Rotor system dynamic response interval analysis method based on contact area correction

Abstract

The invention provides a rotor system dynamic response interval analysis method based on contact area correction, and belongs to the field of aero-engine rotor design. Calculating an effective contact area coefficient distribution interval of the bolt connection structure; establishing a rotor system finite element model for correcting the contact area of the bolt connection structure; calculating the mass, rigidity and damping matrix distribution interval of the rotor system; establishing a rotor system interval kinetic equation considering the contact state change of the bolt connection structure; and calculating the steady-state dynamic response of the rotor system based on a complex-frequency response function matrix interval analysis method. According to the invention, the influence of the contact state of the bolt connection structure on the dynamic characteristics of the rotor system on the system level can be fully researched, and a technical support is provided for the robustness design of the bolt connection structure and the reliability and safety design of an aero-engine.

Description

Technical Field

[0001] The present invention relates to the field of aero-engine rotor design, and in particular to a rotor system dynamic response interval analysis method based on contact area correction. Background Art

[0002] Bolted connections are widely used in advanced aircraft engine rotor systems. Because aircraft engines are high-speed rotating machines with complex and ever-changing operating conditions and environments, bolted connections are subject to complex loads during operation. This can lead to slippage damage at the connection interface, reducing the effective contact area of the bolted connection. This reduces the stiffness of the connection, leading to increased rotor vibration and compromising the robustness of the rotor system and the entire engine. Statistics show that failures related to excessive vibration of the entire engine and its connection structure account for 50-60% of system failures.

[0003] In the traditional dynamic design and analysis of aero-engine rotor systems, the bolted connection structure is often ignored, and the entire rotor system is considered as a continuous structure. The impact of changes in the contact state of the bolted connection structure during operation on the dynamic characteristics of the rotor system is ignored. This not only makes it impossible to evaluate the robustness of the bolted connection structure, but also causes the measured dynamic characteristics of the rotor to deviate from the design state, seriously affecting the reliability and safety of the aero-engine.

[0004] Therefore, in order to fully study the influence of the contact state of the bolted connection structure on the dynamic characteristics of the rotor system at the system level and provide technical support for the robustness assessment of the bolted connection structure, it is urgent to establish a rotor system dynamic response interval analysis method based on contact area correction. Summary of the Invention

[0005] In order to solve the above technical problems and fully study the influence of the contact state of the bolted connection structure on the dynamic characteristics of the rotor system at the system level, the present invention proposes a rotor system dynamic response interval analysis method based on contact area correction, which provides technical support for the robustness design of the bolted connection structure of the aircraft engine and the reliability and safety design of the aircraft engine.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is:

[0007] A rotor system dynamic response interval analysis method based on contact area correction includes the following steps:

[0008] S1: extracting structural characteristic parameters of the bolt connection structure, wherein the structural characteristic parameters include geometric parameters, assembly preload parameters, and working loads received during operation of the bolt connection structure;

[0009] S2: Based on the structural characteristic parameters of the bolt connection structure extracted in S1, a finite element model of the bolt connection structure is established, and the distribution range of the effective contact area coefficient of the bolt connection structure is calculated;

[0010] S3: Based on the distribution interval of the effective contact area coefficient of the bolt connection structure extracted in S2, the contact area of the rotor system connection structure is corrected, and a finite element model of the rotor system with the corrected contact area of the bolt connection structure is established;

[0011] S4: Based on the rotor system finite element model corrected by the contact area of the bolted connection structure established in S3, the mass matrix, stiffness matrix and damping matrix of the rotor system under the minimum effective contact area coefficient, as well as the mass matrix, stiffness matrix and damping matrix of the rotor system under the maximum effective contact area coefficient are calculated, and the distribution range of the mass matrix, stiffness matrix and damping matrix of the rotor system is obtained;

[0012] S5: Based on the distribution intervals of the rotor system mass matrix, stiffness matrix and damping matrix obtained in S4, the interval dynamic equations of the rotor system are established considering the contact state changes of the bolted connection structure;

[0013] S6: Based on the interval dynamic equation of the rotor system established in S5, the distribution interval of the steady-state dynamic response of the rotor system is calculated using the complex frequency response function matrix interval analysis method.

[0014] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the steps of the above-mentioned method for analyzing the dynamic response interval of a rotor system based on contact area correction are implemented.

[0015] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the steps of the above-mentioned rotor system dynamic response interval analysis method based on contact area correction are implemented.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] The present invention proposes a rotor system dynamic response interval analysis method based on contact area correction, which can accurately describe the impact of changes in the contact state of the bolt connection structure on the rotor dynamic characteristics during operation. The method proposed by the present invention can provide technical support for the robustness design and evaluation of the bolt connection structure during the design stage of the aircraft engine rotor, so that the vibration of the rotor system is within a controllable range, ensuring the reliability and safety of the aircraft engine, effectively avoiding repeated iterative design of the rotor system, achieving cost reduction and efficiency improvement, and has important engineering application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 The present invention is a flow chart of a rotor system dynamic response interval analysis method based on contact area correction.

[0019] Figure 2 It is a structural diagram of an advanced aero-engine bolt-connected rotor system.

[0020] Figure 3 It is a schematic diagram of the bolt connection structure of a typical aircraft engine rotor system.

[0021] Figure 4 It is a schematic diagram of the changes in the contact state of the bolt connection structure during the working process.

[0022] Figure 5 It is a schematic diagram of the finite element model of the bolt connection structure.

[0023] Figure 6 Figure 2 is a schematic diagram of the calculated results of the contact area distribution of the bolt connection structure; where a is the minimum effective bolt contact area and b is the maximum effective bolt contact area.

[0024] Figure 7 It is a schematic diagram of the finite element model of the rotor system considering the correction of the contact area of the bolted connection structure.

[0025] Figure 8 It is a schematic diagram of the calculation results of the steady-state response of the rotor system considering the change of the contact state of the bolted connection structure.

[0026] Among them, the figures are marked as: 2a. Second stage compressor bolt connection structure, 2b. Drum shaft bolt connection structure, 3a. Cone shell, 3b. Wheel, 3c. Drum, 3d. Bolt, 3e. Flange edge, 3f. Stop edge. DETAILED DESCRIPTION

[0027] To further clarify the technical solutions and key points of the present invention, the technical solutions of the present invention are described in further detail below with reference to the accompanying drawings and specific examples. The specific embodiments described herein are merely partial embodiments of the present invention and are not intended to limit the present invention. Any changes or substitutions that can be readily conceived by a person skilled in the art within the technical scope disclosed in the present invention are intended to be covered by the scope of protection of the present invention.

[0028] Figure 1 This is a flow chart of a rotor system dynamic response interval analysis method based on contact area correction proposed by the present invention. Figure 2-Figure 8 The present invention is described in further detail.

[0029] Figure 2This is a schematic diagram of the structure of a bolted rotor system for an advanced aircraft engine. This bolted rotor system includes a second-stage compressor bolt connection structure 2a and a drum shaft bolt connection structure 2b. The second-stage compressor bolt connection structure 2a is located on the second-stage compressor disk of the high-pressure rotor and is used to connect the first-stage compressor, the front bearing cone, the second-stage compressor, and the third-stage compressor. The drum shaft bolt connection structure 2b is located on the high-pressure rotor drum shaft and is used to connect the compressor rear cone and the drum shaft.

[0030] Figure 3 This is a schematic diagram of the bolted connection structure of a typical aircraft engine rotor system. The bolted connection structure includes a cone 3a, a disc 3b, a drum 3c, bolts 3d, a flange 3e, and a stop 3f. Bolts 3d pass through the cone 3a, disc 3b, and drum 3c in sequence, connecting the three components into a single unit. The edges of the cone 3a and drum 3c that axially contact the disc 3b are flanges 3e, which connect and secure bolts 3d. The edges of the cone 3a and drum 3c that radially contact the disc 3b are stop 3f, which restrict the radial position of the cone 3a and drum 3c. The bolted connection structure generally uses the disc 3b as the connection reference. Frictional torque transmission is achieved through flanges 3e, centering is achieved through stop 3f, and preload is applied by bolts 3d to compress the multiple components into a single unit. This is a typical rigid connection structure that can transmit torque and axial force, as well as withstand centrifugal loads and bending moments. However, relative motion between the connected components is not permitted.

[0031] Since aircraft engines are high-speed rotating machines with complex and changeable working conditions and environments, during operation, the bolt connection structure is subjected to complex loads, and slip damage may occur on the connection interface. The effective contact area of the bolt connection structure is reduced, which reduces the stiffness of the connection structure, causing the rotor vibration to intensify, affecting the robustness of the rotor system and even the entire machine. Under different lateral concentrated loads, the contact state of the bolt connection structure changes as shown in the figure below. Figure 4 As shown in the figure, when the lateral load is small, most areas of the interface are in a viscous state, and there is slip in a very small part. At this time, the structural functions of most areas are complete, and the overall stiffness of the structure is good; with the increase of the lateral load, the viscous area gradually decreases, and a gap appears and gradually increases; when the lateral load increases again, a gap appears in the connection interface, the connection structure loses its constraint and load-bearing function, and the rotor suffers from serious stiffness loss.

[0032] In order to analyze the influence of the contact state of the bolted connection structure on the rotor dynamic characteristics, such as Figure 1 As shown, the present invention proposes a rotor system dynamic response interval analysis method based on contact area correction, which includes the following steps:

[0033] S1: Extraction of structural characteristic parameters of bolted connection structure, including:

[0034] The structural characteristic parameters of the target bolted joint structure in an aeroengine are extracted, including its geometric parameters, assembly preload parameters, and the operating loads it experiences during operation. The geometric parameters include bolt diameter, barrel diameter, barrel thickness, flange diameter, flange thickness, stop length, and stop thickness. The assembly preload parameters include tightening torque and stop interference. Both the geometric parameters and assembly preload parameters are determined by the bolted joint's machining drawings and assembly process flow. The operating loads of the bolted joint include axial load, bending moment, and temperature load. The loads and their magnitudes are determined by the operating conditions of the entire aeroengine.

[0035] S2: Calculation of the effective contact area coefficient distribution range of bolted connection structures, including:

[0036] Based on the structural characteristic parameters of the bolt connection structure extracted in S1, the following is established: Figure 5 The finite element model of the bolt connection structure shown in the figure uses Solid185 entity elements as the mesh. Figure 5 The grid in is used to apply loads and boundary constraints to the established finite element model through the load condition and boundary condition commands. The load conditions include the axial load, bending moment, and temperature load obtained by S1. The finite element analysis software is used to calculate the effective contact area of the bolted connection structure under different assembly preload parameters and working loads, and to determine the distribution range of the effective contact area of the bolted connection structure.

[0037] The effective contact area of the bolt connection structure is the area on the connection interface that is in the sticky state and the slip state. The calculated minimum and maximum contact area distribution of the bolt connection structure is as follows: Figure 6 As shown, Figure 6 a is the minimum effective contact area of the bolt, Figure 6 b is the maximum effective contact area of the bolt. On this basis, the effective contact area coefficient is calculated ,in, is the viscous area of the bolt connection interface, is the slip area of the bolt connection interface, The effective contact area coefficient can be obtained by taking the total area of the bolt connection interface as The distribution interval , is the maximum effective contact area coefficient, is the minimum effective contact area coefficient.

[0038] S3: Establishment of the finite element model of the rotor system with corrected contact area of the bolted connection structure, including:

[0039] Establish as Figure 7The finite element model of the rotor system shown in the figure uses Solid185 entity elements as the mesh, that is, Figure 7 In the finite element model of the rotor system, the mass, axial position of the center of mass, polar moment of inertia and diametric moment of inertia of each compressor and each turbine stage are the same as those of the actual rotor system to ensure the equivalence of mechanical properties. At the same time, based on the distribution range of the effective contact area coefficient of the bolt connection structure obtained in S2 , the effective contact area of the bolted joint in the finite element model of the rotor system is corrected.

[0040] S4: Rotor system mass / stiffness / damping matrix distribution interval calculation, including:

[0041] Using finite element analysis software, the minimum effective contact area coefficient is derived The lower bound matrix of the rotor system mass under , damping lower bound matrix and the stiffness lower bound matrix , and the maximum effective contact area coefficient The upper bound matrix of the rotor system mass under , damping upper bound matrix and the stiffness upper bound matrix .

[0042] S5: Establishment of interval dynamic equations of the rotor system considering the contact state changes of the bolted connection structure, including:

[0043] Based on the distribution intervals of the rotor system mass matrix, damping matrix and stiffness matrix obtained in S4, the interval dynamic equations of the rotor system are established ,in, is the acceleration matrix of the rotor system, is the velocity matrix of the rotor system, is the displacement matrix of the rotor system, is a non-deterministic mass matrix with interval constraints , and are the lower and upper bound matrices of the rotor system mass determined by S4, is a non-deterministic damping matrix with interval constraints , and are the rotor system damping lower bound matrix and upper bound matrix determined by S4, is a non-deterministic stiffness matrix with interval constraints , and are the lower bound matrix and upper bound matrix of the rotor system stiffness determined by S4, is the motivation matrix.

[0044] S6: Calculation of the steady-state dynamic response of the rotor system based on the complex frequency response function matrix interval analysis method, including:

[0045] Based on the interval dynamic equations of the rotor system established in S5, the interval analysis method of the complex frequency response function matrix is used to solve the steady-state dynamic response of the rotor system, including:

[0046] S6.1: Introducing the state vector , transform the interval dynamic equation of the rotor system established by S5 from physical space to state space:

[0047] ;

[0048] in, is the state vector The first derivative of 、 and are the mass matrix, stiffness matrix and damping matrix distributed in the state space, respectively. , , , is the excitation force matrix in the state space, .

[0049] S6.2: Solving Generalized Eigenvalue Equations , and obtain the generalized eigenvalue of the interval distribution and the generalized eigenvector of the interval distribution ,in, is the modal order; according to the generalized eigenvector and the eigenvector of the interval distribution The relationship between: , the characteristic vector of the interval distribution can be further calculated .

[0050] S6.3: Transform the mass matrix distributed in the state space into intervals , stiffness matrix , damping matrix Regularization, get the regularized modal parameters of the interval distribution , , ,in, is the generalized eigenvector obtained in S6.2 The transpose of .

[0051] S6.4: The generalized eigenvalue of the interval distribution obtained in S6.2 and the eigenvector of the interval distribution And the regularized modal parameters of the interval distribution obtained in S6.3 are substituted into the complex frequency response function calculation formula ,in, is the rotation angular frequency of the rotor system, is the eigenvector obtained in S6.2 The transpose of is the modal order, and the interval distribution can be obtained. Complex frequency response function of the first mode .

[0052] S6.5: Accumulate the complex frequency response functions of each order of the interval distribution obtained in S6.4 to obtain the total complex frequency response function of the interval distribution system :

[0053] ;

[0054] in, For the summation symbol, is the modal order, The first interval distribution obtained in S6.4 The complex frequency response function of the first mode, is the modal order to be considered.

[0055] S6.6: Complex frequency response functions of various orders based on the interval distribution obtained in S6.4 , calculate the steady-state response of the rotor system with interval distribution :

[0056] ;

[0057] in, For the summation symbol, is the modal order, is the motivation matrix, is a natural constant, For time.

[0058] The final calculated steady-state response of the rotor system considering the change in the contact state of the bolted connection structure is as follows: Figure 8As shown, by using the method proposed in the present invention, the correlation between the contact state of the bolt connection structure and the dynamic characteristics of the rotor system at the system level can be established, and not only the interval information of the critical speed can be obtained, but also the interval information of the steady-state response at each speed can be obtained, which can better describe the impact of the change in the contact state of the bolt connection structure caused by the change in assembly preload parameters and working load on the dynamic characteristics of the rotor; using the method proposed in the present invention, technical support can be provided for the robustness design and evaluation of the bolt connection structure during the design stage of the aircraft engine rotor, so that the vibration of the rotor system is within a controllable range, the reliability and safety of the aircraft engine are guaranteed, the repeated iterative design of the rotor system is effectively avoided, and cost reduction and efficiency improvement are achieved, which has important engineering application value.

[0059] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the steps of the above-mentioned method for analyzing the dynamic response interval of a rotor system based on contact area correction are implemented.

[0060] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the steps of the above-mentioned rotor system dynamic response interval analysis method based on contact area correction are implemented.

[0061] Those skilled in the art will appreciate that embodiments of the present invention may be provided as methods or computer program products. Thus, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk drives, CD-ROMs, optical storage devices, etc.) containing computer-usable program code. The solutions in the embodiments of the present invention may be implemented using various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0062] The present invention is described with reference to flowcharts and / or block diagrams of methods and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowcharts and / or block diagrams. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0063] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0064] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0065] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0066] Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if such changes and modifications fall within the scope of the claims and their equivalents, the present invention is intended to include such changes and modifications.

Claims

1. A rotor system dynamic response interval analysis method based on contact area correction, characterized in that: The steps include: S1: extracting structural characteristic parameters of the bolt connection structure, wherein the structural characteristic parameters include geometric parameters, assembly preload parameters, and working loads received during operation of the bolt connection structure; S2: Based on the structural characteristic parameters of the bolt connection structure extracted in S1, a finite element model of the bolt connection structure is established, and the distribution range of the effective contact area coefficient of the bolt connection structure is calculated; S3: Based on the distribution interval of the effective contact area coefficient of the bolt connection structure extracted in S2, the contact area of the rotor system connection structure is corrected, and a finite element model of the rotor system with the corrected contact area of the bolt connection structure is established; S4: Based on the rotor system finite element model corrected by the contact area of the bolted connection structure established in S3, the mass matrix, stiffness matrix and damping matrix of the rotor system under the minimum effective contact area coefficient, as well as the mass matrix, stiffness matrix and damping matrix of the rotor system under the maximum effective contact area coefficient are calculated, and the distribution range of the mass matrix, stiffness matrix and damping matrix of the rotor system is obtained; S5: Based on the distribution intervals of the rotor system mass matrix, stiffness matrix and damping matrix obtained in S4, the interval dynamic equations of the rotor system are established considering the contact state changes of the bolted connection structure; S6: Based on the interval dynamic equation of the rotor system established in S5, the distribution interval of the steady-state dynamic response of the rotor system is calculated using the complex frequency response function matrix interval analysis method.

2. The rotor system dynamic response interval analysis method based on contact area correction according to claim 1 is characterized in that: In S1, the working load includes axial load, bending moment and temperature load.

3. The rotor system dynamic response interval analysis method based on contact area correction according to claim 1 is characterized in that: The S2 includes: S2.1: Use finite element analysis software to import the geometric model of the bolted connection structure, input material parameters, determine the element type, and create a finite element mesh model of the bolted connection structure; S2.2: Apply load constraints and boundary constraints to the finite element mesh model established in S2.1 through load condition and boundary condition commands. The load constraints include the axial load, bending moment, and temperature load obtained in S1. S2.3: Determine the solution type and set the calculation parameters. Calculate the effective contact area of the bolted connection structure under different assembly preload parameters and working loads. Determine the distribution range of the effective contact area of the bolted connection structure. The effective contact area of the bolted connection structure is the area on the connection interface that is in a viscous state and a slipping state. Calculate the effective contact area coefficient. ,in, is the viscous area of the bolt connection interface, is the slip area of the bolt connection interface, is the total area of the bolt connection interface, and the effective contact area coefficient of the bolt connection structure is determined The distribution interval , is the maximum effective contact area coefficient, is the minimum effective contact area coefficient.

4. The rotor system dynamic response interval analysis method based on contact area correction according to claim 1 is characterized in that: The S3 includes: S3.1: Establish a finite element model of the rotor system. In the finite element model of the rotor system, the mass, axial position of the center of mass, polar moment of inertia, and diametric moment of inertia of each compressor stage and each turbine stage are the same as those of the actual rotor system to ensure equivalent mechanical properties. S3.2: Effective contact area coefficient of bolted connection structure obtained in S2 The distribution interval , the effective contact area of the bolted joint in the finite element model of the rotor system is corrected.

5. The rotor system dynamic response interval analysis method based on contact area correction according to claim 4 is characterized in that: The S4 includes: When the effective contact area coefficient of the bolt connection structure is taken as the minimum effective contact area coefficient When the mass matrix, damping matrix and stiffness matrix of the rotor system are derived, the lower bound matrix is 、 and ; When the effective contact area coefficient of the bolt connection structure is taken as the maximum effective contact area coefficient When the rotor system mass matrix, damping matrix and stiffness matrix are derived, they are the upper bound matrices 、 and , thereby obtaining the distribution range of the rotor system mass matrix, damping matrix and stiffness matrix.

6. The rotor system dynamic response interval analysis method based on contact area correction according to claim 5, characterized in that: The S5 includes: Based on the distribution interval of the rotor system mass matrix, damping matrix and stiffness matrix obtained in S4, the interval dynamic equation of the rotor system is established ,in, is the acceleration matrix of the rotor system, is the velocity matrix of the rotor system, is the displacement matrix of the rotor system, is a non-deterministic mass matrix with interval constraints , and are the rotor system mass lower bound matrix and the rotor system mass upper bound matrix determined by S4, is a non-deterministic damping matrix with interval constraints , and are the rotor system damping lower bound matrix and rotor system damping upper bound matrix determined by S4, is a non-deterministic stiffness matrix with interval constraints , and are the rotor system stiffness lower bound matrix and rotor system stiffness upper bound matrix determined by S4, is the motivation matrix.

7. The rotor system dynamic response interval analysis method based on contact area correction according to claim 6, characterized in that: The S6 includes: S6.1: Introducing the state vector , transform the interval dynamic equation of the rotor system established by S5 from physical space to state space: ,in, , is the first-order derivative of the state vector Z, 、 and are the mass matrix, stiffness matrix and damping matrix distributed in the state space, respectively. , , , is the excitation force matrix in the state space, ; S6.2: Solving Generalized Eigenvalue Equations , and obtain the generalized eigenvalue of the interval distribution and the generalized eigenvector of the interval distribution ,in, is the modal order; according to the generalized eigenvector and the eigenvector of the interval distribution The relationship between: , further calculate the characteristic vector of the interval distribution ; S6.3: Transform the mass matrix distributed in the state space into intervals , stiffness matrix , damping matrix Regularization, get the regularized modal parameters of the interval distribution , , ,in, is the generalized eigenvector obtained in S6.2 The transpose of .

8. The rotor system dynamic response interval analysis method based on contact area correction according to claim 7 is characterized in that: The S6 further includes: S6.4: The generalized eigenvalue of the interval distribution obtained in S6.2 and eigenvectors And the regularized modal parameters of the interval distribution obtained in S6.3 are substituted into the complex frequency response function calculation formula ,in, is the rotation angular frequency of the rotor system, is the eigenvector obtained in S6.2 The transpose of is the modal order, and the interval distribution can be obtained. Complex frequency response function of the first mode ; S6.5: Accumulate the complex frequency response functions of each order of the interval distribution obtained in S6.4 to obtain the total complex frequency response function of the interval distribution system ,in, For the summation symbol, is the modal order, The first interval distribution obtained in S6.4 The complex frequency response function of the first mode, is the modal order to be considered; S6.6: Complex frequency response functions of various orders based on the interval distribution obtained in S6.5 , calculate the steady-state response of the rotor system with interval distribution ,in, For the summation symbol, is the modal order, is the motivation matrix, is a natural constant, For time.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the steps of a rotor system dynamic response interval analysis method based on contact area correction according to any one of claims 1 to 8 are implemented.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of a rotor system dynamic response interval analysis method based on contact area correction according to any one of claims 1 to 8 are implemented.

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