氢喷射温度对氢氧火箭发动机燃烧稳定性的影响  

The effect of initial hydrogen temperature on LOX/GH_2 liquid rocket engine combustion instability

作　　者：程钰锋[1] 聂万胜[2] 丰松江[1] 

机构地区：[1]装备指挥技术学院研究生院,北京101416 [2]装备指挥技术学院航天装备系,北京101416

出　　处：《火箭推进》2009年第1期27-30,共4页Journal of Rocket Propulsion

基　　金：国家自然科学基金(50576105)

摘　　要：应用CFD方法对氢氧火箭发动机中高频燃烧不稳定性进行了数值模拟,研究分析了不同工况条件下氢喷射温度对燃烧振荡的影响规律,得出了压力振荡频率变化规律及稳定性极限图。结果表明:在一定的氢喷射温度范围内会发生不稳定燃烧,且随着混合比的增大,发生不稳定燃烧的氢喷射温度上限增大;不稳定燃烧振荡主频呈倍频关系,且在氢喷射温度(70K～110K)内,振荡主频最大。The combustion instability in one LOX/GH2 liquid rocket engine was studied by using CFD methods. The effects of initial hydrogen operational conditions were studied, and the rules temperature on combustion oscillation at different of instable pressure frequencies and the combustion stability limiting map are developed. Resuhs show that combustion instability will happened at a specific initial hydrogen temperature bound and the upper limit of this initial hydrogen temperature bound will increases as the O/F increases. In addition, the instable dominant frequencies are present as multiple frequencies and have a maximum value at a hydrogen temperature bound from 70 K to 110 K.

关 键 词：氢氧火箭发动机 不稳定燃烧 数值模拟 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]