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系統識別號 U0026-0901201909595600
論文名稱(中文) 旋轉梯型管內衝擊噴柱列熱傳實驗研究
論文名稱(英文) Experimental heat transfer of impinging jet row in rotating trapezoidal channel
校院名稱 成功大學
系所名稱(中) 系統及船舶機電工程學系
系所名稱(英) Department of Systems and Naval Mechatronic Engineering
學年度 107
學期 1
出版年 107
研究生(中文) 俞國靖
研究生(英文) Kuo-Ching Yu
電子信箱 P16064031@mail.ncku.edu.tw
學號 P16064031
學位類別 碩士
語文別 中文
論文頁數 90頁
口試委員 指導教授-張始偉
口試委員-吳鴻文
口試委員-吳佩學
中文關鍵字 旋轉通道  噴柱陣列  梯形通道  渦輪動葉冷卻 
英文關鍵字 Rotating Channel  Impinging Jet Row  Trapezoidal Channel  Gas Turbine Rotor Blade Cooling. 
學科別分類
中文摘要 本研究針對燃氣渦輪動葉内冷卻流道熱傳強化需求,探討梯型通道內衝擊噴柱列表面,設置於傾側角為45度之旋轉管道,其迎風面,衝擊面與背風面之熱傳性能。內設衝擊噴柱列,旋轉管道熱傳係數,係利用穩態紅外線檢測技術量测,實驗參數範圍為7500 ≤ 雷諾數(Re) ≤ 17500,0 ≤ Ro ≤ 0.3 ,0≤ 浮力數(Bu) ≤0.0883。
研究顯示,靜態管道之熱傳係數(Nu0)於7500≤ 雷諾數 ≤17500之範圍可提升至平滑圓管流域熱傳(Nu∞)之3.73至3.95倍,靜態管道之范寧摩擦係數( f0 ) 於7500 ≤ 雷諾數 ≤17500之範圍可提升至平滑圓管摩擦係數(f∞)之15.68至23.79倍。靜態管道之熱性能係數(TPF ) 於7500 ≤ 雷諾數 ≤17500之範圍可提升至0.96至1.07。旋轉管道迎風面,衝擊面與背風面與靜態管道相比之平均Nu/Nu0數,隨旋轉數增加先降低而後持續提升,其範圍分別為0.93至1.24倍、1.05至1.15倍與1.44至1.51倍。旋轉管道迎風面,衝擊面與背風面全展流域之平均紐賽數皆隨浮力數持續降低。
旋轉管道與靜態管道之范寧摩擦係數隨雷諾數增加而先降低而後持續提升 ,但與靜態管道之f/f0比值,卻隨雷諾數增加而持續下降至0.91倍。利用實驗結果推導靜態與旋轉通道熱傳及摩擦實驗公式,供CFD模擬或其他相關工程應用。
英文摘要 Drive by the requirement for the heat transfer enhancement of the internal coolant channel of a gas turbine rotor blade, the present study investigates the heat transfer performances of the leading, impinging and trailing endwalls for the rotating trapezoidal channel with the impinging jet-row at the channel orientation angle of 45 degrees. The heat transfer coefficients of the present rotating channel with the imping jet-row were measured using the steady-state infrared thermography method at the parametric conditions defined by Reynolds number (Re), rotation number (Ro), and buoyancy number (Bu) in the respective ranges of 5000For the non-rotating channel at 7500 ≤ Re ≤17500, the present area-average Nusselt numbers (Nu0) were elevated to 3.73 to 3.95 times of the smooth tubular flow (Nu∞) references; and the Fanning friction coefficients (f0) were raised to 15.68 to 23.79 times of the smooth tubular flow (f∞); together to cause the thermal performance factors (TPF) in the range of 0.96-1.07. Acting by the coupled Coriolis-force and buoyancy effects, the rotating-to-static area-averaged Nusselt number ratios (Nu/Nu0) over the leading, apex and trailing walls were initially reduced and followed by the subsequent recoveries as Ro increased from 0 to 0.3, leading to their Nu/Nu0 ratios in the respective ranges of 0.93-1.24, 1.05-1.15 and 1.44-1.51.
Over the leading, apex and trailing walls of the present rotating channel, all the area-averaged Nusselt numbers were decreased by increasing buoyancy number.
For both the present static and rotating channels, the Fanning friction factors were initially reduced and then increased as Reynolds number increased. But the ratios of the rotating-to-static channel Fanning friction factors (f/f0) were reduced to 0.91 by increasing Reynolds number.
Two sets of empirical correlations evaluating the regionally averaged Nusselt numbers and the channel averaged Fanning friction factors were devised using the present sets of experimental data for CFD validations and the relevant engineering applications.
論文目次 摘要 II
Extended Abstract III
謝誌 III
表格目錄 XVIII
圖表目錄 XIX
符號表 XXI
Chapter 1 前言 1
1.1 燃氣渦輪機應用簡介 1
1.2 燃氣渦輪機發展趨勢 5
1.3 渦輪葉片冷卻技術 7
1.4 研究目標 9
Chapter 2 文獻回顧 11
Chapter 3 實驗設備和方法 18
3.1 實驗設備 18
3.2 實驗方法 23
3.3 數據校準 26
Chapter 4 結果與討論 31
4.1 靜態和旋轉通道中的噴柱質量流量分佈 31
4.2 熱傳結果 36
4.3 范寧摩擦係數和熱性能係數 53
Chapter 5 結論 58
Chapter 6 參考文獻 62
附錄
一、 噴嘴流量係數Kj定義說明 65
二、 實驗不確定度分析 66
三、 實驗儀器類比轉數位訊號輸出至資料擷取器接線與設定方法 70
四、 實驗數據彙整 72
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