| A Study of 3D Aerodynamic Design for a Transonic Compressor Blading Optimized by the Locations of Aerofoil Maximum Thickness and Maximum Camber |
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| 引用本文： | Naixing Chen Hongwu Zhang Yanji Xu Weiguang HuangInstitute of Engineering Thermophysics,Chinese Academy of Sciences,P.O. Box 2706,Beijing 100080. A Study of 3D Aerodynamic Design for a Transonic Compressor Blading Optimized by the Locations of Aerofoil Maximum Thickness and Maximum Camber[J]. 热科学学报(英文版), 2003, 12(3): 198-203. DOI: 10.1007/s11630-003-0067-z |
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| 作者姓名： | Naixing Chen Hongwu Zhang Yanji Xu Weiguang HuangInstitute of Engineering Thermophysics Chinese Academy of Sciences P.O. Box 2706 Beijing 100080 |
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| 作者单位： | Naixing Chen Hongwu Zhang Yanji Xu Weiguang HuangInstitute of Engineering Thermophysics，Chinese Academy of Sciences，P.O. Box 2706，Beijing 100080 |
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| 摘 要： | A design procedure for improving the efficiency of a transonic compressor blading was proposed based on a rapid generation method for three-dimensional blade configuration and computational meshes, a three-dimensional Navier-Stokes solver and an optimization approach. The objective of the present paper is to design a transonic compressor blading optimized only by selection of the locations of maximum camber and maximum thickness for the airfoils at different span heights and to study how do these two design parameters affect the blade performance. The blading configuration and the computational meshes can be obtained very rapidly for any given combination of maximum camber and maximum thickness. The computational grid system generated is used for the Navier-Stokes solution to predict adiabatic efficiency, total pressure ratio and flow rate. As a main result of the optimization, adiabatic efficiency was successfully improved.
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| 关 键 词： | 三维空气动力学设计 优化设计 轴向跨音速压气机 网格计算 气体流动 Navier-Stokes解 最大高弯度 最大厚度 机翼 |
A study of 3D aerodynamic design for a transonic compressor blading optimized by the locations of aerofoil maximum thickness and maximum camber |
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| Naixing Chen,Hongwu Zhang,Yanji Xu,Weiguang Huang. A study of 3D aerodynamic design for a transonic compressor blading optimized by the locations of aerofoil maximum thickness and maximum camber[J]. Journal of Thermal Science, 2003, 12(3): 198-203. DOI: 10.1007/s11630-003-0067-z |
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| Authors: | Naixing Chen Hongwu Zhang Yanji Xu Weiguang Huang |
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| Affiliation: | (1) Institute of Engineering Thermophysics, Chinese Academy of Sciences, P.O. Box 2706, 100080 Beijing, China |
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| Abstract: | A design procedure for improving the efficiency of a transonic compressor blading was proposed based on a rapid generation method for three-dimensional blade configuration and computational meshes, a three-dimensional Navier-Stokes solver and an optimization approach. The objective of the present paper is to design a transonic compressor blading optimized only by selection of the locations of maximum camber and maximum thickness for the airfoils at different span heights and to study how do these two design parameters affect the blade performance. The blading configuration and the computational meshes can be obtained very rapidly for any given combination of maximum camber and maximum thickness. The computational grid system generated is used for the Navier-Stokes solution to predict adiabatic efficiency, total pressure ratio and flow rate. As a main result of the optimization, adiabatic efficiency was successfully improved. |
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| Keywords: | axial transonic compressor 3D aerodynamic design optimization N.S. solver rapid generation of computational meshes |
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