CN113358214A - Fault detection method for jet fan structural body and related equipment - Google Patents
Fault detection method for jet fan structural body and related equipment Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
- F04D29/646—Mounting or removal of fans
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Abstract
The application discloses jet fan structure fault detection method and relevant equipment, and the method comprises the following steps: acquiring a vibration data sequence of the jet flow fan in operation by utilizing a sensor array arranged on a jet flow fan structure; performing time domain analysis on the vibration data sequence, and extracting time domain characteristic parameters; carrying out frequency domain analysis on the vibration data sequence, and extracting frequency domain characteristic parameters; calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference and the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference; judging whether the jet fan structural body breaks down or not and judging the position of the fault according to the time domain difference and the frequency domain difference; the method can replace manual regular detection, and can solve the problem that the fault of the installation structure body of the jet fan is difficult to find in time due to the limitation of manual detection.
Description
Technical Field
The application relates to the technical field of equipment testing, in particular to a method for detecting faults of a jet fan structural body and related equipment.
Background
The induced air current in tunnel mainly adopts the efflux fan of suspension type installation to realize, and the efflux fan is generally installed at the top in tunnel, the top on lane promptly, in case the emergence accident that drops will seriously influence tunnel driving safety, consequently, becomes especially important to the fault detection of efflux fan.
However, the detection and maintenance of the jet fan are performed by manual regular inspection, which mainly checks whether the appearance of the jet fan is abnormal or not, judges whether the fan is abnormal or not, and the like, and is difficult to find out whether the installation structure of the jet fan fails or not through manual inspection.
Disclosure of Invention
The embodiment of the application provides a method and related equipment for detecting the structural body fault of a jet fan, which can replace manual regular detection and solve the problem that the fault of an installation structural body of the jet fan cannot be found in time due to the limitation of manual detection.
In a first aspect of the embodiments of the present application, a method for detecting a fault of a jet fan structural body is provided, including:
acquiring a vibration data sequence of a jet flow fan in operation by utilizing a sensor array arranged on a jet flow fan structural body, wherein the jet flow fan structural body comprises the jet flow fan and an installation structural body for erecting the jet flow fan, and the sensor array comprises a plurality of acceleration sensor units;
performing time domain analysis on the vibration data sequence, and extracting time domain characteristic parameters;
carrying out frequency domain analysis on the vibration data sequence, and extracting frequency domain characteristic parameters;
calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, and calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the normal time domain characteristic value range is the numerical range of the time domain characteristic parameter when the jet fan structural body normally operates, and the normal frequency domain characteristic value range is the numerical range of the frequency domain characteristic parameter when the jet fan structural body normally operates;
and judging whether the jet fan structural body breaks down or not and judging the position of the fault according to the time domain difference and the frequency domain difference.
In some embodiments, the mounting structure comprises a blower body mount and a mounting mount, the jet blower being disposed on the blower body mount;
before the step of acquiring the vibration data sequence of the jet flow fan in operation by using the sensor array arranged on the jet flow fan structure body, the method comprises the following steps:
and at least one acceleration sensor unit is respectively arranged on the outer wall of the jet flow fan and the mounting bracket, wherein all the acceleration sensor units form the sensor array.
In some embodiments, the mounting structure further comprises an embedded steel plate, and the mounting bracket is disposed between the blower body bracket and the embedded steel plate;
before the step of acquiring the vibration data sequence of the jet flow fan in operation by using the sensor array arranged on the jet flow fan structure, the method further comprises the following steps:
and installing the acceleration sensor unit on the embedded steel plate.
In some embodiments, the acceleration sensor unit comprises a three-axis acceleration sensor, the vibration data sequence comprises a three-axis acceleration data sequence, and the time-domain characteristic parameter comprises a displacement time-domain effective value;
before the step of performing time domain analysis on the vibration data sequence and extracting time domain characteristic parameters, the method comprises the following steps of:
and sequentially carrying out filtering processing and direct-current component removal processing on the triaxial acceleration data sequence to obtain corresponding acceleration curve data in three axial directions.
In some embodiments, the step of performing a time domain analysis on the vibration data sequence to extract a time domain feature parameter includes:
sequentially carrying out primary integral calculation, primary curve fitting, secondary integral calculation and secondary curve fitting on the acceleration curve data in the three axial directions to obtain displacement curve data;
and calculating the root mean square value of the displacement curve data to obtain the displacement time domain effective value.
In some embodiments, the frequency domain characteristic parameters include an amplitude spectrum;
the step of performing frequency domain analysis on the vibration data sequence and extracting frequency domain characteristic parameters comprises the following steps:
and carrying out Fourier transform on the acceleration curve data in the three axial directions to obtain the amplitude spectrums corresponding to the three axial directions.
In some embodiments, before the step of calculating the difference between the time domain characteristic parameter value range and the normal time domain characteristic value range to obtain the time domain difference, and calculating the difference between the frequency domain characteristic parameter value range and the normal frequency domain characteristic value range to obtain the frequency domain difference, the method includes:
fusing the frequency domain characteristic parameters corresponding to the same acceleration sensor unit to obtain the proportion distribution of energy of each frequency band in the total energy;
calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, and calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the step of calculating the difference comprises the following steps:
calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain the time domain difference;
and calculating the difference between the proportion distribution of the energy of each frequency band in the total energy and the normal proportion distribution to obtain the frequency domain difference.
A second aspect of the embodiments of the present application provides a system for detecting a fault of a jet fan structure, including:
the sensor array is arranged on the jet flow fan structural body and used for acquiring a vibration data sequence of the jet flow fan in operation, wherein the jet flow fan structural body comprises a jet flow fan and an installation structural body for erecting the jet flow fan, and the sensor array comprises a plurality of acceleration sensor units;
the time domain analysis module is used for carrying out time domain analysis on the vibration data sequence and extracting time domain characteristic parameters;
the frequency domain analysis module is used for carrying out frequency domain analysis on the vibration data sequence and extracting frequency domain characteristic parameters;
the difference calculation module is used for calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, and calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the normal time domain characteristic value range is the numerical range of the time domain characteristic parameter when the jet fan structural body normally operates, and the normal frequency domain characteristic value range is the numerical range of the frequency domain characteristic parameter when the jet fan structural body normally operates;
and the diagnosis module is used for judging whether the jet fan structural body breaks down or not and judging the position of the fault according to the time domain difference and the frequency domain difference.
In a third aspect of the embodiments of the present application, an electronic device is provided, where the electronic device includes at least one processor, and at least one memory and a bus connected to the processor; the processor and the memory complete mutual communication through the bus; the processor is used for calling the program instructions in the memory and executing the steps of the method for detecting the structural body fault of the jet flow fan.
In a fourth aspect of the embodiments of the present application, a storage medium is provided, where the storage medium includes a stored program, and when the program runs, the apparatus on which the storage medium is located is controlled to execute the steps of the method for detecting a fault of a jet fan structural body described in any one of the above.
The jet fan structure body fault detection method and the related equipment provided by the embodiment of the application monitor the vibration condition of the jet fan structure body in the operation of the jet fan by adopting the sensor array, and install the acceleration sensor units on the jet fan of the jet fan structure body and the installation structure body, so that the operation condition of the jet fan can be monitored, and the condition of the installation structure body in the operation of the jet fan can be monitored simultaneously. The analysis of two dimensions of a time domain and a frequency domain is carried out on a vibration data sequence collected at a plurality of positions on the jet fan structural body, so that the time domain difference between a time domain characteristic value range and a normal time domain characteristic value range and the frequency domain difference between a frequency domain characteristic value range and a normal frequency domain characteristic value range are obtained, the range size of the time domain difference is judged, the range size of the frequency domain difference is judged, whether the jet fan structural body breaks down or not can be determined, the position of the fault can be determined if the fault happens, the abnormity or the fault can be timely found, and the accurate positioning can be realized. Therefore, the method for detecting the fault of the jet fan structure body provided by the embodiment of the application can detect and locate the fault of whether the bolt of the jet fan is loosened, whether the bracket is cracked, whether the motor bearing is in fault, whether the blade is in unbalanced fault and the like, can replace manual periodic inspection, and solves the problem that the fault of the jet fan is difficult to find in time due to the limitation of manual detection.
Drawings
Fig. 1 is a schematic flow chart of a method for detecting a fault of a jet fan structure according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of a jet fan structure provided in an embodiment of the present application;
FIG. 3 is a top view of a mounting bracket according to an embodiment of the present application;
fig. 4 is a schematic structural block diagram of a fault detection system of a jet fan structural body according to an embodiment of the present disclosure;
fig. 5 is a schematic structural block diagram of an electronic device according to an embodiment of the present application.
Detailed Description
In order to better understand the technical solutions provided by the embodiments of the present specification, the technical solutions of the embodiments of the present specification are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present specification are detailed descriptions of the technical solutions of the embodiments of the present specification, and are not limitations on the technical solutions of the embodiments of the present specification, and the technical features in the embodiments and examples of the present specification may be combined with each other without conflict.
In this document, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element. The term "two or more" includes the case of two or more.
The induced air current in tunnel mainly adopts the efflux fan of suspension type installation to realize, and the efflux fan is generally installed at the top in tunnel, the top on lane promptly, in case the emergence accident that drops will seriously influence tunnel driving safety, consequently, becomes especially important to the fault detection of efflux fan. However, the detection and maintenance of the jet fan are performed by manual regular inspection, which mainly checks whether the appearance of the jet fan is abnormal or not, judges whether the fan is abnormal or not, and the like, and is difficult to find out whether the installation structure of the jet fan fails or not through manual inspection.
In view of this, the present application provides a method and related device for detecting a fault of a structural body of a jet fan, which can replace manual periodic detection, automatically acquire vibration data of the jet fan during operation by using a sensor array, and detect and locate faults such as whether a bolt of the jet fan is loose, whether a bracket is cracked, or whether a motor bearing is in fault through data analysis, so as to solve the problem that the fault of a structural body of the jet fan is difficult to find in time due to the limitation of manual detection.
In a first aspect, in a feasible implementation manner, an embodiment of the present application provides a method for detecting a fault of a jet fan structure, and fig. 1 is a schematic flow chart of the method for detecting a fault of a jet fan structure provided in the embodiment of the present application. As shown in fig. 1, a method for detecting a fault of a jet fan structural body provided in an embodiment of the present application includes:
s100: the method comprises the steps of obtaining a vibration data sequence of the jet flow fan in operation by utilizing a sensor array installed on a jet flow fan structure body, wherein the jet flow fan structure body comprises the jet flow fan and an installation structure body for erecting the jet flow fan, and the sensor array comprises a plurality of acceleration sensor units. The acceleration sensor unit may be a vibration sensor, and the present application is not particularly limited. Acceleration sensor units can be arranged on the jet fan and the mounting structure, all the acceleration sensor units can form a sensor array, and vibration data sequences acquired by each acceleration sensor unit respectively reflect vibration conditions of corresponding mounting positions in operation. Each element of the vibration data sequence may be sampling data corresponding to one sampling time point, and the application is not particularly limited. The vibration data sequence may be collected according to a set sampling rate, and the application is not limited in particular.
S200: and performing time domain analysis on the vibration data sequence and extracting time domain characteristic parameters.
S300: and carrying out frequency domain analysis on the vibration data sequence and extracting frequency domain characteristic parameters. It is easily understood that the vibration data sequence includes time domain information and frequency domain information, which respectively represent data in two dimensions of time and frequency. The time domain analysis is performed on the vibration data sequence, so that various time domain characteristic parameters can be extracted, and the time domain characteristic parameters may include a peak value parameter, a mean value parameter, a root mean square value (effective value) and the like in a sampling period, which is not specifically limited in the present application. The frequency domain analysis is performed on the vibration data sequence, so that various frequency domain characteristic parameters can be extracted, and the frequency domain characteristic parameters may include frequency, amplitude, phase and the like, which is not specifically limited in the present application.
S400: calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, and calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the normal time domain characteristic value range is the numerical range of the time domain characteristic parameter when the jet fan structural body normally operates, and the normal frequency domain characteristic value range is the numerical range of the frequency domain characteristic parameter when the jet fan structural body normally operates. The normal time domain characteristic value range can be a vibration data sequence of the normal jet fan structural body in a normal operation state, extracted normal time domain characteristic values are analyzed through a time domain, and the numerical ranges of all the normal time domain characteristic values form the normal time domain characteristic value range. Similarly, the normal frequency domain characteristic value range may be a normal frequency domain characteristic value range extracted through frequency domain analysis by acquiring a vibration data sequence of the normal jet fan structure in a normal operation state in advance, and the numerical ranges of all the normal frequency domain characteristic values constitute the normal frequency domain characteristic value range. Calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, wherein the numerical range of the time domain characteristic parameter in the step is the numerical range of all the time domain characteristic parameters obtained in the step S200, the time domain difference can reflect the difference between the time domain characteristic parameter of the outgoing flow fan structural body in the current operation and the time domain parameter in the normal operation, and the difference between the data sequences can be embodied by adopting the difference in the numerical range. Calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the numerical range of the frequency domain characteristic parameter in the step is the numerical range of all the frequency domain characteristic parameters obtained in the step S300, the frequency domain difference can reflect the difference between the frequency domain characteristic parameter of the jet fan structural body in the current operation and the frequency domain characteristic parameter in the normal operation, and the difference between the data sequences can be embodied by adopting the difference in the numerical range.
S500: and judging whether the jet fan structural body breaks down or not and judging the position of the fault according to the time domain difference and the frequency domain difference. It is easy to understand that the time domain difference amount and the frequency domain difference amount in this step may be a numerical range, and by determining the range size of the time domain difference amount and determining the range size of the frequency domain difference amount, it may be determined whether the jet fan structural body has a fault, and if so, the position where the fault occurs. For example, if the range of the time domain difference is large, it can be determined that the position of the jet fan structural body corresponding to the acceleration sensor unit corresponding to the data with the large time domain difference is abnormal, and the abnormality may be bolt looseness, bracket cracking or blade imbalance fault. If the range of the frequency domain difference is judged to be large, the motor bearing abnormality of the jet fan corresponding to the sensor corresponding to the data with the large frequency domain difference can be determined. The determined abnormal condition may cause or already cause a failure of the jet fan structure.
The jet fan structure fault detection method provided by the embodiment of the application monitors the vibration condition of the jet fan structure in the operation of the jet fan by adopting the sensor array, and the acceleration sensor units are installed on the jet fan and the installation structure of the jet fan structure, so that the operation condition of the jet fan can be monitored, and the condition of the installation structure in the operation of the jet fan can be monitored simultaneously. The analysis of two dimensions of a time domain and a frequency domain is carried out on a vibration data sequence collected at a plurality of positions on the jet fan structural body, so that the time domain difference between a time domain characteristic value range and a normal time domain characteristic value range and the frequency domain difference between a frequency domain characteristic value range and a normal frequency domain characteristic value range are obtained, the range size of the time domain difference is judged, the range size of the frequency domain difference is judged, whether the jet fan structural body breaks down or not can be determined, the position of the fault can be determined if the fault happens, the abnormity or the fault can be timely found, and the accurate positioning can be realized. Therefore, the method for detecting the structural body fault of the jet fan can detect and locate whether the bolt of the jet fan is loosened, whether the bracket is cracked, whether the motor bearing breaks down, whether the blade imbalance fault exists and the like, can replace manual periodic inspection, and solves the problem that the structural body fault of the jet fan cannot be found in time due to the limitation of manual detection.
In a possible implementation manner, fig. 2 is a schematic structural diagram of a jet fan structure provided in an embodiment of the present application; fig. 3 is a top view of a mounting bracket according to an embodiment of the present application. As shown in fig. 2 and 3, the jet fan structure includes a jet fan 100 and a mounting structure. The mounting structure includes a blower body support 210 and a mounting support 220, the jet blower 100 is disposed on the blower body support 210, and the mounting support 220 is connected to the blower body support 210. The mounting bracket 220 and the fan body bracket 210 may be connected by bolts, specifically, as shown in fig. 3, the bolts may be disposed at four corners of a bottom plate of the mounting bracket 220, which are a first bolt 221, a second bolt 222, a third bolt 223 and a fourth bolt 224, respectively, the third bolt 223 and the fourth bolt 224 are disposed at a side close to the air inlet side Fin of the jet fan, and the first bolt 221 and the second bolt 222 are disposed at a side close to the air outlet side Fout of the jet fan.
Before step S100, the method may include:
at least one acceleration sensor unit is respectively arranged on the outer wall of the jet flow fan and the mounting bracket, wherein all the acceleration sensor units form a sensor array.
With continued reference to fig. 2 and 3, a first acceleration sensor unit B is mounted on an outer wall of the jet fan 100, and a second acceleration sensor unit D1 and a third acceleration sensor unit D2 are mounted on the mounting bracket 220, and illustratively, the third acceleration sensor unit D2 may be mounted between the first bolt 221 and the third bolt 223, and the second acceleration sensor unit D1 may be mounted between the second bolt 222 and the fourth bolt 224. The second acceleration sensor unit D1 may be used to sense vibration conditions of the second and fourth bolts 222 and 224 in the jet fan operating state, and the third acceleration sensor unit D2 may be used to sense vibration conditions of the first and third bolts 221 and 223 in the jet fan operating state. The first acceleration sensor unit B may be used to sense a vibration condition in an operating state of the jet fan.
The jet fan structure fault detection method provided by the embodiment of the application comprises the steps that the acceleration sensor units are respectively arranged on the jet fan and the mounting support, all the acceleration sensor units form a sensor array, the vibration data sequence is synchronously acquired, the running condition of the jet fan can be reflected, the conditions that whether a screw is loosened or the mounting support is cracked or not can be reflected on the mounting support, and the running condition of the jet fan structure can be monitored in all directions.
In one possible embodiment, for example, with continued reference to fig. 2, the mounting structure further includes a pre-embedded steel plate 240 and a cement protector 230, and the mounting bracket 220 is disposed between the blower body bracket 210 and the pre-embedded steel plate 240. The pre-buried steel plate 240 can have two, can do the slope or the radian setting of adaptability with cement protection body 230 according to the slope or the radian of tunnel lateral wall, and installing support 220 can be provided with two curb plates simultaneously, is provided with short curb plate 225 and long curb plate 226 according to the slope or the radian that the adaptability was done to cement protection body 230. The fan body support 210, the mounting support 220 and the embedded steel plate 240 can be made of steel materials and can also be made of other metal materials, and the application is not specifically limited. The pre-buried steel plate 240 can be welded with a tunnel steel structure, and the cement protection body 230 can play a role in protecting and strengthening the welding position of the pre-buried steel plate 240 and the tunnel steel structure.
Before step S100, the method may further include:
the acceleration sensor unit is mounted on the embedded steel plate 240.
For example, referring to fig. 2, a fourth acceleration sensor unit E1 and a fifth acceleration sensor unit E2 may be mounted on the two embedded steel plates 240, respectively. The fourth acceleration sensor unit E1 and the fifth acceleration sensor unit E2 may be used to sense the vibration of the embedded steel plate 240 in the operation state of the jet fan 100. Whether the pre-buried steel plate 240 cracks or not or whether the connection between the pre-buried steel plate 240 and the tunnel steel structure is loosened or not can be detected through sensing the vibration condition of the pre-buried steel plate 240 in the running state of the jet fan 100 by the fourth acceleration sensor unit E1 and the fifth acceleration sensor unit E2.
In a possible implementation, the acceleration sensor unit may include a three-axis acceleration sensor, the vibration data sequence includes a three-axis acceleration data sequence, and the time-domain characteristic parameter includes a displacement time-domain effective value. As shown in fig. 2 and 3, the three axial directions of the three-axis acceleration sensor may be an x-axis, a y-axis, and a z-axis. Each axial direction of each acceleration sensor unit may correspond to one set of acceleration data series, and the first acceleration sensor unit B, the second acceleration sensor unit D1, the third acceleration sensor unit D2, the fourth acceleration sensor unit E1, and the fifth acceleration sensor unit E2 may correspond to 15 sets of acceleration data series.
Before step S200, the method may include:
and sequentially carrying out filtering processing and direct-current component removal processing on the triaxial acceleration data sequence to obtain corresponding acceleration curve data in three axial directions.
Illustratively, the filtering process may employ a 4-order bandpass butterworth digital filter.
Taking the acceleration data sequence in the x-axis direction as an example, the direct current component removal processing can be performed on the triaxial acceleration data sequence by using the following formula:
wherein the content of the first and second substances,
acceleration number in x-axis directionFrom the series (which may be a filtered x-axis acceleration data series),
for the x-axis acceleration data sequence after the dc component is removed, N is a sampling point, N is the total number of sampling points, and N =1,2,3, … N. The formula for removing the direct current component of the acceleration data sequence in the y-axis direction and the acceleration data sequence in the z-axis direction may refer to the above formula, which is not described herein again.
According to the method for detecting the fault of the jet flow fan structural body, amplitude interference and errors in an acceleration data sequence can be removed through filtering and straightening.
In one possible embodiment, step S200 includes:
and sequentially carrying out primary integral calculation, primary curve fitting, secondary integral calculation and secondary curve fitting on the acceleration curve data in the three axial directions to obtain displacement curve data.
For example, taking the acceleration data sequence in the x-axis direction as an example, the formula of the first integral and the second integral can refer to the following formula:
wherein the content of the first and second substances,
for the data sequence in the x-axis direction after integration,
for the x-axis data sequence after removal of the dc component, p =1,2,3, … N, N being the total number of sample points,
for the sampling interval (sampling step length), the integral formula of the acceleration data sequence in the y-axis direction and the acceleration data sequence in the z-axis direction may refer to the above formula, which is not described herein again. If some constant terms exist in the acceleration data sequence, integral calculation is carried outAnd then, the constant term is changed into a slope, which affects subsequent data processing, so that the slope obtained by integrating the constant term can be removed by curve fitting to obtain corresponding curve data, and subsequent data processing is not affected.
And calculating the root mean square value of the displacement curve data to obtain a displacement time domain effective value.
Illustratively, taking the acceleration data sequence in the x-axis direction as an example, the root mean square value is calculated according to the following formula:
wherein the content of the first and second substances,
is a time domain effective value of displacement in the x-axis direction,
for x-axis plot data, for sample points, i =0,1,2,3, … N-1, N being the total number of sample points. The above formula may be referred to as a root mean square value calculation formula of the acceleration data sequence in the y-axis direction and the acceleration data sequence in the z-axis direction, which is not described herein again.
The embodiment of the application provides a jet fan structure fault detection method, adopt the displacement time domain virtual value as the time domain characteristic parameter, the displacement time domain virtual value can be numerical value with displacement curve data conversion, can directly perceivedly judge the change volume and the trend of change of numerical value, three axial displacement time domain virtual value can reflect the displacement condition of acceleration sensor unit in three axial, the displacement condition that the position that acceleration sensor unit installed takes place in three axial then can further be reflected to the displacement condition of acceleration sensor unit in three axial, thereby can reflect the jet fan or the displacement condition in three axial of the mounting structure body of corresponding position. When the displacement time domain effective value is abnormally changed or abnormally changed, the jet fan or the installation structure at the corresponding position can be judged to be abnormal or have a corresponding fault, and the corresponding position where the fault occurs or the abnormal position exists can be corresponded.
In one possible embodiment, the frequency domain characteristic parameter comprises an amplitude spectrum.
Step S300 may include:
and carrying out Fourier transform on the acceleration curve data in the three axial directions to obtain amplitude spectrums corresponding to the three axial directions.
For example, taking an acceleration data sequence in the X-axis direction as an example, the obtained complex frequency spectrum sequence of the acceleration curve data in the X-axis direction after fourier transform is assumed to be X [ K ]]Is a reaction of X [ K ]]Adapting a complex frequency spectrum to a real and imaginary component
The formula of (1) is:
wherein the content of the first and second substances,
is the real part of the signal,
is an imaginary part, k is the order of a characteristic spectral line in Fourier transform, k is more than or equal to 0 and less than or equal to N-1,
is the coefficient of the imaginary part.
The complex frequency spectrum is calculated according to
Corresponding amplitude value
：
The formula for calculating the amplitude spectra of the acceleration data sequence in the y-axis direction and the acceleration data sequence in the z-axis direction may refer to the above formula, which is not described herein again.
In a possible implementation, step S400 may be preceded by:
and (3) fusing the frequency domain characteristic parameters corresponding to the same acceleration sensor unit to obtain the proportion distribution of each frequency band energy in the total energy.
The method is characterized in that three axial amplitude spectrums corresponding to the same acceleration sensor unit are fused to obtain the proportion distribution of each frequency band amplitude in the total amplitude.
For example, taking the first acceleration sensor unit B as an example, the sum of frequency multiplication amplitudes of each order in three axial directions of the first acceleration sensor unit B is calculated according to the following formula:
wherein EX is the sum of frequency multiplication amplitudes of each order in the x-axis direction of the first acceleration sensor unit B,
is an amplitude spectrum of the x-axis direction, EY is the sum of frequency multiplication amplitude of each order of the y-axis direction of the first acceleration sensor unit B,
is an amplitude spectrum of the y-axis, EZ is the sum of frequency multiplication amplitudes of each order of the z-axis of the first acceleration sensor unit B,
the amplitude spectrum in the z-axis direction is obtained, k is the order of a characteristic spectral line in fourier transform, in this embodiment, frequency multiplication can be performed by 8, and the maximum value of k is 8.
Step S400 may include:
calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference;
and calculating the difference between the proportion distribution of the energy of each frequency band in the total energy and the normal proportion distribution to obtain the frequency domain difference.
For example, taking data collected by the first acceleration sensor unit B as an example, the energy of each frequency band may be an amplitude spectrum, and the proportion distribution of the energy of each frequency band in the total energy may be calculated according to the following formula:
wherein the content of the first and second substances,
is a normalized ratio of the sum of k-order amplitude values in the x-axis direction of the first acceleration sensor unit B,
is a normalized ratio of the sum of the k-order amplitudes in the y-axis direction of the first acceleration sensor unit B,
is a normalized ratio of the sum of the k-order amplitudes in the z-axis direction of the first acceleration sensor unit B.
According to the method for detecting the fault of the jet fan structural body, the proportion distribution of the frequency doubling amplitude sum of each order in the three axial directions of each acceleration sensor unit in the total amplitude is obtained through calculation, the proportion distribution of the frequency doubling amplitude sum of each order in the total amplitude obtained through detection is compared with the normal proportion distribution to obtain the frequency domain difference, whether the frequency domain difference exceeds the preset range or not is judged, and if the frequency domain difference exceeds the preset range, the motor bearing of the jet fan is abnormal or has failed can be indicated.
According to the fault position located by the method for detecting the fault of the jet flow fan structure, the jet flow fan structure can be directionally maintained, the maintenance efficiency is improved, the detection precision of the fault of the jet flow fan structure is improved, and the fault and the exact position of the fault can be found in time.
In a second aspect of the embodiment of the present application, a system for detecting a fault of a jet fan structural body is provided, and fig. 4 is a schematic structural block diagram of the system for detecting a fault of a jet fan structural body provided in the embodiment of the present application. As shown in fig. 4, the system for detecting a fault of a jet fan structural body provided in the embodiment of the present application includes:
the sensor array 300 is installed on a jet fan structure and used for acquiring a vibration data sequence of the jet fan in operation, wherein the jet fan structure comprises a jet fan and an installation structure for erecting the jet fan, and the sensor array comprises a plurality of acceleration sensor units;
the time domain analysis module 400 is configured to perform time domain analysis on the vibration data sequence and extract time domain characteristic parameters;
the frequency domain analysis module 500 is configured to perform frequency domain analysis on the vibration data sequence and extract frequency domain characteristic parameters;
a difference calculating module 600, configured to calculate a difference between a time domain characteristic parameter and a normal time domain characteristic value to obtain a time domain difference, and calculate a difference between a frequency domain characteristic parameter and a normal frequency domain characteristic value to obtain a frequency domain difference, where the normal time domain characteristic value is a time domain characteristic parameter when the jet fan structure normally operates, and the normal frequency domain characteristic value is a frequency domain characteristic parameter when the jet fan structure normally operates;
and the diagnosis module 700 is used for judging whether the jet fan structural body breaks down and judging the position of the fault according to the time domain difference and the frequency domain difference.
In a third aspect of the present application, fig. 5 is a schematic structural block diagram of an electronic device provided in an embodiment of the present application. As shown in fig. 5, an embodiment of the present application provides an electronic device 800, which includes at least one processor 810, and at least one memory 820 connected to the processor 810, a bus 830; the processor 810 and the memory 820 complete communication with each other through the bus 830; the processor 810 is configured to call program instructions in the memory to execute the above-described method for detecting the structural failure of the jet fan.
The electronic equipment can be a server, a PC, a PAD, a mobile phone and the like.
In a fourth aspect, an embodiment of the present application provides a storage medium, on which a program is stored, and the program, when executed by a processor, implements the above-mentioned method for detecting a fault of a jet fan structural body.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable flow management apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable flow management apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
In a typical configuration, a device includes one or more processors (CPUs), memory, and a bus. The device may also include input/output interfaces, network interfaces, and the like.
The memory may include volatile memory in a computer readable medium, Random Access Memory (RAM) and/or nonvolatile memory such as Read Only Memory (ROM) or flash memory (flash RAM), and the memory includes at least one memory chip. The memory is an example of a computer-readable medium.
Computer-readable media, including both non-transitory and non-transitory, removable and non-removable media, may implement information storage by any method or technology. The information may be computer readable instructions, data structures, modules of a program, or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), Static Random Access Memory (SRAM), Dynamic Random Access Memory (DRAM), other types of Random Access Memory (RAM), Read Only Memory (ROM), Electrically Erasable Programmable Read Only Memory (EEPROM), flash memory or other memory technology, compact disc read only memory (CD-ROM), Digital Versatile Discs (DVD) or other optical storage, magnetic cassettes, magnetic tape magnetic disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information that can be accessed by a computing device. As defined herein, a computer readable medium does not include a transitory computer readable medium such as a modulated data signal and a carrier wave.
It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in the process, method, article, or apparatus that comprises the element.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The above are merely examples of the present application and are not intended to limit the present application. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (10)
1. A method for detecting faults of a jet fan structural body is characterized by comprising the following steps:
acquiring a vibration data sequence of a jet flow fan in operation by utilizing a sensor array arranged on a jet flow fan structural body, wherein the jet flow fan structural body comprises the jet flow fan and an installation structural body for erecting the jet flow fan, and the sensor array comprises a plurality of acceleration sensor units;
performing time domain analysis on the vibration data sequence, and extracting time domain characteristic parameters;
carrying out frequency domain analysis on the vibration data sequence, and extracting frequency domain characteristic parameters;
calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, and calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the normal time domain characteristic value range is the numerical range of the time domain characteristic parameter when the jet fan structural body normally operates, and the normal frequency domain characteristic value range is the numerical range of the frequency domain characteristic parameter when the jet fan structural body normally operates;
and judging whether the jet fan structural body breaks down or not and judging the position of the fault according to the time domain difference and the frequency domain difference.
2. The method for detecting the fault of the jet fan structural body according to claim 1, wherein the mounting structural body comprises a fan body bracket and a mounting bracket, and the jet fan is arranged on the fan body bracket;
before the step of acquiring the vibration data sequence of the jet flow fan in operation by using the sensor array arranged on the jet flow fan structure body, the method comprises the following steps:
and at least one acceleration sensor unit is respectively arranged on the outer wall of the jet flow fan and the mounting bracket, wherein all the acceleration sensor units form the sensor array.
3. The method for detecting the fault of the jet flow fan structural body according to claim 2, wherein the mounting structural body further comprises an embedded steel plate, and the mounting bracket is arranged between the fan body bracket and the embedded steel plate;
before the step of acquiring the vibration data sequence of the jet flow fan in operation by using the sensor array arranged on the jet flow fan structure, the method further comprises the following steps:
and installing the acceleration sensor unit on the embedded steel plate.
4. The method for detecting the fault of the jet flow fan structural body according to claim 2 or 3, wherein the acceleration sensor unit comprises a three-axis acceleration sensor, the vibration data sequence comprises a three-axis acceleration data sequence, and the time domain characteristic parameter comprises a displacement time domain effective value;
before the step of performing time domain analysis on the vibration data sequence and extracting time domain characteristic parameters, the method comprises the following steps of:
and sequentially carrying out filtering processing and direct-current component removal processing on the triaxial acceleration data sequence to obtain corresponding acceleration curve data in three axial directions.
5. The method for detecting the structural fault of the jet flow fan according to claim 4, wherein the step of performing time domain analysis on the vibration data sequence and extracting time domain characteristic parameters comprises the following steps:
sequentially carrying out primary integral calculation, primary curve fitting, secondary integral calculation and secondary curve fitting on the acceleration curve data in the three axial directions to obtain displacement curve data;
and calculating the root mean square value of the displacement curve data to obtain the displacement time domain effective value.
6. The method of detecting a fault in a jet fan structure of claim 4, wherein the frequency domain characteristic parameters include an amplitude spectrum;
the step of performing frequency domain analysis on the vibration data sequence and extracting frequency domain characteristic parameters comprises the following steps:
and carrying out Fourier transform on the acceleration curve data in the three axial directions to obtain the amplitude spectrums corresponding to the three axial directions.
7. The method for detecting the structural fault of the jet flow fan according to claim 1, wherein the step of calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain the time domain difference, and the step of calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain the frequency domain difference comprises the following steps of:
fusing the frequency domain characteristic parameters corresponding to the same acceleration sensor unit to obtain the proportion distribution of energy of each frequency band in the total energy;
calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, and calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the step of calculating the difference comprises the following steps:
calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain the time domain difference;
and calculating the difference between the proportion distribution of the energy of each frequency band in the total energy and the normal proportion distribution to obtain the frequency domain difference.
8. A jet fan structure fault detection system, characterized by includes:
the sensor array is arranged on the jet flow fan structural body and used for acquiring a vibration data sequence of the jet flow fan in operation, wherein the jet flow fan structural body comprises a jet flow fan and an installation structural body for erecting the jet flow fan, and the sensor array comprises a plurality of acceleration sensor units;
the time domain analysis module is used for carrying out time domain analysis on the vibration data sequence and extracting time domain characteristic parameters;
the frequency domain analysis module is used for carrying out frequency domain analysis on the vibration data sequence and extracting frequency domain characteristic parameters;
the difference calculation module is used for calculating the difference between the numerical range of the time domain characteristic parameter and the normal time domain characteristic value range to obtain a time domain difference, and calculating the difference between the numerical range of the frequency domain characteristic parameter and the normal frequency domain characteristic value range to obtain a frequency domain difference, wherein the normal time domain characteristic value range is the numerical range of the time domain characteristic parameter when the jet fan structural body normally operates, and the normal frequency domain characteristic value range is the numerical range of the frequency domain characteristic parameter when the jet fan structural body normally operates;
and the diagnosis module is used for judging whether the jet fan structural body breaks down or not and judging the position of the fault according to the time domain difference and the frequency domain difference.
9. An electronic device comprising at least one processor, and at least one memory, bus connected to the processor; the processor and the memory complete mutual communication through the bus; the processor is used for calling the program instructions in the memory and executing the steps of the method for detecting the fault of the jet flow fan structural body according to any one of claims 1-7.
10. A storage medium comprising a stored program, wherein the program, when executed, controls a device on which the storage medium is located to perform the steps of the method for detecting a fault in a jet fan structure according to any one of claims 1 to 7.
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