基于优化算法的压气机叶片气动设计

汪光文; 周正贵; 胡骏

基于优化算法的压气机叶片气动设计

南京航空航天大学能源与动力学院, 南京 210016

基金项目: 空军装备部预研基金(A0212-021B)

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出版历程
- 收稿日期: 2007-06-25
- 修回日期: 2007-11-06
- 刊出日期: 2008-07-28

Aerodynamic design of compressor blade using optimization algorithm

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 将数值最优化方法与叶轮机械正问题流场计算相结合,实现对风扇/压气机叶片积叠线、子午面流道和沿径向弦长分布组合的优化设计,数值最优化采用基于局域网的并行遗传算法.运用该软件对NASArotor67风扇转子进行重新设计,设计目标为设计点压比和流量不变、效率最高以及堵点流量不变.与原风扇转子比较,稳定工作流量范围略增大并且在整个工作流量范围内优化转子压比近于不变、效率提高约0.5个百分点.
- 气动优化 /
- 压气机 /
- 弯掠叶片 /
- 子午面流道 /
- 并行遗传算法
Abstract: An automatic aerodynamic optimization system for axial compressor was constructed,which was composed of turbomachinery flow field simulations in3-D Navier-Stokes equation methods,grid automatic generations,parameterizations of blade profiles,meridional channels and stacking line and the advanced parallel genetic algorithm based on intranet.In construction of objective functions,design point adiabatic efficiency,mass flow rates,pressure ratio and non-design point mass flow rates was considered.NASArotor67 was redesigned using the optimization system,and the present method successfully obtained a design that improved adiabatic efficiency by 0.5% compared with the rotor67 while satisfying mass flow rate and pressure ratio.
- aerodynamic optimization /
- compressor /
- swept-curved blade /
- meridional curve /
- parallel genetic algorithm

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参考文献(10)

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