摘要
针对固体火箭发动机尾焰高温(总温超过3500℃)、高污染(氧化铝颗粒和氯化氢气体等)的问题,基于水冷壁、水喷淋等水处理系统的有效性,提出了一种采用具有更多冷能的水的固态形态——冰,对地面热试车的固体火箭发动机尾焰进行冷却降温与污染物沉降的新型处理方法。对冰筒装置内发动机尾焰与冰壁面间的流动换热过程开展了理论分析,并针对XXΦ127及XX500两种规模的固体火箭发动机开展了试车实验。结果表明,发动机出口尾焰在冰筒装置内实现了大幅度降温,冰筒出口气体温度低于100℃,氯化氢气体去除率大于97%,速度低于50 m/s、场外噪音小于85 dB。试验结果成功验证了新型冰筒处理技术的可行性和有效性,能够快速实现固体火箭发动机尾焰降温、降速、降噪和降污染的“四降”目的。
Aiming at the problems of high temperature(total temperature over 3500℃)and high pollution(alumina particles and hydrogen chloride gas,etc.)in solid rocket motor exhaust plume,a new method for treating solid rocket motor exhaust plume with ice,which is a solid form of water with more cooling energy,was proposed in this paper,based on the effectiveness of water treatment systems such as water wall and water spray.The new method can be used for cooling and pollutant deposition of solid rocket motor exhaust plume in ground static firing test.In this paper,the flow heat transfer process between the exhaust plume and the ice wall in the ice tunnel was analyzed theoretically,and tests of XXΦ127 and XX500 solid rocket motors were carried out to verify the working performance of the ice tunnel.The results show that,the exhaust plume temperature in the ice tunnel drop dramatically,and the temperature at the exit of ice tunnel is below 100℃;After passing the ice tunnel,the removal rate of hydrogen chloride gas is above 97%,the flow speed is slower than 50 m/s,and the noise level outside the site is lower than 85 dB.This new ice tunnel processing technology is successfully verified to be feasible and effective,which can quickly achieve the“four decreases”of temperature,flow speed,noise level and pollution of solid rocket motor exhaust plume.
作者
马原
霍东兴
张燕飞
张平
刘童
厉彦忠
MA Yuan;HUO Dongxing;ZHANG Yanfei;ZHANG Ping;LIU Tong;LI Yanzhong(School of Energy and Power Engineering,Xi'an Jiaotong University,Xi'an 710049,China;Key Laboratory of National Defense Science&Technology on Combustion,Thermo-structure and Internal Flow of SRM,Xi'an Institute of Aerospace Power Technology,Xi'an 710025,China;Xi'an Sunward Aeromat Co.,Ltd.,Xi'an 710025,China;iHarbour Academy of Frontier Equipment,Xi'an Jiaotong University,Xi'an 710049,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2022年第2期294-299,共6页
Journal of Solid Rocket Technology
基金
国家自然科学基金资助项目(51906194)
中国博士后科学基金资助项目(2019M663701)。
关键词
固体火箭发动机
尾焰处理
冰筒装置
快速降温
试车实验
solid rocket motor
exhaust plume treatment
ice tunnel device
rapid cooling
ground static firing test
