Convegni ATI - Accesso riservato soci CTI

Autore: E. Benini

Collana: CA - 59 - Genova 2004

Note:
An accurate method for transonic compressor multi-objective design optimization was developed and applied to the Nasa rotor 37, a test case representative of complex three-dimensional viscous flow structures in transonic blades. The optimization problem consisted in maximizing the isentropic efficiency of the rotor and in maximizing its pressure ratio at the design point, using a constraint on the mass flow rate. The two objectives were taken into account simultaneously, using a Pareto multi-objective approach implemented in a novel evolutionary algorithm. The optimization algorithm was coupled with the three-dimensional Navier-Stokes code CFX-TASCflow, which was used for the aerodynamic analysis of blade designs. Prior to optimization, the CFD code was accurately validated against the available experimental data by means of a systematic sensitivity analysis on the influence of the code’s configuration on accuracy of the numerical computations. The optimal rotor configurations, which corresponded to the maximum pressure ratio and maximum efficiency, were obtained and compared to the original design. The reasons for improved performance were discussed critically.