串列叶片技术可以突破常规压气机叶片的负荷极限，因此成为下一代高负荷压气机设计技术的研究热点。为了拓展串列叶片的使用范围，采用数值模拟的方法对跨声速串列转子叶型（来流马赫数1.2）流动特性及前排叶片尾迹发展演化规律展开研究。得出结论：全工况范围内，前排叶片总压损失占比超过50%，前排叶片激波系结构的优化设计是影响串列叶型性能的关键因素；随着出口背压提高，前排叶片尾迹厚度先增加后减小，导致尾迹厚度不同的根本原因是流出前排叶片通道时尾迹的初始速度亏损不同，后排叶片通道的扩压对初始速度亏损有进一步的放大作用。

Tandem blade technology can break through the load limit of conventional compressor blades,so it has become a research hotspot of the next generation high load compressor design technology.In order to expand the application range of tandem blades,the flow characteristics of transonic tandem rotor blade profile with incoming Mach number of 1.2 and the development and evolution law of front row of blade wake are studied by numerical simulation.The main conclusions are as follows: in the whole range of working conditions,total pressure loss of front row of blades accounts for more than 50%,the optimization design of the shock wave system structure of the front row of blade is the key factor affecting the performance of the tandem blade profile; with the increase of the outlet back pressure,the wake thickness of the front row of blade first increases and then decreases.The primary cause of the different wake thickness is the different initial velocity losses of the wake when flowing out of the front row of blade passage,and the diffusion of the rear row of blade passage can further amplify the initial velocity loss.

V232.4

国家科技重大专项（J2019-Ⅱ-0003-0023）