摘要
采用叶栅吹风试验与数值模拟相结合的方法,研究了攻角变化对具有较大前缘半径和进口楔角的透平叶栅气动性能的影响,试验测量在出口马赫数为0.8、攻角-61.0°^+4.0°内进行,对应的雷诺数为6.0×105.在试验验证数值方法可靠性的基础上,对叶栅流动损失进行了数值研究,分析了攻角变化对试验叶栅型面损失中吸力面与压力面边界层损失、尾迹损失和端部次流的影响特性.结果表明:当攻角从+4.0°变化到-41.0°时,叶片表面没有发生流动分离,出口截面的总压损失系数变化幅度不超过0.21%;在负攻角很大(-61.0°)时,压力面边界层发生流动分离,型面损失急剧增大;具有较大前缘半径和进口楔角的试验用叶栅表现出良好的变攻角气动性能.
Cascade wind tunnel experiments and numerical simulation were conducted to investigate the influence of attack angle on aerodynamic performance of turbine cascades with large diameter at leading edge and large wedge angle at the inlet,under the conditions that the incidences range from-61.0° to ＋4.0°,at an outlet Mach numbers of 0.80,and a Reynolds number of 6.0×105.The numerical results were verified by experimental data,based on which numerical simulation was performed to study the flow loss of cascade and analyze the effect of attack angle on the profile losses,such as the boundary mixing loss and trailing edge loss on both the suction and pressure side,and on the variation of secondary flow at the end.Results show that when the incidence varies from ＋4.0° to-41.0°,no separated flow will occur on the blade surface,and the coefficient variation of total pressure loss will be less than 0.21% at cascade outlet;whereas when the incidence is of a large negative data（-61.0°）,separated flow will occur on the pressure boundary,and the profile loss will increase significantly.In general,it is shown that the studied cascade behaves good off-design aerodynamic performance due to the large diameter at leading edge and large wedge angle at the inlet.
出处
《动力工程学报》
CAS
CSCD
北大核心
2011年第12期910-915,共6页
Journal of Chinese Society of Power Engineering
关键词
透平叶栅
攻角
气动性能
型面损失
流动损失
turbine cascade
attack angle
aerodynamic performance
profile loss
flow loss
