摘要
应用NURBS建立了三维轴流压气机叶片的几何型面优化模型,将叶片的气动性能参数与NURBS形状控制权因子关联,形成一套优化判断准则。通过对某型轴流压气机静子叶片优化设计的实例验证,对比研究了优化前后叶片气动性能的差异,证实了该方法可以灵活快速地优化叶片的几何型面,以满足气动性能的需求,具有较好的工程应用价值。
The NURBS method was introduced for the 3D geometric optimization of axialflow compressor blade design. A set of optimization rule was developed by relating some aerodynamic performance parameters with the weights factor of NURBS. In the design of an axial compressor stator blade,the flow structures comparison have been made between the optimized new blade and the original one. The results show that this method could flexibly and rapidly optimize the blade shape to meet the aerodynamic requirements.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第4期625-629,共5页
Journal of Aerospace Power
