摘要
为减小叶型损失,在压气机叶栅叶片表面布置沿流向的对称V形微沟槽,采用数值模拟方法研究了沟槽宽度和顶角、沟槽间隔、沟槽覆盖范围、进口湍流度以及来流马赫数对叶栅气动性能的影响。结果表明,总压损失降低主要由吸力面沟槽产生,合理匹配沟槽几何参数、覆盖范围以及来流条件,可实现较优的减损效果。对吸力面局部带沟槽结构,相同冲角下无间隔沟槽的减损效果优于有间隔沟槽的减损效果,当无间隔沟槽顶角度为60°时减损效果最优;相同沟槽结构的减损效果与冲角相关。来流湍流度增加使得相同冲角下光滑叶片和带沟槽叶片的总压损失增大,相同沟槽结构在同一冲角下的减损效果及最优减损效果对应的冲角受来流湍流度影响。冲角不变时相同沟槽结构的减损效果随来流马赫数增大整体呈下降趋势,最佳减损效果对应的无量纲沟槽宽度和具有减损效果的无量纲沟槽宽度范围不同。当保持沟槽无量纲宽度不变和沟槽其它参数不变时,不同来流马赫数条件下的最佳减损效果及其对应的冲角不同,较低来流马赫数条件下最佳减损效果更突出。微沟槽能够减小壁面平均剪切应力和湍动能,降低湍流边界层损失,同时能够推迟边界层流动分离,使得叶型损失降低。
In order to reduce the profile loss,the streamwise symmetric V-type microsurface riblets are applied on the compressor cascade blade.The numerical method is adopted to study the effects of riblets width and tip angle,riblets spacing,riblets coverage,inlet turbulent intensity and inlet Mach number on the aerodynamic performance of compressor cascade.The results show that the total pressure loss reduction is mainly caused by the riblets on blade suction surface.By properly matching the riblets geometry parameters,riblets coverage position and inlet flow parameters,the optimum total pressure loss reduction can be obtained.For riblets on blade suction surface within partial blade chord range,the loss reduction of riblets without spacing is better than that of riblets with spacing at the same incidence angle.For the riblets without spacing,when the tip angle is 60°the loss reduction is the best.For the same riblets structures,the loss reduction is related with the incidence angle.The increase of inlet turbulent intensity will enlarge the total pressure loss at the same incidence angle for both smooth blade and blade with riblets.For the same riblets structure,the loss reduction at the same incidence angle and the incidence angle corresponding to the optimum loss reduction are related with the inlet turbulent intensity.When the incidence angle is fixed,the loss reduction generally decreases with the increase of inlet Mach number.The dimensionless riblets width corresponding to the optimum loss reduction and the range of riblets dimensionless width with loss reduction are different.When the dimensionless width of riblets and other parameters of riblets are fixed,the optimum loss reduction and its corresponding incidence angle at different inlet Mach numbers are differ ent.The optimum loss reduction at lower Mach number is more obvious.The microsurface riblets can reduce the near wall average shear stress and turbulent kinetic energy,and alleviate the turbulent boundary loss.The boundary flow separation can also be delayed,and the blade profile loss is reduced.
作者
耿少娟
周一帆
李鑫龙
李智慧
GENG Shao-juan;ZHOU Yi-fan;LI Xin-long;LI Zhi-hui(Advanced Gas Turbine Laboratory,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;Key Laboratory of Advanced Energy and Power,Chinese Academy of Sciences,Beijing 100190,China;Innovation Academy for Light-duty Gas Turbine,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)
出处
《机械设计与制造》
北大核心
2024年第7期279-287,294,共10页
Machinery Design & Manufacture
基金
国家重点研发计划(2018YFB1107405)。
关键词
表面微沟槽
边界层损失
湍流度
来流马赫数
压气机叶栅
数值模拟
Microsurface Riblets
Boundary Layer Loss
Turbulent Intensity
Inlet Mach Number
Compressor Cascade
Numerical Simulation
