隔板对液体火箭发动机燃烧室声学模态特性的影响  

Effects of baffle on the acoustic mode characteristics of liquid rocket engine combustion chambers

作　　者：张泽昊 樊志伟 董立宝 何博 聂万胜 ZHANG Zehao;FAN Zhiwei;DONG Libao;HE Bo;NIE Wansheng(Department of Aerospace Science and Technology,Space Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学宇航科学与技术系,北京101416

出　　处：《航空动力学报》2024年第4期234-243,共10页Journal of Aerospace Power

基　　金：国家自然科学基金面上项目(51876219)。

摘　　要：通过采用声学有限元法,求解带有平均流源项的亥姆霍兹方程,进而在考虑燃烧室高温、平均流场因素基础上分析了隔板结构参数对液体火箭发动机燃烧室声学模态特性影响规律。结果表明:增加隔板数目或长度,均会降低燃烧室1阶切向模态的特征频率;存在最佳隔板数目4,使燃烧室1阶切向模态阻尼率最大;而隔板长度越长,1阶切向模态声压波腹的分布面积越小,阻尼率越大;隔板型式对燃烧室1阶切向模态特性影响较小。The Helmholtz equation with the mean flow source term was solved by the acoustic finite element method.Then,on the basis of considering the high temperature and average flow field of the combustion chamber,the influence of baffle structure parameters on the acoustic mode characteristics of the liquid rocket engine combustion chamber was analyzed.The results showed that:increasing the number or length of baffle reduced the eigenfrequency of the first-order tangential mode of the combustion chamber;when the number of baffle was 4,the damping rate of the first-order tangential mode of the combustion chamber was greatest;the longer length of the baffle indicated the smaller distribution area of the first-order tangential mode acoustic pressure and the larger damping rate;the type of baffle had an insignificant effect on the first-order tangential mode characteristics of the combustion chamber.

关 键 词：隔板 液体火箭发动机 燃烧室 声学模态特性 亥姆霍兹方程 

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]