臺灣博碩士論文加值系統

在極音速飛行的發展中，超燃衝壓發動機為目前極音速飛行動力系統的主要選擇之一。為了與燃燒效率更好的橢圓／圓形燃燒室進行結合，進氣道隔離段出口截面勢必進行橢圓／圓形的變化。本研究主要針對三維側壓極音速進氣道進行數值分析，比較下列算例的流場及進氣道性能，以供未來設計參考：(1)出口面積及高寬比相同之矩形出口與橢圓出口、(2)相同出口面積，不同橢圓出口高寬比、(3)正圓出口下，不同出口面積、(4)結合最佳化設計，探討正圓出口進氣道隔離段的截面變化對總壓恢復的影響。
本研究採用數值模擬方法中的有限體積法求解Navier-Stokes方程式，搭配Spalart-Allmaras紊流模組進行穩態的運算，探討不同方案之進氣道於隔離段內的流場。
在四馬赫的速度下，(1)相同的出口面積與高寬比，橢圓出口之總壓恢復係數較矩形出口高1.4%。(2)橢圓出口在不同高寬比下的出口參數相近，其中1:2有最高的總壓恢復係數，與矩形出口相比，提升3.57%；(3)增加出口面積使出口流速增加，在總壓恢復係數上有較好的表現，較原面積提升1.73%。(4)而在最佳化方面，總壓恢復係數比初始算例提高12.5%。

Scramjet is an engine mainly used in the hypersonic flight regime. In order to get high performance combustion efficiency, the inlet-isolator have to adapt configuration from rectangular into circle or elliptical. The main purpose of this study focuses on the design and flowfield of the sidewall compression in a hypersonic inlet as following: (1) change the shape of outlet from rectangular to elliptical with the outlet area and aspect ratio are fixed; (2) different aspect ratio of elliptical outlet isolator with the area of outlet is fixed; (3) different area of circle outlet isolator with the shape of the outlet is fixed; and (4) to consider the optimal design, to study the total pressure recovery (P_T) by changing the cross section of inlet-isolator.
In this study, we applied numerical simulation method of the finite volume method to solve Navier-Stokes equations with Spalart-Allmaras turbulent model to simulate cases on the flowfield of the inlet-isolator.
At Mach No. 4: (1) the recover coefficient (P_T) of the elliptical outlet case is more than rectangular case about 1.4% in the same outlet aspect ratio (H/S); (2) the aspect ratio of 1:2 got the highest P_T than others in all elliptical cases, and the P_T increased 3.57% more than rectangular case; (3) the P_T increased 1.73% than original case while the outlet area increased; (4) for the optimal design, the P_T increased 12.5% than original case.

摘要 I
Abstract II
誌謝 III
目錄 IV
圖目錄 VI
表目錄 X
符號索引 XI
第一章 前言 1
1.1 研究動機 1
1.2 研究背景 2
1.2.1 發動機演進歷史 2
1.2.1 噴射發動機種類 3
1.2.2 衝壓發動機進氣道 4
1.3 超音速進氣道基本流場 11
1.3.1 震波 12
1.3.2 總壓恢復係數 13
1.3.3 增壓比 13
1.4 文獻回顧 15
1.5 研究目的 19
第二章 研究方法 20
2.1 數學模式(Mathematic Model) 21
2.1.2 統御方程式 21
2.1.3 紊流方程式 22
2.2 數值方法(Numerical Technique) 23
2.3 數值最佳化(Numerical Optimization) 24
2.4 最佳化軟體—SmartDo 24
2.4.1 ANSYS Workbench參數輸出與設定 25
2.4.2 SmartDO參數設定 26
第四章 物理模型與格點系統 31
3.1 物理模型 31
3.1.1 矩形出口進氣道模型 31
3.1.2 橢圓出口進氣道模型 31
3.1.3 最佳化分析之正圓出口模型 31
3.2 邊界條件 34
3.3 格點驗證 36
第四章 結果與討論 44
4.1 程式驗證 44
4.2 矩形出口進氣道流場分析 46
4.2.1 二維與三維流場比較 51
4.3 橢圓出口進氣道流場分析 55
4.3.1 不同高寬比之橢圓出口進氣道流場比較 60
4.4 矩形出口與橢圓出口進氣道比較 70
4.5 出口面積大小對進氣道之影響 78
4.6 最佳化分析之算例比較 85
第五章 結論與未來研究 92
5.1 結論 92
5.2 未來展望 92
參考文獻 94
附錄A 97
作者簡介 98

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