臺灣博碩士論文加值系統

本研究透過改變燃料供氣歧管角度，探討無閥式脈衝爆震引擎於操
作時爆震波回傳對供氣阻絕及時序之影響。實驗中乙烯/氧氣於化學當量
下點火，除透過高速顯影觀察反應波引燃後於流道中傳遞動態外，也建
構一雷射陰影(Laser Shadowgraph)系統解析過程中爆震波於流道內傳遞
情形。以及透過動態壓力感測器進行壓力波之量化分析。
由實驗結果可知在30 度入口角時下游反應波傳遞模態為一低速爆
震焰，而在60 度與90 度時則為典型爆震焰模態。由氣相層析儀分析可
得於較小角度時混合狀態較為貧油，30 度角時當量比約為0.6。而在上
游進氣端之雷射陰影觀察可知在較小入口角度時，反應波前方有明顯震
波結構於氧氣歧管中傳遞。而在最大入口角90 度時，震波傳遞至交會
處時則強度大幅降低，即於氧氣歧管中已無發現明顯震波傳遞。實驗也
透過於氧氣進氣歧管中安裝一動態壓力感測器量測管內壓力變化。估算
30 度至90 度之供氣阻斷時間分別約為306 us、219 us 與299 us，提高
供氣壓力後則阻斷時間則分別下降到約281 us、266 us 與270 us。而比
較單發操作以及連續操作下之上游進氣端之反應波與震波之顯影，由結
果中可看出於70 Hz 連續操作下反應波往上游傳遞速度較慢。另外實驗
也於岐管上游處設計一空腔幾何，由壓力記錄可得在原設計時岐管中壓
力峰值約為0.45 MPa，而在具空腔設計條件下其峰值壓力可下降至約
0.12 MPa。

Effects of inlet channel angle on the gas feeding dynamics in pulsed
detonation cycle in a micro pulsed detonation engine were investigated in the
study. Stoichiometric of ethylene/oxygen were used and high-speed
cinematography were applied to observe the flame propagation in mixing
section and inlet manifolds upstream of the ignition spot. Laser shadowgraph
was also utilized to analyze the shock propagations in the manifolds.
It can be found that both of 60° and 90° were typical detonation wave, and a
low-speed detonation mode in 30° case. By using a gas chromatography(GC)
to measure the mixing status in different angle cases. The equivalent ratio
decreased with inlet angle increase. It can be seen that with the smaller inlet
angle, there were an intense shock wave propagating back into the inlet
manifolds. With 90° inlet angle, the shock wave could only propagate until
the cross section, and the expansion resulted in the dissipation of the shock. A
dynamic pressure sensor was installed on the oxygen feeding channel to
quantify the pressure evolutions in the inlet manifold. The results showed that
the shut-off duration for the 30° to 90° inlet was about 306, 219 and 299 us
respectively. And reduce to 281, 266 and 270 us by increasing supply
pressure. Comparison of single shot and continuous operating of 70 Hz, there
were the slowest reaction wave velocity in the inlet section. A cavity design
has been apply in the manifold. It can be seen that the shock wave in oxygen
manifold were not obvious in cavity case. And the value of peak pressure
were 0.45 MPa in original design but there were only 0.12 MPa in cavity case.

摘要 i
誌謝 xii
目錄 xiii
表目錄 xv
圖目錄 xvi
第一章 緒論 1
1-1 前言 1
1-2 研究目的 2
1-3 文獻回顧 3
1-4 本文架構 8
第二章 實驗設備與方法 10
2-1 微爆震腔設計 10
2-2 微爆震腔測試平台 14
2-3 雷射陰影顯影系統 17
2-4 點火系統 20
2-5 爆震波流場顯影 22
高速連續顯影 22
延遲單張顯影 24
2-6 動態壓力量測 27
2-7 氣相層析儀量測 28
2-8 測試流程 31
第三章 燃料進氣角度對爆震波生成與傳遞之影響 34
3-1 爆震波生成與傳遞 34
反應波動態 34
爆震波動態 43
動態壓力量測 47
燃氣組成 48
3-2 反應波與震波對供氣之影響 52
反應波動態 52
爆震波動態 57
供氣阻斷特性分析 64
3-3 小結 69
第四章 脈衝頻率對爆震波生成與傳遞之影響 71
4-1 各燃料進氣角度下之脈衝反應波傳遞模態 71
30度入口角 71
60度入口角 85
90度入口角 98
4-2 各燃料進氣角度下之脈衝反應波回傳動態 111
4-3 各頻率下之脈衝反應波回傳動態 114
4-4 小結 123
第五章 進氣道空腔對爆震波生成與傳遞之影響 124
5-1 反應波傳遞模態 124
5-2 反應波回傳動態 127
5-3 與無空腔進氣道之比較 127
5-4 小結 132
第六章 結論與未來展望 134
6-1 結論 134
6-2 未來展望 136
參考文獻 137
附錄A 不銹鋼流道板設計工程圖 144
附錄B 不銹鋼PDE治具設計工程圖 146

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