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.
An automatic aerodynamic optimization system for axial compressor was constructed, which was composed of turbomachinery flow field simulations in 3-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. NASA rotor67 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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第7期1218-1224,共7页
Journal of Aerospace Power
基金
空军装备部预研基金(A0212-021B)
关键词
气动优化
压气机
弯掠叶片
子午面流道
并行遗传算法
aerodynamic optimization
compressor
swept-curved blade
meridional curve
parallel genetic algorithm
