| 超燃冲压发动机地面试验氢燃烧加热器流场数值模拟 |
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| 引用本文： | 王辽,徐旭.超燃冲压发动机地面试验氢燃烧加热器流场数值模拟[J].航空动力学报,2008,23(8):1397-1402. |
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| 作者姓名： | 王辽 徐旭 |
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| 作者单位： | 北京航空航天大学,宇航学院,北京,100191 |
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| 摘 要： | 采用Fluent软件模拟超燃冲压发动机直联式地面试验用燃烧型加热器的内部流场,对设计的氢气多孔喷射和氢气单孔喷射方案分别进行了研究.计算结果表明:加热器出口流场均能满足设计总温为1 900 K,马赫数为1.85的要求,而氢气单孔喷射方案优于氢气多孔喷射方案.计算中也发现了这两种设计方案中存在的不足.
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| 关 键 词： | 超燃冲压发动机 燃烧加热器 数值模拟 |
| 收稿时间： | 8/1/2007 12:00:00 AM |
| 修稿时间： | 2008/2/21 0:00:00 |
Numerical investigation of hydrogen combustion-heater for scramjet ground test |
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| WANG Liao and XU Xu.Numerical investigation of hydrogen combustion-heater for scramjet ground test[J].Journal of Aerospace Power,2008,23(8):1397-1402. |
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| Authors: | WANG Liao and XU Xu |
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| Institution: | School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Fluent was used to investigate numerically the internal flow field of combustion-heater for direct-connect scramjet ground test facility.The hydrogen multi-hole injection and hydrogen single-hole injection was computed,respectively.The results show that the exit flow field can meet the design requirements of total temperature 1 900 K,Ma=1.85,and the hydrogen single-hole injection is superior to hydrogen multi-hole injection.Meanwhile the computational results also indicate the shortcomings of these two design schemes. |
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| Keywords: | scramjet combustion-heater numerical investigation |
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