连续性和非连续性鼓包对跨声速压气机转子气动性能的影响

Influence of continuous and individual bumps on aerodynamic performance of transonic compressor rotor

为研究鼓包对跨声速压气机转子气动性能的影响,以NASA Rotor 37为研究对象,在其吸力面上布置展向连续性和非连续性鼓包,并采用数值模拟方法研究原型转子和鼓包转子在变转速工况下的流场结构和气动性能。结果表明:在设计转速和110%设计转速下,连续性鼓包对叶顶附近的激波控制效果较好,可以对激波前气体进行预压缩,从而降低激波前后的逆压梯度,减弱激波强度,进而减小激波相关损失;在设计转速最高效率工况下,非连续性鼓包转子总压比提升0.236%、效率提升0.309%,连续性鼓包转子总压比提升0.285%、效率提升0.454%;在50%、60%和90%设计转速下,鼓包并没有起到明显的有益效果。

In order to study the influence of bumps on aerody⁃namic performance of the transonic compressor rotor,NASA Rotor 37 was taken as the research object with the spanwise continuous and individual bumps configured on the suction surface,the flow field structure and aerodynamic performance of the prototype rotor and the bump rotors under variable speed conditions were studied by numerical simulation.Re⁃sults show that at the design speed and 110%design speed,the continuous bump has better control effect on the shock wave near the blade tip,the gas before the shock wave can be pre⁃compressed to reduce the reverse pressure gradient before and after the shock wave,weaken the shock wave intensity,and thereby reducing the losses associated with shock wave.Under the peak efficiency operating condition of the designed speed,the total pressure ratio of the rotor with the spanwise individual bump is increased by 0.236%,and the efficiency is increased by 0.309%.The total pressure ratio of the rotor with the continuous bump is increased by 0.285%,and the effi⁃ciency is increased by 0.454%.At 50%,60%and 90%of design speed,the bumps has no beneficial effect on the aero⁃dynamic performance of the rotor.