| 燃烧室缝槽气膜冷却方案研究 |
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| 引用本文： | 任加万,谭永华.燃烧室缝槽气膜冷却方案研究[J].火箭推进,2007,33(6):28-33. |
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| 作者姓名： | 任加万 谭永华 |
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| 作者单位： | 西安航天动力研究所,陕西,西安,710100;航天推进技术研究院,陕西,西安,710100 |
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| 摘 要： | 针对超音速飞行器冲压发动机高马赫数、长航时的特点,结合工程计算方法和设计思想,建立了燃烧室缝槽气膜冷却过程一维计算模型,详细研究了各主要因素对气膜冷却效果的影响,并给出了某型冲压发动机高温燃烧室缝槽气膜冷却结构参考设计方案。结果表明,通过改善结构布局,合理分配缝隙冷气流量,可以有效地提高气膜冷却效果、降低壁温,适应高温燃气参数分布对隔热屏的热防护要求。
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| 关 键 词： | 冲压发动机 燃烧室 气膜冷却 壁温计算 |
| 修稿时间： | 2007年6月27日 |
Investigation on the structure scheme of slot air film cooling combustion chamber |
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| Ren Jiawan,Tan Yonghua.Investigation on the structure scheme of slot air film cooling combustion chamber[J].Journal of Rocket Propulsion,2007,33(6):28-33. |
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| Authors: | Ren Jiawan Tan Yonghua |
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| Abstract: | Aimed at the special operation requirements of ramjet powered vehicle characterized by high Mach number and long operation duration, combined with engineering calculation methods, a 1-D slot air film cooling analysis model was developed in this paper. The main factors of the film cooling efficiency were investigated in detail. A prediction of the slot film cooling efficiency of a ramjet combustion chamber was obtained. The results show that the film cooling efficiency could be improved and the wall temperature could be decreased by the rational distribution of the flow rate of the slot cooling air and the improvement of the structure. |
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| Keywords: | ramjet combustion chamber air-film cooling computation of wall temperature |
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