A method for simulating and measuring order excitation of a rotating blade disc structure engine

Abstract

The application discloses a rotating blade disc structure engine order excitation simulation implementation and measurement method based on a magnetic excitation device. A series of special magnetic excitation units are uniformly distributed along the circumferential direction and fixed on an upstream support device of the rotating blade disc. Non-contact exciting forces are applied to the rotating blades to simulate the generation of engine order excitation. The method has the advantages of simple equipment, convenient implementation, cleanness, no pollution and low cost. On the basis of the technical scheme, the measurement and analysis method for simulating engine order excitation is provided. The non-contact exciting forces applied to all the rotating blades are measured by force sensors additionally installed on the magnetic excitation units. In combination with the test data of a rotating speed sensor, the measured engine order excitation frequency, amplitude and phase information of all the rotating blades at an arbitrary rotating speed can be obtained, so that the method has outstanding advantages in rotating blade disc structure vibration test and prediction analysis.

Description

TECHNICAL FIELD

[0001] The application relates to a rotating bladed disc structure engine order excitation simulation implementation and measurement method based on a magnetic excitation device, and belongs to the field of structural vibration testing and analysis. BACKGROUND

[0002] A rotating bladed disc structure is a core component for realizing power-energy conversion in an aero-engine and a gas turbine. With the continuous increase of the working load of high-performance fan / compressor and turbine components, a low structural damping level and inevitable random mistuning of blades (random slight differences in geometric / physical properties between blade individuals) cause the rotating bladed disc structure to easily generate high-cycle fatigue failure faults caused by high-level vibration of the blades under air flow excitation, seriously restrict the structural integrity and reliability of the rotating bladed disc structure, and affect the operation safety and life cycle maintenance cost of the aero-engine and the gas turbine. For a long time, the problems of anti-high-cycle fatigue design and structural integrity evaluation of the rotating bladed disc structure have faced important scientific and technical challenges in the related vibration test and analysis evaluation of the rotating bladed disc structure.

[0003] The forms of excitation forces borne by the rotating bladed disc structure in the aero-engine and the gas turbine are various, which can be generally divided into three categories, namely, periodically changing excitation force, non-periodically changing excitation force and random excitation force. For the rotating blades, the periodically changing excitation force caused by the upstream stator blade wake loss, flow instability / random turbulence (for example, blade rotating stall, etc.) and other factors is collectively referred to as "engine order excitation", which is the main reason for causing forced vibration of the rotating blades. The following takes the blade excitation force formed by the upstream stator blade wake loss as an example to briefly introduce the formation mechanism of the engine order excitation borne by the rotating blades.

[0004] Under ideal conditions without interference, the flow field pressure of the incoming flow in front of the engine is shown in FIG. 1. which has the characteristics of stability and uniform distribution along the circumference, as shown in FIG. 2. Figure 1 After the incoming flow passes through the stator blade or the strut, etc., a flow field wake pressure loss will be generated behind the stator blade or the strut, which is a periodically (non-uniformly) distributed flow field , the circumferential spatial fundamental harmonic component of which can be simply denoted as , wherein EO represents the excitation order, which can be regarded as the number of the upstream stator or strut structure of the rotating bladed disc; and represents the circumferential position of the upstream stator or strut structure.

[0005] The non-uniform flow field behind the rotating bladed disc structure rotates at a rotating speed of Ω, the rotating blades are equivalent to being subjected to a periodically changing excitation force , i.e. the so-called engine order excitation. The Fourier series expansion of

[0006] In summary, the engine order excitation of a rotating bladed disk structure composed of N sectors has the following basic characteristics: (1) The fundamental harmonic frequency of the gas excitation force on the rotating blades is related to the excitation order (EO) and the rotational speed Ω, i.e.

[0007]

[0008]

[0009] (2) The engine order excitation is distributed harmonically in space (circumferentially) and time, and there is a phase difference (φ) between the gas excitation forces on the rotating blades of adjacent sectors, where α = 2π / N s is the sector angle.

[0010] In numerical simulation of forced vibration of rotating bladed disk structures, the engine order excitation with a single excitation order component (EO) is usually applied to the same position on each blade in the form of a traveling wave excitation. The expression of the engine order excitation acting on the jth sector is as follows:

[0011] The above formula shows that the excitation force on each blade of the rotating bladed disk structure has a consistent amplitude

[0012] , and the phase difference between the excitation forces on the blades of adjacent sectors is (φ).

[0013] Forced vibration test evaluation of rotating bladed disk structures can be divided into whole machine bench tests and component level tests. Whole machine bench tests can fully reproduce the working environment and load characteristics of rotating bladed disk structures in service state, but the test cost and time cost are high. Component level tests are usually carried out in laboratory environment using engine order excitation simulation devices, which can greatly reduce the test cost, and the test process is more flexible and controllable.

[0014] ​​​​​​​​​Early domestic and foreign component level bladed disk structure forced vibration test mostly uses ground traveling wave excitation device to apply simulated engine order excitation to the static state bladed disk structure, thereby providing convenience for measuring and studying the vibration response distribution of all blades of the bladed disk structure. Different forms of ground traveling wave excitation devices all include two main working units: a vibration excitation force generation unit and an excitation phase control unit. The vibration excitation force generation unit can use electromagnet equipment, piezoelectric actuators or acoustic excitation equipment to apply a simple harmonic vibration excitation force to the blades. The excitation phase control unit controls the phase difference of the simple harmonic vibration excitation force acting on different blades according to the test requirements to obtain the simulated engine order excitation with a specified excitation order.

[0015] At present, there are still certain technical difficulties and challenges in the component level forced vibration test of the bladed disk structure in the rotating state. At present, the aviation engine industry generally uses the method of spraying oil to the surface of the rotating blade to induce the forced vibration response of the bladed disk structure. This vibration excitation technology has the following disadvantages:

[0016] (1) A special oil supply and return system needs to be designed, and the oil tightness of the rotating bladed disk vibration test device is required, which increases the construction cost of the test facility;

[0017] (2) The oil is used as a medium to apply the excitation force to the rotating blade, which may form an attached oil film and dirt on the surface of the blade, affecting the application of advanced non-contact blade vibration measurement technology (such as blade tip timing technology) using optical sensors;

[0018] (3) The excitation force generated by spraying oil to the surface of the rotating blade is difficult to measure, and thus the real engine order excitation information cannot be obtained.

[0019] In summary, the simulated generation device of the engine order excitation is one of the key technologies for carrying out the component level forced vibration test of the rotating bladed disk structure. How to simulate and test the engine order excitation information, and then serve the forced vibration response prediction of the rotating bladed disk structure and effectively carry out the correlation analysis of the measured blade vibration response results, is a long-standing problem that has plagued the academic and industrial circles. SUMMARY

[0020] The application provides a rotating bladed disk structure engine order excitation simulation implementation and measurement method based on a magnetic excitation device to solve the implementation problem of the engine order excitation required by the rotating bladed disk structure forced vibration test.

[0021] The application solves the above technical problems by using the following technical solutions:

[0022] A rotating bladed disk structure engine order excitation simulation implementation method, the specific steps are as follows:

[0023] Step 1, supporting devices are arranged on the upstream of the blade disc structure, and N m magnetic excitation units are evenly distributed and fixed in the circumferential direction to form an engine order excitation simulation system; wherein each magnetic excitation unit contains one same cylindrical permanent magnet, and N m is a positive integer;

[0024] Step 2, during the rotation of the blade disc structure, each blade is subjected to N m excitation forces generated by the magnetic excitation units in one rotation, i.e. forming engine order excitation for the rotating blade disc structure to realize engine order excitation simulation.

[0025] Preferably, in the simulation implementation method, the amplitude level of the non-contact excitation force generated by each magnetic excitation unit on the rotating blade passing below is adjusted by changing the distance between the permanent magnet in each magnetic excitation unit and the blade below.

[0026] Preferably, each permanent magnet is fixed on the supporting device by a tool clamp.

[0027] The application also adopts a measurement method for simulating engine order excitation, and the specific steps are as follows:

[0028] Step 1, using the simulation implementation method as described above, forming engine order excitation for the rotating blade disc structure to realize engine order excitation simulation;

[0029] Step 2, during the rotation of the blade disc structure, measuring the excitation force applied on all rotating blades, obtaining the original time domain measurement data of the excitation force, and synchronously collecting the rotation speed pulse signal of the blade disc structure shaft;

[0030] Step 3, taking the rotation speed pulse signal as a reference, synchronously processing the original time domain measurement data of the excitation force;

[0031] Step 4, processing the rotation speed pulse signal to calculate and obtain the rotation speed between specified adjacent pulse signals;

[0032] Step 5, reconstructing the time domain signal of the non-contact excitation force suffered by the single blade in the process of rotating one circle at the specified rotation speed through the N m magnetic excitation units from the synchronously processed original time domain measurement data of the excitation force;

[0033] Step 6, performing short-time Fourier analysis on the reconstructed time domain signal of the non-contact excitation force suffered by the single blade to obtain the frequency spectrum component of the non-contact excitation force suffered by the single blade at the specified rotation speed;

[0034] Step 7, repeating steps 4 to 6 to obtain the frequency spectrum component of the non-contact excitation force suffered by all single blades at any rotation speed, and further obtaining the engine order excitation frequency, amplitude and phase information.

[0035] Preferably, in step two, the exciting force applied to each blade is measured by installing a force sensor above the permanent magnet of any magnetic excitation unit in the engine order excitation simulation system.

[0036] Preferably, in step two, the rotating speed pulse signal of the rotating disk structure rotating shaft is collected by installing a rotating speed sensor on the rotating disk structure rotating shaft.

[0037] The application also adopts a measurement system simulating engine order excitation, comprising:

[0038] N m magnetic excitation units evenly distributed circumferentially and fixed on the upstream support device of the rotating disk structure form an engine order excitation simulation system for forming engine order excitation for the rotating disk structure; wherein each magnetic excitation unit contains an identical cylindrical permanent magnet, and each permanent magnet is fixed on the support device by a tool clamp;

[0039] A rotating speed sensor installed on the rotating disk structure rotating shaft is used to collect the rotating speed pulse signal of the disk structure rotating shaft.

[0040] A force sensor installed below the permanent magnet of any magnetic excitation unit in the engine order excitation simulation system is used to measure the exciting force applied to each blade during the rotation of the rotating disk structure, and obtain the original time domain measurement data of the exciting force.

[0041] A synchronization module is used to synchronize the original time domain measurement data of the exciting force with the rotating speed pulse signal as a reference.

[0042] A rotating speed processing module is used to process the rotating speed pulse signal and calculate the rotating speed between specified adjacent pulse signals.

[0043] A reconstruction module is used to reconstruct the time domain signal of the non-contact exciting force suffered by a single blade during one rotation at a specified rotating speed from the N m magnetic excitation units.

[0044] A Fourier analysis module is used to perform short-time Fourier analysis on the reconstructed time domain signal of the non-contact exciting force suffered by a single blade at a specified rotating speed, and obtain the frequency spectrum component of the non-contact exciting force suffered by a single blade at a specified rotating speed.

[0045] The application also adopts a computer readable storage medium, characterized in that the computer readable storage medium stores a computer program, and the computer program is executed by a processor to realize the steps of the above measurement method.

[0046] The application also adopts an electronic device, characterized in that comprising:

[0047] A memory for storing a computer program;

[0048] A processor for implementing the steps of the measurement method as described above when executing the computer program.

[0049] The application adopts the above technical solution compared with the prior art, and has the following technical effects:

[0050] 1. The application proposes a rotating blade structure engine order excitation simulation implementation method based on a magnetic excitation device, adopts a permanent magnet to apply a non-contact exciting force to the rotating blade to further simulate the generation of engine order excitation, and has the advantages of simple equipment, convenient implementation, clean and pollution-free, and low cost.

[0051] 2. The application proposes a measurement and analysis method for simulating engine order excitation on the basis of the above technical solution, which can obtain the measured engine order excitation frequency, amplitude and phase information of all rotating blades at any rotating speed, and has outstanding advantages in rotating blade structure vibration test and prediction analysis. BRIEF DESCRIPTION OF DRAWINGS

[0052] Figure 1 It is a schematic diagram of the formation mechanism of engine order excitation.

[0053] Figure 2 It is a magnetic excitation unit.

[0054] Among them, 1 is a supporting device, 2 is a tool clamp, 3 is a force sensor, 4 is a permanent magnet, and 5 is a rotating blade.

[0055] Figure 3 It is a flow chart of the measurement method for simulating engine order excitation.

[0056] Figure 4 It is the original time domain signal obtained by the rotating speed sensor and the force sensor.

[0057] Figure 5 It is the time domain signal of the exciting force suffered by the No. 1 blade at a rotating speed of 2050 r / min.

[0058] Figure 6 It is the frequency spectrum component of the exciting force suffered by the No. 1 blade at a rotating speed of 2050 r / min. DETAILED DESCRIPTION

[0059] The application adopts a magnetic excitation system to simulate the engine order excitation simulation required for rotating blade structure forced vibration test, and further realizes the measurement and analysis of the exciting force suffered by each rotating blade, and extracts the measured information of engine order excitation.

[0060] The following describes the simulation and measurement method for engine order excitation proposed in this invention. Specific steps are as follows: Figure 3 As shown.

[0061] The excitation simulation system consists of a support ring (i.e., a support device) uniformly distributed and fixed above the rotating integral bladed disk along the circumference, and N magnetic excitation units. m It consists of four specially designed magnetic excitation units, which can simulate the engine order excitation experienced by the rotating bladed disk structure inside a real aircraft engine.

[0062] A steel bladed disk simulation test piece is mounted on a vertically driven shaft. During the test, it traverses a specified speed range at a controlled acceleration / deceleration rate, potentially crossing multiple blade resonance zones. This rotating test setup employs a non-invasive tip-timed vibration measurement technique to simultaneously measure the vibration response of all rotating blades. Furthermore, the setup uses an OPR laser speed sensor (Once-Per-Revolution, OPR) to provide the time reference required for the tip-timed technique and can further provide real-time speed information.

[0063] I. Simulation Implementation Method of Engine Order Excitation Based on Magnetic Excitation Device

[0064] (1) Design and construct a specially designed magnetic excitation unit. For example... Figure 2 As shown, each magnetic excitation unit contains an identical cylindrical permanent magnet, which is fixed on a special tooling fixture.

[0065] (2) N m A magnetic excitation unit is evenly distributed circumferentially and fixed on a support ring above the rotating bladed disk to form an engine order excitation simulation system.

[0066] (3) Each magnetic excitation unit generates a non-contact excitation force on the blades that rotate below. The distance between the magnets in each magnetic excitation unit and the blades below can be adjusted to be consistent using the special tooling fixture in (1). If necessary, the distance can also be changed to adjust the magnitude of the excitation force.

[0067] (4) During the rotation of the bladed disk structure, each blade is subjected to N during one rotation. m The non-contact excitation force is generated by the magnetic excitation unit. According to Figure 1 The diagram illustrates the formation mechanism of engine order excitation, a system that can simulate the engine order excitation experienced by the rotating bladed disk structure within a real aero-engine. Theoretically, N... m The excitation order components generated by the uniformly arranged circumferential magnetic excitation units on the rotating bladed disk structure are as follows:

[0068] .

[0069] II. Measurement Methods for Simulated Engine Order Excitation

[0070] (1) A unidirectional force sensor is installed above the permanent magnet of a magnetic excitation unit in the above-mentioned engine order excitation simulation system.

[0071] (2) Install an OPR laser speed sensor on the impeller structure shaft.

[0072] (3) In the rotational vibration test of the bladed disk structure, the force sensor installed in the magnetic excitation unit in (1) can be used to measure the component of the excitation force applied to the rotating blade in the rotational axis, and the speed sensor installed in (2) can be used simultaneously for data acquisition.

[0073] (4) For the original time-domain test data of the excitation force collected by the force sensor in (3), the pulse signal of the speed sensor is used as a reference for synchronous processing.

[0074] Figure 4 The results are presented after synchronous processing of the original time-domain test data of the excitation force collected by the force sensor (right Y-axis signal) and the pulse signal of the OPR laser speed sensor (left Y-axis signal) as the reference.

[0075] (5) Process the speed sensor pulse signal obtained in (4) and calculate the speed between specified adjacent pulse signals.

[0076] (6) Reconstruct the time-domain signal of the non-contact excitation force experienced by a single blade during one revolution at a specified speed.

[0077] Based on the relative positions of the markers (reflective paper) on the rotating shaft and each blade of the OPR laser speed sensor, and using the time-domain signal of the excitation force collected by the force sensor, the process of a single blade rotating one revolution at a specified speed can be reconstructed. The time-domain signal of the excitation force experienced by each magnetic excitation unit.

[0078] In one embodiment, N are uniformly arranged along the circumference of the impeller disk. m =4 magnetic excitation units. Observation Figure 5 It can be seen that at 2050 r / min, blade No. 1 is subjected to N during one rotation. m =4 pulse excitation forces generated by the magnetic excitation unit.

[0079] (7) Obtain the spectral components of the non-contact excitation force on a single rotating blade at a specified rotational speed.

[0080] right Figure 5 By performing short-time Fourier analysis on the time-domain signal of the excitation force acting on blade No. 1, the spectral components of the excitation force at a specified rotational speed can be further obtained, such as...Figure 6 The excitation force acting on a single rotating blade is composed of different engine order (EO) components with different excitation force amplitudes. Figure 6 As shown in the figure, the excitation force acting on a single rotating blade is composed of different engine order (EO) components with different excitation force amplitudes. Figure 6 The single blade excitation order component shown is consistent with the theoretical analysis result.

[0081] (8) Repeat steps (5)-(7) above to obtain the engine order excitation frequency, amplitude and phase information of all single rotating blades at any speed.

[0082] The application also provides a measurement system for simulating engine order excitation, comprising:

[0083] N m magnetic excitation units evenly distributed circumferentially and fixed on the upstream support device of the rotating blade disc structure form an engine order excitation simulation system for forming engine order excitation for the rotating blade disc structure; each magnetic excitation unit comprises a same cylindrical permanent magnet, and each permanent magnet is fixed on the support device by a tool clamp;

[0084] A rotation speed sensor is installed on the rotation shaft of the rotating blade disc structure to collect the rotation speed pulse signal of the blade disc structure rotation shaft;

[0085] A force sensor is installed below the permanent magnet of any magnetic excitation unit in the engine order excitation simulation system to measure the excitation force acting on each blade during rotation of the rotating blade disc structure and obtain original time domain measurement data of the excitation force;

[0086] A synchronization module is used to synchronize the original time domain measurement data of the excitation force based on the rotation speed pulse signal;

[0087] A rotation speed processing module is used to process the rotation speed pulse signal to calculate the rotation speed between specified adjacent pulse signals;

[0088] A reconstruction module is used to reconstruct the time domain signal of the non-contact excitation force acting on a single blade during one rotation at a specified rotation speed by the N m magnetic excitation units;

[0089] A Fourier analysis module is used to perform short-time Fourier analysis on the reconstructed time domain signal of the non-contact excitation force acting on a single blade to obtain the frequency spectrum component of the non-contact excitation force acting on a single blade at a specified rotation speed.

[0090] The technical solution of the measurement system is the same as the measurement method described above, and will not be repeated here.

[0091] Based on the same technical solution, the application further provides an electronic device, comprising:

[0092] a memory for storing a computer program;

[0093] a processor for implementing the steps of the above measurement method when executing the computer program.

[0094] Based on the same technical solution, the application further provides a computer readable storage medium, the computer readable storage medium has a computer program stored thereon, the computer program is executed by a processor to implement the steps of the above measurement method. The computer readable storage medium can include a U disk, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, and various storage program codes.

[0095] A person of ordinary skill in the art can understand that all or part of the above-mentioned embodiment methods can be completed by a computer program instructing related hardware, and the computer program can be stored in a non-volatile computer readable storage medium. When the computer program is executed, it can include the processes of the above-mentioned embodiments of each method. Any reference to memory, storage, database or other medium used in each embodiment provided by the present application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration but not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0096] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the present application and not to limit them, although the present application has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present application can still be modified or replaced by equivalents, and these modifications or equivalent replacements cannot make the modified technical solutions deviate from the spirit and scope of the technical solutions of the present application.

[0097] It should be noted that the above description of the embodiments is only used to help understand the method of the present application and its core idea. Those skilled in the art can make several improvements and modifications to the present application without departing from the principles of the present application, and these improvements and modifications are also within the protection scope of the claims of the present application.

Claims

1. A method of measuring simulated engine order excitation, characterised by, The specific steps are as follows: Step one, the engine order excitation simulation method of the rotating blade disc structure engine is used to form the engine order excitation of the rotating blade disc structure, and the engine order excitation simulation is realized; the specific steps of the simulation method are as follows: Step 1, supporting N m magnetic excitation units on the upstream support device of the blade disc structure, evenly distributed and fixed in the circumferential direction, forming an engine order excitation simulation system; wherein each magnetic excitation unit contains one same cylindrical permanent magnet, N m is a positive integer; Step 2, during the rotation of the blade disc structure, each blade is subjected to N m times of exciting forces generated by the magnetic excitation unit, i.e. engine order excitation for the rotating blade disc structure is formed, to realize engine order excitation simulation; Step two, a force sensor is installed above the permanent magnet of any magnetic excitation unit in the engine order excitation simulation system, and the exciting force applied to each blade is measured during the rotation of the blade disc structure to obtain the original time domain measurement data of the exciting force and synchronously collect the rotating speed pulse signal of the rotating shaft of the blade disc structure; Step three, the rotating speed pulse signal is taken as a reference to synchronously process the original time domain measurement data of the exciting force; Step four, the rotating speed pulse signal is processed to calculate the rotating speed between the specified adjacent pulse signals; Step five, reconstruct the time domain signal of the non-contact exciting force suffered by the single blade during a rotation of one revolution at the specified rotating speed from the synchronized processed exciting force raw time domain measurement data of N m magnetic exciting units. Step six, short-time Fourier analysis is performed on the time domain signal of the reconstructed non-contact exciting force of the single blade to obtain the non-contact exciting force spectrum component of the single blade at the specified rotating speed; Step seven, steps four to six are repeated to obtain the non-contact exciting force spectrum component of all single blades at any rotating speed, and then the different order components, frequency, amplitude and phase information of the engine order excitation are obtained.

2. The measurement method of claim 1, wherein, In step two, the rotating speed sensor installed on the rotating shaft of the rotating blade disc structure is used to collect the rotating speed pulse signal of the rotating shaft of the rotating blade disc structure.

3. The measurement method of claim 1, wherein, In the simulation method, the amplitude level of the non-contact exciting force generated by each magnetic excitation unit on the rotating blade below is adjusted by changing the distance between the permanent magnet in each magnetic excitation unit and the blade below.

4. The measurement method of claim 1, wherein, Each permanent magnet is fixed on the supporting device by a tool clamp.

5. A measurement system for simulating engine order excitation, characterised in that, It comprises: N is evenly distributed circumferentially and fixed on the upstream support device of the rotating bladed disk structure. m An engine order excitation simulation system formed by several magnetic excitation units is used to generate engine order excitation for a rotating bladed disk structure; each magnetic excitation unit contains an identical cylindrical permanent magnet, and each permanent magnet is fixed to a support device by a tooling fixture. A rotating speed sensor installed on the rotating shaft of the rotating blade disc structure is used to collect the rotating speed pulse signal of the rotating shaft of the blade disc structure; A force sensor installed above the permanent magnet of any magnetic excitation unit in the engine order excitation simulation system is used to measure the exciting force applied to each blade during the rotation of the rotating blade disc structure to obtain the original time domain measurement data of the exciting force; A synchronous module is used to take the rotating speed pulse signal as a reference to synchronously process the original time domain measurement data of the exciting force; A rotating speed processing module is used to process the rotating speed pulse signal to calculate the rotating speed between the specified adjacent pulse signals; The reconstruction module is configured to reconstruct, from the synchronized raw time-domain measurement data of the exciting force, a time-domain signal of the non-contact exciting force suffered by the single blade during one revolution at the specified rotating speed and by N m magnetic excitation units. A Fourier analysis module is used to perform short-time Fourier analysis on the time domain signal of the reconstructed non-contact exciting force of the single blade to obtain the non-contact exciting force spectrum component of the single blade at the specified rotating speed.

6. A computer-readable storage medium, characterized in that: The computer readable storage medium stores a computer program, and the computer program is executed by the processor to realize the steps of the measurement method according to any one of claims 1 to 4.

7. An electronic device, comprising: It comprises: A memory is used to store a computer program; A processor is used to execute the computer program to realize the steps of the measurement method according to any one of claims 1 to 4.

Images