CN114687906A - System and method for monitoring health condition of ignition device of aero-engine - Google Patents
System and method for monitoring health condition of ignition device of aero-engine Download PDFInfo
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- CN114687906A CN114687906A CN202011592527.XA CN202011592527A CN114687906A CN 114687906 A CN114687906 A CN 114687906A CN 202011592527 A CN202011592527 A CN 202011592527A CN 114687906 A CN114687906 A CN 114687906A
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 32
- 238000000034 method Methods 0.000 title claims abstract description 10
- 238000004146 energy storage Methods 0.000 claims abstract description 78
- 238000005070 sampling Methods 0.000 claims abstract description 23
- 239000003990 capacitor Substances 0.000 claims description 18
- 238000001514 detection method Methods 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims 3
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010892 electric spark Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02P—IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES
- F02P17/00—Testing of ignition installations, e.g. in combination with adjusting; Testing of ignition timing in compression-ignition engines
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The utility model provides an aeroengine ignition health's monitoring system, includes engine ignition and sampling circuit, signal acquisition circuit and health management system, engine ignition is including the ignition power supply inverter circuit, power step up transformer, energy storage charging circuit, the control circuit that discharges and the output circuit that discharges that connect gradually, sampling circuit connects energy storage charging circuit, signal acquisition circuit and ignition power supply inverter circuit, discharge output circuit, sampling circuit connect respectively, health management system and signal acquisition circuit connect. The system provides a method for monitoring the health condition of the ignition device of the aero-engine, and the health condition of the ignition device of the aero-engine can be monitored comprehensively by using a special ignition device of the aero-engine and acquiring and monitoring signals of three different positions in the ignition device to monitor the signals of the three different positions as the health condition of the ignition device of the aero-engine.
Description
Technical Field
The invention relates to the field of engine monitoring, in particular to a system and a method for monitoring the health condition of an ignition device of an aircraft engine.
Background
The ignition device of the aircraft engine is an important accessory for starting and igniting the engine, and mainly has the function of outputting high-voltage pulses to electrically break down an electric nozzle after a power supply is switched on so as to ignite mixed gas in a combustion chamber of the engine, thereby realizing the starting and igniting of the aircraft engine. At present, all ignition devices are used, state output can be realized only through a mode of breaking down an electric nozzle to form electric sparks, the online working condition of the ignition device can not be monitored in real time, if an ignition fault occurs, fault elimination can not be carried out in time, and the test progress of an engine and even the trip rate of an airplane can be delayed.
Along with the continuous change of flight operation demand, operation performance is continuously improved, and the ignition device which can only realize one mode ignition output through the electric nozzle cannot meet the working demand of an engine, so that the online monitoring on the health of the ignition device becomes a necessary development trend.
Disclosure of Invention
The invention aims to: the system comprises a special engine ignition device, and is characterized in that signals of three different positions in the ignition device are collected and monitored, so that the health condition of the engine ignition device can be monitored comprehensively, and the problems are solved.
The technical scheme adopted by the invention is as follows:
the utility model provides a monitoring system of aeroengine ignition health, includes engine ignition and sampling circuit, signal acquisition circuit and health management system, engine ignition is including the ignition power supply inverter circuit, power step up transformer, energy storage charging circuit, the control circuit that discharges and the output circuit that discharges that connect gradually, sampling circuit connects energy storage charging circuit, signal acquisition circuit and ignition power supply inverter circuit, discharge output circuit, sampling circuit connect respectively, health management system and signal acquisition circuit connect.
In order to better realize the scheme, further, the ignition power supply inverter circuit comprises a pulse width modulation chip U1, and the waveform output by the pulse width modulation chip U1 is a square wave signal 1.
In order to better implement the scheme, further, the power supply step-up transformer includes a flyback transformer T1, the energy storage charging circuit includes an energy storage capacitor C3, one end of the flyback transformer T1 is connected to the ignition power supply inverter circuit, and the other end of the flyback transformer T1 is connected to the energy storage capacitor C3; after receiving the signal transmitted from the ignition power supply inverter circuit, the flyback transformer T1 stores energy in the energy storage capacitor C3, and the waveform of the stored energy is a triangular wave signal 2.
In order to better implement the scheme, the discharge control circuit further includes a transformer T3 and a capacitor C5, the transformer T3 is connected to the energy storage and charging circuit, the transformer T3 performs secondary voltage boosting on the signal after receiving the signal, so as to form a discharge output signal 3, and the discharge output signal 3 is output through the discharge output circuit.
In order to better implement the scheme, further, the discharge output circuit comprises an electric nozzle.
A method for monitoring the health condition of an ignition device of an aircraft engine based on the detection system comprises the following steps,
step S1: after receiving the low-voltage direct-current voltage VDC, the ignition power supply inverter circuit outputs an inverter signal 1;
step S2: after receiving the inversion signal 1, the power supply boosting transformer boosts the inversion signal 1 and outputs the signal to the energy storage charging circuit for charging, and the energy storage charging circuit outputs an energy storage signal 2;
step S3: after receiving the energy storage signal 2, the discharge control circuit performs secondary voltage boosting on the energy storage signal 2, forms a discharge output signal 3 after the secondary voltage boosting, and performs ignition output through the discharge output circuit;
step S4: the signal acquisition circuit acquires an inversion signal 1 and a discharge output signal 3, the sampling circuit acquires an energy storage signal 2 from the energy storage charging circuit, and the energy storage signal is processed and then sent to the signal acquisition circuit;
step S5: the signal acquisition circuit converts the received inversion signal 1, the energy storage signal 2 and the discharge output signal 3 and feeds the converted signals back to the health management system, and the health management system monitors the inversion signal 1, the energy storage signal 2 and the discharge output signal 3 in the working state of the engine ignition device in real time to realize the monitoring of the health condition of the engine ignition device.
In the monitoring system, after a low-voltage direct-current power supply is input, the pulse width modulation chip U1 and an auxiliary circuit thereof form an ignition power supply inverter circuit to generate an inverter signal 1; then, the energy storage capacitor is charged after the voltage is boosted through the flyback transformer, and an energy storage signal 2 is generated; when the energy storage voltage reaches a set value, the discharge control switch is conducted through the sampling circuit to generate a discharge output signal 3; the signal acquisition system is used for acquiring the inversion signal 1, the energy storage signal 2 and the discharge output signal 3 and feeding back the inversion signal, the energy storage signal and the discharge output signal to the health management system, so that the ignition health state is monitored on line.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. the invention relates to a system for monitoring the health condition of an ignition device of an aero-engine, and provides a method for monitoring the health condition of the ignition device of the aero-engine based on the system, wherein the health condition of the ignition device of the aero-engine can be monitored by the aid of a special ignition device of the aero-engine and by acquiring and monitoring signals of three different positions in the ignition device;
2. the invention relates to a system for monitoring the health condition of an ignition device of an aero-engine, and provides a method for monitoring the health condition of the ignition device of the aero-engine based on the system.
Drawings
In order to more clearly illustrate the technical solution, the drawings needed to be used in the embodiments are briefly described below, and it should be understood that, for those skilled in the art, other related drawings can be obtained according to the drawings without creative efforts, wherein:
FIG. 1 is a functional block diagram of the present invention;
fig. 2 is a schematic circuit connection diagram of the present invention.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The present invention will be described in detail with reference to fig. 1 to 2.
Example 1
The utility model provides a monitoring system of aeroengine ignition health, as figure 1, includes engine ignition and sampling circuit, signal acquisition circuit and health management system, engine ignition includes ignition power supply inverter circuit, power step up transformer, energy storage charging circuit, discharge control circuit and the output circuit that discharges that connects gradually, sampling circuit connects energy storage charging circuit, signal acquisition circuit and ignition power supply inverter circuit, discharge output circuit, sampling circuit connect respectively, health management system and signal acquisition circuit connect.
The working principle is as follows: in the monitoring system, after a low-voltage direct-current voltage VDC is input to an ignition power supply inverter circuit, the ignition power supply inverter circuit generates an inverter signal; then, after the voltage is boosted by a power supply boosting transformer, the energy storage and charging circuit is charged; when the energy storage voltage reaches a set value, the discharge control circuit is conducted to generate a discharge output signal and output the discharge output signal through the discharge output circuit; the signal acquisition system is used for acquiring an inversion signal of the ignition power supply inverter circuit and a discharge output signal of the discharge output circuit, the sampling circuit is used for acquiring an energy storage signal of the energy storage charging circuit and then uploading the energy storage signal to the signal acquisition circuit, the signal acquisition circuit is used for feeding the inversion signal, the energy storage signal and the discharge output signal back to the health management system, and the health management system is used for monitoring the three signals in real time, so that the ignition health state can be monitored on line.
Example 2
The utility model provides a monitoring system of aeroengine ignition health, as figure 1, includes engine ignition and sampling circuit, signal acquisition circuit and health management system, engine ignition includes ignition power supply inverter circuit, power step up transformer, energy storage charging circuit, discharge control circuit and the output circuit that discharges that connects gradually, sampling circuit connects energy storage charging circuit, signal acquisition circuit and ignition power supply inverter circuit, discharge output circuit, sampling circuit connect respectively, health management system and signal acquisition circuit connect.
As shown in fig. 2, the ignition power inverter circuit includes a pulse width modulation chip U1, and the waveform output by the pulse width modulation chip U1 is a square wave signal 1. The power supply boosting transformer comprises a flyback transformer T1, the energy storage charging circuit comprises an energy storage capacitor C3, one end of the flyback transformer T1 is connected to the ignition power supply inverter circuit, and the other end of the flyback transformer T1 is connected to the energy storage capacitor C3; after receiving the signal transmitted from the ignition power supply inverter circuit, the flyback transformer T1 stores energy in the energy storage capacitor C3, and the waveform of the stored energy is a triangular wave signal 2. The discharge control circuit comprises a transformer T3 and a capacitor C5, the transformer T3 is connected with the energy storage charging circuit, the transformer T3 performs secondary voltage boosting on the signals after receiving the signals to form a discharge output signal 3, and the discharge output signal 3 is output through the discharge output circuit. The discharge output circuit comprises an electric nozzle.
The working principle is as follows: as shown in fig. 2, the pulse width modulation chip U1 and its auxiliary circuit form an ignition power inverter circuit, when a low-voltage dc voltage (12-32) VDC is input, the waveform parameters of the inverter signal 1 can be set through the capacitor C2 and the resistor R3, the frequency setting range is 100 Hz-500 KHz, and the output waveform is a square wave; after the triode Q1 is turned on, the primary side of the flyback transformer T1 stores energy, after the triode Q1 is turned off, the flyback transformer T1 boosts the secondary side of the flyback transformer T1, the energy storage capacitor C3 is charged, an energy storage signal 2 is formed, the waveform parameters of the energy storage signal 2 are determined by the conduction voltages of the sampling resistor R5, the sampling resistor R6 and the triode Q2, and the waveform form is triangular wave; after the triode Q2 is turned on, the energy storage voltage is subjected to secondary boosting through the transformer T3 and the capacitor C5 to form a discharge output signal 3, and the waveform parameters of the discharge output signal 3 are determined by the transformer T3 and the oscillation capacitor C5; the signal acquisition system is used for acquiring and converting the inversion signal 1, the energy storage signal 2 and the discharge output signal 3, feeding the inversion signal 1, the energy storage signal 2 and the discharge output signal 3 back to the health management system, and the health management system is used for monitoring the inversion signal 1, the energy storage signal 2 and the discharge output signal 3 in the working state of the ignition device in real time, so that the health condition of the ignition device is monitored.
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
Example 3
A method for monitoring the health condition of an ignition device of an aircraft engine based on the detection system of the embodiment 1 or 2 comprises the following steps,
step S1: after receiving the low-voltage direct-current voltage VDC, the ignition power supply inverter circuit outputs an inverter signal 1;
step S2: after receiving the inversion signal 1, the power supply boosting transformer boosts the inversion signal 1 and outputs the signal to the energy storage charging circuit for charging, and the energy storage charging circuit outputs an energy storage signal 2;
step S3: after receiving the energy storage signal 2, the discharge control circuit performs secondary voltage boosting on the energy storage signal 2, forms a discharge output signal 3 after the secondary voltage boosting, and performs ignition output through the discharge output circuit;
step S4: the signal acquisition circuit acquires an inversion signal 1 and a discharge output signal 3, and the sampling circuit acquires an energy storage signal 2 from the energy storage charging circuit and then sends the energy storage signal to the signal acquisition circuit after processing;
step S5: the signal acquisition circuit converts the received inversion signal 1, the energy storage signal 2 and the discharge output signal 3 and feeds the converted signals back to the health management system, and the health management system monitors the inversion signal 1, the energy storage signal 2 and the discharge output signal 3 in the working state of the engine ignition device in real time to realize the monitoring of the health condition of the engine ignition device.
The working principle is as follows: in the monitoring method, after a low-voltage direct-current voltage VDC is input, a pulse width modulation chip U1 and an auxiliary circuit thereof form an ignition power supply inverter circuit to generate an inverter signal 1; then, the energy storage capacitor is charged after the voltage is boosted through the flyback transformer, and an energy storage signal 2 is generated; when the energy storage voltage reaches a set value, the discharge control switch is conducted through the sampling circuit to generate a discharge output signal 3; the signal acquisition system is used for acquiring the inversion signal 1, the energy storage signal 2 and the discharge output signal 3 and feeding back the inversion signal, the energy storage signal and the discharge output signal to the health management system, so that the ignition health state is monitored on line.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (6)
1. The utility model provides a monitoring system of aeroengine ignition health condition, includes engine ignition and sampling circuit, signal acquisition circuit and health management system which characterized in that: the engine ignition device comprises an ignition power supply inverter circuit, a power supply boosting transformer, an energy storage charging circuit, a discharging control circuit and a discharging output circuit which are sequentially connected, wherein the sampling circuit is connected with the energy storage charging circuit, the signal acquisition circuit is respectively connected with the ignition power supply inverter circuit, the discharging output circuit and the sampling circuit, and the health management system is connected with the signal acquisition circuit.
2. The system for monitoring the health of an ignition device of an aircraft engine as defined in claim 1, wherein: the ignition power supply inverter circuit comprises a pulse width modulation chip U1, and the waveform output by the pulse width modulation chip U1 is a square wave signal.
3. The system for monitoring the health of an ignition device of an aircraft engine as defined in claim 1, wherein: the power supply boosting transformer comprises a flyback transformer T1, the energy storage charging circuit comprises an energy storage capacitor C3, one end of the flyback transformer T1 is connected to the ignition power supply inverter circuit, and the other end of the flyback transformer T1 is connected to the energy storage capacitor C3; after receiving the signal transmitted from the ignition power supply inverter circuit, the flyback transformer T1 stores energy in the energy storage capacitor C3, and the waveform of the stored energy is a triangular wave signal.
4. The system for monitoring the health of an ignition device of an aircraft engine as defined in claim 1, wherein: the discharge control circuit comprises a transformer T3 and a capacitor C5, the transformer T3 is connected with the energy storage charging circuit, the transformer T3 performs secondary voltage boosting on the signals after receiving the signals to form discharge output signals, and the discharge output signals are output through the discharge output circuit.
5. The system for monitoring the health of an ignition device of an aircraft engine as defined in claim 1, wherein: the discharge output circuit comprises an electric nozzle.
6. A method for monitoring the health of an ignition device of an aircraft engine, based on a detection system according to any one of claims 1 to 5, characterized in that: comprises the following steps of (a) carrying out,
step S1: after receiving the low-voltage direct-current voltage VDC, the ignition power supply inverter circuit outputs an inverter signal 1;
step S2: after receiving the inversion signal 1, the power supply boosting transformer boosts the inversion signal 1 and outputs the signal to the energy storage charging circuit for charging, and the energy storage charging circuit outputs an energy storage signal 2;
step S3: after receiving the energy storage signal 2, the discharge control circuit performs secondary voltage boosting on the energy storage signal 2, forms a discharge output signal 3 after the secondary voltage boosting, and performs ignition output through the discharge output circuit;
step S4: the signal acquisition circuit acquires an inversion signal 1 and a discharge output signal 3, the sampling circuit acquires an energy storage signal 2 from the energy storage charging circuit, and the energy storage signal is processed and then sent to the signal acquisition circuit;
step S5: the signal acquisition circuit converts the received inversion signal 1, the energy storage signal 2 and the discharge output signal 3 and feeds the converted signals back to the health management system, and the health management system monitors the inversion signal 1, the energy storage signal 2 and the discharge output signal 3 in the working state of the engine ignition device in real time to realize the monitoring of the health condition of the engine ignition device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011592527.XA CN114687906A (en) | 2020-12-29 | 2020-12-29 | System and method for monitoring health condition of ignition device of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011592527.XA CN114687906A (en) | 2020-12-29 | 2020-12-29 | System and method for monitoring health condition of ignition device of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114687906A true CN114687906A (en) | 2022-07-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011592527.XA Pending CN114687906A (en) | 2020-12-29 | 2020-12-29 | System and method for monitoring health condition of ignition device of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114687906A (en) |
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2020
- 2020-12-29 CN CN202011592527.XA patent/CN114687906A/en active Pending
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