This paper presents a new integrated methodology for the optimisation of turbomachinery blade shapes coupling a user interface, a blade geometry generator to an automatic CFD solution process and an optimisation algorithm. The methodology relies on the interaction between a genetic algorithm, a database and user generated objective functions and constraints. The latter includes aerodynamic, geometrical and structural constraint functions, while future developments will extend these to aero-acoustic optimisation objectives. Several examples, covering gas turbine configurations are presented.
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