系統識別號 | U0002-2108201810215700 |
---|---|
DOI | 10.6846/TKU.2018.00638 |
論文名稱(中文) | 脈衝爆震引擎噴嘴流場之初步數值模擬 |
論文名稱(英文) | Preliminary Numerical Simulation of Flow Field Through the Nozzle of Pulse Detonation Engines |
第三語言論文名稱 | |
校院名稱 | 淡江大學 |
系所名稱(中文) | 航空太空工程學系碩士班 |
系所名稱(英文) | Department of Aerospace Engineering |
外國學位學校名稱 | |
外國學位學院名稱 | |
外國學位研究所名稱 | |
學年度 | 106 |
學期 | 2 |
出版年 | 107 |
研究生(中文) | 吳彥澂 |
研究生(英文) | Yen-Cheng Wu |
學號 | 605430049 |
學位類別 | 碩士 |
語言別 | 英文 |
第二語言別 | |
口試日期 | 2018-07-17 |
論文頁數 | 69頁 |
口試委員 |
指導教授
-
牛仰堯
委員 - 劉登 委員 - 楊世昌 |
關鍵字(中) |
爆震引擎 爆震現象 航空發動機 |
關鍵字(英) |
Pulse Detonation Engines Detonation Wave Aircraft Engine |
第三語言關鍵字 | |
學科別分類 | |
中文摘要 |
近期以來,脈衝爆震引擎(PDE)被認為是有發展性的推進技術,其在熱力循環效率,結構的簡單性和操作使用的可擴展性方面具有潛在的優勢。本文目的為針對實際應用較少的爆震引擎進行文獻的回顧與整理,並且建構基礎的模擬模型以利日後發展其相關的分析與評估。在數值模擬的部分,我們探討了三個不同計算模型所產生的不同差異性以及引擎內部的大致流體特性,其模型分別為利用不同算則計算之無黏性的冷流以及無黏性氫氧燃燒化學反應模型。以上模型皆能成功模擬出相似的物理現象,並在之後的研究加以應用。 |
英文摘要 |
The Pulse Detonation Engine (PDE) has been considered a developmental propulsion technology with advantages in thermal efficiency, simple in structure, and widely of operational application. The purpose of this paper is to review the literature for a detonation engine, and to construct a basic simulation model to facilitate the development of its analysis and evaluation. In the numerical simulation, we used the different variations of the three different computational models to simulate the approximate fluid properties inside the engine. The models are the inviscid cold flow with two different scheme and the first-order inviscid chemical reaction model. All of the above models can successfully simulate mostly physical phenomena and apply them in later studies. |
第三語言摘要 | |
論文目次 |
Nomenclature v List of Figure vi 1. Introduction 1 1.1. Background 1 1.3. Literature Review 6 1.4. Cycle Operation of PDE 15 1.4.1 Filling Process 16 1.4.2 Detonation Process 17 1.4.3 Purging Process 17 1.4.4 Rarefaction or Blowdown Process 18 1.5. Detonation Theory 18 1.5.2 ZND Model 34 2. Governing Equation 39 3. Numerical Results 40 3.1 The Numerical Results 45 3.2. Enlarged View 53 3.2.1 Nozzle 53 3.2.2 Throat 55 3.3. Distributions along Centerline 57 3.5 Result Discussion 58 4. Conclusions 62 5. Future Works 63 6. References 64 Figure 1.1 Specific impulse vs. Mach number regimes of various propulsion systems (Ma, 2008) 3 Figure1.2 Comparsion of PDEs with other engines (Ma, 2008) 5 Figure 1.3 Cycle Operation of PDE (Ma, 2008) 16 Figure 1.5 Schematic of Rayleigh lines and Hugoniot curve (Lee, 2008) 20 Figure 1.4 Steady planar detonation wave in a tube (Ma, 2008) 21 Figure 1.6 Schematic of pressure profile for a ZND detonation propagation in a tube (Ma, 2008) 34 Figure 1.7 Comprparison of Brayton and Humphrey cycle 35 Figure 3.1 Geometry (Ma, 2008) 41 Figure 3.2 Time evolution of Mach number field during the first cycle of operation. (Ma, 2008) 42 Figure 3.3 Time evolution of and density-gradient field during the first cycle of operation. (Ma, 2008) 43 Figure3.4 Time evolution of Mach number field and density-gradient field during the first cycle of operation. At t=1.33ms, 1.59 ms, 1.84ms, 2.25 ms, 3.08 ms, 3.83ms. 47 Figure3.5 Time evolution of Mach number field and density-gradient field during the first cycle of operation. At t= 0.6ms, 0.67ms, 0.8ms, 0.94ms, 1.22ms, 1.68ms. 50 Figure3.7 Enlarged views of pressure contour by CE/SE at 0.65 ms (2003, Ma) 53 Figure3.8 Enlarged views of cold flow pressure contour by AUSMD at time= 1.92ms 53 Figure3.9 Enlarged views of cold flow pressure contour by Fluent at time= 0.81ms 54 Figure3.10 Enlarged views of inviscid chemical reaction flow pressure contour by Fluent at time= 0.59ms 54 Figure3.11 Enlarged views of pressure contour by CE/SE (2003, Ma) 55 Figure3.12 Enlarged views of cold flow pressure contour by AUSMD at time= 1.44ms 55 Figure3.13 Enlarged views of cold flow pressure contour by Fluent at time= 0.62ms 56 Figure3.14 Enlarged views of inviscid chemical reaction flow pressure contour by Fluent at time= 0.44ms 56 Figure 3.15 Case cold flow (left) and chemical reaction (right) pressure and Mach number distributions along centerline during first cycle of operation at t=0.67 ms 57 Figure 3.16 Case cold flow (left) and chemical reaction (right) pressure and Mach number distributions along centerline during first cycle of operation at t=0.96 ms 57 Figure 3.17 Case cold flow (left) and chemical reaction (right) pressure and Mach number distributions along centerline during first cycle of operation at t=1.18 ms 58 Figure 3.18. Effect of valve close-up time on specific impulse 62 |
參考文獻 |
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