KIVA程序在固体火箭发动机内流场数值模拟中的应用  

Application of KIVA Program to Numerical Simulation of Internal Flowfields in Solid Rocket Motor

作　　者：孙小团[1] 张平[1] 

机构地区：[1]北京理工大学

出　　处：《燃烧科学与技术》1997年第1期34-41,共8页Journal of Combustion Science and Technology

摘　　要：本文以ＫＩＶＡ程序为研究起点，结合固体火箭发动机燃烧室内流场的特点，新增了边界种类和推进剂燃烧反应模型，用非正交的计算网格实现了对推进剂燃面的动态跟踪，采用ＡＬＥ法求解气相流场。算例为三维短管型装药的燃烧室内轴对称可压流场。数值模拟的结果揭示了燃烧室内瞬态流动的细节。This paper bases on the KIVA program, which is a three dimensional computer code. The modified code includes new boundary conditions and a solid propellant combustion model considering the special features of internal flowfields in the chamber of SRM (Solid Rocket Motor). A non orthogonal cells system is applied to trace the moving burning surfaces of propellant. The implicit ALE method is applied to the calculation of gas phase fluid flows. The computation of an example is carried out, which is a SRM with a three dimensional short tube grain. The computation results show the details of the transient internal flowfields. A direct method is presented for the simulation of the transonic flows in SRM.

关 键 词：固体火箭发动机 内流场 数值模拟 KIVA程序 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]