CN204299767U - For the Auto-Test System of aero-engine ignition system - Google Patents
For the Auto-Test System of aero-engine ignition system Download PDFInfo
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- CN204299767U CN204299767U CN201420734986.0U CN201420734986U CN204299767U CN 204299767 U CN204299767 U CN 204299767U CN 201420734986 U CN201420734986 U CN 201420734986U CN 204299767 U CN204299767 U CN 204299767U
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Abstract
The utility model provides a kind of Auto-Test System for aero-engine ignition system, and this Auto-Test System comprises: power supply, for providing power supply energy to ignition system; Current measuring device, it is coupled to the input current for measurement point ignition system between this power supply and this ignition exciter unit; And ignition system test manager, comprising: communication unit, it couples receive actual power voltage and frequency of supply and couple to receive this input current with this current measuring device by Serial Port Line and this power supply; Command unit, it is coupled to this communication unit, for sending test parameters by this communication unit to this power supply; Data processing unit, it is coupled to this communication unit, for the treatment of the measured value received by this communication unit to obtain test data; And pattern displaying unit, it is coupled to this data processing unit for this test data of display.
Description
Technical field
The utility model relates to the field tests of aero-engine ignition system, particularly relates to a kind of Auto-Test System for aero-engine ignition system.
Background technology
Under normal temperature condition, the ignition system function test of aero-engine mainly comprises continuous ignition function, cycle ignition function, and ignition system performance test mainly comprises input current, output voltage, spark frequency, output current and spark energy etc.Test objective in whole supply district, whether meets ignition system functional requirement and performance indications in order to verifying.In current above-mentioned ignition system functional performance process of the test, the input of the record of test data and experimental condition (i.e. the supply voltage of process of the test ignition system testing site and frequency) all needs manually to complete.
The shortcoming done like this is: the test 1) often completing a testing site, and demand manually sets the measurement parameter of next testing site, wastes test period, adds human cost; 2) laboratory technician is by reading the stopwatch form control ignition system working time, cannot be accurate to just in time, causes test period not meet the standard of test; 3) laboratory technician will record Multitest data (as input current and spark frequency) within the very short duration of ignition simultaneously, can not accomplish the synchronism of data; 4) because the record of test data depends on the record of testing crew, and cause the problems such as test data record is unreasonable, test data measuring point is few, thus bring difficulty to the Performance Evaluation of ignition system, performance change trend analysis and design improvement.
Therefore, this area need a kind of can more comprehensively, the test macro of automatic test point ignition system exactly.
Utility model content
In order to overcome above-mentioned defect, the utility model aims to provide a kind of Auto-Test System for aero-engine ignition system.
According to one side of the present utility model, provide a kind of Auto-Test System for aero-engine ignition system, this aero-engine ignition system comprises ignition exciter unit, firing cable and ignition electric nozzle, it is characterized in that, this Auto-Test System comprises:
Power supply, for providing power supply energy to ignition system;
Current measuring device, it is coupled to the input current for measurement point ignition system between this power supply and this ignition exciter unit; And
Ignition system test manager, comprising:
Communication unit, it couples receive actual power voltage and frequency of supply and couple to receive this input current with this current measuring device by Serial Port Line and this power supply;
Command unit, it is coupled to this communication unit, for sending test parameters by this communication unit to this power supply;
Data processing unit, it is coupled to this communication unit, for the treatment of the measured value received by this communication unit to obtain test data; And
Pattern displaying unit, it is coupled to this data processing unit for this test data of display.
In one example, this ignition system test manager also comprises: data storage cell, and this data storage cell is coupled to this data processing unit for this test data of storage.
In one example, this Auto-Test System also comprises: frequency measuring equipment, and for the spark frequency measuring this ignition electric nozzle place, this communication unit is coupled to this frequency measuring equipment to receive this spark frequency by Serial Port Line.
In one example, this ignition electric nozzle is coupled by firing cable and this ignition exciter unit.
In one example, this ignition exciter unit is coupled to firing cable, this firing cable is coupled to the input of this ignition electric nozzle by single core cable, and this Auto-Test System also comprises: high voltage detector, and this high voltage detector is coupled to the input of this ignition electric nozzle to measure output voltage; And oscillograph, this oscillograph is coupled to this high voltage detector to receive this output voltage, and this communication unit is coupled to this oscillograph to receive this output voltage by Serial Port Line.
In one example, this ignition electric nozzle has sparking plug input connector for the input central electrode of drawing this ignition electric nozzle, this single core cable couples the central electrode of this sparking plug input connector and this firing cable, wherein, two probes of this high voltage detector are coupled to the shell of this sparking plug input connector and this ignition electric nozzle respectively to measure this output voltage.
In one example, Auto-Test System also comprises: current transformer, and this current transformer is coupled to this single core cable to measure output current, and this oscillograph is coupled to this current transformer to receive this output current and to be inputed to this communication unit.
In one example, the induction collar of this current transformer is passed by this single core cable to sense this output current.
In one example, this ignition exciter unit is coupled to firing cable, and this firing cable and this ignition electric nozzle disconnect, and this Auto-Test System also comprises: high voltage detector, and this high voltage detector is coupled to this firing cable to measure output voltage; And oscillograph, this oscillograph is coupled to this high voltage detector to receive this output voltage, and this communication unit is coupled to this oscillograph to receive this output voltage by Serial Port Line.
In one example, two of this high voltage detector probes are coupled to the shell of this firing cable and central electrode respectively to measure this output voltage.
In one example, this data processing unit is coupled to this command unit, this data processing unit is also for exceeding threshold triggers fault-signal in response to this test data, and this command unit sends to this power supply order of cutting off the electricity supply by this communication unit in response to this fault-signal.
In one example, at least one during this test parameters comprises between testing site, the supply voltage of each testing site and frequency of supply, testing site place conduction time, two testing sites power-off time.
The utility model, for the deficiencies in the prior art, proposes a kind of aero-engine ignition system Auto-Test System.Carrying out, in ignition system conventional func performance process of the test, can automatically completing corresponding test, and recording test data in whole process of the test with completing.Relative to conventional art, its improvement is testing crew is liberated from manual labor, after simply test parameters is set, testing stand can complete whole process of the test automatically, comprises the Stateful Inspection etc. in the control of ignition system supply voltage and frequency, the control of power supply break-make, the process of test data, the record of test data and whole process of the test.
Improve test efficiency according to Auto-Test System of the present utility model, save test period, can Real-Time Monitoring ignition system duty, ensure that experimental safe carries out.And can food preservation test condition (comprising the information such as testing site, the voltage at testing site place and frequency), test data (comprising the information such as input current, spark frequency, output current, output voltage and spark energy) automatically, for the Performance Evaluation of ignition system, performance change trend analysis and design improvement bring data supporting.
Accompanying drawing explanation
After the detailed description of reading embodiment of the present disclosure in conjunction with the following drawings, more can understand above-mentioned feature and advantage of the present utility model better.
Fig. 1 shows the block diagram of the test structure of the Auto-Test System for aero-engine ignition system according to one side of the present utility model;
Fig. 2 shows the block diagram of another test structure of the Auto-Test System for aero-engine ignition system according to one side of the present utility model;
Fig. 3 shows the block diagram of another test structure of the Auto-Test System for aero-engine ignition system according to one side of the present utility model.
For clarity sake, the brief description of Reference numeral is below provided:
100: Auto-Test System
110: ignition system test manager
111: communication unit
112: command unit
113: data processing unit
114: pattern displaying unit
115: data storage cell
120: power supply
130: current testing device
140: frequency measuring equipment
150: high voltage detector
160: current transformer
161: the induction collar of current transformer
170: oscillograph
200: ignition system
210: ignition exciter unit
220: ignition electric nozzle
221: central electrode
222: sparking plug input connector
230: firing cable
231: central electrode
240: single core cable
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail.Note, the aspects described below in conjunction with the drawings and specific embodiments is only exemplary, and should not be understood to carry out any restriction to protection domain of the present utility model.
In view of the above-mentioned defect of prior art, ignition system test manager is had according to Design of Automatic Test System of the present utility model, when function test, the information such as the duration of ignition, firing interval, supply voltage and frequency of supply can be set, and the break-make of automatic control ignition power supply completes whole process of the test, record the input current in process of the test and spark frequency simultaneously.Whole process of the test can complete continuous ignition function test and cycle igniting function test continuously, and can real time monitoring input current in experimentation, can cut off igniting power supply, to protect ignition system as input current exceeds threshold value.
When performance test, ignition system test manager can set the information such as the time interval between the supply voltage of testing site and frequency, the power-on time of testing site, testing site, and the break-make of automatic control ignition system power supply power supply completes whole process of the test, record the information such as input current, spark frequency, output voltage and the output current in process of the test simultaneously.Ignition system test manager can have protection mechanism.Carry out in spark frequency and output current performance test process can real time monitoring input current, igniting power supply can be cut off, to protect ignition system as input current exceeds threshold value.Carry out in output voltage performance process can real time monitoring input current and output voltage, igniting power supply can be cut off, to protect ignition system as input current and the arbitrary numerical value of output voltage exceed corresponding threshold value.Carry out in output current and fiery energy characteristics process of the test can real time monitoring input current and output current, igniting power supply can be cut off, to protect ignition system as input current and the arbitrary numerical value of output current exceed corresponding threshold value.
Fig. 1 shows the block diagram of the test structure of the Auto-Test System 100 for aero-engine ignition system 200 according to one side of the present utility model.This test structure can be used for the test of ignition system continuous ignition and cycle and to light a fire function test and input current and spark frequency performance test.
As shown in Figure 1, ignition system 200 can comprise ignition exciter unit 210 and ignition electric nozzle 220.In normal work, ignition electric nozzle 220 couples by firing cable and ignition exciter unit 210.
Auto-Test System 100 can comprise ignition system test manager 110, and the function of the latter mainly sets test parameters to complete automatic test.Auto-Test System 100 also can comprise power supply 120 provides power supply energy for for ignition system 200, wherein provides the major parameter of power supply energy to be supply voltage and frequency of supply.Power supply switch can be comprised to control the break-make of power supply in power supply 120.
Auto-Test System 100 also can comprise the corresponding measurement mechanism for measurement target value.Depend on different measurement target values, various measurement mechanism can be had.As shown in Figure 1, in function test of lighting a fire for the test of ignition system continuous ignition and cycle, and in the framework of input current and spark frequency performance test, Auto-Test System 100 can comprise current measuring device 130 and frequency measuring equipment 140.
Current measuring device 130 can be arranged between power supply 120 and ignition exciter unit 210, is used for the input current of measurement point ignition system 200.Namely current measuring device 130 itself can show size of current.Frequency measuring equipment 140 can be used for the spark frequency measuring ignition electric nozzle 220 place.
Ignition system test manager 110 can comprise communication unit 111, command unit 112, data processing unit 113, pattern displaying unit 114 and data processing unit 115.In outside, communication unit 111 is coupled to power supply 120, current measuring device 130 and frequency measuring equipment 140 by Serial Port Line.In inside, communication unit 111 can be coupled to command unit 112 and data processing unit 113.Command unit 112 sends the order of power supply break-make by communication unit 111 to power supply 120.Especially, command unit 112 sends test parameters by communication unit 111 to power supply 120, such as supply voltage and frequency of supply.Power supply 120 feeds back to the actual supply voltage that provides of ignition system 200 and frequency of supply in real time by communication unit 111.Current measuring device 130 and frequency measuring equipment 140 can feed back respectively to communication unit 111 input current and spark frequency that record.
Data processing unit 113 can process the measured value that communication unit 111 receives, such as amplification, filtering, denoising etc., to obtain test data, and this test data is supplied to pattern displaying unit 114 for display.Test data also can be stored in data storage cell 115 by data processing unit 113.More preferably, data processing unit 113 also can when test data exceeds threshold value trigger fault signal.Such as when test data exceedes the scope of its regulation, or when supply voltage or frequency exceed the scope of ignition system 200 requirement, fault-signal can be sent to command unit 112.Command unit 112 can send to power supply 120 order of cutting off the electricity supply in response to fault-signal.
Framework as shown in Figure 1 can be used for into the continuous ignition of ignition system and cycle igniting function test, and input current and spark frequency performance test.During test, ignition exciter unit 210, firing cable 230 are connected with ignition electric nozzle 220, and access current measuring device 130 at the power input of power supply 120 output and ignition exciter unit 210, and frequency measuring equipment 140 is placed on the rational position that can sense that ignition electric nozzle 220 discharges.Respectively power supply 120, current measuring device 130 and frequency measuring equipment 140 are connected to ignition system test manager 110 finally by Serial Port Line.
Before beginning continuous ignition function test, the voltage and frequency and power supply 120 power-on time that power supply 120 exports is set by command unit 112.After command unit 112 sends power supply ' connection ' order to power supply 120, start continuous ignition test.In process of the test, power supply 120 can the supply voltage of current reality and frequency transmission to ignition system test manager 110.Current measuring device 130 Real-time Collection input current data transfer to ignition system test manager 110, same frequency measuring equipment 140 Real-time Collection spark frequency by data transfer to ignition system test manager 110.Simultaneously data processing unit 113 can process supply voltage, frequency of supply, input current, spark frequency, and the test data obtained after process to occur to data storage cell 115 with food preservation test data, pattern displaying unit 114 to watch Test Information state simultaneously.If find in data handling procedure that supply voltage or frequency exceed its threshold value, data processing unit 113 can send fault-signal to command unit 112, and then command unit 112 can send to power supply 120 switch command of cutting off the electricity supply.
Before the igniting of beginning cycle function test, input current and spark frequency performance test, test can be set by command unit 112 and count, the supply voltage of each testing site and frequency, testing site place conduction time, the power-off time between two testing sites.Good test parameters post command unit 112 to be placed sends ' connection ' order to power supply 120, starts test.Data processing in process of the test, storage, display and troubleshooting are tested identical with continuous ignition.
Fig. 2 shows the block diagram of another test structure of the Auto-Test System 100 for aero-engine ignition system 200 according to one side of the present utility model.This test structure can be used for ignition system output current and spark energy performance test.
As shown in Figure 2, in order to execution point ignition system output current and spark energy performance test, the oscillograph 170 that Auto-Test System 100 also can comprise high voltage detector 150, current transformer 160 and couple with both.High voltage detector 150 can be coupled to the input of ignition electric nozzle 220 to measure output voltage, and current transformer 160 can be used for measuring output current.Oscillograph 170 can receive from the output current of current transformer 160 and high voltage detector 150 and output voltage and can show the numerical values recited of this output current and output voltage.Meanwhile, oscillograph 170 is also coupled to communication unit 111 by Serial Port Line, thus output current and output voltage signal can be passed to ignition system test manager 110 by Serial Port Line.
Framework as shown in Figure 2 can be used for ignition system output current and spark energy performance test.During test, ignition exciter unit 210 is connected with firing cable 230.Drawn by the input central electrode 221 of sparking plug input connector 222 by ignition electric nozzle 220.Connect center pole 231 and the sparking plug input connector 222 of firing cable 230 with single core cable 240, in connection procedure, make sparking plug input connector 222 through the collar 161 of current transformer 160.Two probes of high voltage detector 150 are connected respectively to the shell of sparking plug input connector 222 and ignition electric nozzle 220.
Between power supply 120 output and the power input of ignition exciter unit 210, access current measuring device 130, and frequency measuring equipment 140 is placed on the rational position that can sense that ignition electric nozzle 220 discharges.Respectively power supply 120, current measuring device 130, frequency measuring equipment 140 and oscillograph 170 are connected to the communication unit 111 of ignition system test manager 110 finally by Serial Port Line.
Before beginning output current and spark energy, can parameters by command unit 112, comprise test and count, the supply voltage of each testing site and frequency, testing site place conduction time, the power-off time etc. between two testing sites.Good test parameters post command unit 112 to be placed can send ' connection ' order to power supply 120, starts test.Data processing unit 113 can process supply voltage, frequency of supply, input current, output current, output voltage and spark frequency simultaneously, comprises according to formula
calculate spark energy, the test data after process to occur to data storage cell 115 with food preservation test data, pattern displaying unit 114 to watch Test Information state simultaneously.If find in data handling procedure that supply voltage or frequency exceed its threshold value, data processing unit 113 can send fault-signal to command unit 112, and then command unit 112 can send to power supply 120 switch command of cutting off the electricity supply.
Fig. 3 shows the block diagram of another test structure of the Auto-Test System 100 for aero-engine ignition system 200 according to one side of the present utility model.This test structure can be used for the output voltage performance test of ignition system.
Firing cable 230 is when connecing ignition electric nozzle (see Fig. 1,2) and not connecing ignition electric nozzle 220, and output voltage difference is larger.Due to the electric discharge of ignition electric nozzle 220, sizable output voltage can be discharged.The output voltage performance test of ignition system to measure the output voltage when not having ignition electric nozzle 220 release voltage.
During test, ignition exciter unit 210 is connected with firing cable 230, but firing cable 230 and ignition electric nozzle disconnect.Current measuring device 130 is accessed between power supply 120 output and the power input of ignition exciter unit 210.Two probes of high voltage detector 150 are connected respectively to the shell of firing cable 230 and the central electrode 231 of firing cable 230.High voltage detector 150 is connected with oscillograph 170.Respectively power supply 120, current measuring device 130 and oscillograph 170 are connected to the communication unit 111 of ignition system test manager 110 finally by Serial Port Line.
Before beginning output voltage performance test, by the supply voltage of command unit 112 set-point ignition system power supply 120 and frequency and power supply 120 power-on time.Command unit 112 sends ' connection ' order to power supply 120, starts continuous ignition test.In process of the test, power supply 120 can the supply voltage of current reality and frequency transmission to ignition system test manager 110, and high voltage detector 150 Real-time Collection output voltage is transferred to ignition system test manager 110.Output data processing in process of the test, storage, display and troubleshooting are tested identical with continuous ignition.
Auto-Test System of the present utility model makes ignition system conventional func performance test form automatically become a kind of possibility from manually becoming.Not only can control point ignition system trystate in real time in process of the test, and provide more Data support for ignition system Performance Evaluation, performance change trend analysis and design improvement.Simultaneously can go out oneself ignition system functional performance Testing Software applicable, to meet the needs of self-flare system test according to architecture design herein.Give three kinds of more typical examples in literary composition more all sidedly, but those skilled in the art can design according to real needs the test structure meeting self-demand.
Those skilled in the art will understand, and the various illustrative logical blocks, module, circuit and the step that describe in conjunction with embodiment disclosed herein can be embodied as electronic hardware, computer software or the combination of both.Various illustrative components, frame, module, circuit and step are done vague generalization above with its functional form and are described.This type of functional design constraint specifically how realizing depending on embody rule and put on total system.Technical staff can realize described functional by different modes for often kind of application-specific, but such realize decision-making and should not be interpreted to and cause having departed from scope of the present invention.
Description before providing is to make any technical staff in this area all can put into practice various aspects described herein.But should be appreciated that, protection domain of the present utility model should be as the criterion with claims, and should not be defined to concrete structure and the assembly of above explained orally embodiment.Those skilled in the art, in spirit and scope of the present utility model, can carry out various variation and amendment to each embodiment, and these variations and amendment also drop within protection domain of the present utility model.
Claims (12)
1. for an Auto-Test System for aero-engine ignition system, described aero-engine ignition system comprises ignition exciter unit, firing cable and ignition electric nozzle, it is characterized in that, described Auto-Test System comprises:
Power supply, for providing power supply energy to ignition system;
Current measuring device, it is coupled to the input current for measurement point ignition system between described power supply and described ignition exciter unit; And
Ignition system test manager, comprising:
Communication unit, it couples receive actual power voltage and frequency of supply and couple to receive described input current with described current measuring device by Serial Port Line and described power supply;
Command unit, it is coupled to described communication unit, for sending test parameters by described communication unit to described power supply;
Data processing unit, it is coupled to described communication unit, for the treatment of the measured value received by described communication unit to obtain test data; And
Pattern displaying unit, it is coupled to described data processing unit for the described test data of display.
2., as claimed in claim 1 for the Auto-Test System of aero-engine ignition system, it is characterized in that, described ignition system test manager also comprises:
Data storage cell, described data storage cell is coupled to described data processing unit for the described test data of storage.
3., as claimed in claim 1 for the Auto-Test System of aero-engine ignition system, it is characterized in that, also comprise:
Frequency measuring equipment, for the spark frequency measuring described ignition electric nozzle place, described communication unit is coupled to described frequency measuring equipment to receive described spark frequency by Serial Port Line.
4., as claimed in claim 3 for the Auto-Test System of aero-engine ignition system, it is characterized in that, described ignition electric nozzle is coupled by firing cable and described ignition exciter unit.
5. as claimed in claim 3 for the Auto-Test System of aero-engine ignition system, it is characterized in that, described ignition exciter unit is coupled to firing cable, and described firing cable is coupled to the input of described ignition electric nozzle by single core cable, and described Auto-Test System also comprises:
High voltage detector, described high voltage detector is coupled to the input of described ignition electric nozzle to measure output voltage; And
Oscillograph, described oscillograph is coupled to described high voltage detector to receive described output voltage, and described communication unit is coupled to described oscillograph to receive described output voltage by Serial Port Line.
6. as claimed in claim 5 for the Auto-Test System of aero-engine ignition system, it is characterized in that, described ignition electric nozzle has sparking plug input connector for the input central electrode of drawing described ignition electric nozzle, described single core cable couples the central electrode of described sparking plug input connector and described firing cable
Wherein, two probes of described high voltage detector are coupled to the shell of described sparking plug input connector and described ignition electric nozzle respectively to measure described output voltage.
7., as claimed in claim 5 for the Auto-Test System of aero-engine ignition system, it is characterized in that, also comprise:
Current transformer, described current transformer is coupled to described single core cable to measure output current, and described oscillograph is coupled to described current transformer to receive described output current and to be inputed to described communication unit.
8. as claimed in claim 7 for the Auto-Test System of aero-engine ignition system, it is characterized in that, the induction collar of described current transformer is passed by described single core cable to sense described output current.
9., as claimed in claim 1 for the Auto-Test System of aero-engine ignition system, it is characterized in that, described ignition exciter unit is coupled to firing cable, and described firing cable and described ignition electric nozzle disconnect, and described Auto-Test System also comprises:
High voltage detector, described high voltage detector is coupled to described firing cable to measure output voltage; And
Oscillograph, described oscillograph is coupled to described high voltage detector to receive described output voltage, and described communication unit is coupled to described oscillograph to receive described output voltage by Serial Port Line.
10. as claimed in claim 9 for the Auto-Test System of aero-engine ignition system, it is characterized in that, two probes of described high voltage detector are coupled to the shell of described firing cable and central electrode respectively to measure described output voltage.
11. as claimed in claim 1 for the Auto-Test System of aero-engine ignition system, it is characterized in that, described data processing unit is coupled to described command unit, described data processing unit is also for exceeding threshold triggers fault-signal in response to described test data, and described command unit sends to described power supply order of cutting off the electricity supply by described communication unit in response to described fault-signal.
12. as claimed in claim 1 for the Auto-Test System of aero-engine ignition system, it is characterized in that, described test parameters comprises at least one in the power-off time between testing site, the supply voltage of each testing site and frequency of supply, testing site place conduction time, two testing sites.
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| CN201420734986.0U CN204299767U (en) | 2014-11-28 | 2014-11-28 | For the Auto-Test System of aero-engine ignition system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107367645A (en) * | 2017-06-12 | 2017-11-21 | 中国航发哈尔滨东安发动机有限公司 | A kind of method of testing of ignition device energy |
| CN108051217A (en) * | 2017-11-30 | 2018-05-18 | 四川泛华航空仪表电器有限公司 | The online fault detection method of aero-engine ignition driver |
| CN113932248A (en) * | 2021-11-10 | 2022-01-14 | 四川泛华航空仪表电器有限公司 | Aeroengine plasma ignition system comprehensive test device |
-
2014
- 2014-11-28 CN CN201420734986.0U patent/CN204299767U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107367645A (en) * | 2017-06-12 | 2017-11-21 | 中国航发哈尔滨东安发动机有限公司 | A kind of method of testing of ignition device energy |
| CN108051217A (en) * | 2017-11-30 | 2018-05-18 | 四川泛华航空仪表电器有限公司 | The online fault detection method of aero-engine ignition driver |
| CN108051217B (en) * | 2017-11-30 | 2019-09-17 | 四川泛华航空仪表电器有限公司 | The online fault detection method of aero-engine ignition driver |
| CN113932248A (en) * | 2021-11-10 | 2022-01-14 | 四川泛华航空仪表电器有限公司 | Aeroengine plasma ignition system comprehensive test device |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |