| 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 |
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| 引用本文： | 朱子勇,李培昌,瞿 骞. 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[J]. 航天器环境工程, 2010, 27(2): 231-237. DOI: 10.3969/j.issn.1673-1379.2010.02.022 |
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| 作者姓名： | 朱子勇 李培昌 瞿 骞 |
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| 作者单位： | 1.北京航天试验技术研究所，北京 100074 |
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| 基金项目： | 某型号运载火箭发动机试验系统工艺研究课题 |
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| 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Visual C#.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。
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| 关 键 词： | 火箭发动机；引射试验；扩压器；数值计算 |
| 收稿时间： | 2009-10-02 |
Comparison between the numerical simulation and high altitude simulation test for the ejector of a rocket engine |
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| Zhu Ziyong,Li Peichang and Qu Qian. Comparison between the numerical simulation and high altitude simulation test for the ejector of a rocket engine[J]. Spacecraft Environment Engineering, 2010, 27(2): 231-237. DOI: 10.3969/j.issn.1673-1379.2010.02.022 |
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| Authors: | Zhu Ziyong Li Peichang Qu Qian |
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| Affiliation: | 1.Beijing Institute of Aerospace Testing Technology, Beijing 100074, China |
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| Abstract: | 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,o... |
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| Keywords: | rocket engine ejection test diffuser numerical calculation |
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