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系統識別號 U0026-2108201713243800
論文名稱(中文) 側向雙垂直噴注於超音速空氣流場之交互作用探討
論文名稱(英文) Interactions of Lateral Injected Doublet Liquid Jets in Supersonic Airflow
校院名稱 成功大學
系所名稱(中) 航空太空工程學系
系所名稱(英) Department of Aeronautics & Astronautics
學年度 105
學期 2
出版年 106
研究生(中文) 何仲軒
研究生(英文) Zhong-Xuan He
學號 p46044370
學位類別 碩士
語文別 中文
論文頁數 60頁
口試委員 口試委員-劉正芳
口試委員-趙怡欽
指導教授-袁曉峰
中文關鍵字 超音速燃燒衝壓引擎  雙垂直噴注  震波交互作用 
英文關鍵字 scramjet  doublet liquid jets  shock/shock interactions 
學科別分類
中文摘要 由於氣流進入超燃衝壓引擎燃燒室時速度極高、滯留時間極短,增進其與燃料間的混合是目前的噴注器設計重點。而為了增加引擎推力,一般採用多噴孔陣列噴注器以增加燃料流量,了解燃料液柱間的交互作用,為設計高混合效益噴注器之必要條件。本研究應用並排雙噴注孔,噴注方向與自由流方向垂直,將JP-4燃料注入2馬赫空氣流場,並改變噴注孔間的距離,以觀察燃料液柱間交互作用的模式,以及霧化混合的機制。實驗結果顯示,液柱引發之弓形震波的交互作用會造成氣流減速,對燃料與氣流的霧化混合效果有負面影響,且兩弓形震波之交互作用愈強,流場穩定性愈高;故雙噴注間距愈小,霧化混合效果愈差、液滴消散距離愈長。雙噴注間距愈大,其發展則與單噴注相似度愈高。因穿透高度與噴注本身之動量通量較具關聯性,故震波交互作用對穿透高度無顯著影響。
英文摘要 The scramjet engine performance is highly related to the mixing efficiency between liquid fuel and airflow because of the short residence time of the supersonic airflow. Since multi-point fuel injection is required in scramjet engine, better understand the effect of interactions between jets on fuel-air mixing is important to the scramjet fuel injection design. This thesis research utilizes a reflected shock tunnel to produce Mach 2 airflow. The experiments are conducted with singlet and doublet injection orifices of 0.5mm in diameter laterally aligned to the airflow. The spacing between the doublet orifices are 5mm, 7.5mm, and 10mm. JP-4 fuel is used as the working fluid and injected into the supersonic airflow. Schlieren photography and Mie scattering are adopted to observe the spray structure during the experiments. The experimental observations show that the dissipation distance of spray increase with decreasing spacing between adjacent jets, that is, worse mixing between the fuel spray and air. Further analyses indicate that the shock/shock interactions between the bow shocks induced by adjacent liquid jets enhance the stability of the air flow field and less surface disturbance and more stable spray is observed. As the spacing between the adjacent jets increases to 10mm, the mixing behavior of the doublet jets is similar to the singlet one. It is understood that the penetration heights of jets are crucially sensitive to the momentum flux ratio of jet to airflow, and the experiment results do not show significant variation of penetration heights in cases of different spacing between jets. Concluded from the present observations, the spacing between span-wise align jets is recommended to be more than 20 times of the orifice diameter in engineering applications to achieve adequate mixing of fuel and Mach 2 cross flow of air.
論文目次 目錄
摘要 I
誌謝 VI
目錄 VII
表目錄 IX
圖目錄 X
符號 XIII
第一章 緒論 1
1-1 前言 1
1-2 文獻回顧 3
1-3 研究動機與目的 8
第二章 實驗與研究方法 10
2-1 反射式震波風洞 10
2-1-1 震波風洞驅動過程 10
2-1-2 震波管理論 11
2-2 氣體供給系統 12
2-3 燃料噴注系統 13
2-4 訊號同步系統 13
2-5 影像拍攝系統 14
2-6 視流紋影法 14
2-7 米氏散射光量測法 15
2-8 實驗模型與參數 16
2-9 穿透高度與消散距離之量測方法 16
第三章 實驗結果與討論 18
3-1 弓形震波交互作用點之觀察 18
3-1-1 實驗設備測試 18
3-1-2 弓形震波輪廓與交會位置推測 20
3-1-3 震波交互作用特性 21
3-2 視流紋影法觀察結果 22
3-2-1噴注結構觀察 22
3-2-2消散長度觀察 23
3-2-3穿透高度觀察 24
3-3 米氏散射光量測法觀察結果 25
3-3-1平均影像觀察 25
3-3-2 瞬時影像觀察 26
第四章 結論 28
第五章 未來工作 30
參考文獻 31
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