在以往的文獻當中對於葉片熱傳問題的研究，都使用平滑的熱氣流道，因此，邊界層沿著端壁發展至靜葉片前端，再進入葉片之間的通道受壓力分佈的影響形成複雜的三維流。然而實際上從燃燒室到第一級導向葉片之間的燃氣導管設計相當複雜，第一級導向葉片進口與燃氣導管出口處有可能因為材料的熱脹冷縮產生相對移位而使得葉片端壁有個進口台階，此台階大小可能隨氣輪機負載而改變，並且會影響到下游三維流場之發展。
因此本研究將採用穩態熱傳液晶熱像法量測葉片端壁膜冷卻有效性，在葉片端壁上將改變三種不同幾何形狀的膜冷卻孔，固定主流雷諾數，改變吹氣比M=0.5和2.0，並以平滑進口台階為基準，以前向進口台階和背向進口台階模擬燃氣導管之熱膨脹移位。
結果顯示前向進口台階發生會降低膜冷卻有效性；背向進口台階會增加膜冷卻有效性，但是，在靠近吸力面和靠近壓力面有完全相反的膜冷卻發展現象。提昇吹氣比對－4%台階發生時，有增加膜冷卻有效性的結果，但是，對於0%和4%台階發生時，反而造成膜冷卻有效性的降低。複合角條件對於膜冷卻的提昇有不錯的結果，尤其是前向複合角。

In the existing literature for such a problem, all researchers used smooth walls for hot gas passage. Thus, boundary layer developed along the endwalls before reaching the leading edge of the first stage guide vanes. After that, the flow of hot gas is affected by the pressure distribution in the passage between adjacent vanes and forms complex tree-dimensional flow field. In reality, however, the structure of transition nozzle connecting the combustor chamber and the first stage vanes could be very complicated. The matching of the exit of the transition nozzle and the annular endwalls of the vanes may have relative displacement due to thermal expansion of different materials, causing an entrance step for the hot gas entering the vane passages. The size of the entrance step, which may vary with the load of a gas turbine, will influence the three-dimensional flow downstream.
This research will adopt the way of steady state heat transfer experiment with liquid crystal thermography. At the same time, it will use three compound-angle film cooling holes and set Reynolds number. Then, the blow ratio is adjusted to M= 0.5 and 2.0. Placing the no entrance step as the standard, the experiment uses forward entrance step and backward entrance step to represent the displacement of a transition nozzle due to the thermal expansion.
The result shows that when the condition of forward-facing entrance step exists, it will reduce the film cooling effectiveness. On the opposite, when the condition of backward-facing entrance step exists, it will increase the film cooling effectiveness. However, there is totally different phenomenon of film cooling between suction side and pressure side of endwall. When the condition of backward-facing entrance step exists, increasing the blowing ratio will increase the film cooling effectiveness. Yet, when the condition of smooth entrance step and forward-facing entrance step exists, increasing the blowing ratio will reduce the film cooling effectiveness. The condition of compound angle can improve the increasing of film cooling effectiveness greatly, especially the forward-facing compound angle.

封面內頁
簽名頁
授權書 iii
中文摘要 v
英文摘要 vi
誌謝 viiii
目錄 ix
圖目錄 xii
表目錄 xviiii
符號說明 xviii

第一章 緒論 1
1.1 研究背景與動機 1
1.2 文獻回顧 3
1.2.1 葉片近端壁處之外流場 4
1.2.2 葉片近端壁處之熱傳與膜冷卻相關研究 8
1.2.3 複合角對端壁熱傳與膜冷卻之影響 11
1.3 研究目的 18
第二章 膜冷卻之研究方法與理論 28
2.1 膜冷卻作法與參數定義 28
2.2 膜冷卻有效性量測方法與理論 30
2.2.1 穩態液晶量測技術 30
2.2.2 暫態液晶量測技術 31
2.3 研究方法優缺點比較 33
第三章 實驗系統 34
3.1 風洞系統 34
3.2 膜冷卻流體供應系統 35
3.3 影像處理系統與照明取像設備 36
3.4 溫度量測系統 37
3.5 液晶校正系統 37
3.6 測試段設計 41
3.7 數據化約程序 43
第四章 結果與討論 63
4.1 前向複合角對端壁膜冷卻之影響 64
4.2 橫向複合角對端壁膜冷卻之影響 65
4.3 旋轉複合角對端壁膜冷卻之影響 66
4.4 吹氣比對端壁複合角之影響 67
4.5 台階對端壁複合角之影響 67
第五章 結論 129
參考文獻 130

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