亚音速透平叶型的参数化设计及其性能分析  

Parametric Design and Performance Analysis of Subsonic Turbine Profiles

作　　者：段浩杰 王静 王斌 李卫强 DUAN Haojie;WANG Jing;WANG Bin;LI Weiqiang(Army Military Transportation University,Zhenjiang 212003,China)

机构地区：[1]陆军军事交通学院,江苏镇江212003

出　　处：《军事交通学报》2022年第9期75-80,共6页Journal of Military Transportation University

摘　　要：为获得气动性能良好的亚音速透平叶型,基于叶栅流动特征,建立亚音速透平叶型的参数化造型方法,采用解析多项式曲线和Bezier曲线,对叶片进行参数化造型。案例设计结果表明:动叶设计中,采用多项式曲线构型方法会生成速度分布不合理的唯一解叶型,而Bezier曲线构型可以通过调整叶型表面曲率分布,获得气动性能良好的透平叶型,并且该方法计算量小,适用于一般的亚音速透平叶型的设计。轴向密流比对叶栅气动性能的影响结果表明:叶型型线曲率越大,逆压梯度越大,边界层越容易产生分离;总压损失随着轴向密流比的增加而减小。In order to obtain subsonic turbine blade profiles with good aerodynamic performance,a parametric modeling method of subsonic turbine blade profiles is established based on the flow characteristics of cascades in this paper.The blades are parameterized by using analytical polynomial curves and Bezier curves.The results of the design case show that in the design of moving blades,the polynomial curve configuration method will generate a unique solution blade profile with unreasonable velocity distribution,while the Bezier curve configuration can obtain a turbine blade profile with good aerodynamic performance by adjusting the surface curvature distribution of the blade profile.This method has a small amount of calculation and is suitable for the design of general subsonic turbine blade profiles.The influence of axical velocity density ratio(AVDR)on the aerodynamic performance of cascade shows that the greater the curvature of blade profile,the greater the reverse pressure gradient,the easier the boundary layer separation occurs,and the total pressure loss decreases with the increase of AVDR.

关 键 词：亚音速透平 参数化造型 轴向密流比 总压损失 

分 类 号：TK47[动力工程及工程热物理—动力机械及工程]