摘要
介绍了航空涡轮叶片气膜孔参数化建模的现状,分析了其参数化建模的难度。提取了气膜孔参数化建模的参数,提出了以一组气膜孔为对象的参数化建模流程及参数检查方法,解决了涡轮叶片设计过程中气膜孔反复修改耗时耗力的问题,从而提高了涡轮叶片的设计效率。
In this paper,it has given an introduction of current status of parametric modeling of aeronautic turbine blade filmhole and analyzed the difficulty of it.Has extracted the parameters,offered the processes of the parametric modeling and the method of parameters inspection based on a group of flimhole.Has sloved the problem of spending a lot of time and resource on repeatedly amending flimhole in the turbine blade design,so as to improve the design efficiency.
出处
《航空计算技术》
2011年第3期77-81,共5页
Aeronautical Computing Technique
基金
国家863高技术项目资助(2007AA04Z184)
关键词
涡轮叶片
气膜孔
参数化建模
turbine blade
filmhole
parametric modeling
