摘要
航空发动机涡轮叶片尾缘劈缝是一个复杂的曲面,设计过程繁琐,造型过程中易出现与叶身连接不光顺的问题。针对尾缘劈缝的几何结构特征,提出一种基于桥接线的涡轮叶片尾缘劈缝的建模方法,以尾缘劈缝截面线和叶身内形曲面为边界条件,采用模拟退火算法创建桥接线,以此为基础完成尾缘劈缝的建模。开发了尾缘劈缝参数化建模模块,提高了叶片设计效率。
Trailing edge of turbine blade in aeroengine is a kind of complex surface,of which the design process is complicated,and the non-fairness of continuity between trailing edge and blade shape easily occurs in modeling process.According to geometric and structural characteristics of trailing edge,a modeling method based on bridge curve is provided,which initially generates bridge curve by utilizing simulated annealing algorithm,with boundary conditions of the section curves of trailing edge and the surface of inner blade shape,then modeling of trailing edge based on bridge curve is conducted.The parametric design module of trailing edge is developed.Therefore,the method improves the efficiency of turbine blade design,and contributes references for parametric modeling of the complicated surface of aeroengine.
出处
《航空制造技术》
2015年第3期30-33,共4页
Aeronautical Manufacturing Technology
基金
课题编号:国家科技支撑计划2012\BAF10B09
课题名称:重型军用车辆企业集团多项目协同管控平台应用示范
关键词
尾缘劈缝
涡轮叶片
桥接线
模拟退火算法
Trailing edge
Turbine blade
Bridge curve
Simulated annealing algorithm
