| 高超声速飞行器发动机热防护与发电一体化系统 |
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| 引用本文： | 姜培学,张富珍,胥蕊娜,祝银海.高超声速飞行器发动机热防护与发电一体化系统[J].航空动力学报,2021,36(1):1-7. |
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| 作者姓名： | 姜培学 张富珍 胥蕊娜 祝银海 |
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| 作者单位： | 清华大学能源与动力工程系二氧化碳资源化利用与减排技术北京市重点实验室,北京100084;清华大学能源与动力工程系热科学与动力工程教育部重点实验室,北京100084 |
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| 基金项目： | 国家自然科学基金创新研究群体项目(51621062)； 国家自然科学基金重点项目(51536004) |
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| 摘 要： | 在对高超声速飞行器的热防护和机载设备电能需求的综合考虑下,立足发动机能量管理优化,结合CO2的物性特点,提出了以超临界CO2为循环工质的高效热防护与高温发电一体化系统.此一体化方案可以在实现发动机热防护的同时,提供电能、并减少冷却用燃油流量.基于燃油为该一体化系统的唯一热沉,通过理论分析和计算,提出了两个一体化系统,通...
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| 关 键 词： | 高超声速飞行器 一体化系统 热防护 超临界CO2 闭式布雷顿循环 |
| 收稿时间： | 2020/5/30 0:00:00 |
Integrated thermal protection and power generation system of hypersonic vehicle engine |
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| JIANG Peixue,ZHANG Fuzhen,XU Ruin,ZHU Yinhai,ZHANG Fuzhen,XU Ruin,ZHU Yinhai.Integrated thermal protection and power generation system of hypersonic vehicle engine[J].Journal of Aerospace Power,2021,36(1):1-7. |
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| Authors: | JIANG Peixue ZHANG Fuzhen XU Ruin ZHU Yinhai ZHANG Fuzhen XU Ruin ZHU Yinhai |
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| Institution: | 1.Beijing Key Laboratory for CO2 Utilization and Reduction Technology,Department of Energy and Power Engineering,Tsinghua University,Beijing 100084,China2.Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,Department of Energy and Power Engineering,Tsinghua University,Beijing 100084,China |
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| Abstract: | Considering the thermal protection of hypersonic vehicle and the power demand of airborne equipment, based on the optimization of engine energy management, an integrated system of high temperature power generation and high efficiency thermal protection was proposed with supercritical CO2 as the circulating working fluid combined with CO2 physical characteristics. This integrated scheme can provide electricity and reduce the fuel carrying capacity on the premise of achieving thermal protection purpose. The measures to improve the performance of the integrated system were put forward by analyzing the integrated system based on the fuel as the sole heat sink: to maximize the temperature of the fuel heated in the CO2cooler and improve the performance of the CO2 closed Brayton cycle by using regeneration. The thermal efficiency of the system can reach 17%. When the flight time was 30 minutes, compared with battery and fuel cell, the net mass gain of the integrated system was reduced by 85% and 68%, and the volume was reduced by 81% and 59%. |
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| Keywords: | hypersonic vehicle integrated system thermal protection supercritical CO2 closed Brayton cycle |
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