CN105486507A - Modularized fault elimination device and method for trial test of aeroengine - Google Patents
Modularized fault elimination device and method for trial test of aeroengine Download PDFInfo
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- CN105486507A CN105486507A CN201510817541.8A CN201510817541A CN105486507A CN 105486507 A CN105486507 A CN 105486507A CN 201510817541 A CN201510817541 A CN 201510817541A CN 105486507 A CN105486507 A CN 105486507A
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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Abstract
The invention relates to a modularized fault elimination device and method for trial test of an aeroengine. The device comprises a temperature unit, a temperature scanning valve unit, a pressure unit, a pressure scanning valve unit, a frequency unit, a VXI collection cabinet and a computer, wherein the temperature unit comprises multiple temperature measurement isolation modules, the temperature scanning valve unit includes one temperature scanning valve; the pressure unit comprises multiple pressure measurement isolation modules and multiple pressure transmitters whose amount is the same with that of the pressure measurement isolation modules; the pressure scanning valve unit includes a pressure scanning valve; and the frequency unit comprises multiple frequency measurement isolation modules. According to the fault elimination method, parameters of test channels are modularized by classification units, the test channels are replaced, faults are eliminated from the test channels, the same type of test faults can be eliminated rapidly and effectively, it is ensured that the faults are eliminated in the trial test of the aeroengine, the trial test efficiency and the production efficiency of the aeroengine are improved, the quality and period of trial test of the aeroengine are ensured, the structure is flexible and convenient, and the fault elimination device and method can be popularized to certain extent.
Description
Technical field
The invention belongs to aero engine technology field, be specifically related to aeroengine test run modularization fault removal device and troubleshooting methodology thereof.
Background technology
Aeroengine test run is an extremely numerous and jumbled systems engineering, and it is all multi-specialized that it contains test run technique, observing and controlling, vibration etc.Aeroengine test run not only the cycle long, and expend huge, aeromotor ground run bad environments, test event nearly hundred kinds, very easily occur various fault in commissioning process, as vibration exceeding the standard, the fault such as data are unstable, signal is malfunctioning, failture evacuation needs to take the plenty of time, affect integral production efficiency, significantly increase test run cost.At present, ground test stand all adopts dispersion test, unification is tested by data acquisition system (DAS), once there is the failure of some or multiple signal testing, needing to take a large amount of troubleshooting time determines that the problem such as circuit, sensor, communication of certain or multiple signal solves, and affects engine production efficiency.
Summary of the invention
For the deficiencies in the prior art, the present invention proposes aeroengine test run modularization fault removal device and troubleshooting methodology thereof.
Aeroengine test run modularization fault removal device, comprises temperature unit, temperature scanning valve cell, pressure unit, pressure scanning valve cell, frequency cells, VXI collection cabinet and computing machine;
Described temperature unit comprises multiple temperature survey isolation module, described temperature scanning valve cell is a temperature scanning valve, described pressure unit comprises multiple pressure survey isolation module and the pressure unit identical with pressure survey isolation module quantity, described pressure scanning valve cell is a pressure scanning valve, and described frequency cells comprises multiple frequency measurement isolation module;
In described temperature unit, the input end of each temperature survey isolation module connects test bay aeromotor temperature sensor measuring point by the one 32 hole aviation plug, and in temperature unit, the output terminal of each temperature survey isolation module connects VXI collection cabinet by the 2 32 hole aviation plug; The input end of each passage of the temperature scanning valve in described temperature scanning valve cell connects test bay aeromotor temperature point by the 3 32 hole aviation plug, and the output terminal of the temperature scanning valve of temperature scanning valve cell connects computing machine by the first netting twine attachment plug; The input end of each pressure survey isolation module in described pressure unit connects a pressure unit respectively, the input end of each pressure unit connects test bay aeromotor pressure-measuring-point by pressure measurement flexible pipe, and in pressure unit, the output terminal of each pressure survey isolation module connects VXI collection cabinet by the 4 32 hole aviation plug; The input end of each passage of the pressure scanning valve of described pressure scanning valve cell connects test bay aeromotor pressure-measuring-point by pressure measurement flexible pipe, and the output terminal of the pressure scanning valve of pressure scanning valve cell connects computing machine by the second netting twine attachment plug; In described frequency cells, the input end of each frequency measurement isolation module connects test bay aeroplane engine unit frequency measuring point by the 5 32 hole aviation plug, and in frequency cells, the output terminal of each frequency measurement isolation module connects VXI collection cabinet by the 6 32 hole aviation plug; The output terminal that described VXI gathers cabinet connects computing machine.
Described temperature unit, for when the temperature value display of test bay aeromotor certain or multiple temperature sensor measuring point is abnormal, temperature survey isolation module in temperature unit is connected to this temperature sensor measuring point, the temperature test acquisition channel of this temperature sensor measuring point is replaced by described temperature unit, if now the temperature value display of this temperature point is normal, the then temperature test acquisition channel fault of this temperature sensor measuring point, carry out the failture evacuation of the replacing of temperature test acquisition channel, if still there is temperature value abnormal show phenomenon, the then temperature sensor fault of the temperature test acquisition channel of this temperature sensor measuring point, carry out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel,
Described temperature scanning valve cell, when temperature value display for the temperature point when test bay aeromotor certain or multiple temperature scanning valve thermometric is abnormal, by the expanding channels of the temperature scanning valve in temperature scanning valve cell to this temperature point, the temperature scanning valve test acquisition channel of this temperature point is replaced with the passage of described temperature scanning valve cell, carries out the failture evacuation of the temperature scanning valve test acquisition channel of this temperature point;
Described pressure unit, for when the force value display of test bay aeromotor certain or multiple pressure-measuring-point is abnormal, the pressure measurement flexible pipe that pressure survey isolation module in pressure unit is connected by pressure unit is connected to this pressure-measuring-point, the pressure test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure unit, carries out the failture evacuation of the pressure test acquisition channel of this pressure-measuring-point;
Described pressure scanning valve cell, when force value display for the pressure-measuring-point when test bay aeromotor certain or the pressure measurement of multiple pressure scanning valve is abnormal, the passage of the pressure scanning valve of pressure scanning valve cell is connected to this pressure-measuring-point by pressure measurement flexible pipe, the pressure scanning valve test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure scanning valve cell, carries out the failture evacuation of the pressure scanning valve test acquisition channel of this pressure-measuring-point;
Described frequency cells, for when the tachometer value of test bay aeromotor certain or multiple frequency measuring point or flow value display abnormal time, frequency measurement isolation module in frequency cells is connected to this frequency measuring point, the described frequency cells of the frequency quantity of this frequency measuring point test acquisition channel is replaced, if now frequency values or flow value display are normally, the then frequency quantity test acquisition channel fault of this frequency measuring point, carry out the normal eliminating of event of the replacing of frequency quantity test acquisition channel, if still there is tachometer value or flow value abnormal show phenomenon, then the frequency quantity of this frequency measuring point tests speed probe or the flow sensor fault of acquisition channel, carry out the failture evacuation by the frequency quantity of this frequency measuring point test speed probe of acquisition channel or the replacing of flow sensor,
Described VXI gathers cabinet, for being changed by the signal of temperature unit, pressure unit and frequency cells collection, transfers to computing machine.
This device also comprises shell, and described temperature unit, temperature scanning valve cell, pressure unit, pressure scanning valve cell and frequency cells are arranged at enclosure;
Described one 32 hole aviation plug, the 2 32 hole aviation plug, the 3 32 hole aviation plug, the 4 32 hole aviation plug, the 5 32 hole aviation plug, the 6 32 hole aviation plug, the first netting twine patchplug and the second netting twine patchplug are arranged in shell;
Described shell was also provided with ancient piece of jade, round, flat and with a hole in its centre hole, for pressure hose of transferring;
Each temperature survey isolation module described is fixed together by draw-in groove, is positioned in shell;
Described temperature scanning valve is fixed on shell by four fixing screws;
Each pressure survey isolation module described is fixed together by draw-in groove, and be positioned in shell, each pressure unit is fixed on outer casing inner wall respectively by boring;
Described pressure scanning valve is fixed on shell by four fixing screws;
Each frequency measurement isolation module described is fixed together by draw-in groove, is positioned in shell.
Described shell was also provided with ancient piece of jade, round, flat and with a hole in its centre hole, for penetrating pressure measurement flexible pipe.
Adopt aeroengine test run modularization fault removal device to carry out the method for failture evacuation, comprise the following steps:
Step 1: when the temperature value display of test bay aeromotor certain or multiple temperature sensor measuring point is abnormal, temperature-measuring module in temperature unit is connected to this temperature sensor measuring point, the temperature test acquisition channel of this temperature sensor measuring point is replaced by described temperature unit;
Step 2: judge whether the temperature value of now this temperature point shows normally, if so, perform step 3, otherwise, perform step 4;
Step 3: the temperature test acquisition channel fault of this temperature sensor measuring point, carries out the failture evacuation of the replacing of temperature test acquisition channel, performs step 5;
Step 4: the temperature sensor fault of the temperature test acquisition channel of this temperature sensor measuring point, carries out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel;
Step 5: when the temperature value display of the temperature point of test bay aeromotor certain or multiple temperature scanning valve thermometric is abnormal, by the expanding channels of the temperature scanning valve in temperature scanning valve cell to this temperature point, the temperature scanning valve test acquisition channel of this temperature point is replaced with the passage of described temperature scanning valve cell, carries out the failture evacuation of the temperature scanning valve test acquisition channel of this temperature point;
Step 6: when the force value display of test bay aeromotor certain or multiple pressure-measuring-point is abnormal, judges that whether this pressure-measuring-point is the pressure measurement point of pressure survey isolation module, if so, then performs step 7, otherwise, perform step 8;
Step 7: the pressure measurement flexible pipe that the pressure survey isolation module in pressure unit is connected by pressure unit is connected to this pressure-measuring-point, the pressure test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure unit, carry out the failture evacuation of the pressure test acquisition channel of this pressure-measuring-point, perform step 9;
Step 8: the passage of the pressure scanning valve of pressure scanning valve cell is connected to this pressure-measuring-point by pressure measurement flexible pipe, the pressure scanning valve test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure scanning valve cell, carries out the failture evacuation of the pressure scanning valve test acquisition channel of this pressure-measuring-point;
Step 9: when the tachometer value of test bay aeromotor certain or multiple frequency measuring point or flow value display abnormal time, frequency measurement isolation module in frequency cells is connected to this frequency measuring point, the described frequency cells of the frequency quantity of this frequency measuring point test acquisition channel is replaced;
Step 10: judge that now whether normally frequency values or flow value display, if so, perform step 11, otherwise, perform step 12;
Step 11: the frequency quantity test acquisition channel fault of this frequency measuring point, carries out the normal eliminating of event of the replacing of frequency quantity test acquisition channel;
Step 12: the speed probe of the frequency quantity test acquisition channel of this frequency measuring point or flow sensor fault, carries out the failture evacuation by the frequency quantity of this frequency measuring point test speed probe of acquisition channel or the replacing of flow sensor.
Beneficial effect of the present invention:
The present invention proposes aeroengine test run modularization fault removal device and troubleshooting methodology thereof, by test channel parameter is sorted out unit-modularized after the design of quick-replaceable troubleshooting, fast and effeciently get rid of same type test failure smoothly, ensure the smooth eliminating of the test failure of engine run, improve test run efficiency and the production efficiency of engine, ensure that engine run quality and cycle, flexible structure is convenient, has certain dissemination to aeroengine test run work.
Accompanying drawing explanation
Fig. 1 is the structural representation of aeroengine test run modularization fault removal device in the specific embodiment of the invention;
Fig. 2 is the annexation schematic diagram of the modules of aeroengine test run modularization fault removal device in the specific embodiment of the invention;
Wherein, 1-temperature unit, 2-temperature scanning valve cell, 3-pressure unit, 4-pressure scanning valve cell, 5-frequency cells, 6-the 1 hole aviation plug, 7-the 2 32 hole aviation plug, 8-the 3 32 hole aviation plug, 9-the 4 32 hole aviation plug, 10-the 5 32 hole aviation plug, 11-the 6 32 hole aviation plug, 12-first netting twine patchplug, 13-second netting twine patchplug, 14-shell, 15-temperature survey isolation module, 16-pressure survey isolation module, 17-frequency measurement isolation module, 18-pressure unit, 19-crosses ancient piece of jade, round, flat and with a hole in its centre hole;
Fig. 3 is the process flow diagram of this engine run modularization troubleshooting methodology of aviation in the specific embodiment of the invention.
Embodiment
Below in conjunction with accompanying drawing to specific embodiment of the invention detailed description in addition.
Aeroengine test run modularization fault removal device, as shown in Figure 1, comprises temperature unit 1, temperature scanning valve cell 2, pressure unit 3, pressure scanning valve cell 4, frequency cells 5, VXI collection cabinet and computing machine.
In present embodiment, temperature unit 1 comprises 16 temperature survey isolation modules 15, and the model of temperature survey isolation module 15 is M5TS-24-R.
In present embodiment, temperature scanning valve cell 2 is a temperature scanning valve, and the model of temperature scanning valve is DSA3250.
In present embodiment, pressure unit 3 comprises 16 pressure survey isolation modules 16 and 16 pressure units 18, and the model of pressure survey isolation module 16 is M5VS-A6-R/K, and the model of pressure unit 18 is De Luke pressure unit.
In present embodiment, pressure scanning valve cell 4 is a pressure scanning valve, and the model of pressure scanning valve is DSA3207/3217.
In present embodiment, frequency cells 5 comprises 16 frequency measurement isolation modules 17, and the model of frequency measurement isolation module 17 is TAIKELECTRICS3-VD-1-00A4C.
In present embodiment, as shown in Figure 2, each input end of 16 temperature survey isolation modules in temperature unit 1 connects test bay aeromotor temperature sensor measuring point by the one 32 hole aviation plug 6, in figure, part connecting line is only shown, the output terminal of 16 temperature survey isolation modules in temperature unit 1 connects VXI by the 2 32 hole aviation plug 7 and gathers cabinet.
The input end of each passage of the temperature scanning valve in temperature scanning valve cell 2 connects test bay aeromotor temperature point by the 3 32 hole aviation plug 8, in figure, part connecting line is only shown, the output terminal of the temperature scanning valve of temperature scanning valve cell 2 connects computing machine by the first netting twine attachment plug 12.
Each input end of 16 pressure survey isolation modules in pressure unit 3 connects a pressure unit 18 respectively, the input end of pressure unit 18 connects test bay aeromotor pressure-measuring-point by pressure measurement flexible pipe, in figure, part connecting line is only shown, in pressure unit 3, the output terminal of 16 pressure survey isolation modules connects VXI collection cabinet by the 4 32 hole aviation plug 9.
The input end of each passage of the pressure scanning valve of pressure scanning valve cell 4 connects test bay aeromotor pressure-measuring-point by pressure measurement flexible pipe, in figure, part connecting line is only shown, the output terminal of the pressure scanning valve of pressure scanning valve cell 4 connects computing machine by the second netting twine attachment plug 13.
In frequency cells 5, each input end of 16 frequency measurement isolation modules 17 connects test bay aeroplane engine unit frequency measuring point by the 5 32 hole aviation plug 10, in figure, part connecting line is only shown, in frequency cells 5, the output terminal of 16 frequency measurement isolation modules 17 connects VXI collection cabinet by the 6 32 hole aviation plug 11, and the output terminal that VXI gathers cabinet connects computing machine.
Temperature unit 1, for when the temperature value display of test bay aeromotor certain or multiple temperature sensor measuring point is abnormal, temperature survey isolation module 15 in temperature unit 1 is connected to this temperature sensor measuring point, the described temperature unit 1 of the temperature test acquisition channel of this temperature sensor measuring point is replaced, if now the temperature value display of this temperature point is normal, the then temperature test acquisition channel fault of this temperature sensor measuring point, carry out the failture evacuation of the replacing of temperature test acquisition channel, if still there is temperature value abnormal show phenomenon, the then temperature sensor fault of the temperature test acquisition channel of this temperature sensor measuring point, carry out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel.
Temperature scanning valve cell 2, when temperature value display for the temperature point when test bay aeromotor certain or multiple temperature scanning valve thermometric is abnormal, by the expanding channels of the temperature scanning valve in temperature scanning valve cell 2 to this temperature point, the temperature scanning valve test acquisition channel of this temperature point is replaced with the passage of described temperature scanning valve cell 2, carries out the failture evacuation of the temperature scanning valve test acquisition channel of this temperature point.
Pressure unit 3, for when the force value display of test bay aeromotor certain or multiple pressure-measuring-point is abnormal, the pressure measurement flexible pipe that pressure survey isolation module 16 in pressure unit 3 is connected by pressure unit 18 is connected to this pressure-measuring-point, the passage of the pressure test acquisition channel of this pressure-measuring-point with described pressure unit 3 is replaced, carries out the failture evacuation of the pressure test acquisition channel of this pressure-measuring-point.
Pressure scanning valve cell 4, when force value display for the pressure-measuring-point when test bay aeromotor certain or the pressure measurement of multiple pressure scanning valve is abnormal, the passage of the pressure scanning valve of pressure scanning valve cell 4 is connected to this pressure-measuring-point by pressure measurement flexible pipe, the pressure scanning valve test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure scanning valve cell 4, carries out the failture evacuation of the pressure scanning valve test acquisition channel of this pressure-measuring-point.
Frequency cells 5, for when the tachometer value of test bay aeromotor certain or multiple frequency measuring point or flow value display abnormal time, frequency measurement isolation module 17 in frequency cells 5 is connected to this frequency measuring point, the described frequency cells 5 of the frequency test acquisition channel of this frequency measuring point is replaced, if now frequency values or flow value display are normally, the then frequency test acquisition channel fault of this frequency measuring point, carry out the normal eliminating of event of the replacing of frequency test acquisition channel, if still there is tachometer value or flow value abnormal show phenomenon, the then speed probe of the frequency test acquisition channel of this frequency measuring point or flow sensor fault, carry out the failture evacuation of the speed probe of frequency test acquisition channel by this frequency measuring point or the replacing of flow sensor.
VXI gathers cabinet, for being changed by the signal of temperature unit, pressure unit and frequency cells collection, transfers to computing machine, and in present embodiment, the model that VXI gathers cabinet is Agilent E1421B.
This device also comprises shell 14, and it is inner that temperature unit 1, temperature scanning valve cell 2, pressure unit 3, pressure scanning valve cell 4 and frequency cells 5 are arranged at shell 14.
One 32 hole aviation plug the 6, the 2 32 hole aviation plug the 7, the 3 32 hole aviation plug the 8, the 4 32 hole aviation plug the 9, the 5 32 hole aviation plug the 10, the 6 32 hole aviation plug 11, first netting twine patchplug 12 and the second netting twine patchplug 13 are arranged on shell 14.
Shell 14 was also provided with ancient piece of jade, round, flat and with a hole in its centre hole 19, for pressure measurement flexible pipe of transferring.
16 temperature survey isolation modules 15 are fixed together by draw-in groove, are positioned in shell 14.
Temperature scanning valve is fixed in shell 14 by four fixing screws.
16 pressure survey isolation modules 16 are fixed together by draw-in groove, are positioned in shell 14, and 16 pressure units 18 are fixed on shell 14 inwall respectively by boring.
Pressure scanning valve is fixed in shell 14 by four fixing screws.
16 frequency measurement isolation modules 17 are fixed together by draw-in groove, are positioned in shell 14.
Adopt aeroengine test run modularization fault removal device to carry out the method for failture evacuation, as shown in Figure 3, comprise the following steps:
Step 1: when the temperature value display of test bay aeromotor certain or multiple temperature sensor measuring point is abnormal, temperature-measuring module in temperature unit is connected to this temperature sensor measuring point, the temperature test acquisition channel of this temperature sensor measuring point is replaced by described temperature unit.
Step 2: judge whether the temperature value of now this temperature point shows normally, if so, perform step 3, otherwise, perform step 4.
Step 3: the temperature test acquisition channel fault of this temperature sensor measuring point, carries out the failture evacuation of the replacing of temperature test acquisition channel, performs step 5.
Step 4: the temperature sensor fault of the temperature test acquisition channel of this temperature sensor measuring point, carries out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel.
Step 5: when the temperature value display of the temperature point of test bay aeromotor certain or multiple temperature scanning valve thermometric is abnormal, by the expanding channels of the temperature scanning valve in temperature scanning valve cell to this temperature point, the temperature scanning valve test acquisition channel of this temperature point is replaced with the passage of described temperature scanning valve cell, carries out the failture evacuation of the temperature scanning valve test acquisition channel of this temperature point.
Step 6: when the force value display of test bay aeromotor certain or multiple pressure-measuring-point is abnormal, judges that whether this pressure-measuring-point is the pressure measurement point of pressure survey isolation module, if so, then performs step 7, otherwise, perform step 8.
Step 7: the pressure measurement flexible pipe that the pressure survey isolation module in pressure unit is connected by pressure unit is connected to this pressure-measuring-point, the pressure test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure unit, carry out the failture evacuation of the pressure test acquisition channel of this pressure-measuring-point, perform step 9.
Step 8: the passage of the pressure scanning valve of pressure scanning valve cell is connected to this pressure-measuring-point by pressure measurement flexible pipe, the pressure scanning valve test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure scanning valve cell, carries out the failture evacuation of the pressure scanning valve test acquisition channel of this pressure-measuring-point.
Step 9: when the tachometer value of test bay aeromotor certain or multiple frequency measuring point or flow value display abnormal time, frequency measurement isolation module in frequency cells is connected to this frequency measuring point, the frequency test acquisition channel of this frequency measuring point is replaced by described frequency cells.
Step 10: judge that now whether normally frequency values or flow value display, if so, perform step 11, otherwise, perform step 12.
Step 11: the frequency test acquisition channel fault of this frequency measuring point, carries out the normal eliminating of event of the replacing of frequency test acquisition channel.
Step 12: the speed probe of the frequency test acquisition channel of this frequency measuring point or flow sensor fault, carries out the failture evacuation of the speed probe of frequency test acquisition channel by this frequency measuring point or the replacing of flow sensor.
Claims (5)
1. aeroengine test run modularization fault removal device, is characterized in that, comprises temperature unit, temperature scanning valve cell, pressure unit, pressure scanning valve cell, frequency cells, VXI collection cabinet and computing machine;
Described temperature unit comprises multiple temperature survey isolation module, described temperature scanning valve cell is a temperature scanning valve, described pressure unit comprises multiple pressure survey isolation module and the pressure unit identical with pressure survey isolation module quantity, described pressure scanning valve cell is a pressure scanning valve, and described frequency cells comprises multiple frequency measurement isolation module;
In described temperature unit, the input end of each temperature survey isolation module connects test bay aeromotor temperature sensor measuring point by the one 32 hole aviation plug, and in temperature unit, the output terminal of each temperature survey isolation module connects VXI collection cabinet by the 2 32 hole aviation plug; The input end of each passage of the temperature scanning valve in described temperature scanning valve cell connects test bay aeromotor temperature point by the 3 32 hole aviation plug, and the output terminal of the temperature scanning valve of temperature scanning valve cell connects computing machine by the first netting twine attachment plug; The input end of each pressure survey isolation module in described pressure unit connects a pressure unit respectively, the input end of each pressure unit connects test bay aeromotor pressure-measuring-point by pressure measurement flexible pipe, and in pressure unit, the output terminal of each pressure survey isolation module connects VXI collection cabinet by the 4 32 hole aviation plug; The input end of each passage of the pressure scanning valve of described pressure scanning valve cell connects test bay aeromotor pressure-measuring-point by pressure measurement flexible pipe, and the output terminal of the pressure scanning valve of pressure scanning valve cell connects computing machine by the second netting twine attachment plug; In described frequency cells, the input end of each frequency measurement isolation module connects test bay aeroplane engine unit frequency measuring point by the 5 32 hole aviation plug, and in frequency cells, the output terminal of each frequency measurement isolation module connects VXI collection cabinet by the 6 32 hole aviation plug; The output terminal that described VXI gathers cabinet connects computing machine.
2. aeroengine test run modularization fault removal device according to claim 1, it is characterized in that, described temperature unit, for when the temperature value display of test bay aeromotor certain or multiple temperature sensor measuring point is abnormal, temperature survey isolation module in temperature unit is connected to this temperature sensor measuring point, the temperature test acquisition channel of this temperature sensor measuring point is replaced by described temperature unit, if now the temperature value display of this temperature point is normal, the then temperature test acquisition channel fault of this temperature sensor measuring point, carry out the failture evacuation of the replacing of temperature test acquisition channel, if still there is temperature value abnormal show phenomenon, the then temperature sensor fault of the temperature test acquisition channel of this temperature sensor measuring point, carry out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel,
Described temperature scanning valve cell, when temperature value display for the temperature point when test bay aeromotor certain or multiple temperature scanning valve thermometric is abnormal, by the expanding channels of the temperature scanning valve in temperature scanning valve cell to this temperature point, the temperature scanning valve test acquisition channel of this temperature point is replaced with the passage of described temperature scanning valve cell, carries out the failture evacuation of the temperature scanning valve test acquisition channel of this temperature point;
Described pressure unit, for when the force value display of test bay aeromotor certain or multiple pressure-measuring-point is abnormal, the pressure measurement flexible pipe that pressure survey isolation module in pressure unit is connected by pressure unit is connected to this pressure-measuring-point, the pressure test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure unit, carries out the failture evacuation of the pressure test acquisition channel of this pressure-measuring-point;
Described pressure scanning valve cell, when force value display for the pressure-measuring-point when test bay aeromotor certain or the pressure measurement of multiple pressure scanning valve is abnormal, the passage of the pressure scanning valve of pressure scanning valve cell is connected to this pressure-measuring-point by pressure measurement flexible pipe, the pressure scanning valve test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure scanning valve cell, carries out the failture evacuation of the pressure scanning valve test acquisition channel of this pressure-measuring-point;
Described frequency cells, for when the tachometer value of test bay aeromotor certain or multiple frequency measuring point or flow value display abnormal time, frequency measurement isolation module in frequency cells is connected to this frequency measuring point, the described frequency cells of the frequency quantity of this frequency measuring point test acquisition channel is replaced, if now frequency values or flow value display are normally, the then frequency quantity test acquisition channel fault of this frequency measuring point, carry out the normal eliminating of event of the replacing of frequency quantity test acquisition channel, if still there is tachometer value or flow value abnormal show phenomenon, then the frequency quantity of this frequency measuring point tests speed probe or the flow sensor fault of acquisition channel, carry out the failture evacuation by the frequency quantity of this frequency measuring point test speed probe of acquisition channel or the replacing of flow sensor,
Described VXI gathers cabinet, for being changed by the signal of temperature unit, pressure unit and frequency cells collection, transfers to computing machine.
3. aeroengine test run modularization fault removal device according to claim 1, it is characterized in that, this device also comprises shell, and described temperature unit, temperature scanning valve cell, pressure unit, pressure scanning valve cell and frequency cells are arranged at enclosure;
Described one 32 hole aviation plug, the 2 32 hole aviation plug, the 3 32 hole aviation plug, the 4 32 hole aviation plug, the 5 32 hole aviation plug, the 6 32 hole aviation plug, the first netting twine patchplug and the second netting twine patchplug are arranged on shell;
Each temperature survey isolation module described is fixed together by draw-in groove, is positioned in shell;
Described temperature scanning valve is fixing in the enclosure by four fixing screws;
Each pressure survey isolation module described is fixed together by draw-in groove, and be positioned in shell, each pressure unit is fixed on outer casing inner wall respectively by boring;
Described pressure scanning valve is fixing in the enclosure by four fixing screws;
Each frequency measurement isolation module described is fixed together by draw-in groove, is positioned in shell.
4. the aeroengine test run modularization fault removal device according to claim 1 or 3, is characterized in that, described shell was also provided with ancient piece of jade, round, flat and with a hole in its centre hole, for pressure measurement flexible pipe of transferring.
5. adopt aeroengine test run modularization fault removal device according to claim 1 to carry out the method for failture evacuation, it is characterized in that, comprise the following steps:
Step 1: when the temperature value display of test bay aeromotor certain or multiple temperature sensor measuring point is abnormal, temperature-measuring module in temperature unit is connected to this temperature sensor measuring point, the temperature test acquisition channel of this temperature sensor measuring point is replaced by described temperature unit;
Step 2: judge whether the temperature value of now this temperature point shows normally, if so, perform step 3, otherwise, perform step 4;
Step 3: the temperature test acquisition channel fault of this temperature sensor measuring point, carries out the failture evacuation of the replacing of temperature test acquisition channel, performs step 5;
Step 4: the temperature sensor fault of the temperature test acquisition channel of this temperature sensor measuring point, carries out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel;
Step 5: when the temperature value display of the temperature point of test bay aeromotor certain or multiple temperature scanning valve thermometric is abnormal, by the expanding channels of the temperature scanning valve in temperature scanning valve cell to this temperature point, the temperature scanning valve test acquisition channel of this temperature point is replaced with the passage of described temperature scanning valve cell, carries out the failture evacuation of the temperature scanning valve test acquisition channel of this temperature point;
Step 6: when the force value display of test bay aeromotor certain or multiple pressure-measuring-point is abnormal, judges that whether this pressure-measuring-point is the pressure measurement point of pressure survey isolation module, if so, then performs step 7, otherwise, perform step 8;
Step 7: the pressure measurement flexible pipe that the pressure survey isolation module in pressure unit is connected by pressure unit is connected to this pressure-measuring-point, the pressure test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure unit, carry out the failture evacuation of the pressure test acquisition channel of this pressure-measuring-point, perform step 9;
Step 8: the passage of the pressure scanning valve of pressure scanning valve cell is connected to this pressure-measuring-point by pressure measurement flexible pipe, the pressure scanning valve test acquisition channel of this pressure-measuring-point is replaced with the passage of described pressure scanning valve cell, carries out the failture evacuation of the pressure scanning valve test acquisition channel of this pressure-measuring-point;
Step 9: when the tachometer value of test bay aeromotor certain or multiple frequency measuring point or flow value display abnormal time, frequency measurement isolation module in frequency cells is connected to this frequency measuring point, the described frequency cells of the frequency quantity of this frequency measuring point test acquisition channel is replaced;
Step 10: judge that now whether normally frequency values or flow value display, if so, perform step 11, otherwise, perform step 12;
Step 11: the frequency quantity test acquisition channel fault of this frequency measuring point, carries out the normal eliminating of event of the replacing of frequency quantity test acquisition channel;
Step 12: the speed probe of the frequency quantity test acquisition channel of this frequency measuring point or flow sensor fault, carries out the failture evacuation by the frequency quantity of this frequency measuring point test speed probe of acquisition channel or the replacing of flow sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510817541.8A CN105486507B (en) | 2015-11-23 | 2015-11-23 | Aeroengine test run modularization fault removal device and its troubleshooting methodology |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510817541.8A CN105486507B (en) | 2015-11-23 | 2015-11-23 | Aeroengine test run modularization fault removal device and its troubleshooting methodology |
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| CN105486507A true CN105486507A (en) | 2016-04-13 |
| CN105486507B CN105486507B (en) | 2017-11-07 |
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| CN201510817541.8A Active CN105486507B (en) | 2015-11-23 | 2015-11-23 | Aeroengine test run modularization fault removal device and its troubleshooting methodology |
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| CN105486507B (en) | 2017-11-07 |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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