Aerodynamic optimization of the tangential stacking line of a transonic axial flow compressor rotor using genetic algorithm

  • M. AsghariEmail author
  • M. Agha Seyed Mirzabozorg
  • M. Adami
Technical Paper


In this paper, aerodynamic optimization of the tangential stacking line of the NASA Rotor 37 as a transonic axial flow compressor rotor is carried out using computational fluid dynamics and genetic algorithm. To cover a wide range of curves with a minimum number of design parameters, a B-spline curve with three control points at 33, 66 and 100% of the blade span is used to define the blade stacking lines. Firstly, by rotating the tangential position of the control points, different rotors have been created and are simulated using the Navier–Stokes governing equations. Then, using genetic algorithm operators, based on the adiabatic efficiency as an objective function, new blades are created and numerically simulated. This process is repeated to achieve maximum adiabatic efficiency. The comparison of the optimum blade and the original blade indicates that optimal tangential stacking line causes the shock wave to move downstream and reduce the secondary flow which has led to an improvement of about 1.7% of the adiabatic efficiency.


Axial flow compressor Transonic rotor Genetic algorithm optimization Tangential stacking line CFD 

List of symbols


Pressure coefficient




Leading edge


Rotor tip relative Mach number


Pressure ratio at max efficiency


Static pressure


Total pressure


Total temperature


Non-dimensional wall distance


Adiabatic efficiency


Lean angle at 33% span


Lean angle at 66% span


Lean angle at 100% span



Additive correction multi-grid


Computational fluid dynamics


Genetic algorithm


Multi-circular arc


Shear Stress Transport


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Copyright information

© The Brazilian Society of Mechanical Sciences and Engineering 2018

Authors and Affiliations

  1. 1.Department of Mechanical and Aerospace EngineeringMalek Ashtar University of TechnologyIsfahanIran

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