Ma=4液体碳氢燃料超燃冲压发动机点火试验  

Ignition experimental for liquid hydrocarbon fueled scramiet with simulated flight Mach 4

作　　者：李大鹏[1] 丁猛[1] 梁剑寒[1] 刘卫东[1] 王振国[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2009年第4期385-389,395,共6页Journal of Propulsion Technology

摘　　要：在模拟飞行马赫数Ma=4,飞行高度H=20 km的条件下,针对不同燃料喷射方式、不同点火位置以及不同燃料当量比,进行了液体碳氢燃料超燃冲压发动机内点火过程的直连式试验研究。试验结果表明,在低飞行马赫数条件下,采用火花塞+引导氢的点火方式可以顺利实现单一点火位置条件下的火焰传播过程,并最终在整个燃烧室内实现各喷射位置燃料的燃烧;采用火花塞+引导氢的点火方式有利于实现煤油的点火、火焰维持与稳定燃烧;对于多位置喷油方案,引导氢与煤油的相对位置和当量比配比会使各喷射位置煤油的燃烧产生相互影响;试验最终在当量比0.66的条件下实现了煤油自持、稳定的燃烧。Several direct-connect ignition experiments were performed for a liquid hydrocarbon(kerosene) fueled scramjet combustor on the simulated flight Mach 4.Various injection modes,equivalence ratios and igniter positions were studied.It is indicated that pilot hydrogen plus spark igniter was an effective method to ignite,sustain flame and stabilize combustion for liquid hydrocarbon scramjet.At a single igniter position,flame can spread through whole combustor.A self-sustained and stable combustion process of ker...

关 键 词：超燃冲压发动机 点火 煤油 稳定燃烧 自持燃烧 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]