| 三组元喷嘴结构参数对混合腔中两相流的影响 |
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| 引用本文： | 田章福,李清廉,沈赤兵,周进,王振国.三组元喷嘴结构参数对混合腔中两相流的影响[J].推进技术,2002,23(4):276-279. |
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| 作者姓名： | 田章福 李清廉 沈赤兵 周进 王振国 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,湖南,长沙,410073 |
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| 基金项目： | 国家“八六三”基金资助项目 (86 3 2 3 4 8) |
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| 摘 要： | 进行了三组元喷嘴混合腔冷态试验 ,研究了喷嘴结构参数对喷嘴混合腔中气液两相流流量特性的影响规律。结果表明 :混合腔中两相流流量系数是气液质量比的函数 ,气液比变化时 ,两相流流量系数变化不大(0 6 8<μm<0 82 )。两相流流量系数随着混合腔出口角度、内外喷嘴缩进长度、混合腔长度和混合腔进气孔位置到混合腔出口距离的增加而减小
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| 关 键 词： | 结构参数 影响 液体推进剂火箭发动机 三元推进剂 二相流 喷嘴 流量系数 流动特性 |
| 文章编号： | 1001-4055(2002)04-0276-04 |
| 修稿时间： | 2001年8月7日 |
Effection of structural parameters of tripropellant injector on twophase flow in the mixer |
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| TIAN Zhang fu,LI Qing lian,SHEN Chi bing,ZHOU Jin and WANG Zhen guo.Effection of structural parameters of tripropellant injector on twophase flow in the mixer[J].Journal of Propulsion Technology,2002,23(4):276-279. |
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| Authors: | TIAN Zhang fu LI Qing lian SHEN Chi bing ZHOU Jin and WANG Zhen guo |
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| Institution: | Inst of Aerospace and Material Engineering, National Univ of Defense Technology, Changsha 410073, China;Inst of Aerospace and Material Engineering, National Univ of Defense Technology, Changsha 410073, China;Inst of Aerospace and Material Engineering, National Univ of Defense Technology, Changsha 410073, China;Inst of Aerospace and Material Engineering, National Univ of Defense Technology, Changsha 410073, China;Inst of Aerospace and Material Engineering, National Univ of Defense Technology, Changsha 410073, China |
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| Abstract: | The cold flow injection test about tripropellant injector mixer was conducted and discharge characteristics was discussed Some conclusion can be drawn from the discharge characteristics experiment First,the discharge coefficient of two phase flux in the mixer depends on the ratio of gas mass to liquid mass But this dependence was weak Second,the discharge coefficient of two phase flux decreased with the increasing of the mixer transition angle,the recess length of internal and outer injector,the mixer length,and the distance between the inlet or fice for gas and the mixer outlet |
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| Keywords: | Liquid propellant rocket engine Tripropellant Twophase flow Injector Flow coefficient Flow characteristic |
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