本文旨在以實驗技術研究實際渦輪噴射引擎葉片內冷卻通道在高旋轉數下之熱傳特性。由文獻回顧得知現有之內置方形肋條矩形(AR=2)冷卻通道之熱傳實驗數據皆侷限於低旋轉數(Ro<0.5) 而高旋轉數下 (Ro≧0.5)相關實驗結果非常缺乏。實驗方法為熱電偶量測技術，對矩形截面(AR=2、Dh=30)內置方形肋條(H/Dh=0.1、P/H =10、α=45°)徑向外流之單一冷卻通道進行迎風面與背風面中心表面溫度量測。主要研究參數計有：旋轉數Ro (0-2.0)、雷諾數Re(5000-15000)、密度差比值DR(0.07-0.25)及冷卻通道與轉動平面夾角 β(90°、135°)。實驗數據主要以旋轉數Ro為區隔對局部紐塞數Nu與管道平均紐塞數 加以討論。低旋轉數(Ro<0.5)下實驗所得數據與先前研究結果ㄧ致。高旋轉數(Ro≧0.5)實驗數據結果分別對旋轉數Ro、密度差比值DR及冷卻通道與轉動平面夾角 β提出臨界旋轉數Ro以區隔不同熱傳增益特性。並進一步探討浮力參數Bu對熱傳增益的影響得出臨界浮力參數Bu=0.1。

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