A system and method for monitoring the health of an aircraft engine ignition device

Abstract

The application discloses a kind of aero-engine ignition device health condition monitoring system, including engine ignition device and sampling circuit, signal acquisition circuit and health management system, the engine ignition device includes ignition power inverter circuit, power boost transformer, energy storage charging circuit, discharge control circuit and discharge output circuit connected in sequence, the energy storage charging circuit is connected to the sampling circuit, the signal acquisition circuit and ignition power inverter circuit, discharge output circuit, sampling circuit are connected respectively, and the health management system is connected with signal acquisition circuit.Based on the system, a kind of aero-engine ignition device health condition monitoring method is provided, by special engine ignition device, and the signals of three different positions in ignition device are collected and monitored, the signals of three different positions are monitored, and the health condition of engine ignition device is monitored as a whole.

Description

Technical Field

[0001] This invention relates to the field of engine monitoring, and in particular to a system and method for monitoring the health status of an aircraft engine ignition device. Background Technology

[0002] The ignition system for aero-engines is a crucial accessory for engine starting and ignition. Its main function is to output a high-voltage pulse of electricity after power is connected, which breaks down the contact tip to ignite the air-fuel mixture in the engine's combustion chamber, thus achieving engine starting and ignition. Currently, all ignition systems in use can only achieve status output by creating an electric spark through contact tip breakdown. The online operating status of the ignition system itself cannot be monitored in real time. If an ignition failure occurs, it cannot be troubleshooted in a timely manner, which will delay engine testing progress and even reduce aircraft operational availability.

[0003] With the ever-changing demands of flight operations and the continuous improvement of combat performance, ignition devices that can only achieve one mode of ignition output through electric nozzles can no longer meet the operational requirements of engines. Online monitoring of the health of ignition devices has become a necessary development trend. Summary of the Invention

[0004] The purpose of this invention is to provide a monitoring system for the health status of an aircraft engine ignition device, and based on this system, a method for monitoring the health status of an aircraft engine ignition device. By using a special engine ignition device and collecting and monitoring signals from three different locations within the ignition device, the health status of the engine ignition device can be monitored more comprehensively, thus solving the aforementioned problems.

[0005] The technical solution adopted in this invention is as follows:

[0006] A monitoring system for the health status of an aircraft engine ignition device includes an engine ignition device, a sampling circuit, a signal acquisition circuit, and a health management system. The engine ignition device includes an ignition power inverter circuit, a power step-up transformer, an energy storage charging circuit, a discharge control circuit, and a discharge output circuit connected in sequence. The sampling circuit is connected to the energy storage charging circuit. The signal acquisition circuit is connected to the ignition power inverter circuit, the discharge output circuit, and the sampling circuit, respectively. The health management system is connected to the signal acquisition circuit.

[0007] To better implement this solution, the ignition power inverter circuit further includes a pulse width modulation chip U1, and the waveform output by the pulse width modulation chip U1 is a square wave signal 1.

[0008] To better implement this solution, the power supply step-up transformer further includes a flyback transformer T1, and the energy storage and charging circuit includes an energy storage capacitor C3. One end of the flyback transformer T1 is connected to the ignition power inverter circuit, and the other end of the flyback transformer T1 is connected to the energy storage capacitor C3. After receiving the signal from the ignition power 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.

[0009] To better implement this solution, 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. After receiving a signal, the transformer T3 performs a secondary boost on the signal to form a discharge output signal 3, which is output through the discharge output circuit.

[0010] To better implement this solution, the discharge output circuit further includes a discharge nozzle.

[0011] A method for monitoring the health status of an aircraft engine ignition device, based on any of the detection systems described above, includes the following steps:

[0012] Step S1: After receiving the low-voltage DC voltage VDC, the ignition power inverter circuit outputs inverter signal 1;

[0013] Step S2: After receiving inverter signal 1, the power supply step-up transformer boosts the voltage of inverter signal 1 and outputs it to the energy storage charging circuit for charging. The energy storage charging circuit outputs energy storage signal 2.

[0014] Step S3: After receiving the energy storage signal 2, the discharge control circuit performs a second boost on the energy storage signal 2, and the second boost generates a discharge output signal 3, which is then used for ignition output through the discharge output circuit.

[0015] Step S4: The signal acquisition circuit acquires the inverter signal 1 and the discharge output signal 3, and the sampling circuit acquires the energy storage signal 2 from the energy storage charging circuit, and then sends it to the signal acquisition circuit after processing.

[0016] Step S5: The signal acquisition circuit converts the received inverter signal 1, energy storage signal 2 and discharge output signal 3 and feeds them back to the health management system. The health management system monitors the inverter signal 1, energy storage signal 2 and discharge output signal 3 in real time during the operation of the engine ignition device, thereby monitoring the health status of the engine ignition device.

[0017] In the monitoring system described in this solution, after a low-voltage DC power supply is input, the pulse width modulation chip U1 and its auxiliary circuits form an ignition power inverter circuit, generating an inverter signal 1. Then, after being boosted by a flyback transformer, the energy storage capacitor is charged, generating an energy storage signal 2. When the energy storage voltage reaches a set value, the discharge control switch is turned on through a sampling circuit, generating a discharge output signal 3. The inverter signal 1, energy storage signal 2, and discharge output signal 3 are collected by the signal acquisition system and fed back to the health management system, thereby realizing online monitoring of the ignition health status.

[0018] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0019] 1. The present invention provides a monitoring system for the health status of an aircraft engine ignition device, and based on the system, provides a method for monitoring the health status of an aircraft engine ignition device. By using a special engine ignition device and collecting and monitoring signals from three different locations in the ignition device, the health status of the engine ignition device can be monitored.

[0020] 2. The present invention provides a monitoring system for the health status of an aircraft engine ignition device, and based on this system, a method for monitoring the health status of an aircraft engine ignition device is provided. Through a special engine ignition device, signals from three different locations within the ignition device are collected and monitored. The signals from the three different locations are used together as the health status of the engine ignition device, enabling a relatively comprehensive monitoring of the health status of the engine ignition device. Attached Figure Description

[0021] To more clearly illustrate this technical solution, the accompanying drawings used in the embodiments will be briefly described below. It should be understood that, for those skilled in the art, other related drawings can be obtained based on these drawings without any creative effort.

[0022] Figure 1 This is a schematic diagram of the principle of the present invention;

[0023] Figure 2 This is a circuit connection diagram of the present invention. Detailed Implementation

[0024] To more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments, and therefore should not be regarded as a limitation on the scope of protection. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "set up," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0026] The following is combined Figures 1 to 2 The present invention will be described in detail below.

[0027] Example 1

[0028] A monitoring system for the health status of an aircraft engine ignition device, such as Figure 1 The system includes an engine ignition device and a sampling circuit, a signal acquisition circuit, and a health management system. The engine ignition device includes an ignition power inverter circuit, a power step-up transformer, an energy storage charging circuit, a discharge control circuit, and a discharge output circuit connected in sequence. The sampling circuit is connected to the energy storage charging circuit. The signal acquisition circuit is connected to the ignition power inverter circuit, the discharge output circuit, and the sampling circuit, respectively. The health management system is connected to the signal acquisition circuit.

[0029] Working Principle: In the monitoring system described in this solution, after a low-voltage DC voltage VDC is input to the ignition power inverter circuit, the ignition power inverter circuit generates an inverter signal. Then, after being stepped up by the power supply step-up transformer, the energy storage and charging circuit charges. When the energy storage voltage reaches the set value, the discharge control circuit is turned on, generating a discharge output signal which is output through the discharge output circuit. The signal acquisition system collects the inverter signal from the ignition power inverter circuit and the discharge output signal from the discharge output circuit. The sampling circuit collects the energy storage signal from the energy storage and charging circuit and uploads it to the signal acquisition circuit. The signal acquisition circuit then feeds back the inverter signal, the energy storage signal, and the discharge output signal to the health management system. The health management system monitors these three signals in real time, thereby realizing online monitoring of the ignition health status.

[0030] Example 2

[0031] A monitoring system for the health status of an aircraft engine ignition device, such as Figure 1The system includes an engine ignition device and a sampling circuit, a signal acquisition circuit, and a health management system. The engine ignition device includes an ignition power inverter circuit, a power step-up transformer, an energy storage charging circuit, a discharge control circuit, and a discharge output circuit connected in sequence. The sampling circuit is connected to the energy storage charging circuit. The signal acquisition circuit is connected to the ignition power inverter circuit, the discharge output circuit, and the sampling circuit, respectively. The health management system is connected to the signal acquisition circuit.

[0032] like Figure 2 The ignition power inverter circuit includes a pulse width modulation chip U1, which outputs a square wave signal 1. The power boost transformer includes a flyback transformer T1, and the energy storage charging circuit includes an energy storage capacitor C3. One end of the flyback transformer T1 is connected to the ignition power inverter circuit, and the other end is connected to the energy storage capacitor C3. After receiving a signal from the ignition power inverter circuit, the flyback transformer T1 stores energy in the energy storage capacitor C3, and the stored energy waveform is a triangular wave signal 2. The discharge control circuit includes a transformer T3 and a capacitor C5. The transformer T3 is connected to the energy storage charging circuit. After receiving a signal, the transformer T3 boosts the signal a second time to form a discharge output signal 3, which is output through the discharge output circuit. The discharge output circuit includes a charging nozzle.

[0033] Working principle: such as Figure 2 The pulse width modulation chip U1 and its auxiliary circuits form the ignition power inverter circuit. When a low-voltage DC voltage (12~32) VDC is input, the waveform parameters of inverter signal 1 can be set through capacitor C2 and resistor R3. The frequency setting range is 100Hz~500KHz, and the output waveform is a square wave. After transistor Q1 is turned on, the primary winding of flyback transformer T1 stores energy. After transistor Q1 is turned off, flyback transformer T1 performs secondary voltage boosting, charging energy storage capacitor C3 to form energy storage signal 2. The waveform parameters of energy storage signal 2 are determined by sampling resistor R5, sampling resistor R6, and transistor Q2. The conduction voltage determines the waveform, which is a triangular wave. After transistor Q2 is turned on, the energy storage voltage is boosted twice by transformer T3 and capacitor C5 to form discharge output signal 3. The waveform parameters of discharge output signal 3 are determined by transformer T3 and oscillation capacitor C5. The signal acquisition system collects and converts the inverter signal 1, energy storage signal 2 and discharge output signal 3, and feeds them back to the health management system. The health management system monitors the inverter signal 1, energy storage signal 2 and discharge output signal 3 in real time during the operation of the ignition device, thereby monitoring the health status of the ignition device.

[0034] The other parts of this embodiment are the same as those in Embodiment 1 above, so they will not be described again.

[0035] Example 3

[0036] A method for monitoring the health status of an aircraft engine ignition device, based on the detection system described in Embodiment 1 or 2 above, includes the following steps:

[0037] Step S1: After receiving the low-voltage DC voltage VDC, the ignition power inverter circuit outputs inverter signal 1;

[0038] Step S2: After receiving inverter signal 1, the power supply step-up transformer boosts the voltage of inverter signal 1 and outputs it to the energy storage charging circuit for charging. The energy storage charging circuit outputs energy storage signal 2.

[0039] Step S3: After receiving the energy storage signal 2, the discharge control circuit performs a second boost on the energy storage signal 2, and the second boost generates a discharge output signal 3, which is then used for ignition output through the discharge output circuit.

[0040] Step S4: The signal acquisition circuit acquires the inverter signal 1 and the discharge output signal 3, and the sampling circuit acquires the energy storage signal 2 from the energy storage charging circuit, and then sends it to the signal acquisition circuit after processing.

[0041] Step S5: The signal acquisition circuit converts the received inverter signal 1, energy storage signal 2 and discharge output signal 3 and feeds them back to the health management system. The health management system monitors the inverter signal 1, energy storage signal 2 and discharge output signal 3 in real time during the operation of the engine ignition device, thereby monitoring the health status of the engine ignition device.

[0042] Working principle: In the monitoring method described in this solution, after inputting a low-voltage DC voltage VDC, the pulse width modulation chip U1 and its auxiliary circuit form an ignition power inverter circuit, generating an inverter signal 1; then, after being boosted by a flyback transformer, the energy storage capacitor is charged, generating an energy storage signal 2; when the energy storage voltage reaches the set value, the sampling circuit turns on the discharge control switch, generating a discharge output signal 3; the signal acquisition system collects the inverter signal 1, the energy storage signal 2, and the discharge output signal 3, and feeds them back to the health management system, thereby realizing online monitoring of the ignition health status.

[0043] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A monitoring system for the health status of an aircraft engine ignition device, comprising an engine ignition device and a sampling circuit, a signal acquisition circuit, and a health management system, characterized in that: The engine ignition device includes an ignition power inverter circuit, a power step-up transformer, an energy storage and charging circuit, a discharge control circuit, and a discharge output circuit connected in sequence. The sampling circuit is connected to the energy storage and charging circuit. The signal acquisition circuit is connected to the ignition power inverter circuit, the discharge output circuit, and the sampling circuit, respectively. The health management system is connected to the signal acquisition circuit. 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; the power boost transformer includes a flyback transformer T1, and the energy storage charging circuit includes an energy storage capacitor C3. One end of the flyback transformer T1 is connected to the ignition power inverter circuit, and the other end of the flyback transformer T1 is connected to the energy storage capacitor C3. After receiving a signal from the ignition power inverter circuit, the flyback transformer T1 stores energy in the energy storage capacitor C3, and the stored energy waveform is a triangular wave signal. The discharge control circuit includes a transformer T3 and a capacitor C5. The transformer T3 is connected to the energy storage and charging circuit. After receiving the signal, the transformer T3 performs a secondary voltage boost on the signal to form a discharge output signal, which is output through the discharge output circuit.

2. The monitoring system for the health status of an aircraft engine ignition device according to claim 1, characterized in that: The discharge output circuit includes a discharge nozzle.

3. A method for monitoring the health status of an aircraft engine ignition device, based on the aircraft engine ignition device health status monitoring system described in claim 1 or 2, characterized in that: Includes the following steps: Step S1: After receiving the low-voltage DC voltage VDC, the ignition power inverter circuit outputs an inverter signal (1). Step S2: After receiving the inverter signal (1), the power supply step-up transformer boosts the inverter signal (1) and outputs it to the energy storage charging circuit for charging. 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 a second boost on the energy storage signal (2), and after the second boost, a discharge output signal (3) is generated, which is then used for ignition output through the discharge output circuit; Step S4: The signal acquisition circuit acquires the inverter signal (1) and the discharge output signal (3), and the sampling circuit acquires the energy storage signal (2) from the energy storage charging circuit, and then sends it to the signal acquisition circuit after processing; Step S5: The signal acquisition circuit converts the received inverter signal (1), energy storage signal (2) and discharge output signal (3) and feeds them back to the health management system. The health management system monitors the inverter signal (1), energy storage signal (2) and discharge output signal (3) in the working state of the engine ignition device in real time, so as to realize the monitoring of the health status of the engine ignition device.

Images