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| Impact of Manufacturing Variations on Aerodynamic Performance of Compressor Blade |
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| DOI：10.7643/issn.1672-9242.2023.01.004 |
| KeyWord:compressor blade manufacturing variations thickness change midline change numerical simulation plane blade aerodynamic performance |
| Author | Institution |
| SHAO Wen-bo |
Key Laboratory of Thermal Science and Power Engineering of the Ministry of Education, Department of Energy and Power Engineering, Tsinghua University, Beijing , China |
| HU Bo |
Collaborative R&D Center for Key Technology of Gas Turbine, Wuxi Research Institute of Applied Technologies, Tsinghua University, Jiangsu Wuxi , China;Key Laboratory of Thermal Science and Power Engineering of the Ministry of Education, Department of Energy and Power Engineering, Tsinghua University, Beijing , China |
| LI Xue-song |
Collaborative R&D Center for Key Technology of Gas Turbine, Wuxi Research Institute of Applied Technologies, Tsinghua University, Jiangsu Wuxi , China |
| REN Xiao-dong |
Collaborative R&D Center for Key Technology of Gas Turbine, Wuxi Research Institute of Applied Technologies, Tsinghua University, Jiangsu Wuxi , China;Key Laboratory of Thermal Science and Power Engineering of the Ministry of Education, Department of Energy and Power Engineering, Tsinghua University, Beijing , China |
| GU Chun-wei |
Collaborative R&D Center for Key Technology of Gas Turbine, Wuxi Research Institute of Applied Technologies, Tsinghua University, Jiangsu Wuxi , China;Key Laboratory of Thermal Science and Power Engineering of the Ministry of Education, Department of Energy and Power Engineering, Tsinghua University, Beijing , China |
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| Abstract: |
| The work aims to study the impact of manufacturing variations of different regions on the aerodynamic performance of the blade. The middle section of export-grade static blade of axial compressor was selected. With the blade thickness change and midline change as the characteristics, manufacturing variations were added to leading edge, maximum thickness and trailing edge of blade. The numerical simulation method was used to compare the aerodynamic performance of designed blade and study the impact of geometric variations of different regions on the performance. The geometric variations of leading edge of blade had the greatest impact on aerodynamic performance and the deviation of midline caused by the variations played a leading role in the performance change. The impact trend of geometric variations of trailing edge on the performance was completely opposite to that of geometric variations of leading edge. Considering the overall variations of blade, the performance deterioration caused by the positive deviation of profile was more obvious. The obtained impact law of geometric variations can provide data support for the formulation of process and over-variation trial in the actual blade manufacturing process. |
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