||Studies of Supersonic Ramjet Engine Cooling Technology by using Endothermic Hydrocarbon Fuels
||Department of Aeronautics & Astronautics
2-D axisymmetric tube
heat transfer deterioration
empirical heat transfer correlations
Scramjet engine thermal management system technology, which combined convection cooling by passing fuel through internal channel structures and the fuel endothermic cracking reaction, is one of the main efforts of our current national defense science and technology. Such thermal management system with convection cooling and fuel endothermic cracking reaction has been regarded as a key technology of scramjet engine around the world. With the implementation of this research, it is expected to develop an analysis tool of scramjet engine thermal management system that can help researchers in the field of scramjet engine in their design of thermal management systems. The research developed a high efficiency thermal management system that can be used for the next generation hypersonic speed vehicle scramjet's cooling problems. Scramjet engine thermal management systems analysis technology platform development in this research, in addition to the implementation of this research, it can also promote the possibility of technical autonomy. This research will analyze the thermal management system designs for the scramjet engine in hypersonic vehicle based on the heat flux needs and surface temperature limits. It is found that the closer working pressure of the hydrocarbon endothermic fuel in the cooling pipe is to the critical pressure, the more severe physical properties changes. In this process, the heat transfer deterioration caused by the decreased Cp and ρ. Various endothermic fuel thermal management system will be designed and evaluated to meet the heat transfer needs. Comparison with empirical heat transfer correlations, and then make new heat transfer correlation of JP-10 hydrocarbon fuel to facilitate Compared with the heat transfer empirical formula in the literature, the physical properties (density, specific heat, thermal conductivity, viscosity coefficient) and pressure parameters of the JP-10 hydrocarbon fuel can not be used in the JP-10 hydrocarbon fuel. Therefore, the heat transfer empirical formula will be made in this paper to facilitate the consideration of setting parameters.
第一章 緒論 1
1.1 前言 1
1.2 文獻回顧 3
1.2.1 熱防護系統 3
1.2.2 吸熱型碳氫燃料 11
1.2.3 超臨界狀態 12
1.2.4 裂解反應 14
1.3 研究動機 19
1.4 本文架構 21
第二章 研究方法與步驟 22
2.1 系統介紹 22
2.2 Fluent介紹 24
2.2.1 連續方程式 26
2.2.2 動量方程式 26
2.2.3 能量方程式 27
2.2.4 RNG紊流模型 28
2.3 燃油物理性質 29
2.4 網格收斂性 36
第三章 超燃衝壓引擎冷卻管道系統2-D軸對稱圓管數值分析 41
3.1 熱傳惡化 41
3.2 物理性質的影響 50
3.2.1 比熱影響熱流場 51
3.2.2 密度影響熱流場 53
3.2.3 熱傳導係數影響熱流場 57
3.2.4 黏滯係數影響熱流場 58
3.3 管徑的影響 64
3.4 熱通量的影響 67
3.5 壓力的影響 68
3.6 相關文獻之熱傳經驗公式與建立 70
第四章 超燃衝壓引擎冷卻管道系統3-D冷卻管道數值分析 79
4.1 三維網格獨立性與模擬測試 79
4.2 3-D冷卻管道模擬結果 84
第五章 結論 88
Aspen plus介紹 90
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