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阐述了一种以有限体积的时间推进方法为基础求解跨声速压气机叶栅设计的反问题方法。应用这一技术设计叶型，规定叶片表面无量纲目标速度分布，通过比较目标速度分布和计算获得的速度分布来修改叶片压力面和吸力面的坐标，最终获得要求的叶片形状。计算程序使用分布体力方法模拟粘性，用局部时间步长和多重网格方法加速收敛。还介绍了这种方法求解的基本方程系统，并给出了采用这种方法设计的无激波超临界跨声速压气机叶栅的设计结果。
A method to solve the inverse problem of transonic compressor cascade design based on time-propulsion method with finite volume is presented. Applying this technique, the leaf shape is designed to specify the dimensionless target velocity distribution on the blade surface. The target pressure distribution and the calculated velocity distribution are used to modify the coordinate of the blade’s pressure surface and suction surface. Finally, the required blade shape is obtained. The computational program simulates the viscosity using a distributed physical approach, accelerating convergence with local time steps and multiple grid methods. The basic equations system solved by this method is also introduced. The design results of non-shock supercritical transonic compressor cascade designed by this method are also given.