Solution of Turbine Blade Cascade Flow Using an Improved Panel Method
An improved panel method has been developed to calculate compressible inviscid flow through a turbine blade row. The method is a combination of the panel method for infinite cascade, a deviation angle model, and a compressibility correction. The resulting solution provides a fast flexible mesh-free...
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| Main Authors: | , |
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| Format: | Article |
| Language: | English |
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Wiley
2015-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2015/312430 |
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| _version_ | 1832564808528953344 |
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| author | Zong-qi Lei Guo-zhu Liang |
| author_facet | Zong-qi Lei Guo-zhu Liang |
| author_sort | Zong-qi Lei |
| collection | DOAJ |
| description | An improved panel method has been developed to calculate compressible inviscid flow through a turbine blade row. The method is a combination of the panel method for infinite cascade, a deviation angle model, and a compressibility correction. The resulting solution provides a fast flexible mesh-free calculation for cascade flow. A VKI turbine blade cascade is used to evaluate the method, and the comparison with experiment data is presented. |
| format | Article |
| id | doaj-art-21846c8590944aa6b8617d86449e714a |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2015-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-21846c8590944aa6b8617d86449e714a2025-02-03T01:10:05ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742015-01-01201510.1155/2015/312430312430Solution of Turbine Blade Cascade Flow Using an Improved Panel MethodZong-qi Lei0Guo-zhu Liang1Department of Aerospace Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, ChinaDepartment of Aerospace Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, ChinaAn improved panel method has been developed to calculate compressible inviscid flow through a turbine blade row. The method is a combination of the panel method for infinite cascade, a deviation angle model, and a compressibility correction. The resulting solution provides a fast flexible mesh-free calculation for cascade flow. A VKI turbine blade cascade is used to evaluate the method, and the comparison with experiment data is presented.http://dx.doi.org/10.1155/2015/312430 |
| spellingShingle | Zong-qi Lei Guo-zhu Liang Solution of Turbine Blade Cascade Flow Using an Improved Panel Method International Journal of Aerospace Engineering |
| title | Solution of Turbine Blade Cascade Flow Using an Improved Panel Method |
| title_full | Solution of Turbine Blade Cascade Flow Using an Improved Panel Method |
| title_fullStr | Solution of Turbine Blade Cascade Flow Using an Improved Panel Method |
| title_full_unstemmed | Solution of Turbine Blade Cascade Flow Using an Improved Panel Method |
| title_short | Solution of Turbine Blade Cascade Flow Using an Improved Panel Method |
| title_sort | solution of turbine blade cascade flow using an improved panel method |
| url | http://dx.doi.org/10.1155/2015/312430 |
| work_keys_str_mv | AT zongqilei solutionofturbinebladecascadeflowusinganimprovedpanelmethod AT guozhuliang solutionofturbinebladecascadeflowusinganimprovedpanelmethod |