| 液氢液氧发动机喷管化学反应流数值模拟 |
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| 引用本文： | 方丁酉,张为华,夏智勋,王建平.液氢液氧发动机喷管化学反应流数值模拟[J].推进技术,1996,17(4):1-4. |
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| 作者姓名： | 方丁酉 张为华 夏智勋 王建平 |
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| 作者单位： | 国防科技大学航天技术系 |
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| 摘 要： | 用时间相关的半隐格式求解液氢液氧发动机喷管中的化学反应流动，考虑了６种燃烧产物，８个基元反应，得到了流动参数和产物的质量分数在流场中的分布，为发动机化学动力学损失计算和喷管热结构设计提供了必要数据。计算结果表明，采用半隐格式解决组分连续方程刚性引起的数值不稳定是有效的。
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| 关 键 词： | 氢氧发动机，发动机喷管，喷管气流，反应流，数值模拟 |
NUMERICAL SIMULATION OF REACTING FLOWS IN LO2/LH2 ROCKET ENGINE NOZZLE |
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| Fang Dingyou,Zhang Weihu,Xia Zhixun and Wang Jianping.NUMERICAL SIMULATION OF REACTING FLOWS IN LO2/LH2 ROCKET ENGINE NOZZLE[J].Journal of Propulsion Technology,1996,17(4):1-4. |
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| Authors: | Fang Dingyou Zhang Weihu Xia Zhixun and Wang Jianping |
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| Institution: | Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073 |
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| Abstract: | The reacting flowfield in LO2/LH2 rocket engine nozzle is computed by using time-dependent semi-implicit difference scheme. An 6-species, 8-step chemistry model is adopted for LO2-LH2reactions. The distributions of flow parameters and mass fraction of products are presented. The computations indicate that the numerical instability is overcome by semi-implicit scheme. |
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| Keywords: | Hydrogen oxygen engine Engine nozzle Nozzle gas flow Reacting flow Numerical simulation |
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