基于氦氙工质的预旋系统流动与温降特性数值研究  

Numerical Study on Flow Characteristics and Tempreture Reduction of Pre-Swirl System based on Helium-Xenon Working Fluid

作　　者：彭鸿博[1] 刘志宏 姜浩然 张宗卫[1] PENG Hong-bo;LIU Zhi-hong;JIANG Hao-ran;ZHANG Zong-wei(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin,China,Post Code:300300;Tianjin Zhenxing Chemical Co.Ltd.,Tianjin,China,Post Code:300300)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]天津市振兴化工有限公司,天津300300

出　　处：《热能动力工程》2020年第9期29-35,64,共8页Journal of Engineering for Thermal Energy and Power

基　　金：上海航天科技创新基金(SAST2018-017)。

摘　　要：新型空间核动力航天器以氦氙作为冷却工质对涡轮组件进行冷却。为了研究氦氙工质在预旋系统的流动与温降特性,在旋转雷诺数为1.14×10~6~3.43×10~6条件下对3种不同喷嘴结构的预旋系统模型进行了数值模拟。分析了直孔型喷嘴的不同喷嘴角度对盘腔流动与温降特性的影响。进一步优化喷嘴结构,对比了直孔型扩口型与新型叶型孔式喷嘴预旋系统的流动与温降特性,并分析了旋转雷诺数对系统流动情况与温降效果的影响。结果表明:随着喷嘴角度的增大,系统质量流量增大,温降减小;3种喷嘴结构下的预旋系统质量流量均随旋转雷诺数的增大而增大,系统温降随着旋转雷诺数的增大而减小;叶型喷嘴预旋系统的质量流量和温降分别比直孔型喷嘴增大5.1%和44.6%,比扩口型喷嘴增大0.46%和12.6%。The new space nuclear-powered spacecraft uses the helium-xenon as the coolant to cool the turbine assembly.In order to study the flow characteristics and temperature reduction of the helium-xenon in the pre-swirl system,the pre-swirl model of three different nozzle structures was numerically simulated at the rotational Reynolds number ranging from 1.14×106 to 3.43×106.The effects of different nozzle angles of simple drilled hole on the flow characteristics and temperature reduction of the disk cavity were studied;and the nozzle structure was optimized.The flow characteristics and temperature reduction of the simple drilled hole,aerodynamic hole and vane shaped hole(VSH)pre-swirl system were compared,and the influence of the rotational Reynolds number on the flow and temperature drop of the system were analyzed as well.The results show that with the increase of the pre-swirl nozzle angle,the mass flow increases,and the temperature drop decreases.With the increase of the rotating Reynolds number,the mass flow of the pre-swirl system of the three nozzle structures increases,and the temperature drop decreases.The mass flow and temperature drop of the VSH nozzle pre-swirl system are 5.1%and 44.6%larger than those of the simple drilled nozzle,respectively,0.46%and 12.6%larger than those of the aerodynamic nozzle.

关 键 词：氦氙 预旋系统 温降 旋转雷诺数 喷嘴结构 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]