高亚声速时叶尖小翼对压气机叶栅泄漏流动的影响  

Effect of tip winglet on the leakage flow of compressor cascade at high subsonic speed

作　　者：吴宛洋 钟兢军 WU Wanyang;ZHONG Jingjun(Merchant Marine College, Shanghai Maritime University, Shanghai 201306, China)

机构地区：[1]上海海事大学商船学院,上海201306

出　　处：《国防科技大学学报》2022年第2期162-178,共17页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(51906134,51406002)。

摘　　要：为了探索跨声速来流条件时,不同安装位置、不同宽度的叶尖小翼对压气机叶栅气动特性的影响,对Ma=0.8时包括原型叶栅在内的7种扩压叶栅的流场进行了数值研究。结果表明:在多种因素的共同影响下,不同来流冲角的吸力面叶尖小翼在流场中都为负效果,增加了流场复杂性;压力面叶尖小翼则改善了泄漏流动,减小了流动损失。两种安装位置的叶尖小翼对流场的影响效果都与其宽度成正比。叶尖小翼对流场的干扰或改善效果在正冲角工况下都更为明显。与原型工况相比,在正6°冲角工况时可以观察到两种叶尖小翼的效果最明显,宽度为原型叶片叶顶宽度2.0倍的吸力面叶尖小翼带来4.17%的流场损失,宽度为原型叶片叶顶宽度2.0倍的压力面叶尖小翼则伴随着10.15%的改善效果。To explore effects of different installation locations and different widths of tip winglets on the aerodynamic characteristics of compressor cascades under the condition of transonic incoming flow,the flow fields of seven diffused cascades including the prototype cascade were numerically studied at Ma=0.8.The results show that under the combined influence of various factors,the suction surface tip winglets with different incoming flow attack angles have negative effects in the flow field,and increase the complexity of the flow field.Meanwhile,the pressure surface tip winglets improve the leakage flow and reduce the flow loss.The effect of the tip winglet on the flow field is proportional to its width in both installation positions.The interference or improvement effect of the tip winglet on the flow field is more obvious at positive angle of incidence.Compared with the normal condition,the most obvious effects of the two types of tip winglets can be obtained under the condition of positive 6°.The suction surface tip winglet with a width of 2.0 times of the original width causes 4.17%flow field loss,while the pressure surface tip winglet whose width is 2.0 times of the original width is accompanied by an improvement effect of 10.15%.

关 键 词：压气机叶栅 亚声速 吸力面叶尖小翼 压力面叶尖小翼 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]