A low-temperature plasma ignition power supply and ignition system

Abstract

The invention discloses a low-temperature plasma ignition power supply, which includes a main circuit module and a control circuit module. The main circuit module includes a sequentially connected DC power supply, a voltage regulating circuit, a full-bridge inverter circuit, a series resonant circuit, and a boost output circuit. The control circuit module includes sequentially connected given input control, DSP control circuit, drive circuit, and control signal, which provide control signals for the voltage regulating circuit switch and the full-bridge inverter switch in the main circuit module. Also disclosed is a low-temperature plasma ignition system, which is composed of a low-temperature plasma ignition power supply and a boss discharge load. The invention realizes that the low-temperature plasma power supply generates low-temperature plasma according to a certain frequency and pulse width, has low energy consumption, high ignition efficiency, wide range and adjustable power supply parameters for laboratory use, fixed airborne power supply parameters, small volume and high reliability. High, to meet the ignition requirements of the engine.

Description

technical field [0001] The invention relates to the technical field of aerospace engine ignition, in particular to a low-temperature plasma ignition power supply and an ignition system. Background technique [0002] As the aircraft moves from low altitude to high altitude, and moves towards the adjacent space, the airflow parameters of the engine combustion chamber vary greatly, and the working conditions of the combustion chamber are very harsh. It is prone to difficult ignition and poor combustion stability at low altitude and high pressure and high altitude and low pressure. In order to improve the reliability of ignition and secondary ignition within the flight envelope, and broaden the stable working range, it is necessary to develop a new type of high-efficiency ignition power supply. [0003] Common ignition methods include laser-induced spark ignition, thermal plasma flow ignition, catalytic ignition, liquid oxygen kerosene ignition, low-temperature plasma ignition, ...

AI Technical Summary

Problems solved by technology

Laser-induced spark ignition needs to focus high-energy laser pulses, which is relatively large in size and weight, and is difficult to miniaturize; thermal plasma jet ignition technology has the ability to shorten ignition delay time, expand ignition range, and strengthen high-altitude secondary ignition, but the ignition efficiency is low. The equipment is complex and heavy, and it is very difficult to apply to aircraft ignition; the catalytic ignition uses a venturi tube, catalytic element and rectifier cone, which requires a high temperature of the inlet air flow, and the mixed gas passes through the platinum-rhodium wire catalytic layer to form a flame, the flame speed is low, and the rigidity is weak , Platinum-rhodium wire is expensive, susceptible to pollution and failure, which affects the reliability of ignition; liquid oxygen kerosene ignition requires an on-board oxygen cylinder and ignition power supply, the system is complex, heavy, and poor in safety, but reliable ignition; low-temperature plasma can achieve large volume Ignition, improve ignitability, shorten ignition delay time and improve ignition limit. One is to use AC to drive dielectric barrier discharge, but the barrier dielectric is easy to be broken down and burned, and there are disadvantages such as high discharge voltage and large power supply volume. There are still many shortcomings in the ignition of high-speed combustion chambers. The other is nanosecond pulse ignition technology. The instantaneous discharge voltage is as high as tens of thousands of volts, and the discharge time is 50-100ns. It has reached the application level; the ignition volume of the spark plug is small, the ignition efficiency is low, it belongs to the thermal ignition mechanism, and the ignition reliability is poor under severe working conditions; the ignition energy of the powder rod is high, the performance is reliable, and the technology is mature. The disadvantage is that it can be used once and cannot be ignited multiple times

[0008] Low-temperature plasma ignition has obvious advantages over spark plugs, but the existing low-temperature plasma power supply mainly adjusts the voltage gradually by manual means, and implements continuous discharge to generate low-temperature plasma, which consumes a lot of energy, which cannot meet the ignition requirements of aeroengines, and even Can not meet the requirements of PDE ignition and detonation, thus limiting the application of low temperature plasma ignition technology

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