深宽比对氢氧推力室冷却通道传热特性的影响  

Effects on the Heat Transfer Characteristics of Aspect Ratio in Hydrogen Oxygen Thrust Chamber Cooling Channel

作　　者：王珏[1] 王仙[2] 王召[2] 许晓勇[2] Wang Jue;Wang Xian;Wang Zhao;Xu Xiao-yong(China Academy of Launch Vehicle Technology,Beijing,100076;Beijing Aerospace Propulsion Institute,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京航天动力研究所,北京100076

出　　处：《导弹与航天运载技术》2021年第5期1-6,共6页Missiles and Space Vehicles

摘　　要：为了研究液氢冷却的不同深宽比冷却通道结构的传热特性,设计了深宽比分别为15、9.6、6.7和3的4种冷却通道沿圆周均布的分区并联组合式传热试验装置,采取了肋条测温模块以测量肋条不同深度的温度分布,开展了不同室压和混合比的气氢与液氧燃烧环境下液氢的传热特性试验。试验室压为6~7.4MPa,混合比为5.5~7.2。试验结果表明:高深宽比冷却通道换热面积增大,肋条效应更高,换热能力增强;深宽比越大肋条温度分层现象越明显,肋温沿径向逐渐增加;随着冷却通道深宽比增加,冷却剂温升逐渐增加,传热效果增强,但冷却剂流阻先减小后增大。In order to study the heat transfer characteristics of different aspect ratio cooling channel structures for liquid hydrogen cooling in hydrogen oxygen thrust chamber,a combined heat transfer test device with partition and parallel connection which has four cooling channels distributed uniformly along the circumference with aspect ratio of 15,9.6,6.7 and 3 is designed.The wall temperature measurement module is used to measure the temperature distribution at different depths of the wall structure.Experiment on heat transfer characteristics of liquid hydrogen under different chamber pressure and mixture ratios is carried out.The experiment chamber pressure is 6~7.4 MPa,the mixture ratio is 5.5~7.2.The test result show that with the increase of aspect ratio cooling channel,heat transfer area and rib effect of wall structure is higher,the heat transfer ability is enhanced;the higher the aspect ratio,the more obvious the temperature stratification,the wall structure temperature increases along the radial direction.With the increase of the aspect ratio of the cooling channel,the coolant temperature increase gradually and the heat transfer is enhanced,but the coolant flow resistance decreases first and then increase.

关 键 词：氢氧推力室 冷却通道 深宽比 传热特性 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]