. Establish the performance state matrix of the rotor system under various operating conditions;

[0012] S6. Formulate recommended parameters for rotor system service.

[0013] The present invention is further configured as follows:

[0014] S11. Determine the rationality of the sweep frequency parameter range based on the technical parameters of the electric vibrator and the mass of the rotor system;

[0015] S12. Sweep the rotor system from low frequency to high frequency according to the preset excitation displacement to determine the resonant frequency of the rotor system and find the potential stable state and critical state position of the rotor system under internal and external vibration excitation.

[0016] The present invention is further configured as follows:

[0017]

[0018] in, For the mass of the rotor being measured, This represents the upper limit of the frequency sweep range. The set sweep frequency displacement amplitude, The rated excitation force of the electric vibrator, The rated excitation speed of the electric vibrator.

[0019] The present invention is further configured as follows:

[0020] S21. Apply step load to the rotor system with a rated axial load of less than or equal to 80%; apply step load to the rotor system with a rated radial load of less than or equal to 80%; apply vibration excitation according to the sweep frequency range in S11, and avoid the resonant frequency in S12.

[0021] S22, Upgrade the strength under axial and radial force loading;

[0022] Each level differs by 20% of the maximum value of its corresponding rated axial load and rated radial load.

[0023] The present invention is further configured as follows:

[0024] S31. After upgrading the intensity according to step S22, run for 5 minutes;

[0025] S32. Measure the radial and axial displacements of the rotor system under vibration and static / dynamic force loading conditions;

[0026] S33. Test and record the axial elongation of the rotor system in different stages of cold and hot states.

[0027] S34. Under static loading, test and calculate the linear ratio of the axial loading force to the radial loading force to the corresponding directional displacement response of the rotor system.

[0028] The present invention is further configured as follows:

[0029] S4. Calculate and isolate the relative displacement deviation caused by asynchronous motion, and correct the rotor radial error motion value; in terms of angle When rotating, the ideal Cartesian coordinates of the rotor system are:

[0030]

[0031] in, and These represent the actual positions of the center of the rotation axis of the rotor system under ideal conditions. The base circle radius; however, due to manufacturing and assembly errors in the rotor system, when there is no relative displacement between the displacement sensor bracket and the rotor system, the actual position of the center of the rotor system's rotation axis ( ) )for:

[0032]

[0033]

[0034] in, It is the vector of error motion; the radial error motion component of the rotor system. It is the projection of the error vector onto the radial unit vector:

[0035]

[0036] During the loading test, due to the stiffness issue of the cantilever structure connecting the displacement sensor bracket and the rotor system, relative motion occurs between them during the test, resulting in an additional relative displacement deviation in the calculation of the rotor's radial error motion. Therefore, considering both the radial error component caused by the rotor system's own manufacturing and assembly errors, and the influence of the relative motion between the tested rotor and the displacement sensor bracket, the corrected radial error motion value of the rotor system is:

[0037]

[0038] in, and These represent the relative displacement deviations of the rotor system in the two directions mentioned above, calculated as follows:

[0039]

[0040]

[0041] in, and These represent the accelerations of the displacement sensor bracket in the directions perpendicular to and parallel to the horizontal plane, respectively. and These represent the accelerations of the rotor support frame in the directions perpendicular to and parallel to the horizontal plane, respectively.

[0042] The present invention is further configured as follows:

[0043] S51. Based on the three orthogonal dimensions of axial force, radial force, and vibration excitation, and associated with the relative displacement deviation, axial elongation, and linear ratio of directional displacement response, a three-dimensional working condition matrix is ​​constructed and grouped according to the number of upgrades.

[0044] S52. Generate a global performance cloud map based on multiple sets of three-dimensional working condition matrices using an interpolation algorithm, and identify regions of parameter mutation.

[0045] The present invention is further configured as follows:

[0046] S6. Based on the rotational error motion state of the rotor system under precise load conditions, accurately formulate the optimal operating parameters suitable for the rotor; based on the load deformation in the three-dimensional operating condition matrix, set load limits and determine the magnitude of the safe axial force and radial force when the rotor is working; based on the axial thermal elongation record, optimize the rotor thermal management strategy, increase forced cooling or optimize the bearing preload.

[0047] A performance testing device for a rotor system excited by a vibration table includes an electric vibrator, a motor fixedly connected to the top of the electric vibrator, a rotor system connected to the output end of the motor, a rotor support frame disposed on the side of the rotor system away from the motor, a radial electric cylinder mounted on the side of the rotor support frame away from the motor, a first axial electric cylinder disposed on the side of the radial electric cylinder away from the rotor support frame, and a second axial electric cylinder disposed parallel to the side of the first axial electric cylinder, the first axial electric cylinder, the second axial electric cylinder, and the radial electric cylinder being fixedly connected to the cylinder support frame, the first axial electric cylinder and the second axial electric cylinder being disposed parallel to the axis of the rotor system, and the radial electric cylinder being disposed perpendicular to the axis of the rotor system.

[0048] The present invention further illustrates that pressure sensors are installed at the output ends of the first axial electric cylinder, the second axial electric cylinder, and the radial electric cylinder. A radial loading support is connected to one side of a set of pressure sensors installed at the output end of the radial electric cylinder. The two sets of pressure sensors installed at the output ends of the first axial electric cylinder and the second axial electric cylinder are connected to a set of axial loading supports. A connecting bracket is provided at the top of the axial loading support. The axial loading support is movably connected to the connecting bracket. The radial loading support is movably connected to the connecting bracket. The connecting bracket is fixedly connected to the support.

[0049] The present invention further illustrates that the rotor system is clamped and fixed with a main shaft clamp, the connecting bracket is fixed to the top of the main shaft clamp with bolts, and a displacement sensor bracket is fixed to the front of the connecting bracket with bolts. The displacement sensor bracket is provided with a first displacement sensor, a second displacement sensor, a third displacement sensor, and a fourth displacement sensor in a direction perpendicular to the standard test bar and parallel to and perpendicular to the horizontal plane, respectively. The displacement sensor bracket is provided with a fifth displacement sensor in a direction parallel to the standard test bar.

[0050] The present invention further illustrates that a standard test bar is provided on the side of the rotor system near the second axial electric cylinder, the standard test bar being arranged parallel to the second axial electric cylinder, and a displacement sensor is installed on the side of the connecting bracket near the second axial electric cylinder, the displacement sensor being arranged parallel to the standard test bar.

[0051] The present invention further illustrates that a first magnetic vibration sensor is installed at the top of the bracket, a second magnetic vibration sensor is installed at the top of the connecting bracket, a fourth magnetic vibration sensor is installed at the top of the electric vibrator, and a third magnetic vibration sensor is installed on the side of the bracket near the motor. A displacement sensor bracket is provided around the outer sides of the first magnetic vibration sensor, the displacement sensor, the pressure sensor, the second magnetic vibration sensor, the third magnetic vibration sensor, and the fourth magnetic vibration sensor.

[0052] Compared with the prior art, the beneficial effects achieved by the present invention are:

[0053] (1) This invention proposes a method and device for testing the performance of a rotor system excited by a vibration table. It can quickly test multiple parameters such as rotational error, thermal elongation, and static stiffness of the rotor system under load. It can effectively solve the problems of no-load testing being unable to reflect the actual working performance of the rotor system, long test replacement time, and changes in test accuracy benchmark. It can truly reflect the actual performance of the rotor system and significantly reduce the test time cost and the consumption of manpower and material resources.

[0054] (2) A method and device for testing the performance of a rotor system excited by a vibration table were invented, which realizes the active excitation and intelligent identification of the performance degradation of the rotor system under the resonant unstable working condition. Then, the actual service parameters can be set according to the established rotor system working condition matrix. This can effectively solve the problems of lack of load performance testing capability and test results that cannot guide actual application, and effectively improve the testing efficiency and the availability of results. Attached Figure Description

[0055] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0056] Figure 1 This is a flowchart of a multi-parameter performance testing method for a rotor system excited by a vibration table;

[0057] Figure 2 This is a schematic diagram of a multi-parameter performance testing device for a rotor system excited by a vibration table.

[0058] Figure 3 This is a top view schematic diagram of a part of the multi-parameter performance testing device for a rotor system excited by a vibration table;

[0059] Figure 4 This is a side view schematic diagram of a part of the multi-parameter performance testing device for a rotor system excited by a vibration table;

[0060] In the diagram: 1. Electric vibrator; 2. First axial electric cylinder; 3. Second axial electric cylinder; 4. Radial electric cylinder; 5. Rotor support frame; 6. First magnetic vibration sensor; 7. Motor; 8. Rotor system; 9. Axial loading support; 10. First displacement sensor; 11. Second displacement sensor; 12. Third displacement sensor; 13. Fourth displacement sensor; 14. Fifth displacement sensor; 15. Standard probe; 16. Displacement sensor bracket; 17. Pressure sensor; 18. Second magnetic vibration sensor; 19. Radial loading support; 20. Connecting bracket; 21. Third magnetic vibration sensor; 22. Spindle clamp. Detailed Implementation

[0061] The following detailed, non-limiting description of the technical solution of the present invention, in conjunction with preferred embodiments and accompanying drawings, is provided. Obviously, the described embodiments are merely some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0062] Example 1, see Figure 1 Taking the performance test of the spindle of a CNC machining machine as an example, the specific steps of the test are as follows:

[0063] S1. Perform resonance search on the rotor system under test;

[0064] S11. Determine the rationality of the sweep frequency parameter range based on the technical parameters of the electric vibrator 1 and the mass of the spindle system; wherein, the determination of the rationality of the sweep frequency parameter range is obtained through a range rationality algorithm, the formula of which is:

[0065]

[0066] in, For the mass of the spindle being measured, This represents the upper limit of the frequency sweep range. The set sweep frequency displacement amplitude, The rated excitation force of the electric vibrator 1, The rated excitation speed of the electric vibrator.

[0067] S12. Sweep the spindle system from low frequency to high frequency according to the sweep frequency parameters to determine the resonant frequency of the spindle system and find the potential stable state and critical state position of the spindle system under internal and external vibration excitation.

[0068] Based on the technical parameters of the electric vibrator 1 and the mass of the spindle system, the sweep frequency range was finally determined to be 5~250Hz. With a constant sweep frequency displacement of 2mm, perpendicular to the horizontal plane, the frequency was swept from low frequency to high frequency at different speeds to find the resonant frequency; the stable state and critical state of the spindle system under internal and external vibration excitation were determined.

[0069] S2. Apply vibration and static / dynamic force loading to the rotor system;

[0070] S21. Apply step load to the spindle system with a rated axial load of less than or equal to 80% (4000N); apply step load to the spindle system with a rated radial load of less than or equal to 80% (3000N); apply vibration excitation according to the sweep frequency range in S11, and avoid the resonant frequency in S12.

[0071] S22, Upgrade the strength under axial and radial force loading;

[0072] Each level differs by 20% of the maximum value of its corresponding rated axial load and rated radial load.

[0073] Axial force, radial force, and vibration excitation are applied simultaneously. The axial force is applied in steps with a maximum value of 3200N through the first axial electric cylinder 2 and the second axial electric cylinder 3. The radial force is applied in steps with a maximum value of 2400N through the radial electric cylinder 4, perpendicular to the spindle axis. The vibration excitation is applied in steps based on the frequency sweep range determined in step one, and the resonant frequency position is marked. The increment of each loading step is 800N and 600N, respectively. After each loading step, the system needs to be stabilized for 5 minutes before data is collected.

[0074] S3. Measure the performance parameters of the rotor system under load;

[0075] S31. After upgrading the intensity according to step S22, run for 5 minutes:

[0076] S32. Measure the radial and axial displacements of the spindle system under vibration and static / dynamic force loading conditions.

[0077] S33. Test and record the axial elongation of the spindle system in different stages of cold and hot states.

[0078] S34. Under static loading, test and calculate the linear ratio of the axial loading force to the radial loading force in the direction of displacement response of the spindle system.

[0079] While loading, the spindle system's rotational error, thermal elongation, and static stiffness are tested. Rotational error testing: The radial displacement change of the spindle is measured using the first displacement sensor 10, the second displacement sensor 11, the third displacement sensor 12, and the fourth displacement sensor 13. The fifth displacement sensor 14, along with the first magnetic vibration sensor 6 and the second magnetic vibration sensor 18, monitors the relative displacement deviation caused by the asynchronous movement of the displacement sensor bracket 16 and the spindle system during loading. This deviation is eliminated and corrected when calculating the rotational error, achieving radial / axial error motion testing under vibration and static / dynamic force loading conditions. Thermal elongation testing: The axial elongation of the spindle is measured and recorded using the first displacement sensor 10 at different stages of the spindle system's cold and hot states. Static stiffness testing: Under static loading, the linear ratio of the axial loading force to the radial loading force and the spindle system's displacement response in the corresponding directions is tested and calculated.

[0080] S4. Calculate and isolate the relative motion influence between the rotor under test and the displacement sensor support, and correct the rotor radial error motion value.

[0081] Calculate the relative displacement deviation of the rotor system in two directions, perpendicular and parallel to the horizontal plane. and :

[0082]

[0083]

[0084] in, and The accelerations of the displacement sensor bracket in the vertical and horizontal directions are respectively measured by the first magnetic vibration sensor 6. and These are the accelerations of the main shaft support frame in the vertical and horizontal directions, respectively, measured by the second magnetic vibration sensor 18. The corrected radial error motion value of the rotor system is calculated:

[0085]

[0086] S5. Establish the performance state matrix of the rotor system under various operating conditions;

[0087] S51. Based on the three orthogonal dimensions of axial force, radial force, and vibration excitation, and associated with the relative displacement deviation, axial elongation, and linear ratio of directional displacement response, a three-dimensional working condition matrix is ​​constructed and grouped according to the number of upgrades.

[0088] S52. Generate a global performance cloud map based on multiple sets of three-dimensional working condition matrices using an interpolation algorithm, and identify regions of parameter mutation.

[0089] A three-dimensional working condition matrix is ​​constructed using axial force, radial force, and vibration amplitude as three orthogonal dimensions, with each dimension divided according to the number of step loading cycles. The associated data for each matrix unit are: peak-to-peak value of rotational error, thermal elongation, and load deformation. A global performance cloud map is generated using an interpolation algorithm to identify regions of parameter abrupt changes.

[0090] S6. Formulate recommended parameters for rotor system service;

[0091] Based on the precision requirements of the machined parts and the spindle system rotation error motion status table, the rotation speed is precisely determined, and appropriate feed rate, depth of cut and other parameters are set for the machine tool according to the cutting force calculation formula; load limits are set according to the load deformation in the three-dimensional working condition matrix (e.g., not greater than 2000N); if the thermal elongation exceeds 50 μm, it is recommended to increase forced cooling and optimize the bearing preload.

[0092] Example 2, see Figure 2-4A performance testing device for a rotor system excited by a vibration table includes an electric vibration table excitation system, a static and dynamic force loading system, and a performance testing system. The electric vibration table excitation system includes an electric vibrator 1, with a motor 7 fixedly connected to its top. A rotor system 8 is connected to the output end of the motor 7, and a rotor support frame 5 is mounted on the side of the rotor system 8 away from the motor 7. The rotor system 8 is the workpiece being tested. The static and dynamic force loading system includes a radial electric cylinder 4, a pressure sensor 17, a first axial electric cylinder 2, a second axial electric cylinder 3, a radial loading support 19, and an axial loading support 9. The radial electric cylinder 4 is mounted on the side of the rotor support frame 5 away from the motor 7. The first axial electric cylinder 2 is mounted on the side of the radial electric cylinder 4 away from the rotor support frame 5. The second axial electric cylinder 3 is arranged parallel to the first axial electric cylinder 2 on the side of the first axial electric cylinder 2. The first axial electric cylinder 2, the second axial electric cylinder 3, and the radial electric cylinder 4 are fixedly connected to the rotor support frame 5. The first axial electric cylinder 2 and the second axial electric cylinder 3 are arranged parallel to the axis of the rotor system 8, and the radial electric cylinder 4 is arranged perpendicular to the axis of the rotor system 8. The output ends of the first axial electric cylinder 2, the second axial electric cylinder 3, and the radial electric cylinder 4 are all equipped with pressure sensors 17. A radial loading support 19 is connected to one side of a set of pressure sensors 17 installed at the output end of the radial electric cylinder 4. The two sets of pressure sensors 17 installed at the output ends of the first axial electric cylinder 2 and the second axial electric cylinder 3 are connected to a set of axial loading supports 9. The pressure sensors 17 are used to monitor the magnitude of the force load. The radial electric cylinder 4 is used to apply force to the radial loading support 19. The first axial electric cylinder 2 and the second axial electric cylinder 3 are used to apply force to the axial loading support 9, thereby realizing the axial and radial force loading of the rotor system 8. The performance testing system includes a first magnetic vibration sensor 6, a second magnetic vibration sensor 18, a first displacement sensor 10, a second displacement sensor 11, a third displacement sensor 12, a fourth displacement sensor 13, a fifth displacement sensor 14, a displacement sensor bracket 16, a standard test bar 15, a connecting bracket 20, a third magnetic vibration sensor 21, a pressure sensor 17, and the connecting bracket 20 are connected by bolts; the axial loading support 9 is provided with a connecting bracket 20 at its top end, the axial loading support 9 is movably connected to the connecting bracket 20, the radial loading support 19 is movably connected to the connecting bracket 20, and the connecting bracket 20 is fixedly connected to the rotor support frame 5.A standard probe 15 is provided on the side of the rotor system 8 near the second axial electric cylinder 3. The standard probe 15 is arranged parallel to the second axial electric cylinder 3 and is clamped by the rotor system 8. The rotor system 8 is clamped and fixed to the main shaft clamp 22. The connecting bracket 20 is fixed to the top of the main shaft clamp 22 by bolts. The front of the connecting bracket 20 is fixed to the displacement sensor bracket 16 by bolts. The first displacement sensor 10, the second displacement sensor 11, the third displacement sensor 12, and the fourth displacement sensor 13 are respectively arranged on the displacement sensor bracket 16 in a direction perpendicular to the standard probe 15 and parallel and perpendicular to the horizontal plane. A fifth displacement sensor 14 is arranged on the displacement sensor bracket 16 parallel to the standard probe 15. The first displacement sensor 10, the second displacement sensor 11, and the third displacement sensor 14 are respectively arranged on the displacement sensor bracket 16 in a direction perpendicular to the standard probe 15 and parallel and perpendicular to the horizontal plane. The system includes a fourth displacement sensor 13, a fifth displacement sensor 14 mounted parallel to the standard test bar 15 on the displacement sensor bracket 16, a first magnetic vibration sensor 6 mounted on the top of the rotor support frame 5, a second magnetic vibration sensor 18 mounted on the top of the connecting bracket 20, and a third magnetic vibration sensor 21 mounted on the side of the rotor support frame 5 near the motor 7. The temperature sensor is used to monitor the temperature rise of the rotor system 8 under multi-load conditions in real time. The first displacement sensor 10 is used to calculate and analyze the rotational error and stiffness of the rotor system 8 under multi-load conditions in real time. The first magnetic vibration sensor 6 and the second magnetic vibration sensor 18 are used to monitor the relative position change caused by the asynchronous movement of the test device and the rotor system 8 during loading, and this effect is removed when calculating the rotational error through a correction compensation algorithm, reflecting the true performance of the rotor system 8. The third magnetic vibration sensor 21 is used to acquire the dynamic characteristics of the rotor system 8 at different speeds.

[0093] 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 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 the present invention.

Claims

1. A method for testing the performance of a rotor system excited by a vibration table, characterized in that, Includes the following steps: S1. Perform resonance search on the rotor system under test; S2. Apply vibration and static / dynamic force loading to the rotor system; The vibration and static / dynamic force loading of the rotor system includes: S21. Apply step load to the rotor system with a rated axial load of less than or equal to 80%; apply step load to the rotor system with a rated radial load of less than or equal to 80%; apply vibration excitation according to the sweep frequency range in S11, and avoid the resonant frequency in S12. S22, Upgrade the strength under axial and radial force loading; Each level differs by 20% of the maximum value of its corresponding rated axial load and rated radial load. S3. Measure the performance parameters of the rotor system under load; The synchronous measurement of the rotor system's performance parameters under loading conditions includes: S31. After upgrading the intensity according to step S22, run for 5 minutes: S32. Measure the radial and axial displacements of the rotor system under vibration and static / dynamic force loading conditions; S33. Test and record the axial elongation of the rotor system in different stages of cold and hot states. S34. Under static loading, test and calculate the linear ratio of the axial loading force to the radial loading force to the corresponding directional displacement response of the rotor system. S4. Calculate and isolate the relative motion influence between the rotor under test and the displacement sensor support, and correct the rotor radial error motion value. In S4, the relative motion influence between the measured rotor and the displacement sensor support is calculated and isolated. This relative motion influence refers to the relative displacement deviation caused by asynchronous motion, and the rotor radial error motion value is corrected. (The remaining text appears to be incomplete and requires further context.) When rotating, the ideal Cartesian coordinates of the rotor system are: ； in, and These represent the actual positions of the center of the rotation axis of the rotor system under ideal conditions. The base circle radius; however, due to manufacturing and assembly errors in the rotor system, when there is no relative displacement between the displacement sensor bracket and the rotor system, the actual position of the center of the rotor system's rotation axis ( ) )for: ； ； in, It is the vector of error motion; the radial error motion component of the rotor system. It is the projection of the error vector onto the radial unit vector: ； During the loading test, due to the stiffness issue of the cantilever structure connecting the displacement sensor bracket and the rotor system, relative motion occurs between them during the test, resulting in an additional relative displacement deviation in the calculation of the rotor's radial error motion. Therefore, considering both the radial error component caused by the rotor system's own manufacturing and assembly errors, and the influence of the relative motion between the tested rotor and the displacement sensor bracket, the corrected radial error motion value of the rotor system is: ； in, and These represent the relative displacement deviations of the rotor system in the two directions mentioned above, calculated as follows: ； ； in, and These represent the accelerations of the displacement sensor bracket in the directions perpendicular to and parallel to the horizontal plane, respectively. and These are the accelerations of the rotor support frame in the directions perpendicular to and parallel to the horizontal plane, respectively. S5. Establish the performance state matrix of the rotor system under various operating conditions; The establishment of the performance state matrix of the rotor system under various operating conditions includes: S51. Based on the three orthogonal dimensions of axial force, radial force, and vibration excitation, and associated with the relative displacement deviation, axial elongation, and linear ratio of directional displacement response, a three-dimensional working condition matrix is ​​constructed and grouped according to the number of upgrades. S52. Generate a global performance cloud map based on multiple sets of three-dimensional working condition matrices using an interpolation algorithm, and identify areas of parameter mutation. S6. Formulate recommended parameters for rotor system service.

2. The method for testing the performance of a rotor system excited by a vibration table according to claim 1, characterized in that, In S1, the resonant search of the rotor system under test includes: S11. Determine the rationality of the sweep frequency parameter range based on the technical parameters of the electric vibrator and the mass of the rotor system; S12. According to the sweep frequency parameter range, sweep the rotor system from low frequency to high frequency at different speeds to determine the resonant frequency of the rotor system and find the potential stable state and critical state position of the rotor system under internal and external vibration excitation.

3. The method for testing the performance of a rotor system excited by a vibration table according to claim 2, characterized in that, In S11, the determination of the reasonableness of the frequency sweep parameter range is obtained through a range reasonableness algorithm, the formula of which is: ； in, For the mass of the rotor being measured, This represents the upper limit of the frequency sweep range. The set sweep frequency displacement amplitude, The rated excitation force of the electric vibrator, The rated excitation speed of the electric vibrator.

4. The method for testing the performance of a rotor system excited by a vibration table according to claim 1, characterized in that, In S6, the recommended service parameters for the rotor system include: Based on the precise measurement of the rotor system's rotational error motion state under load conditions, the optimal operating parameters for the rotor are accurately determined; based on the load deformation in the three-dimensional operating condition matrix, load limits are set, and the magnitudes of the safe axial and radial forces during rotor operation are determined; based on the axial thermal elongation records, the rotor thermal management strategy is optimized, and forced cooling or bearing preload is increased or optimized.

5. A performance testing device for a rotor system excited by a vibration table, used to implement the method described in any one of claims 1 to 4, characterized in that: The system includes an electric vibrator (1), a motor (7) fixedly connected to the top of the electric vibrator (1), a rotor system (8) connected to the output end of the motor (7), a rotor support frame (5) provided on the side of the rotor system (8) away from the motor (7), a radial electric cylinder (4) installed on the side of the rotor support frame (5) away from the motor (7), a first axial electric cylinder (2) provided on the side of the radial electric cylinder (4) away from the rotor support frame (5), a second axial electric cylinder (3) arranged parallel to the side of the first axial electric cylinder (2), the first axial electric cylinder (2), the second axial electric cylinder (3), and the radial electric cylinder (4) fixedly connected to the rotor support frame (5), and the first axial electric cylinder (2) and the second axial electric cylinder (3) arranged parallel to the axis of the rotor system (8). The cylinder (4) is set perpendicular to the axis of the rotor system (8). Pressure sensors (17) are installed at the output ends of the first axial electric cylinder (2), the second axial electric cylinder (3), and the radial electric cylinder (4). A radial loading support (19) is connected to one side of a set of pressure sensors (17) installed at the output end of the radial electric cylinder (4). The two sets of pressure sensors (17) installed at the output ends of the first axial electric cylinder (2) and the second axial electric cylinder (3) are connected to a set of axial loading supports (9). A connecting bracket (20) is provided at the top of the axial loading support (9). The axial loading support (9) is movably connected to the connecting bracket (20). The radial loading support (19) is movably connected to the connecting bracket (20). The connecting bracket (20) is fixedly connected to the rotor support frame (5).

6. The rotor system performance testing device excited by a vibration table according to claim 5, characterized in that: A standard test bar (15) is provided on the side of the rotor system (8) near the second axial electric cylinder (3). The standard test bar (15) is arranged parallel to the second axial electric cylinder (3) and is clamped by the rotor system (8). The rotor system (8) is clamped and fixed to the main shaft clamp (22). The connecting bracket (20) is fixed to the top of the main shaft clamp (22) by bolts. A displacement sensor bracket (16) is fixed to the front of the connecting bracket (20) by bolts. The displacement sensor bracket (16) is perpendicular to the standard test bar (15) and to the horizontal plane. A first displacement sensor (10), a second displacement sensor (11), a third displacement sensor (12), and a fourth displacement sensor (13) are respectively set in parallel and perpendicular directions. A fifth displacement sensor (14) is set on the displacement sensor bracket (16) parallel to the standard test bar (15). A first magnetic vibration sensor (6) is installed at the top of the rotor support frame (5). A second magnetic vibration sensor (18) is installed at the top of the connecting bracket (20). A third magnetic vibration sensor (21) is installed on the side of the rotor support frame (5) near the motor (7).

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