| In this work, one has attempted to find an optimum radial compressor impeller geometry at both single and multi-point operation by utilizing advanced numerical concepts. In particular the optimization that was attempted is based on advanced numerical tools applied to aerodynamics such as: (1) Artificial Neural Network (ANN); (2) Genetic Algorithm (GA); (3) Navier-Stokes Solver (NS).;With this system the performance is predicted using a fast approximate model known as an Artificial Neural Network (ANN), and then subsequently verified by a very accurate but slow computing Navier-Stokes Solver, the core of this knowledge based-on design being a Genetic Algorithm (GA).;Optimum geometries were found for both the single point case and multiple point case which were different and have improved efficiencies relative to the baseline geometry. Thus, the main conclusion is that the geometry that works well for one operating point will not necessarily work well for multiple point operation. |
