基于引导线的涡轮气冷叶片伸根建模方法

朱谦; 宁涛; 席平

基于引导线的涡轮气冷叶片伸根建模方法

北京航空航天大学机械工程及自动化学院, 北京 100191

基金项目: 国家自然科学基金资助项目(51075021)

详细信息

中图分类号: V 232.4
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- 被引次数: 0
出版历程
- 收稿日期: 2011-04-20
- 网络出版日期: 2012-08-30

Root extending section of turbine blade modeling method based on guide curves

School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 发动机涡轮气冷叶片伸根段是复杂的过渡曲面,设计过程繁琐.针对伸根段的几何结构特征,提出了基于引导线的伸根过渡曲面建模方法,由伸根段边界条件生成引导线,使用最小能量法优化引导线,以此为基础完成伸根段的建模,实现了指定高度截面面积修改.开发了伸根段参数化建模模块,提高了叶片设计效率,并为航空发动机复杂过渡曲面参数化建模提供参考.
- 计算机应用 /
- 伸根 /
- 涡轮叶片 /
- 引导线 /
- 最小能量法
Abstract: Root extending section of turbine blade is a kind of complex transition surface, of which the design process is complicated. According to geometric and structural characteristics of root extending section, a modeling method based on guide curves was provided. It initially generates guide curves by utilizing boundary conditions of root extending section, and then improves guide curves by applying minimizing energy method, finally conducts modeling of root extending section based on guide curves. This modeling method realizes the modification of area size of a cross section at a given height. The parametric design module of root extending section was developed. Therefore, the method improves the efficiency of turbine blade design, and contributes reference for parametric modeling of complicated transition surfaces of aircraft engines.
- computer application /
- root extending section /
- turbine blade /
- guide curve /
- minimizing energy method

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参考文献(5)

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