Abstract
This study presents an aerodynamic design optimization of a micro radial compressor impeller on a turbocharger used in a 0.8 L two-cylinder gasoline engine. In the conventional design optimization of the impeller, the hub and shroud curve of the main blade is commonly parameterized with a beta distribution, and splitter blades are generally considered short versions of the full blade. However, geometrical parameterizations in our study mainly focus on the beta distribution of a full blade, and it is parameterized differently from the conventional way. Eight parameters are selected as design variables for the beta distribution. To maximize the isentropic efficiency, design points that are created by Design of Experiment (DOE) are evaluated through single-objective optimization coupled with a non-parametric regression surrogate model. Furthermore, the splitter leading edge location on the meridional plane is investigated to enhance the performance of the impeller after the optimization process. The results show that total efficiency enhancement of approximately 2.2% is achieved. Furthermore, the findings show that a full blade beta distribution and the splitter leading edge location are sufficient parameters to optimize the impeller, and, with the proposed optimization, splitter blades are no longer copies of the full blade for each application.
Highlights
Centrifugal compressors are widely utilized in many engineering disciplines, such as turbochargers, industrial gas and steam turbines, and small gas turbines in the aviation field
Metamodel coupled optimization techniques incorporating three-dimensional Reynold-average Naver-Stokes (RANS) analyses have been suggested by several authors to enhance performance parameters such as efficiency, pressure ratio, and operation range [7,8,9,10,11]
Geometry parameterization is a critical stage in the optimization process; design of compressors greatly depends on the hub and shroud profiles of the blades, beta distribution, and lean angle [12,13,14]
Summary
Centrifugal compressors are widely utilized in many engineering disciplines, such as turbochargers, industrial gas and steam turbines, and small gas turbines in the aviation field. Due to their higher compression ratio in a single stage with a low mass flow rate and lower installation space requirements compared with axial compressors, centrifugal compressors have become more attractive to researchers. Several optimization techniques have been suggested to improve compressor design [1,2,3,4,5,6]. In addition to the already mentioned design parameters, the leading edge location of the splitter blade can be considered to reduce flow blockage and to improve flow guidance [15]
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