| 氢喷射温度对氢氧火箭发动机燃烧稳定性的影响 |
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| 引用本文： | 程钰锋,聂万胜,丰松江.氢喷射温度对氢氧火箭发动机燃烧稳定性的影响[J].火箭推进,2009,35(1):27-30. |
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| 作者姓名： | 程钰锋 聂万胜 丰松江 |
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| 作者单位： | 1. 装备指挥技术学院研究生院,北京,101416
2. 装备指挥技术学院,航天装备系,北京,101416 |
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| 摘 要： | 应用CFD方法对氢氧火箭发动机中高频燃烧不稳定性进行了数值模拟，研究分析了不同工况条件下氢喷射温度对燃烧振荡的影响规律，得出了压力振荡频率变化规律及稳定性极限图。结果表明：在一定的氢喷射温度范围内会发生不稳定燃烧，且随着混合比的增大，发生不稳定燃烧的氢喷射温度上限增大；不稳定燃烧振荡主频呈倍频关系，且在氢喷射温度（70K～110K）内，振荡主频最大。
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| 关 键 词： | 氢氧火箭发动机 不稳定燃烧 数值模拟 |
The effect of initial hydrogen temperature on LOX/GH_2 liquid rocket engine combustion instability |
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| Cheng Yufeng,Nie Wansheng,Feng Songjiang.The effect of initial hydrogen temperature on LOX/GH_2 liquid rocket engine combustion instability[J].Journal of Rocket Propulsion,2009,35(1):27-30. |
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| Authors: | Cheng Yufeng Nie Wansheng Feng Songjiang |
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| Institution: | 1 Department of Postgraduate;the Academy of Equipment Command & Technology;Beijing 101416;China;2 Department of Space Equipment;China |
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| Abstract: | The combustion instability in one LOX/GH2 liquid rocket engine was studied by us- ing CFD methods. The effects of initial hydrogen temperature on combustion oscillation at different operational conditions were studied, and the rules of instable pressure frequencies and the combus- tion stability limiting map are developed. Results show that combustion instability will happened at a specific initial hydrogen temperature bound and the upper limit of this initial hydrogen temperature bound will increases as th... |
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| Keywords: | hydrogen-oxygen rocket engine combustion instability numerical simulation |
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