CN108051217B - The online fault detection method of aero-engine ignition driver - Google Patents
The online fault detection method of aero-engine ignition driver Download PDFInfo
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- CN108051217B CN108051217B CN201711241230.7A CN201711241230A CN108051217B CN 108051217 B CN108051217 B CN 108051217B CN 201711241230 A CN201711241230 A CN 201711241230A CN 108051217 B CN108051217 B CN 108051217B
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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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- 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
- G01M15/02—Details or accessories of testing apparatus
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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
- G01M15/04—Testing internal-combustion engines
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The invention discloses the online fault detection methods of aero-engine ignition driver, the online test method includes the detection decision circuit being arranged in ignition exciter unit with ignition exciter unit circuit connection, pass through detection decision circuit online acquisition ignition exciter unit power supply input circuit positive and negative end voltage value and circuit output current value, according to collected input circuit positive and negative end voltage value judge ignition exciter unit power input whether failure, according to collected circuit output current value judge ignition exciter unit output circuit whether failure.The online fault detection method of aero-engine ignition driver provided by the invention is monitored working condition, the fault condition of the ignition exciter unit being already installed in aero-engine, it can quickly and efficiently detect the failure of ignition exciter unit, to debug in time, and then the success rate of raising aero-engine and the complete rate of aircraft, the rate of attendance and task execution.
Description
Technical field
The present invention relates to aero-engine fault detection technique fields, and in particular to the boat with online fault detection system
Empty engine ignition driver.
Background technique
Aero-engine ignition driver (hereinafter referred to as ignition exciter unit) is the important component of engine, ignition exciter unit
Ignition system is formed together with firing cable, ignition electric nozzle, for engine start or reinforcing electric ignition.Modern Aviation is jet-propelled
Engine is mostly using 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 row i null point firearm ignition failure includes three aspects: (1) ignition exciter unit internal fault；(2) igniting is led
Line failure；(3) ignition electric nozzle failure.And wherein ignition exciter unit since inside is equipped with main ignition operation circuit, electric appliance
Element is more, and working environment is severe, results in it and is easiest to break down, and fault type is most complicated.The failure of ignition exciter unit
Mode can be divided into 3 kinds: ignition exciter unit is different without output, ignition exciter unit output frequency exception, ignition exciter unit output energy
Often.
As aircraft runing 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, it is serious to will cause that igniting is unsuccessful, and these failures 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 complete rate, the rate of attendance and the task execution of aero-engine and aircraft.For faulty igniter,
Many aircraft engine maintenance companies, which directly adopt, abandons the processing mode that faulty igniter more renews igniter, causes
The great wasting of resources.
Summary of the invention
The present invention is directed to the prior art, provides a kind of online fault detection method of aero-engine ignition driver, can be right
Working condition, the fault condition for the ignition exciter unit being already installed in aero-engine are monitored on-line, can be quick high
Effect detects the failure of ignition exciter unit, to debug in time, and then improve aero-engine and aircraft complete rate,
The success rate of the rate of attendance and task execution.
A kind of online fault detection method of aero-engine ignition driver provided by the invention is by the following technical programs
Implement: the online test method includes the detection decision circuit with ignition exciter unit circuit connection, detection decision circuit connection
Engine control system online acquisition ignition exciter unit power supply input circuit positive and negative end voltage value and circuit output current value,
And according to two sections of voltage values of collected input circuit positive and negative anodes judge ignition exciter unit power input whether failure, according to acquisition
The circuit output current value arrived judge ignition exciter unit output circuit whether failure.
The detection decision circuit includes the first detection decision circuit and the second detection decision circuit, the ignition exciter unit
Be provided on internal circuit fiery driver power supply input circuit positive and negative end the first test point and the second test point,
The third test point and the 4th test point of fiery driver output end, the first detection decision circuit and the first test are set
Point, the connection of the second test point, are used for the first test point of online acquisition, the second test point voltage signal；Second detection determines
Circuit is connect for online acquisition third test point, the 4th test point current signal with third test point, the 4th test point.
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；The adjustable resistance R3 connection is for exporting the engine of adjustable resistance R3 voltage signal
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 resistance of the first divider resistance R1 is consistently greater than the resistance of adjustable resistance R2, avoids test circuit consumption larger
Power tests the voltage on adjustable resistance R2.This voltage signal is exported to engine control system and is judged, if voltage
Signal is in the voltage range that power supply normally inputs, then voltage swing is normal, is otherwise exactly abnormal.
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 protective resistance R4 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 protective resistance R4
Output has high-voltage pulse electric, i.e. the current transformer L3 of the 4th test point connection exports high voltage pulse.When ignition exciter unit exports
When open-circuit fault, then the energy on energy-storage capacitor is discharged by the circuit that protective resistance R4 is formed, so passing through protective resistance
The electric current of R4 is larger, i.e. the current transformer L2 output HIGH voltage signal of third test point connection, can be with according to the size of voltage
Judgement passes through the larger of the electric current of protective resistance R4, and the current transformer L3 of the 4th test point connection can't detect pressure, judge
Ignition exciter unit exports failure.
The judgment method of the online failure detection result of ignition exciter unit are as follows:
(1) first test point, the second test point voltage signal correspond to input supply voltage greater than input supply voltage or small
In input supply voltage, input supply voltage is abnormal；
(2) third test point no current, ignition exciter unit failure；
(3) third test point has electric current, and the 4th test point has electric current, and ignition exciter unit is 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) the 4th test points have an electric current, but current value is bigger than normal or less than normal when current value is worked normally compared with ignition exciter unit, point
Fiery driver failure.
The online test method further includes that engine control system passes through detection decision circuit online acquisition ignition stimuli
Device power supply input circuit electric current inputs frequency and circuit output frequency, and inputs frequency judgement input electricity according to collected electric current
The frequency in source judges that ignition exciter unit is abnormal with the presence or absence of output frequency with the presence or absence of exception, according to collected output frequency.
It is described first detection decision circuit further include with concatenated first optocoupler of current transformer L1, the first counter, cut
Whether first optocoupler and the first counter are connect with engine control system, normal for testing input power frequency.It is logical
Overcurrent mutual inductor L1 output pulse signal, pulse frequency are the frequency of input power, which passes through optocoupler and meter
Number devices it can be concluded that power input frequency values, frequency values are exported to engine control system and are judged, if the frequency values
In the range of (380~420), then the frequency of input power is normal, is otherwise exactly abnormal.
It is described second detection decision circuit further include with concatenated second optocoupler of current transformer L3 and the second counter, cut
Second optocoupler and the second counter are connect with engine control system, and output low voltage signal is made to pass through optocoupler, counter
Obtain the output frequency of ignition exciter unit.This signal is output to engine control system, engine control system can obtain
The output frequency of ignition exciter unit out.It is powered in ignition exciter unit, under the premise of power input is normal, by being surveyed to third
The testing current of pilot and the 4th test point we can be determined that ignition exciter unit whether failure.
The judgment method of the online failure detection result of ignition exciter unit are as follows:
(1) first test point, the corresponding power input voltage of the second test point voltage are greater than input supply voltage or are less than
Input supply voltage, input supply voltage are abnormal；
(2) first test points, the second test point pulse frequency are greater than input power frequency or are less than input power frequency,
Input power frequency anomaly；
(3) third test point no current, ignition exciter unit failure；
(4) third test point has electric current, and the 4th test point has electric current, and ignition exciter unit is normal；
(5) 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；
(6) the 4th test points have an electric current, but current value is bigger than normal or less than normal when current value is worked normally compared with ignition exciter unit, point
Fiery driver failure；
(7) the 4th test point pulse frequencies are abnormal, ignition exciter unit failure.
Compared with prior art, the present invention have the following advantages that and the utility model has the advantages that
The online fault detection method of aero-engine ignition driver provided by the invention is used and is set in ignition exciter unit
The detection decision circuit with ignition exciter unit circuit connection is set, and corresponding detection decision circuit is provided with four test points to igniting
Power input voltage, frequency and the electric power outputting current of driver, frequency are monitored on-line, to being already installed on aeroplane engine
Working condition, the fault condition of ignition exciter unit on machine are monitored on-line, quickly and efficiently can detect ignition stimuli
The failure of device greatly reduces the artificial and time loss of aero-engine ignition driver fault detection, improves aeroplane engine
The success rate of the complete rate of machine and aircraft, the rate of attendance and task execution.
Detailed description of the invention
Fig. 1 is circuit diagram of the present invention；
Fig. 2 is that the present invention first detects decision circuit schematic diagram；
Fig. 3 is that the present invention 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 embodiment
The present invention is described in further detail below with reference to embodiment, embodiments of the present invention are not limited thereto.
Embodiment 1:
It is widely used that high pressure high-energy ignition driver (energy storage type igniter), in aero-engine at present with certain type
For the energy storage type ignition system of low-voltage alternating-current input, the ignition system major parameter is as follows:
Power input: 110~115V/380~420Hz；
Output voltage: voltage peak is not less than 15kV；
Peak point current；Not less than 2000A；
Spark frequency: 2 ± 0.5Hz.
As shown in Figure 1, the circuit structure of the ignition exciter unit is mainly made of 3 parts: AC boosting module, rectification times
Press energy-storage module, discharge module.
Its circuit element specifically includes that
Suppressor: including filter inductance L01, L02 and feedthrough capacitor C01, C02, play the role of current regulation, control igniting
The input power and spark efficiency of driver；And it can prevent the low frequency signal of ignition exciter unit, high-frequency signal from pouring into aircraft electricity
Source 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: it is used for energy storage；
Times voltage capacitance C4, C3: for charging to storage capacitor C5；
Discharge resistance R5: it for when ignition exciter unit power-off, the residual charge in storage capacitor C5 gradually to be bled off, hinders
Value is very big, and its effect very little in igniter normal work；
Current-limiting resistance R4: the charging current for limiting capacitance C3；
Current-limiting resistance R6: for limiting the charging current of high frequency oscillation capacitor C6；
High frequency transformer T2；
High frequency oscillation capacitor C6: for energy storage, disruptive discharge pipe G1 and pass through high frequency transformer T2 perforation ignition sparking plug, shape
At firing circuit access.
Discharge tube G1: being to separate ignition electric nozzle circuit and storage capacitor C5, when making sparking plug operation conditions change, can make
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 feeling 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 holding negative, the high diode temperature D3 conducting before arriving of voltage wave crest, high diode temperature D2 cut-off, 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
Greater than secondary windings output voltage, high diode temperature D2 conducting, 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 conducting before arriving of voltage wave crest, high diode temperature D3 cut-off, to voltage capacitance C4, energy storage again
The branch charging that capacitor C5, times voltage capacitance C3 are connected into；After voltage crosses wave crest sometime, the electricity on times voltage capacitance C4
Pressure is greater than secondary windings output voltage, and high diode temperature D3 conducting, high diode temperature D2 cut-off, 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 simultaneously also by high frequency transformer T2 primary and current-limiting resistance R6 to high frequency oscillation capacitor C6.With charging time
Several increases, the voltage on storage capacitor C5, high frequency oscillation capacitor C6 are gradually increasing.High frequency oscillation capacitor 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 capacitor C6 is applied to T2's
Primary, secondarily grade generates the high pressure of (15~20) 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 online fault detection method of ignition exciter unit is ignition exciter unit internal circuit connecting detection decision circuit, institute
Stating detection decision circuit includes the first detection decision circuit, the second detection decision circuit, and on ignition exciter unit internal circuit
First test point 1, the second test point 2, third test point 3, the 4th test point 4 be set, the first detection decision circuit and the
One test point 1,2 circuit connection of the second test point, the second detection decision circuit and third test point 3,4 electricity of the 4th test point
Road connection, the first detection decision circuit are connect with engine control system with the second detection decision circuit.
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 by the first detection decision circuit in pole both ends whether normal.The third test point 3 is arranged
In protective resistance, the 4th test point 4 is arranged on ignition exciter unit internal output circuit, and third test point 3 passes through the second inspection
The size of current of decision circuit test protective resistance is surveyed, the 4th test point 4 tests ignition stimuli by the second detection decision circuit
Device exports pulse electric frequency and size of current.
As shown in Fig. 2, it is described first detection decision circuit include the diode for being connected into circuit, the first divider resistance R1,
Second divider resistance R2, adjustable resistance R3, current transformer；The adjustable resistance R3 voltage output engine control system.Institute
It is in parallel with input power from the first test point 1, the second test point 2 to state the first detection decision circuit, electric current is through diode D1, 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 value of divider resistance R3 are consistently greater than the electricity of adjustable resistance R2
Resistance avoids test circuit consumption relatively high power, tests the voltage on adjustable resistance R2.Meanwhile it can be by adjusting adjustable resistance R2
On resistance value, the normal voltage signal of power input is adjusted within the scope of 1.1 ~ 1.2V, corresponding power input voltage
For 110V ~ 115V, this voltage signal is exported to engine control system and is judged, if voltage signal is 1.1 ~ 1.2V's
In voltage range, 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
Meet the current transformer L3 in the 4th test point 4；The current transformer L2 and current transformer L3 output engine 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 protective resistance R4 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 smaller by the electric current of protective resistance R4, and output circuit is normal in ignition exciter unit, and ignition exciter unit is defeated
There is high-voltage pulse electric out, i.e. the current transformer L3 of the 4th test point 4 connection exports high voltage pulse.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 protective resistance R4 is formed, so passing through protective resistance R4
Electric current it is larger, i.e., third test point 3 connect current transformer L2 output HIGH voltage signal, can be sentenced according to the size of voltage
Surely by the larger of the electric current of protective resistance R4, and the current transformer L3 of the 4th test point 4 connection can't detect voltage, light a fire
Driver exports failure.
The judgment method of the online failure detection result of ignition exciter unit are as follows:
(1) first test point 1, the second 2 voltages of test point>1.2V or<1.1V, input supply voltage are abnormal；
(2) 3 no current of third test point, ignition exciter unit failure；
(3) third test point 3 has electric current, and the 4th test point 4 has electric current, and ignition exciter unit is normal；
(4) 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；
(5) the 4th test points 4 have an 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 to improve on the basis of embodiment 1, is theed improvement is that: first detection determines electricity
Road further includes and concatenated first optocoupler of current transformer, the first counter, and first optocoupler and the first counter and hair
Whether the connection of motivation control system is normal for testing input power frequency.Pass through current transformer L1 output pulse signal, arteries and veins
Rush the frequency that frequency is input power, the pulse signal by optocoupler and counter it can be concluded that the frequency values of power input,
Frequency values are exported to engine control system and are judged, if the frequency values input electricity in the range of 380~420 Hz
The frequency in source is normal, is otherwise exactly abnormal.
The second detection decision circuit further includes and concatenated second optocoupler of current transformer and the second counter, and institute
It states the second optocoupler and the second counter is connect with engine control system, obtain output low voltage signal by optocoupler, counter
The output frequency of ignition exciter unit out.This signal is output to engine control system, you can get it for engine control system
The output frequency of ignition exciter unit.It is powered in ignition exciter unit, under the premise of power input is normal, by testing third
Point 3 and the 4th test point 4 testing current we can be determined that ignition exciter unit whether failure.
The judgment method of the online failure detection result of ignition exciter unit are as follows:
(1) first test point 1, the second 2 voltages of test point>1.2V or<1.1V, input supply voltage are abnormal；
(2) first test points 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, and the 4th test point 4 has electric current, and ignition exciter unit is 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) the 4th test points 4 have an 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；
4 pulse frequency of (7) the 4th test point 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 presently preferred embodiments of the present invention, not does limitation in any form to the present invention, it is all according to
According to technical spirit any simple modification to the above embodiments of the invention, equivalent variations, protection of the invention is each fallen within
Within the scope of.
Claims (8)
1. the online fault detection method of aero-engine ignition driver, it is characterised in that: setting and point in ignition exciter unit
The detection decision circuit of fiery divider chain connection, by detecting decision circuit online acquisition ignition exciter unit power supply input circuit
Positive and negative end voltage value and circuit output current value judge to light a fire according to collected input circuit positive and negative end voltage value
Driver power input whether failure, according to collected circuit output current value judge ignition exciter unit output circuit whether therefore
Barrier；The detection decision circuit includes the first detection decision circuit and the second detection decision circuit, inside the ignition exciter unit
The first test point (1) and the second test point of fiery driver power supply input circuit positive and negative end are provided on circuit
(2), the third test point (3) and the 4th test point (4) of ignition exciter unit output end, the first detection decision circuit are set
It is connect with the first test point (1), the second test point (2), is used for the first test point of online acquisition (1), the second test point (2) voltage
Signal；The second detection decision circuit is connect with third test point (3), the 4th test point (4), is surveyed for online acquisition third
Pilot (3), the 4th test point (4) current signal；The third test point (3) is arranged in protective resistance, the 4th test point (4)
It is arranged on ignition exciter unit internal output circuit.
2. the online fault detection method of aero-engine ignition driver according to claim 1, it is characterised in that: described
The judgment method of the online failure detection result of ignition exciter unit are as follows:
(1) first test point (1), the corresponding power input voltage of the second test point (2) voltage are greater than input supply voltage or small
In input supply voltage, input supply voltage is abnormal；
(2) third test point (3) no current, ignition exciter unit failure；
(3) third test point (3) has electric current, and the 4th test point (4) has electric current, and ignition exciter unit is normal；
(4) third test point (3) has electric current, and the 4th test point (4) no current, ignition exciter unit is normal, rear class connection open circuit or
Cable sparking plug failure；
(5) the 4th test points (4) have an electric current, but current value is bigger than normal or less than normal when current value is worked normally compared with ignition exciter unit, point
Fiery driver failure.
3. the online fault detection method of aero-engine ignition driver according to claim 1, it is characterised in that: described
First detection decision circuit include concatenated diode D1, the first divider resistance R1, adjustable resistance R2, the second divider resistance R3,
Current transformer L1；The adjustable resistance R3 connection is for exporting the engine control system of adjustable resistance R3 voltage signal.
4. the online fault detection method of aero-engine ignition driver according to claim 1, it is characterised in that: described
Second detection decision circuit includes being connected to the current transformer L2 of third test point (3), being connected to the electricity of the 4th test point (4)
Current transformer L3；The current transformer L2 and current transformer L3 are connect with engine control system.
5. the online fault detection method of aero-engine ignition driver according to claim 1, it is characterised in that: described
Online test method further includes inputting frequency and circuit output frequency by detection decision circuit online acquisition ignition exciter unit circuit
Rate, and frequency is inputted according to collected circuit and judges that the frequency of input power whether there is exception, according to collected circuit
Output frequency judges that ignition exciter unit is abnormal with the presence or absence of output frequency.
6. the online fault detection method of aero-engine ignition driver according to claim 5, it is characterised in that: described
The judgment method of the online failure detection result of ignition exciter unit are as follows:
(1) first test point (1), the corresponding power input voltage of the second test point (2) voltage are greater than input supply voltage or small
In input supply voltage, input supply voltage is abnormal；
(2) first test points (1), the second test point (2) pulse frequency are greater than input power frequency or are less than input power frequency
Rate, input power frequency anomaly；
(3) third test point (3) no current, ignition exciter unit failure；
(4) third test point (3) has electric current, and the 4th test point (4) has electric current, and ignition exciter unit is normal；
(5) third test point (3) has electric current, and the 4th test point (4) no current, ignition exciter unit is normal, rear class connection open circuit or
Cable sparking plug failure；
(6) the 4th test points (4) have an electric current, but current value is bigger than normal or less than normal when current value is worked normally compared with ignition exciter unit, point
Fiery driver failure；
(7) the 4th test point (4) pulse frequencies are abnormal, ignition exciter unit failure.
7. the online fault detection method of aero-engine ignition driver according to claim 6, it is characterised in that: described
First detection decision circuit further includes connecting with concatenated first optocoupler of current transformer L1 and the first counter, and described the
One optocoupler and the series connection of the first counter are connect with engine control system, for acquiring the frequency of ignition exciter unit power input
Rate value judges whether power input frequency is abnormal.
8. the online fault detection method of aero-engine ignition driver according to claim 6, it is characterised in that: described
Second detection decision circuit further includes connecting with concatenated second optocoupler of current transformer L3 and the second counter, and described the
Two optocouplers and the series connection of the second counter are connect with engine control system, for acquiring the output frequency of ignition exciter unit,
Judge whether ignition exciter unit output frequency is abnormal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711241230.7A CN108051217B (en) | 2017-11-30 | 2017-11-30 | The online fault detection method of aero-engine ignition driver |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711241230.7A CN108051217B (en) | 2017-11-30 | 2017-11-30 | The online fault detection method of aero-engine ignition driver |
Publications (2)
| Publication Number | Publication Date |
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| CN108051217A CN108051217A (en) | 2018-05-18 |
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| CN108761246A (en) * | 2018-06-28 | 2018-11-06 | 中国人民解放军空军工程大学 | A kind of polymer matrix dielectric barrier discharge plasma driver ageing state observation circuit and monitoring method |
| CN112628050B (en) * | 2020-12-18 | 2022-08-19 | 陕西航空电气有限责任公司 | Withstand voltage value determination method for boost capacitor of aircraft engine ignition circuit |
| CN112523899A (en) * | 2020-12-25 | 2021-03-19 | 内蒙动力机械研究所 | High-voltage pulse power ignition circuit and method based on peak-staggering charging mechanism |
| CN116105172A (en) * | 2022-11-18 | 2023-05-12 | 天津航空机电有限公司 | Large-energy high-efficiency ignition circuit and method for heavy-duty gas turbine |
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| US2518427A (en) * | 1947-05-15 | 1950-08-08 | Lindberg Jr | Engine power analyzer |
| CN103104347A (en) * | 2013-02-18 | 2013-05-15 | 成都泛华航空仪表电器有限公司 | High energy solid state discharge igniting module |
| CN204299767U (en) * | 2014-11-28 | 2015-04-29 | 中航商用航空发动机有限责任公司 | For the Auto-Test System of aero-engine ignition system |
| CN106121829A (en) * | 2016-08-18 | 2016-11-16 | 四川泛华航空仪表电器有限公司 | The fault-preventing device of monitoring engine ignitor duty |
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| US2518427A (en) * | 1947-05-15 | 1950-08-08 | Lindberg Jr | Engine power analyzer |
| CN103104347A (en) * | 2013-02-18 | 2013-05-15 | 成都泛华航空仪表电器有限公司 | High energy solid state discharge igniting module |
| CN204299767U (en) * | 2014-11-28 | 2015-04-29 | 中航商用航空发动机有限责任公司 | For the Auto-Test System of aero-engine ignition system |
| CN106121829A (en) * | 2016-08-18 | 2016-11-16 | 四川泛华航空仪表电器有限公司 | The fault-preventing device of monitoring engine ignitor duty |
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