摘要
本文采用数值模拟的方法,研究了激波对斜孔情况下超声速气膜冷却的影响。其中主流马赫数为2.44,冷却流马赫数分别考虑1.2, 1.5和1.8三种情况,研究了温度场分布规律及平均冷却效率变化情况。结果发现:在本文计算工况范围中,三种冷却流马赫数工况下平均气膜冷却效率较接近;存在激波入射的情况下的平均气膜冷却效率整体要低于无激波入射工况,并且冷却效率呈现出先急剧下降后又逐渐增大、整体趋势为下降的锯齿状现象。
The present study numerically investigated the influence of shock wave impingement on supersonic film cooling with discrete hole. The effect of shock waves and coolant inlet Mach number on the temperature distribution and average film cooling effectiveness were studied with the main flow Mach number of 2.44 and the coolant flow Mach number of 1.2, 1.5, 1.8. The results showed that： for the three cases of different coolant Mach numbers, the film cooling effectiveness showed little difference; the film cooling effectiveness with shock wave impingement is lower than that of no shock wave condition; with 10 ° shock wave interaction, the film cooling effectiveness decreases sharply and then gradually increased, with the trend of a declining sawtooth waveform.
作者
孙小凯
姜培学
彭威
王捷
SUN Xiao-Kai;JIANG Pei-Xue;PENG Wei;WANG Jie(Institute of Nuclear and New Energy Technology,Tsinghua University,Collaborative Innovation Center for Advanced Nuclear Energy Technology,Key laboratory of Advanced Reactor Engineering and Security of Ministry of Educations,Beijing 100084,China;Key Laboratory of Thermal Science and Power Engineering of Ministry of Educations,Department of Energy and Power Engineering,Tsinghua University,Beijing 100084,China)
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2018年第11期2476-2479,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金青年项目(No.51306099)
国家自然科学创新研究群体项目(No.51621062)
国家科技重大专项项目(No.ZX06901)
关键词
超声速气膜冷却
激波
马赫数
冷却效率
supersonic film cooling
shock wave
Mach number
film cooling effectiveness
