Low-temperature plasma non-hot point fire steadying flame device

Abstract

The invention provides a low-temperature plasma no-heat ignition flame stabilization device which adopts the low-temperature plasma to cause the flammable mixed gas to produce a plurality of free radicals and active components such as electrons and hydroniums, etc. to implement large-volume igniting flammable mixed gas, belonging to aeronautics and astronautics power thrust system field. The invention consists of a high pressure powers supply 1, a high pressure electrode 2, an air inlet hole 3, an air inlet seat 4, a retaining medium 5, a low voltage electrode 6, a rectifier 7 and a combustion chamber 8; the high voltage electrode 2 is hermetically connected with the air inlet seat 4 and is connected with a high voltage electrode 1; the air inlet hole 3 is provided with openings on the air inlet seat 4; the interior of the air inlet seat 4 is hermetically connected with the retaining medium 5; the external wall of the rectifier 7 is tightly close to the internal wall of the retaining medium 5; the upstream is the high voltage electrode 1 and the downstream is the combustion room 8 which is hermetically connected with the retaining medium 5. The invention can implement large-volume ignition, reduces the voltage amplitude to large extent, has simple structure and reliable system, and is an ignition device with extremely developmental prospect used by the aeronautics and astronautics and industrial combustion systems.

Description

technical field [0001] The invention relates to a low-temperature plasma non-thermal ignition combination device for an aerospace propulsion system, which uses low-temperature plasma to generate a large number of free radicals and active components such as electrons and ions in a combustible gas mixture to realize large-volume ignition of a combustible gas mixture The device belongs to the field of aerospace power propulsion system. Background technique [0002] At present, the most commonly used ignition methods for fuel combustion in aerospace propulsion systems are: (1) hot surface or filament; (2) spot flame; (3) laser-induced spark; (4) discharge spark and plasma flow. For (1), the ignition delay time is longer, and the life of the hot surface or filament is also shorter. (2) then there is the deficiency that the spot flame may be blown out and need to stabilize the flame. Type (3) laser-induced spark ignition requires focused high-energy laser pulses. The (4) spark ...

AI Technical Summary

Problems solved by technology

Its disadvantages are: the glow discharge generated by the channel requires high voltage, ceramics are easy to break down, and the service life is short

The ignition pressure and gas flow velocity of combustible gas mixture are low. Generally, the gas pressure is 0.01-0.03Mpa, and the gas flow velocity is less than 30m / s. Such a narrow working range greatly limits its application in aerospace propulsion systems.

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