Abstract
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.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
