运动激波引射高温燃气的数值研究  

Numerical Study on High Temperature Burned Gas Induced by a Moving Shock

作　　者：徐胜利[1] 张红杰[1] 孙英英[1] 韩肇元[1] 

机构地区：[1]中国科学技术大学,合肥230026

出　　处：《空气动力学学报》1999年第4期398-404,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：本文从一维非定常守恒方程出发，用Ｒｉｃｈｔｍ ｙｅｒ－Ｌａｘ－Ｗｅｎｄｒｏｆｆ格式研究了夹膜方式、夹膜位置、破膜压力和破膜延时对激波引射高温燃气参数的影响。结果表明：在激波风洞组合设备中，用引燃激波管模拟亚燃室开展双燃式煤油超燃研究的方案是可行的，引燃激波管布置的建议方案是：单膜片、膜片位于管子右端出口处、破膜压力尽可能低、破膜延时尽可能小。One dimensional unsteady equations and Richtmyer Lax Wendroff scheme were used to study the hot and fuel rich burned gases influenced by the diaphragm arrangement, critical pressure and time delay for the diaphragm bursting. The results indicate that the single diaphragm which is at the exit of a combustion shock tube, lower critical pressure and short time delay for diaphragm bursting are suggested in studying kerosene supersonic combustion in a combined facility which is composed of a shock tunnel and a combustion shock tube. The combustion shock tube acts as a subsonic combustion chamber.

关 键 词：激波管 超声速燃烧 数值模拟 航天器 发动机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.751