A method for measuring and analyzing signals of torsional and axial vibrations of an aero-engine

Abstract

The application relates to the technical field of aero-engines, in particular to a method for measuring and analyzing torsional vibration and axial vibration of an aero-engine, which comprises the following steps: collecting original time-domain signals by an eddy current displacement sensor under the condition that the aero-engine is started; wherein the original time-domain signals contain coupling information of torsional vibration and axial vibration; demodulating the original time-domain signals to obtain independent axial vibration components and torsional vibration components from the original time-domain signals; and performing spectrum analysis on the independent axial vibration components and torsional vibration components respectively to obtain vibration frequency domains and amplitudes of the axial vibration components and the torsional vibration components respectively. The method can decouple and analyze the axial vibration and the torsional vibration synchronously and with high precision by using only a single eddy current displacement sensor and a speed measuring sound wheel of the engine, so that the system is simplified, the cost is reduced, and the engineering applicability and the measurement reliability are improved.

Description

Technical Field

[0001] The embodiments of this application relate to the field of aero-engine technology, and in particular to a method for measuring and analyzing the torsional and axial vibrations of aero-engines. Background Technology

[0002] Vibration in aero-engine rotor systems is an unavoidable dynamic phenomenon. Torsional vibration is a constant companion during engine operation, and shaft fatigue and even shaft breakage accidents caused by severe torsional vibration occur frequently. However, monitoring of torsional vibration in aero-engine rotors is not yet widespread, and comprehensive real-time assessment standards are lacking.

[0003] Currently, non-contact measurement is commonly used for rotating machinery such as aero engines, but existing monitoring systems focus on monitoring the lateral bending vibration and axial movement of the rotor. To simultaneously monitor torsional vibration, traditional solutions require additional dedicated sensors within the limited installation space inside the engine. This not only increases system complexity, weight, and cost but also makes it difficult to adapt to the harsh environment of high temperatures and oil contamination inside the engine. For example, patent document CN115876450A discloses a rotating machinery torsional vibration testing system that relies on photoelectric sensors and specific excitation devices, primarily for laboratory bench testing and difficult to apply to real aero engine environments. Patent document CN113029322B proposes a method using an eddy current sensor in conjunction with a gear disk to simultaneously extract bending and torsional vibration signals, but this method is only applicable to lateral bending vibration, and the signal processing algorithm used has limited accuracy when processing high-frequency complex signals.

[0004] Therefore, how to effectively acquire and accurately decouple the coupled signals of axial vibration and torsional vibration of aero-engine rotors is a technical problem that urgently needs to be solved. Summary of the Invention

[0005] In view of this, embodiments of this application propose a method for measuring and analyzing torsional and axial vibrations of an aero-engine. This method utilizes only a single eddy current displacement sensor in conjunction with the engine's existing velocimetry wheel to simultaneously and accurately decouple and analyze axial and torsional vibrations, thereby simplifying the system, reducing costs, and improving engineering applicability and measurement reliability.

[0006] To achieve the above objectives, embodiments of this application propose a method for measuring and analyzing the torsional and axial vibrations of an aero-engine. A single eddy current displacement sensor is mounted on the aero-engine casing, and the probe of the eddy current displacement sensor is positioned directly opposite the aero-engine's inherent velocimeter wheel. The method includes: When the aircraft engine is running, the raw time-domain signal is acquired by an eddy current displacement sensor; the raw time-domain signal contains the coupling information of torsional vibration and axial vibration. The original time-domain signal is demodulated to obtain independent axial vibration and torsional vibration components from the original time-domain signal; Spectral analysis was performed on the independent axial vibration component and torsional vibration component to obtain their respective vibration frequency domain and amplitude.

[0007] To achieve the above objectives, embodiments of this application also propose a system for measuring and analyzing torsional and axial vibrations of an aero-engine. A single eddy current displacement sensor is mounted on the aero-engine casing, and the probe of the eddy current displacement sensor is positioned directly opposite the aero-engine's inherent velocimeter wheel. The system includes: The signal acquisition module is used to acquire raw time-domain signals via an eddy current displacement sensor when the aero-engine is started; the raw time-domain signals contain coupled information of torsional vibration and axial vibration. The demodulation processing module is used to demodulate the original time-domain signal to obtain independent axial vibration components and torsional vibration components from the original time-domain signal. The spectrum analysis module is used to perform spectrum analysis on the independent axial vibration components and torsional vibration components to obtain their respective vibration frequency domain and amplitude.

[0008] To achieve the above objectives, embodiments of this application also propose an electronic device, including a processor and a memory, wherein the memory stores instructions executable by the processor, and the processor is configured to execute the instructions such that the electronic device can implement the above-described method for measuring and analyzing torsional and axial vibrations of an aero-engine.

[0009] To achieve the above objectives, embodiments of this application also propose a computer-readable storage medium storing a computer program that, when executed by a processor, enables the implementation of the above-described method for measuring and analyzing torsional and axial vibrations of an aero-engine.

[0010] This application proposes a method for measuring and analyzing torsional and axial vibrations of an aero-engine. First, with the aero-engine running, an eddy current displacement sensor acquires raw time-domain signals, which contain coupled information of torsional and axial vibrations. Then, the raw time-domain signals are demodulated to obtain independent axial and torsional vibration components. Finally, spectral analysis is performed on the independent axial and torsional vibration components to obtain their respective vibration frequency domains and amplitudes. Since a single eddy current displacement sensor is installed on the aero-engine casing, and the sensor's probe is directly facing the aero-engine's inherent velocimetry sound wheel, effective acquisition and high-precision decoupling analysis of the coupled signals of the aero-engine rotor's axial and torsional vibrations are achieved. Based on this, this solution utilizes only a single eddy current displacement sensor in conjunction with the engine's existing velocimetry sound wheel to synchronously and accurately decouple and analyze axial and torsional vibrations, thereby simplifying the system, reducing costs, and improving engineering applicability and measurement reliability.

[0011] Optionally, the eddy current displacement sensor is mounted on the inner wall of the aero-engine casing via a sensor bracket. The velocimeter wheel is perpendicular to the eddy current displacement sensor, so that the output signal of the eddy current displacement sensor can be stabilized within a preset range by adjusting the gap between its probe and the tooth edge of the velocimeter wheel; the preset range is greater than or equal to 500 micrometers; the acquisition of the original time-domain signal by the eddy current displacement sensor when the aero-engine is started includes: when the aero-engine is started, the velocimeter wheel is driven to rotate by the rotation of the aero-engine; when the velocimeter wheel vibrates axially, the voltage signal induced by the rotation of the velocimeter wheel is acquired in real time by the eddy current displacement sensor and the data acquisition system connected to it, and used as the original time-domain signal.

[0012] Optionally, the original time-domain signal is demodulated to obtain independent axial vibration components and torsional vibration components from the original time-domain signal, including: performing a Hilbert transform on the original time-domain signal to extract the axial vibration component from the original time-domain signal through the constructed complex analytic signal; and extracting the torsional vibration component from the original time-domain signal based on the axial vibration component and the original time-domain signal.

[0013] Optionally, a Hilbert transform is performed on the original time-domain signal to extract the axial vibration component from the original time-domain signal using the constructed complex analytic signal. This includes: performing a Hilbert transform on the original time-domain signal to obtain a first signal; constructing a complex analytic signal by using the original time-domain signal as the real part and the first signal as the imaginary part; calculating the envelope signal of the complex analytic signal, and performing amplitude correction and DC removal processing on the envelope signal to obtain the separated axial vibration signal.

[0014] Optionally, based on the axial vibration component and the original time-domain signal, the torsional vibration component is extracted from the original time-domain signal, including: subtracting the axial vibration component from the original time-domain signal to eliminate the interference of the axial vibration component and obtain the torsional vibration correlation signal; based on the torsional vibration correlation signal, calculating the rotor transient angular velocity sequence by detecting the zero-crossing point or extreme point of the signal, and using the transient angular velocity sequence as the separated torsional vibration component.

[0015] Optionally, based on the torsional vibration correlation signal, the transient angular velocity sequence of the rotor is calculated by detecting the zero-crossing point or extreme point of the signal, and the transient angular velocity sequence is used as the separated torsional vibration component, including: identifying the continuous components in the net torsional vibration correlation signal. The target points within each cycle; among them. The target point is either a zero-crossing point or a specific extreme point; the time interval between adjacent target points is calculated, and the transient angular velocity is calculated based on the time interval and the angle corresponding to a single tooth of the velocimetric wheel. The continuously calculated transient angular velocity sequence is then used as the separated torsional vibration component.

[0016] Optionally, spectral analysis is performed on the independent axial vibration component and torsional vibration component separately to obtain their respective vibration frequency domain and amplitude. This includes: using Fast Fourier Transform to perform spectral analysis on the axial vibration component to expand the axial vibration component into a series, and then converting the axial vibration component from the time domain to the frequency domain to obtain the vibration frequency domain and amplitude of the axial vibration component; using Fast Fourier Transform to perform spectral analysis on the torsional vibration component to expand the torsional vibration component into a series, and then converting the torsional vibration component from the time domain to the frequency domain to obtain the vibration frequency domain and amplitude of the torsional vibration component. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments or related technologies of this application, the accompanying drawings used in the description of the embodiments or related technologies of this application will be briefly introduced below. Obviously, the following drawings are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. The drawings described herein are only used to explain this application and are not intended to limit this application.

[0018] Figure 1 This is a flowchart of a method for measuring and analyzing torsional and axial vibrations of an aero-engine, provided in one embodiment of this application. Figure 2 This is a schematic diagram of the arrangement of an eddy current displacement sensor provided in one embodiment of this application; Figure 3 This is a schematic diagram of signal transmission provided in one embodiment of this application; Figure 4 This is a schematic diagram of the original time-domain signal including torsional vibration signal and axial vibration signal provided in one embodiment of this application; Figure 5 This is a schematic diagram of measured engine test signals provided in one embodiment of this application; Figure 6 This is a schematic diagram of the decoupled axial vibration signal provided in one embodiment of this application; Figure 7 This is a schematic diagram of the decoupled torsional vibration signal provided in one embodiment of this application; Figure 8 This is a schematic diagram of the spectrum analysis results of the decoupled axial vibration signal provided in one embodiment of this application; Figure 9 This is a schematic diagram of the spectrum analysis results of the decoupled torsional vibration signal provided in one embodiment of this application; Figure 10 This is a schematic diagram of the structure of an aero-engine torsional vibration and axial vibration measurement and signal analysis system provided in another embodiment of this application; Figure 11 This is a schematic diagram of the structure of an electronic device provided in another embodiment of this application. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the various embodiments of this application will be described in detail below with reference to the accompanying drawings. Those skilled in the art will understand that many technical details have been presented in the embodiments of this application to facilitate better understanding. However, the technical solutions claimed in this application can be implemented even without these technical details and various variations and modifications based on the following embodiments. The division of the following embodiments is for ease of description and should not constitute any limitation on the specific implementation of this application. The following embodiments can be combined with and referenced by each other without contradiction.

[0020] Vibration in aero-engine rotor systems is an unavoidable dynamic phenomenon. Torsional vibration is a constant companion during engine operation, and shaft fatigue and even shaft breakage accidents caused by severe torsional vibration occur frequently. However, monitoring of torsional vibration in aero-engine rotors is not yet widespread, and comprehensive real-time assessment standards are lacking.

[0021] Currently, non-contact measurement is commonly used for rotating machinery such as aero engines, but existing monitoring systems focus on monitoring the lateral bending vibration and axial movement of the rotor. To simultaneously monitor torsional vibration, traditional solutions require additional dedicated sensors within the limited installation space inside the engine. This not only increases system complexity, weight, and cost but also makes it difficult to adapt to the harsh environment of high temperatures and oil contamination inside the engine. For example, patent document CN115876450A discloses a rotating machinery torsional vibration testing system that relies on photoelectric sensors and specific excitation devices, primarily for laboratory bench testing and difficult to apply to real aero engine environments. Patent document CN113029322B proposes a method using an eddy current sensor in conjunction with a gear disk to simultaneously extract bending and torsional vibration signals, but this method is only applicable to lateral bending vibration, and the signal processing algorithm used has limited accuracy when processing high-frequency complex signals.

[0022] In summary, current technologies are either limited by the type of sensor used, making them unsuitable for the harsh operating conditions of aero-engines, or limited to measuring specific types of vibrations, and suffer from insufficient accuracy in decoupling algorithms for complex signals. Particularly for aero-engines, there is currently a lack of a method for obtaining and decoupling the coupled torsional and axial vibration signals using eddy current displacement sensors to achieve high-precision monitoring of axial and torsional vibrations. Therefore, how to effectively acquire and accurately decouple the coupled signals of axial and torsional vibrations of aero-engine rotors is a pressing technical problem that needs to be solved.

[0023] In view of this, embodiments of this application propose a method for measuring and analyzing torsional and axial vibrations of an aero-engine. This method utilizes only a single eddy current displacement sensor in conjunction with the engine's existing velocimetry wheel to simultaneously and accurately decouple and analyze axial and torsional vibrations, thereby simplifying the system, reducing costs, and improving engineering applicability and measurement reliability.

[0024] One embodiment of this application proposes a method for measuring and analyzing the torsional and axial vibrations of an aero-engine, applied to an electronic device. The electronic device can be a terminal or a server; this embodiment and subsequent embodiments will use a server as an example. The implementation details of the method for measuring and analyzing the torsional and axial vibrations of an aero-engine proposed in this embodiment are described below. The following details are provided for ease of understanding and are not essential for implementing this solution.

[0025] The specific process of the method for measuring and analyzing torsional and axial vibrations of aero-engines proposed in this embodiment can be described as follows: Figure 1 As shown, it includes steps 101 to 103.

[0026] For example, in an embodiment of this application, a single eddy current displacement sensor is mounted on the aircraft engine casing, and the probe of the eddy current displacement sensor is directly facing the velocimeter wheel inherent to the aircraft engine.

[0027] In one possible embodiment, the eddy current displacement sensor is mounted on the inner wall of the aircraft engine casing via a sensor bracket. The velocimeter wheel is perpendicular to the eddy current displacement sensor so that the output signal of the eddy current displacement sensor can be stabilized within a preset range by adjusting the gap between its probe and the tooth edge of the velocimeter wheel.

[0028] The preset range is greater than or equal to 500 micrometers.

[0029] like Figure 2 As shown, Figure 2 This is a schematic diagram of the arrangement of an eddy current displacement sensor provided for an embodiment of this application.

[0030] When installing the eddy current displacement sensor, the eddy current displacement sensor 2 must be fixedly mounted on the inner wall of the aircraft engine casing 1 using a sensor bracket. The velocimeter wheel 3 should be perpendicular to the eddy current displacement sensor 2, and the probe of the eddy current displacement sensor 4 must be aligned with the edge of the velocimeter wheel 3. This way, when the velocimeter wheel 3 vibrates axially, the gap voltage generated by the eddy current displacement sensor 2 will change significantly, resulting in an amplitude modulation effect. Adjust the distance between the eddy current displacement sensor 2 and the velocimeter wheel 3 so that the gap voltage between them is between 9.8 mV and 10.2 mV to ensure optimal measurement sensitivity.

[0031] For example, the hardware system mainly includes: an aircraft engine casing 1, an eddy current displacement sensor 2, an engine-inherent speed measuring sound wheel 3, a sensor bracket 4, and a data acquisition system.

[0032] like Figure 3 As shown, Figure 3 A schematic diagram of a signal transmission provided for an embodiment of this application; Specifically, the eddy current displacement sensor is fixed to the aircraft engine casing, mounted axially facing the velocimetric wheel, and connected to the data acquisition system. The eddy current displacement sensor must meet the requirement of an average sensitivity error ≤ ±5% within its measurement range to adapt to the harsh environment of the aircraft engine, characterized by high temperatures and oil contamination, and to ensure measurement accuracy. The data acquisition system must be used in conjunction with the eddy current displacement sensor, and the sampling frequency must be no less than 200 kHz to satisfy the Nyquist sampling theorem for high-frequency gear signals, ensuring signal integrity. The velocimetric wheel 3 must have at least 10 teeth to ensure sufficient signal period for analysis.

[0033] It should be noted that both the velocity sound wheel 3 and the aircraft engine casing 1 are inherent components in the aircraft engine.

[0034] Step 101: With the aircraft engine running, the raw time-domain signal is acquired using an eddy current displacement sensor.

[0035] The original time-domain signal contains coupled information of torsional vibration and axial vibration.

[0036] In one possible embodiment, step 101 includes: when the aircraft engine is started, driving the velocimeter wheel to rotate by the rotation of the aircraft engine; when the velocimeter wheel vibrates axially, acquiring the voltage signal induced by the rotation of the velocimeter wheel in real time through an eddy current displacement sensor and a data acquisition system connected thereto, and using it as the original time domain signal.

[0037] For example, when an aircraft engine rotates, it drives a velocimetric wheel to operate. When the velocimetric wheel vibrates axially, the gap between the velocimetric wheel and the eddy current displacement sensor changes periodically, causing the amplitude of the output signal of the eddy current displacement sensor to be modulated. When the velocimetric wheel vibrates torsionally, its instantaneous angular velocity changes periodically, causing the frequency of the output signal of the eddy current displacement sensor to be modulated.

[0038] After installation and commissioning, the aircraft engine is started. As the engine rotates, it drives the velocimetry wheel, causing an eddy current displacement sensor to detect the gap change generated by the passing of the toothed disc, outputting a voltage signal. This signal is converted into a digital signal by a data acquisition system and input into data analysis software on a computer to obtain the raw time-domain signal. ,like Figure 4 As shown, Figure 4 This is a schematic diagram of a raw time-domain signal containing torsional vibration signal and axial vibration signal, provided for an embodiment of this application. Figure 5 The original time-domain signal was collected during an actual engine bench test, as shown in the embodiments of this application.

[0039] Specifically, for the input raw voltage signal, when the shaft does not experience axial or torsional vibration, the output signal of the eddy current displacement sensor is a set of sinusoidal signals with a constant frequency. : ; in, This indicates the number of teeth on the gear of the velocimetric sound wheel. This indicates the rotational speed of the velocimetric sound wheel; Indicates the signal amplitude. This represents the sensor sensitivity coefficient; When the rotor (i.e., the tachometer wheel) undergoes torsional vibration, the speed of the rotor passing through the toothed disc will change periodically, and the frequency of the change is the rotor torsional vibration frequency. At this time, the rotor speed is: ; in, This represents the instantaneous angular velocity of torsional vibration. This represents the torsional vibration influence coefficient, and ; Indicates the frequency of torsional vibration. The initial phase angle of the torsional vibration; Indicates the amplitude of the angular displacement during torsional vibration; At this time, the output signal of the eddy current displacement sensor for: ; At this point, if the rotor experiences axial vibration, its axial displacement will be disturbed. The low-frequency axial vibration and the high-frequency gear disk signal produce amplitude modulation, thus affecting the output of the original time-domain signal. for: (4) in, This represents the axial vibration amplitude. The axial vibration frequency is This represents the initial phase angle of the axial vibration.

[0040] Step 102: Demodulate the original time-domain signal to obtain independent axial vibration components and torsional vibration components from the original time-domain signal.

[0041] In one possible embodiment, step 102 includes: performing a Hilbert transform on the original time-domain signal to extract the axial vibration component (i.e., the axial vibration signal) from the original time-domain signal through the constructed complex analytic signal; and extracting the torsional vibration component (i.e., the torsional vibration signal) from the original time-domain signal based on the axial vibration component and the original time-domain signal.

[0042] For example, performing a Hilbert transform on the original time-domain signal to extract the axial vibration component from the original time-domain signal using the constructed complex analytic signal includes: performing a Hilbert transform on the original time-domain signal to obtain a first signal; constructing a complex analytic signal by using the original time-domain signal as the real part and the first signal as the imaginary part; calculating the envelope signal of the complex analytic signal, and performing amplitude correction and DC removal processing on the envelope signal to obtain the separated axial vibration signal.

[0043] For example, the extraction of axial vibration components is as follows: First, the original time-domain signal Perform a Hilbert transform to obtain the first signal; where, the first signal The calculation formula is as follows: ; The original time-domain signal As the real part, the first signal As the imaginary part, construct a complex analytic signal; complex analytic signal The calculation formula is as follows: ; Complex analytic signal Extract its envelope signal from the absolute value of the signal. : ; For envelope signal Amplitude correction and DC removal are performed to obtain the separated axial vibration components. .

[0044] ; It should be noted that, in the embodiments, for real data signals... Its amplitude With envelope signal The mean values ​​are equal.

[0045] For example, based on the axial vibration component and the original time-domain signal, the torsional vibration component is extracted from the original time-domain signal, including: subtracting the axial vibration component from the original time-domain signal to eliminate the interference of the axial vibration component and obtain the torsional vibration correlation signal; based on the torsional vibration correlation signal, calculating the rotor transient angular velocity sequence by detecting the zero-crossing point or extreme point of the signal, and using the transient angular velocity sequence as the separated torsional vibration component.

[0046] Specifically, based on torsional vibration correlation signals, the transient angular velocity sequence of the rotor is calculated by detecting the zero-crossing points or extreme points of the signals, and the transient angular velocity sequence is used as the separated torsional vibration components, including: identifying continuous components in the net torsional vibration correlation signal. The target point is within a cycle; the time interval between adjacent target points is calculated, and the transient angular velocity is calculated based on the time interval and the angle corresponding to a single tooth of the velocimetric wheel. The continuously calculated transient angular velocity sequence is then used as the separated torsional vibration component.

[0047] in, The target point is either a zero-crossing point or a specific extreme point.

[0048] For example, the extraction of torsional vibration components is as follows: The original time-domain signal Subtract axial vibration component This eliminates interference from the axial vibration component, resulting in a signal free from axial vibration interference. ; ; Pick A signal of one cycle (including) A maximum point, (The number of teeth on the velocimetric sound wheel). Greater than or equal to 4; and calculate the first maximum point and the th maximum point. Time difference between each maximum point The average speed of the rotor is then... for: ; Calculate the signal mean The measured signal is subtracted from its mean to construct a zero-mean signal, i.e.: ; Calculate the duration between consecutive rising edges of the signal passing through the zero point. Dividing this by the angle corresponding to the two teeth gives an approximate value for the rotor's transient angular velocity, i.e.: ; ; Continuous calculation The transient angular velocity of the signal over one period can be used to obtain the time series of the transient angular velocity, which is the torsional vibration component. .

[0049] This completes the decoupling of the torsional vibration component and the axial vibration component.

[0050] Step 103: Perform spectral analysis on the independent axial vibration component and torsional vibration component to obtain their respective vibration frequency domain and amplitude.

[0051] In one possible embodiment, step 103 includes: performing spectral analysis on the axial vibration component using Fast Fourier Transform to expand the axial vibration component into a series, and then converting the axial vibration component from the time domain to the frequency domain to obtain the vibration frequency domain and amplitude of the axial vibration component; and performing spectral analysis on the torsional vibration component using Fast Fourier Transform to expand the torsional vibration component into a series, and then converting the torsional vibration component from the time domain to the frequency domain to obtain the vibration frequency domain and amplitude of the torsional vibration component.

[0052] For example, this embodiment uses Fast Fourier Transform for analysis. The time-domain signal... and Converting to the frequency domain yields their respective spectrum diagrams. In the spectrum diagram, the frequencies corresponding to the prominent peaks in amplitude are the main axial or torsional vibration frequencies, and their amplitudes represent the vibration intensity of that frequency component.

[0053] This application proposes a method for measuring and analyzing torsional and axial vibrations of an aero-engine. First, with the aero-engine running, an eddy current displacement sensor acquires raw time-domain signals, which contain coupled information of torsional and axial vibrations. Then, the raw time-domain signals are demodulated to obtain independent axial and torsional vibration components. Finally, spectral analysis is performed on the independent axial and torsional vibration components to obtain their respective vibration frequency domains and amplitudes. Since a single eddy current displacement sensor is installed on the aero-engine casing, and the sensor's probe is directly facing the aero-engine's inherent velocimetry sound wheel, effective acquisition and high-precision decoupling analysis of the coupled signals of the aero-engine rotor's axial and torsional vibrations are achieved. Based on this, this solution utilizes only a single eddy current displacement sensor in conjunction with the engine's existing velocimetry sound wheel to synchronously and accurately decouple and analyze axial and torsional vibrations, thereby simplifying the system, reducing costs, and improving engineering applicability and measurement reliability.

[0054] The effectiveness of this method can be verified by testing on an engine rotor test bench. In the experiment, the acquired raw signals ( Figure 5 By applying the decoupling algorithm provided in the above embodiments, it is possible to successfully separate components such as... Figure 6 The axial vibration signal shown and Figure 7 The torsional vibration signal is shown. Subsequently, FFT analysis was performed on these two signals, and their spectra were obtained as shown below. Figure 8 and Figure 9 As shown, that is Figure 8 The axial vibration signal spectrum and Figure 9 The spectrum of the torsional vibration signal. Figure 8 In the analysis, the 30.2Hz component is dominant, which is consistent with the results of other axial vibration measurement channels. Figure 9 The 35.2Hz component is dominant, which is consistent with the analysis results of other torsional vibration measurement channels.

[0055] The steps described above are for clarity only. In implementation, they can be combined into one step, or some steps can be broken down into multiple steps, as long as they involve the same logical relationship, they are all within the scope of protection of this application. Adding insignificant modifications or introducing insignificant designs to the algorithm or process, without changing the core design of the algorithm and process, are also within the scope of protection of this application.

[0056] Another embodiment of this application proposes a system for measuring and analyzing torsional and axial vibrations of an aero-engine. The details of this system are described below for ease of understanding and are not essential for implementing this example. Figure 10 This is a schematic diagram of the structure of an aero-engine torsional vibration and axial vibration measurement and signal analysis system proposed in this embodiment, including: The signal acquisition module 210 is used to acquire raw time-domain signals via an eddy current displacement sensor when the aero-engine is started; wherein the raw time-domain signals contain coupled information of torsional vibration and axial vibration. The demodulation processing module 220 is used to demodulate the original time-domain signal to obtain independent axial vibration components and torsional vibration components from the original time-domain signal. The spectrum analysis module 230 is used to perform spectrum analysis on the independent axial vibration component and torsional vibration component to obtain their respective vibration frequency domain and amplitude.

[0057] It is not difficult to see that this embodiment is a system embodiment corresponding to the above method embodiments, and this embodiment can be implemented in conjunction with the above method embodiments. The relevant technical details and technical effects mentioned in the above method embodiments are still valid in this embodiment, and will not be repeated here to reduce repetition. Accordingly, the relevant technical details mentioned in this embodiment can also be applied to the above method embodiments.

[0058] It is worth mentioning that all modules and units involved in this embodiment are logical modules. In practical applications, a logical unit can be a physical unit, a part of a physical unit, or a combination of multiple physical units. Furthermore, to highlight the innovative aspects of this application, this embodiment does not introduce units that are not closely related to solving the technical problems proposed in this application; however, this does not mean that other units are absent in this embodiment.

[0059] Another embodiment of this application provides an electronic device, such as Figure 11 As shown, it includes a processor 31 and a memory 32. The memory 32 stores instructions that the processor 31 can execute. When the processor 31 is configured to execute the instructions, the electronic device can realize a method for measuring and analyzing torsional vibration and axial vibration of an aero-engine as described in the above method embodiment.

[0060] The memory and processor are connected via a bus, which includes any number of interconnecting buses and bridges, connecting various circuits of one or more processors and the memory. The bus can also connect various other circuits such as peripheral devices, voltage regulators, and power management circuits, which are well known in the art and will not be described further herein. The bus interface provides an interface between the bus and the transceiver. The transceiver can be a single component or multiple components, such as multiple receivers and transmitters, providing a unit for communicating with various other devices over a transmission medium. Data processed by the processor is transmitted over the wireless medium via an antenna, which further receives data and transmits it to the processor.

[0061] The processor manages the bus and general processing, and also provides various functions, including timing, peripheral interfaces, voltage regulation, power management, and other control functions. Memory is used to store data used by the processor during operation.

[0062] Another embodiment of this application proposes a computer-readable storage medium storing a computer program that, when executed by a processor, enables a method for measuring and analyzing torsional and axial vibrations of an aero-engine as described in the above method embodiments.

[0063] That is, those skilled in the art will understand that all or part of the steps in the above method embodiments can be implemented by a program instructing related hardware. The program is stored in a storage medium and includes several instructions to cause a device (such as a microcontroller, chip, etc.) or processor to execute all or part of the steps of the method described in the method embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory, random access memory, magnetic disks, or optical disks.

[0064] Those skilled in the art will understand that the above embodiments are specific implementations of this application, and in practical applications, various changes can be made in form and detail without departing from the spirit and scope of this application. For those skilled in the art, several improvements and modifications can be made without departing from the principles of this application, and these improvements and modifications are also considered to be within the scope of protection of this application.

Claims

1. A method for measuring and analyzing the torsional and axial vibrations of an aero-engine, characterized in that, A single eddy current displacement sensor is mounted on the aircraft engine casing, and the probe of the eddy current displacement sensor is directly facing the aircraft engine's inherent velocimeter wheel. The method includes: When the aircraft engine is running, the raw time-domain signal is acquired by an eddy current displacement sensor; the raw time-domain signal contains the coupling information of torsional vibration and axial vibration. The original time-domain signal is demodulated to obtain independent axial vibration and torsional vibration components from the original time-domain signal; Spectral analysis was performed on the independent axial vibration component and torsional vibration component to obtain their respective vibration frequency domain and amplitude.

2. The method according to claim 1, characterized in that, The eddy current displacement sensor is mounted on the inner wall of the aircraft engine casing via a sensor bracket. The velocimeter wheel is perpendicular to the eddy current displacement sensor so that the output signal of the eddy current displacement sensor can be stabilized within a preset range by adjusting the gap between its probe and the tooth edge of the velocimeter wheel; the preset range is greater than or equal to 500 micrometers. The process of acquiring raw time-domain signals via an eddy current displacement sensor when the aero-engine is started includes: When the aircraft engine is running, the speed measuring sound wheel is driven to rotate by the rotation of the aircraft engine. When the velocimetric wheel vibrates axially, the voltage signal generated by the rotation of the velocimetric wheel is collected in real time by the eddy current displacement sensor and the data acquisition system connected to it, and used as the original time domain signal.

3. The method according to claim 1, characterized in that, The demodulation process of the original time-domain signal to obtain independent axial vibration and torsional vibration components from the original time-domain signal includes: The Hilbert transform is performed on the original time-domain signal to extract the axial vibration component from the original time-domain signal through the constructed complex analytic signal; Based on the axial vibration component and the original time-domain signal, the torsional vibration component is extracted from the original time-domain signal.

4. The method according to claim 3, characterized in that, The step of performing a Hilbert transform on the original time-domain signal to extract the axial vibration component from the original time-domain signal using the constructed complex analytic signal includes: The first signal is obtained by performing a Hilbert transform on the original time-domain signal. A complex analytic signal is constructed by taking the original time-domain signal as the real part and the first signal as the imaginary part. The envelope signal of the complex analytic signal is calculated, and the amplitude is corrected and DC is removed from the envelope signal to obtain the separated axial vibration signal.

5. The method according to claim 3, characterized in that, The extraction of torsional vibration components from the original time-domain signal based on the axial vibration component and the original time-domain signal includes: The axial vibration component is subtracted from the original time-domain signal to eliminate the interference of the axial vibration component, thus obtaining the torsional vibration correlation signal; Based on the torsional vibration correlation signal, the transient angular velocity sequence of the rotor is calculated by detecting the zero-crossing point or extreme point of the signal, and the transient angular velocity sequence is used as the separated torsional vibration component.

6. The method according to claim 5, characterized in that, The method of calculating the rotor transient angular velocity sequence based on torsional vibration correlation signals by detecting signal zero-crossing points or extreme points, and using the transient angular velocity sequence as the separated torsional vibration components, includes: Identifying continuous signals in net torsional vibration correlation signals The target points within each cycle; among them. The target point is either a zero-crossing point or a specific extreme point; The time interval between adjacent target points is calculated, and the transient angular velocity is calculated based on the time interval and the angle corresponding to a single tooth of the velocimetric wheel. The continuously calculated transient angular velocity sequence is then used as the separated torsional vibration component.

7. The method according to any one of claims 1 to 6, characterized in that, The process of performing spectral analysis on the independent axial vibration components and torsional vibration components to obtain their respective vibration frequency domains and amplitudes includes: Fast Fourier Transform is used to perform spectral analysis on the axial vibration component, so as to expand the axial vibration component into a series, and then convert the axial vibration component from the time domain to the frequency domain, so as to obtain the vibration frequency domain and amplitude of the axial vibration component. The torsional vibration component is subjected to spectral analysis using Fast Fourier Transform (FFT) to expand the torsional vibration component into a series, thereby converting the torsional vibration component from the time domain to the frequency domain, and obtaining the vibration frequency domain and amplitude of the torsional vibration component.

8. A system for measuring and analyzing torsional and axial vibrations of an aero-engine, characterized in that, A single eddy current displacement sensor is mounted on the aircraft engine casing, with the probe of the eddy current displacement sensor facing the aircraft engine's inherent velocimeter wheel. The system includes: The signal acquisition module is used to acquire raw time-domain signals via an eddy current displacement sensor when the aero-engine is started; the raw time-domain signals contain coupled information of torsional vibration and axial vibration. The demodulation processing module is used to demodulate the original time-domain signal to obtain independent axial vibration components and torsional vibration components from the original time-domain signal. The spectrum analysis module is used to perform spectrum analysis on the independent axial vibration components and torsional vibration components to obtain their respective vibration frequency domain and amplitude.

9. An electronic device, characterized in that, include: A processor and a memory, wherein the memory stores instructions that the processor can execute, and the processor is configured to, when executing the instructions, enable the electronic device to implement a method for measuring and analyzing torsional and axial vibrations of an aero-engine as described in any one of claims 1 to 7.

10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it can realize a method for measuring and analyzing torsional vibration and axial vibration of an aero-engine as described in any one of claims 1 to 7.

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