周向非均匀叶尖间隙对某转子旋转不稳定现象影响的数值模拟  

Numerical simulation of effect of circumferential non-uniform tip clearance on rotating instability in a rotor

作　　者：姜超 王志宽 乐贵高[2] 胡骏[3] JIANG Chao;WANG Zhikuan;LE Guigao;HU Jun(Beijing System Design Institute of Electro-Mechanic Engineering,The Fourth Academy,China Aerospace Science and Industry Corporation Limited,Beijing 100854,China;School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国航天科工集团有限公司第四研究院北京机电工程总体设计部,北京100854 [2]南京理工大学机械工程学院,南京210094 [3]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2024年第12期327-342,共16页Journal of Aerospace Power

摘　　要：为了研究非均匀叶尖间隙压气机中的旋转不稳定流动现象,以Rotor 67为研究对象,采用全环非定常数值计算方法,对3种偏心度转子在不同的工况下分别进行了详细的计算,获得了3种偏心度情况下的特性线,得到了3种偏心度情况下的流场结果。数值计算结果表明:当平均叶尖间隙一定时,偏心度对未失速部分的总压比特性线和效率曲线几乎没有影响,而对失速边界影响明显;同心和偏心转子叶尖区域的扰动具有统一的物理结构,其在机匣上表现为移动的低压团,在三维空间上是起始于叶片吸力面,终止于机匣上的三维径向涡,与叶尖间隙泄漏涡并无直接关系;偏心度只是改变了扰动的周向分布规律,并不改变扰动的物理本质。In order to study the flow phenomenon of rotating instability in compressors with nonuniform tip clearance,the Rotor 67 was taken as the research object,and the detailed flow field results and the characteristic lines of three kinds of eccentric rotor were calculated utilizing the three-dimensional full annulus unsteady computational fluid dynamics.The numerical calculation results showed that when the average tip clearance was constant,the eccentricity had little effect on the characteristic line of the nonstall part,but had a significant effect on the stall boundary.The disturbances in the tip region of concentric and eccentric rotors had a unified physical structure.These disturbances presented as moving low-pressure spots on the shroud,which were three-dimensional radial vortices starting from the suction surface of the blade and ending in the shroud,and had no direct relationship with the tip clearance leakage vortex.The eccentricity only changed the circumferential distribution pattern of the disturbances,and did not change the physical nature of the perturbation.

关 键 词：转子 周向非均匀叶尖间隙 叶尖间隙泄漏流 旋转不稳定 低压团 径向涡 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]