Application of numerical simulation for turbomachinery blade design

The numerical method for prediction plane steady potential flow of ideal gas through transonic turbine cascade is applied to resolve combination of direct and inverse tasks with purpose of blade design. The method of analytic expansions in local polar coordinate system is used to analyse the flow field near stagnation point at the leading edge of blade. The influence of the expansion constants and the trailing edge form is determined on the gas flow through turbine cascade. The new blade surface is designed with purpose to provide the required velocities by resolving the local inverse tasks.