突扩后突缩的二维流场计算

CALCULATION ON 2-D INTERNAL FLOW FIELD WITH SUDDEN SHRINK-AFTER-SUDDEN ENLARGEMENT

关键词:  固体火箭发动机  尾喷管  二维流  流伤  计算

Key words:  Solid rocket engine  Jet nozzle  Two-Dimensional flow  Flow field  Computation

摘要:

本文模拟固体火箭发动机药柱后端流场,建立了简化的计算模型,采用压力耦合方程半隐式解法,对突扩后突缩的二维粘性流场进行了计算分析.在计算过程中,对网格划分及控制体的选择、复杂边界条件的处理、差分格式的选取、方程的离散化及方程的解法等做了分析研究.计算结果表明:在突扩台阶后得到的二次涡与Finash,F.和Ghaddar,N.K.等人的结论吻合,进一步证实了Pan,F.和Acriuos,A.的嵌套涡族理论.

Abstract:

In this paper the flow field after grains in solid rocket engine is simulated and a simplified calculation model is assumed.By means of SIMPLE algorithm,a calculation analysis to the 2-D internal flow field with sudden shrink-after-sudden enlargement is also presented. In the calculation analysis, grid dividing, control volume selecting, treatment method of complex boundary condition, difference scheme selecting, equation discretization and solution of equations, etc.are analysed. The vortex pair obtained after the sudden enlargement stage coinsides with conclusion of Finaish, F. and Ghaddar, N.K. ,therefore Pan’s and Acrivos’s nested vortex group theory is further verified.