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研究生： 黃祖洋
Huang, Tsu-Yang
論文名稱： 雙推進劑液體火箭燃燒室之共軛熱傳數值模擬分析
Numerical Analyses of the Conjugate Heat Transfer in a Bipropellant Liquid Rocket Combustor
指導教授： 江滄柳
Jiang, Tsung-Leo
學位類別： 碩士
Master
系所名稱： 工學院 - 航空太空工程學系
Department of Aeronautics & Astronautics
論文出版年： 2010
畢業學年度： 98
語文別： 中文
論文頁數： 76
中文關鍵詞： 共軛熱傳
外文關鍵詞： conjugate heat transfer
相關次數： 點閱：148  下載：5 
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    • 雙推進劑液態火箭燃燒室產生之高溫氣體，會燒蝕燃燒室壁，造成整體結構之破壞。因此，會將部分燃料噴向燃燒室壁面，以形成薄膜來冷卻壁溫。本研究建立一雙推進劑液態火箭燃燒模擬分析模式，並以此模式針對液態火箭燃燒室壁及流場之共軛熱傳進行模擬分析。模擬結果發現，燃料液膜能隔絕燃燒室產生之高溫氣體，有效地降低燃燒壁面之溫度。模擬結果顯示，在考慮重力參數下，冷卻液膜延伸效果較好，但因為燃燒反應會受到重力牽引而往噴嘴方向移動，導致此處之流場溫度也較高；而噴注排列方向為NTO/MMH，即NTO噴注之方向為由內往外，MMH之噴注方向為由外往內噴時，由於燃燒火焰較集中於燃燒室中心，使得燃燒室內之冷卻液膜蒸發速度較緩，但於噴嘴處因為燃燒反應較為劇烈，使得此處之壁溫較高；而縮短冷卻噴注與壁面的距離，可以提早對燃燒室壁面的保護，但較無法阻擋燃燒室頂部流場之高溫。

    　The high-temperature gas of a bipropellant liquid rocket combustor may burn and erode the chamber wall, damaging the whole structure. Therefore, in a general practice, part of the fuel of a bipropellant liquid rocket is injected toward the chamber wall to form a film, cooling down the chamber wall. In the present study, a bipropellant liquid rocket combustion simulation model is developed for the conjugate heat transfer analysis the combustion flow and the chamber wall. The simulation results indicate that considering the effect of gravity leads to better extension of the cooling film and higher temperature on nozzle. For the investigation of the arrangement of impinging jets, the case of NTO(inner)/MMH(outer) results in the center flame structure and slower evaporating velocity of the cooling film than that of the case using MMH(inner)/NTO(outer). The NTO/MMH arrangement also leads to more drastic combustion and higher wall temperature. Reducing the distance between cooling jets and the wall of the combustion chamber leads to earlier protection on the wall of the combustion chamber, while it does not alleviate the high temperature flow near impinging jets.

    目錄 中文摘要........................................I Abstract ........................................II 致謝........................................III 目錄...............................................IV 表目錄.........................................VI 圖目錄..........................................VII 符號說明.................................................XI 第一章 導論..............................................1 §1-1 前言.............................................1 §1-2 文獻回顧........................................ 2 §1-3 研究動機........................................ 6 第二章 數學及物理模式..................................... 7 §2-1基本假設.........................................7 §2-2紊流模式...........................................8 §2-3邊牆函數...........................................8 §2-4氣項流場統馭方程式....................................8 §2-5噴霧油滴相關方程式....................................10 §2-6雙推進劑衝擊霧化模式............................13 §2-7燃燒室壁共軛熱傳模式.............................14 §2-8冷卻燃料噴注模式...................................16 §2-9油滴與氣相流場的關係.......................17 §2-10化學反應模式...............................18 §2-11動態化學反應........................................18 §2-12平衡化學反應...................................19 第三章 數值方法與格點系統.................................21 §3-1 簡介............................................. 21 §3-2 計算程序......................................... 21 §3-3 共軛熱傳計算程序................................. 23 §3-4 格點系統......................................... 24 第四章 結果與討論................................. 26 §4-1 重力對燃燒室壁面共軛熱傳之影響................... 27 §4-2噴注器之噴注方向對燃燒室壁面共軛熱傳之影響........ 30 §4-3冷卻噴注之距離對燃燒室壁面共軛熱傳之影響..........34 §4-4與實驗結果對照.................................... 39 第五章 結論與未來工作...............................40 參考文獻.......................................42 自述............................................76

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