Abstract:

A computer aided design method for transonic turbine aerofoil shaping and thermodynamic analysis is presented. It adopts the technique of "Computational Geometry"developed by authors for blade space shapingi. An improved Streamline Curvature method for cascade analysis, called CASC, is applied to blade to-blade stream surface analysis. Its advantage over the conventional streamline curvature method lies in using oblique computational stations. On the basis of choosing the throat as a basic computational station, all oblique computational stations are generated from input data by circular spline fitting and interpolating.A high-loaded turbine cascade with anti-convex suction surface near the trailing edge has been designed with success by this method. Its appreciable supersonic performance is testified in wind tunnel. This method is comprised in our 'Turbine Blade Computer Aided Design System （GTCAD） as one of core modules.