本研究建立二維模型，模擬甲烷-空氣預混氣體在輻射熱燃燒器中燃燒現象，幾何模型為燃燒室內放入排孔平板，簡化成火焰在單一流道中傳播，探討各項參數對火焰穩定存在於排孔平板內位置以及輻射熱燃燒器工作效率影響。模擬採用FLUENT商業套裝軟體進行計算，輻射熱傳則使用UDF方程式掛載，探討表面放射率時使用FLUENT商業套裝軟體內建DO模型，化學反應式採用甲烷單步驟反應式，整個計算域採用均勻正交網格計算。
模擬結果顯示固體熱傳導係數增加，燃氣反應後有較高之絕熱火焰速度和溫度，使火焰往上游移動，當固體熱傳導係數大於20W/m-K，超焓燃燒效果對於增加絕熱火焰溫度效果有限 ; 隨著燃氣入口流速增加，燃氣中心需要較長距離使甲烷消耗率達到100%，並且火焰往下游方向移動，增強對下游加熱量，減少上游對環境輻射熱傳散失量，同時降低燃燒器輻射加熱效率 ; 燃氣入口流速極限時有該當量比下最高絕熱火焰溫度，固體熱傳導係數越大，燃氣入口流速操作範圍越廣 ; 當量比增加絕熱火焰速度和溫度同時提高，燃氣中心甲烷消耗率到達100%所需距離減少，並且火焰往上游移動，提高對環境輻射熱傳散失 ; 排孔平板表面熱傳導係數越好，下游輻射加熱效率越高，整體上來說在低當量比、低入口流速、低平板熱傳導係數、高表面放射率、燃燒器有較佳輻射加熱效率。

In this study, established a two dimensional CFD model with orthogonal mesh to simulate the combustion phenomenon of methane-air mixture gas in the radiation combustor. The combustion chamber of this model which consists of a cellular array was simplified to modeling flame propagation inside a channel, and therefore parameters effects of flame ignited location and efficiency of this combustor has been discussed. Using ANSYS FLUENT and user-defined function (UDF) to simulate flame propagating and heat radiation, and using DO model of ANSYS FLUENT to simulate surfaces emissivity. In this study, considering methane and air stoichiometric combustion modeled by a simple one-step irreversible reaction
The results reveal that increase of thermal conductivity results in the increase of adiabatic flame propagating speed and temperature, and thus flame propagats to upstream side. However, when thermal conductivity greater than 20 W/m-K, it was limited for the effects of thermal conductivity to increasing adiabatic flame temperature. If the inlet fuel velocity increase, it needs longer distance to achieve 100% fuel consumption. Flame propagating to the downstream side heats the methane-air mixture gas closed to the downstream side, increases downstream radiation heat flux , reduces radiation heat loss flux to the environment of upstream side and results in worse combustion efficiency. With certain equivalence ratio, at the limit fuel inlet velocity, it causes the maximum adiabatic temperature, but with large solid thermal conductivity it can employ wide range of fuel inlet velocity. With case of large equivalence ratio, adiabatic flame speed and temperature, it needs a shorter distance to achieve 100% fuel consumption, also leads to flame propagate to the upstream side and increases the radiation heat loss. Downstream radiation heat efficiency would increase with increasing perforated-plate internal emissivity. Overall, using a combustor which consists of lower equivalence ratio, lower fuel inlet velocity, lower perforated-plate conductivity, and higher perforated-plate internal emissivity,will gain better radiation heat efficiency.

論文審定書 i
誌謝 ii
摘要 iii
Abstract iv
目錄 vi
圖目錄 viii
表目錄 xiii
符號說明 xiv
第一章 序論 1
1.1前言 1
1.2 輻射熱燃燒器工作原理 3
1.3文獻回顧 7
1.3.1火焰於小管中燃燒 10
1.4研究目的 14
第二章 數值模型 17
2.1數學模型 17
2.2統御方程式 18
2.3輻射模型 23
2.3.1非透明壁面邊界條件處理方式 24
2.4數值方法 26
2.5網格測試和收斂標準 27
第三章 結果與討論 29
3.1.輻射模型比較 30
3.2熱傳導系數對火焰在燃燒器之影響 32
3.3燃氣入口流速對火焰在燃燒器之影響 39
3.3.1平板熱傳導係數2W/m-K 模擬結果 39
3.3.2平板熱傳導係數 20W/-K 46
3.4當量比對火焰在燃燒器之影響 53
3.4.1平板熱傳導係數2W/m-K 模擬結果 53
3.4.2平板熱傳導係數20W/m-K 59
3.5表面放射率對火焰在燃燒器之影響 66
3.5.1平板熱傳導係數2W/m-K 模擬結果 66
3.5.2平板熱傳導係數20W/m-K 模擬結果 72
3.6燃氣入口流速極限 79
第四章 結論 82
第五章 未來展望 84
參考文獻 85

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