临界攻角下锯齿尾缘压气机叶片气动特性  

Aerodynamic Characteristics of Serrated Trailing Edge Compressor Blades Under Critical Angle of Attack

作　　者：屈伟 冯和英 王俊娇 杨成浩 QU Wei;FENG Heying;WANG Junjiao;YANG Chenghao(Hunan Provincial Key Laboratory of Mechanical Equipment Health Maintenance,Hunan University of Science and Technology,Xiangtan 411201,China)

机构地区：[1]湖南科技大学机械设备健康维护湖南省重点实验室,湖南湘潭411201

出　　处：《湖南科技大学学报（自然科学版）》2022年第2期88-94,共7页Journal of Hunan University of Science And Technology：Natural Science Edition

基　　金：国家自然科学基金资助项目(51875194)。

摘　　要：基于Smagorinsky亚格子应力模型的大涡模拟,研究不同攻角下某型压气机叶栅的性能变化规律,获得临界攻角.分析临界攻角下不同齿高比(1.0~2.0)的锯齿尾缘叶片的气动特性及锯齿结构抑制流动分离的物理机理.研究表明:当攻角增至临界攻角时,叶栅的升压、扩压能力达到最大值,但此时伴随着流动分离、涡脱落等复杂流动现象,导致流动损失增加;锯齿尾缘结构能够改善叶片吸力面的流动分离,从而有效地减少吸力面边界层的厚度,延缓叶片失速,并能在不影响压气机增压能力的情况下降低损失;综合考虑流动损失及增压、扩压能力,齿高比在1.2左右时锯齿叶片的性能最佳;相较于基准叶片,最佳锯齿叶片的扩压能力基本相同,但是至少可以减少28.1%的流动损失,并提高1.2%的增压能力.Based on Smagorinsky lattice stress model of large eddy simulation,the different performance of a compressor cascade under the angle of attack change law is studied,and the critical angle of attack is obtained.The blade aerodynamic characteristics and sawtooth structure of separation flow mechanism under different gear ratio(1.0~2.0)blade trailing edge is analyzed.The study shows that when the angle of attack reaches the critical angle of attack,cascade reaches the maximum pressure diffusion ability.However,at the moment with the complex flow separation and vortex shedding flow phenomena,it has led to an increased flow loss.Serrated blades can improve flow separation on suction surface,effectively reduce the thickness of suction surface boundary layer,delay the blade stall,and reduce the losses without affecting the compressor’s supercharging capacity.Considering the flow loss and the increased pressure and pressure expansion ability,the sawtooth blade with the tooth height ratio of about 1.2 has the best performance.Compared with the reference blade,the optimal saw blade has the same pressure-expansion ability,but at least the flow loss can be reduced by 28.1%and the boost capacity can be increased by 1.2%.

关 键 词：临界攻角 锯齿尾缘 增压比 流动损失 压气机 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]