固體火箭流體轉向之數值研究

淡江大學機構典藏 > 工學院 > 航空太空工程學系暨研究所 > 會議論文 > Item 987654321/96323

jsp.display-item.identifier=請使用永久網址來引用或連結此文件: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/96323

题名:	固體火箭流體轉向之數值研究
其它题名:	A Numerical Study of Flow Turning Losses in a Simulated Solid Rocket Motor
作者:	陳增源;李世鳴
贡献者:	淡江大學航空太空工程學系
关键词:	火箭;燃燒不穩定;流體轉向;壓力振盪;頻率;流場速度;Rocket;Combustion Instability;Flow Turning;Pressure Oscillation;Frequency;Flow Velocity
日期:	1991-12
上传时间:	2014-03-07 09:07:53 (UTC+8)
摘要:	這篇文章是探討有關固體火箭流體轉向對於燃燒不穩定之影響,這個研究結果顯示聲波場之存在,造成流場之振盪,而其振盪頻率和聲場之頻率相同。此流場週期振盪之現象發生於所有之測試情況;同時,其振盪之現象和聲波之振幅、頻率,以及聲場之位置有關。這些結果顯示在固體火箭中流體轉向之趨動或抑制特性和聲波場之特性有關。 This paper describes results of a numerical study of the effect of the flow turning process upon axial instabilities in a simulated solid rocket motor. Specifically, the flow velocity behavior under different pressure excitations were presented in this paper. These studies revealed that the presence of a pressure oscillation produced oscillatory axial and vertical velocities having the same frequency as the pressure wave for all test frequencies. In addition, this oscillatory flow behavior was observed when the flow turning region was located at a pressure node, a pressure antinode, and in between. The amplitudes and phases of these velocity oscillations depended on the magnitudes and frequencies of the pressure oscillations, and on the temperature of the vertical injected flow. These results suggest that the driving/damping characteristics of the flow turning process would depend on the acoustic characteristics inside the rocket motors.
關聯:	中國航空太空學會民國八十年學術研討會論文集=Proceedings of the 1991 Aeronautics and Astronautics Conference of the A=eronautical and Astronautical Society of the R.O.C.，頁781-790
显示于类别:	[航空太空工程學系暨研究所] 會議論文

文件中的档案:

档案	描述	大小	格式	浏览次数
固體火箭流體轉向之數值研究_中文摘要.docx	摘要	15Kb	Microsoft Word	150	检视/开启
固體火箭流體轉向之數值研究_西文摘要.docx	摘要	15Kb	Microsoft Word	103	检视/开启

在機構典藏中所有的数据项都受到原著作权保护.

TAIR相关文章

数据加载中.....