加力燃烧室热射流点火的燃油自燃规律研究  

Investigation on Fuel Autoignition Law of Hot-jet Ignition for Afterburner

作　　者：徐兴平[1] 张孝春[1] 游庆江[1] 高家春[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2014年第1期39-41,74,共4页Aeroengine

基　　金：航空动力基础研究项目资助

摘　　要：为了分析燃油在高温高速气流中自燃延迟时间与燃气流动速度、燃气温度、喷油量等的关系,通过模拟试验,开展了热射流点火的燃油在高温高速气流中自燃规律的研究,经分析得出:气流温度对自燃有明显影响,在模拟的范围内存在1个自燃温度临界点(1160 K);气流温度、气流压力的升高使自燃延迟距离和延迟时间减小;气流速度的增大使自燃延迟距离增加。研究结果为航空发动机加力燃烧室的热射流点火系统和供油系统等的设计提供初步试验依据。In order to analyze the relation of autoignition delay time of fuel and gas velocity, temperature and injection quantity at high temperature and high speed airflow, the fuel autoignition law of hot-jet ignition was investigated by simulation test. The temperature of airflow has obvious influence on autoignition by analysis. There is a critical point （1160 K） of autoignition temperature at simulation range. The rising of airflow temperature and pressure would decrease the distance and time of autoignition delay. The rising of airflow velocity would increase the distance of autoignition delay. The research results provide initial experimental reference for design of hot-jet ignition system and fuel supply system of aeroengine afterburner.

关 键 词：热射流点火 自燃 延迟时间 加力燃烧室 航空发动机 

分 类 号：V233.3[航空宇航科学与技术—航空宇航推进理论与工程]