Reduction of flow loss in turbo-machinery is significant for improving the performance of turbine blades in design of aviation turbine blade.In this paper,the application of a continuous viscous adjoint equation method to the aerodynamic design optimization of a low aspect-ratio turbine blade to reduce the secondary flow loss through endwall profiles contouring is presented.Firstly,an inverse design case is performed to achieve a given flow turning distribution at the outlet through re-staggering the blade ...