| 喷管超声段壁面冷却热态试验研究 |
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| 引用本文： | 额日其太,王强,吴寿生,魏福清.喷管超声段壁面冷却热态试验研究[J].推进技术,2001,22(4):322-325. |
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| 作者姓名： | 额日其太 王强 吴寿生 魏福清 |
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| 作者单位： | 北京航空航天大学 热动力工程研究所, |
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| 摘 要： | 在高温条件下，对三种轴对称收－扩喷管超声段壁面排气引射冷却方案（缝隙式气膜冷却、离散孔气膜冷却和冲击－气膜组合冷却）进行了试验研究。得到了不同冷却方案的壁面压力分布、壁面温度分布和红外辐射特性，以及冷却气流量对这些性能的影响。结果表明：采用排气引射冷却技术可以大幅度降低喷管的壁温和红外信号特征，其中缝隙式气膜冷却的应用前景最好，离散孔式气膜冷却值得深入研究，冲击－气膜组合冷却不适合作为喷管排气引射冷却的基本方案。
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| 关 键 词： | 轴对称收－扩喷管超声段壁面 冷却试验 喷管排气引射冷却方案 红外辐射 缝隙式气膜冷却方案 离散孔式气膜冷却 冲击－气膜组合 热态试验 军用飞机排气系统 |
| 文章编号： | 1001-4055(2001)04-0322-04 |
| 修稿时间： | 2000年10月26 |
Hot-air experimental investigation of cooling applicable to exhaust nozzles |
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| E RiQiTai,Wang Qiang,Wu ShouSheng and Wei FuQing.Hot-air experimental investigation of cooling applicable to exhaust nozzles[J].Journal of Propulsion Technology,2001,22(4):322-325. |
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| Authors: | E RiQiTai Wang Qiang Wu ShouSheng and Wei FuQing |
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| Institution: | Inst. of Thermo Power Engineering, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;Inst. of Thermo Power Engineering, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;Inst. of Thermo Power Engineering, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;Inst. of Thermo Power Engineering, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | The hot air experimental results of three cooling methods applicable to axisymmtric convergent divergent exhaust pumping nozzle with cooling on divergent wall were presented. The three methods include slot film cooling, discrete hole film cooling, and impact film cooling. To each scheme, the influence of cooling air flowrate on the distributions of wall pressure distribution and wall temperature and infrared radiation characteristics of nozzles were also investigated. The results reveal that the ejector pumping nozzle concept has significant potential to meet the challenges of reducing exhaust system hot-parts temperature and infrared radiation. |
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| Keywords: | Engine nozzles Gaseous film cooling Infrared radiation Heat test |
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