This paper presents a method for the computer aided design of the transonic turbine blade profile shaping and aero thermodynamic analysis.
A new technique of “Computational Geometry” was developed for blade flow path shaping. An improved method of “Streamline Curvature” for cascade analysis is used for blade-to-blade stream surface analysis.
Using above method, a high-loaded turbine cascade with anti-convex suction surface near the trailing edge has been successfully designed, and appreciable supersonic performance was achieved through wind tunnel test.
This method has been included in our “Turbine Blade Computer Aided Design System (GTCAD)” as one of the core modules.