Method of Analysis for Compressible Flow Past Arbitrary Turbomachine Blades on General Surface of Revolution.

摘要

A method of obtaining the flow of a nonviscous compressible fluid past arbitrary compressor or turbine blades between two neighboring surfaces of revolution is presented. The equations of continuity and motion obtained for such flow are combined into a nonlinear second- order differential equation in terms of a stream function defined for such flow. Numerical solution by the use of differentiation coefficients for unequally spaced grid points is suggested. Means for satisfying the boundary conditions outside the channel and solutions by the relaxation method with manual computation and by a matrix method with a large-scale digital computing machine are described.