超声速叶型前缘几何形状对叶栅气动性能的影响
Influence effect of supersonic airfoil’s leading edge geometric shape on aero-dynamical performance of cascade
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摘要: 应用NURBS技术构造超声速叶型, 采用两个控制参数调整叶栅前缘椭圆弧的几何形状, 来探索不同的前缘构型对超声速叶型气动性能的影响效应;通过对比分析调整每个参数所得的一系列叶栅的流场计算结果, 发现椭圆弧的形状控制因子对超声速叶栅的前缘激波和气流流动状况具有一定的改善效果, 同时在保证叶栅气动弦长基本不变的情况下, 存在某个椭圆弧形状控制因子和方向控制因子的匹配能够使叶栅的气动性能达到最佳.Abstract: NURBS method was applied to reshape some supersonic airfoils, and two controlling parameters were used to adjust the geometric shape of supersonic airfoil’s leading edge, these methods were adopted to investigate the supersonic airfoil’s aero-dynamic performance influence effect with different leading edge geometric shape; The contrastive analysis results, which were obtained from a series of airfoil’s flow field structure with changing each controlling parameter, shown ellipse shape controlling factor not only could weaken the shock wave intensity near the leading edge region of airfoil but also could improve the flow field structure; At the same time, this paper demonstrated that the matching between some ellipse shape controlling factor and some ellipse direction controlling factor could make the responding supersonic airfoil’s aero-dynamic performance reach to the best while its chord keeping no change.
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Key words:
- aerospace propulsion system /
- NURBS /
- ellipse edge arc /
- supersonic airfoil /
- aero-dynamic performance effect /
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[1] 陆宏志,徐力平,方韧.压气机叶片前缘形状的改进设计[J].航空动力学报,2000,15(2):129-132.LU Hongzhi,XU Liping,FANG Ren.Improvement of compressor blade leading edge design[J].Journal of Aerospace Power,2000,15(2):129-132. [2] 周岳琨,王建新,管继伟,等.汽轮机叶片设计和几何成型方法综述[J].汽轮机技术,2001,43(4):198-202.ZHOU Yuekun,WANG Jianxin,GUAN Jiwei,et al.A summary about turbine blade design and molding method[J].Turbine Technology,2001,43(4):198-202. [3] Mengistu T,Ghaly W.Single and multipoint shape optimization of gas turbine blade cascades[R].AIAA 2004-4446. [4] Papila N,Shyy W.Shape optimization of supersonic turbines using response surface and neural network methods[R].AIAA 2001-1065. [5] Painchaud-Ouellet S,Tribes C,Trepanier J Y.Airfoil shape optimization using NURBS representation under thickness constraint[R].AIAA 2004-1095. [6] Nadir M,Kim I Y.Structural shape optimization considering both performance and manufacturing cost[R].AIAA 2004-4593. [7] 肖敏,刘波,仲永兴.轴流压气机超声速叶型几何设计方法的研究[J].航空动力学报,2000,15(3).237-240.XIAO Min,LIU Bo,ZHONG Yongxing.A study on geometric methods for designing supersonic aerofoil of axial flow compressor[J].Journal of Aerospace Power,2000,15(3).237-240. [8] Mengistu T T,Ghaly W S.A geometric representation of turbomachinery cascades using NURBS[R].AIAA 2002-0318.
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