Abstract
This paper describes the numerical design optimization and experimental study of centrifugal compressors with leaned curvilinear element blades. The design targets were a fully shrouded centrifugal impeller and a low-solidity vaned diffiiser. A new method of defining the curvilinear element blade was developed for centrifugal turbomachinery using coordinate transformations between a revolutionary flow-surface coordinate system and a cylindrical coordinate system. Geometries of model compressors with curvilinear element blades were then numerically optimized at a suction flow coefficient of 0.073, using a multi-objective genetic algorithm, Kriging surrogate model, and steady Reynolds-averaged Navier Stokes simulations. The optimal impeller had a concave blade suction surface and a concave leading edge. Although clear patterns in geometrical features for optimal diffiiser vanes could not be captured, we found that the dihedral profile had a predominant effect on aerodynamic performance. The performance of model compressors was experimentally measured and compared with traditional compressors as to their aerodynamic performance. The results demonstrated that the models' adiabatic efficiency was higher by 1.4% at the design point. The stall margin stayed unchanged and the surge margin expanded by 6.7%.
Sign-in/Register to access full text options 
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: The Proceedings of Mechanical Engineering Congress, Japan
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.
