Multi-Row Turbomachinery Aerodynamic Design Optimization by an Efficient and Accurate Discrete Adjoint Solver

This paper proposes an approach that combines manual differentiation (MD) and automatic (AD) to develop efficient accurate multi-row discrete adjoint solver. In this approach, the structures of codes generated using AD tool are first analyzed. Then, AD-generated manually adjusted reduce memory CPU time consumption. adjustment is performed by replacing automatically low-efficient differentiated with developed ones. To demonstrate effectiveness proposed single-stage transonic compressor–NASA Stage 35 1.5-stage Aachen turbine–are used. The solution information exchange at a rotor-stator/stator-rotor interface achieved conservative, non-reflective, robust mixing plane method. results show solver hybrid more economical in computational cost than purely has higher sensitivity accuracy constant eddy viscosity (CEV) assumption. Moreover, turbomachinery design optimizations can be efficiently differentiation.