摘要
在小函道比风扇级的设计中,本文将风扇转子叶片、外函、内函静子叶片的通流设计反问题与分流机匣的气动设计问题有机结合,而成为一个统一的双函道叶轮机通流反问题。在内函静子叶片流线、外函静子叶片流线、分流机匣流线和机匣位置四者实现一个统一的准径向平衡之后,造型出转子叶片、静子叶片和分流机匣,从而一次完成风扇级设计和确保准确函道比的机匣设计。实现本方法的关键是引入一个通流中的加质量流动。本方法可加入现有通流算法中。本方法的第二个重要应用是可对带减震凸台的转子叶片进行通流设计。
In the design of a low bypass ratio fan stage,this paper links the through flow inverse problem of the fan rotor,the core channel fan stator and the bypass channel fan stator together,as an organic whole,with the splitter aerodynamic design problem.It forms thus a unified through flow inverse problem for two channel turbomachines.After an overall quasiradialequilibrium is iteratively achieved among four parts-the streamlines of the core channel fan stator,the bypass channel fan stator,the splitter and the position of the splitter,the blading processes for one fan blade,two fan vanes and one splitter are performed.This method designs in one pass a fan stage and a splitter with a precise value of bypass ratio.Its primary and key approach scheme is the introduction of a mass addition half way through the through flow streamline development.This scheme can serve as a new feature which can be inserted into existing through flow programs.When subtracting mass flow after adding a mass flow,alternatively,this scheme can also be used to treat the problem of inverse design of fan/compressor rotor blades with partspan shrouds.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2003年第4期542-545,共4页
Journal of Aerospace Power
