Effects of profile variability on aerodynamic performance of supersonic compressor cascade
ObjectivesThis study seeks to evaluate the effects of profile variability on the aerodynamic per-formance of a compressor and provide guidance for the robust design of compressor blades. MethodsA mathematical model of profile variability distribution with a single peak is established. The effects of...
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| Format: | Article |
| Language: | English |
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Editorial Office of Chinese Journal of Ship Research
2024-02-01
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| Series: | Zhongguo Jianchuan Yanjiu |
| Subjects: | |
| Online Access: | http://www.ship-research.com/en/article/doi/10.19693/j.issn.1673-3185.03300 |
| _version_ | 1797201167515648000 |
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| author | Zhuoyuan CHEN Shaojuan GENG Shuaipeng LIU Jiahao LIU Hailong LIU |
| author_facet | Zhuoyuan CHEN Shaojuan GENG Shuaipeng LIU Jiahao LIU Hailong LIU |
| author_sort | Zhuoyuan CHEN |
| collection | DOAJ |
| description | ObjectivesThis study seeks to evaluate the effects of profile variability on the aerodynamic per-formance of a compressor and provide guidance for the robust design of compressor blades. MethodsA mathematical model of profile variability distribution with a single peak is established. The effects of the combined profile variability of the blade pressure and suction surface on the aerodynamic performance of two supersonic planar cascades are then investigated by numerical simulation. ResultsThe results show that the profile variability distribution on the suction surface is the key factor behind cascade total pressure loss. The total pressure loss coefficient decreases gradually with the position of maximum profile variability on the suction surface moving downstream. The profile variability distribution on the blade pressure and suction surface influences the flow turning angle and static pressure rise coefficient with opposite trends. The profile variability on the suction surface plays a dominant role in the flow turning angle and static pressure rise of cascade with lower incoming Mach number; for cascade with higher incoming Mach number, the profile variability on the pressure surface has a significant impact on the flow turning angle and static pressure rise. The position and intensity of the shockwave and the end wall profile of the expansion channel after the shockwave comprehensively determine the flow state on the blade surface and in the cascade blade passage. The flow loss near the blade suction surface increases, the flow loss near the blade pressure surface decreases, and the compound effect determines the change of cascade loss, flow turning angle and static pressure rise. ConclusionsThe results of this study can provide guidance for the design, manufacture and manufacturing variability evaluation of transonic compressors. |
| first_indexed | 2024-04-24T07:43:14Z |
| format | Article |
| id | doaj.art-1c048f4fdfd54ebda7824665d55d60da |
| institution | Directory Open Access Journal |
| issn | 1673-3185 |
| language | English |
| last_indexed | 2024-04-24T07:43:14Z |
| publishDate | 2024-02-01 |
| publisher | Editorial Office of Chinese Journal of Ship Research |
| record_format | Article |
| series | Zhongguo Jianchuan Yanjiu |
| spelling | doaj.art-1c048f4fdfd54ebda7824665d55d60da2024-04-19T05:29:51ZengEditorial Office of Chinese Journal of Ship ResearchZhongguo Jianchuan Yanjiu1673-31852024-02-0119219720610.19693/j.issn.1673-3185.03300ZG3300Effects of profile variability on aerodynamic performance of supersonic compressor cascadeZhuoyuan CHEN0Shaojuan GENG1Shuaipeng LIU2Jiahao LIU3Hailong LIU4Research Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang 212013, ChinaAdvanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, ChinaAdvanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, ChinaResearch Center of Fluid Machinery Engineering and Technology, Jiangsu University, Zhenjiang 212013, ChinaSchool of Energy and Power Engineering, Jiangsu University, Zhenjiang 212013, ChinaObjectivesThis study seeks to evaluate the effects of profile variability on the aerodynamic per-formance of a compressor and provide guidance for the robust design of compressor blades. MethodsA mathematical model of profile variability distribution with a single peak is established. The effects of the combined profile variability of the blade pressure and suction surface on the aerodynamic performance of two supersonic planar cascades are then investigated by numerical simulation. ResultsThe results show that the profile variability distribution on the suction surface is the key factor behind cascade total pressure loss. The total pressure loss coefficient decreases gradually with the position of maximum profile variability on the suction surface moving downstream. The profile variability distribution on the blade pressure and suction surface influences the flow turning angle and static pressure rise coefficient with opposite trends. The profile variability on the suction surface plays a dominant role in the flow turning angle and static pressure rise of cascade with lower incoming Mach number; for cascade with higher incoming Mach number, the profile variability on the pressure surface has a significant impact on the flow turning angle and static pressure rise. The position and intensity of the shockwave and the end wall profile of the expansion channel after the shockwave comprehensively determine the flow state on the blade surface and in the cascade blade passage. The flow loss near the blade suction surface increases, the flow loss near the blade pressure surface decreases, and the compound effect determines the change of cascade loss, flow turning angle and static pressure rise. ConclusionsThe results of this study can provide guidance for the design, manufacture and manufacturing variability evaluation of transonic compressors.http://www.ship-research.com/en/article/doi/10.19693/j.issn.1673-3185.03300axial compressortransonic cascadeprofile variabilityvariability accuracyvariability distributionaerodynamic performance |
| spellingShingle | Zhuoyuan CHEN Shaojuan GENG Shuaipeng LIU Jiahao LIU Hailong LIU Effects of profile variability on aerodynamic performance of supersonic compressor cascade Zhongguo Jianchuan Yanjiu axial compressor transonic cascade profile variability variability accuracy variability distribution aerodynamic performance |
| title | Effects of profile variability on aerodynamic performance of supersonic compressor cascade |
| title_full | Effects of profile variability on aerodynamic performance of supersonic compressor cascade |
| title_fullStr | Effects of profile variability on aerodynamic performance of supersonic compressor cascade |
| title_full_unstemmed | Effects of profile variability on aerodynamic performance of supersonic compressor cascade |
| title_short | Effects of profile variability on aerodynamic performance of supersonic compressor cascade |
| title_sort | effects of profile variability on aerodynamic performance of supersonic compressor cascade |
| topic | axial compressor transonic cascade profile variability variability accuracy variability distribution aerodynamic performance |
| url | http://www.ship-research.com/en/article/doi/10.19693/j.issn.1673-3185.03300 |
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