基于动态边界的跨声速压气机过渡态载荷研究

针对航空涡轮发动机压气机部件的过渡态，基于动态边界并结合双向流固耦合（FSI）方法模拟了跨声速压气机NASA Rotor 67的过渡态过程，获得了考虑叶片弹性变形的压气机过渡过程特性曲线，研究了叶片气动弹性变形对跨声速压气机加速过程中气动参数、流场激波结构演变过程的影响，分析了加速过程中非定常气动载荷与离心载荷共同作用下的叶片变形特征。结果表明:随转速升高，叶片变形对上半叶高区域的总压比和总温比的影响较显著；加速过程中，叶片变形对通道内激波结构特征及其演变有一定的影响；叶片变形主要集中在上半叶高，以弯曲变形为主导，主要由离心载荷造成，加速过程中叶尖区域的叶型出现反扭现象，从而引起压气机气动性能参数的变化。 

Research on transient load for transonic compressor based on dynamic boundaries

Focusing on the transient state of aviation turbine engines components, a method based on dynamic boundaries and a two-way fluid-structure interaction(FSI) method were used to calculate the acceleration process of the transonic compressor NASA Rotor 67.The curve of the compressor transient process considering the blade deformation was calculated, and the influences of the aeroelastic deformation of the blade on the aerodynamic parameters during the acceleration process and the shock wave structure and evolution process in the flow field were studied.And the deformation distribution of the blade in acceleration process under unsteady aerodynamic load and centrifugal load was also studied.The results showed that: with the increase of the rotational speed, the influence of the blade deformation on the total pressure ratio parameter and the total temperature ratio parameter was more obvious.The structure and evolution of the shock wave in the flow path when considering blade deformation were slightly different with those without blade deformation in the acceleration process of the transonic compressor.The transient load caused the gradual increase of blade deformation during the acceleration process.The blade deformation was mainly concentrated in the upper half of the blade, and mainly caused by centrifugal load, which was dominated by bending deformation, and caused the torsion phenomenon at the leading edge of the tip to cause change of aerodynamic performance.