CN-114687906-B - System and method for monitoring health condition of aeroengine ignition device

Abstract

The utility model provides a monitoring system of aeroengine ignition device health condition, includes engine ignition device and sampling circuit, signal acquisition circuit and health management system, engine ignition device is including ignition power 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 inverter circuit, the output circuit that discharges, sampling circuit connect respectively, health management system and signal acquisition circuit connect. The system is used for monitoring the health condition of the ignition device of the aeroengine, and the health condition of the ignition device of the engine can be comprehensively monitored by the aid of the special ignition device of the engine and collecting and monitoring signals of three different positions in the ignition device and monitoring the signals of the three different positions.

Inventors

• WANG TINGTING
• LEI YU

Assignees

• 四川泛华航空仪表电器有限公司

Dates

Publication Date

20260508

Application Date

20201229

Claims (3)

1. 1. The system for monitoring the health condition of the aeroengine ignition device comprises an engine ignition device, a sampling circuit, a signal acquisition circuit and a health management system, and is characterized in that the engine ignition device comprises an ignition power supply inverter circuit, a power supply step-up transformer, an energy storage charging circuit, a discharge control circuit and a discharge output circuit which are sequentially connected, 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 discharge output circuit and the sampling circuit, and the health management system is connected with the signal acquisition circuit; The power supply boosting transformer comprises a flyback transformer T1, an energy storage charging circuit and a discharging control circuit, wherein the flyback transformer T1 comprises an energy storage capacitor C3, one end of the flyback transformer T1 is connected to the ignition power supply inverting circuit, the other end of the flyback transformer T1 is connected to the energy storage capacitor C3, the energy storage capacitor C3 stores energy after receiving a signal transmitted by the ignition power supply inverting circuit, the waveform of the stored energy is a triangular wave signal, the discharging control circuit comprises a transformer T3 and a capacitor C5, the transformer T3 is connected with the energy storage charging circuit, the transformer T3 boosts the signal for the second time after receiving the signal to form a discharging output signal, and the discharging output signal is output through the discharging output circuit.
2. 2. A system for monitoring the health of an aircraft engine ignition according to claim 1, wherein said discharge output circuit comprises a mouthpiece.
3. 3. A method for monitoring the health of an aircraft engine ignition device based on a system for monitoring the health of an aircraft engine ignition device according to claim 1 or 2, comprising the steps of: step S1, after an ignition power inverter circuit receives a low-voltage direct-current voltage VDC, an inverter signal (1) is output; step S2, after receiving the inversion signal (1), the power supply boosting transformer boosts the inversion signal (1) and outputs the boosted inversion signal to the energy storage charging circuit for charging, and the energy storage charging circuit outputs the energy storage signal (2); Step S3, after receiving the energy storage signal (2), the discharge control circuit performs secondary boosting on the energy storage signal (2), and a discharge output signal (3) is formed after the secondary boosting, and ignition output is performed through the discharge output circuit; S4, a signal acquisition circuit acquires an inversion signal (1) and a discharge output signal (3), a sampling circuit acquires an energy storage signal (2) from an energy storage charging circuit, and the energy storage signal is sent to the signal acquisition circuit after being processed; And S5, converting the received inversion signal (1), the energy storage signal (2) and the discharge output signal (3) by the signal acquisition circuit, feeding back to the health management system, and monitoring 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 by the health management system to realize the monitoring of the health condition of the engine ignition device.

Description

System and method for monitoring health condition of aeroengine ignition device 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 aeroengine ignition device. Background The ignition device of the aeroengine is an important accessory for starting and igniting the engine, and has the main function of outputting high-voltage pulse to electrically break down the electric nozzle after being powered on so as to ignite mixed gas in the combustion chamber of the engine, thereby realizing the starting and igniting of the aeroengine. At present, all ignition devices are used, state output can be realized only through a mode of forming electric sparks by breakdown of an electric nozzle, the on-line working condition of the ignition devices cannot be monitored in real time, if ignition faults occur, the faults cannot be timely discharged, the test progress of an engine and even the trip rate of an airplane can be delayed. With the continuous change of flight fight demands, fight performance is continuously improved, and an ignition device capable of realizing one mode ignition output only through an electric nozzle cannot meet the working demands of an engine, so that the health of the ignition device is in a trend of necessary development. Disclosure of Invention The invention aims to provide a system for monitoring the health condition of an aero-engine ignition device, and provides a method for monitoring the health condition of the aero-engine ignition device based on the system. The technical scheme adopted by the invention is as follows: The utility model provides a monitoring system of aeroengine ignition device health condition, includes engine ignition device and sampling circuit, signal acquisition circuit and health management system, engine ignition device is including ignition power 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 inverter circuit, the output circuit that discharges, sampling circuit connect respectively, health management system and signal acquisition circuit connect. In order to better realize the scheme, the ignition power inverter circuit further 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 realize the scheme, 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 inversion circuit, the other end of the flyback transformer T1 is connected to the energy storage capacitor C3, the flyback transformer T1 stores energy after receiving a signal transmitted by the ignition power supply inversion circuit, and the energy storage capacitor C3 stores energy, wherein the waveform of the stored energy is a triangular wave signal 2. In order to better realize the scheme, further, 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 carries out secondary boosting on the signal after receiving the signal 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 solution, further, the discharge output circuit comprises a mouthpiece. A method for monitoring the health condition of an aircraft engine ignition device, which is based on the detection system of any one of the above steps, Step S1, after an ignition power inverter circuit receives a low-voltage direct-current voltage VDC, an inverter signal 1 is output; Step S2, after receiving the inversion signal 1, the power supply boosting transformer boosts the inversion signal 1 and outputs the boosted inversion signal 1 to the energy storage charging circuit for charging, and the energy storage charging circuit outputs the energy storage signal 2; Step S3, after receiving the energy storage signal 2, the discharge control circuit performs secondary boosting on the energy storage signal 2, and forms a discharge output signal 3 after the secondary boosting, and the discharge output signal is used for ignition output; S4, a signal acquisition circuit acquires an inversion signal 1 and a discharge output signal 3, a sampling circuit acquires an energy storage signal 2 from an energy storage charging circuit, and the energy storage signal is sent to the signal acquisition circuit after being processed; And S5, converting the received inversion signal 1, the energy storage signal 2 and the discharge output signal 3 by the signal acquisition circuit,