中弧线角度分布对跨音叶栅特性影响研究

Effects of Metal Angle Distribution of Mean Camber Line on Aerodynamic Characteristics of Transonic Cascade

中弧线角度分布形式对压气机叶片表面等熵马赫数分布具有重要的影响。为了对比不同压气机叶型的流动特征,采用数值模拟和平面叶栅试验相结合,对两种中弧线角度分布形式的跨音叶型在不同来流工况下的气动特性展开了详细研究。结果表明:在设计点,前加载配合均匀加载的中弧线角度分布叶型能够消除叶片吸力面的局部超音区,与前加载的中弧线角度分布叶型相比,叶片表面等熵马赫数分布更加饱满。其次,前加载配合均匀加载叶型能够推迟叶片吸力面的涡层失稳,减弱了吸力面分离涡与端壁分离涡的耦合作用,进而改善了端区的流动状况,截面平均总压损失系数降低了8.2%。最后,对非设计工况下两种中弧线角度分布的气动特性进行了分析,随着来流马赫数的降低,两种中弧线角度分布叶型的损失差异逐渐减小,均具有较优的气动性能。来流速度对叶片表面等熵马赫数、损失分布和分离面形状特征影响较小,仅影响叶片表面等熵马赫数和损失数值大小。

The metal angle distribution of mean camber line has an important effect on the isentropic mach number distribution of compressor blade surface.In order to compare the flow characteristics of different compressor blade profiles,the aerodynamic characteristics of two transonic blade with different metal angle distribution under different inflow conditions are numerically and experimentally studied.The results show that:At the design point,compared with the front-loaded blade,the metal angle distribution blade with front loading and uniform loading has a fuller isentropic Mach number distribution on the blade surface,which can eliminate the local supersonic zone.Secondly,this kind of blade delays the instability position of the vortex layer on the suction surface,and weakens the coupling of the suction separation vortex and the end wall separation vortex.The corner separation is suppressed,and the flow in the corner area is improved.The average total pressure loss coefficient is reduced by 8.2%.Finally,the aerodynamic characteristics of the cascade under off-design conditions are analyzed.With the decrease of the inflow Mach number,the difference of the loss of the two metal anger distribution blades gradually decreases,and both have good aerodynamic performance.