臺灣博碩士論文加值系統

軸流式壓縮器各級壓縮比無法太高的主要原因為：若後級壓力比前級高太多，則很難控制氣流順利往後級流動。然而提高各級壓縮比的優點是可提升引擎推力並減少壓縮機的總級數，進而減輕引擎長度、重量並增加推重比，因此提升壓縮比是壓縮器設計者的目標之一。
本研究以NASA Rotor 67為模型，並採用ANSYS之3D之BladeGen、BladeEditor軟體建構扇葉3D模型，再以TurboMesh產生結構化網格，Turbomachinery Fluid Flow（CFX）驗證3D流場。後續以Static Structural與Modal確認結構強度與頻率，在藉由模態分析結果匯入CFX進行顫振(Flutter)分析，觀察葉片間相互作用以確保其安全性。
參考現有之NASA R67 Rotor的軸流式穿音速葉片實驗數據彙整，於CFX中設定已知邊界條件：質量流率、出口背壓、轉速、入口總壓與總溫。質量流率、壓縮比、效率及所需功率，誤差低於5%。再藉由修改扇葉幾何達到提升壓縮比之目標。

The reason why compression ratio of each level of axial-flow compressor can’t be too high is as follow: It is difficult to control air flow if hinder level pressure is much higher than previous level. However, higher compression ratio of each level will improve thrust of engines and reduce total number of compressor level. This indicate that engine length and weight may reduce while thrust-to-weight ratio enhance. Thus, increase compression ratio is the priority of designing compressor.
This work is based on NASA Rotor 67, ANSYS 3D software of BladeGen and BladeEditor was used to build 3D model of blades, TubroMesh was used to generate structural grip, Turbomachinery Fluid Flow (CFX) was use to simulate and examine flow field. Static Structural and Modal modulus was used to confirm structural strength and natural frequency. By import results to CFX proceed Flutter analysis, observed the interaction of propeller to ensure safety.
Refered to NASA R67 Rotor axial-flow compressor transonic propeller experiment date and summarized them into CFX to set up initial boundary condition, including mass flow rate, exit backpressure, angular velocity, entrance total pressure and entrance total temperature. Error of mass flow rate, compression ratio, efficiency and power output should lower than 5%. Finally, modified propeller geometry to enhance compression ratio.

目錄
誌謝 I
摘要 II
Abstract III
目錄 IV
圖目錄 VII
表目錄 X
第一章 緒論 1
1.1 前言 1
1.2 研究目的 5
1.3 文獻回顧 6
1.4 論文結構 9
第二章 基礎理論與軟體介紹 10
2.1 流場統御方程式 10
2.3 數值方法 14
2.4 流固耦合分析 16
2.5 軸流壓縮機理論 17
2.6 結構力學基礎理論 19
2.7 結構模態理論 26
2.8 葉片顫振效應 30
第三章 研究方法與步驟 31
3.1 葉片模型建立 32
3.2 網格產生 33
3.3 轉子流場分析 36
3.4 轉子靜態結構與模態分析 40
3.5 轉子顫振分析 44
3.6 轉子設計分析 48
3.7 單級流場分析 50
第四章 模擬結果 53
4.1 轉子流場分析結果 53
4.2 轉子靜態分析結果 60
4.3 轉子模態分析結果 64
4.4 轉子顫振分析 67
4.5 轉子設計分析 69
4.6 單級流場分析 78
第五章 結論與未來展望 82
5.1 流場分析結論 82
5.2 靜態分析結論 83
5.3 模態分析結論 83
5.4 顫振分析結論 83
5.5 轉子設計分析結論 84
5.6 單級流場分析結論 84
5.7 未來展望 85

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