穿音速軸流式壓縮器內流動現象非常複雜，舉凡穿音速流、紊流、二次流、間隙流及各級間流場的干擾現象等，加上渦輪引擎用壓縮器葉片外形複雜，具高度扭曲、高寬比大、厚度薄等特性，需使用三維的數值模擬方法才得以掌握整體流場的變化。研究是採用CFX公司的TurboGrid及TASCflow商用套裝軟體建構三維的O-H網格，並以控制體積有限元素法為基礎求解Reynolds-averaged Navier-Stokes方程式。
研究過程中，嘗試用不同的網格數量及方法模擬壓縮器流場，並比對美國太空總署（NASA）Lewis Research Center的Fan Rotor-67測試報告，以尋找出適合的紊流模式。結果顯示，使用RNG 的紊流模式，與實驗比對較為準確。計算出來的流場中可發現相對馬赫數等位線分布、震波生成的位置及二次流的產生等現象，皆大致符合實驗結果與氣動力特性。然後再模擬一小型的一級穿音速軸流式壓縮器流場，探討其變化及特性。

The flow field within the blade rows of a multistage axial compressor is extremely complex. This includes transonic flows, turbulence, secondary flows, tip clearance flows, inter-blade row interference, etc. The blade shape in transonic axial compressor is complex too, including high twist, high aspect ratio, thinner thickness, etc. Hence, the fully three-dimensional approach is the only plausible way to numerically investigate the flow variation in compressor field.
Various computer algorithms and CFD codes are being proposed to satisfy this need, TurboGrid in constructed O-H grid system and TASCflow in solving the Reynolds-averaged Navier-Stokes equations by control volume finite element method, are used in this study. The validation of CFD codes is conducted by comparing the predictions with a benchmark database acquired experimentally on a FAN ROTOR-67 NASA transonic fan. Then, the simulation and analysis of one stage transonic axial compressor is performed.

誌謝 ii
摘要 iii
ABSTRACT iv
目錄 v
表目錄 vii
圖目錄 viii
符號說明 xi
1. 前言 1
2. 文獻回顧 6
3. 研究方法 13
3.1 統御方程式 13
3.2 紊流模型介紹 15
3.2.1 紊流模型 15
3.2.2 RNG 紊流模型 16
3.2.3 紊流模型 17
3.3 數值方法 18
3.3.1 通量元素 19
3.3.2 擴散項與壓力項的處理 23
3.3.3 數值通量的計算 24
3.3.4 壓力與速度的耦合 26
3.3.5 矩陣的求解 27
4. 物理模型與邊界條件 29
4.1 物理模型 29
4.2 網格產生 29
4.3 動態網格 31
4.4 邊界條件 33
5. 結果驗證與討論 35
5.1 網格驗證 35
5.2 數值比對 40
5.3 流場比對 43
5.4 流場分析 48
5.5 一級壓縮器流場模擬結果與分析 50
6. 結論與建議 50
6.1 結論 50
6.2 研究建議與方向 50
6.3未來展望 50
參考文獻 50
自傳…….75

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