Aero-engine rotor vibration mode test device and test method

Abstract

The invention discloses an aero-engine rotor vibration mode test device and test method, and belongs to the technical field of aero-engine rotors, the aero-engine rotor vibration mode test device comprises two mounting seats, an adapter plate, a heightening plate and a test platform, the mounting seats are symmetrically mounted on a rotor, and the adapter plate is mounted on the test platform; the mounting base comprises a bottom plate, a mounting plate and a reinforcing plate, the bottom plate and the mounting plate are perpendicular to each other to form a T-shaped structure, the mounting plate is used for supporting the rotor, the reinforcing plate is located on the side, away from the rotor, of the mounting plate to support the mounting plate, and the bottom plate is connected with the test platform through bolts. According to the invention, the actual installation state of the aero-engine rotor can be simulated, and the technical problem that the test result is interfered by coupling vibration between the test device and the rotor in the rotor modal test can be avoided.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine rotors, and in particular to an aircraft engine rotor vibration modal test device and a test method. Background Art

[0002] The general specifications for aviation gas turbine engines (GJB241-87, GJB242-87) require that the engine should not experience destructive vibration at all speeds and powers in the entire operating range, including steady state and transient state. The dynamic characteristics of the installation system equipped with the engine should meet the following requirements: the natural frequency of all harmful vibration modes excited by the residual unbalance of the rotor should not be higher than 80% of the slow speed. Before the endurance test, the rotor vibration characteristic test and analysis should be completed.

[0003] The vibration modal test of aircraft engine rotors can be divided into free state modal, simulated installation state modal and actual installation state modal according to the different states of the test piece. In order to measure the vibration characteristics of aircraft engine rotors in real state, modal test should be carried out in actual installation state in theory. However, in this state, the rotor is blocked by various casings, and it is very difficult to directly excite it and measure its response. Therefore, when developing aircraft engines, rotor modal test is generally not carried out directly in actual installation state, but in simulation of its actual installation state. The simulated installation state is to simulate the boundary conditions of the actual installation state of the engine to carry out rotor modal test. This state has very high requirements for the test device.

[0004] The commonly used elastic support structure of aero-engine bearings is referred to as bearing elastic support, and the mounting edge of the bearing elastic support is connected to the casing by bolts. In order to simulate this boundary condition, a reasonable test device needs to be designed. In addition to meeting the boundary conditions, the device should also pay attention to the natural frequency of the device being far away from the rotor frequency response range of concern, to avoid the coupling vibration phenomenon between the test device and the rotor during the test, which seriously interferes with the modal test results and affects the identification of the rotor vibration characteristics. Therefore, it is necessary to optimize the design of the transition section. Summary of the invention

[0005] The present invention provides an aero-engine rotor vibration modal test device and a test method to simulate the actual installation state of the engine rotor and avoid the technical problem of coupling vibration between the test device and the rotor interfering with the test structure in the modal test.

[0006] According to one aspect of the present invention, there is provided an aircraft engine rotor vibration modal test device, comprising a mounting seat and a test platform, wherein two mounting seats are symmetrically installed on the test platform, wherein the mounting seat comprises a base plate, a mounting plate and a reinforcing plate, wherein the base plate and the mounting plate are perpendicular to each other to form a T-shaped structure, wherein the mounting plate is used to support the rotor, wherein the reinforcing plate is located on a side of the mounting plate away from the rotor to support the mounting plate, and wherein the base plate is connected to the test platform by bolts.

[0007] Optionally, the base plate is provided with bolts on both sides of the mounting plate for connection with the test platform.

[0008] Optionally, an adapter plate is arranged between the mounting plate and the bearing spring of the rotor, and the adapter plate is fixed to the mounting plate. Bolt holes are opened on the adapter plate. Multiple groups of bolt holes are arranged according to the distance from the rotor rotation center axis, and each group of bolt holes includes multiple bolts evenly distributed circumferentially around the rotation center.

[0009] Optionally, a center hole is formed on the mounting plate along the axial direction of the rotor to match the radial dimension of the rotor bearing end.

[0010] Optionally, the bolts connecting the base plate and the test platform are T-bolts, and a plurality of slide grooves matching the ends of the T-bolts are provided in parallel on the test platform.

[0011] Optionally, a heightening plate is provided between the base plate and the test platform, a weight-reducing groove is provided at the center of the heightening plate, and through holes for T-bolts to pass through are provided at the edge of the heightening plate.

[0012] Optionally, a cut corner is provided at one end of the mounting plate away from the base plate.

[0013] Optionally, a lifting eye hole is provided at one end of the mounting plate away from the base plate, and the lifting eye hole is located at the symmetrical center of the mounting plate.

[0014] According to another aspect of the present invention, there is also provided an aircraft engine rotor vibration modal test method, which comprises the following steps: S100, preparation work, selecting device components suitable for the test rotor, including a heightening plate and an adapter plate; S200, device assembly, the mounting base is connected to the test platform through T-slot bolts to ensure the rigidity of the test device and avoid coupled vibration; S300, install heightening plates as needed to ensure that the device can adapt to the needs of rotors with different radial sizes; S400, rotor installation, connect the spring support of the rotor bearing to the adapter plate, the adapter plate is connected to the installation through bolt holes evenly distributed around the circumference, ensure that the connection is firm and not loose, adjust the height and configuration of the test device to ensure the matching of the rotor and the device; S500, Excitation and testing, install the vibration sensor and excitation system, set the excitation signal frequency range, start the excitation system to excite the rotor mode, and collect vibration response data; S600, data acquisition and analysis, collects vibration data and performs spectrum analysis, identifies the rotor's natural frequency, vibration mode and damping ratio, and evaluates modal characteristics for comparison and verification with design or simulation data.

[0015] In summary, the present application includes at least one of the following beneficial technical effects: The configuration of the mounting base, adapter plate, heightening plate and rotor of the test device makes the overall device have higher stability and rigidity. The base plate and mounting plate in the mounting base are combined through a mutually perpendicular T-shaped structure to enhance the vertical and horizontal rigidity. In particular, during the rotor excitation process, by optimizing the connection method between the base plate and the mounting plate, it is ensured that the rotor will not induce unnecessary structural vibration under excitation, thereby effectively reducing the coupled vibration with the test piece. In addition, the reinforcing plate set on the mounting plate plays a supporting role, further increasing the rigidity of the device and avoiding frequency drift and vibration interference caused by uneven load or deformation of the mounting plate. The overall structure has enhanced rigidity and more uniform support, which avoids the resonance of the test device itself or the coupled vibration between it and the rotor during the test, ensuring the test accuracy of the vibration mode and the reliability of the data.

[0016] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 It is a structural schematic diagram of an aircraft engine rotor vibration modal test device of the present invention; Figure 2 It is a structural schematic diagram of the mounting seat of the present invention; Figure 3 is a side view of the mounting base of the present invention; Figure 4 It is a structural schematic diagram of the mounting plate of the present invention.

[0018] Legend: 1. Bearing spring support; 2. Adapter plate; 3. Mounting seat; 4. Slide groove; 5. Test platform; 6. Mounting plate; 7. Reinforcement plate; 8. Bottom plate; 9. Cutting angle; 10. Lifting eye hole; 11. Heightening plate. DETAILED DESCRIPTION

[0019] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0020] The following is combined with Figure 1-4 This application is described in further detail.

[0021] The embodiments of the present application disclose an aero-engine rotor vibration modal test device and a test method.

[0022] Reference Figure 1 The aircraft engine rotor vibration modal test device includes a mounting seat 3, an adapter plate, a heightening plate 11 and a test platform. Two mounting seats 3 are symmetrically installed on the rotor. The mounting seat 3 includes a bottom plate 8, a mounting plate 6 and a reinforcing plate 7. The bottom plate 8 and the mounting plate 6 are perpendicular to each other to form a T-shaped structure. The mounting plate 6 is used to support the rotor. The reinforcing plate 7 is located on the side of the mounting plate 6 away from the rotor to support the mounting plate 6. The bottom plate 8 is connected to the test platform by bolts.

[0023] The test platform provides the basic support for the device to ensure that the entire system is placed firmly. Above the test platform, two mounting seats 3 are installed in a symmetrical manner to form a symmetrical support structure to ensure the balance and stability of the rotor in the entire device. Each mounting seat 3 includes three key parts: a base plate 8, a mounting plate 6, and a reinforcing plate 7. The base plate 8 and the mounting plate 6 are connected vertically to form a T-shaped structure. The design of this T-shaped structure greatly enhances the rigidity of the device. The main function of the base plate 8 is to provide a solid basic support, which is fixedly connected to the test platform by bolts to ensure that the entire device is not displaced or vibrated by external interference. The mounting plate 6, as the main part supporting the rotor, plays a role in firmly fixing the rotor and ensuring that the rotor works stably during the test. The function of the reinforcing plate 7 is to improve the bending and deformation resistance of the mounting plate 6, and ensure that the mounting plate 6 can withstand a large load without deformation during the test. The reinforcing plate 7 is connected vertically to the mounting plate 6 and the base plate 8. This design helps to enhance the overall rigidity and structural stability of the device. Specifically, one surface of the reinforcing plate 7 is fixedly connected to the side of the mounting plate 6 away from the rotor, and the other surface is vertically connected to the bottom plate 8, providing additional support to prevent the mounting plate 6 from bending or deforming when bearing load. Through this vertical connection method, the reinforcing plate 7 effectively improves the bearing capacity of the entire device, avoids unnecessary structural deviation, and ensures the stability of the test process.

[0024] Compared with the traditional L-shaped mounting base 3, the base plate 8 and the mounting plate 6 of the T-shaped structure are connected vertically, and it can distribute the load more evenly when subjected to force. In the L-shaped structure, the connection between the mounting plate 6 and the base plate 8 can usually only withstand relatively local pressure, which will cause a large stress concentration under high load or dynamic load, which may cause local deformation or instability. The T-shaped structure can better disperse the vibration force from the rotor due to a laterally longer base plate 8, and through the vertical connection with the mounting plate 6, the force-bearing surface is more extensive and uniform, avoiding the problem of local force concentration that may occur in the L-shaped structure. Secondly, the support surface of the T-shaped structure is more stable and can provide stronger bending stiffness. Under stress, the force points of the T-shaped structure are more dispersed, which can effectively resist bending deformation, avoiding the defect that the L-shaped structure is prone to distortion or uneven deformation when subjected to vibration or external force due to only one vertical support point.

[0025] Reference Figure 1 and Figure 2 , the base plate 8 is provided with bolts for connecting with the test platform on both sides of the mounting plate 6. By arranging bolts on both sides, bidirectional support of the base plate 8 and the test platform can be achieved, so that the connection between the base plate 8 and the test platform is more firm and the force is more uniform. In this way, the whole device can better disperse the dynamic load generated by the vibration of the rotor, avoiding the local stress concentration and deformation problems that may be caused by relying on only a single connection point. Compared with the design of arranging bolts only on one side of the mounting plate 6, the double-sided bolt connection can effectively prevent the uneven deformation caused by the single-sided force, especially under high load and high vibration frequency, it can significantly improve the overall stiffness of the structure and reduce the deformation and instability of the system. Although the design of the single-sided bolt can save materials and simplify the structure, it will make the connection between the base plate 8 and the test platform more prone to uneven force, which is easy to cause local distortion or deformation of the structure, affecting stability and test accuracy. The design of the double-sided bolt ensures the uniform distribution of force, making the overall structure more solid and stable, and can better cope with the impact of dynamic loads and vibration on the test platform, providing higher reliability and accuracy.

[0026] Reference Figure 2 and Figure 3, an adapter plate 2 is arranged between the mounting plate 6 and the bearing spring support 1 of the rotor, the adapter plate 2 is fixed on the mounting plate 6, and bolt holes are opened on the adapter plate 2. The bolt holes are arranged in multiple groups according to the distance from the rotor rotation center axis, and each group of bolt holes includes multiple bolts uniformly distributed circumferentially around the rotation center. The adapter plate 2 arranged between the mounting plate 6 and the bearing spring support 1 of the real rotor is a key component in the test device, and they jointly undertake the tasks of supporting, transferring loads and simulating actual working conditions during the rotor test. The adapter plate 2 is fixed on the mounting plate 6 and is firmly connected to the mounting plate 6 through the bolt holes, ensuring that the adapter plate 2 stably and reliably supports the rotor during the test. The bolt holes on the adapter plate 2 are precisely designed according to the distance from the rotor rotation center axis to form multiple groups of bolt holes, and each group of bolt holes is evenly distributed around the rotation center, ensuring the symmetry and uniform force of the device. The design of these bolt hole groups is for rotors of different diameters, and the connection is made by selecting the bolt holes of the corresponding group, thereby ensuring that the connection between the rotor and the test device is precisely matched. The uniform distribution of each set of bolts not only enhances the stability of the adapter plate 2, but also ensures the relative motion balance between the rotor and the test device during the excitation process, which helps to improve the test accuracy.

[0027] A center hole is provided on the mounting plate 6 along the axial direction of the rotor to match the radial dimension of the rotor bearing end. The main purpose is to provide the space required for the installation of the test piece. This design takes into account the situation where the radial dimension of the rotor bearing end is large. When the radial dimension of the rotor bearing end is large, the conventional size may not be installed normally due to insufficient space. By providing a center circular hole on the mounting plate 6, the device can flexibly adapt to rotors of different sizes, provide sufficient installation space, and ensure that the rotor can be stably installed on the test platform. In this way, no matter how the radial dimension of the rotor changes, the device can adapt without changing other structures, thereby effectively improving the versatility and adaptability of the test device and avoiding the problem of redesign and processing due to insufficient space in the device.

[0028] The bolts connecting the base plate 8 and the test platform are T-bolts, and a plurality of slide grooves 4 matching the ends of the T-bolts are provided in parallel on the test platform. The design of the plurality of parallel slide grooves 4 allows different positions to be selected as needed during installation, which provides more flexibility for the adjustment and positioning of the device. Through this design, the relative position between the base plate 8 and the test platform can be accurately controlled to adapt to different assembly requirements and load conditions. The use of T-bolts prevents the bolts from coming out of the slide grooves 4, because the head structure of the T-bolts matches the shape of the slide grooves 4, which can effectively fix the bolt position without loosening or falling off. This structure makes the connection more stable, and even under stress or vibration, the connection between the bolt and the slide groove 4 can maintain stability, avoiding the performance of the entire device being affected by loose installation or sliding errors.

[0029] An increasing plate 11 is arranged between the base plate 8 and the test platform, and a weight-reducing groove is provided in the center of the increasing plate 11, and a through hole for T-bolts to pass through is provided at the edge of the increasing plate 11. The design of the increasing plate 11 is mainly used to adjust the height of the test device to meet the requirements of rotors of different sizes. Through the use of the increasing plate 11, the versatility of the test device can be ensured. When the radial dimension of the rotor is large, the increasing plate 11 can provide additional height support to ensure the adaptability and stability of the device. The weight-reducing groove opened in the center of the increasing plate 11 is mainly to reduce the weight of the device while increasing the height, so as to avoid operating difficulties or unnecessary burdens caused by excessive weight. The weight-reducing groove effectively reduces the overall mass, which not only ensures the strength and rigidity of the structure, but also makes the equipment lighter and easier to carry and install. The through holes on the edge of the increasing plate 11 are used for the passage and fixation of T-bolts. Through these through holes, the increasing plate 11 can be stably connected to the test platform and the base plate 8 to ensure the tightness of the connection. The matching design of the T-bolts and the through holes ensures the stable installation of the height-enhancing plate 11 and prevents the bolts from loosening or falling off.

[0030] Reference Figure 4 , a cut corner 9 is provided at one end of the mounting plate 6 away from the bottom plate 8. The main purpose is to reduce the overall mass of the device while ensuring the rigidity of the mounting plate 6. This cut corner 9 structure effectively removes unnecessary materials and reduces the weight of the device, thereby improving the convenience of operation and reducing the difficulty of transportation. At the same time, the cut corner 9 can also improve the mechanical properties of the structure, avoid stress concentration, and reduce potential structural problems caused by excessive local stress. By reducing unnecessary weight, the cut corner 9 design also helps to increase the natural frequency of the test device, enabling it to better avoid resonance with the rotor modal frequency, thereby improving the stability and accuracy of the modal test. A lifting eye hole 10 is provided at one end of the mounting plate 6 away from the bottom plate 8, and the lifting eye hole 10 is located at the symmetric center of the mounting plate 6. In actual operation, the test device often needs to be moved to different positions or adjusted. The design of the lifting eye hole 10 allows the entire device to be easily lifted by equipment such as a crane, reducing the difficulty and labor intensity of manual handling. In addition, the symmetric center design of the lifting eye hole 10 ensures balance during lifting, effectively avoiding structural deformation or damage caused by unbalanced lifting.

[0031] In a specific implementation, the natural frequency of the aircraft engine rotor vibration modal test device is far away from the frequency range of interest of the rotor, and when the rotor vibration modal test is performed, no coupled vibration occurs between the test piece and the test device.

[0032] Table 1 Modal test results of the device Order Frequency (Hz) Damping ratio (%) Mode shape 1 752 3.97 swing 2 1319 3.28 Twist 3 1385 3.04 Twist The vibration modal test device for the aircraft engine rotor of the present invention has been successfully used to complete the vibration modal test of a certain type of turboprop engine high-pressure rotor in a simulated installation state, providing a reference for the rotor dynamics design and safety test of the core engine of this type, and making a positive contribution to model development. The device is highly functional and easy to use, and can be extended to the development of other aircraft gas turbine engine models and related research topics. The device will produce good economic and social benefits in terms of improving the accuracy of rotor vibration modal tests, improving scientific research efficiency, reducing rotor failures during engine test runs, and enhancing the safety of whole machine and component test runs.

[0033] According to another aspect of the present invention, there is also provided an aircraft engine rotor vibration modal test method, which comprises the following steps: S100, preparation work, selecting device components suitable for the test rotor, including a heightening plate and an adapter plate.

[0034] In the preparation stage, it is first necessary to select the appropriate device components according to the size and structure of the rotor to be tested. The height increase plate is used to adjust the height of the test device, especially when the radial dimension of the rotor bearing end is large, the use of the height increase plate can ensure that the equipment can adapt to the needs of different rotors. The adapter plate is connected to the mounting seat by bolts to ensure that the rotor can be vibrated under stable support. In particular, the multiple sets of bolt holes on the adapter plate can select the appropriate connection method according to the different diameters of the rotor, which can provide a more accurate and stable connection.

[0035] S200, device assembly, the mounting base (3) is connected to the test platform through T-slot bolts to ensure the rigidity of the test device and avoid coupled vibration.

[0036] The key to this stage is to connect the various components according to the design requirements to ensure the rigidity and stability of the device. The mounting base is connected to the test platform via T-bolts. This design can effectively prevent the bolts from falling off and ensure the firmness of the connection. The combination of T-bolts and slides makes the connection of the device more flexible, and the adjustable position ensures the adaptability of different rotor sizes. In addition, the bolt connection between the test platform and the test platform of the mounting base, as well as the adaptive design of the heightening plate, also provide guarantees for the rigidity and stability of the entire device, avoiding the coupled vibration of the rotor and the equipment during the test.

[0037] S300, install the heightening plate as needed to ensure that the device can adapt to the needs of rotors with different radial sizes.

[0038] At this stage, the specific requirements of the test rotor determine whether a height plate is required. The height plate is bolted to the base plate to provide additional height adjustment, ensuring that the test rig can accommodate rotor bearing ends of different sizes. The central weight-reducing slot design of the height plate can reduce the overall weight of the rig while maintaining the rigidity of the structure, thus ensuring that the rig will not be overweight and affect the accuracy and stability of the test.

[0039] S400, rotor installation, connect the rotor upper bearing spring support with the adapter plate, connect the adapter plate with the mounting seat through circumferentially evenly distributed bolt holes, adjust the height and configuration of the test device to ensure the matching of the rotor and the device.

[0040] In the rotor installation step, the rotor needs to be accurately installed on the test device. During the installation process, the rotor needs to be stably fixed through the connection holes between the bearing support and the adapter plate. By accurately adjusting the height and configuration of the device, the matching of the rotor and the test device is ensured so that the rotor bearing end can be aligned with the center hole of the test device. This ensures that the vibration characteristics of the rotor during the test are not disturbed by the device itself. At the same time, by using multiple sets of bolt holes in different positions, the most suitable position can be selected for connection according to rotors of different diameters to ensure the stability of the rotor and the reliability of the experiment.

[0041] S500, Excitation and Testing, install the vibration sensor and excitation system, set the excitation signal frequency range, start the excitation system to excite the rotor mode, and collect vibration response data.

[0042] At this stage, the structure of the test device provides sufficient rigidity and stability to ensure that the rotor can accurately respond to the excitation signal. After the vibration sensor and excitation system are prepared, the rotor is excited by setting a reasonable excitation signal frequency range. The high rigidity structure of the test device and the precise rotor fixing method can avoid any coupling vibration between the device and the rotor, so that the excitation signal can accurately act on the rotor. The excitation signal is transmitted through the adapter plate, bearing spring support and other structures to ensure that every detail of the rotor vibration is accurately captured. S600, data acquisition and analysis, collects vibration data and performs spectrum analysis to identify the rotor's natural frequency, vibration mode and damping ratio, and evaluates vibration characteristics for comparison and verification with design or simulation data.

[0043] The data acquisition system obtains the vibration response data of the rotor under excitation through vibration sensors. Due to the connection between the adapter plate and the mounting base and the structural design of the base plate and the test platform, the entire system can provide a high degree of stability to ensure the accuracy of the data. By performing spectral analysis on the vibration data, modal parameters such as the rotor's natural frequency, vibration mode, and damping ratio can be obtained. The structural design of the device, such as the flexibility of the T-bolts and the slide slots, allows the fixed position of the rotor to be adjusted as needed, thereby optimizing the effect of data acquisition and ensuring that the vibration characteristics of the rotor under different working conditions are fully verified. These analysis results will be compared with the design or simulation data of the rotor to evaluate its performance in actual working conditions.

[0044] Through such a test method, combined with a precisely designed device structure, it is possible to ensure that the vibration modal test of the aircraft engine rotor can obtain reliable and stable test data under various rotor sizes and operating conditions.

[0045] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. Aeroengine rotor vibration modal test device, characterized by: The invention comprises a mounting seat (3) and a test platform (5), wherein two mounting seats (3) are symmetrically mounted on the test platform (5), wherein the mounting seat (3) comprises a base plate (8), a mounting plate (6) and a reinforcing plate (7), wherein the base plate (8) and the mounting plate (6) are perpendicular to each other to form a T-shaped structure, wherein the mounting plate (6) is used to support a rotor, and the reinforcing plate (7) is located on a side of the mounting plate (6) away from the rotor to support the mounting plate (6), and the base plate (8) is connected to the test platform (5) by bolts.

2. The aero-engine rotor vibration modal test device according to claim 1, characterized in that: The bottom plate (8) is provided with bolts on both sides of the mounting plate (6) for connection with the test platform (5).

3. The aero-engine rotor vibration modal test device according to claim 2, characterized in that: An adapter plate (2) is provided between the mounting plate (6) and the rotor bearing spring support (1); the adapter plate (2) is fixed to the mounting plate (6); bolt holes are provided on the adapter plate (2); a plurality of groups of bolt holes are provided according to the distance from the rotor rotation center axis; each group of bolt holes includes a plurality of bolts evenly distributed in the circumferential direction around the rotation center.

4. The aero-engine rotor vibration modal test device according to claim 3, characterized in that: The mounting plate (6) is provided with a center hole extending through the rotor axial direction to match the radial dimension of the rotor bearing end.

5. The aero-engine rotor vibration modal test device according to claim 2, characterized in that: The bolts connecting the bottom plate (8) and the test platform (5) are T-shaped bolts, and the test platform (5) is provided with a plurality of sliding grooves (4) in parallel that match the ends of the T-shaped bolts.

6. The aero-engine rotor vibration modal test device according to claim 5, characterized in that: A heightening plate (11) is provided between the bottom plate (8) and the test platform (5), a weight-reducing groove is provided at the center of the heightening plate (11), and a through hole for T-bolts to pass through is provided at the edge of the heightening plate (11).

7. The aero-engine rotor vibration modal test device according to claim 6, characterized in that: A cut corner (9) is provided at one end of the mounting plate (6) away from the bottom plate (8).

8. The aero-engine rotor vibration modal test device according to claim 7, characterized in that: A lifting eye hole (10) is provided at one end of the mounting plate (6) away from the bottom plate (8), and the lifting eye hole (10) is located at the symmetrical center of the mounting plate (6).

9. A method for testing the vibration modal of an aircraft engine rotor, using the aircraft engine rotor vibration modal testing device according to any one of claims 1 to 8, characterized in that: The steps include: S100, preparation work, selecting device components adapted to the test rotor, including a heightening plate (11) and an adapter plate (2); S200, device assembly, the mounting base (3) is connected to the test platform (5) through T-slot bolts to ensure the rigidity of the test device and avoid coupled vibration; S300, installing a heightening plate (11) as required to ensure that the device can adapt to the needs of rotors with different radial sizes; S400, rotor installation, connect the rotor upper bearing spring support (1) with the adapter plate (2), connect the adapter plate (2) with the mounting seat (3) through bolt holes evenly distributed in the circumference, ensure that the connection is firm and not loose, adjust the height and configuration of the test device, and ensure that the rotor matches the device; S500, Excitation and testing, install the vibration sensor and excitation system, set the excitation signal frequency range, start the excitation system to excite the rotor mode, and collect vibration response data; S600, data acquisition and analysis, collects vibration data and performs spectrum analysis, identifies the rotor's natural frequency, vibration mode and damping ratio, and evaluates modal characteristics for comparison and verification with design or simulation data.

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