涡流混气中冷等离子体点火特性研究  

Ignition characteristics of low temperature plasma igniter in vortex mixture

作　　者：王玉清 秦飞[1] 付蒙[2] 蒋妮 李立翰[2] WANG Yuqing;QIN Fei;FU Meng;JIANG Ni;LI Lihan(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]北京动力机械研究所,北京100074

出　　处：《推进技术》2025年第3期101-108,共8页Journal of Propulsion Technology

摘　　要：为了实现冲压发动机在大攻角和侧滑角下安全、可靠工作,并有效解决导弹机动飞行过程中冲压发动机熄火的问题,设计了一种与冲压发动机共用气源和燃料的冷等离子体点火器,开展了不同来流条件下冲压发动机涡流混气中的等离子体点火实验研究。研究了冲压发动机涡流混气中低温等离子体的点火特性,分析了该点火器燃烧室流场分布,并根据冲压发动机涡流混气低速涡区选定了点火器安装位置和工作状态。通过单项点火实验,研究了不同点火器结构尺寸对燃烧火焰长度和强度的影响。通过点火器与发动机联合实验,获取了基于等离子体点火器的发动机点火特性。研究结果表明:设计的冷等离子体电弧点火器,实现了冲压发动机多次点火和持续燃烧的要求,在不同的气流速度、温度和贫富油状态下,点火器燃烧效果良好。To ensure the safe operation of the ramjet under large angles of attack and significant sideslip,and to address the issue of the ramjet engine stalling during missile maneuvering,a low-temperature plasma ig⁃niter that shares the gas source and fuel with the ramjet engine was designed.This study focused on plasma igni⁃tion within the vortex mixture of the ramjet engine under different incoming flow conditions.The research includ⁃ed an analysis of the ignition characteristics of low-temperature plasma in the vortex mixture of the ramjet engine.By examining the flow field of the ignition combustion chamber,the optimal installation position and operating state of the igniter were determined based on the low-speed regions of the ramjet mixture.Single-phase ignition experiments were conducted to study the effects of different ignition structure sizes on the length and intensity of the combustion flame.Joint experiments of the igniter and engine were performed to analyze the ignition character⁃istics of the engine based on the plasma igniter.The results indicate that the low-temperature plasma igniter effec⁃tively meets the requirements for multiple ignitions and continuous combustion of the ramjet.The igniter exhibited good combustion performance under different air speeds,temperatures and fuel conditions.

关 键 词：冲压发动机 冷等离子体 点火器 涡流混气 点火实验 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程]