大型火箭发动机试验导流槽热防护设计  

Thermal Protection Design of Flame Diversion Trough for Large Rocket Engine Test

作　　者：张伟[1,2] 方维 王树光[1,2] 李培昌 ZHANG Wei;FANG Wei;WANG Shu-guang;LI Pei-chang(Beijing Institute of A erospace Testing Technology,Beijing 100074,China;Beijing Engineering Research Center of Aerospace Propulsion Testing Technology andEquipment. Beijing 100074,China)

机构地区：[1]北京航天试验技术研究所,北京100074 [2]北京市航天动力试验技术与装备工程技术研究中心,北京100074

出　　处：《传感器世界》2019年第2期7-12,共6页Sensor World

摘　　要：火箭发动机热试车时喷射出的高温高速气流具有很大的冲击力和腐蚀力。导流槽的作用就是将燃气迅速地导向远离试车台的地方,防止火焰、烟尘及碎片反射回来冲击试验台,毁坏发动机和设备。随着我国大推力运载火箭研制立项,导流槽烧蚀的问题日益严峻。本文提出了一种新型导流槽热防护技术方案:通过数值分析和工程计算分析导流槽力、热环境;基于膜冷却原理,采用分区喷流水冷却的方法,根据热流密度不同在各区域采取不同的供水方式。此方案在保证导流槽冷却系统可靠性的同时,降低了试验台高度、节约了水资源。The high-temperature and high-speed airflow emitted during the high-thrust rocket engine test have great impact force and corrosion force. The flame diversion trough plays the role to guide the gas away fom the test bed to prevent the flame, smoke and debris from reflecting back and damaging the test bench, the rocket engine and equipment. With the development of high-thrust launch vehicle in China, the problem of ablation of flame diversion trough is becoming more and more serious. In this paper, a new type of thermal protection technical scheme for the flame diversion trough is proposed. The force and thermal environment of flame diversion trough are analyzed by numerical analysis and engineering calculation. Based on the principle of film cooling, by using the method of zonal waterjet, different water supply modes are adopted in different regions according to difterent heat flux density. This scheme not only ensures the reliability of the cooling system of the flame diversion trough, but also reduces the height of the test bed and saves water resources.

关 键 词：火箭发动机试验 导流槽 热防护 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]