| 多斜孔冷却技术分析 |
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| 引用本文： | 孟祥泰,刘高恩. 多斜孔冷却技术分析[J]. 航空动力学报, 1994, 9(4): 391-393,443 |
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| 作者姓名： | 孟祥泰 刘高恩 |
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| 作者单位： | 北京航空航天大学 |
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| 摘 要： | 通过燃烧室火焰筒壁一种先进冷却技术(多斜孔壁)的计算分析表明, 采用这种冷却技术的火焰筒壁温要比纯气膜冷却的火焰筒壁温约低150K, 并且指出这种冷却技术中的内对流冷却项是使壁温降低的一项重要因素。
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| 关 键 词： | 空气喷气发动机 环形燃烧室 燃烧 冷却 火焰筒 |
| 收稿时间： | 1994-04-01 |
| 修稿时间： | 1994-06-01 |
MULTIHOLE COOLING TECHNOLOGY ANALYSES |
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| Meng Xiangtai and Liu Gaoen. MULTIHOLE COOLING TECHNOLOGY ANALYSES[J]. Journal of Aerospace Power, 1994, 9(4): 391-393,443 |
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| Authors: | Meng Xiangtai and Liu Gaoen |
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| Affiliation: | 4th Dept.,Beijing University of Aeronautics and Astronautics,Beijing 100083 |
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| Abstract: | This paper is to analyse the advantage of the multihole cooling technology.The calculation showed that the combuster liner temperature with multihole cooling technology would be 150K to 200K less than the wall temperature with film cooling technology,and the term of inner convection within the multihole is the main factor to make the wall temperature being lower. |
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| Keywords: | Combustion Cooling Flame tubes |
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