| 新型液体火箭发动机燃烧不稳定性研究 |
| |
| 引用本文： | 丰松江,聂万胜,郑永斌,何浩波,侯志勇,庄逢辰.新型液体火箭发动机燃烧不稳定性研究[J].工程热物理学报,2010(3). |
| |
| 作者姓名： | 丰松江 聂万胜 郑永斌 何浩波 侯志勇 庄逢辰 |
| |
| 作者单位： | 装备指挥技术学院;国防科技大学; |
| |
| 基金项目： | 国家自然科学基金资助项目(No.50576105) |
| |
| 摘 要： | 应用CFD方法对新型液体火箭发动机燃烧过程进行全尺寸数值模拟。首次有针对性地系统得出了混合比、液氧喷雾初始尺寸分布、缩进区液氧蒸发质量对氢氧火箭发动机燃烧振荡的影响规律,评估了1轮毂3径向喷嘴隔板抑制燃烧振荡的效果,并对氢氧、液氧/甲烷两种火箭发动机的燃烧不稳定性特征进行了对比分析。结果表明:存在某一特定的混合比、喷雾液滴直径、缩进区液氧蒸发质量敏感区间,易导致不稳定燃烧;喷嘴轮毂隔板可很好地抑制燃烧振荡;氢氧、液氧/甲烷燃烧分别以高频和低频压力振荡为主。
|
| 关 键 词： | 氢氧火箭发动机 液氧/甲烷火箭发动机 燃烧不稳定性 数值仿真 |
COMBUSTION INSTABILITY OF NEW-STYLE LIQUID ROCKET ENGINE |
| |
| FENG Song-Jiang NIE Wan-Sheng ZHENG Yong-Bin HE Hao-Bo HOU Zhi-Yong ZHUANG Feng-Chen.COMBUSTION INSTABILITY OF NEW-STYLE LIQUID ROCKET ENGINE[J].Journal of Engineering Thermophysics,2010(3). |
| |
| Authors: | FENG Song-Jiang NIE Wan-Sheng ZHENG Yong-Bin HE Hao-Bo HOU Zhi-Yong ZHUANG Feng-Chen |
| |
| Institution: | 1.The Academy of Equipment Command & Technology;Beijing 101416;China;2.National University of Defense Technology;Changsha 410073;China |
| |
| Abstract: | The combustion process of one full-scale new-style liquid rocket engine was numerically simulated by using CFD methods.The effect rules of O/F equivalence ratio,the LOX spray initial drop size and the evaporation quality at LOX injector recess area on combustion oscillation of LOX/GH_2 engine were studied.The control effect of one-hub-and-three-blade injector baffle on combustion oscillation was investigated.Additionally,the combustion instability characteristic of LOX/GH_2 rocket engine was compared with t... |
| |
| Keywords: | LOX/GH_2 rocket engine LOX/CH_4 rocket engine combustion instability numerical simulation |
| 本文献已被 CNKI 等数据库收录！ |
