固体火箭发动机转角涡脱落分类  

Classification of corner vortex shedding in solid rocket motor

作　　者：张翔宇[1,2] 何国强[1] 刘佩进[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场国家级重点实验室,西安710072 [2]中国航天科技集团公司航天动力技术研究院西安航天动力技术研究所,西安710025

出　　处：《航空动力学报》2014年第8期2003-2011,共9页Journal of Aerospace Power

摘　　要：应用三维大涡模拟(LES)方法对C1x模拟试验器进行了数值模拟,以研究转角涡脱落引起的声涡耦合现象.结果表明:与二维和轴对称LES相比,三维LES方法可以准确捕获转角涡脱落运动的三维特性及锁频现象.根据转角涡脱落是否在腔内形成声反馈循环过程可将其分为两类问题,第1类形成声反馈循环涡;第2类形成自耗散涡.燃烧室的台阶扩张比、台阶前后长径比是影响两类转角涡脱落现象的重要结构参数.A test motor named Clx was numerically simulated by the three-dimensional large eddy simulation （LES） method to study the acoustic-vortex coupling caused by corner vortex shedding. The results show that three-dimensional LES method obtains more accurate result on corner vortex shedding motion and lock-on characteristic than the two-dimensional LES and the axisymmetric LES. Two types of the corner vortex shedding are determined ac- cording to whether an acoustic feedback cycle is formed in the chamber. One type of the cor- ner vortex shedding causes the acoustic-vortex formation feedback cycle （named 1st vortex shedding）, and the other is dissipated during convecting downstream （named 2nd vortex shedding）. Step expansion ratio and aspect ratio upstream and downstream the step of com- bustion are the important parameters for summarizing the corner vertex shedding type.

关 键 词：转角涡脱落 压强振荡 声涡耦合 固体火箭发动机 大涡模拟 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]