突扩后缩型喷管前腔的流场计算

CALCULATION OF FLOW FIELD IN THE FRONT CAVITY OF NOZZLE WITH SUDDEN SHRINK-AFTER-SUDDEN ENLARGEMENT

本文是为解决有关发动机喷管的实际烧蚀问题而进行的喷管前腔流场计算分析的一部分。探讨了SIMPLE算法在复杂边界下运行问题,重点研究了突扩后缩型喷管前腔的流场结构。计算表明:本文所提供的双涡系统与Finaish等人的结论是一致的,进一步证实了F.Pan和A.Acrivos的嵌套涡族理论。

This paper is a part of calculation and analysis of flow field on front cavity of nozzle for solving the ablation problem of engine, nozzle and explores the operation problem of SIMPLE algorithm under complex boundary, especially on the study of flow field in the front cavity of the nozzle with sudden shrink-after-sudden enlargement. Calculated results show that the double vortex system provided by this paper is concord with Finaish's conclusion, and F. Pan and A. Acrivos's theroy of the vortex group is verified further.