| 超燃冲压发动机支板热环境及热防护方案 |
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| 引用本文： | 孙冰,郑力铭.超燃冲压发动机支板热环境及热防护方案[J].航空动力学报,2006,21(2):336-341. |
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| 作者姓名： | 孙冰 郑力铭 |
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| 作者单位： | 北京航空航天大学,宇航学院,北京,100083 |
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| 摘 要： | 在超燃冲压发动机工作过程中,支板前缘的热环境非常恶劣.本文研究了超燃冲压发动机支板前缘的热环境,得到了热载荷分布.提出了支板前缘金属结构再生冷却方案、耐烧蚀材料热防护方案和气体喷射热防护方案,并对这三种方案的热防护效果进行了数值模拟.数值模拟的结果表明,金属结构再生冷却方案无法对支板进行有效的热防护;耐烧蚀材料方案可以在飞行马赫数8以下起到很好的热防护效果;而当马赫数大于8时,则只有气体喷射方案可以实现有效的热防护.
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| 关 键 词： | 航空、航天推进系统 超燃冲压发动机 热环境 热防护 |
| 文章编号： | 1000-8055(2006)02-0336-06 |
| 收稿时间： | 2005/5/17 0:00:00 |
| 修稿时间： | 2005年5月17日 |
Research of Scramjet Strut Thermal Environment and Thermal Protection Scheme |
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| SUN Bing and ZHENG li-ming.Research of Scramjet Strut Thermal Environment and Thermal Protection Scheme[J].Journal of Aerospace Power,2006,21(2):336-341. |
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| Authors: | SUN Bing and ZHENG li-ming |
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| Institution: | School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | The thermal environment of the scramjet strut leading edge is rigorous.In this paper,the thermal environment was studied,and the heat load distribution was obtained.Based on the thermal environment,three thermal protection schemes were put forward,i.e.regeneration cooling scheme,C/SiC thermal protection scheme and gas jet thermal protection scheme.Numerical simulation was employed to obtain the thermal protection effectiveness of these three schemes.The results show that the regeneration cooling scheme can't protect strut leading edge from destruction;C/SiC thermal protection scheme works well up to flight mach number not exceeding 8,and only gas jet thermal protection scheme can protect strut leading edge from destruction up to Mach 8 and higher. |
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| Keywords: | aerospace propulsion system scramjet thermal environment thermal protection |
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