Towards Unsteady Adjoint Analysis For Turbomachinery Applications

This paper presents a general framework to derive an unsteady discrete adjoint method as part of a gradient-based aerodynamic shape optimization process. The method calculates the gradient of an objective function w.r.t. the design variables of the aerodynamic shape. The formulation of the adjoint equations is introduced within a generic time-dependent optimal design problem. Results are shown that demonstrate the solution of the unsteady adjoint equations for a representative row of nozzle guide vanes of a high pressure turbine

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