CN105486507B - Aeroengine test run modularization fault removal device and its troubleshooting methodology - Google Patents
Aeroengine test run modularization fault removal device and its troubleshooting methodology Download PDFInfo
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- CN105486507B CN105486507B CN201510817541.8A CN201510817541A CN105486507B CN 105486507 B CN105486507 B CN 105486507B CN 201510817541 A CN201510817541 A CN 201510817541A CN 105486507 B CN105486507 B CN 105486507B
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- G—PHYSICS
- G01—MEASURING; TESTING
- 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 present invention relates to aeroengine test run modularization fault removal device and its troubleshooting methodology, the device includes temperature unit, temperature scanning valve cell, pressure unit, pressure scanning valve cell, frequency cells, VXI gathers cabinet and computer, temperature unit includes multiple temperature survey isolation modules, temperature scanning valve cell is a temperature scanning valve, pressure unit include multiple pressure measxurement isolation modules and with pressure measxurement isolation module quantity identical pressure transmitter, pressure scanning valve cell is a pressure scanning valve, frequency cells include multiple frequency measurement isolation modules, the inventive method sorts out unit-modularized rear quick-replaceable troubleshooting by the way that TCH test channel parameter is carried out, fast and effeciently exclude same type test failure, ensure the exclusion of engine test test failure, improve the test run efficiency and production efficiency of engine, it ensure that engine test quality and cycle, flexible structure is convenient, there is certain dissemination to aeroengine test run work.
Description
Technical field
The invention belongs to aero-engine technology field, and in particular to aeroengine test run modularization fault removal device
And its troubleshooting methodology.
Background technology
Aeroengine test run is an extremely numerous and jumbled system engineering, and it is many that it covers test run technique, observing and controlling, vibration etc.
Specialty.Not only the cycle is long for aeroengine test run, and expends huge, aero-engine ground run bad environments, test item
, easily there are various failures in nearly hundred kinds of mesh in commissioning process, such as vibration exceeding the standard, data are unstable, signal failure failure, failure
Exclusion needs to take the plenty of time, and the overall production efficiency of influence significantly increases test run cost.At present, ground test stand is used
Scattered test, it is unified to be tested by data collecting system, once there is some or the failure of multiple signal testings, it is necessary to take a large amount of
The troubleshooting time, which determines, the problems such as be the circuit, sensor, communication of some or multiple signals solves, influence engine production effect
Rate.
The content of the invention
In view of the shortcomings of the prior art, the present invention proposes aeroengine test run modularization fault removal device and its failure
Method for removing.
Aeroengine test run modularization fault removal device, including temperature unit, temperature scanning valve cell, pressure list
Member, pressure scanning valve cell, frequency cells, VXI collection cabinet and computer；
The temperature unit includes multiple temperature survey isolation modules, and the temperature scanning valve cell is a temperature scanning
Valve, the pressure unit include multiple pressure measxurement isolation modules and with pressure measxurement isolation module quantity identical pressure inverting
Device, the pressure scanning valve cell is a pressure scanning valve, and the frequency cells include multiple frequency measurement isolation modules；
The input of each temperature survey isolation module is tried by the one 32 hole aviation plug connection in the temperature unit
The output end of each temperature survey isolation module passes through the 2nd 32 in ride aero-engine temperature sensor measuring point, temperature unit
Hole aviation plug connection VXI collection cabinets；The input of each passage of the temperature scanning valve in the temperature scanning valve cell
Test bay aero-engine temperature point is connected by the 3rd 32 hole aviation plug, the temperature scanning valve of temperature scanning valve cell
Output end connects plug by the first netting twine and connects computer；Each pressure measxurement isolation module in the pressure unit it is defeated
Enter end and connect a pressure transmitter respectively, the input of each pressure transmitter connects test bay aviation by pressure measurement flexible pipe and sent out
The output end of each pressure measxurement isolation module is connected by the 4th 32 hole aviation plug in motivation pressure-measuring-point, pressure unit
VXI gathers cabinet；The input of each passage of the pressure scanning valve of the pressure scanning valve cell is connected by pressure measurement flexible pipe
Test bay aero-engine pressure-measuring-point, the output end of the pressure scanning valve of pressure scanning valve cell is connected by the second netting twine inserts
Head connection computer；The input of each frequency measurement isolation module is connected by the 5th 32 hole aviation plug in the frequency cells
The output end for connecing each frequency measurement isolation module in test bay aeroplane engine unit frequency measuring point, frequency cells passes through the 6th 32 hole
Aviation plug connection VXI collection cabinets；The output end connection computer of the VXI collections cabinet.
The temperature unit, shows for the temperature value when test bay aero-engine some or multiple temperature sensor measuring points
When showing abnormal, the temperature survey isolation module in temperature unit is connected to the temperature sensor measuring point, by the temperature sensor
The temperature test acquisition channel of measuring point is replaced with the temperature unit, if now the temperature value of the temperature point is shown just
Often, then the temperature test acquisition channel failure of the temperature sensor measuring point, carries out the failure of the replacing of temperature test acquisition channel
Exclude, if still suffering from temperature value abnormal show phenomenon, the temperature of the temperature test acquisition channel of the temperature sensor measuring point is passed
Sensor failure, carries out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel；
The temperature scanning valve cell, for when test bay aero-engine some or multiple use temperature scanning valve thermometrics
When the temperature value display of temperature point is abnormal, the passage of the temperature scanning valve in temperature scanning valve cell is connected to the temperature and surveyed
Point, the temperature scanning valve test acquisition channel of the temperature point is replaced with the passage of the temperature scanning valve cell, entered
The failture evacuation of the temperature scanning valve test acquisition channel of the row temperature point；
The pressure unit, shows abnormal for the pressure value when test bay aero-engine some or multiple pressure-measuring-points
When, the pressure measurement flexible pipe that the pressure measxurement isolation module in pressure unit is connected by pressure transmitter is connected to pressure survey
Point, the pressure test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure unit, the pressure-measuring-point is carried out
Pressure test acquisition channel failture evacuation；
The pressure scanning valve cell, for when test bay aero-engine some or multiple use pressure scanning valve pressure measurement
When the pressure value display of pressure-measuring-point is abnormal, the passage of the pressure scanning valve of pressure scanning valve cell is connected by pressure measurement flexible pipe
To the pressure-measuring-point, the pressure scanning valve test acquisition channel of the pressure-measuring-point is entered with the passage of the pressure scanning valve cell
Row is replaced, and carries out the failture evacuation of the pressure scanning valve test acquisition channel of the pressure-measuring-point；
The frequency cells, for when the tachometer value or flow value of some or multiple frequency measuring points of test bay aero-engine
When display is abnormal, the frequency measurement isolation module in frequency cells is connected to the frequency measuring point, by the frequency of the frequency measuring point
Measure test acquisition passage to be replaced with the frequency cells, if now frequency values or flow value are shown normally, the frequency is surveyed
The frequency quantity test acquisition channel failure of point, carries out the former normal exclusion of the replacing of frequency quantity test acquisition channel, turns if still suffering from
The speed probe or flow of speed value or flow value abnormal show phenomenon, then the frequency quantity test acquisition channel of the frequency measuring point
Sensor fault, enters to be about to the speed probe or flow sensor of the frequency quantity test acquisition channel of the frequency measuring point more
The failture evacuation changed；
The VXI gathers cabinet, and the signal for temperature unit, pressure unit and frequency cells to be gathered is changed,
Transmit to computer.
The device also includes shell, the temperature unit, temperature scanning valve cell, pressure unit, pressure scanning valve cell
Enclosure is arranged at frequency cells；
The one 32 hole aviation plug, the 2nd 32 hole aviation plug, the 3rd 32 hole aviation plug, the 4th 32 hole aviation are inserted
Head, the 5th 32 hole aviation plug, the 6th 32 hole aviation plug, the first netting twine patchplug and the second netting twine patchplug are arranged at
In shell；
Wall hole was additionally provided with the shell, for pressure hose of transferring；
Each described temperature survey isolation module is fixed together by neck, is positioned in shell；
The temperature scanning valve is fixed on shell by four fixed screws；
Each described pressure measxurement isolation module is fixed together by neck, is positioned in shell, each pressure inverting
Device is fixed on outer casing inner wall by drilling respectively；
The pressure scanning valve is fixed on shell by four fixed screws；
Each described frequency measurement isolation module is fixed together by neck, is positioned in shell.
Wall hole was additionally provided with the shell, for penetrating pressure measurement flexible pipe.
The method that failture evacuation is carried out using aeroengine test run modularization fault removal device, is comprised the following steps：
Step 1：, will when the temperature value of test bay aero-engine some or multiple temperature sensor measuring points shows abnormal
Temperature-measuring module in temperature unit is connected to the temperature sensor measuring point, and the temperature test of the temperature sensor measuring point is adopted
Collection passage is replaced with the temperature unit；
Step 2：Judge whether the temperature value of the now temperature point shows normally, if so, performing step 3, otherwise, perform
Step 4；
Step 3：The temperature test acquisition channel failure of the temperature sensor measuring point, carries out temperature test acquisition channel more
The failture evacuation changed, performs step 5；
Step 4：The temperature sensor fault of the temperature test acquisition channel of the temperature sensor measuring point, carries out temperature test
The failture evacuation of the replacing of the temperature sensor of acquisition channel；
Step 5：When the temperature value of the temperature point of test bay aero-engine some or multiple use temperature scanning valve thermometrics
When display is abnormal, the passage of the temperature scanning valve in temperature scanning valve cell is connected to the temperature point, by the temperature point
Temperature scanning valve test acquisition channel be replaced with the passage of the temperature scanning valve cell, carry out the temperature of the temperature point
The failture evacuation of degree scanning valve test acquisition channel；
Step 6：When the pressure value of test bay aero-engine some or multiple pressure-measuring-points shows abnormal, the pressure is judged
Whether power measuring point is the pressure measurement point of pressure measxurement isolation module, if so, then performing step 7, otherwise, performs step 8；
Step 7：The pressure measurement flexible pipe that pressure measxurement isolation module in pressure unit is connected by pressure transmitter is connected
To the pressure-measuring-point, the pressure test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure unit, carried out
The failture evacuation of the pressure test acquisition channel of the pressure-measuring-point, performs step 9；
Step 8：The passage of the pressure scanning valve of pressure scanning valve cell is connected to the pressure-measuring-point by pressure measurement flexible pipe,
The pressure scanning valve test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure scanning valve cell, is somebody's turn to do
The failture evacuation of the pressure scanning valve test acquisition channel of pressure-measuring-point；
Step 9：When the tachometer value or flow value of test bay aero-engine some or multiple frequency measuring points show abnormal,
Frequency measurement isolation module in frequency cells is connected to the frequency measuring point, the frequency quantity test collection of the frequency measuring point is logical
Road is replaced with the frequency cells；
Step 10：Judge that now frequency values or flow value are displayed whether normally, if so, performing step 11, otherwise, perform step
Rapid 12；
Step 11：The frequency quantity test acquisition channel failure of the frequency measuring point, carries out frequency quantity test acquisition channel more
The former normal exclusion changed；
Step 12：The speed probe or flow sensor failure of the frequency quantity test acquisition channel of the frequency measuring point,
The failure row for entering to be about to the replacing of the speed probe or flow sensor of the frequency quantity test acquisition channel of the frequency measuring point
Remove.
Beneficial effects of the present invention：
The present invention proposes aeroengine test run modularization fault removal device and its troubleshooting methodology, by that will test
The design of quick-replaceable troubleshooting after channel parameters classification is unit-modularized, fast and effeciently smoothly excludes same type test event
Barrier, ensures the smooth exclusion of the test failure of engine test, improves the test run efficiency and production efficiency of engine, it is ensured that hair
Motivation test run quality and cycle, flexible structure are convenient, have certain dissemination to aeroengine test run work.
Brief description of the drawings
Fig. 1 is the structural representation of aeroengine test run modularization fault removal device in the specific embodiment of the invention
Figure；
Fig. 2 is the modules of aeroengine test run modularization fault removal device in the specific embodiment of the invention
Annexation schematic diagram；
Wherein, 1- temperature units, 2- temperature scanning valve cells, 3- pressure units, 4- pressure scanning valve cells, 5- frequency lists
Member, the hole aviation plugs of 6- the 1st, the hole aviation plugs of 7- the 2nd 32, the hole aviation plugs of 8- the 3rd 32, the hole aviations of 9- the 4th 32 are inserted
Head, the hole aviation plugs of 10- the 5th 32, the hole aviation plugs of 11- the 6th 32,12- the first netting twine patchplugs, the netting twines of 13- second turn
Plug, 14- shells, 15- temperature survey isolation modules, 16- pressure measxurement isolation modules, 17- frequency measurement isolation modules,
18- pressure transmitters, 19- crosses wall hole；
Fig. 3 is the flow chart of the aviation engine test modularization troubleshooting methodology in the specific embodiment of the invention.
Embodiment
The specific embodiment of the invention is described in detail below in conjunction with the accompanying drawings.
Aeroengine test run modularization fault removal device, as shown in figure 1, including temperature unit 1, temperature scanning valve list
Member 2, pressure unit 3, pressure scanning valve cell 4, frequency cells 5, VXI collection cabinets and computer.
In present embodiment, temperature unit 1 includes 16 temperature survey isolation modules 15, temperature survey isolation module 15
Model M5TS-24-R.
In present embodiment, temperature scanning valve cell 2 is a temperature scanning valve, the model of temperature scanning valve
DSA3250。
In present embodiment, pressure unit 3 includes 16 pressure measxurement isolation modules 16 and 16 pressure transmitters 18, pressure
Power measures the model M5VS-A6-R/K of isolation module 16, the model De Luke pressure transmitters of pressure transmitter 18.
In present embodiment, pressure scanning valve cell 4 is a pressure scanning valve, the model of pressure scanning valve
DSA3207/3217。
In present embodiment, frequency cells 5 include 16 frequency measurement isolation modules 17, frequency measurement isolation module 17
Model TAIK ELECTRIC S3-VD-1-00A4C.
In present embodiment, as shown in Fig. 2 each input of 16 temperature survey isolation modules in temperature unit 1
Connected by the one 32 hole aviation plug 6 in test bay aero-engine temperature sensor measuring point, figure and part connecting line be only shown,
The output end of 16 temperature survey isolation modules in temperature unit 1 connects VXI harvesters by the 2nd 32 hole aviation plug 7
Case.
The input of each passage of the temperature scanning valve in temperature scanning valve cell 2 passes through the 3rd 32 hole aviation plug 8
Connect in test bay aero-engine temperature point, figure and part connecting line, the temperature scanning valve of temperature scanning valve cell 2 are only shown
Output end pass through the first netting twine connect plug 12 connect computer.
Each input of 16 pressure measxurement isolation modules in pressure unit 3 connects a pressure transmitter respectively
18, the input of pressure transmitter 18 is connected in test bay aero-engine pressure-measuring-point, figure by pressure measurement flexible pipe only shows portion
Divide the output end of 16 pressure measxurement isolation modules in connecting line, pressure unit 3 to pass through the 4th 32 hole aviation plug 9 and connect VXI
Gather cabinet.
The input of each passage of the pressure scanning valve of pressure scanning valve cell 4 connects test bay by pressure measurement flexible pipe and navigated
Part connecting line is only shown, the output end of the pressure scanning valve of pressure scanning valve cell 4 passes through in empty engine pressure measuring point, figure
The second netting twine connection connection computer of plug 13.
Each input of 16 frequency measurement isolation modules 17 is connected by the 5th 32 hole aviation plug 10 in frequency cells 5
Connect and 16 frequency measurement isolation modes in part connecting line, frequency cells 5 are only shown in test bay aeroplane engine unit frequency measuring point, figure
The output end of block 17 connects VXI by the 6th 32 hole aviation plug 11 and gathers cabinet, and the output end connection of VXI collection cabinets is calculated
Machine.
Temperature unit 1, shows for the temperature value when test bay aero-engine some or multiple temperature sensor measuring points
When abnormal, the temperature survey isolation module 15 in temperature unit 1 is connected to the temperature sensor measuring point, by the temperature sensor
The temperature test acquisition channel of measuring point is replaced with the temperature unit 1, if now the temperature value of the temperature point is shown just
Often, then the temperature test acquisition channel failure of the temperature sensor measuring point, carries out the failure of the replacing of temperature test acquisition channel
Exclude, if still suffering from temperature value abnormal show phenomenon, the temperature of the temperature test acquisition channel of the temperature sensor measuring point is passed
Sensor failure, carries out the failture evacuation of the replacing of the temperature sensor of temperature test acquisition channel.
Temperature scanning valve cell 2, for when the temperature of some or multiple use temperature scanning valve thermometrics of test bay aero-engine
When spending the temperature value display exception of measuring point, the passage of the temperature scanning valve in temperature scanning valve cell 2 is connected to the temperature and surveyed
Point, the temperature scanning valve test acquisition channel of the temperature point is replaced with the passage of the temperature scanning valve cell 2, entered
The failture evacuation of the temperature scanning valve test acquisition channel of the row temperature point.
Pressure unit 3, for when the pressure value of test bay aero-engine some or multiple pressure-measuring-points shows abnormal,
The pressure measurement flexible pipe that pressure measxurement isolation module 16 in pressure unit 3 is connected by pressure transmitter 18 is connected to pressure survey
Point, the pressure test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure unit 3, the pressure-measuring-point is carried out
Pressure test acquisition channel failture evacuation.
Pressure scanning valve cell 4, for when the pressure of some or multiple use pressure scanning valve pressure measurement of test bay aero-engine
When the pressure value display of power measuring point is abnormal, the passage of the pressure scanning valve of pressure scanning valve cell 4 is connected by pressure measurement flexible pipe
To the pressure-measuring-point, by passage of the pressure scanning valve test acquisition channel of the pressure-measuring-point with the pressure scanning valve cell 4
It is replaced, carries out the failture evacuation of the pressure scanning valve test acquisition channel of the pressure-measuring-point.
Frequency cells 5, show for the tachometer value or flow value when test bay aero-engine some or multiple frequency measuring points
When showing abnormal, the frequency measurement isolation module 17 in frequency cells 5 is connected to the frequency measuring point, by the frequency of the frequency measuring point
Test acquisition channel is replaced with the frequency cells 5, if now frequency values or flow value are shown normally, the frequency measuring point
Frequency test acquisition channel failure, carry out frequency test acquisition channel replacing it is former it is normal exclusion, if still suffer from tachometer value or
Flow value abnormal show phenomenon, the then speed probe of the frequency test acquisition channel of the frequency measuring point or flow sensor event
Barrier, the failure row for entering to be about to the replacing of the speed probe or flow sensor of the frequency test acquisition channel of the frequency measuring point
Remove.
VXI gathers cabinet, and the signal for temperature unit, pressure unit and frequency cells to be gathered is changed, and transmits
To computer, in present embodiment, VXI gathers the model Agilent E1421B of cabinet.
The device also includes shell 14, temperature unit 1, temperature scanning valve cell 2, pressure unit 3, pressure scanning valve cell
4 and frequency cells 5 be arranged inside shell 14.
One 32 hole aviation plug 6, the 2nd 32 hole aviation plug 7, the 3rd 32 hole aviation plug 8, the 4th 32 hole aviation are inserted
First 9, the 5th 32 hole aviation plug 10, the 6th 32 hole aviation plug 11, the first netting twine patchplug 12 and the switching of the second netting twine are inserted
First 13 are arranged on shell 14.
Wall hole 19 was additionally provided with shell 14, for pressure measurement flexible pipe of transferring.
16 temperature survey isolation modules 15 are fixed together by neck, are positioned in shell 14.
Temperature scanning valve is fixed in shell 14 by four fixed screws.
16 pressure measxurement isolation modules 16 are fixed together by neck, are positioned in shell 14,16 pressure invertings
Device 18 is fixed on the inwall of shell 14 by drilling respectively.
Pressure scanning valve is fixed in shell 14 by four fixed screws.
16 frequency measurement isolation modules 17 are fixed together by neck, are positioned in shell 14.
The method that failture evacuation is carried out using aeroengine test run modularization fault removal device, as shown in figure 3, including
Following steps：
Step 1：, will when the temperature value of test bay aero-engine some or multiple temperature sensor measuring points shows abnormal
Temperature-measuring module in temperature unit is connected to the temperature sensor measuring point, and the temperature test of the temperature sensor measuring point is adopted
Collection passage is replaced with the temperature unit.
Step 2：Judge whether the temperature value of the now temperature point shows normally, if so, performing step 3, otherwise, perform
Step 4.
Step 3：The temperature test acquisition channel failure of the temperature sensor measuring point, carries out temperature test acquisition channel more
The failture evacuation changed, performs step 5.
Step 4：The temperature sensor fault of the temperature test acquisition channel of the temperature sensor measuring point, carries out temperature test
The failture evacuation of the replacing of the temperature sensor of acquisition channel.
Step 5：When the temperature value of the temperature point of test bay aero-engine some or multiple use temperature scanning valve thermometrics
When display is abnormal, the passage of the temperature scanning valve in temperature scanning valve cell is connected to the temperature point, by the temperature point
Temperature scanning valve test acquisition channel be replaced with the passage of the temperature scanning valve cell, carry out the temperature of the temperature point
The failture evacuation of degree scanning valve test acquisition channel.
Step 6：When the pressure value of test bay aero-engine some or multiple pressure-measuring-points shows abnormal, the pressure is judged
Whether power measuring point is the pressure measurement point of pressure measxurement isolation module, if so, then performing step 7, otherwise, performs step 8.
Step 7：The pressure measurement flexible pipe that pressure measxurement isolation module in pressure unit is connected by pressure transmitter is connected
To the pressure-measuring-point, the pressure test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure unit, carried out
The failture evacuation of the pressure test acquisition channel of the pressure-measuring-point, performs step 9.
Step 8：The passage of the pressure scanning valve of pressure scanning valve cell is connected to the pressure-measuring-point by pressure measurement flexible pipe,
The pressure scanning valve test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure scanning valve cell, is somebody's turn to do
The failture evacuation of the pressure scanning valve test acquisition channel of pressure-measuring-point.
Step 9：When the tachometer value or flow value of test bay aero-engine some or multiple frequency measuring points show abnormal,
Frequency measurement isolation module in frequency cells is connected to the frequency measuring point, by the frequency test acquisition channel of the frequency measuring point
It is replaced with the frequency cells.
Step 10：Judge that now frequency values or flow value are displayed whether normally, if so, performing step 11, otherwise, perform step
Rapid 12.
Step 11：The frequency test acquisition channel failure of the frequency measuring point, carries out the replacing of frequency test acquisition channel
Therefore often exclude.
Step 12：The speed probe or flow sensor failure of the frequency test acquisition channel of the frequency measuring point, enter
It is about to the failture evacuation of the replacing of the speed probe or flow sensor of the frequency test acquisition channel of the frequency measuring point.
Claims (5)
1. aeroengine test run modularization fault removal device, it is characterised in that including temperature unit, temperature scanning valve list
Member, pressure unit, pressure scanning valve cell, frequency cells, VXI collection cabinets and computer；
The temperature unit includes multiple temperature survey isolation modules, and the temperature scanning valve cell is a temperature scanning valve,
The pressure unit include multiple pressure measxurement isolation modules and with pressure measxurement isolation module quantity identical pressure transmitter,
The pressure scanning valve cell is a pressure scanning valve, and the frequency cells include multiple frequency measurement isolation modules；
The input of each temperature survey isolation module connects test bay by the one 32 hole aviation plug in the temperature unit
The output end of each temperature survey isolation module is navigated by the 2nd 32 hole in aero-engine temperature sensor measuring point, temperature unit
Blind plug connection VXI collection cabinets；The input of each passage of the temperature scanning valve in the temperature scanning valve cell passes through
3rd 32 hole aviation plug connection test bay aero-engine temperature point, the output of the temperature scanning valve of temperature scanning valve cell
End connects plug by the first netting twine and connects computer；The input of each pressure measxurement isolation module in the pressure unit
A pressure transmitter is connected respectively, and the input of each pressure transmitter connects test bay aero-engine by pressure measurement flexible pipe
The output end of each pressure measxurement isolation module connects VXI by the 4th 32 hole aviation plug and adopted in pressure-measuring-point, pressure unit
Collect cabinet；The input of each passage of the pressure scanning valve of the pressure scanning valve cell connects test bay by pressure measurement flexible pipe
Aero-engine pressure-measuring-point, the output end of the pressure scanning valve of pressure scanning valve cell connects plug by the second netting twine and connected
Computer；The input of each frequency measurement isolation module connects test run by the 5th 32 hole aviation plug in the frequency cells
The output end of each frequency measurement isolation module is inserted by the 6th 32 hole aviation in platform aeroplane engine unit frequency measuring point, frequency cells
Head connection VXI collection cabinets；The output end connection computer of the VXI collections cabinet.
2. aeroengine test run modularization fault removal device according to claim 1, it is characterised in that the temperature
Unit, for when the temperature value of test bay aero-engine some or multiple temperature sensor measuring points shows abnormal, by temperature
Temperature survey isolation module in unit is connected to the temperature sensor measuring point, and the temperature test of the temperature sensor measuring point is adopted
Collection passage is replaced with the temperature unit, if now the temperature value of the temperature point is shown normally, the temperature sensor
The temperature test acquisition channel failure of measuring point, carries out the failture evacuation of the replacing of temperature test acquisition channel, if still suffering from temperature
It is worth the temperature sensor fault of abnormal show phenomenon, then the temperature test acquisition channel of the temperature sensor measuring point, enters trip temperature
Test the failture evacuation of the replacing of the temperature sensor of acquisition channel；
The temperature scanning valve cell, for when the temperature of some or multiple use temperature scanning valve thermometrics of test bay aero-engine
When the temperature value display of measuring point is abnormal, the passage of the temperature scanning valve in temperature scanning valve cell is connected to the temperature point,
The temperature scanning valve test acquisition channel of the temperature point is replaced with the passage of the temperature scanning valve cell, is somebody's turn to do
The failture evacuation of the temperature scanning valve test acquisition channel of temperature point；
The pressure unit, for when the pressure value of test bay aero-engine some or multiple pressure-measuring-points shows abnormal,
The pressure measurement flexible pipe that pressure measxurement isolation module in pressure unit is connected by pressure transmitter is connected to the pressure-measuring-point, will
The pressure test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure unit, carries out the pressure of the pressure-measuring-point
Test the failture evacuation of acquisition channel；
The pressure scanning valve cell, for when the pressure of some or multiple use pressure scanning valve pressure measurement of test bay aero-engine
When the pressure value display of measuring point is abnormal, the passage of the pressure scanning valve of pressure scanning valve cell is connected to this by pressure measurement flexible pipe
Pressure-measuring-point, the pressure scanning valve test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure scanning valve cell
Change, carry out the failture evacuation of the pressure scanning valve test acquisition channel of the pressure-measuring-point；
The frequency cells, show for the tachometer value or flow value when test bay aero-engine some or multiple frequency measuring points
When abnormal, the frequency measurement isolation module in frequency cells is connected to the frequency measuring point, the frequency of the frequency measuring point is measured
Test acquisition passage is replaced with the frequency cells, if now frequency values or flow value are shown normally, the frequency measuring point
Frequency quantity tests acquisition channel failure, the former normal exclusion of the replacing of frequency quantity test acquisition channel is carried out, if still suffering from tachometer value
Or the speed probe or flow sensing of flow value abnormal show phenomenon, then the frequency quantity test acquisition channel of the frequency measuring point
Device failure, enters to be about to the replacing of the speed probe or flow sensor of the frequency quantity test acquisition channel of the frequency measuring point
Failture evacuation；
The VXI gathers cabinet, and the signal for temperature unit, pressure unit and frequency cells to be gathered is changed, and transmits
To computer.
3. aeroengine test run modularization fault removal device according to claim 1, it is characterised in that the device is also
Including shell, the temperature unit, temperature scanning valve cell, pressure unit, pressure scanning valve cell and frequency cells are arranged at
Enclosure；
The one 32 hole aviation plug, the 2nd 32 hole aviation plug, the 3rd 32 hole aviation plug, the 4th 32 hole aviation plug,
5th 32 hole aviation plug, the 6th 32 hole aviation plug, the first netting twine patchplug and the second netting twine patchplug are arranged at outer
On shell；
Each described temperature survey isolation module is fixed together by neck, is positioned in shell；
The temperature scanning valve is fixed in shell by four fixed screws；
Each described pressure measxurement isolation module is fixed together by neck, is positioned in shell, each pressure transmitter point
It is not fixed on by drilling on outer casing inner wall；
The pressure scanning valve is fixed in shell by four fixed screws；
Each described frequency measurement isolation module is fixed together by neck, is positioned in shell.
4. aeroengine test run modularization fault removal device according to claim 3, it is characterised in that the shell
On be additionally provided with wall hole, for pressure measurement flexible pipe of transferring.
5. the method for failture evacuation is carried out using the aeroengine test run modularization fault removal device described in claim 1,
It is characterised in that it includes following steps：
Step 1：When the temperature value of test bay aero-engine some or multiple temperature sensor measuring points shows abnormal, by temperature
Temperature-measuring module in unit is connected to the temperature sensor measuring point, and the temperature test of the temperature sensor measuring point is gathered into logical
Road is replaced with the temperature unit；
Step 2：Judge whether the temperature value of the now temperature point shows normally, if so, performing step 3, otherwise, perform step
4；
Step 3：The temperature test acquisition channel failure of the temperature sensor measuring point, carries out the replacing of temperature test acquisition channel
Failture evacuation, performs step 5；
Step 4：The temperature sensor fault of the temperature test acquisition channel of the temperature sensor measuring point, carries out temperature test collection
The failture evacuation of the replacing of the temperature sensor of passage；
Step 5：When the temperature value of the temperature point of test bay aero-engine some or multiple use temperature scanning valve thermometrics is shown
When abnormal, the passage of the temperature scanning valve in temperature scanning valve cell is connected to the temperature point, by the temperature of the temperature point
Degree scanning valve test acquisition channel is replaced with the passage of the temperature scanning valve cell, and the temperature for carrying out the temperature point is swept
Retouch the failture evacuation of valve test acquisition channel；
Step 6：When the pressure value of test bay aero-engine some or multiple pressure-measuring-points shows abnormal, judge that the pressure is surveyed
Whether point is the pressure measurement point of pressure measxurement isolation module, if so, then performing step 7, otherwise, performs step 8；
Step 7：The pressure measurement flexible pipe that pressure measxurement isolation module in pressure unit is connected by pressure transmitter is connected to this
Pressure-measuring-point, the pressure test acquisition channel of the pressure-measuring-point is replaced with the passage of the pressure unit, the pressure is carried out
The failture evacuation of the pressure test acquisition channel of power measuring point, performs step 9；
Step 8：The passage of the pressure scanning valve of pressure scanning valve cell is connected to the pressure-measuring-point by pressure measurement flexible pipe, by this
The pressure scanning valve test acquisition channel of pressure-measuring-point is replaced with the passage of the pressure scanning valve cell, carries out the pressure
The failture evacuation of the pressure scanning valve test acquisition channel of measuring point；
Step 9：, will frequency when the tachometer value or flow value of test bay aero-engine some or multiple frequency measuring points show abnormal
Frequency measurement isolation module in rate unit is connected to the frequency measuring point, and the frequency quantity test acquisition channel of the frequency measuring point is used
The frequency cells are replaced；
Step 10：Judge that now frequency values or flow value are displayed whether normally, if so, performing step 11, otherwise, perform step
12；
Step 11：The frequency quantity test acquisition channel failure of the frequency measuring point, carries out the replacing of frequency quantity test acquisition channel
Therefore often exclude；
Step 12：The speed probe or flow sensor failure of the frequency quantity test acquisition channel of the frequency measuring point, are carried out
The frequency quantity of the frequency measuring point is tested to the failture evacuation of the replacing of the speed probe or flow sensor of acquisition channel.
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| CN106370345A (en) * | 2016-08-25 | 2017-02-01 | 中国电子科技集团公司第四十八研究所 | Multichannel pressure scanning valve |
| CN107421745B (en) * | 2017-05-31 | 2019-05-14 | 中国人民解放军空军工程大学 | A kind of engine automation ground detection system and method based on engine data logger |
| CN112046782A (en) * | 2020-09-16 | 2020-12-08 | 中国航发沈阳黎明航空发动机有限责任公司 | Single-engine fault elimination method for double-engine airplane |
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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 |