Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger
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 distr...
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| Format: | Article |
| Language: | English |
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MDPI AG
2018-07-01
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| Series: | Energies |
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| Online Access: | http://www.mdpi.com/1996-1073/11/7/1827 |
| _version_ | 1811300338064424960 |
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| author | Omer Faruk Atac Jeong-Eui Yun Taehyun Noh |
| author_facet | Omer Faruk Atac Jeong-Eui Yun Taehyun Noh |
| author_sort | Omer Faruk Atac |
| collection | DOAJ |
| description | 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. |
| first_indexed | 2024-04-13T06:49:35Z |
| format | Article |
| id | doaj.art-a82a016a3ae142bb874bbf5b49dbdb5b |
| institution | Directory Open Access Journal |
| issn | 1996-1073 |
| language | English |
| last_indexed | 2024-04-13T06:49:35Z |
| publishDate | 2018-07-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj.art-a82a016a3ae142bb874bbf5b49dbdb5b2022-12-22T02:57:27ZengMDPI AGEnergies1996-10732018-07-01117182710.3390/en11071827en11071827Aerodynamic Design Optimization of a Micro Radial Compressor of a TurbochargerOmer Faruk Atac0Jeong-Eui Yun1Taehyun Noh2Department of Mechanical Design Engineering, Kangwon National University, Samcheok 25913, KoreaDepartment of Mechanical Design Engineering, Kangwon National University, Samcheok 25913, KoreaKey Yang Precision Co., R&D Center, 1012-4 Eungmyeong-dong (63 Gongdan 4-gil), Gimcheon-si 39537, KoreaThis 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.http://www.mdpi.com/1996-1073/11/7/1827radial compressoroptimizationefficiencybeta distributionimpellersplitter |
| spellingShingle | Omer Faruk Atac Jeong-Eui Yun Taehyun Noh Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger Energies radial compressor optimization efficiency beta distribution impeller splitter |
| title | Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger |
| title_full | Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger |
| title_fullStr | Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger |
| title_full_unstemmed | Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger |
| title_short | Aerodynamic Design Optimization of a Micro Radial Compressor of a Turbocharger |
| title_sort | aerodynamic design optimization of a micro radial compressor of a turbocharger |
| topic | radial compressor optimization efficiency beta distribution impeller splitter |
| url | http://www.mdpi.com/1996-1073/11/7/1827 |
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