High energy solid state discharge igniting module

Abstract

The invention relates to a high energy solid state discharge igniting module, a inverter component is composed of a PWM control chip U1 which enables electric connection between a filter circuit and a boosting transformer and its auxiliary circuit, the boosting transformer is electrically connected to an energy-storage capacitor component through a high voltage silicon stack D1, a discharge control component is electrically connected to a part between the energy-storage capacitor component and a high voltage boost circuit, the high voltage boost circuit is composed of a high-frequency transformer electrically connected to a mutual inductance coil L1 and an oscillation capacitance C8, a dc source DC is electrically connected to the filter through a power supply input interface for completing the filtering, and converted to high voltage AC pulse through an inversion circuit and the boosting transformer, and is charged through the silicon stack rectification backward energy-storage capacitor component, and high voltage is output to a high voltage output interface can be completed by the discharge control circuit and the high voltage boost circuit. The high energy solid state discharge igniting module has the advantages of high loss of gas discharge tube energy, low transition efficiency and short life, and the output energy and transition efficiency can be increased by about 30%. The high energy solid state discharge igniting module has the characteristics of high efficiency, long life and no radioactivity.

Description

technical field [0001] The invention relates to an ignition device for igniting the fuel mixture gas of an aeroengine during starting and running. Background technique [0002] Ignition device is an important part of modern aero-engine, and it is a key component of engine ground start and air parking restart. success rate. The ignition device for aero-engines works in a short-time repetitive manner, and the power input is divided into two types: DC 28V and AC 115V / 400Hz. Among various ignition devices, the ignition type commonly used in aero-engines is the DC inverter capacitive discharge ignition device, which accounts for more than 90%. [0003] In the prior art, the DC inverter capacitive discharge ignition device of an aero-engine generally consists of a filtering component, an inverter circuit, a boosting component, a rectifying component, an energy storage component and a discharge control component. Its working principle is: after the DC power supply is filtered by...

AI Technical Summary

Problems solved by technology

The ignition devices used in domestic aero-engines generally have disadvantages such as large size, heavy weight, low electrical efficiency, low reliability, short life, and inconvenient radioactive disposal.

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