摘要
射流角度和壁面曲率是空间液体火箭发动机液膜冷却设计的重要参数,通过实验研究了入射角和壁面曲率半径对射流撞壁液膜形态和液膜厚度的影响;实验中液膜厚度的测量采用探针法法测量。对射流撞壁的溅射现象进行的分析表明,射流由壁面附着状态转变为液滴飞溅状态的临界We数为214.1,射流撞壁后由附壁状态转变为溅射状态的临界入射角度为23.1°,根据液体火箭发动机冷却的需要可以选择合适的射流角度。
Impingement angle and wall curvature are important for liquid film cooling design of liquid rocket engine. The effect of impingement angle and wall curvature on film form and thickness was studied experimentally. The film thickness was calculated by contact needle method. Splash occurred with high Webber number during impingement. The critical Webber number for transformation from adherent to splash is 214.1, and the critical impingement angle is 23.1 ° , which means the impingement angle can be optimized for different liquid rocket engines.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2013年第2期17-21,共5页
Journal of National University of Defense Technology
基金
国家部委资助项目
关键词
液体火箭发动机
液膜冷却
入射角
实验研究
liquid rocket engine
liquid film cooling
impingement angle
experimental study
