装药及喷管型面对固体发动机涡声振荡影响  

Influence of internal surfaces of grains and nozzles on vortex-acoustic oscillations in solid rocket motor

作　　者：曹俊维 李军伟[1] 王小东 王宁飞[1] CAO Junwei;LI Junwei;WANG Xiaodong;WANG Ningfei(School of Aerospace Engineering,Beijing Institute of Technology,Beijing100081,China;Inner Mongolia Power Machinery Research Institute,Hohhot010010,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]内蒙动力机械研究所,呼和浩特010010

出　　处：《航空学报》2024年第21期229-244,共16页Acta Aeronautica et Astronautica Sinica

基　　金：中央高校基本科研业务费专项资金(2024CX06002);国家自然科学基金(22027811)。

摘　　要：为研究某翼柱装药固体火箭发动机内部压力振荡的原因,应用大涡模拟等方法计算了流场,捕捉到了压强振荡频率与涡脱落频率,分析了不同时刻燃面、不同喷管收敛段以及不同突扩结构对涡声耦合的影响。结果显示:翼柱型装药在燃面退移早期更易发生涡声振荡,燃烧末期时流场比较稳定;通过调整喷管收敛段的型面能一定程度上减弱压强振荡,但无法打破涡声频率;通过改变突扩结构能有效消除涡声耦合现象,从而抑制固体火箭发动机燃烧室不稳定燃烧现象。To study the cause of internal pressure oscillation of a Solid Rocket Motor(SRM) with the finocyl grain,we calculate the flow field with large eddy simulation and other methods,capture the pressure oscillation frequency and the vortex shedding frequency,and analyze the effects of burning surfaces at different times,different nozzle convergence sections and different dump structures on the vortex-acoustic coupling.The results show that the finocyl grain is more prone to vortex-acoustic oscillation in the early stage of the grain burnback,while the flow field is relatively stable at the end of combustion.By adjusting the convergence section surface of the nozzle,the pressure oscillation can be weakened to a certain extent.However,the vortex-acoustic frequency cannot be broken.By changing the dump structure,the vortex-acoustic coupling phenomenon can be effectively eliminated,so as to inhibit the unstable combustion of combustion chambers of solid rocket motors.

关 键 词：涡声耦合 压力振荡 燃面 喷管收敛段 突扩结构 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]