基于NURBS曲线的轴流透平叶片气动 数值优化

王录; 刘海清; 张宏武; 杨建道

基于NURBS曲线的轴流透平叶片气动数值优化

1.
中国航天科技集团公司北京空间飞行器总体设计部, 北京 100094
2.
中国科学院工程热物理研究所, 北京 100190
3.
中国科学院研究生院, 北京 100190
4.
上海电气电站设备有限公司汽轮机厂, 上海 200240

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出版历程
- 收稿日期: 2011-06-07
- 刊出日期: 2012-05-28

Numerical aerodynamic optimization of axial turbomachinery blades based on NURBS

1.
Institute of Spacecraft System Engeneering, China Aerospace Science and Technology Corporation, Beijing 100094, China
2.
Institute of Engineering Thermophysics, Chinese Academy of Science, Beijing 100190, China
3.
Graduate University of Chinese Academy of Science, Beijing 100190, China
4.
Turbing Plant, Shanghai Electric Power Generation Equipment Company Limited, Shanghai 200240, China

摘要

摘要: 通过搭建适用于轴流式透平叶片气动数值优化的设计平台,对某NASA透平级动静叶片进行等熵效率、流量相对变化、落压比相对变化的多目标寻优.该平台包括三个核心模块: 叶片的参数化造型、流场气动性能评估、优化策略.采用非均匀有理B样条(NURBS)曲线对叶片进行参数化拟合;针对叶片气动数值优化的多变量、多模态的特征,采用试验设计和遗传算法组合优化策略进行寻优.经过气动优化, 在设计工况点优化叶片性能较原始叶片有明显提高,为轴流式叶片的气动优化提供了可借鉴的措施.
- NURBS曲线 /
- 遗传算法 /
- 多目标优化 /
- 轴流透平叶片 /
- 气动优化
Abstract: A NASA(National Aeronautics and Space Administration) transonic single stage turbine was taken as an example,describing how to use an aerodynamic numerical optimization platform to find the optimal solution.The platform had three parts:parameterization and fitting of blades,simulation of flow field and optimization strategy.Blades were parameterized based on non-uniform rational B-splines(NURBS) curve.Integrated optimizationstrategy which included DOE(design of experiments) method and genetic algorithm was used to find the global optimal solution.Results show that the performance is improved at the optimized work point.The platform provides a useful reference for analogous optimization of axial turbomachinery blades.
- non-uniform rational B-splines (NURBS) /
- genetic algorithm /
- multi-objective optimization /
- axial turbomachinery blades /
- aerodynamic optimization

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参考文献(13)

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