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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,并为航空发动机复杂曲面参数化建模提供了参考
Aeroengine turbine blade tail edge split is a complex curved surface, the design process is cumbersome, easy to appear in the process of modeling and leaf body connection is not smooth problem. In view of the geometric structure of the tail rift seam, a modeling method based on bridging line is proposed for the tail rift split of the turbine blade. The boundary conditions of the trailing edge rift seam section line and the blade internal shape surface are used as the boundary conditions, and the simulated annealing algorithm is used to create the bridge Wiring, as a basis for the completion of tail-edge split seam modeling. The tail-split split-seam parameterized modeling module is developed to improve the efficiency of blade design and provide a reference for parametric modeling of aero-engine complex curved surface