摘要
针对涡轮转子叶片内冷技术,使用TR-PIV(time resolved particle image velocimetry)技术与热线技术同步原位测量了壁面加热条件下旋转通道内边界层速度场和温度场特性。结果显示:旋转数大于0.48时前缘面附近出现了回流现象,并从受力分析的角度给出了解释;回流区一般出现于流场下游、较大密度比、较高旋转数下,可以利用回流区的影响达到增强前缘面换热的目的;得到了旋转条件下无量纲温度型、温度脉动量和努塞尔数的变化规律,可以看出湍流边界层内部的温度场分布在旋转效应的影响下产生了强烈的不对称性,与静止条件下的标准规律相比会产生一定的偏差。
For the turbine rotor blade internal cooling technology,TR-PIV(time resolved particle image velocimetry)and hot wire technology were used to measure the velocity and temperature field of the boundary layer in the rotating channel under wall heating conditions.The results showed that when the rotation number was greater than 0.48,backflow occurred near the leading side,and an explanation was given from the force analysis.The backflow zone generally appeared downstream the flow field at a higher density ratio and a higher rotation number.The backflow effects can be used to achieve the purpose of enhancing the heat transfer of the leading side.The change laws of the dimensionless temperature profiles,temperature fluctuation and Nusselt number under different rotation conditions were obtained.The temperature field distribution inside the turbulent boundary layer produced a strong asymmetry under the rotation effect,generating a certain deviation compared with the standard law under static conditions.
作者
李刚夫
李海旺
由儒全
夏双枝
Ll Gangfu;Ll Haiwang;YOU Ruquan;XIA Shuangzhi(National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics.Aero Engine Research Institute,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;China Poly Group New Era Technology Company Limited,Beijing 100088,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第12期2573-2582,共10页
Journal of Aerospace Power
基金
国家自然科学基金(51906008,51822602)
国家科技重大专项(2017-Ⅲ-0003-0027)。
