CN101216372A - Aerial engine air passage electrostatic monitoring system and analog experiment apparatus - Google Patents
Aerial engine air passage electrostatic monitoring system and analog experiment apparatus Download PDFInfo
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- CN101216372A CN101216372A CNA2008100191022A CN200810019102A CN101216372A CN 101216372 A CN101216372 A CN 101216372A CN A2008100191022 A CNA2008100191022 A CN A2008100191022A CN 200810019102 A CN200810019102 A CN 200810019102A CN 101216372 A CN101216372 A CN 101216372A
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Abstract
A gas-path electrostatic monitor system of an aero-engine and a simulation test device belong to the field of gas-path stage monitor and fault diagnosis of the aero-engine. The monitor system comprises an electrostatic sensor, a signal conditioning circuit, a signal collection card and a computer. The simulation test device comprises a fuel oil burner (1), an electrostatic duster, the gas-path electrostatic monitor system, a flange (3), a first pipe (4), a rub-impact device (5), a second pipe (6), a third pipe (8), an exhaust pipe (9), an axial fan (10), a medium-pressure fan (11), a rub-impact device support platform (12) and a bracket (13). The invention can monitor the state of the engine and provide fault alarm information by monitoring the general electrostatic charge level of the gas path of the engine by the electrostatic monitor arranged at the nozzle at the tail portion of the engine. The constructed simulation test device simulates the gas-path operation state of the engine and the direct results of normal faults, thus providing a simulation test platform for early study of gas-path electrostatic monitor system of the aero-engine.
Description
Technical field
The present invention is by the variation of monitoring aerial engine air passage total charge level, come the duty of aerial engine air passage parts is carried out real time and on line monitoring with this, for engine air circuit unit initial failure provides early warning information, improve the health status managerial ability of engine.The test unit that makes up is used for the gas circuit environment of aeromotor jet pipe is simulated, and utilizes electroduster, blower fan, pipeline and test macro to carry out simulated experiment under normal temperature, the high temperature.Belong to aeromotor condition monitoring and fault diagnosis field.
Background technology
In this complicated mechanical system of aeromotor, gas path component is owing to its bad working environment becomes the main generation source of fault, and the duty how research monitors the engine air circuit unit is a complex engineering that relates to different subjects such as aerodynamics, thermodynamics, mechanics, fluid mechanics, chemistry.At present, about the gas circuit monitoring, diagnosing, different according to its monitoring principle, method and monitoring target, can be divided into three major types, that is: based on the condition diagnosing technology of gas circuit parameter and gas circuit thermodynamical model, be mainly used to solve the supervision and the diagnosis problem of engine complete machine performance state; Based on the fault diagnosis technology of inner method of detection, be mainly used to solve engine air passage parts status detection forecasting problem; Based on the fault diagnosis technology of vibration monitoring, be mainly used to solve engine air passage change quiet bump rub, faults such as rotor and other rotary part imbalance, the distortion of rotor permanent bend; The method of these three kinds of fault diagnosises all needs to deteriorate in fault and causes that to a certain degree the assembly geometric parameter Shi Caineng that changes detects the existence of fault, all is difficult to the needs that satisfy real time on-line monitoring and early warning information is provided.
Summary of the invention
The present invention is directed to existing monitoring technology and be difficult to realize on-line real time monitoring, and the weak point of early warning information can not be provided in early days in fault, proposed a kind of aeromotor on-line monitoring system based on the air passage electrostatic monitoring.This system to realizing engine air circuit unit duty monitors by the variation of the electrostatic field of electrically charged particle generation in the electrostatic transducer monitoring engine air passage.As long as there is particle to produce, just can monitor at the fault commitment it, the early warning of gas path failure is provided.Employing can realize on-line monitoring easily based on the monitoring system of gas circuit particle static, the diagnosing malfunction (as the fault of firing chamber) that easily conventional method is difficult for detection, for bumping of engine air circuit unit rub, wear and tear, corrode, the burn real time on-line monitoring and the diagnosis of class fault, a kind of brand-new theoretical method and technological means are provided.
The generation reason of electrically charged particle thing: mainly comprise carbon dioxide, oxides of nitrogen, water vapor, hydrocarbon, carbon monoxide, oxysulfide and molecule after the aeroengine combustor buring in the emission product.In the particle that aeromotor tail gas contains, the soot particle accounts for significant proportion.When rich oil or burning performance decline, all can produce a large amount of soot particles, except that the soot particle that normal combustion produces, exotic, the part, blade exhaust limit that air intake duct sucks occurs that TRANSIENT HIGH TEMPERATURE causes that blade is ablated, the blade part under hot environment, be subjected to cyclic stress cause material lose and blade and casing, O-ring seal between bump that to rub all be the possible source of particle in the tail gas.
Indoor at engine combustion, because high temperature causes gas ionization, produces a large amount of charged ions, when the particle that forms in the rich oil district is through the thermal-flame district and thermal ionization the reaction free electron, the ionic interaction that form, the formation electrically charged particle; The particle of the formation such as collision between particle and the tube wall is charged in addition also is partly cause.
The present invention is based on the principle of electrostatic induction: in the time of an electrically charged particle process electrostatic transducer surface, the electronics of sensor internal can redistribute under the effect of electric field force, the field intensity that is produced when the additional field intensity and the outside electrically charged particle of sensor sensing charge generation close field intensity when being zero, conductor comprises that its surface does not have the orientation of electric charge to move, and promptly reaches the electrostatic equilibrium state.When the electrically charged particle that contains in the tail gas away from the electrostatic transducer surface time, it is zero that the induced charge that sensor surface produces returns again, and sensor internal comes back to the electrobalance state.Electrically charged particle near and process away from sensor surface in, caused the orientation of electronics in the sensor to move, thereby formed induction current.
Monitoring technology principle based on gas circuit particle static: when engine is in normal condition following time, particle in its tail gas is mainly carbon soot particles, centralized particle diameter is in 5～7nm and two zones of 20～30nm, and the overall static charge level of gas circuit remains on a metastable level, and when the engine air passage component capabilities fails or breaks down, can produce a large amount of abnormal grains, these abnormal grain particle diameters are all bigger, usually more than 40um, because particle is big more, institute's carrying capacity is also just big more, produces just because of extra bulky grain to cause the overall static charge level of gas circuit to change.Engine air passage particle electrostatic monitoring system based on the electrostatic induction principle design, monitor the variation of engine air passage electrostatic lotus level just in real time, this variation has reflected the variation of abnormal grain content in the engine air passage, thereby the duty that has reflected gas path component realizes engine air passage is carried out the purpose of on-line monitoring with this.
Aerial engine air passage electrostatic monitoring system of the present invention comprises electrostatic transducer, signal conditioning circuit, data acquisition card, computing machine.Wherein sensor is installed in the jet pipe of aeromotor, and the output that the output that is connected in input, the signal conditioning circuit of signal conditioning circuit by induced signal is connected in the input of data acquisition card, data acquisition card links to each other with computing machine.The variation of static charge will show by the variation of sensor sensing electric current, through signal conditioning circuit signal is carried out amplification filtering and handles, then by computer data acquisition and analyze.
Whole monitoring system wants to realize airborneization, must carry out engine rig test electrostatic transducer and test macro are carried out performance verification, yet carry out bench test drive test and have following problem: (1) test need be with reference to the engine operate as normal and the signal when breaking down, therefore need carry out the simulation of various faults to engine, because the price of engine own is high, can not carry out destructive test, and testing expenses are very high.(2) general unit lacks the experiment porch of engine testsand, is difficult to do the fault simulation test of this big machinery.
In order to overcome present simulated engine gas circuit particle electrostatic monitoring problem of environment, the invention provides a kind of aerial engine air passage particle electrostatic monitoring environmental experiment analogue means, this device can be used for carrying out the experiment of engine air passage particle electrostatic monitoring system research.Use stainless steel metal pipeline simulated engine gas circuit environment, charged particle in the electrostatic dusting device simulation gas circuit, bump with rotating vane and tube wall and to rub, utilize Middle pressure draught fan and axial fan simulation high velocity air and provide air for oil inflame with rub fault and produce abrasive particle of bumping of blade in the simulated engine.
The related engine air passage electrostatic monitoring system simulation test device of experimental technique comprises: oil burner, electroduster, air passage electrostatic monitoring system, ring flange, the 1st pipeline, bump the device that rubs, the 2nd pipeline, the 3rd pipeline, gas outlet, axial fan, Middle pressure draught fan, bump the device brace table that rubs, and support.Wherein oil burner links to each other with the 1st pipeline by ring flange, electroduster is installed on the ring flange by the mouth that dusts on the ring flange and communicates with the 1st pipeline, bumping the device that rubs is installed on the 1st pipeline, support by bumping the brace table that rubs, the 1st pipeline, the 2nd pipeline, the 3rd pipeline, gas outlet fuses mutually by flange successively, and place on the support, the 2nd pipeline and the 3rd pipeline link to each other with electrostatic transducer in the air passage electrostatic monitoring system by the electrostatic transducer interface respectively, the axial fan that is used for exhaust places the endpiece of gas outlet, and Middle pressure draught fan is connected in ring flange by ventilation duct fans entrance communicates with the 1st pipeline.
Described electrostatic transducer comprises electrostatic transducer shell and electrostatic transducer probe, the electrostatic transducer shell fuses by insulating material and electrostatic transducer probe, in the jet pipe of electrostatic transducer probe insertion aeromotor or in the 2nd pipeline or in the 3rd pipeline.
The described device that rubs that bumps comprises the 1st, the 2nd, motor, bearing seat, connection cord, bumps mount knob, bumps the blade that rubs.Wherein the 1st links to each other with the output shaft of motor, and be installed on two bearing seats, the 1st end links to each other with the 2nd flexibility by connection cord, and the 2nd other end links to each other with the blade that rubs that bumps in placing the 1st pipeline, and the 2nd is installed on the 1st pipeline and inserts in the 1st pipeline by bumping mount knob.
Described electroduster comprises air compressor and podwer gun, and compressor links to each other with podwer gun, and podwer gun is installed on the ring flange in the pipe with pipeline 1 by the mouth that dusts on the ring flange and communicates.
Description of drawings
Fig. 1 is the composition frame chart of aerial engine air passage electrostatic monitoring system.
Fig. 2 is that the simulation test device of aerial engine air passage electrostatic monitoring system is formed synoptic diagram
Fig. 3 is the electrostatic transducer composition diagram.
Fig. 4 bumps the device that rubs to form synoptic diagram.
Label title among Fig. 1～Fig. 4:
1, oil burner, 2, electroduster, 3, ring flange, the 4, the 1st pipeline, 5, bump the device that rubs, the 6, the 2nd pipeline, 7, air passage electrostatic monitoring system, the 8, the 3rd pipeline, 9, gas outlet, 10, axial fan, 11, Middle pressure draught fan, 12, bump the device brace table that rubs, 13, support, 14, the electrostatic transducer shell, 15, the electrostatic transducer probe, 16, the 1st, 17, the 2nd, 18, motor, 19, bearing seat, 20, connection cord, 21, bump mount knob, 22, bump the blade that rubs.
Embodiment
Fig. 1 is the composition frame chart of aerial engine air passage electrostatic monitoring system of the present invention.It is that electrostatic transducer is installed in the jet pipe of aeromotor, the variation of the electrostatic field that electrically charged particle produces in the monitoring engine air passage, current changing signal input signal conditioning circuit by the electrostatic transducer induction, signal after signal conditioning circuit carries out the amplification filtering processing to the current signal of importing is sent into computing machine through data acquisition card acquisition data and is carried out analyzing and processing, realizes aerial engine air passage is carried out the purpose of on-line monitoring.
Fig. 2 is the composition synoptic diagram of the simulation test device of aerial engine air passage electrostatic monitoring system of the present invention.Comprise oil burner 1, electroduster 2, air passage electrostatic monitoring system 7, ring flange the 3, the 1st pipeline 4, bump device the 5, the 2nd pipeline the 6, the 3rd pipeline 8 that rubs, gas outlet 9, axial fan 10, Middle pressure draught fan 11, bump the device brace table 12 that rubs, support 13.Wherein: for the gas circuit environment of simulated engine, oil burner uses aviation kerosene to act as a fuel, adopt metal powder respectively, metallic screw is simulated the bulky grain and the super large abnormal grain of generation, oil burner provides the combustion high temperature environment and produces a large amount of carbon soot particles, its air door can be regulated, with the simulation rich oil, oil-poor different combustion positions, adopt electroduster charged by particle, its concentration of dusting can be regulated, to simulate the charged particle substrate concentration respectively, compressor links to each other with podwer gun and is used for blowing out particle, and blower fan is used for simulating the generation high velocity air.Sensor interface place on tube wall is used for installing electrostatic transducer, its scheme of installation as shown in Figure 3, bump the interface that rubs and be used for doing bumping when rubbing simulated experiment and use, its motor and blade are installed as shown in Figure 4, wherein adopt the mode that flexibly connects between the 1st 16 and the 2nd 17.Because it is the same to bump the interface of rub interface and electrostatic transducer on the pipeline, can select sensor installation or bump the device that rubs according to requirement of experiment.The three-joint pipe road links to each other by flange, and order can be changed according to the experiment needs.The end of final section pipeline links to each other with gas outlet, and propeller fan is housed in gas outlet, is used for quickening air-flow.
Using method
Electrostatic dusting device, oil burner, Middle pressure draught fan and axial fan and electrostatic transducer are installed on appropriate location on the stainless steel pipes on request, and correctly connect test macro.Be ready to test required metal powder or particle, aviation kerosene, debug air compressor and electrostatic dusting device then, start Middle pressure draught fan and axial fan afterwards to obtain high velocity air, treat to start oil burner behind the steady air current, obtain thermal-flame.After treating that burning tends towards stability, can begin simulated experiment.The log-on data acquisition system can be noted the overall process signal of collection from finishing to simulated experiment before lighting a fire.
(1) at the mouth that dusts of pipeline front end, insert podwer gun and in pipeline, spray into particle, in the simulation gas circuit as suck exotic or material and lose and wait abnormal grain, and the test figure of collection overall process.
(2) can simulate by the size of regulating the oil burner air door because rich oil or chamber performance decline etc. are former thereby a large amount of carbon granules of generation.
(3) open the rotation of driven by motor blade, be rotated counterclockwise and bump mount knob, then can make and bump rub blade and tube wall and rub, simulated engine gas circuit blade and casing bump the fault of rubbing.
Characteristics of the present invention are: a kind of brand-new engine state monitor system is provided, and can be at engine Gas path component breaks down provides early warning information in early days, and the simulation test device of invention can effectively be simulated and be started Machine gas circuit environment is for the research of aerial engine air passage electrostatic monitoring system provides a cheaply effectively examination Test platform.
Claims (4)
1. aerial engine air passage electrostatic monitoring system, it is characterized in that, comprise electrostatic transducer, signal conditioning circuit, data acquisition card, computing machine, wherein electrostatic transducer is installed in the jet pipe of aeromotor, and the output that the output that is connected in input, the signal conditioning circuit of signal conditioning circuit by induced signal is connected in the input of data acquisition card, data acquisition card links to each other with computing machine.
2. the simulation test device of an aerial engine air passage electrostatic monitoring system, it is characterized in that, comprise oil burner (1), electroduster (2), air passage electrostatic monitoring system (7), ring flange (3), the 1st pipeline (4), bump the device that rubs (5), the 2nd pipeline (6), the 3rd pipeline (8), gas outlet (9), axial fan (10), Middle pressure draught fan (11), bump the device brace table (12) that rubs, and support (13), wherein oil burner (1) links to each other with the 1st pipeline (4) by ring flange (3), electroduster (2) is installed in ring flange (3) by the mouth that dusts on the ring flange (3) and upward communicates with the 1st pipeline (4), bumping the device that rubs (5) is installed on the 1st pipeline (4), support by bumping the brace table that rubs (12), the 1st pipeline (4), the 2nd pipeline (6), the 3rd pipeline (8), gas outlet (9) fuses mutually by flange successively, and place on the support (13), the 2nd pipeline (6) and the 3rd pipeline (8) link to each other with electrostatic transducer in the air passage electrostatic monitoring system (7) by the electrostatic transducer interface respectively, the axial fan (10) that is used for exhaust places the endpiece of gas outlet (9), and Middle pressure draught fan (11) is connected in ring flange (3) by ventilation duct fans entrance communicates with the 1st pipeline (4).
3. aerial engine air passage electrostatic monitoring system according to claim 1, or the simulation test device of the described aerial engine air passage electrostatic monitoring system of claim 2, it is characterized in that, described electrostatic transducer comprises electrostatic transducer shell (14) and electrostatic transducer probe (15), electrostatic transducer shell (14) fuses by insulating material and electrostatic transducer probe (15), in the jet pipe of electrostatic transducer probe insertion aeromotor or in the pipeline gas circuit of analogue experiment installation.
4. the simulation test device of aerial engine air passage electrostatic monitoring system according to claim 2, it is characterized in that, the described device that rubs (5) that bumps, comprise the 1st (16), the 2nd (17), motor (18), bearing seat (19), connection cord (20), bump mount knob (21), bump the blade that rubs (22), wherein the 1st (16) link to each other with the output shaft of motor (18), and be installed on the bearing seat (19), the 1st (16) other end links to each other by connection cord (20) and the 2nd (17) are flexible, the 2nd (17) other end links to each other with the blade that rubs that bumps in placing the 1st pipeline (4), and the 2nd (17) are by bumping mount knob (21) and be installed on the 1st pipeline (4) and inserting in the 1st pipeline (4).
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| CNB2008100191022A CN100557402C (en) | 2008-01-11 | 2008-01-11 | Aerial engine air passage electrostatic monitoring system and simulation test device |
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| CNB2008100191022A CN100557402C (en) | 2008-01-11 | 2008-01-11 | Aerial engine air passage electrostatic monitoring system and simulation test device |
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