| 考虑导热对流和辐射作用的轴对称收扩喷管壁温计算 |
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| 引用本文： | 刘友宏,李江宁,才娟.考虑导热对流和辐射作用的轴对称收扩喷管壁温计算[J].航空动力学报,2008,23(4):635-641. |
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| 作者姓名： | 刘友宏 李江宁 才娟 |
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| 作者单位： | 1. 北京航空航天大学能源与动力工程学院,北京,100083
2. 沈阳发动机设计研究所,沈阳,11001 |
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| 摘 要： | 基于N-S方程求解了包括引射流、加力燃烧室在内的轴对称收扩喷管内外流一体化的流场,建立了考虑导热、对流换热和辐射换热作用的轴对称收扩喷管各层壁温分布的计算模型,包括隔热屏、喷管筒体、外调节片三层结构.对某航空发动机进行了多工况计算,燃气的物性随压力、温度和油气比的变化采用了一系列精度较高的计算公式和计算方法.计算结果表明:基于密度求解器求解包含引射流在内的轴对称收扩喷管内外流一体化的跨声速流场是成功的.隔热屏和收扩喷管筒体沿流向温度逐渐升高,喷管筒体壁温在喉部达到最大,在扩张段逐渐降低;收扩喷管外调节片壁温与收扩喷管筒体的壁温变化规律相同,但是壁温最大值则位于喉部前某一位置.计算结果与经过试验验证程序的结果符合良好.
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| 关 键 词： | 航空、航天推进系统 收扩喷管 跨声速流场 壁温 辐射换热 导热 对流换热 |
| 文章编号： | 1000-8055(2008)04-0635-07 |
| 收稿时间： | 2007/9/28 0:00:00 |
| 修稿时间： | 2007年9月28日 |
Wall temperature calculation on an axi-symmtrical converging-diverging nozzle considering heat conduction,convection and radiation |
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| LIU You-Hong,LI Jiang-Ning and CAI Juan.Wall temperature calculation on an axi-symmtrical converging-diverging nozzle considering heat conduction,convection and radiation[J].Journal of Aerospace Power,2008,23(4):635-641. |
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| Authors: | LIU You-Hong LI Jiang-Ning and CAI Juan |
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| Affiliation: | School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;Shenyang Aeroengine Design and Research Institute, Shenyang 110015, China;Shenyang Aeroengine Design and Research Institute, Shenyang 110015, China |
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| Abstract: | The flow field and the wall temperature distribution calculation models on a converging-diverging nozzle considering the heat conduction,heat convection and radiation heat transfer are established and computed.The flow field is governed by the Navier-Stokes equations and the equations are solved based on the density solver.The wall temperature distribution calculation model is based on the heat transfer mechanism and the heat flux equilibrium.And the corresponding FORTRAN programs for the three layer wall temperature calculation of the nozzle are written.Many flight cases are calculated in which the properties of the burning gas mixture are calculated by a series of formulas and methods considering them varied with the pressure,the temperature and the ratio of oil to air.The results show that the heat shield temperature and the converging-diverging nozzle cylindrical wall temperature increase along the flow direction and decrease in the expand segment of the nozzle.The maximum wall temperature happens around the nozzle throat position.The outer adjustment plate temperature outside of the nozzle cylinder reaches its maximum some little before the nozzle throat position.The best agreement between the calculation and the given data can be observed in the paper. |
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| Keywords: | aerospace propulsion system converging-diverging nozzle transitional sonic flow field wall temperature radiative heat transfer heat conduction convective heat transfer |
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