Optimization of Transonic Compressor Profiles Using Genetic Algorithm and Computational Fluid Dynamics (CFD)

In this research, the optimization of NASA Rotor 67 is studied to reduce the total pressure loss and conserving the mass flow rate and the flow turning angle. The blade profile is parameterized using B-splines to generate the blade camber line and the thickness distribution. the CFD solvers are utilized coupled with the genetic algorithm to improve the performance of the compressor. Finally, the optimized profiles are employed in the three-dimensional blade geometry and the flow field is solved using a 3D flow solver. In the first case, the hub and mid sections are replaced and the compressor efficiency is enhanced by 0/48%. However, the mass flow rate is decreased for this case. By applying the three optimized profiles in the hub, mid and tip sections of the Rotor 67 blade, the maximum efficiency is improved by 0/41% while the mass flow capacity of the compressor is increased as well.