The ‘multi-point design’ approach for single airfoils in aeronautical engineering is introduced into the optimal design for diffuser cascades of centrifugal compressors. Genetic algorithms are used to solve the multi-point problem. The proposed approach is applied to a ‘two-point design’ of a real diffuser cascade. The numerical results show that a group of optimal blade profiles can be obtained, from which the designer can select performance compromises for the two given design condition points.
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