CN207892709U - Aero-engine ignition driver with online fault detection system - Google Patents
Aero-engine ignition driver with online fault detection system Download PDFInfo
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- CN207892709U CN207892709U CN201721640340.6U CN201721640340U CN207892709U CN 207892709 U CN207892709 U CN 207892709U CN 201721640340 U CN201721640340 U CN 201721640340U CN 207892709 U CN207892709 U CN 207892709U
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Abstract
The utility model discloses the aero-engine ignition drivers with online fault detection system, it is connect with engine control system, including being arranged the working condition for on-line checking ignition exciter unit, the online fault detection system of fault condition are connected in power input and the low tension terminal being connect with input power and the control circuit that the high tension terminal in output end and ignition electric nozzle connection is arranged and is arranged between low tension terminal and high tension terminal, the control circuit.The utility model can be monitored working condition, the fault condition for the ignition exciter unit being already installed in aero-engine, it can be with the failure for detecting ignition exciter unit of quickness and high efficiency, to debug in time, and then improve complete rate, the success rate of the rate of attendance and task execution of aero-engine and aircraft.
Description
Technical field
The utility model is related to aero-engine fault detection technique fields, and in particular to have online fault detection system
Aero-engine ignition driver.
Background technology
Aero-engine ignition driver（Hereinafter referred to as ignition exciter unit）It is the important component of engine, ignition exciter unit
Ignition system is formed with together with firing cable, ignition electric nozzle, for engine start or reinforcing electric ignition.Modern Aviation is jet-propelled
Engine is mostly to use high pressure high-energy ignition driver, and storage energy is in 4J or more.The major function of ignition exciter unit is
Low-voltage direct/the alternating current come will be transmitted on ground or machine and is converted to high-voltage pulse electric, and high-voltage pulse electric is passed by firing cable
It is defeated to arrive ignition electric nozzle, high energy electric spark is generated at ignition electric nozzle ignition end, with the indoor gas mixture of ignition engine burning.
Aerial ignition device ignition failure is always one of the typical fault in aircraft maintenance.According to the structure of aerial ignition device
At the main source of aerial ignition device ignition failure includes three aspects：（1）Ignition exciter unit internal fault；（2）Harness
Failure；（3）Ignition electric nozzle failure.And wherein main ignition operation circuit, electric appliance are first since inside is equipped with for ignition exciter unit
Part is more, and working environment is severe, results in it and is easiest to break down, and fault type is most complicated.The failure mould of ignition exciter unit
Formula can be divided into 3 kinds：Ignition exciter unit is abnormal without output, ignition exciter unit output frequency exception, ignition exciter unit output energy.
As aircraft run time increases, the ignition exciter unit of aero-engine will appear reduced performance or even cause first device
The generation of part damage, can all have an impact spark energy, spark frequency etc., cause that spark rate is not normal, ignition energy is small, puts
The failures such as piezoelectric voltage deficiency, serious to cause to light a fire unsuccessful, and these failures can be reacted to greatly the phase of firing circuit
It answers in electrical characteristics.These failure problems reduce engines ground and aerial starting performance.So the performance of ignition exciter unit
Reliability, the success rate etc. of engine ignition are directly affected, and then affects the complete rate of aero-engine and aircraft, turn out for work
The success rate of rate and task execution.
Traditional aero-engine ignition driver lacks to effective online fault detection method, it is difficult to having pacified
Working condition, the fault condition of ignition exciter unit in aero-engine are monitored, and result in traditional aeroplane engine
Machine ignition exciter unit is difficult to find in time, excludes the ignition exciter unit failure being already installed in aero-engine, and then influences
Affect the success rate of aero-engine and complete rate, the rate of attendance and the task execution of aircraft.For faulty igniter,
Many aircraft engine maintenance companies directly more renew the processing mode of igniter using the faulty igniter of discarding, cause
The great wasting of resources.
Utility model content
The utility model is directed to traditional aero-engine ignition driver, provides a kind of with online fault detection system
Aero-engine ignition driver, can be to being already installed on working condition, the failure of the ignition exciter unit in aero-engine
Situation is monitored, can be with the failure for detecting ignition exciter unit of quickness and high efficiency, to debug in time, and then improves boat
The complete rate of empty engine and aircraft, the success rate of the rate of attendance and task execution.
Aero-engine ignition driver provided by the utility model with online fault detection system, with engine control
System connection processed, technical solution are：The ignition exciter unit includes being arranged in power input and being connect with input power
Low tension terminal and be arranged the high tension terminal being connect with ignition electric nozzle in output end and be arranged in low tension terminal and high pressure
Control circuit between binding post, the control circuit are connected with the working condition for on-line checking ignition exciter unit, failure
The online fault detection system of situation.
The online fault detection system includes the first test point being arranged on ignition exciter unit internal circuit, the second survey
Pilot, third test point, the 4th test point, the first detection decision circuit, the second detection decision circuit, the first detection judgement
Circuit is connect with the first test point, the second test dot circuit, and the second detection decision circuit is surveyed with third test point, the 4th
Pilot circuit connects, and the first detection decision circuit is connect with engine control system with the second detection decision circuit.
The control circuit include the suppressor being connect with low tension terminal, the transformer T1 being connect with suppressor it is primary,
Energy-storage capacitor, safe Resistance R6, discharge tube G1, high frequency oscillation capacitance C6 and the high frequency transformation being connect with T1 grade of transformer
Device T2；The energy-storage capacitor and high frequency transformer T2 primary are connected to the both ends of discharge tube G1；The high frequency transformer
T2 primary and safe Resistance R6 are connected to high frequency oscillation capacitance both ends, and the high frequency transformer secondary connects with ignition electric nozzle
It connects.
First test point, the second test point are separately positioned between low tension terminal positive and negative end and suppressor
On circuit, it is whether normal that ignition exciter unit power input is tested by the first detection decision circuit.The third test point setting
On the circuit of safe Resistance R6, the size of current that safe Resistance R6 is tested by the second detection decision circuit judges ignition stimuli
Device whether failure.The 4th test point for testing ignition exciter unit output pulse electric frequency and size of current is arranged in height
On circuit between frequency power transformer and ignition electric nozzle, ignition exciter unit output current size is tested by the second detection decision circuit
Judge whether ignition exciter unit output is normal.
It is described first detection decision circuit include concatenated diode D1, the first divider resistance R1, the second divider resistance R2,
Adjustable resistance R3, current transformer L1；Engine of the adjustable resistance R3 connections for exporting adjustable resistance R3 voltage signals
Control system.The first detection decision circuit is in parallel with input power from the first test point, the second test point, and electric current is through two poles
Pipe D1, the first divider resistance R1, adjustable resistance R2, the second divider resistance R3, current transformer forming circuit.
The first divider resistance R1 and the second concatenated resistance values of divider resistance R3 are consistently greater than adjustable resistance R2
Resistance, avoid test circuit from consuming relatively high power, the voltage on test adjustable resistance R2.This voltage signal is exported to hair
Motivation control system is judged that if voltage signal is in the voltage range that power supply normally inputs, voltage swing is normal, otherwise
It is exactly abnormal.
Further, the first detection decision circuit further includes and concatenated first optocouplers of current transformer L1 and first
Counter, first optocoupler and the first counter are connect with engine control system, for whether testing input power frequency
Normally.By current transformer L1 output pulse signals, pulse frequency is the frequency of input power, which passes through
One optocoupler and the first counter can obtain the frequency values of power input, and frequency values are exported to engine control system and are sentenced
It is disconnected, otherwise it is exactly abnormal if the frequency values, in the range of power input, the frequency of input power is normal.
So the voltage swing and frequency when input power have any exception, the input electricity of ignition system can be judged
Source is abnormal.
The second detection decision circuit includes the current transformer L2 for being connected to third test point, is connected to the 4th test
The current transformer L3 of point；The current transformer L2 and current transformer L3 are connect with engine control system, and output is online
The current value of acquisition, the second detection decision circuit further include being counted with concatenated second optocouplers of current transformer L3, second
Device, second optocoupler and the second counter are connect with engine control system, export the frequency values of online acquisition.
When ignition exciter unit works normally, the energy of energy-storage capacitor is largely exported by ignition electric nozzle, then is passed through
The electric current of safe Resistance R6 is smaller, i.e. the current transformer L2 of third test point connection exports low voltage signal, according to voltage
Size can be determined that output circuit is normal in ignition exciter unit, and ignition exciter unit by the smaller of the electric current of safe Resistance R6
Output has high-voltage pulse electric, i.e. the current transformer L3 of the 4th test point connection to detect voltage.When ignition exciter unit output is opened
When the failure of road, then the energy on energy-storage capacitor is discharged by the circuit that safe Resistance R6 is formed, so passing through safe Resistance R6
Electric current it is larger, i.e., third test point connection current transformer L2 output HIGH voltage signals, can be sentenced according to the size of voltage
Surely by the larger of the electric current of safe Resistance R6, and the current transformer L3 of the 4th test point connection can't detect voltage, judge
Ignition exciter unit exports failure.
Further, the second optocoupler and the second counter string of the current transformer L3 and output engine control system
It is abnormal with the presence or absence of output frequency can also to detect ignition exciter unit for testing size of the 4th test point by electric current for connection.
The current transformer L3 of the 4th test point connection connects with the second optocoupler, the second counter, makes the low electricity of output
Pressure signal obtains the output frequency of ignition exciter unit by the second optocoupler, the second counter.This signal is output to engine
Control system, engine control system can obtain the output frequency of ignition exciter unit.It is powered in ignition exciter unit, power supply
Under the premise of input is normal, by the testing current to third test point and the 4th test point, we can be determined that ignition exciter unit
Whether failure.
The online fault detection system is additionally provided with the buzzer being connect with engine control system, works as ignition exciter unit
There is electric current, electricity in any one or more test points in first test point, the second test point, third test point, the 4th test point
When pressure or frequency occur abnormal, prompt is made a sound, reminds staff.
The suppressor is the composite filter being composed of choke coil and feedthrough capacitor, can effectively filter space flight and start
The low-frequency disturbance and High-frequency Interference that intensive electronic device is formed on machine reduce the probability that ignition exciter unit breaks down.
Aero-engine ignition driver provided by the utility model with online fault detection system is provided with four
Test point monitors the power input voltage of ignition exciter unit, frequency and electric power outputting current, frequency on-line, can be to aviation
Engine ignition driver carries out online fault detect, can be to being already installed on the work of the ignition exciter unit in aero-engine
State, fault condition are monitored, and can greatly reduce aeroplane engine with the failure for detecting ignition exciter unit of quickness and high efficiency
The artificial and time loss of machine ignition exciter unit fault detect, improve the complete rate of aero-engine and aircraft, the rate of attendance and
The success rate of task execution.
Description of the drawings
Fig. 1 is the utility model circuit diagram；
Fig. 2 is that the utility model first detects decision circuit schematic diagram；
Fig. 3 is that the utility model second detects decision circuit schematic diagram；
In figure, the 1-the first test point, the 2-the second test point, 3-third test points, the 4-the four test point.
Specific implementation mode
The utility model is described in further detail with reference to embodiment, but the embodiment of the utility model is not
It is limited to this.
Embodiment 1
High pressure high-energy ignition driver is widely used that in aero-engine at present（Energy storage type igniter）, with certain type
For the energy storage type ignition system of low-voltage alternating-current input, the ignition system major parameter is as follows：
（a）Power input：110~115V/380~420Hz；
（b）Output voltage：Voltage peak is not less than 15kV；
（c）Peak point current；Not less than 2000A；
（d）Spark frequency：2±0.5Hz.
Including being arranged in power input and the low tension terminal that is connect with input power and setting in output end and igniting
The high tension terminal of sparking plug connection and the control circuit being arranged between low tension terminal and high tension terminal, the control electricity
Road is connected with the working condition for on-line checking ignition exciter unit, the online fault detection system of fault condition.
The circuit element of the control circuit includes mainly：
Suppressor：Filter inductance L01, L02 and feedthrough capacitor C01, C02 including being connected to power input, play electricity
Adjustment effect is flowed, the input power and spark efficiency of ignition exciter unit are controlled；And can prevent ignition exciter unit low frequency signal,
High-frequency signal pours into aircraft power system, interferes other equipment；
Transformer T1：Including armature winding and secondary windings, the alternating current of 110~115V is increased to 2120V or so；
High diode temperature D2, D3：For carrying out rectification and multiplier electrode to AC signal；
Storage capacitor C5：For energy storage；
Times voltage capacitance C4, C3：For charging to storage capacitor C5；
Discharge resistance R5：For when ignition exciter unit powers off, the residual charge in storage capacitor C5 gradually to be bled off, hinder
Value is very big, and its effect very little in igniter normal work；
Current-limiting resistance R4：Charging current for limiting capacitance C3；
Safe Resistance R6：Charging current for limiting high frequency oscillation capacitance C6；
High frequency transformer T2；
High frequency oscillation capacitance C6：For energy storage, disruptive discharge pipe G1 and pass through high frequency transformer T2 perforation ignition sparking plugs, shape
At firing circuit access.
Discharge tube G1：It is to separate ignition electric nozzle circuit and storage capacitor C5, when making sparking plug operation conditions change, can makes
Storage capacitor C6 is charged to defined breakdown voltage, is not influenced by ignition electric nozzle operating condition；
Safe Resistance R6：Resistance is very big, is to make discharge tube G1 direct feelings to the voltage of storage capacitor C5, can be in high frequency
When transformer T2 and a times voltage capacitance C3 fall off, a discharge channel is provided for storage capacitor C5, C5 is prevented to be charged to danger always
And the voltage value of safety and breakdown storage capacitor C5.
Its specific work process is：When ignition exciter unit power input, when on secondary windings induced voltage be it is upper rectify, under
When end is negative, the high diode temperature D3 conductings before arriving of voltage wave crest, high diode temperature D2 cut-offs, to voltage capacitance C4 again, energy storage electricity
Hold C5, the branch charging that times voltage capacitance C3 is connected into；After voltage crosses wave crest sometime, the voltage on times voltage capacitance C3
More than secondary windings output voltage, high diode temperature D2 conductings, high diode temperature D3 ends, and a times voltage capacitance C3 passes through storage capacitor
Through secondary winding charge, a times voltage capacitance C4 continues to charge to storage capacitor C5 C3；When on secondary windings induced voltage be upper end it is negative,
Lower end timing, the high diode temperature D2 conductings before arriving of voltage wave crest, high diode temperature D3 cut-offs, to voltage capacitance C4, energy storage again
The branch charging that capacitance C5, times voltage capacitance C3 are connected into；After voltage crosses wave crest sometime, the electricity on times voltage capacitance C4
Pressure is more than secondary windings output voltage, and high diode temperature D3 conductings, high diode temperature D2 cut-offs, it is electric that times voltage capacitance C4 passes through energy storage
Hold C5 through secondary winding charge, a times voltage capacitance C3 continues to charge to storage capacitor C5；Secondary windings induced voltage positive-negative half-cycle is handed over
For progress, no matter how induced voltage direction changes, and storage capacitor C5 is in charged state always, and voltage rises to become in interruption
Gesture.It charges to high frequency oscillation capacitance C6 simultaneously also by high frequency transformer T2 primary and safe Resistance R6.With charging time
Several increases, the voltage on storage capacitor C5, high frequency oscillation capacitance C6 are gradually increasing.High frequency oscillation capacitance C6 rises to discharge tube
When the threshold voltage of G1, then can disruptive discharge pipe G1 enter electric discharge link, the voltage on high frequency oscillation capacitance C6 is applied to T2's
Primary, secondarily grade generation（15~20）The high pressure of kV, perforation ignition sparking plug so that the electric energy stored on storage capacitor C5 passes through
The discharge path electric discharge that discharge tube G1, T2 grade of high frequency transformer, firing cable, ignition electric nozzle are formed, while in ignition electric nozzle
Ignition end formed electric discharge electric spark, complete igniting.
The ignition exciter unit further includes being mounted on working online situation, failure to ignition exciter unit in aero-engine
The online fault detection system of detection, the online fault detection system includes being arranged the first of ignition exciter unit internal circuit
Test point 1, the second test point 2, third test point 3, the 4th test point 4, first detection decision circuit, the second detection judgement electricity
Road, the first detection decision circuit are connect with the first test point 1,2 circuit of the second test point, the second detection judgement electricity
Road is connect with third test point 3,4 circuit of the 4th test point, and the first detection decision circuit and the second detection decision circuit are equal
It is connect with engine control system.
First test point 1, the second test point 2 are separately positioned on the positive and negative of ignition exciter unit internal electric source input circuit
Ignition exciter unit power input is tested in pole both ends whether normal by the first detection decision circuit.The third test point 3 is arranged
On safe Resistance R6, the 4th test point 4 is arranged on ignition exciter unit internal output circuit, and third test point 3 passes through second
The size of current of decision circuit test safe Resistance R6 is detected, the 4th test point 4 is tested by test the second detection decision circuit
Ignition exciter unit exports pulse electric frequency and size of current.
As shown in Fig. 2, the first detection decision circuit includes concatenated diode D1, the first divider resistance R1, second
Divider resistance R2, adjustable resistance R3, current transformer L1；The adjustable resistance R3 connections are for exporting adjustable resistance R3 voltages letter
Number engine control system.The first detection decision circuit from the first test point 1, the second test point 2 with input power simultaneously
Connection, electric current are formed back through diode D1, the first divider resistance R1, adjustable resistance R2, the second divider resistance R3, current transformer L1
Road.
The first divider resistance R1 and the second concatenated resistance values of divider resistance R3 are consistently greater than adjustable resistance R2
Resistance, avoid test circuit from consuming relatively high power, the voltage on test adjustable resistance R2.Meanwhile it can be by adjusting adjustable electric
The resistance value on R2 is hindered, the normal voltage signal of power input is adjusted within the scope of 1.1 ~ 1.2V, corresponding power input
Voltage is 110V ~ 115V, this voltage signal is exported to engine control system and is judged, if voltage signal 1.1 ~
In the voltage range of 1.2V, then voltage swing is normal, is otherwise exactly abnormal.
As shown in figure 3, the second detection decision circuit includes the current transformer L2 for being connected to third test point 3, connects
It is connected on the current transformer L3 of the 4th test point 4；The current transformer L2 and current transformer L3 output engines control system
System, the second counter output engine control system.
When ignition exciter unit works normally, the energy of energy-storage capacitor is largely exported by ignition electric nozzle, then is passed through
The electric current of safe Resistance R6 is smaller, i.e., the current transformer L2 that third test point 3 connects exports low voltage signal, according to voltage
Size can be determined that output circuit is normal in ignition exciter unit, and ignition exciter unit by the smaller of the electric current of safe Resistance R6
Output has high-voltage pulse electric, i.e. the current transformer L3 of the 4th test point 4 connection to export high voltage pulse.When ignition exciter unit exports
When open fault, then the energy on energy-storage capacitor is discharged by the circuit that safe Resistance R6 is formed, so passing through safe Resistance
The electric current of R6 is larger, i.e., the current transformer L2 output HIGH voltage signals that third test point 3 connects, can be with according to the size of voltage
Judgement passes through the larger of the electric current of safe Resistance R6, and the current transformer L3 of the 4th test point 4 connection can't detect pressure, judge
Ignition exciter unit exports failure.
The judgment method of the online failure detection result of ignition exciter unit is：
（1）First test point, the second test point voltage>1.2V or<1.1V, input supply voltage are abnormal；
（2）Third test point no current, ignition exciter unit failure；
（3）Third test point has electric current, the 4th test point to have electric current, ignition exciter unit normal；
（4）Third test point has electric current, and the 4th test point no current, ignition exciter unit is normal, rear class connection open circuit or electricity
Cable sparking plug failure；
（5）4th test point 4 has electric current, but current value is bigger than normal or less than normal when current value is worked normally compared with ignition exciter unit,
Ignition exciter unit failure.
Embodiment 2
The present embodiment is improved on the basis of embodiment 1, is theed improvement is that：The current transformer and company
The first optocoupler and the series connection of the first counter of engine control system are connect, it is whether normal for testing input power frequency.
By current transformer L1 output pulse signals, pulse frequency is the frequency of input power, which passes through the first light
Coupling and the first counter can obtain the frequency values of power input, and frequency values are exported to engine control system and are judged,
Otherwise it is exactly abnormal if the frequency values, in the range of 380~420 Hz, the frequency of input power is normal.
So the voltage swing and frequency when input power have any exception, we can judge the defeated of ignition system
Enter abnormity of power supply.
The current transformer L3 connects with the second optocoupler of output engine control system and the second counter, for surveying
Size of the 4th test point 4 by electric current is tried, it is abnormal with the presence or absence of output frequency that ignition exciter unit can also be detected.
The current transformer L3 of 4th test point 4 connection connects with the second optocoupler, the second counter, makes the low electricity of output
Pressure signal obtains the output frequency of ignition exciter unit by the second optocoupler, the second counter.This signal is output to engine
Control system, engine control system can obtain the output frequency of ignition exciter unit.It is powered in ignition exciter unit, power supply
Under the premise of input is normal, by the testing current to third test point 3 and the 4th test point 4, we can be determined that ignition stimuli
Device whether failure.
The specific detection method of the online fault detection system of the ignition exciter unit is：
（1）First test point 1,2 voltage of the second test point>1.2V or<1.1V, input supply voltage are abnormal；
（2）First test point 1,2 pulse frequency of the second test point>420 Hz or<380 Hz, input power frequency are different
Often；
（3）3 no current of third test point, ignition exciter unit failure；
（4）Third test point 3 has electric current, the 4th test point 4 to have electric current, ignition exciter unit normal；
（5）Third test point 3 has electric current, and 4 no current of the 4th test point, ignition exciter unit is normal, rear class connection open circuit or
Cable sparking plug failure；
（6）4th test point 4 has electric current, but current value is bigger than normal or less than normal when current value is worked normally compared with ignition exciter unit,
Ignition exciter unit failure；
（7）4th test point, 4 pulse frequency is abnormal, ignition exciter unit failure；
Other parts are substantially the same manner as Example 1 in the present embodiment, therefore no longer repeat one by one.
The above is only the preferred embodiment of the utility model, not does limit in any form to the utility model
System, any simple modification made by the above technical examples according to the technical essence of the present invention, equivalent variations, each falls within
Within the scope of protection of the utility model.
Claims (8)
1. the aero-engine ignition driver with online fault detection system, connect, including set with engine control system
Set power input and connect with input power low tension terminal, the high-voltage connecting being connect with ignition electric nozzle in output end is set
Terminal and the control circuit being arranged between low tension terminal and high tension terminal, it is characterised in that：The control circuit connects
It is connected to the working condition for on-line checking ignition exciter unit, the online fault detection system of fault condition；The online failure
Detecting system includes the first test point of setting on the control circuitry（1）, the second test point（2）, third test point（3）, the 4th
Test point（4）, the first detection decision circuit, the second detection decision circuit, the first detection decision circuit and the first test point
（1）, the second test point（2）Circuit connects, the second detection decision circuit and third test point（3）, the 4th test point（4）Electricity
Road connects；The first detection decision circuit is connect with engine control system with the second detection decision circuit；The control
Circuit includes the suppressor being connect with low tension terminal, the transformer T1 primary being connect with suppressor and T1 cascade of transformer
Energy-storage capacitor, safe Resistance R6, discharge tube G1, high frequency oscillation capacitance C6 and the high frequency transformer T2 connect；The energy storage electricity
Container and high frequency transformer T2 primary are connected to the both ends of discharge tube G1；The high frequency transformer T2 primary and safe Resistance
R6 is connected to high frequency oscillation capacitance both ends, and the high frequency transformer secondary is connect with ignition electric nozzle.
2. the aero-engine ignition driver according to claim 1 with online fault detection system, feature exist
In：First test point（1）, the second test point（2）It is separately positioned between low tension terminal positive and negative end and suppressor
Circuit on；For testing the third test point for passing through safe Resistance R6 size of current（3）Circuit in safe Resistance R6 is set
On；The 4th test point for testing ignition exciter unit output pulse electric frequency and size of current（4）Setting becomes in high frequency
On circuit between depressor and ignition electric nozzle.
3. the aero-engine ignition driver according to claim 1 with online fault detection system, feature exist
In：The first detection decision circuit includes concatenated diode D1, the first divider resistance R1, adjustable resistance R2, the second partial pressure
Resistance R3, current transformer L1；The adjustable resistance R3 connections are controlled for exporting the engine of adjustable resistance R3 voltage signals
System.
4. the aero-engine ignition driver according to claim 3 with online fault detection system, feature exist
In：The first detection decision circuit further include with concatenated first optocouplers of current transformer L1 and the first counter, described the
One optocoupler and the first counter are connect with engine control system circuit.
5. the aero-engine ignition driver according to claim 3 with online fault detection system, feature exist
In：The first divider resistance R1 and the second concatenated resistance values of divider resistance R3 are consistently greater than the resistance value of adjustable resistance R2.
6. the aero-engine ignition driver according to claim 1 with online fault detection system, feature exist
In：The second detection decision circuit includes being connected to third test point（3）Current transformer L2, be connected to the 4th test point
（4）Current transformer L3；The current transformer L2 and current transformer L3 output current signals are to engine control system.
7. the aero-engine ignition driver according to claim 6 with online fault detection system, feature exist
In：The second detection decision circuit further include with concatenated second optocouplers of current transformer L3 and the second counter, described the
Two optocouplers and the second counter are connect with engine control system circuit.
8. there is the aero-engine ignition driver of online fault detection system according to claim 1 ~ 7 any one of them,
It is characterized in that：The suppressor uses the composite filter being composed of choke coil and feedthrough capacitor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721640340.6U CN207892709U (en) | 2017-11-30 | 2017-11-30 | Aero-engine ignition driver with online fault detection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721640340.6U CN207892709U (en) | 2017-11-30 | 2017-11-30 | Aero-engine ignition driver with online fault detection system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207892709U true CN207892709U (en) | 2018-09-21 |
Family
ID=63548390
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721640340.6U Active CN207892709U (en) | 2017-11-30 | 2017-11-30 | Aero-engine ignition driver with online fault detection system |
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| CN (1) | CN207892709U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112627987A (en) * | 2020-12-11 | 2021-04-09 | 陕西航空电气有限责任公司 | Main and boost integrated ignition device circuit with discharge frequency feedback |
| US11519335B1 (en) | 2021-08-27 | 2022-12-06 | Unison Industries, Llc | Turbine engine ignition system and method |
-
2017
- 2017-11-30 CN CN201721640340.6U patent/CN207892709U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112627987A (en) * | 2020-12-11 | 2021-04-09 | 陕西航空电气有限责任公司 | Main and boost integrated ignition device circuit with discharge frequency feedback |
| CN112627987B (en) * | 2020-12-11 | 2023-09-29 | 陕西航空电气有限责任公司 | Main and boosting integrated ignition device circuit with discharging frequency feedback |
| US11519335B1 (en) | 2021-08-27 | 2022-12-06 | Unison Industries, Llc | Turbine engine ignition system and method |
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