A blade aerodynamic excitation verification method, device, electronic device and storage medium

Abstract

This application discloses a blade aerodynamic excitation verification method, device, electronic device, and storage medium. The method includes the following steps: S1, analyzing and selecting target modes using a simulation calculation model; S2, calculating the theoretical resonant speed, detuned vibration response, theoretical dwell speed, etc. based on the target modes; S3, determining the strain gauge patch position and patch direction based on the vibration response simulation calculation results and vibration stress; S4, performing a first speed sweep test by attaching the strain gauge to obtain the measured resonant speed and the modal frequency of the blade under the working state; S5, correcting the parameters of the simulation calculation model and calculating the simulated average vibration stress; S6, performing a second speed sweep test to obtain the measured vibration stress; and S7, analyzing the test results to obtain the calculation error of the aerodynamic excitation. This application has a small number of measurement points, high test accuracy, and minimal impact on aerodynamic excitation, effectively reflecting the comprehensive effect of aerodynamic excitation at different locations on the blade surface.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a blade aerodynamic excitation verification method, device, equipment and storage medium. Background Art

[0002] Flow-induced vibration is a major cause of high-cycle fatigue failure in aeroengine blades. Predicting the forced vibration response of blades during the design phase and avoiding harmful resonances are important approaches to preventing high-cycle fatigue failure. Aerodynamic excitation and damping are the primary input parameters for blade forced vibration response analysis. Blade aerodynamic excitation can be derived through the calculation of unsteady aerodynamic forces. The aerodynamic excitation of a blade includes amplitude and phase information, and the amplitude and phase of the aerodynamic excitation generally vary at different locations on the blade surface. The accuracy of the aerodynamic excitation analysis directly impacts the accuracy of the blade forced vibration response analysis. By validating the simulation analysis results of the aerodynamic excitation, the aerodynamic calculation model can be modified, improving the accuracy of the simulation analysis of the aerodynamic excitation, thereby improving the prediction accuracy of the forced vibration response and more effectively avoiding harmful resonances of the blade.

[0003] Because the blade's forced vibration response is influenced by numerous factors, aerodynamic excitation, damping, detuning, and the accuracy of the finite element model all affect the blade's forced vibration response. Testing the strain under resonance by attaching strain gauges is difficult to verify the accuracy of aerodynamic excitation analysis. For example, when the error in aerodynamic excitation simulation analysis is large, but the aerodynamic excitation error just offsets the error in damping, detuning, or the finite element model, the simulation analysis results of the vibration stress at blade resonance may agree well with the strain gauge test results. In this case, the strain test error cannot reflect the accuracy of the aerodynamic excitation analysis. Pressure changes on the blade surface can usually be achieved using dynamic stress testing, but dynamic pressure testing is difficult to arrange sensors on rotating blades. Furthermore, dynamic pressure sensors are easily affected by aerodynamic pressure after installation, affecting test accuracy. Furthermore, pressure can only be measured at certain points, making it difficult to obtain pressure pulsations at different locations and failing to fully reflect the aerodynamic excitation distribution characteristics of the blade. At the same time, the aerodynamic excitation of the blade can be obtained through simulation calculation. Since the aerodynamic excitation amplitude and phase at different positions on the blade surface are different, and the engine rotor blades are in a high-speed rotation state when working, it is necessary to arrange more measuring points on the rotating blade surface to obtain the aerodynamic excitation distribution law of the blade. Therefore, the aerodynamic excitation test of the engine rotating blade is difficult to achieve, and it is difficult to verify the accuracy of the aerodynamic excitation simulation analysis.

[0004] In summary, the existing technologies mainly have the following problems:

[0005] 1) It is difficult to arrange sensors for frequent dynamic pressure tests on rotating blades, and the sensor arrangement can easily affect the aerodynamic pressure and thus the test accuracy;

[0006] 2) It is difficult to obtain the dynamic pressure distribution at different positions when performing dynamic pressure testing on rotating blades;

[0007] 3) The resonance strain test includes the influence of multiple factors such as excitation, damping, detuning and model error, and cannot fully reflect the magnitude of aerodynamic excitation. Summary of the Invention

[0008] On the one hand, the present application provides a blade aerodynamic excitation verification method for solving the technical problems of the prior art requiring a large number of measurement points, low test accuracy, a large impact on aerodynamic excitation, and inability to fully reflect the size of aerodynamic excitation at different blade positions.

[0009] This application is implemented through the following scheme:

[0010] A blade aerodynamic excitation verification method comprises the following steps:

[0011] S1. Use a simulation calculation model to simulate the rotor blade-disk coupled mode. During the calculation, based on the main excitation source of the rotor blade, the target mode is selected from the modes with resonance through resonance mode analysis, mode shape analysis, and frequency difference between adjacent modes;

[0012] S2. Calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode The detuned vibration response of the blade under different damping ratios is shown in the following table. Determining the theoretical engine stall speed using detuned vibration response , and based on the engine theoretical dwell speed The speed ratio ξ is obtained by adding the theoretical resonance speed i ;

[0013] S3, based on the simulation results of the forced vibration response of the detuned blade under aerodynamic excitation, the theoretical parking speed of each engine n i The vibration stress under the strain gauge determines the position and direction of the strain gauge patch;

[0014] S4. After the strain gauge is pasted, the first speed sweep test is carried out to obtain the measured resonance speed n i,0 , and obtain the modal frequency of the blade in working state according to the vibration response peak value of the strain gauge test;

[0015] S5. The modal frequency obtained from the first speed sweep test and the frequency of the calculated target mode f i The comparison results of the simulation model are used to modify the parameters of the simulation model. After modification, the speed ratio ξ i The average vibration stress of each strain gauge under different modes is calculated based on the invariance principle. ;

[0016] S6. Carry out the second speed sweep test. During the test, set a stable dwell time at each actual dwell speed to obtain the measured vibration stress of all strain gauges at each dwell speed. The actual dwell speed N i According to the measured resonance speed n i,0 and speed ratio ξ i Calculated;

[0017] S7. Analyze the test results of the strain gauge and compare the measured vibration stress with the average vibration stress calculated by simulation to obtain the calculation error of the aerodynamic excitation.

[0018] Preferably, the step S1 specifically includes the steps of:

[0019] S11. Use a finite element simulation model to simulate the rotor blade-disk coupled modes, consider the main excitation sources of the rotor blades during the calculation, and analyze the modes with resonance;

[0020] S12. After determining the resonant modes, perform modal screening based on the vibration modes for subsequent verification of the comprehensive effect of aerodynamic excitation at different positions on blade vibration using strain gauges. The vibration modes include: blade first-order bending mode, blade torsional mode, blade bending-torsion coupled mode, and blade high-order chord-wise bending mode.

[0021] S13, further screening out the target mode based on the modes screened according to the vibration shape to avoid mutual coupling between adjacent modes, wherein the frequency difference between the target mode and the adjacent mode is greater than the required threshold ,Right now:

[0022] ;

[0023] in, is the frequency of the target mode to be calculated, and are the frequencies of two adjacent modes.

[0024] Preferably, the step S2 specifically includes the steps of:

[0025] S21. Calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode ;

[0026] S22. Applying aerodynamic excitation of the blade to the surface of the blade, calculating the deharmonic vibration response of the blade using different damping ratios for the target mode, and obtaining a curve of the vibration amplitude of each blade as a function of the rotation speed under different damping ratios;

[0027] S23, according to the theoretical resonance speed Determining the theoretical engine stall speed using detuned vibration response , where the selected engine theoretical parking speed is Both of the following conditions are met:

[0028] (a) Theoretical dwell speed Theoretical resonant speed in tune with the blade The difference is less than the set threshold;

[0029] (b) Theoretical dwell speed The deharmonic vibration responses of the blades under different damping satisfy the following relationship:

[0030] ;

[0031] The theoretical dwell speed The maximum vibration amplitude of all blades under different damping conditions is The theoretical dwell speed The minimum vibration amplitude of all blades under different damping conditions, γ is the vibration amplitude difference threshold;

[0032] S24, based on theoretical dwell speed Theoretical resonant speed of the blade in the tuned state Get the speed ratio:

[0033] .

[0034] Preferably, when determining the strain gauge patch position and patch direction in step S3, a position where the vibration stress is large and the stress distribution is uniform is selected as the strain gauge patch position, and the patch direction is consistent with the maximum principal stress direction.

[0035] Preferably, the step S5 specifically includes:

[0036] S51, comparing the modal frequency obtained from the first speed sweep test with the calculated target modal frequency;

[0037] S52, if the difference in the comparison is greater than a set threshold, modifying the parameters of the simulation calculation model, the modified parameters including: material parameters, temperature field, and constraint conditions;

[0038] S53, after the simulation calculation model is corrected, according to the principle of constant speed ratio, the speed ratio ξ is calculated. i When the detuned vibration stress of each blade under different damping conditions at the patch position and direction is calculated, the average value is taken to obtain the simulated average vibration stress of each strain gauge under different modes. .

[0039] Preferably, the step S6 specifically includes the steps of:

[0040] S61. Obtain the measured resonance speed based on the first speed sweep test , based on the speed ratio ξ i The actual stopping speed during the blade test is calculated based on the unchanged principle:

[0041] ;

[0042] S62. Carry out the second speed sweep test. During the test, make a stable stop at each actual dwell speed for more than 30 seconds to obtain the measured vibration stress of all strain gauges at each dwell speed. .

[0043] Preferably, the step S7 specifically includes the steps of:

[0044] S71. Analyze the test results of each strain gauge, compare the measured vibration strain with the simulated vibration stress, calculate the corresponding error, and obtain the error of each strain gauge in each mode:

[0045] ;

[0046] S72. Take the average value of the errors of each strain gauge in each mode as calculation error of aerodynamic excitation.

[0047] Another preferred embodiment of the present application further provides a blade aerodynamic excitation verification device, comprising:

[0048] The target mode screening module is used to simulate the rotor blade-disk coupled mode using a simulation calculation model. During the calculation, the target mode is screened from the resonant modes through resonance mode analysis, mode shape analysis, and frequency difference between adjacent modes based on the main excitation source of the rotor blade.

[0049] The detuned vibration response and theoretical dwell speed calculation module is used to calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode. The detuned vibration response of the blade under different damping ratios is shown in the following table. Determining the theoretical engine stall speed using detuned vibration response , and based on the engine theoretical dwell speed The speed ratio ξ is obtained by adding the theoretical resonance speed i ;

[0050] The patch position and direction determination module is used to determine the position and direction of the patch according to the simulation results of the forced vibration response of the detuned blade disk under aerodynamic excitation and the theoretical parking speed of each engine. The vibration stress under the strain gauge determines the position and direction of the strain gauge patch;

[0051] The speed sweep test module is used to perform the first speed sweep test after the strain gauge is attached to obtain the measured resonant speed. , and obtain the modal frequency of the blade in working state according to the vibration response peak value of the strain gauge test;

[0052] The simulation calculation model correction module is used to correct the simulation calculation model based on the comparison results of the modal frequency obtained from the first speed sweep test and the calculated target mode frequency. After correction, the simulation calculation average vibration stress of each strain gauge under different modes is calculated according to the principle of constant speed ratio;

[0053] The speed dwell test module is used to carry out the second speed sweep test. During the test, a stable dwell time is set at each actual dwell speed to obtain the measured vibration stress of all strain gauges at each dwell speed. The actual dwell speed is calculated based on the measured resonant speed and the speed ratio.

[0054] The test data analysis module is used to analyze the test results of the strain gauge and compare the measured vibration stress with the average vibration stress calculated by simulation to obtain the calculation error of the aerodynamic excitation.

[0055] On the other hand, the present application also provides an electronic device, including 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 blade aerodynamic excitation verification method when executing the computer program.

[0056] On the other hand, the present application further provides a storage medium, which includes a stored program, and when the program is run, controls the device where the storage medium is located to execute the steps of the blade aerodynamic excitation verification method.

[0057] Compared with the existing technology, this application has the following beneficial effects:

[0058] The present application provides a blade aerodynamic excitation verification method, device, electronic device, and storage medium. The blade aerodynamic excitation verification method, on the one hand, uses target mode screening, resonance analysis, frequency differences between adjacent modes, and modal vibration shape analysis to analyze detuned responses and determine dwell speeds. On the other hand, a test spectrum for dynamic stress measurement is provided, including a speed sweep test and a speed dwell test, combined with simulation analysis for model correction to avoid the influence of model errors and uncertain parameters such as damping and detuning. Secondly, the present application provides an aerodynamic excitation verification method based on strain gauge testing. The technical solution of the present application establishes a corresponding relationship between aerodynamic excitation and vibration stress, and the aerodynamic excitation analysis error is represented by the analysis error of the vibration stress. The strain gauge bonding has little effect on the aerodynamic excitation, has high analysis accuracy, and can reflect the comprehensive effect of aerodynamic excitation at different locations on the blade surface. Therefore, the blade aerodynamic excitation verification method of the present application uses the strain analysis error of the strain gauge to represent the aerodynamic excitation simulation analysis error. It has the characteristics of a small number of measurement points, high test accuracy, and little impact on aerodynamic excitation. It can also reflect the comprehensive effect of aerodynamic excitation at different locations on the blade surface.

[0059] In addition to the above-described purposes, features and advantages, the present application also has other purposes, features and advantages. The present application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0060] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0061] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, a person skilled in the art can derive other drawings based on these drawings without inventive effort, among which:

[0062] Figure 1 This is a flow chart of a blade aerodynamic excitation verification method according to a preferred embodiment of the present application;

[0063] Figure 2 This is the curve of the vibration amplitude of each blade of the present application changing with the rotation speed at different damping ratios (different colors represent different damping ratios);

[0064] Figure 3 This is a schematic diagram of the speed change over time in the first speed sweep test;

[0065] Figure 4 This is a schematic diagram of the change of speed with time in the second speed sweep test;

[0066] Figure 5 This is a schematic diagram of a module of a blade aerodynamic excitation verification device according to a preferred embodiment of the present application;

[0067] Figure 6 This is a schematic block diagram of an electronic device according to a preferred embodiment of the present application;

[0068] Figure 7 It is a diagram of the internal structure of a computer device according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0069] It should be understood that the specific embodiments described herein are merely used to explain the technical solutions of the present application and are not intended to limit the present application.

[0070] In order to better understand the technical solution of the present application, a detailed description will be given below in conjunction with the accompanying drawings and specific implementation methods.

[0071] It should be noted that the execution entity of this embodiment may be a computing service device with data processing, network communication, and program execution capabilities, such as a tablet computer, personal computer, or mobile phone, or a blade aerodynamic excitation verification device capable of performing the aforementioned functions. This embodiment and the following embodiments will be described below using the blade aerodynamic excitation verification device as an example.

[0072] like Figure 1 As shown, a preferred embodiment of the present application provides a blade aerodynamic excitation verification method, comprising the steps of:

[0073] S1. Use a simulation calculation model to simulate the rotor blade-disk coupled mode. During the calculation, based on the main excitation source of the rotor blade, the target mode is selected from the modes with resonance through resonance mode analysis, mode shape analysis, and frequency difference between adjacent modes;

[0074] S2. Calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode The detuned vibration response of the blade under different damping ratios is shown in the following table. Determining the theoretical engine stall speed using detuned vibration response , and based on the engine theoretical dwell speed The speed ratio ξ is obtained by adding the theoretical resonance speed i ;

[0075] S3, based on the simulation results of the forced vibration response of the detuned blade under aerodynamic excitation, the theoretical parking speed of each engine n i The vibration stress under the strain gauge determines the position and direction of the strain gauge patch;

[0076] S4. After the strain gauge is pasted, the first speed sweep test is carried out to obtain the measured resonance speed n i,0 , and obtain the modal frequency of the blade in working state according to the vibration response peak value of the strain gauge test;

[0077] S5. The modal frequency obtained from the first speed sweep test and the frequency of the calculated target mode f i The comparison results of the simulation model are used to modify the parameters of the simulation model. After modification, the speed ratio ξ i The average vibration stress of each strain gauge under different modes is calculated based on the invariance principle. ;

[0078] S6. Carry out the second speed sweep test. During the test, set a stable dwell time at each actual dwell speed to obtain the measured vibration stress of all strain gauges at each dwell speed. The actual dwell speed N i According to the measured resonance speed n i,0 and speed ratio ξ i Calculated;

[0079] S7. Analyze the test results of the strain gauge and compare the measured vibration stress with the average vibration stress calculated by simulation to obtain the calculation error of the aerodynamic excitation.

[0080] This embodiment provides a blade aerodynamic excitation verification method. This method, on the one hand, uses target mode screening, resonance analysis, frequency differences between adjacent modes, and modal shape analysis to analyze detuned responses and determine dwell speeds. On the other hand, it provides a test spectrum for dynamic stress measurement, including speed sweep tests and speed dwell tests, and combines simulation analysis with model correction to avoid the influence of model errors and uncertain parameters such as damping and detuning. Furthermore, this embodiment provides an aerodynamic excitation verification method based on strain gauge testing. This method's technical solution establishes a correspondence between aerodynamic excitation and vibration stress, and uses the analysis error of vibration stress to represent the aerodynamic excitation analysis error. Strain gauge bonding has little effect on aerodynamic excitation, resulting in high analysis accuracy and the ability to reflect the combined effects of aerodynamic excitation at different locations on the blade surface. This embodiment's blade aerodynamic excitation verification method, which uses strain gauge strain analysis error to represent aerodynamic excitation simulation analysis error, features a small number of measurement points, high test accuracy, and minimal impact on aerodynamic excitation. Furthermore, it can reflect the combined effects of aerodynamic excitation at different locations on the blade surface.

[0081] In a preferred embodiment of the present application, step S1 specifically includes the following steps:

[0082] S11. Use a finite element simulation model to simulate the rotor blade-disk coupled modes, consider the main excitation sources of the rotor blades during the calculation, and analyze the modes with resonance;

[0083] S12. After determining the resonant modes, perform modal screening based on the vibration modes for subsequent verification of the comprehensive effect of aerodynamic excitation at different positions on blade vibration using strain gauges. The vibration modes include: blade first-order bending mode, blade torsional mode, blade bending-torsion coupled mode, and blade high-order chord-wise bending mode.

[0084] S13, further screening out the target mode based on the modes screened according to the vibration shape to avoid mutual coupling between adjacent modes, wherein the frequency difference between the target mode and the adjacent mode is greater than the required threshold ,Right now:

[0085] ;

[0086] in, is the frequency of the target mode to be calculated, and are the frequencies of two adjacent modes, The reference value is 10%.

[0087] In this embodiment, the finite element simulation calculation is performed through steps S11 to S13 to screen out the target mode. The purpose and benefits thereof include: identifying the mode with resonance and avoiding mutual coupling between modes.

[0088] In a preferred embodiment of the present application, step S2 specifically includes the following steps:

[0089] S21. Calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode ;

[0090] S22. Apply the aerodynamic excitation of the blade to the surface of the blade, and calculate the detuned vibration response of the blade using different damping ratios for the target mode, and obtain the curve of the vibration amplitude of each blade at different damping ratios as a function of the rotation speed (see Figure 2 );

[0091] S23, according to the theoretical resonance speed Determining the theoretical engine stall speed using detuned vibration response , where the selected engine theoretical parking speed is Both of the following conditions are met:

[0092] (a) Theoretical dwell speed Theoretical resonant speed in tune with the blade The difference is less than the set threshold;

[0093] (b) Theoretical dwell speed The deharmonic vibration responses of the blades under different damping satisfy the following relationship:

[0094] ;

[0095] The theoretical dwell speed The maximum vibration amplitude of all blades under different damping conditions is The theoretical dwell speed The minimum vibration amplitude of all blades under different damping conditions is γ, which is the vibration amplitude difference threshold with a reference value of 3%.

[0096] S24, based on theoretical dwell speed Theoretical resonant speed of the blade in the tuned state Get the speed ratio:

[0097] .

[0098] In this embodiment, the theoretical resonant speed of the blade disk in the tuned state is calculated through steps S21 to S24. , Theoretical engine stop speed and speed ratio, its purpose and benefits include: being used to determine the dwell speed in subsequent speed dwell tests.

[0099] In a preferred embodiment of the present application, when determining the strain gauge patch position and patch direction in step S3, a position with large vibration stress and uniform stress distribution is selected as the strain gauge patch position, and the patch direction is consistent with the maximum principal stress direction, such as Figure 3 As shown, during the first speed sweep test, the engine should be slowly accelerated to maximum speed without pausing. After the test is complete, the modal frequencies of the blade under operating conditions are determined based on the peak vibration response measured by the strain gauges. The benefits and objectives of selecting the strain gauge placement and orientation in this manner include: The strain gauges have higher sensitivity, making it easier to measure large vibration stresses, thereby reducing test errors.

[0100] In a preferred embodiment of the present application, step S5 specifically includes:

[0101] S51, comparing the modal frequency obtained from the first speed sweep test with the calculated target modal frequency;

[0102] S52, if the difference in the comparison is greater than a set threshold, modifying the parameters of the simulation calculation model, the modified parameters including: material parameters, temperature field, and constraint conditions;

[0103] S53, after the simulation calculation model is corrected, according to the principle of constant speed ratio, the speed ratio ξ is calculated. i When the detuned vibration stress of each blade under different damping conditions at the patch position and direction is calculated, the average value is taken to obtain the simulated average vibration stress of each strain gauge under different modes. .

[0104] In steps S51 to S53 of this embodiment, the parameters of the simulation model are modified by comparing the modal frequency obtained by the experiment with the frequency of the calculated target mode. Based on the modified simulation model and the principle of constant speed ratio, the deharmonic vibration stress of each blade under different damping at the patch position and direction is calculated and the average value is taken to obtain the simulated average vibration stress of each strain gauge under different modes. ,The purpose and benefits include that according to the parking speed determined by this scheme, due to the influence of detuning and damping, there are still small differences in the calculated results of the patch positions and directions of different blades, and taking the average value can reduce the analysis error.

[0105] In a preferred embodiment of the present application, step S6 specifically includes the following steps:

[0106] S61. Obtain the measured resonance speed based on the first speed sweep test , based on the speed ratio ξ i The actual stopping speed during the blade test is calculated based on the unchanged principle:

[0107] ;

[0108] S62, carry out the second speed sweep test (see Figure 4 ), during the test, a stable stop is made at each actual stop speed, the stop time is more than 30 seconds, and the measured vibration stress of all strain gauges at each stop speed is obtained .

[0109] In this embodiment, the actual dwell speed of the blade during the test is obtained by converting the measured resonance speed and the speed ratio through steps S61-S62, and a second speed sweep test is carried out according to the actual dwell speed to obtain the measured vibration stress of all strain gauges at each dwell speed. , its purpose and benefits include: By calculating the actual dwell speed and performing a second speed sweep test, the vibration stress at a stable dwell speed of a given speed ratio can be obtained, avoiding large test errors caused by unstable dwell speed.

[0110] In a preferred embodiment of the present application, step S7 specifically includes the following steps:

[0111] S71. Analyze the test results of each strain gauge, compare the measured vibration strain with the simulated vibration stress, calculate the corresponding error, and obtain the error of each strain gauge in each mode:

[0112] ;

[0113] S72. Take the average value of the errors of each strain gauge in each mode as calculation error of aerodynamic excitation.

[0114] In this embodiment, the measured vibration strain is compared with the simulated vibration stress in steps S71-S72 to calculate the corresponding error to obtain the error of each strain gauge in each mode. Then, the average value of the error of each strain gauge in each mode is obtained. As the calculation error of aerodynamic excitation, the difference between the actual stress measured by the strain gauge and the simulation calculation result can reflect the calculation error of aerodynamic excitation, that is, It can be expressed as the difference between the aerodynamic excitation simulation results and the actual aerodynamic excitation. Its purpose and benefits include: the vibration stress of different modes tested by different strain gauges may be different from the simulation calculated values. Taking the average value can reduce the impact of this difference.

[0115] In summary, since the technical solution of this application can basically eliminate the influence of damping, detuning and simulation model on the results, the vibration stress of the blade is mainly affected by aerodynamic excitation. The difference between the strain gauge measured stress and the simulation calculation result can reflect the calculation error of aerodynamic excitation, that is, It can be expressed as the difference between the aerodynamic excitation simulation result and the actual aerodynamic excitation.

[0116] In the preferred embodiment of the present application, the aerodynamic excitation of the unsteady simulation of a blade is verified based on the technical solution of the present application. Strain gauges are attached to a total of 3 blades, with two strain gauges attached to each blade. The comparison of the simulation and test results is shown in Table 1. In Table 1, the average error between the simulation and test of stress at the test dwell speed is The value is 16.5%, which can be used to evaluate the accuracy of aerodynamic excitation analysis.

[0117] Table 1: Verification of engine blade aerodynamic excitation simulation accuracy

[0118]

[0119] like Figure 5 As shown, another preferred embodiment of the present application further provides a blade aerodynamic excitation verification device, comprising:

[0120] The target mode screening module is used to simulate the rotor blade-disk coupled mode using a simulation calculation model. During the calculation, the target mode is screened from the resonant modes through resonance mode analysis, mode shape analysis, and frequency difference between adjacent modes based on the main excitation source of the rotor blade.

[0121] The detuned vibration response and theoretical dwell speed calculation module is used to calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode. The detuned vibration response of the blade under different damping ratios is shown in the following table. Determining the theoretical engine stall speed using detuned vibration response , and based on the engine theoretical dwell speed The speed ratio ξ is obtained by adding the theoretical resonance speed i ;

[0122] The patch position and direction determination module is used to determine the position and direction of the patch according to the simulation results of the forced vibration response of the detuned blade disk under aerodynamic excitation and the theoretical parking speed of each engine. The vibration stress under the strain gauge determines the position and direction of the strain gauge patch;

[0123] The speed sweep test module is used to perform the first speed sweep test after the strain gauge is attached to obtain the measured resonant speed. , and obtain the modal frequency of the blade in working state according to the vibration response peak value of the strain gauge test;

[0124] The simulation calculation model correction module is used to correct the simulation calculation model based on the comparison results of the modal frequency obtained from the first speed sweep test and the calculated target mode frequency. After correction, the simulation calculation average vibration stress of each strain gauge under different modes is calculated according to the principle of constant speed ratio;

[0125] The speed dwell test module is used to carry out the second speed sweep test. During the test, a stable dwell time is set at each actual dwell speed to obtain the measured vibration stress of all strain gauges at each dwell speed. The actual dwell speed is calculated based on the measured resonant speed and the speed ratio.

[0126] The test data analysis module is used to analyze the test results of the strain gauge and compare the measured vibration stress with the average vibration stress calculated by simulation to obtain the calculation error of the aerodynamic excitation.

[0127] The blade aerodynamic excitation verification device provided in the application utilizes the blade aerodynamic excitation verification method described in the aforementioned embodiment, resolving the technical issues of the prior art, such as the large number of measurement points required, low test accuracy, significant impact on aerodynamic excitation, and inability to fully reflect the magnitude of aerodynamic excitation at different blade positions. Compared to the prior art, the electronic device provided in this application achieves the same beneficial effects as the blade aerodynamic excitation verification method described in the aforementioned embodiment, and the other technical features of the electronic device are the same as those disclosed in the aforementioned embodiment, and are not further detailed here.

[0128] like Figure 6 As shown, a preferred embodiment of the present application also provides an electronic device, including 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 blade aerodynamic excitation verification method in the above embodiment when executing the computer program.

[0129] The electronic device provided in this application, employing the blade aerodynamic excitation verification method described in the aforementioned embodiment, can address the technical issues of the prior art, such as the large number of measurement points required, low test accuracy, significant impact on aerodynamic excitation, and inability to fully reflect the magnitude of aerodynamic excitation at different blade positions. Compared to the prior art, the electronic device provided in this application achieves the same beneficial effects as the blade aerodynamic excitation verification method described in the aforementioned embodiment, and the other technical features of the electronic device are the same as those disclosed in the aforementioned embodiment, and are not further elaborated here.

[0130] like Figure 7 As shown, the preferred embodiment of the present application further provides a computer device, which can be a terminal or a liveness detection server, and its internal structure diagram can be as shown in FIG. Figure 7 As shown. The computer device includes a processor, a memory, and a network interface connected via a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, the steps of the above-mentioned blade aerodynamic excitation verification method are implemented.

[0131] Those skilled in the art will understand that Figure 7 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than shown in the figure, or combine certain components, or have a different component arrangement.

[0132] The computer device provided in this application, employing the blade aerodynamic excitation verification method described in the aforementioned embodiment, can address the technical issues of the prior art, such as the large number of measurement points required, low test accuracy, significant impact on aerodynamic excitation, and an inability to fully reflect the magnitude of aerodynamic excitation at different blade positions. Compared to the prior art, the computer device provided in this application offers the same beneficial effects as the blade aerodynamic excitation verification method described in the aforementioned embodiment, and will not be further elaborated upon here.

[0133] A preferred embodiment of the present application further provides a storage medium, which includes a stored program. When the program is run, the device where the storage medium is located is controlled to execute the steps of the blade aerodynamic excitation verification method in the above embodiment.

[0134] It should be noted that the steps shown in the flowcharts of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and that, although a logical order is shown in the flowcharts, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0135] If the functions described in the method of this embodiment are implemented in the form of a software functional unit and sold or used as an independent product, they can be stored in a storage medium readable by one or more computing devices. Based on this understanding, the part of the embodiment of this application that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium and includes a number of instructions for enabling a computing device (which can be a personal computer, server, mobile computing device or network device, etc.) to execute all or part of the steps of the method described in each embodiment of this application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, and other media that can store program code.

[0136] Those skilled in the art will appreciate that the embodiments of the present application may be provided as methods, systems, or computer program products. Therefore, the present application may take the form of a fully hardware embodiment, a fully software embodiment, or an embodiment combining software and hardware. Furthermore, the present application may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of the present application may be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0137] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or block in the flowchart and / or block diagram, as well as the combination of processes and / or blocks in the flowchart and / or block diagram, 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 flowchart and / or block diagram. 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.

[0138] 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.

[0139] 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.

[0140] The present application also provides a computer program product, comprising a computer program, which implements the steps of the blade aerodynamic excitation verification method as described above when executed by a processor.

[0141] The computer program product provided in this application addresses the technical issues of existing technologies, such as the large number of measurement points required, low test accuracy, significant impact on aerodynamic excitation, and inability to fully reflect the magnitude of aerodynamic excitation at different blade positions. Compared to existing technologies, the computer program product provided in this application offers the same beneficial effects as the blade aerodynamic excitation verification method provided in the aforementioned embodiments, and will not be further elaborated here.

[0142] Although the preferred embodiments of the present application 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 application.

[0143] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

Claims

1. A blade aerodynamic excitation verification method, characterized in that: Including steps: S1. Use a simulation calculation model to simulate the rotor blade-disk coupled mode. During the calculation, based on the main excitation source of the rotor blade, the target mode is selected from the modes with resonance through resonance mode analysis, mode shape analysis, and frequency difference between adjacent modes; S2. Calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode The detuned vibration response of the blade under different damping ratios is shown in the following table. Determining the theoretical engine stall speed using detuned vibration response , and based on the engine theoretical dwell speed The speed ratio ξ is obtained by adding the theoretical resonance speed i ; S3, based on the simulation results of the forced vibration response of the detuned blade under aerodynamic excitation, the theoretical parking speed of each engine n i The vibration stress under the strain gauge determines the position and direction of the strain gauge patch; S4. After the strain gauge is pasted, the first speed sweep test is carried out to obtain the measured resonance speed n i,0 , and obtain the modal frequency of the blade in working state according to the vibration response peak value of the strain gauge test; S5. The modal frequency obtained from the first speed sweep test and the frequency of the calculated target mode f i The comparison results of the simulation model are used to modify the parameters of the simulation model. After modification, the speed ratio ξ i The average vibration stress of each strain gauge under different modes is calculated based on the invariance principle. ; S6. Carry out the second speed sweep test. During the test, set a stable dwell time at each actual dwell speed to obtain the measured vibration stress of all strain gauges at each dwell speed. The actual dwell speed N i According to the measured resonance speed n i,0 and speed ratio ξ i Calculated; S7. Analyze the test results of the strain gauge and compare the measured vibration stress with the average vibration stress calculated by simulation to obtain the calculation error of the aerodynamic excitation.

2. The blade aerodynamic excitation verification method according to claim 1, characterized in that: The step S1 specifically includes the following steps: S11. Use a finite element simulation model to simulate the rotor blade-disk coupled modes, consider the main excitation sources of the rotor blades during the calculation, and analyze the modes with resonance; S12. After determining the resonant modes, perform modal screening based on the vibration modes for subsequent verification of the comprehensive effect of aerodynamic excitation at different positions on blade vibration using strain gauges. The vibration modes include: blade first-order bending mode, blade torsional mode, blade bending-torsion coupled mode, and blade high-order chord-wise bending mode. S13, further screening out the target mode based on the modes screened according to the vibration shape to avoid mutual coupling between adjacent modes, wherein the frequency difference between the target mode and the adjacent mode is greater than the required threshold ,Right now: ； in, is the frequency of the target mode to be calculated, and are the frequencies of two adjacent modes.

3. The blade aerodynamic excitation verification method according to claim 1, characterized in that: The step S2 specifically includes the following steps: S21. Calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode ; S22. Applying aerodynamic excitation of the blade to the surface of the blade, calculating the deharmonic vibration response of the blade using different damping ratios for the target mode, and obtaining a curve of the vibration amplitude of each blade as a function of the rotation speed under different damping ratios; S23, according to the theoretical resonance speed Determining the theoretical engine stall speed using detuned vibration response , where the selected engine theoretical parking speed is Both of the following conditions are met: (a) Theoretical dwell speed Theoretical resonant speed in tune with the blade The difference is less than the set threshold; (b) Theoretical dwell speed The deharmonic vibration response of each blade under different damping conditions satisfies the following relationship: ； The theoretical dwell speed The maximum vibration amplitude of all blades under different damping conditions is The theoretical dwell speed The minimum vibration amplitude of all blades under different damping conditions, γ is the vibration amplitude difference threshold; S24, based on theoretical dwell speed Theoretical resonant speed of the blade in the tuned state Get the speed ratio: 。 4. The blade aerodynamic excitation verification method according to claim 1, characterized in that: When determining the strain gauge patch position and patch direction in step S3, a position where the vibration stress is large and the stress distribution is uniform is selected as the strain gauge patch position, and the patch direction is consistent with the maximum principal stress direction.

5. The blade aerodynamic excitation verification method according to claim 1, characterized in that: The step S5 specifically includes: S51, comparing the modal frequency obtained from the first speed sweep test with the calculated target modal frequency; S52, if the difference in the comparison is greater than a set threshold, modifying the parameters of the simulation calculation model, the modified parameters including: material parameters, temperature field, and constraint conditions; S53, after the simulation calculation model is corrected, according to the principle of constant speed ratio, the speed ratio ξ is calculated. i When the detuned vibration stress of each blade under different damping conditions at the patch position and direction is calculated, the average value is taken to obtain the simulated average vibration stress of each strain gauge under different modes. .

6. The blade aerodynamic excitation verification method according to claim 5, characterized in that: The step S6 specifically includes the following steps: S61. Obtain the measured resonance speed based on the first speed sweep test , based on the speed ratio ξ i The actual stopping speed during the blade test is calculated based on the unchanged principle: ； S62. Carry out the second speed sweep test. During the test, make a stable stop at each actual dwell speed for more than 30 seconds to obtain the measured vibration stress of all strain gauges at each dwell speed. .

7. The blade aerodynamic excitation verification method according to claim 6, characterized in that: The step S7 specifically includes the following steps: S71. Analyze the test results of each strain gauge, compare the measured vibration strain with the simulated vibration stress, calculate the corresponding error, and obtain the error of each strain gauge in each mode: ； S72. Take the average value of the errors of each strain gauge in each mode as calculation error of aerodynamic excitation.

8. A blade aerodynamic excitation verification device, characterized in that: include: The target mode screening module is used to simulate the rotor blade-disk coupled mode using a simulation calculation model. During the calculation, the target mode is screened from the resonant modes through resonance mode analysis, mode shape analysis, and frequency difference between adjacent modes based on the main excitation source of the rotor blade. The detuned vibration response and theoretical dwell speed calculation module is used to calculate the theoretical resonant speed of the blade in the tuned state based on the parameters of the target mode. The detuned vibration response of the blade under different damping ratios is shown in the following table. Determining the theoretical engine stall speed using detuned vibration response , and based on the engine theoretical dwell speed The speed ratio ξ is obtained by adding the theoretical resonance speed i ; The patch position and direction determination module is used to determine the position and direction of the patch according to the simulation results of the forced vibration response of the detuned blade disk under aerodynamic excitation and the theoretical parking speed of each engine. The vibration stress under the strain gauge determines the position and direction of the strain gauge patch; The speed sweep test module is used to perform the first speed sweep test after the strain gauge is attached to obtain the measured resonant speed. , and obtain the modal frequency of the blade in working state according to the vibration response peak value of the strain gauge test; The simulation calculation model correction module is used to correct the simulation calculation model based on the comparison results of the modal frequency obtained from the first speed sweep test and the calculated target mode frequency. After correction, the simulation calculation average vibration stress of each strain gauge under different modes is calculated according to the principle of constant speed ratio; The speed dwell test module is used to carry out the second speed sweep test. During the test, a stable dwell time is set at each actual dwell speed to obtain the measured vibration stress of all strain gauges at each dwell speed. The actual dwell speed is calculated based on the measured resonant speed and the speed ratio. The test data analysis module is used to analyze the test results of the strain gauge and compare the measured vibration stress with the average vibration stress calculated by simulation to obtain the calculation error of the aerodynamic excitation.

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 computer program, the steps of the blade aerodynamic excitation verification method according to any one of claims 1 to 7 are implemented.

10. A storage medium comprising a stored program, characterized in that: When the program is running, the device where the storage medium is located is controlled to execute the steps of the blade aerodynamic excitation verification method according to any one of claims 1 to 7.

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