求解跨声速压气机叶栅粘性流动反问题的数值解  

NUMERICAL SOLUATION ON VISCOUS INVERSE PROBLEM FOR TRANSONIC COMPRESSOR CASCADES

作　　者：杨策[1] 老大中 蒋滋康[1] 

机构地区：[1]清华大学热能工程系

出　　处：《推进技术》1999年第4期57-60,共4页Journal of Propulsion Technology

摘　　要：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 new numerical method for solving viscous inverse problem of transonic compressor cascades was developed.The calculation was performed directly on the physical plane by simplified Navier Stokes equations which were solved by time marching,finite volume method.This technique can be used to design the blade profile with prescribed dimensionless velocity distribution at the suction and pressure surface.Depending on comparing the aimed velocity distribution with the calculated velocity distribution,the new blade was obtained by modifying the blade profile shape.The turbulence eddy viscosity was simulated by B L model and region time steps with the multigrid techniques being used in the code in order to accelerate the convergence.Computed results of shock free supercritical cascade were presented

关 键 词：跨声速 压气机 叶栅 粘性流 数值计算 反问题 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程] V231.3