固体发动机水下点火尾流场计算  

Calculation of Wake Field for Underwater Ignition of Solid Rocket Motors

作　　者：周君[1] 江晓瑞 李卓[1] 鲁荣 ZHOU Jun;JIANG Xiao-rui;LI Zhuo;LU Rong(College of Science,Inner Mongolia University of Technology,Hohhot Inner Mongolia 010051,China;School of Civil Engineering,Hebei University of Engineering,Handan Hebei 056038,China;Inner Mongolia Aerospace Hongxia Chemical Co.,Ltd.,Hohhot Inner Mongolia 010070,China)

机构地区：[1]内蒙古工业大学理学院,内蒙古呼和浩特010051 [2]河北工程大学土木工程学院,河北邯郸056038 [3]内蒙古航天红峡化工有限公司,内蒙古呼和浩特010070

出　　处：《计算机仿真》2024年第5期63-70,共8页Computer Simulation

基　　金：国家自科学基金(11962021)。

摘　　要：为研究固体发动机水下点火初期喷管内燃气泡的流动和发展过程及流场结构,利用CFD方法通过fluent分析软件对固体火箭发动机水下点火过程气液两相流场进行数值模拟计算,得到了发动机尾流场燃气马赫数、压力、温度等瞬态阶段演变情况。结果表明,发动机水下点火时,燃气与水之间产生强烈地相互作用,射流通道沿轴向存在周期性胀缩,一个周期内相继出现膨胀—液体回压—回流—颈缩—继续膨胀现象,随着流场发展涨缩强度逐渐减弱,颈缩位置向下游移动;燃气射流初期,轴向压力最高点在燃气泡头部位置;点火初始时刻喷管出口出现压力峰值;全计算域内温度在一定范围内振荡,沿轴向远离出口区域有剧烈的传热和明显的气液混合。In order to study the flow and development process and flow field structure of internal combustion bubbles in the nozzle at the initial stage of underwater ignition of solid rocket motor,the gas-liquid two-phase flow field in the underwater ignition process of solid rocket motor was numerically simulated by CFD method and Fluent analysis software,and the transient evolution of gas Mach number,pressure and temperature in the wake flow field of solid rocket motor were obtained.The results show that there is a strong interaction between gas and water during the underwater ignition of the engine.The jet channel expands and contracts periodically along the axial direction;In one cycle,the phenomena of inflation,the liquid back pressure,backflow,necking and reswell of the liquid appear one after another;With the development of the flow field,the strength of expansion and contraction gradually weakened,and the necking position moves downstream;At the initial stage of the gas jet,the axial pressure reaches its highest point at the head of the gas bubble.The pressure peak appears at the nozzle outlet at the initial moment of ignition;The temperature oscillates within a certain range in the whole calculation domain,along the axial direction away from the outlet area,and there is intense heat transfer and obvious gas-liquid mixing.

关 键 词：固体火箭发动机 水下燃气射流 尾流场 燃汽泡 数值仿真 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]