CN116818343A - Non-intervention type aeroengine state monitoring system and implementation method - Google Patents
Non-intervention type aeroengine state monitoring system and implementation method Download PDFInfo
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Abstract
The invention provides a non-invasive aeroengine state monitoring system and an implementation method. The whole system comprises an electric field sensor, a tail gas electric field sensing device, a signal acquisition device and a computer. The tail gas electric field induction device is provided with an electric field sensor to obtain the charge quantity of the tail gas, and sends the measured data to a computer through a signal acquisition device, so that signal processing, analysis and display are completed in the computer. The state sensing of the aero-engine adopts a mode of measuring electric field values around charged particles in tail gas, the analysis mode adopts a total electric charge amount estimation method in a closed space based on Gaussian theorem, the electric charge amount of the charged particles in the tail gas is estimated based on the measured electric field, and the corresponding relation between the electric charge amount of the tail gas and the working state of the aero-engine is obtained by utilizing a data mining technology, so that the working state of the aero-engine is monitored, and the system is high in accuracy, easy to realize and low in cost.
Description
Technical Field
The invention belongs to the field of aeroengine state monitoring and fault diagnosis, and particularly relates to a non-intrusive aeroengine state monitoring system and an implementation method thereof.
Background
The perception and acquisition of the working state of the engine are important means for monitoring the state of the engine, and are also important detection means for monitoring faults in the running process of the engine, diagnosing defects of the engine design and the like. The traditional engine state work sensing means such as based on blade vibration, gas path parameters and a gas path thermodynamic model often need to be deteriorated to a certain degree to monitor corresponding changes, and the problems of limited sensor installation, difficult signal positioning and the like inherent to the technologies also exist for a long time.
When the aircraft engine is in a working state, tail gas particles can carry a certain amount of charges under the actions of contact, adsorption, atomic ionization, combustion chamber chemical reaction and the like. The exhaust gases of aircraft engines in a healthy state mainly contain soot particles, which are the result of soot formation in the main combustion zone and subsequent oxidation in the high temperature zone, which exhaust particles are of small charge, high number and relatively uniform distribution. When the performance of the engine is declined or fails, such as vane abrasion, abrasion failure of gas circuit components of the engine or aging problem of the components reaching the service life, the tail gas contains abnormal solid particles, and the abnormal particles have large charge quantity, small quantity and sparse distribution. In addition, as the fault worsens, the charge of the abnormal particles gradually increases with the degree of the fault, so that the working state of the aeroengine can be monitored by sensing the charge of the charged particles in the tail gas of the aeroengine.
The aeroengine state monitoring technology based on the tail gas charged particles is a passive measurement method and has the advantages of good linearity, strong robustness, low cost and the like. The existing aeroengine tail gas static monitoring method comprises a contact type static sensing method and an induction type static sensing method, wherein the contact type static sensing method is generally completed by arranging a large number of probes, a charge signal at the center of a pipeline is sensitive, but a probe goes deep into a flow field to cause certain interference to an electrostatic field, so that measurement errors are caused. The induction type electrostatic sensor is not in direct contact with charged particles, but is insensitive to the charged particles in a central area, so that a new measurement system for the charged quantity of tail gas of the aero-engine is urgently needed to be developed, and a new means is provided for monitoring the operation faults of the aero-engine.
Disclosure of Invention
In order to overcome the problems in the prior art, the invention discloses a non-intrusive aeroengine state monitoring system and an implementation method thereof, and provides a method for estimating total charge quantity in a closed space based on a Gaussian theorem. The invention aims to monitor the state of an aeroengine by sensing the charge quantity of charged particles in tail gas of the aeroengine.
In order to achieve the above purpose, the present invention adopts the following technical scheme: the non-intervention type aeroengine state monitoring system comprises a tail gas electric field sensing device, a multi-path electric field sensor, a data acquisition module and a computer; the method is realized by calculating the real-time charged particle charge quantity in the tail gas electric field induction device according to the arrangement rule of a plurality of electric field sensors on the tail gas electric field induction device and a total charge quantity estimation method in a closed space based on Gaussian theorem, and then obtaining the working state of the aero-engine according to the relationship between the charge quantity of the tail gas of the aero-engine and the working state of the aero-engine.
The tail gas electric field induction device is arranged in the vicinity of the tail nozzle of the engine, so that tail gas flows through the center of the tail gas electric field induction device, and the electric field sensor is arranged inside the tail gas electric field induction device. Because the tail gas is sprayed out to contain soot particles and has certain diffusion, a horn-shaped appearance structure is selected so as to avoid influencing the movement of the tail gas particles. The radius design of the front bottom surface of the tail gas induction device needs to consider the influence of the air flow temperature, and meets the requirement of the working temperature of the sensor. The length design of the tail gas induction device needs to consider the processing difficulty and the system precision; every m electric field sensors are uniformly distributed to form a sensing plane array, and each sensing plane array is fixed along the tail gas sensing device at intervals of h meters.
The multichannel electric field sensor is installed in tail gas induction system's specific point position: and a space rectangular coordinate system is established at the center of the front bottom surface of the tail gas electric field sensing device, a z-axis points to the rear bottom surface, and an XOY section with a z-coordinate interval of h meters is selected from the front bottom surface to the rear bottom surface of the tail gas sensing device as an electric field sensing plane to arrange an electric field sensor. The electric field sensors with the same characteristics are equally divided into a plurality of groups, each group comprises m electric field sensors, and the m electric field sensors are evenly distributed on m points of a circular surface along the edge of the section. Each group of sensors is fixed on the tail gas electric field induction device in a back-mounted mode. The electric field sensor uses a non-contact electric field sensor, and has stronger applicability.
The signal acquisition module comprises an acquisition card and an acquisition card using a plurality of channels, so that the signal acquisition requirement of the multipath electric field sensor can be met, the acquisition card is required to have higher frequency, and each channel can synchronously output the electric field sensor signals acquired in real time to a computer so as to complete the signal acquisition with high precision and high speed.
The computer comprises a data processing and storing module, a charge quantity soft measuring module and a display module. The data processing and storage module receives data of the high-speed signal acquisition module, the charge quantity soft measurement module performs signal conversion according to the total charge quantity estimation method in the closed space based on the Gaussian theorem, the acquired electric field data are converted into required charge quantity data, and the display module displays the calculated charge quantity data and the electric field data.
The soft charge quantity measuring module is a method for estimating total charge quantity in a closed space based on a Gaussian theorem, and according to the arrangement characteristics of 24 electric field sensors, an exhaust electric field sensing device is used as a closed curved surface, and the charge quantity in the whole closed curved surface is accurately and efficiently estimated through a space electric field value of a limit point measured by an electric field sensor array, and the method comprises the following steps:
step one, introducing electric field signals of a real-time electric field sensing array on a tail gas sensing device;
and step two, taking the tail gas sensing device as a closed curved surface, and splitting the tail gas sensing device into a circular surface S1 with the radius R of the front bottom surface, a side fan ring surface S2 and a circular surface S3 with the radius R of the rear bottom surface, as shown in fig. 4. S1 and S2 can be obtained by multiplying the average value of the in-plane electric field sensor by its area. The fan ring S2 can be divided into n small fan rings according to the number of layers of the sensor plane array, each small fan ring can be divided into m small areas according to the number of sensors contained in each electric field sensing plane, and the electric field value of each small area is approximated by the electric field average value of the step one at the vertex position of the small area.
Thirdly, based on the Gaussian theorem, the electric flux of any closed curved surface is equal to algebraic sum of electric charge quantity in the closed curved surface divided by vacuum dielectric constant epsilon 0 Therefore, area integration of the electric field value is performed for each small region. Finally, accumulating the electric flux of each part to obtain the total electric flux of the whole trumpet-shaped closed curved surface, and combining the total electric flux with epsilon 0 The amount of charge in the closed curved surface can be calculated by multiplication.
In the method for estimating the total charge in the closed space based on the gaussian theorem, the load in the tail gas induction device is calculated based on the gaussian theorem in the third step, and the method specifically comprises the following steps:
wherein ψ is E The electric flux on the closed curved surface of the tail gas induction device is represented by S1, S3, S2, E, and S2, wherein S1 represents the horn-shaped front bottom surface, S3 represents the horn-shaped rear bottom surface, and S2 represents the horn-shaped side surface k Representing the electric field mean value for each small region.
Wherein, the liquid crystal display device comprises a liquid crystal display device,indicating the electric charge quantity epsilon in the closed curved surface of the tail gas sensing device 0 Is vacuum dielectric constant.
In addition, the invention also provides a monitoring method based on the system, which comprises the following steps:
step one, placing the monitoring system around an aircraft engine tail nozzle so that tail gas can flow through a tail gas sensing device;
step two, testing is carried out in 5 stages of normal engine operation respectively, wherein the testing comprises that the main engine is slowly accelerated to 10% of the highest rotating speed under the driving of the auxiliary engine, the engine is started in an ignition way, the rotating speed is rapidly increased to the maximum value, the rotating speed of the engine is slowly reduced, the engine is gradually accelerated again, and the rotating speed of the engine is slowly reduced until the engine is stable;
calculating the electric charge quantity in the tail gas induction device by using the electric field value measured by the electric field sensing array based on the electric charge quantity soft measurement method, and measuring the standard electric charge quantity of the tail gas when the state of the engine changes;
and step four, analyzing the deviation value of the charge quantity of the tail gas charged particles and the standard charge quantity when the engine runs, so as to realize the monitoring of the state of the aeroengine, and specifically comprises the following steps: if the deviation value exceeds a certain threshold value, judging that the engine is in a fault state; if the deviation value is within the threshold value, the engine is judged to be in a certain normal operation stage.
Compared with the prior art, the invention has the following remarkable effects:
the invention provides a non-intervention type aeroengine state sensing and monitoring mode, and provides a brand new mode for aeroengine fault diagnosis. Compared with the traditional monitoring method, the method disclosed by the invention has the advantages that the state of the aero-engine is indirectly measured based on the tail gas of the aero-engine, and the real-time performance is realized;
according to the invention, the electric field value of the tail gas is measured through the electric field sensing array to estimate the electric charge quantity of the charged particles of the tail gas, so that the state of the aero-engine is measured, the cost is low, and the measurement accuracy is high;
the tail gas electric field sensing device provided by the invention enables the electric field sensing array to be arranged outside the aeroengine, and the engine or the test run environment does not need to be modified, so that the tail gas electric field sensing device is easy to realize from the engineering perspective, meanwhile, the electric field sensor is arranged along the tail gas electric field sensing device, so that the high temperature of tail gas can be avoided, the requirements on the sensor are lower, and the cost of the required sensor is lower.
The method for estimating the total charge quantity in the closed space based on the Gaussian theorem is high in applicability, suitable for calculating the charge quantity of charged particles in the tail gas electric field sensing device, and small in measurement error.
The invention is described in further detail below with reference to the attached drawings and detailed description:
drawings
FIG. 1 is a schematic diagram of a non-intrusive aircraft engine condition monitoring system based on tail gas charged particle soft measurement;
FIG. 2 is a schematic diagram of the system operation of the present invention;
FIG. 3 is a flow chart of a data acquisition procedure in the present invention;
FIG. 4 is a graph of the error of estimating the charge amount of the charged particles in the exhaust gas according to the embodiment;
FIG. 5 is a schematic diagram of a computer display module according to the present invention;
fig. 6 is a schematic diagram of a method for estimating total charge in an enclosed space based on gaussian theorem in the present invention.
Wherein, 1-electric field sensor, 2-tail gas electric field induction device, 3-data acquisition card, 4-computer, 5-tail gas spray pipe, 6-menu bar, 7-each electric field sensor value display area, 8-charged particle point cloud display area, 9-electric field sensor curve display area, 10-tail gas charged particle charge quantity curve display area
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
The invention relates to a non-invasive aeroengine state monitoring system, as shown in figure 1, which comprises the following parts: the device comprises an electric field sensor 1, a tail gas induction device 2, a data acquisition card 3 and a computer 4. The tail gas electric field sensing device comprises a tail gas sensing device, a data acquisition card, a computer, a charge soft measurement algorithm and a software development device, wherein each 8 electric field sensors form an electric field sensing plane array for acquiring electric field signals, the tail gas electric field sensing device is of a structure for carrying the fixed electric field sensors, the radius of the front bottom surface is preferably 1 meter, the horn-shaped angle is 8 degrees, each electric field plane array is uniformly arranged along the tail gas sensing device, three layers are preferably arranged, each layer comprises 8 electric field sensors, the tail gas sensors are arranged along the edge of the tail gas sensing device, the data acquisition card is connected with all the sensors, the values of the sensors are processed and stored, the processed electric field data are output to the computer, the electric field data are stored on the computer, the electric field data are converted into required charge values by the charge soft measurement algorithm, and finally the charge quantity and the corresponding electric field values are displayed by the developed software.
As shown in fig. 2, the overall operation of the system is schematically illustrated. The tail gas electric field induction device is placed behind the tail gas spray pipe, the cross section of the tail gas spray pipe is in the same plane as the cross section of the tail gas induction device, and the perpendicular bisectors of the two planes are consistent, so that the tail gas flow flows through the center of the tail gas induction device. When the tail gas flows through the tail gas electric field induction device, the electric field around changes due to charged particles of the tail gas, the electric field sensor signal continuously changes, the signal acquisition module acquires the signal of the electric field sensor and outputs the real-time electric field signal to the computer, and soft measurement and display of the electric charge quantity are completed in the computer.
Fig. 3 is a flow chart of the data acquisition procedure of the present invention. In order to realize the acquisition program, the acquisition program of the acquisition card is packaged into a dynamic link library, and the acquisition function is realized by transmitting corresponding parameters to a Dynamic Link Library (DLL) interface. Specifically, after the manual acquisition is clicked, parameters are transmitted to the DLL by utilizing a function interface according to the set parameters such as the sampling rate and the like, and an array with corresponding length is newly built for storing data. And after the data acquisition card finishes acquisition, storing the obtained electric field value data in an array. Because the acquisition time of each acquisition channel is not completely synchronous, the synchronous output participates in calculation when the data in the set array reaches the set quantity, so that the synchronization of the data is realized.
Fig. 4 is a schematic diagram of a method for estimating total charge in an enclosed space based on gaussian theorem according to the present invention. In order to accurately and efficiently estimate the electric flux of the whole closed curved surface by the space electric field value of the limited point measured by the electric field sensor array. Therefore, the closed curved surface is divided into a plurality of small regions, and the area integration of the electric field value is performed for each small region, thereby obtaining the electric flux of each region. And finally, accumulating the electric fluxes of all the areas to obtain the total electric flux on the whole closed curved surface. Taking a horn-shaped closed curved surface as an example, the closed curved surface can be split into a front bottom circular surface S1, a side fan ring surface S2 and a rear bottom circular surface S3. S1 and S2 can be obtained by multiplying the average value of the in-plane electric field sensor by its area. The sector ring S2 can be divided into 3 small sector rings according to the layer number of the sensor plane array, each small sector ring can be divided into 8 small areas according to the electric field sensor plane of each layer, and the electric field value of each small area is approximated by the electric field average value of 4 vertexes of the area. The area integration of the electric field value is performed for each small region. And finally, accumulating the electric fluxes of all the parts to obtain the total electric flux of the whole horn-shaped closed curved surface, and multiplying the total electric flux by the vacuum dielectric constant to calculate the electric charge in the closed curved surface.
As shown in fig. 5, the page structure of the display module is shown, the software page includes five parts, and the menu bar can import some configuration and data to set the acquisition card; the upper left part is a data column for displaying the real-time electric field value of each path of the acquisition card; the lower left three-dimensional stereogram shows a real-time electric field point cloud image of the electric field sensing array; the two columns on the right side are two-dimensional waveform diagram display areas, the upper right area displays the fluctuation of the electric field value of the sensor array along with the change of time, and the lower right area displays the real-time waveform diagram of the electric charge quantity obtained by the soft measurement method.
As shown in fig. 6, which shows measurement errors of a soft measurement method for tail gas charged particles in particles, three charged particles with known charge amounts are placed at any position on the middle cross section of a tail gas sensing device, the charge amounts of the charged particles are measured by using the system, the relative error between the estimated charge amounts of the charged particles and the actual charge amounts is calculated, and a graph of the relative error and the distance between the positions of the charged particles and the center of the cross section is drawn. The accuracy of the total charge amount estimation method in the closed space based on the Gaussian theorem is irrelevant to the charge amount, and the method is effective in verification; the maximum value of the measurement error of the estimated charge amount is 26.15%, and the accuracy of the charge amount estimated based on the gaussian theorem, which is 11.80%, is related to the charge position, and is higher as the distance from the center is closer, that is, as the distance from the sensor of the monitoring plane is farther.
While the applicant has described the embodiments of the present invention in detail and with reference to the drawings, it should be understood by those skilled in the art that the above examples are only preferred embodiments of the present invention, and the detailed description is only for the purpose of helping the reader to better understand the spirit of the present invention, and not to limit the scope of the present invention, but any improvements or modifications based on the spirit of the present invention should fall within the scope of the present invention.
Claims (7)
1. A non-intrusive aeroengine state monitoring system and an implementation method thereof are characterized in that:
the non-intrusive aeroengine state monitoring system consists of four parts, namely an electric field sensor, a tail gas electric field sensing device, a signal acquisition device and a computer; the tail gas electric field induction device is a bracket for fixing the arrangement position of an electric field sensor, the electric field sensor is used as a sensing unit to measure the electric field value of a certain position, a plurality of electric field sensors form a plane array, and the electric field sensing plane array is arranged along the tail gas electric field induction device; the tail gas is sprayed out from the tail gas spray pipe and flows through the tail gas sensing device, the electric field sensor senses an electric field value at a position near the tail gas, the electric field value is sent to the computer through the signal acquisition device to be subjected to data processing, the real-time charged particle charge quantity in the tail gas electric field sensing device is estimated based on a total charge quantity estimation method in a closed space based on the Gaussian theorem, and the corresponding relation between the tail gas charge quantity and the working state of the aeroengine is obtained by utilizing a data mining technology, so that the working state of the aeroengine is monitored.
2. The electric field sensor of claim 1, wherein:
the electric field sensor is a non-contact electric field sensor, is arranged on the tail gas electric field sensing device, has the characteristics of small volume, low power consumption and high reliability, and can measure the electric field value at a certain position in a non-contact mode.
3. The exhaust gas electric field sensing device of claim 1, wherein:
the tail gas electric field induction device is used for fixing the position of the electric field sensor, the appearance of the tail gas electric field induction device is horn-shaped, charged particles of tail gas air flow cannot interfere the sensor, the temperature of the tail gas air flow is high, and the electric field sensor is arranged on the tail gas electric field induction device, so that the high temperature of tail gas can be avoided, and the tail gas electric field induction device works normally; the electric field sensor forms an electric field sensing plane array along the tail gas induction device, so that the field intensity of a plurality of position points on the tail gas electric field induction device can be obtained, and the charged particle charge quantity in the tail gas electric field induction device can be reduced with higher precision and lower cost.
4. The signal acquisition device of claim 1, wherein:
the signal acquisition device is a signal acquisition card and is provided with a plurality of channels, each channel is connected with an electric field sensor, the signal output end is connected with a computer, and the values of the electric field sensors of the channels are synchronously output to the computer for processing through an acquisition program. In order to realize the acquisition program, the acquisition program of the acquisition card is packaged into a dynamic link library, and the acquisition function is realized by transmitting corresponding parameters to a Dynamic Link Library (DLL) interface; specifically, after manual collection is clicked, parameters are transmitted to the DLL by utilizing a function interface according to the set parameters such as sampling rate and the like, an array with corresponding length is newly built for storing data, the obtained electric field value data are stored in the array after the data collection card is used for collection, and as the collection time of each collection channel is not completely synchronous, the data in the array are synchronously output to participate in calculation when reaching the set quantity, so that the synchronization of the data is realized.
5. A computer as claimed in claim 1, wherein:
the computer comprises a data processing module, a charge quantity soft measurement module and a software display module; the data processing module can store signals of electric field signals of the signal acquisition device, the electric field value measured by the electric field value measuring module is converted into the electric quantity of charged particles in the tail gas electric field sensing device by the total electric quantity estimating method in the closed space based on the Gaussian theorem, and the software display module displays the electric field value and the electric quantity by using developed software.
6. The method for estimating the total charge amount in the closed space based on the gaussian theorem according to claim 1, characterized in that:
when the non-intrusive aeroengine state monitoring system works, the tail gas electric field sensing device is used as a closed curved surface, the whole closed curved surface is divided into a plurality of small areas due to different electric field signals at any point on the closed curved surface, the average value of the electric field signals at the limited position of the edge of the tail gas electric field sensing device collected by the system is used as the electric field value of the small areas on each small area, then the area integration is carried out to obtain the electric flux of the small areas, finally the electric flux of the whole closed curved surface is obtained through accumulation, and the charged particle charge quantity in the whole closed curved surface is estimated through calculation of the Gaussian theorem.
7. The software display module of claim 5, wherein:
the page of the software display module comprises five parts, and a menu bar can import some configurations and data to set the acquisition card; the upper left part is a data column for displaying the real-time electric field value of each path of the acquisition card; the lower left three-dimensional stereogram shows a real-time electric field point cloud image of the electric field sensing array; the two columns on the right side are two-dimensional waveform diagram display areas, the upper right area displays the fluctuation of the electric field value of the sensor array along with the change of time, and the lower right area displays the real-time waveform diagram of the electric charge quantity obtained by the soft measurement method.
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