某型号火箭发动机高空模拟试验中扩压器的数值计算与试验比较  

Comparison between the numerical simulation and high altitude simulation test for the ejector of a rocket engine

作　　者：朱子勇[1] 李培昌[1] 瞿骞 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《航天器环境工程》2010年第2期231-237,134,共7页Spacecraft Environment Engineering

基　　金：某型号运载火箭发动机试验系统工艺研究课题

摘　　要：文章利用FLUENT软件对某型号液氢/液氧火箭发动机在高空模拟引射试验中扩压器进行数值计算,并与试验测量数据进行比较。用VisualC#.NET软件编制了二次喉道扩压器引射过程计算程序,将该程序的计算结果与FLUENT软件的数值计算结果进行了比较。利用FLUENT软件对二次喉道扩压器在不同入口长度、不同收缩比和长径比情况下的流场情况进行了计算,分析了对发动机启动的影响;并把数值计算结果同吹风试验的数据进行了比较,结果表明数值计算具有较高的置信度。The numerical simulation of the high altitude simulation test for a liquid hydrogen/liquid oxygen rocket engine was carried out by using FLUENT software,and the results were compared with the measurement data of the test.Visual C#.NET software and FLUENT software were used to calculate the ejection parameters of the secondary throat diffuser,and their numerical calculation results are compared.The flow field of the secondary throat diffuser was obtained by using FLUENT software under various aspect ratios,or contraction ratios or entrance lengths(Xst),and the influence on the engine startup was analyzed.The results show that the numerical simulation method is reliable.

关 键 词：火箭发动机 引射试验 扩压器 数值计算 

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] TB115[理学—数学]