航空制造技术
航空製造技術
항공제조기술
Aeronautical Manufacturing Technology
2015年
3期
31-34
,共4页
尾缘劈缝%涡轮叶片%桥接线%模拟退火算法
尾緣劈縫%渦輪葉片%橋接線%模擬退火算法
미연벽봉%와륜협편%교접선%모의퇴화산법
Trailing edge%Turbine blade%Bridge curve%Simulated annealing algorithm
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。
航空髮動機渦輪葉片尾緣劈縫是一箇複雜的麯麵，設計過程繁瑣，造型過程中易齣現與葉身連接不光順的問題。針對尾緣劈縫的幾何結構特徵，提齣一種基于橋接線的渦輪葉片尾緣劈縫的建模方法，以尾緣劈縫截麵線和葉身內形麯麵為邊界條件，採用模擬退火算法創建橋接線，以此為基礎完成尾緣劈縫的建模。開髮瞭尾緣劈縫參數化建模模塊，提高瞭葉片設計效率，併為航空髮動機複雜麯麵參數化建模提供瞭參攷。
항공발동궤와륜협편미연벽봉시일개복잡적곡면，설계과정번쇄，조형과정중역출현여협신련접불광순적문제。침대미연벽봉적궤하결구특정，제출일충기우교접선적와륜협편미연벽봉적건모방법，이미연벽봉절면선화협신내형곡면위변계조건，채용모의퇴화산법창건교접선，이차위기출완성미연벽봉적건모。개발료미연벽봉삼수화건모모괴，제고료협편설계효솔，병위항공발동궤복잡곡면삼수화건모제공료삼고。
[ABSTRACT] Trailing edge of turbine blade in aeroengine is a kind of complex surface, of which the de-sign process is complicated, and the non-fairness of conti-nuity 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 trail-ing edge based on bridge curve is conducted. The paramet-ric design module of trailing edge is developed. Therefore, the method improves the efifciency of turbine blade design, and contributes references for parametric modeling of the complicated surface of aeroengine.
