针对跨声速压气机叶片内复杂的三维流动，采用自行开发的三维CFD程序对跨音速轴流压气机NASA Rotor 37流场进行数值模拟，对比分析了L-F（LaxFriedrichs）、StegerWarming及Van Leer 3种通矢量分裂格式和AUSMDV混合格式在跨声速叶轮流场数值计算时的格式效应。研究表明：与其他格式相比，AUSMDV在设计工况下的计算结果与实验误差最小，对激波和叶顶间隙泄漏的捕捉能力最强，Van Leer格式次之；StegerWarming格式在计算过程中收敛性最好。

Aiming at the complex threedimensional flow in transonic compressor blades,a selfdeveloped threedimensional computational fluid dynamics (CFD) program was used to simulate the flow field of transonic axial compressor NASA rotor 37 numerically.This paper compared and analyzed three fluxvector splitting schemes,such as LAXFriedrichs(L-F),StegerWarming and Van Leer,as well as mixed AUSMDV scheme in the aspect of scheme effects in numerical calculation of transonic impeller flow field.Research shows that compared with other schemes,AUSMDV has the smallest error between calculation and experiment results and the strongest ability to capture the shock wave and tip clearance leakage under the design condition,followed by Van Leer scheme;StegerWarming scheme has the best convergence in the calculation process.

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