Aerodynamic Design of Turbomachinery Cascades Using an Enhanced Time-Marching Finite Volume Method

摘要

The paper presents an aerodynamic design method for turbomachinery cascades of blades. The prescribed conditions are the aerodynamic blade load and the blade thickness distributions. An iterative procedure was implemented, based on the solution of the Euler equations, to seek the blade geometry that provides the specified design conditions. A central finite-volume explicit time-marching scheme is used to solve the Euler equations in two-dimensional flow. The numerical scheme uses an adaptive nonlinear artificial dissipation term based on the limiter theory. Starting with the results from the flow analysis through an initially guessed cascade geometry, the design code modifies the blade camber line by relating the axial distribution of the mean tangential velocity component through the cascade with the blade camber-line angle. The procedure allows the iterative calculation of the blade geometry that gives the desired aerodynamic blade load distribution. The accuracy of the method has been verified by calculating a parabolic cascade and by redesigning a transonic compressor cascade.