补燃循环发动机推力室声阻尼特性分析及优化  

Analysis and optimization of acoustic damping characteristics of staged combustion cycle engine thrust chamber

作　　者：孟敬芫 李斌 汪广旭 肖虹 杨宝娥 MENG Jingyuan;LI Bin;WANG Guangxu;XIAO Hong;YANG Baoe(Science and Technology on Liquid Rocket Engine Laboratory,Xi’an Aerospace Propulsion Institute,China Aerospace Science and Technology Corporation,Xi’an 710100,China;Academy of Aerospace Propulsion Technology,China Aerospace Science and Technology Corporation,Xi’an 710100,China)

机构地区：[1]中国航天科技集团有限公司,西安航天动力研究所液体火箭发动机技术重点实验室,西安710100 [2]中国航天科技集团有限公司航天推进技术研究院,西安710100

出　　处：《航空动力学报》2024年第12期398-408,共11页Journal of Aerospace Power

基　　金：重点实验室基金(6142704210102)。

摘　　要：针对补燃循环液体火箭发动机的研制需求,开展推力室混合头部声阻尼特性研究及优化分析。建立考虑阻尼源项及整流栅声阻抗的三维线性声阻尼特性模型量化混合头部的阻尼耗散,通过求解Helmholtz方程获得推力室声模态频率及增长率,并对整流栅和喷嘴等阻尼部件进行优化。研究表明:流栅阻抗与喷嘴平均流均能产生阻尼效应,且平均流作用更为显著;整流栅小孔尺寸及间距、整流腔高度、喷嘴长度是提高混合头部阻尼效应的关键参数。In view of the development requirements of the staged combustion cycle liquid rocket engine,a research and optimization analysis of the acoustic damping characteristics of the mixed head in the thrust chamber was carried out.A three-dimensional linear acoustic damping characteristic model considering the acoustic impedance of the flow distributor and the damping source term was established to quantify the damping dissipation of the mixed head.The acoustic mode frequency and growth rate of the thrust chamber were obtained by solving the Helmholtz equation,and the damping components such as the flow distributor and the injector were optimized.The results showed that the impedance of the flow distributor and the advective mean flow energy of the injector had a damping effect,and the average mean effect was more significant.The size and spacing of the hole within the flow distributor,the height of the oxidizer plenum and the length of the injector constituted the key parameters to improve the damping effect of the mixed head.

关 键 词：补燃循环液体火箭发动机 高频燃烧不稳定 混合头部 声阻尼优化 模态增长率 

分 类 号：V434.24[航空宇航科学与技术—航空宇航推进理论与工程]