用高精度迎风格式模拟潜入式喷管流场  

Application of higher order upwind scheme to simulating submerged nozzle flowfield

作　　者：袁新[1] 金琰[1] 

机构地区：[1]清华大学热能工程系,北京100084

出　　处：《清华大学学报（自然科学版）》2000年第6期45-48,共4页Journal of Tsinghua University(Science and Technology)

基　　金：国家自然科学基金项目 !( 5 96760 0 4);国防科技重点实验室基金

摘　　要：为了研究固体火箭发动机潜入式喷管内部工质的流动特性 ,首先采用改进的 L U-SGS方法和高精度、高分辨率的 MUSCL TVD格式数值模拟了 JPL美国喷气推进实验室喷管 ,数值模拟结果和实验结果吻合得很好。证明了这种方法可以准确地捕捉到流场中可能出现的各种复杂流动。用同样的数值计算方法模拟了固体火箭发动机潜入式喷管 3个时刻的准三维流场 ,对复杂的计算区域做了分区处理 ,为复杂的边界条件做了简化处理模型。分析了燃烧室潜入段处涡的形成和发展过程以及入口湍流度对喷管的气动参数的影响 。This paper analyzed the flow characteristics of a solid rocket motor (SRM) submerged nozzle. A new Lower Upper implicit scheme and a high accuracy and high resolution MUSCL TVD scheme were employed to simulate the axisymmetric flowfield of the JPL nozzle. The simulation results agreed well with experimental data, which verified that the complicated phenomena in the flowfield can be accurately modeled with the scheme. The same scheme was applied to simulate the flowfield of a submerged nozzle. The multiblock technique and a simplifed model was used to model with the complicated flow area and boundary conditions. The vortex growth in the submerged nozzle and the influence of the inflow turbulence intensity on the aerodynamic parameters in the nozzle were discussed. The analysis can be used to design high perfomance SRM.

关 键 词：固体火箭发动机 潜入式喷管 流场 迎风格式 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]