摘要
为消除叶型表面曲率不连续对压气机叶片性能的影响,提高压气机平面叶栅的优化设计水平,提出一种表面曲率连续的参数化方法。利用Bezier曲线端点导矢与控制点的性质,使对应控制点满足特定关系便可实现两条Bezier曲线在衔接点处曲率连续。基于这一性质,对压气机叶型前、尾缘重新构型,采用最小二乘法对吸力面和压力面重新参数化,解决叶型参数化过程中前缘与叶身衔接点处曲率不连续的问题。运用数值模拟方法进行流场计算,并与原始叶型进行对比。结果表明:该参数化方法可得到表面曲率连续的压气机叶型,有效改善叶型前缘的流动,提高叶型的气动性能。
In order to eliminate the infuence of the discontinuous curvature on the performance of the compressor airfoil and improve the optimal design capability of compressor cascade,a parameterization method with a continuous-curvature surface was proposed.The curvature continuity condition of the two Bezier curves at the connection point can be achieved,by using the connection of the endpoint guide vector and the control point of the Bezier curve to make the corresponding control point satisfy a specific relationship.Based on this property of the Bezier curve,the leading edges and trailing edges of the compressor blade are reconfigured.In order to remove discontinuous curvature at the connection point between the leading edge and the airfoil,the least squares method was used to fit the suction section and pressure section of compressor airfoil in the parameterization process.The numerical simulation method is used to calculate the fow field,and the aerodynamic performance of the parameterization airfoil and the original airfoil are compared.The results show that the parameterization method can obtain a continuous-curvature surface,which can effectively improve the flow condition of the leading edge and improve the aerodynamic performance of the compressor airfoil.
作者
覃锴
黄典贵
QIN Kai;HUANG Diangui(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai 200093,China)
出处
《工程热物理学报》
北大核心
2025年第6期1858-1864,共7页
Journal of Engineering Thermophysics
基金
国家自然科学基金(No.51906155)
国家科技重大专项(No.Y2019-I-0002-0003,No.J2019-II-0010-0030,No.J2019-II-0016-0037)。
关键词
参数化
压气机叶型
曲率连续
最小二乘法拟合
parameterization
compressor airfoil
continuous-curvature
least square approximation
