Abstract: In order to reduce the shock wave loss of transonic cascade，and improve the total pressure recovery coefficient，a cascade design program was developed based on the two dimensional viscous inverse design method theories. The strength of shock wave was reduced by adjusting the pressure load distribution of blade surface and keeping blade total load unchanged. The DFVLR L030-4 cascade experiment data was used to validate the calculation results. Then，a new blade profile was designed by using the modified load distribution of L030-4 based on the inverse design program. A blade surface load parameterization method was also developed to modify the load distribution. The numerical research shows better performance of cascade is achieved in terms of cascade outlet Mach number，total pressure loss and shock wave loss，which demonstrates the effectiveness of this method.

Key words: Inverse method；Shock wave loss control；Load distribution；Permeable boundary condition

摘要： 为了降低跨声速叶栅通道中的激波损失，提高叶栅出口的总压恢复系数，以二维粘性反问题设计方法理论为基础，发展了二维叶栅反问题设计方法，通过调整叶片表面沿轴向的载荷分布，在保持叶片总载荷不变的同时，达到降低叶栅槽道中的激波强度，减少激波损失的目的。为验证方法的正确性，首先运用德国宇航中心L030-4叶栅实验数据与计算结果进行对比，在此基础上对叶片载荷进行分析，并提出了一种叶片表面载荷分布参数化方法，运用该方法修改叶片表面载荷分布后通过反问题设计方法得到新的叶型。结果表明，通过修改叶片表面载荷分布，运用二维反问题设计方法得到的新叶型激波强度明显降低，叶栅出口总压恢复系数以及马赫数较原型均有增加，叶栅气动性能明显提高。

关键词: 反问题设计方法；激波损失控制；载荷分布；渗透边界条件