Blade shape optimization of multistage turbomachinery by adjoint method

The computational amount of the adjoint method is almost changeless with increase of the number of design variables. Blade aerodynamic shape optimization method for multistage turbomachinery with three dimensional thin layer viscous model was developed by using the adjoint method. It includes the derivation of adjoint equation and its boundary conditions, the sensitivity relationship between the objective function and the design variables. A corresponding aerodynamic shape optimization system was established by combining three dimensional blades parametric method based on Hicks-Henne function with the steepest descent method. The effectiveness of the system was verified by inverse-designed blades of the second row of a 1.5 stage compressor. Then another 1.5 stage supersonic compressor is redesign with entropy as the objective function, its aerodynamic performance was improved.