| 亚/超燃混合发动机模块间界面参数设计及数值仿真 |
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| 引用本文： | 李璞,郭荣伟.亚/超燃混合发动机模块间界面参数设计及数值仿真[J].航空动力学报,2009,24(8):1837-1842. |
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| 作者姓名： | 李璞 郭荣伟 |
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| 作者单位： | 南京航空航天大学能源与动力学院; |
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| 摘 要： | 对轴对称双燃烧室冲压发动机亚/超燃模块间界面进行了初步设计研究.模拟了两股平行气流掺混的冷态流场,重点研究了台阶高度、台阶几何形状、亚燃模块流量比例等设计参数对掺混性能的影响规律,并提出了参数选择建议.在此基础上,给出了一个性能较优的设计方案,性能如下:马赫数为4时掺混段出口马赫数为1.48,总压恢复系数为0.765,增压比为17.71,温升比为4.05;马赫数为6时掺混段出口马赫数为2.08,总压恢复系数为0.502,增压比为28.03,温升比为4.67.
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| 关 键 词： | 高超声速流 双燃烧室冲压发动机 界面 数值分析 掺混性能 |
| 收稿时间： | 8/14/2008 8:05:11 PM |
| 修稿时间： | 2008/12/15 0:00:00 |
Design of the interface between ramjet and scramjet modules of dual combustor ramjet and flow field simulation |
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| LI Pu and GUO Rong-wei.Design of the interface between ramjet and scramjet modules of dual combustor ramjet and flow field simulation[J].Journal of Aerospace Power,2009,24(8):1837-1842. |
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| Authors: | LI Pu and GUO Rong-wei |
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| Institution: | College of Energy and Power Engineering;Nanjing University of Aeronautics and Astronautics;Nanjing 210016;China |
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| Abstract: | A preliminary study was carried out on the interface between ramjet and scramjet modules of dual combustor ramjet.Efforts were focused on the influence of the design parameters on the mixing performance using numerical method.The design parameters included the height of the step,the step geometry and the proportion of the mass flow of ramjet modules.An interface with better mixing performance was presented in the paper.Results indicate: the Mach number at the duct exit is 1.48,the total pressure recovery is... |
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| Keywords: | hypersonic flow dual combustor ramjet interface numerical analysis mixing performance |
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