一种求解涡轮平面叶栅的跨音松驰法

一、引　　言跨音松驰法是七十年代初发展的一种新方法。文献 1 ]是一篇关于跨音松驰法的奠基性文章 ,文章提出了求解小扰动势方程的混合差分格式。文献 2 ]发展了求解全位势方程的旋转混合差分格式。近年来 ,求解跨音全位势方程的方法有了更全面的发展 4、5]。作者于 80年发展了一种求解大弯度二维叶栅的跨音松驰法3] 。本文将该法推广到求解涡轮平面叶栅跨音带激波流场 ,直接求解全位势方程 ,进一步提高边界区差分格式的精度 ,并注意初场的给法。本法具有节约机时和内存的优点。数值算例表明 ,对于头部不大的涡轮平面叶栅 ,应用本方法…

A RELAXATION METHOD FOR TRANSONIC POTENTIAL FLOWS THROUGH 2-D CASCADE WITH LARGE CAMBER ANGLE

A new trnsonic relaxation method is presented which can be used for computation of transonic,potential flows through two-dimensional cascade with large camber angle.A non-orthogonal mesh system composed of streamlines and straight lines parallel to y-axis is employed here.The governing equation expressed by the streamline coordinate system is solved in physical plane.Because of the streamline coordiate system,the governing equation is greatly simplified and the formulation of the finite difference scheme is also made correctly and easily.In the case of the cascade with large camber angle (especially for turbine) direct formulation of difference scheme from full-potential equation (instead of perturbation-potential equation) is suggested. The numerical experimentations show that both the convergence and the stability of the finite difference scheme proposed here are satisfactory.The compuation results with acceptable accuracy can be obtained after 60 to 90 relaxation steps.The numerical examples also show that the results are in good agreement with experimental data and analytical solution (for Hobson-airfoil).