固体火箭发动机喷管分离流场数值模拟及试验研究  

Analysis of numerical simulation and test of the separated flow field in solid rocket motor nozzle

作　　者：李耿[1] 侯晓[1] 陈慧[1] 赵昆[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2013年第3期324-328,共5页Journal of Solid Rocket Technology

摘　　要：针对某试验发动机大扩张比喷管,开展了分离流场数值模拟及试验研究。通过计算,获得了喷管壁面的压强分布、分离点位置,用于指导试验方案的设计;通过试验测试,验证了计算模型的准确性,揭示了分离点前后燃气流动特性的不同;对分离点前后监测点压强进行了频谱分析。结果表明,分离后喷管内流动变的更紊乱,在较低的频带内,也存在较强的湍流脉动效应。该研究为大扩张比喷管结构设计、地面试验及试车分析提供了重要参考。Numerical simulation and test of the separated flow field in a solid rocket motor nozzle with large expansion ratio were carried out. In order to guide the test, pressure distribution and the position of separation point of the flow field on nozzle wall were obtained by numerical simulation ; by the test, the accuracy of the computation model was validated, then the different gas flow characteristics before and after the separation point were revealed. Results show that internal flow field in nozzle becomes more dis- organized when the separation occurs and turbulent fluctuation phenomenon also exists in lower frequency band by spectrum analysis of the inspected points pressure before and after the separation point. This research could provide important reference for structure design, ground test and test analysis of nozzle with large expansion ratio.

关 键 词：固体火箭发动机 喷管 分离流场 频谱分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]