Adjoint blade aerodynamic optimization

Adjoint Aerodynamic Design Optimization for Multi-stage Turbomachinery Blades

Method Ingredients:

  1. A continuous Adjoint method has been developed based on a 3-D time-marching finite volume RANS solver. This enables the performance gradient sensitivities to be calculated  very efficiently,  particularly for situations with a large number of design variables.
  2. A novel adjoint ‘mixing-plane’ model has been developed. This model makes it possible to carry out the adjoint design optimization in a multi-stage environment.
  3. The optimization approach with the above capabilities has been implemented in a parallel mode, with which a simultaneous multi-point optimization can be conducted.

Adjoint Aerodynamic Design Optimization for Multi-stage Turbomachinery Blades

Adjoint Aerodynamic Design Optimization for Multi-stage Turbomachinery Blades 2

 

Adjoint Method 2

References:

- D. X. Wang and L. He, “Adjoint Aerodynamic Design Optimization for Blades in Multi-Stage Turbomachines: Part I – Methodology and Verification”,  ASME Journal of Turbomachinery, Vol.132, No.2, 021011, 2010.

- D. X. Wang, L. He, Y.S Li and R.G. Wells, “Adjoint Aerodynamic Design Optimization for Blades in Multi-Stage Turbomachines: Part II – Verification and Application”, ASME Journal of Turbomachinery, Vol.132, No.2, 021012,  2010.