淡江大學機構典藏:Item 987654321/46040
English  |  正體中文  |  简体中文  |  全文笔数/总笔数 : 62797/95867 (66%)
造访人次 : 3738062      在线人数 : 522
RC Version 7.0 © Powered By DSPACE, MIT. Enhanced by NTU Library & TKU Library IR team.
搜寻范围 查询小技巧:
  • 您可在西文检索词汇前后加上"双引号",以获取较精准的检索结果
  • 若欲以作者姓名搜寻,建议至进阶搜寻限定作者字段,可获得较完整数据
  • 进阶搜寻


    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/987654321/46040


    题名: Effects of Flow Turning Processes on Combustion Instabilities in a Simulated Rocket Combustor
    其它题名: 模擬火箭燃燒室中流體轉向對燃燒不穩定效應之研究
    作者: 陳增源;Chen, Tzeng-yuan
    贡献者: 淡江大學航空太空工程學系
    关键词: 固體火箭;燃燒不穩定;流體轉向;solid rockets;combustion instability;flow turning
    日期: 1995-09
    上传时间: 2010-03-26 20:49:37 (UTC+8)
    出版者: 中國航空太空學會
    摘要: 此研究是有關模擬固體火箭燃燒室中,“流體轉向”(flow turning)對燃燒不穩定之驅動/抑制特性之實驗探討。研究中以雷射測速儀(LDV)作週期速度振盪之量測,水冷之麥克風作壓力振盪之量測。所得到之振盪速度及壓力值利用聲能法(acoustic energy approach)決定在含有流體轉向之區域中,聲能因流體轉向而損失抑或增加。實驗結果顯示,流體轉向之效應造成燃燒室中聲能之損失,因此,有抑制固體火箭燃燒不穩定之效應。研究結果同時顯示,燃燒之效應加強流體轉向之聲能吸收,因此,更有抑制燃燒不穩定之效果。燃燒室中不均勻溫度之分佈,造成聲波之折射:同時,在壓力及速度振盪之研究中造成不同之驅動/抑制聲波之場特性。此不均勻之溫度分佈,在火箭燃燒不穩定中,亦可能是重要之驅動/抑制基理(mechanism)。
    This research is concerned with the experimental investigations of the driving or damping of axial instabilities in a simulated solid rocket combustor by the ”flow turning” process. These studies included extensive oscillatory velocity and acoustic pressure measurements performed by using a forward scatter laser Doppler velocimetry (LDV) and a water cooled microphone pressure probe, respectively. These data were used to determine the energy fluxes through the control volume containing the regions of ”flow turning” and, thus, determines the energy generation or absorption by flow turning process. The results obtained in this study suggest that the flow turning process may absorb acoustic energy and, thus, damp the acoustic field in solid propellant rocket motors. This study also shows that the combustion process enhances acoustic energy absorption by the flow turning process. In addition, the non-uniform temperature effect, which results in sound refraction and different driving and damping effects between pressure and velocity oscillation studies, may also represent an important mechanism of energy absorption and generation.
    關聯: 中國航空太空學會學刊 27(3),頁223-231
    显示于类别:[航空太空工程學系暨研究所] 期刊論文

    文件中的档案:

    档案 大小格式浏览次数
    Effects of Flow Turning Processes on Combustion Instabilities in a Simulated Rocket Combustor.html0KbHTML18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

    DSpace Software Copyright © 2002-2004  MIT &  Hewlett-Packard  /   Enhanced by   NTU Library & TKU Library IR teams. Copyright ©   - 回馈