压气机扩压叶栅的类/形函数表示方法与应用  

Application of Class/Shape Function Representation of Compressor Diffusion Cascade

作　　者：韩瑞雪 陈榴[1] 戴韧[1] HAN Rui-Xue;CHEN Liu;DAI Ren(School of Energy and Power Engincering,University of Shanghai for Science and Technology,Shanghai 200093,China)

机构地区：[1]上海理工大学能源与动力工程学院,上海200093

出　　处：《工程热物理学报》2020年第9期2186-2192,共7页Journal of Engineering Thermophysics

基　　金：上海市科委战略新兴产业引导专项(No.16DZ1121202)。

摘　　要：类/形函数变换(CST)方法是流线型几何形状参数化表示的新方法。应用CST方法表示轴流压气机NACA65叶型以及一种可控扩压叶型(CDA),研究不同阶次形函数表示叶型厚度分布对叶栅气动的影响。结果表明使用2阶Bernstein多项式定义形函数,即可表达轴流压气机叶型的气动性能,保证一定的精度并避免病态参数化过程。应用2阶CST方法优化NACA65叶型,设计点叶型损失下降16%,有效工作范围扩大10%。基于CST方法建立了一套轴流叶栅的反问题求解方法,从NACA65叶型开始,交替修正叶型的中弧线和厚度分布,反设计出可控扩压叶型。The Class/Shape Function Transformation(CST) is a new method to shape a streamlined geometry.In this paper,CST is used to represent NACA 65 and CD airfoil of axial compressor blade profiles respectively.The influence of profile thickness distribution represented by different order functions on aerodynamic performance was studied.Results show that the second-order shape function of Bernstein polynomial has enough capacity to represent an axial flow compressor airfoil.The accuracy of representation is ensured and the ill-conditioned parameterization process is avoided.A normal NACA65 profile is optimized to reduce the profile loss by 16% and enlarge the effective operation range by 10%.CST method is proved effective in an inverse design of CD airfoil started from a normal NACA65 profile.

关 键 词：类/形函数变换 可控扩压叶型 反问题求解 气动优化 

分 类 号：TK474.8[动力工程及工程热物理—动力机械及工程]