再燃室结构及煤油喷注角度对固体火箭引射式发动机性能影响  

Effects of Reburning Chamber Structure and Kerosene Injection Angle on the Performance of Solid Rocket Ejecting Engine

作　　者：蔡平 郭宇 徐义华[1] 孙海俊[1] 冯喜平[2] CAI Ping;GUO Yu;XU Yi-hua;SUN Hai-jun;FENG Xi-ping(Jiangxi Key Laboratory of Micro Aeroengine,School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China;Science and Technology on Combustion,Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]南昌航空大学飞行器工程学院江西省微小航空发动机重点实验室,南昌330063 [2]西北工业大学燃烧、热结构与内流场重点实验室,西安710072

出　　处：《南昌航空大学学报（自然科学版）》2022年第2期9-17,共9页Journal of Nanchang Hangkong University(Natural Sciences)

基　　金：国家自然科学基金(51666012,12102161);航空科学基金(20200001056001)。

摘　　要：为研究固体火箭引射式发动机在飞行状态下再燃室结构对发动机性能的影响,在发动机飞行马赫为0.6的工作状态下,煤油以直径为0.01 mm液滴形式喷注,速度设为80 m/s,注入质量流量为0.2 kg/s。煤油与空气采用单步反应,分别对内置扩张和内置收缩两种结构进行了燃烧流动数值计算,对比了其引射效率、推力、推力增益和燃烧效率,得到扩张型结构发动机引射性能更优,但收缩型结构发动机燃烧效率、推力增益远大于扩张型。在内置收缩型结构基础上,研究了不同煤油喷注方向与燃烧室轴向的夹角角度(90°~180°)对发动机性能的影响。结果表明:煤油喷注角小于130°时难以实现燃烧;在燃烧的工况中,发动机性能参数基本一致,随着喷射角度增大,推力及推力增益略微增大。In order to investigate the effect of reburning chamber structure on the performance of solid rocket ejector engine in flight,kerosene was injected in the form of droplets with a diameter of 0.01 mm at a speed of 80 m/s and an injection mass flow rate of0.2 kg/s under the operative condition of engine flight Mach 0.6.Kerosene and air adopt one-step reaction,and the combustion flow numerical calculations of the built-in expansion and built-in contraction structures are carried out,respectively.The injection efficiency,thrust,thrust gain and combustion efficiency are compared.It is obtained that the injection performance of the expansion structure engine is better,but the combustion efficiency and thrust gain of the contraction structure engine are much greater than that of the expansion structure engine.Based on the built-in contraction structure,the effects of different angles between kerosene injection direction and combustion chamber axis(90°to 180°)on engine performance are studied.The results show that it is difficult to achieve combustion when kerosene injection angle is less than 130°,under the cases of being able to burn,the engine performance parameters are basically the same,and the thrust and thrust gain increase slightly with the increase of injection angle.

关 键 词：固体火箭 引射式发动机 引射效率 推力增益 燃烧效率 

分 类 号：U458[建筑科学—桥梁与隧道工程]