Blade dynamic frequency test determination method and device, electronic equipment and test system

Abstract

The invention discloses a blade dynamic frequency test determination method and device, electronic equipment and a test system, and the method comprises the steps: collecting blade data, constructing a blade finite element model, and obtaining blade modal data according to the blade finite element model; a load working condition is set, harmonic response analysis is conducted on the blade finite element model according to the load working condition, unit load frequency response data are obtained, and the unit load frequency response data comprise real part response data and imaginary part response data; the excitation force is calculated according to nozzle parameters, the nozzle load is calculated according to the blade data and the nozzle parameters, the nozzle setting data are compared and adjusted according to the nozzle load and the unit load frequency response data, and the nozzle setting data comprise the nozzle number and the distribution angle; and obtaining strain amplitude data according to the rotor speed, the nozzle load corresponding to the nozzle parameter and the unit load frequency response data, and confirming a test scheme according to the strain amplitude data.

Description

Technical Field

[0001] This invention relates to the field of gas turbine research and development technology, specifically to a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of blades. Background Technology

[0002] In the development stage of gas turbines, in order to accurately obtain the natural frequency of the blades in the rotating state and ensure that the blade resonance frequency avoids the known excitation frequency, blade excitation tests are generally carried out on a rotating test chamber. The current practice is to add a sensing device to the blade, install a nozzle at a certain height of the blade, and spray high-pressure gas or hydraulic oil into the nozzle. Under the condition of continuous excitation of the blade by gas / oil, the rotor is driven and the speed is changed to perform scanning tests. The natural frequency of the blade is identified by frequency domain analysis of the signal from the sensing device.

[0003] However, existing technologies lack relevant guidance for experimental design. Experimental design relies heavily on the experience of the experimenter, as key parameters such as the number of nozzles, nozzle spray direction, and excitation location are crucial. This experience-driven approach makes it difficult to guarantee accurate excitation of the target vibration mode in every experiment. In some cases, the key vibration mode may not be excited, leading to incomplete experimental results and an inability to accurately assess the resonance risk of the blade during actual operation. Due to the uncertainty and incompleteness of the experimental results, subsequent blade design and optimization work may lack accurate data support, potentially resulting in unclear optimization directions during the design phase, an inability to effectively avoid resonance problems, and an increased risk of blade failure during actual operation. Furthermore, the trial-and-error method of repeatedly adjusting the excitation location during the experiment leads to excessively long experimental cycles or failure to achieve the expected experimental goals. The main reason is the lack of rapid calculation and optimization methods for the blade's resonance speed and resonance response under the experimental scheme. The conceivable calculation method is fluid-structure analysis, but since the experiment is conducted in a vacuum environment, the calculation of discontinuous fluids is currently technically immature and consumes significant computational resources.

[0004] Patent document CN118443250A discloses a test method for simulating excitation factors under blade rotation, including S1, blade design; S2, vibration calculation; S3, determining the number and location of nozzles; S4, flow rate calibration; S5, temperature calibration; S6, strain gauge attachment; S7, vibration strain response measurement; and S8, resonance margin evaluation. If the design requirements are met, the test stops; otherwise, S1 is repeated. This method does not solve the problem that existing design methods cannot ensure test accuracy, efficiency, and safety, and it is difficult to accurately assess resonance risk.

[0005] Patent document CN115752977A discloses a test bench and method for measuring the vibration of gas turbine rotating blades based on tip timing. The test bench includes a first mounting base, a sensor support base, a second mounting base, and a motor support base fixed on a base. The main shaft is mounted on the first and second mounting bases respectively via bearings through the sensor support base. The sensor support base located above the main shaft is a downwardly curved arched structure, on which a gas-driven nozzle and at least one tip timing sensor are mounted. The main shaft is driven to one end of a torque-speed sensor through a coupling, and the other end of the torque-speed sensor is driven to a motor mounted on the motor support base. However, this method does not solve the problem that the existing design method cannot ensure the test accuracy, efficiency, and safety, and it is difficult to accurately assess the resonance risk.

[0006] In summary, neither of the two existing patents addresses the problem that existing design methods cannot ensure experimental accuracy, efficiency, and safety, and are difficult to accurately assess resonance risks. Summary of the Invention

[0007] Based on the above-mentioned technical problems, this invention proposes a method, device, electronic equipment and test system for determining the dynamic frequency of blades, which solves the problems that existing design methods cannot ensure test accuracy, efficiency and safety, and are difficult to accurately assess resonance risk.

[0008] To achieve the above objectives, this invention proposes a method for determining the dynamic frequency of a blade through testing.

[0009] A method for determining the dynamic frequency of a blade by testing includes: Collect blade data to construct a finite element model of the blade, and obtain blade modal data based on the finite element model of the blade. Set a load condition, and perform harmonic response analysis on the finite element model of the blade according to the load condition to obtain unit load frequency response data, which includes real part response data and imaginary part response data; The excitation force is calculated based on the nozzle parameters. The nozzle load is calculated based on the blade data and the nozzle parameters. The nozzle setting data is adjusted by comparing the nozzle load and the unit load frequency response data. The nozzle setting data includes the number of nozzles and the distribution angle. The strain amplitude data is obtained based on the rotor speed, the nozzle load corresponding to the nozzle parameters, and the unit load frequency response data. The test plan is then confirmed based on the strain amplitude data.

[0010] Furthermore, the blade modal data includes modal order, natural frequency, and strain ratio.

[0011] Further, obtaining blade modal data based on the blade finite element model includes: setting two model strain gauges on the blade finite element model, simulating the blade finite element model based on different rotor speeds using simulation analysis software, obtaining the modal order of the blade finite element model at different rotor speeds, the natural frequency corresponding to the modal order, and the strain data and principal strain data at the model strain gauges.

[0012] Furthermore, obtaining blade modal data based on the blade finite element model also includes: obtaining the strain ratio based on the ratio of the strain data at the strain gauge of the model to the principal strain data.

[0013] Furthermore, setting the load conditions includes: setting the load amplitude and preset frequency, and calculating the chordal load and vertical chordal load based on the load amplitude and the preset frequency, respectively.

[0014] Furthermore, harmonic response analysis is performed on the finite element model of the blade according to the load conditions to obtain unit load frequency response data, including: inputting the chordal load and the vertical chordal load into simulation analysis software to obtain unit load frequency response data, and constructing a load frequency response curve based on the unit load frequency response data.

[0015] Furthermore, the nozzle parameters include nozzle mass flow rate, nozzle airflow absolute velocity, and nozzle rotation radius.

[0016] Furthermore, the excitation force includes a chordal component and a vertical chordal component.

[0017] Furthermore, the excitation force is calculated based on the nozzle parameters, including: The blade data includes blade length, nozzle airflow angle, and blade mounting angle; Calculate the tangential velocity of the radius blade based on the rotor speed and the nozzle rotation radius; The relative velocity of the airflow is obtained based on the tangential velocity of the radial blade and the absolute velocity of the airflow from the nozzle. The chordal component and the vertical chordal component are calculated based on the nozzle mass flow rate, the relative velocity of the airflow, the tangential velocity of the radial blade, the absolute velocity of the airflow from the nozzle, and the blade installation angle, respectively.

[0018] Further, calculating the nozzle load based on the blade data and the nozzle parameters includes: The nozzle amplitude is calculated based on the nozzle mass flow rate and the relative velocity of the airflow. The duration is calculated based on the rotor speed, the nozzle rotation radius, and the blade length; The fundamental frequency of the rotational speed is obtained based on the rotor speed. The nozzle load is calculated based on the nozzle setting data, the nozzle amplitude, the duration, and the rotational speed base frequency.

[0019] Further, adjusting the nozzle setting data by comparing the nozzle load and the unit load frequency response data includes: constructing a load comparison diagram based on different nozzle setting data and different modal orders according to frequency, adjusting the nozzle setting data so that the amplitude of the nozzle load is within the frequency range corresponding to different modal orders, and saving the nozzle setting data.

[0020] Further, strain amplitude data is obtained based on rotor speed, nozzle load corresponding to the nozzle parameters, and unit load frequency response data, including: calculating total strain based on the chordal component, the vertical chordal component, the real part response data, and the imaginary part response data; generating strain amplitude data based on the rotational speed interval set by the rotor speed and the total strain.

[0021] Furthermore, the total strain is calculated based on the chordal component, the perpendicular chordal component, the real part response data, and the imaginary part response data, as expressed below: , in The total strain is given. For the chord component, The vertical chord component. The real part response data, The imaginary part response data, Let be the real part of the complex number, and let I be the imaginary part of the complex number. It is the imaginary unit.

[0022] Furthermore, the expressions for the real and imaginary parts of the resulting complex number are as follows: , in Let be the real part of the complex number, and let I be the imaginary part of the complex number. The mass flow rate of the nozzle. The relative velocity of the airflow, This is the impact load spectrum vector constructed based on the unit load frequency response data. The blade installation angle, The relative velocity angle, The data refers to the chord component in the real response data. The data refers to the vertical chord component in the real response data. The data refers to the chord component in the imaginary response data. The data refers to the vertical chord component in the imaginary response data.

[0023] Furthermore, the expression for the impact load spectrum vector is as follows: , in Let be the frequency spectrum vector of the impact load. The data refers to the frequencies that correspond sequentially in the unit load frequency response data, where n is the index.

[0024] Further, confirming the test plan based on the strain amplitude data includes: determining whether the strain amplitude data corresponding to different frequencies and modal orders is greater than the preset strain data; if it is greater than the strain data, then the corresponding nozzle setting data is used as the test plan; if it is less than the strain data, then the nozzle setting data is adjusted and iterated until the obtained strain amplitude data is greater than the preset strain data.

[0025] To achieve the above objectives, the present invention also proposes a blade dynamic frequency test determination device.

[0026] A blade dynamic frequency testing and determination device, characterized in that it comprises: The acquisition and construction module is used to acquire blade data, construct a blade finite element model, and obtain blade modal data based on the blade finite element model. The load calculation module is used to set the load conditions and perform harmonic response analysis on the finite element model of the blade according to the load conditions to obtain unit load frequency response data, which includes real part response data and imaginary part response data. The nozzle setting module is used to calculate the excitation force based on the nozzle parameters, calculate the nozzle load based on the blade data and the nozzle parameters, and adjust the nozzle setting data by comparing the nozzle load and the unit load frequency response data. The nozzle setting data includes the number of nozzles and the distribution angle. The test determination module is used to obtain strain amplitude data based on the rotor speed, the nozzle load corresponding to the nozzle parameters, and the unit load frequency response data, and to confirm the test plan based on the strain amplitude data.

[0027] To achieve the above objectives, the present invention also proposes a blade dynamic frequency testing system.

[0028] A blade dynamic frequency testing system, characterized in that it includes a rotor, a disk, a blade, a strain gauge, a signal transmitting device, a signal receiving device, a signal analysis system, and nozzles. The blade is arranged radially along the rotor, the strain gauge is disposed on the blade, the signal transmitting device is disposed at one end of the rotor, the signal transmitting device is connected to the strain gauge via wired or wireless means, the signal receiving device is connected to the signal analysis system via wired or wireless means, the signal analysis system is used to obtain vibration data collected by the strain gauge, and the nozzles are evenly arranged circumferentially along the rotor for spraying gas or hydraulic oil onto the blade.

[0029] Based on the above technical solution, the present invention has at least the following beneficial effects: 1. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of blades. By collecting blade data to construct a finite element model and obtain modal data, it provides a precise theoretical basis for the scientific design of the test scheme. Through harmonic response analysis, it obtains unit load frequency response data, enabling a refined analysis of the dynamic response characteristics of the blade under unit load conditions, providing a key basis for subsequent load and nozzle parameter optimization. By accurately calculating the excitation force and nozzle load, and combining the unit load frequency response data with adjustments to the number and distribution angle of nozzles, it achieves systematic optimization of nozzle setting data, ensuring that the nozzle setting method can efficiently and accurately excite the key vibration modes of the blade during the test, significantly improving the accuracy and reliability of the test. Based on rotor speed, nozzle parameters, nozzle load, and unit load frequency response data, it calculates the strain amplitude and confirms the test scheme accordingly, which not only effectively shortens the test cycle and reduces test costs, but also significantly improves the safety and repeatability of the test. This method provides high-precision and high-reliability data support for optimizing the test scheme for obtaining vibration parameters of gas turbine blades, making resonance tests on blades more accurate, effectively reducing the resonance risk of blades in actual operation, and improving the overall operating performance and reliability of gas turbines.

[0030] 2. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of a blade. By setting strain gauges on the finite element model of the blade and performing simulation analysis at different rotor speeds, it is possible to accurately obtain modal data such as the modal order, natural frequency, and strain ratio of the blade. Combined with the dynamic characteristics of the blade at different speeds, it provides a high-precision theoretical basis for the design of the test scheme. Furthermore, by setting load conditions and performing harmonic response analysis, unit load frequency response data is obtained, and load frequency response curves are constructed. This enables a refined analysis of the dynamic response characteristics of the blade under different load conditions, providing a unitized and visualized frequency response data. This process not only improves the accuracy of modal analysis but also provides a key basis for the optimization of nozzle parameters and the scientific design of the test scheme. It allows for the calculation of unit load frequency response data when calculating multiple nozzle cases, ensuring that the key vibration modes of the blade can be excited efficiently and accurately during the test, significantly improving the accuracy and reliability of the test, and providing more accurate data support for blade design optimization.

[0031] 3. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of a blade. By calculating the nozzle load using blade data and nozzle parameters, it can identify load comparison diagrams corresponding to different nozzle setting parameters, i.e., different design schemes. It allows selection of nozzle setting data that can excite the maximum vibration frequency of the blade, and can also formulate multiple nozzle setting data according to test requirements. By accurately calculating the nozzle parameters and the chordal and vertical chordal components of the excitation force, combined with unit load frequency response data, it calculates the total strain and generates strain amplitude data corresponding to different modes. This allows for further screening to determine whether the scheme meets the strain amplitude requirements. This invention can dynamically adjust the nozzle setting data to ensure that the nozzle load amplitude reaches the optimal effect in the frequency region corresponding to different modal orders. It not only optimizes the nozzle parameters but also ensures the scientific validity and effectiveness of the test scheme through strain amplitude data verification, significantly improving the success rate and efficiency of the test, reducing test costs and time, and providing reliable technical support for the development and optimization of gas turbine blades.

[0032] 4. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of a blade. The testing system integrates key components such as a rotor, blade, strain gauges, signal transmitting and receiving devices, a signal analysis system, and nozzles to construct an efficient and precise testing platform specifically designed for studying the dynamic characteristics of blades in rotation. The strain gauges can collect the vibration data of the blade in real time, while the signal transmitting and receiving devices ensure that this data can be stably and accurately transmitted to the signal analysis system to obtain the vibration data generated by the blade during the test. Different systems can be connected and transmit signals via wired or wireless means, ensuring the accuracy and stability of the system. This testing system can quickly respond to different testing needs, adapt to various blades and operating conditions, greatly shorten the testing cycle, reduce testing costs, and provide an efficient and reliable testing method for the research and optimization of gas turbine blades. Attached Figure Description

[0033] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 A flowchart of a method for determining the dynamic frequency of a blade according to one embodiment is shown; Figure 2 A schematic diagram of a blade finite element model according to one embodiment is shown; Figure 3 A schematic diagram of the nozzle parameters of a blade according to one embodiment is shown; Figure 4 The real response curve of one embodiment is shown; Figure 5 The imaginary part response curve of one embodiment is shown; Figure 6 A load comparison diagram is shown in one embodiment when the number of nozzles is 2; Figure 7 A load comparison diagram is shown in one embodiment when the number of nozzles is 3; Figure 8 A vibration waterfall diagram of one embodiment is shown; Figure 9 A schematic diagram of a blade dynamic frequency testing device according to one embodiment is shown; Figure 10 A cross-sectional schematic diagram of a blade dynamic frequency testing system according to one embodiment is shown; Figure 11 An axial schematic diagram of a blade dynamic frequency testing system according to one embodiment is shown; Figure 12A schematic diagram of the structure of a blade dynamic frequency test to determine the product is shown in one embodiment; Figure 13 A schematic diagram of the structure of an electronic device according to an embodiment is shown.

[0034] The above figures include the following reference numerals: 1. Rotor; 2. Wheel; 3. Blade; 4. Strain gauge; 5. Signal transmitting device; 6. Signal receiving device; 7. Signal analysis system; 8. Air source; 9. Nozzle; 10. Finite element model of the blade; 31. Leaf blade; 32. Tenon; 1031. Model blade; 1032. Model tenon; 104. Model strain gauge. Detailed Implementation

[0035] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0036] The present invention will be further described in detail below with reference to specific embodiments, which should not be construed as limiting the scope of protection claimed by the present invention.

[0037] Example

[0038] To address the problems of existing design methods failing to ensure experimental accuracy, efficiency, and safety, and making it difficult to accurately assess resonance risks, this invention proposes a method, apparatus, electronic equipment, and experimental system for determining blade dynamic frequency.

[0039] To achieve the above objectives, the present invention also proposes a method for determining the dynamic frequency of a blade.

[0040] In this embodiment, "simulation analysis software" refers to a professional software tool used for complex engineering calculations such as finite element analysis, modal analysis, and harmonic response analysis. It can help accurately simulate and analyze the dynamic response characteristics of blades under different operating conditions, and can be ANSYS, ABAQUS, NASTRAN, OLIDWORKS Simulation, or ADINA.

[0041] like Figure 1 The figure illustrates a method for determining the dynamic frequency of a blade according to an embodiment of the present invention. The process mainly includes the following steps: S101: Collect blade data to construct a finite element model of the blade, and obtain blade modal data based on the finite element model of the blade.

[0042] Specifically, constructing such Figure 2The blade finite element model 10 shown includes a blade body 1031 and a tenon 1032. Model strain gauges 104 are mounted on the blade body 1031. In this embodiment, two model strain gauges 104 are mounted. The principle for the placement of the model strain gauges 104 on the blade finite element model 10 is that the ratio of the strain data obtained by simulation analysis software at at least one model strain gauge 104 location to the maximum principal strain value in the principal strain data is greater than 0.20. In this embodiment, the strain gauges are positioned as follows: Figure 2 The arrangement shown is located near the air intake edge of the model blade 1031.

[0043] Furthermore, the blade modal data includes modal order, natural frequency, and strain ratio.

[0044] Specifically, the above-mentioned simulation analysis software was used to analyze... Figure 2 The blade finite element model 10 constructed in the model was simulated and analyzed. The modal orders and natural frequencies corresponding to the modal orders of the blade finite element model 10 at different high speeds were obtained. The strain data and principal strain data at strain gauge 104 of the model were obtained. According to the strain data, principal strain data and strain ratios of different modal orders, as shown in Table 1 below, the first column is the edge position, and the second, third, fourth and fifth columns are the strain ratios corresponding to the 1st, 2nd, 3rd and 4th modal orders, respectively. As shown in Table 2 below, the natural frequencies corresponding to the 1st, 2nd, 3rd and 4th modal orders at rotor speeds of 0%, 50%, and 100% Nnominal are the natural frequencies corresponding to the 1st, 2nd, 3rd and 4th modal orders, respectively. 100% Nnominal is 3000 rpm.

[0045] Table 1. Strain Ratio Correspondence Table

[0046] Table 2. Correspondence of Natural Frequencies

[0047] S102: Set the load conditions, and perform harmonic response analysis on the finite element model of the blade according to the load conditions to obtain unit load frequency response data, wherein the unit load frequency response data includes real part response data and imaginary part response data.

[0048] Furthermore, a load amplitude and a preset frequency are set, and the chordal load and the vertical chordal load are calculated based on the load amplitude and the preset frequency, respectively.

[0049] Specifically, the prestressed modes are calculated at the three different rotor speeds mentioned above, such as... Figure 3 The finite element model 10 of the blade is set around the rotor's rotation axis, with chordal A, vertical chordal U, and absolute velocity of the nozzle airflow respectively defined. relative velocity of airflow Blade installation angle Nozzle airflow angle and relative velocity angle .

[0050] Furthermore, chordal and vertical chordal loads were added to the nozzle excitation position during the simulation of the finite element model 10 of the blade using simulation analysis software. The maximum analysis frequency of the simulation analysis software was 1.1 times the natural frequency of the blade under test, the calculation frequency interval was 1Hz, and the amplitudes of the chordal and vertical chordal loads were both set to 1N, i.e., F. a =F u =1, calculate the chordal load, its expression is F a sin(2 The expression for the vertical chordal load is F(ft). u sin(2 ft), where F a and F u These represent the load amplitudes in the chord direction and perpendicular to the chord direction, respectively; f is the preset frequency; and t is time.

[0051] Furthermore, harmonic response analysis was performed on the input chordal and vertical chordal loads using simulation analysis software to obtain the chordal and vertical chordal strain response amplitudes at the strain gauge 104 position on the model blade 1031 at each frequency. The real and imaginary response data, i.e., the unit load frequency response data, are used to construct a load frequency response curve, such as... Figure 4 and Figure 5 As stated in, among which Figure 4 The real response curves are constructed from the real response data, with frequency on the horizontal axis and amplitude on the vertical axis. Ha,real represents the real response data in the chord direction, and Hu,real represents the real response data in the chord direction. Figure 5 The figure shows the imaginary response curves constructed from the imaginary response data, where Ha,img represents the imaginary response data in the chord direction, and Hu,img represents the imaginary response data in the chord direction.

[0052] S103: Calculate the excitation force based on the nozzle parameters, calculate the nozzle load based on the blade data and the nozzle parameters, and adjust the nozzle setting data by comparing the nozzle load and the unit load frequency response data. The nozzle setting data includes the number of nozzles and the distribution angle.

[0053] Furthermore, the nozzle parameters are set, including the nozzle mass flow rate, the absolute velocity of the nozzle airflow, and the nozzle rotation radius.

[0054] Furthermore, the blade data includes blade length, nozzle airflow angle, and blade installation angle. The radius-of-gravity blade tangential velocity is calculated based on the rotor speed and the nozzle rotation radius, and its expression is as follows: , in The radius of the blade tangential velocity, Where i is the rotor speed and i is the index. The nozzle rotation radius is the distance from the rotor axis perpendicular to the nozzle position. The relative velocity of the airflow is obtained based on the tangential velocity of the blades and the absolute velocity of the airflow at the nozzle, expressed as follows: , in The relative velocity of the airflow. The absolute velocity of the airflow at the nozzle. The radius of the blade tangential velocity, The nozzle airflow angle is given. The chordal component and the vertical chordal component are calculated based on the nozzle mass flow rate, the relative velocity of the airflow, the tangential velocity of the radial blade, the absolute velocity of the nozzle airflow, and the blade installation angle, respectively. Their expressions are as follows: , , , in The relative velocity angle, For the chord component, For the vertical chord component, The absolute velocity of the airflow at the nozzle. The radius of the blade tangential velocity, Install the blade angle. The nozzle airflow angle, The relative velocity of the airflow. This represents the nozzle mass flow rate.

[0055] Further, calculating the nozzle load based on the blade data and the nozzle parameters includes: The nozzle amplitude is calculated based on the nozzle mass flow rate and the relative velocity of the airflow, and its expression is as follows: , in For nozzle amplitude, This refers to the nozzle mass flow rate. The relative velocity of the airflow is given; the duration is calculated based on the rotor speed, the nozzle rotation radius, and the blade length, and its expression is as follows: , in The duration is calculated for the blade length, where L is the blade length, such as... Figure 2 As shown, The radius of the blade tangential velocity, The nozzle rotation radius, The rotor speed is [value]; the interval between the impact signals of two adjacent nozzles is [value]. m is the number of nozzles. The angles of the distribution of m nozzles are as follows: Figure 11 As shown, the fundamental frequency of the rotational speed is obtained based on the rotor speed, and its expression is as follows: , in The fundamental frequency of rotational speed, The rotor speed is used as the reference. The nozzle load is calculated based on the nozzle setting data, the nozzle amplitude, the duration, and the fundamental frequency of the rotational speed, and its expression is as follows: , in For nozzle load, For nozzle amplitude, The fundamental frequency of rotational speed, The duration is calculated based on the blade length, where m is the number of nozzles. Let m be the angles at which the nozzles are distributed.

[0056] Furthermore, based on different nozzle setting data, a load comparison diagram is constructed for the nozzle load and different modal orders according to frequency. The nozzle setting data is adjusted so that the amplitude of the nozzle load is within the frequency range corresponding to different modal orders, and the nozzle setting data is saved.

[0057] Specifically, in this embodiment, the number of nozzles m=2 and the number of nozzles m=3, and the distribution angle are respectively used. Nozzle mass flow rate , radius of blade tangential velocity Blade installation angle Nozzle installation angle Nozzle rotation radius , blade length Calculate the nozzle load, and construct the following based on the nozzle load and frequency: Figure 6 and Figure 7 The load comparison graph shown here represents frequencies on the horizontal axis and the amplitude of the nozzle load on the vertical axis. Figure 6 This is a load comparison chart with 2 nozzles. Figure 7 This is a load comparison chart with 3 nozzles. Figure 6 and Figure 7In the above table 2, the natural frequencies corresponding to different mode orders are plotted. Mode1, Mode2, Mode3, and Mode4 correspond to the 1st, 2nd, 3rd, and 4th order natural frequencies, respectively. Taking the 1st order as an example, Mode1 (274Hz-306Hz) is plotted in the table. Figure 6 In the process, the natural frequencies corresponding to other modal orders are plotted sequentially; because Figure 6 The amplitude of the nozzle load is within Mode 2, indicating that when the number of nozzles is 2, the maximum response frequency of the blade can be excited at the second order when tested with the parameters calculated above. Therefore, the scheme in this embodiment is effective. Figure 7 As described above, when the number of nozzles m=3, the maximum response frequency of the blades cannot be excited in any mode when the test is conducted with the parameters calculated above. Therefore, this scheme is invalid. The number of nozzles or the distribution angle needs to be adjusted and the above steps need to be repeated until the amplitude of the nozzle load is within the range of any mode. In other embodiments, the amplitude of the nozzle load can be made to exist in all modes or in a specified mode according to the requirements of the test, and the final number of nozzles and distribution angle can be determined as the nozzle setting data.

[0058] S104: Obtain strain amplitude data based on rotor speed, nozzle load corresponding to the nozzle parameters, and unit load frequency response data, and confirm the test plan based on the strain amplitude data.

[0059] Furthermore, the total strain is calculated based on the chordal component, the vertical chordal component, the real part response data, and the imaginary part response data. The strain amplitude data is generated based on the rotational speed interval set by the rotor speed and the total strain.

[0060] Furthermore, the total strain expression is as follows: , in The total strain is given. For the chord component, The vertical chord component. The real part response data, The imaginary part response data, Let be the real part of the complex number, and let I be the imaginary part of the complex number. It is the imaginary unit.

[0061] Furthermore, the expressions for the real and imaginary parts of the resulting complex number are as follows: , in Let be the real part of the complex number, and let I be the imaginary part of the complex number. The mass flow rate of the nozzle. The relative velocity of the airflow, This is the impact load spectrum vector constructed based on the unit load frequency response data. The blade installation angle, The relative velocity angle, The data refers to the chord component in the real response data. The data refers to the vertical chord component in the real response data. The data refers to the chord component in the imaginary response data. The data refers to the vertical chord component in the imaginary response data.

[0062] Furthermore, the expression for the impact load spectrum vector is as follows: , in Let be the frequency spectrum vector of the impact load. The data refers to the frequencies that correspond sequentially in the unit load frequency response data, where n is the index.

[0063] Further, it is determined whether the strain amplitude data corresponding to different frequencies and modal orders is greater than the preset strain data. If it is greater than the strain data, the corresponding nozzle setting data is used as the test scheme. If it is less than the strain data, the nozzle setting data is adjusted and iterated until the obtained strain amplitude data is greater than the preset strain data.

[0064] Specifically, strain amplitude data with two nozzles and a distribution angle of 45° are categorized according to different modal orders, such as... Figure 8 The vibration waterfall diagram shows the frequency on the X-axis, the rotor speed on the Y-axis, and the stress amplitude on the Z-axis. Mode1, Mode2, Mode3, and Mode4 represent the stress amplitude data generated at the 1st, 2nd, 3rd, and 4th order, respectively, with corresponding natural frequencies of 306Hz, 755Hz, 1565Hz, and 2360Hz. In this embodiment, the preset strain value is set to 5µm / m. Since the stress amplitude values ​​corresponding to Mode1 and Mode2 are greater than 5µm / m, the corresponding frequency, rotor speed, nozzle parameters, and nozzle settings are recorded as the experimental scheme.

[0065] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.

[0066] Based on another aspect of the embodiments of this application, the present invention also provides a blade dynamic frequency test determination device. For example... Figure 9 As shown, the device includes: The acquisition and construction module 901 is used to acquire blade data, construct a blade finite element model, and obtain blade modal data based on the blade finite element model. The load calculation module 902 is used to set the load conditions and perform harmonic response analysis on the blade finite element model according to the load conditions to obtain unit load frequency response data, the unit load frequency response data including real part response data and imaginary part response data. The nozzle setting module 903 is used to calculate the excitation force based on the nozzle parameters, calculate the nozzle load based on the blade data and the nozzle parameters, and adjust the nozzle setting data by comparing the nozzle load and the unit load frequency response data. The nozzle setting data includes the number of nozzles and the distribution angle. The test determination module 904 is used to obtain strain amplitude data based on the rotor speed, the nozzle load corresponding to the nozzle parameters, and the unit load frequency response data, and to confirm the test plan based on the strain amplitude data.

[0067] As an optional solution, the above-mentioned device is also used to: collect the blade modal data, including modal order, natural frequency and strain ratio.

[0068] As an optional solution, the above-mentioned device is also used to: obtain blade modal data based on the blade finite element model, including: setting two model strain gauges on the blade finite element model, simulating the blade finite element model based on different rotor speeds using simulation analysis software, and obtaining the modal order of the blade finite element model at different rotor speeds, the natural frequency corresponding to the modal order, and the strain data and principal strain data at the model strain gauges.

[0069] As an optional solution, the above-mentioned device is also used to: obtain blade modal data based on the blade finite element model, and further includes: obtaining the strain ratio based on the ratio of the strain data at the strain gauge of the model to the principal strain data.

[0070] As an optional solution, the above-mentioned device is also used to: set load conditions, including: setting load amplitude and preset frequency, and calculating chordal load and vertical chordal load according to the load amplitude and the preset frequency respectively.

[0071] As an optional solution, the above-mentioned device is also used to: perform harmonic response analysis on the finite element model of the blade according to the load conditions to obtain unit load frequency response data, including: inputting the chordal load and the vertical chordal load into simulation analysis software to obtain unit load frequency response data, and constructing a load frequency response curve based on the unit load frequency response data.

[0072] As an optional solution, the above-mentioned device is also used for: the nozzle parameters, including nozzle mass flow rate, nozzle airflow absolute velocity, and nozzle rotation radius.

[0073] As an alternative, the above-mentioned device is also used for: the excitation force, including a chordal component and a vertical chordal component.

[0074] As an optional solution, the above-mentioned device is also used to: calculate the excitation force based on the nozzle parameters, including: the blade data including blade length, nozzle airflow angle and blade installation angle; calculate the tangential velocity of the radial blade based on the rotor speed and the nozzle rotation radius; obtain the relative velocity of the airflow based on the tangential velocity of the radial blade and the absolute velocity of the airflow at the nozzle; and calculate the chordal component and the vertical chordal component based on the nozzle mass flow rate, the relative velocity of the airflow, the tangential velocity of the radial blade, the absolute velocity of the airflow at the nozzle, and the blade installation angle, respectively.

[0075] As an optional solution, the above-mentioned device is also used to: calculate the nozzle load based on the blade data and the nozzle parameters, including: calculating the nozzle amplitude based on the nozzle mass flow rate and the relative velocity of the airflow; calculating the duration based on the rotor speed, the nozzle rotation radius and the blade length; obtaining the rotational speed fundamental frequency based on the rotor speed; and calculating the nozzle load based on the nozzle setting data, the nozzle amplitude, the duration and the rotational speed fundamental frequency.

[0076] As an optional solution, the above-mentioned device is also used to: compare and adjust the nozzle setting data according to the nozzle load and the unit load frequency response data, including: constructing a load comparison diagram of the nozzle load and different modal orders according to frequency based on different nozzle setting data, adjusting the nozzle setting data so that the amplitude of the nozzle load is within the frequency region corresponding to different modal orders, and saving the nozzle setting data.

[0077] As an optional solution, the above-mentioned device is also used to: obtain strain amplitude data based on rotor speed, nozzle load corresponding to the nozzle parameters, and unit load frequency response data, including: calculating total strain based on the chordal component, the vertical chordal component, the real part response data, and the imaginary part response data; generating the strain amplitude data based on the rotational speed interval set according to the rotor speed and the total strain.

[0078] As an optional solution, the above-mentioned device is also used to: calculate the total strain based on the chordal component, the vertical chordal component, the real part response data, and the imaginary part response data, as expressed below: , in The total strain is given. For the chord component, The vertical chord component. The real part response data, The imaginary part response data, Let be the real part of the complex number, and let I be the imaginary part of the complex number. It is the imaginary unit.

[0079] As an optional solution, the above-mentioned apparatus is further used to: express the real and imaginary parts of the resulting complex number as follows: , in Let be the real part of the complex number, and let I be the imaginary part of the complex number. The mass flow rate of the nozzle. The relative velocity of the airflow, This is the impact load spectrum vector constructed based on the unit load frequency response data. The blade installation angle, The relative velocity angle, The data refers to the chord component in the real response data. The data refers to the vertical chord component in the real response data. The data refers to the chord component in the imaginary response data. The data refers to the vertical chord component in the imaginary response data.

[0080] As an optional solution, the above-mentioned device is further used for: the expression of the impact load spectrum vector is as follows: , in Let be the frequency spectrum vector of the impact load. The data refers to the frequencies that correspond sequentially in the unit load frequency response data, where n is the index.

[0081] As an optional solution, the above-mentioned device is also used to: confirm the test plan based on the strain amplitude data, including: determining whether the strain amplitude data corresponding to different frequencies and modal orders is greater than the preset value strain data; if it is greater than the strain data, then the corresponding nozzle setting data is used as the test plan; if it is less than the strain data, then the nozzle setting data is adjusted and iterated until the obtained strain amplitude data is greater than the preset value strain data.

[0082] In this application embodiment, the terms "module" or "unit" refer to a computer program or part of a computer program that has a predetermined function and works with other related parts to achieve a predetermined goal, and can be implemented wholly or partially using software, hardware (such as processing circuitry or memory), or a combination thereof. Similarly, a processor (or multiple processors or memory) can be used to implement one or more modules or units. Furthermore, each module or unit can be part of an overall module or unit that includes the functionality of that module or unit.

[0083] Regarding the apparatus in the above embodiments, the specific manner in which each module performs its operation has been described in detail in the embodiments related to the method, and will not be elaborated upon here.

[0084] Based on another aspect of the embodiments of this application, the present invention also provides a blade dynamic frequency testing system, such as... Figure 10 As shown, the system includes a rotor 1, a wheel 2, blades 3, strain gauges 4, a signal transmitting device 5, a signal receiving device 6, a signal analysis system 7, and nozzles 9. The blades 3 are arranged radially along the rotor 1, the strain gauges 4 are disposed on the blades 3, the signal transmitting device 5 is disposed at one end of the rotor 1, and the signal transmitting device 5 is connected to the strain gauges 4 via wired or wireless means. The signal receiving device 6 is connected to the signal analysis system 7 via wired or wireless means. The signal analysis system 7 is used to obtain the vibration data collected by the strain gauges 4. The nozzles 9 are evenly arranged circumferentially along the rotor 1 and are used to spray gas or hydraulic oil onto the blades 3.

[0085] Furthermore, the blade 3 includes a blade body 31 and a tenon 32. The tenon 32 can be fitted into the wheel disk 2 for testing, or it can be fixed to the wheel disk 2 by welding or other fixing methods. The blade body 31 is arranged radially along the wheel disk 2, and the strain gauge 4 is arranged on the blade body 31. The wheel disk 2 is fixed circumferentially to the outer periphery of the rotor 1.

[0086] Furthermore, such as Figure 11As shown, multiple nozzles 9 are evenly distributed on the same circumference, and the nozzles 9 have the same angle. The angle formed between the outermost nozzles 9 is the aforementioned distribution angle.

[0087] Furthermore, combined Figure 10 and Figure 11 As shown, gas source 8 supplies gas or hydraulic oil to nozzle 9.

[0088] According to one aspect of this application, a computer program product is provided, the computer program product comprising a computer program.

[0089] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0090] Figure 12 A schematic block diagram of a computer system architecture for implementing an electronic device according to embodiments of the present application is shown.

[0091] It should be noted that, Figure 12 The computer system 1200 of the electronic device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments of this application.

[0092] like Figure 12 As shown, the computer system 1200 includes a central processing unit (CPU) 1201, which can perform various appropriate actions and processes based on programs stored in read-only memory (ROM) 1202 or programs loaded from storage section 1208 into random access memory (RAM). The RAM 1203 also stores various programs and data required for system operation. The CPU 1201, ROM 1202, and RAM 1203 are interconnected via a bus 1204. An input / output interface 1205 (I / O interface) is also connected to the bus 1204.

[0093] The following components are connected to the input / output interface 1205: an input section 1206 including a keyboard, mouse, etc.; an output section 1207 including a cathode ray tube (CRT), liquid crystal display (LCD), etc., and speakers, etc.; a storage section 1208 including a hard disk, etc.; and a communication section 1209 including a network interface card such as a local area network card, modem, etc. The communication section 1209 performs communication processing via a network such as the Internet. A drive 1210 is also connected to the input / output interface 1205 as needed. A removable medium 123, such as a disk, optical disk, magneto-optical disk, semiconductor memory, etc., is installed on the drive 1210 as needed so that computer programs read from it can be installed into the storage section 1208 as needed.

[0094] Specifically, according to embodiments of this application, the processes described in the various method flowcharts can be implemented as computer software programs. For example, embodiments of this application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication section 1209, and / or installed from removable medium 123. When the computer program is executed by central processing unit 1201, it performs various functions defined in the system of this application.

[0095] In such an embodiment, the computer program can be downloaded and installed from a network via the communication section 1209, and / or installed from the removable medium 123. When the computer program is executed by the central processing unit 1201, it performs various functions provided in the embodiments of this application.

[0096] According to another aspect of the embodiments of this application, an electronic device for a method of determining the dynamic frequency of a blade is also provided. This embodiment uses this electronic device as an example of a terminal device. Figure 13 As shown, the electronic device includes a memory 1302 and a processor 1304. The memory 1302 stores a computer program, and the processor 1304 is configured to execute the steps of any of the above method embodiments through the computer program.

[0097] Optionally, in this embodiment, the aforementioned electronic device may be located in at least one of a plurality of network devices in a computer network.

[0098] Optionally, in this embodiment, the processor may be configured to execute the methods in the embodiments of this application via a computer program.

[0099] Alternatively, as those skilled in the art will understand, Figure 13 The structure shown is for illustrative purposes only. Figure 13 This does not limit the structure of the aforementioned electronic devices. For example, the electronic device may also include components that are more... Figure 13 The more or fewer components shown (such as network interfaces, etc.), or having the same Figure 13 The different configurations shown.

[0100] The memory 1302 can be used to store software programs and modules, such as the program instructions / modules corresponding to the blade dynamic frequency test determination method and apparatus in this embodiment. The processor 1304 executes various functional applications and data processing by running the software programs and modules stored in the memory 1302, thereby realizing the aforementioned blade dynamic frequency test determination method. The memory 1302 may include high-speed random access memory, and may also include non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some instances, the memory 1302 may further include memory remotely located relative to the processor 1304, and these remote memories can be connected to the terminal via a network. Examples of such networks include, but are not limited to, the Internet, corporate intranets, local area networks, mobile communication networks, and combinations thereof. Specifically, the memory 1302 may be used, but is not limited to, to store collected operational data or cleaned data information. As an example, such as... Figure 13 As shown, the memory 1302 may include, but is not limited to, the acquisition and construction module 901, load calculation module 902, nozzle setting module 903, and test determination module 904 from the blade dynamic frequency test determination device described above. Furthermore, it may include, but is not limited to, other module units from the aforementioned device, which will not be elaborated upon in this example.

[0101] Optionally, the transmission device 1306 described above is used to receive or send data via a network. Specific examples of the network described above may include wired networks and wireless networks. In one example, the transmission device 1306 includes a Network Interface Controller (NIC), which can be connected to other network devices and a router via a network cable to communicate with the Internet or a local area network. In another example, the transmission device 1306 is a Radio Frequency (RF) module, used for wireless communication with the Internet.

[0102] In addition, the aforementioned electronic device also includes: a display 1308 for displaying the aforementioned operating data or cleaning data; and a connection bus 1310 for connecting the various module components in the aforementioned electronic device.

[0103] In other embodiments, the aforementioned terminal device or server can be a node in a distributed system, wherein the distributed system can be a blockchain system, which is a distributed system formed by connecting multiple nodes through network communication. The nodes can form a peer-to-peer network, and any form of computing device, such as a server, terminal, or other electronic device, can become a node in the blockchain system by joining this peer-to-peer network.

[0104] According to one aspect of this application, a computer-readable storage medium is provided, wherein a processor of an electronic device reads computer instructions from the computer-readable storage medium, and executes the computer instructions, causing the electronic device to perform a blade dynamic frequency test determination method provided in one of the various alternative implementations of the blade dynamic frequency test determination aspect described above.

[0105] Optionally, in this embodiment, the computer-readable storage medium described above may be configured to store methods for performing the embodiments of this application.

[0106] Optionally, in this embodiment, those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be implemented by a program instructing the hardware related to the terminal device. The program can be stored in a computer-readable storage medium, which may include: flash drive, read-only memory (ROM), random access memory (RAM), disk or optical disk, etc.

[0107] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0108] If the integrated units in the above embodiments are implemented as software functional units and sold or used as independent products, they can be stored in the aforementioned computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause one or more electronic devices to execute all or part of the steps of the methods described in the various embodiments of this application.

[0109] In the above embodiments of this application, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0110] In the several embodiments provided in this application, it should be understood that the disclosed application can be implemented in other ways. The device embodiments described above are merely illustrative; for example, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the displayed or discussed mutual couplings, direct couplings, or communication connections may be through some interfaces; indirect couplings or communication connections between units or modules may be electrical or other forms.

[0111] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0112] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0113] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0114] In summary, as can be seen from the above description, the embodiments of the present invention achieve the following technical effects: 1. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of blades. By collecting blade data to construct a finite element model and obtain modal data, it provides a precise theoretical basis for the scientific design of the test scheme. Through harmonic response analysis, it obtains unit load frequency response data, enabling a refined analysis of the dynamic response characteristics of the blade under unit load conditions, providing a key basis for subsequent load and nozzle parameter optimization. By accurately calculating the excitation force and nozzle load, and combining the unit load frequency response data with adjustments to the number and distribution angle of nozzles, it achieves systematic optimization of nozzle setting data, ensuring that the nozzle setting method can efficiently and accurately excite the key vibration modes of the blade during the test, significantly improving the accuracy and reliability of the test. Based on rotor speed, nozzle parameters, nozzle load, and unit load frequency response data, it calculates the strain amplitude and confirms the test scheme accordingly, which not only effectively shortens the test cycle and reduces test costs, but also significantly improves the safety and repeatability of the test. This method provides high-precision and high-reliability data support for optimizing the test scheme for obtaining vibration parameters of gas turbine blades, making resonance tests on blades more accurate, effectively reducing the resonance risk of blades in actual operation, and improving the overall operating performance and reliability of gas turbines.

[0115] 2. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of a blade. By setting strain gauges on the finite element model of the blade and performing simulation analysis at different rotor speeds, it is possible to accurately obtain modal data such as the modal order, natural frequency, and strain ratio of the blade. Combined with the dynamic characteristics of the blade at different speeds, it provides a high-precision theoretical basis for the design of the test scheme. Furthermore, by setting load conditions and performing harmonic response analysis, unit load frequency response data is obtained, and load frequency response curves are constructed. This enables a refined analysis of the dynamic response characteristics of the blade under different load conditions, providing a unitized and visualized frequency response data. This process not only improves the accuracy of modal analysis but also provides a key basis for the optimization of nozzle parameters and the scientific design of the test scheme. It allows for the calculation of unit load frequency response data when calculating multiple nozzle cases, ensuring that the key vibration modes of the blade can be excited efficiently and accurately during the test, significantly improving the accuracy and reliability of the test, and providing more accurate data support for blade design optimization.

[0116] 3. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of a blade. By calculating the nozzle load using blade data and nozzle parameters, it can identify load comparison diagrams corresponding to different nozzle setting parameters, i.e., different design schemes. It allows selection of nozzle setting data that can excite the maximum vibration frequency of the blade, and can also formulate multiple nozzle setting data according to test requirements. By accurately calculating the nozzle parameters and the chordal and vertical chordal components of the excitation force, combined with unit load frequency response data, it calculates the total strain and generates strain amplitude data corresponding to different modes. This allows for further screening to determine whether the scheme meets the strain amplitude requirements. This invention can dynamically adjust the nozzle setting data to ensure that the nozzle load amplitude reaches the optimal effect in the frequency region corresponding to different modal orders. It not only optimizes the nozzle parameters but also ensures the scientific validity and effectiveness of the test scheme through strain amplitude data verification, significantly improving the success rate and efficiency of the test, reducing test costs and time, and providing reliable technical support for the development and optimization of gas turbine blades.

[0117] 4. This invention proposes a method, apparatus, electronic equipment, and testing system for determining the dynamic frequency of a blade. The testing system integrates key components such as a rotor, blade, strain gauges, signal transmitting and receiving devices, a signal analysis system, and nozzles to construct an efficient and precise testing platform specifically designed for studying the dynamic characteristics of blades in rotation. The strain gauges can collect the vibration data of the blade in real time, while the signal transmitting and receiving devices ensure that this data can be stably and accurately transmitted to the signal analysis system to obtain the vibration data generated by the blade during the test. Different systems can be connected and transmit signals via wired or wireless means, ensuring the accuracy and stability of the system. This testing system can quickly respond to different testing needs, adapt to various blades and operating conditions, greatly shorten the testing cycle, reduce testing costs, and provide an efficient and reliable testing method for the research and optimization of gas turbine blades.

[0118] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0119] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0120] It should be noted that, in the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

Claims

1. A method for determining the dynamic frequency of a blade through testing, characterized in that, include: Collect blade data to construct a finite element model of the blade, and obtain blade modal data based on the finite element model of the blade. Set a load condition, and perform harmonic response analysis on the finite element model of the blade according to the load condition to obtain unit load frequency response data, which includes real part response data and imaginary part response data; The excitation force is calculated based on the nozzle parameters. The nozzle load is calculated based on the blade data and the nozzle parameters. The nozzle setting data is adjusted by comparing the nozzle load and the unit load frequency response data. The nozzle setting data includes the number of nozzles and the distribution angle. The strain amplitude data is obtained based on the rotor speed, the nozzle load corresponding to the nozzle parameters, and the unit load frequency response data. The test plan is then confirmed based on the strain amplitude data.

2. The method according to claim 1, characterized in that, The blade modal data includes modal order, natural frequency, and strain ratio.

3. The method according to claim 2, characterized in that, Based on the blade finite element model, the blade modal data are obtained, including: Two strain gauges are set on the blade finite element model. The blade finite element model is simulated by simulation analysis software based on different rotor speeds to obtain the modal order of the blade finite element model at different rotor speeds, the natural frequency corresponding to the modal order, and the strain data and principal strain data at the strain gauges.

4. The method according to claim 3, characterized in that, Obtaining blade modal data based on the blade finite element model also includes: The strain ratio is obtained by comparing the strain data at the strain gauge of the model with the main strain data.

5. The method according to claim 1, characterized in that, Set load conditions, including: Set the load amplitude and preset frequency, and calculate the chordal load and vertical chordal load respectively based on the load amplitude and preset frequency.

6. The method according to claim 5, characterized in that, Harmonic response analysis of the blade finite element model based on the load conditions is performed to obtain unit load frequency response data, including: The chordal load and the vertical chordal load are input into simulation analysis software to obtain unit load frequency response data, and load frequency response curves are constructed based on the unit load frequency response data.

7. The method according to claim 1, characterized in that, The nozzle parameters include nozzle mass flow rate, nozzle airflow absolute velocity, and nozzle rotation radius.

8. The method according to claim 7, characterized in that, The excitation force includes a chordal component and a vertical chordal component.

9. The method according to claim 8, characterized in that, The excitation force is calculated based on the nozzle parameters, including: The blade data includes blade length, nozzle airflow angle, and blade mounting angle; Calculate the tangential velocity of the radius blade based on the rotor speed and the nozzle rotation radius; The relative velocity of the airflow is obtained based on the tangential velocity of the radial blade and the absolute velocity of the airflow from the nozzle. The chordal component and the vertical chordal component are calculated based on the nozzle mass flow rate, the relative velocity of the airflow, the tangential velocity of the radial blade, the absolute velocity of the airflow from the nozzle, and the blade installation angle, respectively.

10. The method according to claim 9, characterized in that, Calculating the nozzle load based on the blade data and the nozzle parameters includes: The nozzle amplitude is calculated based on the nozzle mass flow rate and the relative velocity of the airflow. The duration is calculated based on the rotor speed, the nozzle rotation radius, and the blade length; The fundamental frequency of the rotational speed is obtained based on the rotor speed. The nozzle load is calculated based on the nozzle setting data, the nozzle amplitude, the duration, and the rotational speed base frequency.

11. The method according to claim 2, characterized in that, Adjust the nozzle setting data by comparing the nozzle load and the unit load frequency response data, including: Based on different nozzle setting data, a load comparison diagram is constructed for the nozzle load and different modal orders according to frequency. The nozzle setting data is adjusted so that the amplitude of the nozzle load is within the frequency region corresponding to the different modal orders, and the nozzle setting data is saved.

12. The method according to claim 9, characterized in that, Strain amplitude data is obtained based on the rotor speed, the nozzle load corresponding to the nozzle parameters, and the unit load frequency response data, including: The total strain is calculated based on the chordal component, the vertical chordal component, the real response data, and the imaginary response data. The strain amplitude data is generated based on the rotational speed interval set by the rotor speed and the total strain.

13. The method according to claim 12, characterized in that, The total strain is calculated based on the chordal component, the perpendicular chordal component, the real part response data, and the imaginary part response data, as expressed below: ， in The total strain is given. For the chord component, The vertical chord component. The real part response data, The imaginary part response data, Let be the real part of the complex number, and let I be the imaginary part of the complex number. It is the imaginary unit.

14. The method according to claim 13, characterized in that, The expressions for the real and imaginary parts of the resulting complex number are as follows: ， in Let be the real part of the complex number, and let I be the imaginary part of the complex number. The mass flow rate of the nozzle. The relative velocity of the airflow, This is the impact load spectrum vector constructed based on the unit load frequency response data. The blade installation angle, The relative velocity angle, The data refers to the chord component in the real response data. The data refers to the vertical chord component in the real response data. The data refers to the chord component in the imaginary response data. The data refers to the vertical chord component in the imaginary response data.

15. The method according to claim 14, characterized in that, The expression for the impact load spectrum vector is as follows: ， in Let be the frequency spectrum vector of the impact load. The data refers to the frequencies that correspond sequentially in the unit load frequency response data, where n is the index.

16. The method according to claim 2, characterized in that, The test plan was confirmed based on the strain amplitude data, including: Determine whether the strain amplitude data corresponding to different frequencies and modal orders is greater than the preset strain data. If it is greater than the strain data, then the corresponding nozzle setting data is used as the test scheme. If it is less than the strain data, then adjust the nozzle setting data and iterate until the obtained strain amplitude data is greater than the preset strain data.

17. A device for determining the dynamic frequency of a blade, characterized in that, include: The acquisition and construction module is used to acquire blade data, construct a blade finite element model, and obtain blade modal data based on the blade finite element model. The load calculation module is used to set the load conditions and perform harmonic response analysis on the finite element model of the blade according to the load conditions to obtain unit load frequency response data, which includes real part response data and imaginary part response data. The nozzle setting module is used to calculate the excitation force based on the nozzle parameters, calculate the nozzle load based on the blade data and the nozzle parameters, and adjust the nozzle setting data by comparing the nozzle load and the unit load frequency response data. The nozzle setting data includes the number of nozzles and the distribution angle. The test determination module is used to obtain strain amplitude data based on the rotor speed, the nozzle load corresponding to the nozzle parameters, and the unit load frequency response data, and to confirm the test plan based on the strain amplitude data.

18. A computer-readable storage medium, characterized in that, The computer-readable storage medium includes a stored computer program, wherein the computer program can be executed by an electronic device to perform the method described in any one of claims 1 to 16.

19. A computer program product, comprising a computer program, characterized in that, When executed by a processor, the computer program performs the steps of the method described in any one of claims 1 to 16.

20. An electronic device comprising a memory and a processor, characterized in that, The memory stores a computer program, and the processor is configured to execute the method described in any one of claims 1 to 16 through the computer program.

21. A blade dynamic frequency testing system, characterized in that, The system includes a rotor (1), a wheel (2), blades (3), strain gauges (4), a signal transmitting device (5), a signal receiving device (6), a signal analysis system (7), and nozzles (9). The blades (3) are arranged radially along the rotor (1), the strain gauges (4) are disposed on the blades (3), the signal transmitting device (5) is disposed at one end of the rotor (1), the signal transmitting device (5) is connected to the strain gauges (4) by wired or wireless means, the signal receiving device (6) is connected to the signal analysis system (7) by wired or wireless means, the signal analysis system (7) is used to obtain the vibration data collected by the strain gauges (4), and the nozzles (9) are evenly arranged along the circumference of the rotor (1) for spraying gas or hydraulic oil onto the blades (3).

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