铝冰发动机两相内弹道计算  

Calculation of two-phase internal ballistics in ALICE SRM

作　　者：刘平安 王良 LIU Ping′an;WANG Liang(College of Aerospace and Civil Engineering,Harbin Engineering University,Harbin 150001,China;Hu’nan Aviation Power Machinery Research Institute,Aero Engine(Group)Corporation of China,Zhuzhou 412000,China)

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,黑龙江哈尔滨150001 [2]中国航发湖南动力机械研究所,湖南株洲412000

出　　处：《哈尔滨工程大学学报》2018年第8期1321-1327,共7页Journal of Harbin Engineering University

基　　金：中央高校基本科研基金资助项目(HEUCFG201815)

摘　　要：为了在铝冰发动机内弹道计算中考虑两相不平衡效应的影响,提高压强估算的精度,本文应用两相等温流模型、颗粒定温模型对喷管两相流控制方程进行简化和推导,得到发动机稳态工作时燃烧室零维平衡压强的两相流修正计算式。使用铝含量为50%的铝冰发动机实验结果对压强修正公式进行验证,两相等温流模型修正的压强公式估算结果误差约为13.08%,颗粒定温模型修正的压强公式估算误差约为6.57%,可用于指导铝冰发动机实验开展。To consider the two-phase non-equilibrium effect in the calculation of the internal ballistics of an aluminum-ice(ALICE)solid rocket motor(SRM)and improve the pressure intensity estimation accuracy,a two-phase isothermal model(ITM)and fixed particle temperature model(FPTM)were applied to simplify and deduce the two-phase flow control equation of the effuser to obtain a two-phase flow revision calculation formula on the zero-dimensional pressure intensity of the combustor when the engine operates steadily.The experimental result of an ALICE SRM with 50%aluminum content was used to verify the revised pressure intensity formula.The results show estimation errors of about 13.08%and 6.57%for the pressure intensity formula revised by the two-phase ITM and FPTM,respectively.The results can help guide other ALICE SRMs experiments.

关 键 词：铝冰发动机 内弹道 两相流 两相等温流模型 颗粒定温模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]