叶端加不同小翼对Krain离心叶轮气动性能影响的数值研究  

Numerical Investigation on the Effect of Blade Tip Winglets on the Aerodynamic Performance of Krain Centrifugal Impeller

作　　者：陈亚莉 孙中国[1] 唐永洪[1] 赵阳[1] CHEN Yali;SUN Zhongguo;TANG Yonghong;ZHAO Yang(School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]西安交通大学能源与动力工程学院

出　　处：《西安交通大学学报》2019年第11期49-55,共7页Journal of Xi'an Jiaotong University

基　　金：国家自然科学基金资助项目(51576154)

摘　　要：为了控制离心压气机叶顶泄漏流,以压比为4.7的Krain低速叶轮为研究对象,将叶尖小翼技术应用到离心压气机中,采用数值模拟对其性能进行分析研究。对3组不同间隙加装不同宽度的小翼,分析了小翼在不同间隙下对于压气机性能及失速裕度的影响,以及不同宽度的小翼对于叶顶泄漏量、泄漏涡结构及轨迹的影响。结果表明:小翼结构可提升压气机的失速裕度,且小间隙下小翼结构对失速裕度的提升效果显著,其中1.0倍宽度小翼的失速裕度增加了8.73%;小翼结构可有效减少叶顶泄漏量,在叶片靠近前缘或尾缘位置加装小翼改善效果显著,泄漏量与小翼宽度成反比关系;小翼结构使得泄漏涡运行轨迹向压力面移动,形成泄漏涡的位置更加远离前缘,泄漏涡强度减弱。To control the tip leakage flow of centrifugal compressor,a Krain low-speed impeller with the pressure ratio of 4.7 was taken as the research object.The tip winglet was applied to centrifugal compressor,and its performance was analyzed by numerical simulation.For three groups of blade tip winglets with different widths installed in different clearances,the effects of blade tip winglet on compressor performance and stall margin,as well as the effects of blade tip winglet on tip leakage,leakage vortex structure and trajectory,were analyzed.The results show that blade tip winglet structure can improve the stall margin of compressor,and the effect of blade tip winglet structure on stall margin is more obvious in small clearances.The stall margin of the winglet with 1.0 time of width is increased by 8.73%.The blade tip winglet can effectively reduce tip leakage,the effect of adding blade tip winglet near the leading edge or trailing edge of the blade is more obvious,and the leakage is inversely proportional to the width of the blade tip winglet.The blade tip winglet makes the trajectory of the leakage vortices move to the pressure surface,the formation position of the leakage vortices is farther away from the leading edge,and the strength of the leakage vortices is weakened.

关 键 词：离心压气机 叶尖小翼 失速裕度 叶顶泄漏 泄漏涡轨迹 

分 类 号：TK269[动力工程及工程热物理—动力机械及工程]