Based on the three-dimensional design concept

a design method of low pressure turbine nozzle blade in wide angle diffused meridian passage was presented. The result indicates that smaller inner wall angle of divergence and bigger outer wall angle of divergence should be used to keep the flow stability near inner wall when design meridian passage

meanwhile make the vane lean to pressure side to increase the reaction near inner wall and keep the lean direction near outer wall to decrease the trend of passage vortex moving to mean radius for decreasing or eliminating the possibility of flow separation and increasing flow stability near the outer wall

and so decreasing the loss. This method has been applied and verified on a real aero-engine low pressure turbine.