旋转盘腔轴向通流的压降和温升数值研究  

Numerical Study on Pressure Drop and Temperature Rise of an Axial Throughflow Passing Through Rotating Cavity

作　　者：高齐宏 张靖周[1] 谭晓茗[1] GAO Qi-hong;ZHANG Jing-zhou;TAN Xiao-ming(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2021年第9期2062-2070,共9页Journal of Propulsion Technology

基　　金：国家科技重大专项(2017-lll-0011-0037)。

摘　　要：为获得旋转雷诺数对盘腔轴向通流温升和压降的影响,对轴向通流雷诺数Re_(x)恒定为1.0×10^(5),旋转雷诺数Re_(ω)=0~5.31×10^(6)、绝热边界下的流动进行了数值模拟,从流场特征、盘面绝热温升以及轴向通流压降和温升等三个方面进行了分析。研究表明,旋转雷诺数对于盘腔内部和轴向通流的流动均具有显著影响;尽管是绝热盘面,但是由于高速旋转的黏性耗散作用引发盘腔内气流的温升,由温度差引起的浮升力对于盘腔内流动和盘面温度分布的影响也是不可忽略的;随旋转雷诺数增大,轴向通流出口温度相对进口温度的温升急剧增大,在旋转雷诺数<2.5×10^(6)时,轴向通流相对温升系数在0.01以内,当旋转雷诺数>4.5×10^(6)时,轴向通流相对温升系数达到0.04以上。To demonstrate the effects of rotational Reynolds number(Reω)on the pressure drop and temperature rise of an axial throughflow passing through rotating cavity,a series of numerical simulations were performed under a fixed axial throughflow Reynolds number Re_(x)=1.0×10^(5),rotational Reynolds number between 0 and 5.31×10^(6) in adiabatic thermal boundary condition.The detailed flow fields,the adiabatic temperature rise on rotating disks,as well as the pressure drop and temperature rise of an axial throughflow were analyzed.The results show that the rotational Reynolds number affects the flow fields significantly,both inside the rotating cavity and inside the axial throughflow path.Although the disk is thermally adiabatic,the centrifugal-buoyancy force caused by temperature rise is not to be ignored due to the viscous dissipation effect,which affects the flow instable and temperature distribution.As the rotational Reynolds number increases,the absolute temperature rise with respect to the axial throughflow inlet increased rapidly.When the rotational Reynolds number is less than 2.5×10^(6),the relevant temperature-rise coefficient of axial throughflow is generally less than 0.01.When the rotational Reynolds number is greater than 4.5×10^(6),the relevant temperature-rise coefficient of axial throughflow reaches up to 0.04.

关 键 词：轴向通流 旋转盘腔 压降 温升 数值模拟 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]