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不同去旋角度进气共转盘腔内流动与换热研究
引用本文:杨守辉,王锁芳.不同去旋角度进气共转盘腔内流动与换热研究[J].航空发动机,2011,37(6):17-20.
作者姓名:杨守辉  王锁芳
作者单位:南京航空航天大学能源与动力学院,南京,210016
摘    要:以带有去旋喷嘴的共转盘腔为研究对象,运用RNG k-ε湍流模型,分别对3种喷嘴角度(90°、60°、30°)的3维模型进行了数值计算,揭示了去旋角度对盘腔内气体切向速度、盘腔内压降和转盘表面换热的影响规律。研究结果表明:随着去旋角度的减小,盘腔内气体的切向速度减小,盘腔内压降减小,转盘表面的局部努赛尔数Nur增大。

关 键 词:共转盘腔  去旋角度  流动  数值计算  航空发动机

Investigation on Flow and Heat Transfer inside Co-rotating Disc Cavity with Different De-swirl Angle
Authors:YANG Shou-hui  WANG Suo-fang
Institution:(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
Abstract:The 3D numerical simulation of the co-rotating disc cavity with the de-swirl nozzles was carried by the RNG k-ε turbulence model with three kinds of de-swirl angles(90°,60°,and 30°).The influence of the de-swirl angle on the tangential velocity,the pressure loss in the disc cavity and the heat transfer of the rotational disc is discoverd.The results show that as the de-swirl angle reduces,the flow tangential velocity in the disc cavity decreases,the pressure loss in the disc cavity reduces,the local Nur number of the rotational disc surface increases.
Keywords:co-rotating cavity  de-swirl angle  flow  numerical calculation  aeroengine
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