基于DMD的双喉道矢量喷管的流场重构与分析  

Flow field reconstruction and characteristic analysis of dual-throat control vector nozzle based on dynamic mode decomposition

作　　者：王建明 刘晓东 夏瑄泽 王成军 WANG Jianming;LIU Xiaodong;XIA Xuanze;WANG Chengjun(Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System,School of Aero-engine,Shenyang Aerospace University,Shenyang 110136,China)

机构地区：[1]沈阳航空航天大学航空发动机学院辽宁省航空推进系统先进测试技术重点实验室,沈阳110136

出　　处：《航空动力学报》2024年第6期186-195,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(51476106)。

摘　　要：采用分离涡模拟方法对双喉道矢量喷管的三维流场进行数值模拟,分析原始流场的压力系数以及密度梯度分布。运用动力学模态分解技术(DMD)对喷管z=0截面压力系数进行模态分解,选取得到的模态重构流场,将对应的模态进行时间演化并分析其特性。结果表明:利用动力学模态分解得到的前5阶模态可以较完整地重构出双喉道矢量喷管的压力系数场,其中第1模态主要反映的是分离激波的摆动现象以及其对回流区与主流之间剪切层的压力脉动的影响。2阶模态的主要特征是剪切层中的涡系脱落。3阶模态中主要反映的是分离激波强度的变化。4阶、5阶模态主要表现为分离激波位置以及强度上的高阶振荡。The three-dimensional flow field of the thrust vectoring nozzle was simulated by detached eddy simulation method,and the pressure coefficient and density gradient distribution of flow field were analyzed.The dynamic modal decomposition(DMD)technology was applied to modal decomposition of the pressure coefficient of the z=0 section,the obtained modal recombination flow field was selected to evolve in time.The results indicated that the first five-order modes obtained by dynamic modal decomposition can be used to reconstruct the pressure coefficient field of the dual-throat control vector nozzle more completely.The first-order mode mainly illustrated the swing phenomenon of the separated shock wave and its influence on the pressure pulsation of the shear layer between the recirculation zone and the main flow;the second-order mode mainly illustrated the separation of the vortex system in the shear layer.The third-order mode mainly illustrated the change in the intensity of the separated shock wave,the fourth and fifth-order modes were mainly manifested as high-order oscillations in the position and intensity of the separated shock wave and the shear layer near the recirculation zone.

关 键 词：推力矢量技术 双喉道矢量喷管 非定常流动 动力学模态分解 激波边界层干扰 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]