一种基于计算几何控制无量纲参数的叶片造型方法  

Innovative Blading Method Based on Calculating Geometry

作　　者：安利平[1] 黄萍[1] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500

出　　处：《燃气涡轮试验与研究》2013年第4期8-12,17,共6页Gas Turbine Experiment and Research

摘　　要：应用目前先进的自由曲线理论,开发了一种新的叶片造型方法——B样条控制中线角叶型(BMAA)方法。分别选取准均匀B样条和贝塞尔曲线,实现了对叶型中线和厚度的方便、灵活控制;同时综合考虑方便性与实用性,选取四点控制参数进行设计。分别利用BMAA方法与原有定制叶型、任意中线方法,对某单级压气机进行设计,结果表明:对于超/跨声叶片设计,BMAA方法设计的叶片性能略优于定制叶型;与任意中线叶型达到的性能相当,但叶型控制便捷性和叶型光滑性优于任意中线叶型。Using the free-form curve theory, an innovative blading method-BMAA was developed. Uni-form B-spline and Bézier curve were chosen separately to realize the smart control of camber line and thick-ness. Considering the practicability and facility, four points were selected to design the curve of angle. In the end, BMAA, tailored airfoil and arbitrary camber lines methods were adopted to design a single-stage compressor. The results show that the blade designed by new methods is better than tailored airfoil for super-sonic/transonic blading design; and the blading performance is equal to that of arbitrary camber lines. In ad-dition, the convenience of controlling and smoothness of airfoil are superior to that of arbitrary camber lines.

关 键 词：压气机 叶片造型方法 均匀B样条 激波 BÉZIER曲线 定制叶型 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]