A frequency-stabilized aero-engine ignition device using a dual-stage power supply

Abstract

The invention discloses a frequency-stabilized aero-engine ignition device using a dual-stage power supply, comprising an EMI filter circuit, a flyback stabilized voltage isolation power supply module circuit, a self-excited flyback conversion booster circuit, a rectifier circuit, an energy storage circuit and a discharge circuit , EMI filter circuit, regulated isolation power supply circuit, flyback boost conversion circuit, rectifier circuit and discharge circuit are connected in sequence; the rectifier circuit includes a high-voltage silicon stack. Charge the energy storage circuit; when the voltage difference of the high-energy gas discharge tube in the discharge circuit is greater than the breakdown voltage, the high-energy gas discharge tube breaks down, outputs the energy stored in the high-voltage mica capacitor, breaks down the oil and gas mixture, forms a spark, and completes the ignition . The first-stage power supply of the invention realizes the functions of regulated output and electrical isolation, solves the problem that the spark frequency fluctuates with the power supply, and realizes the stable ignition frequency within the full voltage range.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a frequency-stabilized aero-engine ignition device using a dual-stage power supply. Background technique [0002] The ignition system of an aero-engine consists of an ignition device, an ignition cable, and an ignition nozzle. Usually, the aeroengine ignition device is powered by DC 28V. The ignition device converts the input DC low-voltage electrical signal into a high-voltage pulse electrical signal (2800V) through the internal conversion circuit. The high-voltage pulse electrical signal is transmitted to the ignition nozzle through the ignition cable, and the high-voltage pulse electrical signal Break down the positive and negative poles of the ignition nozzle, so that the nozzle generates electric sparks, thereby igniting the fuel mixture in the engine combustion chamber, and completing the engine ignition process. [0003] At present, the engine ignition system in the prior art,...

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Problems solved by technology

[0003] At present, the engine ignition system in the prior art, including domestic and imported ones, the high-voltage pulse output by the ignition device and the spark frequency of the ignition nozzle are greatly affected by the power supply voltage. Under low voltage, the ignition frequency is very low, and the engine ignites successfully. The ignition rate is low, and under high voltage conditions, the ignition frequency is too fast, which is not conducive to the improvement of the life of the ignition system. The ignition frequency of a domestic ignition device tested at a low voltage of 12V is only 0.5Hz, which is far lower than the requirement of 3Hz at a rated voltage of 28V. The ignition frequency at high voltage 36V is 6Hz, which is much higher than the rated requirement

[0004] The patent of publication number CN109653877A "a fixed-frequency ignition circuit for aeroengine ignition" requires the use of a discharge pulse signal sampling shaping unit and a discharge frequency control signal synthesis unit. The circuit structure is complex and the stored energy is small (only 1.7J). The output spark frequency is as high as 6.18Hz, the overall efficiency is not enough, and the input voltage range is small, which belongs to the low energy efficiency high frequency ignition device

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