摘要
开发了一种通用于轴流、斜流和离心式压气机叶片的任意中弧造型设计方法.该方法以通流计算的结果为基础,其优点在于可以通过调整通流设计的环量的分布,来获得所要求的气动性能,并最终生成与通流计算结果较为一致的三维叶型.修改造型控制参数可以同时实现对主叶片、分流叶片的造型控制,以及对叶型尾缘形状的控制.通过在微小型发动机压气机叶片设计中的应用,得到了比较理想的叶片.此外,该方法还可以用于压气机叶片的优化设计.
A blading design method for both axial and centrifugal compressor blades was discussed by using arbitrary camber lines. This method was based on through flow calculation. Three dimensional blades consistent with the result of through flow calculation can be obtained by modifying the distribution of velocity circulation. Meanwhile, it can control main blade/splitter blading and the shape of trailing edge of the airfoil. It has been applied to the design of compressor blades of some micro-engines, and fairly ideal airfoils are obtained. Also, this method can be used for optimization of compressor blades.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第1期150-156,共7页
Journal of Aerospace Power
基金
国家自然科学基金(501360105067600450736007)
关键词
任意中弧造型
通流设计
离心叶轮
分流叶片
优化设计
arbitrary camber lines blading
through flow design
centrifugal impeller
splitter blade
optimization design
