WCSSA-based dynamic balance optimization method without trial weight for aero-engine rotor

Abstract

The invention is suitable for the technical field of aero-engine vibration control, and provides a WCSSA-based aero-engine rotor non-trial-weight dynamic balance optimization method, which comprises the following steps: firstly, obtaining an aero-engine rotor model, then carrying out modal analysis processing on the aero-engine rotor model, generating original vibration information and transfer function matrix information, and carrying out dynamic balance optimization on the original vibration information and the transfer function matrix information; the method comprises the following steps: acquiring original vibration information, generating balance weight solution set information according to the original vibration information and transfer function matrix information on the basis of a WCSSA algorithm, and finally quickly determining optimal weight information on the basis of an enumeration method. According to the method, the dynamic balance process of the high-speed rotor can be optimized based on the virtual prototype technology, the trial weight link in the traditional dynamic balance optimization process is reduced, the dynamic balance efficiency is greatly improved, meanwhile, the stability and reliability of a high-speed aero-engine rotor system are remarkably improved, and the application prospect is wide. Technical reference is provided for vibration control of the high-speed aero-engine rotor, and the method has important engineering application value.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engine vibration control, and in particular to a WCSSA-based aircraft engine rotor non-test weight dynamic balancing optimization method. Background Art

[0002] The high-performance flexible rotor structure is the core component of an aircraft engine. It needs to operate under high temperature, high pressure and high speed conditions, and its reliability directly affects the safety of the engine. With the improvement of the thrust-to-weight ratio of aircraft engines, lightweighting has become the main trend of engine components.

[0003] Under high-speed rotation conditions, due to the slender and often hollow shaft design, the flexible rotor is extremely sensitive to tiny imbalances, which can easily cause deformation and destroy the balance state, leading to complex vibration problems.

[0004] At present, the unbalance vector of the flexible rotor structure is usually identified by technicians performing multiple manual weight tests. However, this method requires multiple tests, and each weight test must be selected very accurately to avoid damage to the rotor due to excessive vibration caused by improper selection. There is a problem of low dynamic balancing efficiency, which needs further improvement. Summary of the invention

[0005] Based on this, an embodiment of the present application provides an aircraft engine rotor non-test weight dynamic balancing optimization method based on WCSSA to solve the problem of low dynamic balancing efficiency in the prior art.

[0006] In a first aspect, an embodiment of the present application provides a method for optimizing dynamic balancing of an aircraft engine rotor without test weight based on WCSSA, the method comprising:

[0007] Obtain a preset aircraft engine rotor model;

[0008] Analyzing and processing the aircraft engine rotor model to generate original vibration information and transfer function matrix information;

[0009] Based on a preset WCSSA algorithm, generating balancing weight solution set information according to the original vibration information and the transfer function matrix information, wherein the balancing weight solution set information includes a plurality of balancing weight scheme information;

[0010] Based on the enumeration method and the balancing weight solution set information, the balancing weight solution information that minimizes the maximum residual vibration amplitude is determined as the optimal balancing weight information.

[0011] Compared with the prior art, the beneficial effects are as follows: in the WCSSA-based aero-engine rotor non-test weight dynamic balancing optimization method provided in the embodiment of the present application, the terminal device can first obtain the aero-engine rotor model, and then perform vibration analysis and processing on the aero-engine rotor model to generate original vibration information and transfer function matrix information, and then based on the WCSSA algorithm, generate balancing weight solution information according to the original vibration information and transfer function matrix information, and finally, based on the enumeration method and the balancing weight solution information, determine the balancing weight scheme information that minimizes the maximum residual vibration amplitude as the optimal balancing weight information, thereby realizing the optimization of the dynamic balancing process of high-speed rotors based on virtual prototype technology, reducing the test weight link in the traditional dynamic balancing optimization process, effectively improving the dynamic balancing efficiency, and to a certain extent solving the current problem of low dynamic balancing efficiency.

[0012] In a second aspect, an embodiment of the present application provides an aircraft engine rotor non-test weight dynamic balancing optimization system based on WCSSA, the system comprising:

[0013] Aircraft engine rotor model acquisition module: used to obtain a preset aircraft engine rotor model;

[0014] The original vibration information generating module is used to analyze and process the aero-engine rotor model to generate original vibration information and transfer function matrix information;

[0015] A balancing weight solution information generation module is used to generate balancing weight solution information based on a preset WCSSA algorithm according to the original vibration information and the transfer function matrix information, wherein the balancing weight solution information includes a plurality of balancing weight scheme information;

[0016] The optimal balancing weight information determination module is used to determine the balancing weight solution information that minimizes the maximum residual vibration amplitude as the optimal balancing weight information based on the enumeration method and the balancing weight solution information.

[0017] In a third aspect, an embodiment of the present application provides a terminal device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the method of the first aspect described above when executing the computer program.

[0018] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the method of the first aspect described above are implemented.

[0019] It can be understood that the beneficial effects of the second to fourth aspects mentioned above can be found in the relevant description of the first aspect mentioned above, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments or the description of the prior art are briefly introduced below.

[0021] Figure 1 It is a flow chart of a method for optimizing dynamic balancing of an aircraft engine rotor without test weight provided in one embodiment of the present application;

[0022] Figure 2 is a first schematic diagram of a rotor system simulation test bench provided by an embodiment of the present application;

[0023] Figure 3 is a second schematic diagram of a rotor system simulation test bench provided in one embodiment of the present application;

[0024] Figure 4 It is a flowchart of step S101 in the method for optimizing the dynamic balancing of an aircraft engine rotor without test weight provided in one embodiment of the present application;

[0025] Figure 5 It is a schematic diagram of the flow chart after step S1013 in the method for optimizing the dynamic balancing of an aircraft engine rotor without test weight provided in one embodiment of the present application;

[0026] Figure 6 is a schematic diagram of the natural frequency provided by an embodiment of the present application;

[0027] Figure 7 (a) is a schematic diagram of a first mode vibration shape provided by an embodiment of the present application, Figure 7 (b) is a schematic diagram of a second mode vibration type provided in an embodiment of the present application, Figure 7 (c) is a schematic diagram of a third mode vibration type provided in an embodiment of the present application;

[0028] Figure 8 is a schematic diagram of an unbalanced mass provided by an embodiment of the present application;

[0029] Fig. 9 It is a flowchart of step S301 in the method for optimizing the dynamic balancing of an aircraft engine rotor without a test weight provided in one embodiment of the present application;

[0030] Fig.10 is a schematic diagram of the number of iterations provided in an embodiment of the present application;

[0031] Fig.11 (a) is a first schematic diagram of the vibration amplitude provided by an embodiment of the present application, Fig.11 (b) is a second schematic diagram of the vibration amplitude provided by an embodiment of the present application, Fig.11 (c) is a third schematic diagram of vibration amplitude provided by an embodiment of the present application;

[0032] Fig.12 This is a module block diagram of an aircraft engine rotor non-test weight dynamic balancing optimization system provided by an embodiment of the present application;

[0033] Fig.13 It is a schematic diagram of a terminal device provided in one embodiment of the present application.

[0034] Description of Figure Numbers:

[0035] 1. Drive motor;

[0036] 2. Coupling;

[0037] 31. First support seat; 32. Second support seat; 33. Third support seat;

[0038] 41. first balance plane; 42. second balance plane; 43. third balance plane; 44. fourth balance plane;

[0039] 5. Second stage turbine disc. DETAILED DESCRIPTION

[0040] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0041] In the description of the present application specification and the appended claims, the terms "first", "second", "third", etc. are only used to distinguish the descriptions and cannot be understood as indicating or implying relative importance.

[0042] References to "one embodiment" or "some embodiments" etc. described in the specification of this application mean that one or more embodiments of the present application include specific features, structures or characteristics described in conjunction with the embodiment. Therefore, the statements "in one embodiment", "in some embodiments", "in some other embodiments", "in some other embodiments", etc. that appear in different places in this specification do not necessarily refer to the same embodiment, but mean "one or more but not all embodiments", unless otherwise specifically emphasized in other ways. The terms "including", "comprising", "having" and their variations all mean "including but not limited to", unless otherwise specifically emphasized in other ways.

[0043] In order to illustrate the technical solution described in this application, a specific embodiment is provided below for illustration.

[0044] See also Figure 1 , Figure 1 It is a flow chart of the WCSSA-based aircraft engine rotor non-test weight dynamic balancing optimization method provided in the embodiment of the present application. In the present embodiment, the execution subject of the aircraft engine rotor non-test weight dynamic balancing optimization method is a terminal device. It is understandable that the types of terminal devices include but are not limited to mobile phones, tablet computers, laptops, ultra-mobile personal computers (Ultra-Mobile Personal Computer, UMPC), netbooks, personal digital assistants (Personal Digital Assistant, PDA), etc. The embodiment of the present application does not impose any restrictions on the specific type of terminal devices.

[0045] See also Figure 1 The method for optimizing the dynamic balance of an aircraft engine rotor without a test weight provided in the embodiment of the present application includes but is not limited to the following steps:

[0046] In S100, a preset aircraft engine rotor model is obtained.

[0047] Specifically, the terminal device can first use a specific aircraft engine rotor system as a prototype to build a rotor system simulation test bench. Figure 2 The rotor system simulation test bench may include a drive motor 1, a coupling 2, a first support seat 31, a second support seat 32, a third support seat 33 and a secondary turbine disk 5; the rotor system simulation test bench also includes a first balance plane 41, a second balance plane 42, a third balance plane 43 and a fourth balance plane 44.

[0048] In one possible implementation, since the aircraft engine rotor system is relatively complex, in order to simulate the dynamic characteristics of the aircraft engine rotor system as realistically as possible, the three equivalent modeling principles of mass, stiffness and mode can be fully met when establishing the aircraft engine rotor model, and the actual model after corresponding simplification is as follows: Figure 3 shown.

[0049] In some possible implementations, in order to obtain the aircraft engine rotor model, before step S100, the method further includes but is not limited to the following steps:

[0050] In S101, an aircraft engine rotor model is constructed.

[0051] Specifically, before the terminal device obtains the aircraft engine rotor model, the terminal device may first construct the aircraft engine rotor model.

[0052] In order to realize the construction of aircraft engine rotor model, see some possible implementations. Figure 4 Step S101 includes but is not limited to the following steps:

[0053] In S1011, the size information of the aircraft engine rotor system is obtained.

[0054] Specifically, the terminal device may first obtain the aircraft engine rotor system size information, wherein the aircraft engine rotor system size information is used to describe the size of the aircraft engine rotor system.

[0055] In S1012, based on the preset three-dimensional design software and according to the size information of the aircraft engine rotor system, three-dimensional model diagram information of the aircraft engine rotor system is generated.

[0056] Specifically, after the terminal device obtains the size information of the aircraft engine rotor system, the terminal device can generate three-dimensional model drawing information of the aircraft engine rotor system based on the preset three-dimensional design software and the size information of the aircraft engine rotor system, wherein the three-dimensional model drawing information of the aircraft engine rotor system is used to describe the three-dimensional model of the aircraft engine rotor system; the three-dimensional design software can be SolidWorks, CATIA or Creo.

[0057] In S1013, based on the preset finite element software, the three-dimensional model diagram information of the aircraft engine rotor system is modeled and processed to generate virtual prototype model information.

[0058] Specifically, after the terminal device generates the three-dimensional model diagram information of the aircraft engine rotor system, the terminal device can perform virtual prototype modeling processing on the three-dimensional model diagram information of the aircraft engine rotor system based on the preset finite element software to generate virtual prototype model information, wherein the virtual prototype model information is used to describe the model after the virtual prototype modeling processing is performed on the three-dimensional model of the aircraft engine rotor system.

[0059] In S1014, it is determined that the virtual prototype model information is an aircraft engine rotor model.

[0060] Specifically, after the terminal device generates the virtual prototype model information, the terminal device may determine that the virtual prototype model information is an aircraft engine rotor model.

[0061] In some possible implementations, in order to verify the effectiveness of the virtual prototype model, please refer to Figure 5 After step S1013, the method further includes but is not limited to the following steps:

[0062] In S10131, theoretical speed information and critical speed information are obtained based on the virtual prototype model information.

[0063] Specifically, the terminal device can obtain theoretical speed information and critical speed information based on the virtual prototype model information, wherein the theoretical speed information is used to describe the theoretical critical speed of the virtual prototype model information, and the critical speed information is used to describe the measured critical speed of the virtual prototype model information.

[0064] For some possible implementations, see Figure 6 The terminal device can obtain the natural frequency of the aircraft engine rotor system test bench through the hammer method, and then perform modal analysis through finite element software to obtain the critical speed corresponding to the virtual prototype of the aircraft engine rotor system. After comparative verification, the terminal device can correct the virtual prototype model so that the model error is less than 5%.

[0065] In S10132, validity verification information is generated based on the theoretical speed information and the critical speed information.

[0066] Specifically, after the terminal device obtains the theoretical speed information and the critical speed information, the terminal device may generate validity verification information according to the theoretical speed information and the critical speed information, wherein the validity verification information is verification pass information or verification fail information.

[0067] In S10133, if the validity verification information is verification failure information, the preset model parameters of the finite element software are modified, and the preset finite element software is re-executed to model the three-dimensional model diagram information of the aircraft engine rotor system, generate virtual prototype model information, and generate validity verification information based on the theoretical speed information and critical speed information until the validity verification information is verification pass information.

[0068] Specifically, if the validity verification information is verification failure information, the terminal device can modify the model parameters preset in the finite element software and re-execute the above steps S1013, S10131 and S10132 until the validity verification information is verification pass information.

[0069] In S10134, if the validity verification information is verification passed information, the virtual prototype model information is determined to be an aircraft engine rotor model.

[0070] Specifically, if the validity verification information is verification passed information, the terminal device can execute the above step S1014.

[0071] In S200, the aircraft engine rotor model is analyzed and processed to generate original vibration information and transfer function matrix information.

[0072] Specifically, after the terminal device acquires the aircraft engine rotor model, the terminal device can analyze and process the aircraft engine rotor model to generate original vibration information and transfer function matrix information.

[0073] For example, see Figure 7 and Figure 8 , Figure 7 The figure is a schematic diagram of the vibration type analysis of the aircraft engine rotor model. Three dynamic balancing points can be set on the aircraft engine rotor system, that is, the dynamic balancing points can be set at the vibration type anti-nodes. Figure 7 (a) is used to show the first mode shape (i.e. Figure 8 The measuring point 1) in Figure 7 (b) is used to show the second mode shape (i.e. Figure 8 The measuring point 2) in Figure 7 (c) is used to show the third mode shape (i.e. Figure 8 3). Please refer to Figure 8 The terminal device can attach mass points on the turbine disk to simulate unbalanced mass. The size of the unbalanced mass can be 15 grams, and the eccentricity of the unbalanced mass can be 1.05×10 -1 m, the phase of the unbalanced mass can be 180 degrees.

[0074] Without loss of generality, according to the critical speed value of the rotor system, the terminal device can set the frequency range of the solution to 0-300 Hz, apply the same unbalanced excitation to the four balancing planes respectively, the magnitude of the applied unbalanced excitation is 15 grams, and the phase of the applied unbalanced excitation can be 180 degrees. Since the maximum speed of the test bench can be 6000 revolutions per minute, the terminal device can set the balancing speed to 4700 revolutions per minute, 5000 revolutions per minute, 5300 revolutions per minute, and 5600 revolutions per minute.

[0075] Exemplarily, the terminal device may determine that the high-speed aircraft engine rotor dynamic balancing method has three measuring points and four balancing planes, so the transfer function matrix may be a (3×4)×4 matrix; in a possible implementation, the transfer function matrix at a certain speed may be:

[0076]

[0077] In the formula, H 11 The first 1 corresponding to the subscript of represents the response value of measurement point 1, H 11 The second 1 corresponding to the subscript of indicates that the excitation is input only at the first balance plane, and so on.

[0078] Exemplarily, the transfer function value matrix values ​​determined by the terminal device are shown in Table 1.

[0079] Table 1 Transfer function value data table

[0080]

[0081]

[0082] In S300, based on a preset WCSSA algorithm, balancing weight solution information is generated according to original vibration information and transfer function matrix information.

[0083] Specifically, after the terminal device generates original vibration information and transfer function matrix information, the terminal device can generate balancing weight solution information based on the preset WCSSA algorithm according to the original vibration information and transfer function matrix information, wherein the balancing weight solution information includes multiple balancing weight scheme information.

[0084] In some possible implementations, in order to generate the balancing weight solution set information, before step S300, the method further includes but is not limited to the following steps:

[0085] In S301, the preset SAA algorithm is improved according to the preset infinite folding chaotic mapping algorithm, the preset whale optimization algorithm, and the preset Cauchy mutation strategy to generate a WCSSA algorithm.

[0086] Specifically, the terminal device can improve the preset SAA algorithm according to the preset infinite folding chaotic mapping algorithm, the preset whale optimization algorithm, and the preset Cauchy mutation strategy to generate a WCSSA algorithm.

[0087] In some possible implementations, to implement the generated WCSSA algorithm, see Fig. 9 Step S301 includes but is not limited to the following steps:

[0088] In S3011, the initialization population of the preset SAA algorithm is improved according to the preset infinite folding chaotic mapping algorithm to generate a first improved algorithm.

[0089] Specifically, the terminal device can improve the initialization population of the preset SAA algorithm according to the preset infinite folding chaotic mapping algorithm, and use the infinite folding chaotic mapping to replace the initialization population function of the SAA algorithm to generate a first improved algorithm, thereby improving the diversity of the initial population through the randomness and ergodicity of the chaotic sequence, which helps the algorithm to better explore the solution space and reduce the possibility of falling into the local optimum.

[0090] In a possible implementation, the infinite folding chaotic mapping algorithm can be:

[0091]

[0092] In the formula, x i+1 is the variable value at the i+1th iteration, i is the number of iterations, x i is the variable value at the i-th iteration, α is the control parameter, and the value of α can be 2.

[0093] In S3012, according to the preset whale optimization algorithm, the update position corresponding to the discoverer position of the first improved algorithm is improved to generate a second improved algorithm.

[0094] Specifically, after the terminal device generates the first improved algorithm, the terminal device can generate a second improved algorithm based on the preset whale optimization algorithm, so as to improve the update position corresponding to the discoverer position of the first improved algorithm, and use the whale optimization algorithm in the first stage of the global exploration strategy to replace the discoverer position update position of the original sparrow algorithm, thereby making up for the sparrow algorithm's excessive reliance on the previous generation of sparrow position update method.

[0095] In a possible implementation, the whale optimization algorithm may be:

[0096]

[0097] In the formula, The updated value of the position of the ith algorithm simulation individual in the dth dimension at the t+1th generation. The algorithm simulation individual is the sparrow in the sparrow algorithm. is the value of the current global optimal position in the dth dimension; Simulate the value of the current position of the individual in the dth dimension at the tth generation for the i-th algorithm; is an algorithm randomly selected in the tth generation to simulate the position of the individual in the dth dimension; A is the preset control parameter, A = 2a × ra; a is the preset linearly decreasing control parameter, a decreases from 2 to 0; r is a random vector between [0,1]; D is the preset distance parameter, the distance parameter is used to determine the step size of the position update, D = |C × X*(t) - X(t)|; C = 2r; X*(t) is the position of the current optimal solution.

[0098] In S3013, according to the preset Cauchy perturbation mutation boosting algorithm, the update formula corresponding to the follower position of the second improved algorithm is improved to generate a WCSSA algorithm.

[0099] Specifically, after the terminal device generates the second improved algorithm, the terminal device can improve the update formula corresponding to the follower position of the second improved algorithm according to the preset Cauchy perturbation mutation boosting algorithm to generate a WCSSA algorithm, thereby using the Cauchy mutation strategy to replace the follower position update formula of the original sparrow algorithm, significantly enhancing the exploration scope and diversity of the algorithm.

[0100] In a possible implementation, the above Cauchy perturbation variation boosting algorithm can be:

[0101]

[0102] In the formula, The variable values ​​of the individuals simulated by the i-th algorithm and the j-th algorithm at the t+1th iteration; is the variable value of the individual simulated by the ith algorithm and the individual simulated by the jth algorithm at the tth iteration; γ is the preset scaling factor, which is used to adjust the mutation intensity; Cauchy(0,1) is a Cauchy distributed random number with a mean of 0 and a scale parameter of 1.

[0103] Without loss of generality, the above Cauchy perturbation mutation boosting algorithm may also include:

[0104]

[0105] Where f(x) is the probability density function of the Cauchy distribution.

[0106] In one possible implementation, the influence coefficient method can be expressed as:

[0107]

[0108] In the formula, T(Ω) is the influence coefficient, is the correction mass, V is the vibration of the vibration measuring section, and R is the residual vibration.

[0109] Without loss of generality, the terminal device can determine the specific relationship between the transfer function method and the influence coefficient method as follows:

[0110] T(Ω)=Ω 2 H(Ω)

[0111] Where T(Ω) is the influence coefficient matrix, H(Ω) is the transfer function matrix, and Ω is the speed.

[0112] Without loss of generality, the terminal device can convert the transfer function matrix into the influence coefficient matrix based on the specific relationship between the transfer function method and the influence coefficient method, and then substitute it into the WCSSA algorithm for solution. The original vibration is shown in Table 2. At the same time, the terminal device can initialize and set the WCSSA parameters, that is, set the search lower limit to -50g, the search upper limit to 50g, the population size to 500, and the number of iterations to 350. The iteration results are shown in Table 2. Fig.10 shown.

[0113] Table 2 Original vibration data table

[0114]

[0115]

[0116] In S400, based on the enumeration method and the balancing weight solution information, the balancing weight solution information that minimizes the maximum residual vibration amplitude is determined as the optimal balancing weight information.

[0117] Without loss of generality, since the core advantage of the enumeration method lies in its completeness, that is, it ensures that all potential solution spaces can be traversed, so as to not only find all feasible solutions, but also identify the optimal weighting scheme under a specific optimization goal (such as minimizing the maximum value of the residual vibration of each measuring point), the weighting candidate solutions of each balance plane are substituted into the influence coefficient method one by one, the residual vibration level of each measuring point under each weighting scheme is evaluated, and the weighting configuration that minimizes the maximum residual vibration amplitude is screened out.

[0118] Specifically, after the terminal device generates the balancing weight solution information, the terminal device can quickly determine the balancing weight solution information that minimizes the maximum residual vibration amplitude as the optimal balancing weight information based on the enumeration method and the balancing weight solution information.

[0119] Exemplarily, after determining the correction amount after stabilization, the terminal device can continue to solve by enumeration, that is, looping from the first solution after stabilization to the last solution, and then finding the solution that minimizes the maximum value of the residual vibration of each measuring point at 3 measuring points and 4 speeds from the solution set, and the corresponding counterweight is the final counterweight, as shown in Table 3.

[0120] Table 3 Balance weight data table

[0121] First balance plane Second balance plane The third balance plane Fourth balance plane 6.1g,77.3° 13.7g,-127.8° 7.1g,-55.4° 7.9g,-179.9°

[0122] In one possible implementation, in order to verify the validity and accuracy of the aircraft engine rotor model, the terminal equipment can be verified on a high-speed aircraft engine rotor test bench. For example, in the test preparation stage, the inspection personnel can install eddy current sensors at the first measuring point, the second measuring point and the third measuring point to measure the vibration displacement, and then install acceleration sensors at the second support seat and the third support seat for modal testing experiments. At the same time, eddy current sensors are installed at the key phase groove on the shaft as key phase sensors, and an electronic balance is used for weighing. A 15g screw is added to the threaded hole of the turbine disk as the initial unbalanced mass. The counterweight ring used to balance the counterweight mass is provided with a threaded hole, so the counterweight can be removed and assembled by disassembling the screws.

[0123] Without loss of generality, see Fig.11 (a) Fig.11 (b) and Fig.11(c), the amplitude in the figure represents the amplitude corresponding to the maximum vibration; based on the high-speed aircraft engine rotor system designed in the present application, when the rotation speed is 4700 revolutions per minute, the peak-to-peak amplitude is reduced by 54.81%; when the rotation speed is 5000 revolutions per minute, the peak-to-peak amplitude is reduced by 58.42%; when the rotation speed is 5300 revolutions per minute, the peak-to-peak amplitude is reduced by 59.4%; when the rotation speed is 5600 revolutions per minute, the peak-to-peak amplitude is reduced by 58.19%.

[0124] The implementation principle of the WCSSA-based aero-engine rotor dynamic balancing optimization method without trial weights in the embodiment of the present application is as follows: the terminal device can first obtain the aero-engine rotor model, and then perform vibration analysis and processing on the aero-engine rotor model to generate original vibration information and transfer function matrix information, and then generate balancing weight solution information based on the original vibration information and transfer function matrix information based on the WCSSA algorithm, and finally, based on the enumeration method and the balancing weight solution information, determine the balancing weight scheme information that minimizes the maximum residual vibration amplitude as the optimal weight information, thereby optimizing the dynamic balancing process of high-speed rotors based on virtual prototype technology, reducing the trial weight link in the traditional dynamic balancing optimization process, and effectively improving the dynamic balancing efficiency.

[0125] It should be noted that the size of the serial numbers of the steps in the above embodiments does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present application.

[0126] The embodiment of the present application also provides an aircraft engine rotor non-test weight dynamic balancing optimization system based on WCSSA. For ease of description, only the parts related to the present application are shown, such as Fig.12 As shown, the system 120 includes:

[0127] The aircraft engine rotor model acquisition module 121 is used to acquire a preset aircraft engine rotor model;

[0128] The original vibration information generating module 123 is used to analyze and process the aircraft engine rotor model to generate original vibration information and transfer function matrix information;

[0129] The balancing weight solution information generating module 123 is used to generate the balancing weight solution information according to the original vibration information and the transfer function matrix information based on the preset WCSSA algorithm, wherein the balancing weight solution information includes a plurality of balancing weight scheme information;

[0130] The optimal balancing weight information determination module 124 is used to determine the balancing weight solution information that minimizes the maximum residual vibration amplitude as the optimal balancing weight information based on the enumeration method and the balancing weight solution information.

[0131] Optionally, the system 120 further includes:

[0132] Aircraft engine rotor model building module: used to build aircraft engine rotor models.

[0133] Optionally, the above-mentioned aircraft engine rotor model building module includes:

[0134] Aircraft engine rotor system size information acquisition submodule: used to obtain aircraft engine rotor system size information;

[0135] The aircraft engine rotor system three-dimensional model diagram information generation submodule is used to generate the aircraft engine rotor system three-dimensional model diagram information based on the preset three-dimensional design software and the aircraft engine rotor system size information;

[0136] Virtual prototype model information generation submodule: used to model and process the three-dimensional model diagram information of the aircraft engine rotor system based on the preset finite element software to generate virtual prototype model information;

[0137] Aircraft engine rotor model determination submodule: used to determine that the virtual prototype model information is an aircraft engine rotor model.

[0138] Optionally, the system 120 further includes:

[0139] Theoretical speed information acquisition module: used to obtain theoretical speed information and critical speed information based on virtual prototype model information;

[0140] A validity verification information generation module: used to generate validity verification information according to theoretical speed information and critical speed information, wherein the validity verification information is verification pass information or verification fail information;

[0141] Preset model parameter modification module: used for modifying the preset model parameters of the finite element software if the validity verification information is verification failure information, and re-executing the preset finite element software to perform modeling processing on the three-dimensional model diagram information of the aircraft engine rotor system, generate virtual prototype model information, and generate validity verification information according to the theoretical speed information and the critical speed information, until the validity verification information is verification passing information;

[0142] Determine the execution module: if the validity verification information is the verification passed information, then execute and determine that the virtual prototype model information is the aircraft engine rotor model.

[0143] Optionally, the system 120 further includes:

[0144] WCSSA algorithm generation module: used to improve the preset SAA algorithm according to the preset infinite folding chaotic mapping algorithm, the preset whale optimization algorithm, and the preset Cauchy mutation strategy to generate the WCSSA algorithm.

[0145] Optionally, the WCSSA algorithm generation module includes:

[0146] The first improved algorithm generation submodule is used to improve the initialization population of the preset SAA algorithm according to the preset infinite folding chaotic mapping algorithm to generate a first improved algorithm;

[0147] The second improved algorithm generating submodule is used to improve the update position corresponding to the discoverer position of the first improved algorithm according to the preset whale optimization algorithm to generate a second improved algorithm;

[0148] WCSSA algorithm generation submodule: used to improve the update formula corresponding to the follower position of the second improved algorithm according to the preset Cauchy perturbation mutation boosting algorithm, and generate the WCSSA algorithm.

[0149] It should be noted that the information interaction, execution process and other contents between the above-mentioned modules are based on the same concept as the method embodiment of the present application. Their specific functions and technical effects can be found in the method embodiment part and will not be repeated here.

[0150] The present application also provides a terminal device, such as Fig.13 As shown, the terminal device 130 of this embodiment includes: a processor 131, a memory 132, and a computer program 133 stored in the memory 132 and executable on the processor 131. When the processor 131 executes the computer program 133, the steps in the above-mentioned aircraft engine rotor non-test weight dynamic balancing optimization method embodiment are implemented, such as Figure 1 Steps S100 to S400 shown; or, when the processor 131 executes the computer program 133, the functions of each module in the above device are realized, for example Fig.12 The functions of modules 121 to 124 are shown.

[0151] The terminal device 130 may be a computing device such as a desktop computer, a notebook, a PDA, or a cloud server, and the terminal device 130 includes but is not limited to a processor 131 and a memory 132. Those skilled in the art will appreciate that Fig.13 It is only an example of the terminal device 130 and does not constitute a limitation of the terminal device 130. It may include more or fewer components than shown in the figure, or a combination of certain components, or different components. For example, the terminal device 130 may also include input and output devices, network access devices, buses, etc.

[0152] Among them, the processor 131 can be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc.; the general-purpose processor can be a microprocessor or the processor can also be any conventional processor, etc.

[0153] The memory 132 may be an internal storage unit of the terminal device 130, such as a hard disk or memory of the terminal device 130, or an external storage device of the terminal device 130, such as a plug-in hard disk, a smart memory card (Smart Media Card, SMC), a secure digital (Secure Digital, SD) card, a flash card (FlashCard), etc. equipped on the terminal device 130; further, the memory 132 may also include both an internal storage unit and an external storage device of the terminal device 130, and the memory 132 may also store a computer program 133 and other programs and data required by the terminal device 130, and the memory 132 may also be used to temporarily store data that has been output or is to be output.

[0154] One embodiment of the present application also provides a computer-readable storage medium, which stores a computer program, and when the computer program is executed by a processor, the steps of each of the above method embodiments can be implemented. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form, etc.; the computer-readable medium may include: any entity or device that can carry computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium, etc.

[0155] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, all equivalent changes made according to the methods, principles, and structures of the present application should be included in the protection scope of the present application.

Claims

1. A WCSSA-based method for optimizing dynamic balancing of aircraft engine rotors without test weight, characterized in that: The method comprises: Obtain a preset aircraft engine rotor model; Analyzing and processing the aircraft engine rotor model to generate original vibration information and transfer function matrix information; Based on a preset WCSSA algorithm, generating balancing weight solution set information according to the original vibration information and the transfer function matrix information, wherein the balancing weight solution set information includes a plurality of balancing weight scheme information; Based on the enumeration method and the balancing weight solution set information, the balancing weight solution information that minimizes the maximum residual vibration amplitude is determined as the optimal balancing weight information.

2. The method according to claim 1, characterized in that Before obtaining the preset aircraft engine rotor model, the method further includes: Constructing the aero-engine rotor model; Wherein, constructing the aero-engine rotor model comprises: Obtain aircraft engine rotor system size information; Based on the preset three-dimensional design software, according to the size information of the aircraft engine rotor system, generate the three-dimensional model diagram information of the aircraft engine rotor system; Based on the preset finite element software, the three-dimensional model diagram information of the aircraft engine rotor system is modeled and processed to generate virtual prototype model information; The virtual prototype model information is determined to be the aircraft engine rotor model.

3. The method according to claim 2, characterized in that After the three-dimensional model diagram information of the aircraft engine rotor system is modeled based on the preset finite element software to generate virtual prototype model information, the method further includes: Based on the virtual prototype model information, obtaining theoretical speed information and critical speed information; Generate validity verification information according to the theoretical speed information and the critical speed information, wherein the validity verification information is verification pass information or verification fail information; If the validity verification information is the verification failure information, modify the preset model parameters of the finite element software, and re-execute the preset finite element software to perform modeling processing on the three-dimensional model diagram information of the aircraft engine rotor system to generate virtual prototype model information, until the validity verification information is generated according to the theoretical speed information and the critical speed information, until the validity verification information is the verification pass information; If the validity verification information is the verification pass information, the step of determining that the virtual prototype model information is the aircraft engine rotor model is executed.

4. The method according to claim 1, characterized in that: Before generating the balancing weight solution information based on the preset WCSSA algorithm according to the original vibration information and the transfer function matrix information, the method further includes: According to the preset infinite folding chaotic mapping algorithm, the preset whale optimization algorithm, and the preset Cauchy mutation strategy, the preset SAA algorithm is improved to generate the WCSSA algorithm; The method of improving the preset SAA algorithm according to the preset infinite folding chaotic mapping algorithm, the preset whale optimization algorithm, and the preset Cauchy mutation strategy to generate the WCSSA algorithm includes: According to the preset infinite folding chaotic mapping algorithm, the initialization population of the preset SAA algorithm is improved to generate a first improved algorithm; According to the preset whale optimization algorithm, the update position corresponding to the discoverer position of the first improved algorithm is improved to generate a second improved algorithm; According to the preset Cauchy perturbation mutation boosting algorithm, the update formula corresponding to the follower position of the second improved algorithm is improved to generate the WCSSA algorithm.

5. The method according to claim 4, characterized in that The infinite folding chaotic mapping algorithm is: In the formula, x i+1 is the variable value at the i+1th iteration, i is the number of iterations, x i is the variable value at the i-th iteration, α is the control parameter; The whale optimization algorithm is: In the formula, The updated value of the position of the individual in the dth dimension simulated by the ith algorithm at the t+1th generation; is the value of the current global optimal position in the dth dimension; Simulate the value of the current position of the individual in the dth dimension at the tth generation for the i-th algorithm; is a randomly selected algorithm in the tth generation to simulate the position of an individual in the dth dimension; A is a preset control parameter, A = 2a × ra; a is a preset linearly decreasing control parameter, a decreases from 2 to 0; r is a random vector between [0, 1]; D is a preset distance parameter, which is used to determine the step size of the position update, D = |C × X*(t) - X(t)|; C = 2r; X*(t) is the position of the current optimal solution; The Cauchy perturbation mutation boosting algorithm is: In the formula, The variable values ​​of the individuals simulated by the ith algorithm and the individuals simulated by the jth algorithm at the t+1th iteration; is the variable value of the ith algorithm simulation individual and the jth algorithm simulation individual at the tth iteration; γ is a preset scaling factor, which is used to adjust the mutation intensity; Cauchy(0,1) is a Cauchy distribution random number with a mean of 0 and a scale parameter of 1.

6. A WCSSA-based aero-engine rotor non-test weight dynamic balancing optimization system, characterized in that: The system comprises: Aircraft engine rotor model acquisition module: used to obtain a preset aircraft engine rotor model; The original vibration information generating module is used to analyze and process the aero-engine rotor model to generate original vibration information and transfer function matrix information; A balancing weight solution information generation module is used to generate balancing weight solution information based on a preset WCSSA algorithm according to the original vibration information and the transfer function matrix information, wherein the balancing weight solution information includes a plurality of balancing weight scheme information; The optimal balancing weight information determination module is used to determine the balancing weight solution information that minimizes the maximum residual vibration amplitude as the optimal balancing weight information based on the enumeration method and the balancing weight solution information.

7. The system according to claim 6, characterized in that The system further comprises: Aircraft engine rotor model building module: used to build the aircraft engine rotor model.

8. A terminal device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 5 are implemented.

9. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 5 are implemented.

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