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研究生： 張雅筑
Chang, Ya-Chu
論文名稱： 超音速燃燒衝壓引擎下游壓力擾動對隔離段燃燒室震波串之影響
Response of Shock Train in Isolator-Combustor to Downstream Pressure Oscillation of a Scramjet Engine
指導教授： 袁曉峰
Yuan, Tony
學位類別： 博士
Doctor
系所名稱： 工學院 - 航空太空工程學系
Department of Aeronautics & Astronautics
論文出版年： 2022
畢業學年度： 110
語文別： 英文
論文頁數： 103
中文關鍵詞： 超燃衝壓引擎內流場 、超燃衝壓引擎隔離段燃燒室 、震波串 、震波動態 、流場擾動
外文關鍵詞： scramjet internal flow, scramjet isolator-combustor, shock train, shock dynamics, flow oscillation
ORCID： 0000-0002-3259-8006
相關次數： 點閱：100  下載：15 
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    • 本研究經由三維冷流場數值模擬探討超音速燃燒衝壓引擎內流場為馬赫2.2時，震波串對下游擾動之響應。計算區域包含了隔離段與燃燒室，並採用了k–ω SST紊流模式以改善傳統雙方程紊流模式在逆向壓力邊界層問題往往過於高估其剪應力之缺點。流道出口邊界條件設置為一給定壓力，以模擬燃燒過後產生之高壓，並且加上從188到1128赫茲之週期性壓力振盪頻率以模擬因燃燒不穩定產生之流場振盪現象。結果顯示下游的壓力擾動會透過分離的邊界層傳遞至上游，而分離邊界層引發了分離震波與分離泡，超音速中心流因而產生X型震波以調節中心流場與分離泡之間的壓力差，並且形成了一系列的震波串。震波串隨著下游擾動而產生位移，當擾動頻率較小時，震波串位移較大，並且發現震波串位移之加速度與分離泡內之壓力變化率相關，當下游擾動頻率增加時，分離泡壓力變化率隨之增加，進而產生較大之震波串負向加速度，使震波串往隔離段入口移動，在低頻率時位移較大是因為其振盪週期較大。然而當下游擾動壓力大於1128赫茲時，分離泡內壓力不再隨著擾動頻率增加而增加，使得震波串趨於穩定。當下游振盪振幅減小時，震波串也會較為穩定，因分離泡內壓力變化率較小，產生之震波串負向加速度也較小。通過導納函數分析，震波串可視為一低通濾波器與阻尼器，將隔離段與燃燒室之間的振盪減幅直至消散。

    The response of Mach 2.2 internal flowfield to downstream pressure oscillation in a scramjet engine is studied numerically. The physical domain includes both the isolator and combustor. The theoretical formulation is based on the full conservation equations of three-dimensional non-reacting flow. Turbulence closure is achieved using the k–ω SST model to improve the prediction of shear stress under adverse pressure gradient. As part of the downstream boundary condition, the high pressure with periodic oscillations in the frequency range of 188-1128 Hz are imposed to mimic flow oscillations caused by combustion instability. The downstream disturbance is found to influence the supersonic core flow in the isolator through separated boundary layers. A shock train is initiated from corner separation shocks, and X-type shocks take place to adjust the pressure between the core flow and the separation bubble on the wall. When the frequency of back pressure oscillation is lower, the shock front fluctuates over a larger displacement. The shock front acceleration is correlated to the rate of change of pressure in the separation bubble and increases in negative direction with increasing back pressure frequency, leading the shock train to move toward inlet. The shock train has larger displacement in low-frequency since the longer period of oscillation. However, when the oscillation increases to 1128 Hz, the rate of change of pressure in the separation bubble decreases, resulting in a more stable shock front. When the oscillation amplitude is smaller, the shock front becomes stable because the pressure variation and the shock acceleration magnitude are small. From the admittance function analysis, the shock train acts as a low-pass filter and damps flow oscillation in the isolator-combustor.

    ABSTRACT i 摘要 ii 致謝 iii TABLE OF CONTENT iv LIST OF TABLES vii LIST OF FIGURES viii NOMENCLATURE xiii Chapter 1 1 1.1 Background 1 1.1.1 “Statoréacteur” 1 1.1.2 Scramjet 3 1.1.3 History of scramjet 5 1.1.4 Some aspects and challenges of scramjet 9 1.1.4.1 Supersonic combustion 10 1.1.4.2 Fuel and mixing 10 1.2 Motivation and thesis objective 18 1.3 Literature review 12 1.3.1 Shock train 12 1.3.2 Acoustic waves 16 1.3.3 Combustion oscillation 16 Chapter 2 18 2.1 Governing equations 19 2.2 Constitutive relations and equations of states 20 2.3 Turbulence modeling 21 2.3.1 Closure problem 22 2.3.2 Turbulence energy equation model 25 2.3.3 Effects of compressibility 28 2.3.3.1 Favre-averaged governing equations 28 2.3.3.2 Compressibility effect on turbulent eddy 30 2.3.4 Species diffusion 31 Chapter 3 33 3.1 Coupled solver 33 3.2 Flowpath configurations and boundary conditions 35 3.3 Grid independence study 37 Chapter 4 39 4.1 Benchmark comparison 39 4.2 Free expansion condition 40 4.2.1 With injections 40 4.2.2 Without injections 42 4.3 Steady-state flowfield 42 4.3.1 Flow properties 43 4.3.2 Formation of shock train 44 4.4 Shock train length prediction 47 4.5 Shock wave response to downstream disturbance 50 4.6 Shock front three-dimensionality 54 4.7 Influence of disturbance frequency on shock response 55 4.8 Effect of back pressure oscillation amplitude 57 4.9 Acoustic wave response to shock wave 58 Chapter 5 61 5.1 Concluding remarks 61 5.2 Recommendation for future work 63 5.2.1 Constraint of isolator configuration on shock train length 63 5.2.2 Separation on different walls 63 Bibliography 65

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