压气机跨音速叶栅叶型的数值模拟  

Numerical value simulation of transonic compressor cascade airfoil

作　　者：张广[1] 徐志晖[1] 陆超[1] 

机构地区：[1]沈阳航空工业学院动力与能源工程学院,辽宁沈阳110136

出　　处：《沈阳航空工业学院学报》2008年第4期26-29,共4页Journal of Shenyang Institute of Aeronautical Engineering

摘　　要：以抑制叶型吸力面激波强度、附面层分离,降低叶型损失为目标,对某型压气机跨音速叶栅叶型进行气动优化。运用数值模拟的方法对比研究优化后的叶栅同原型叶栅在相同工况下的气动性能,概述了气动性能产生变化的机理。与优化前对比发现,优化后的叶型具有低损失,工作范围大的特点。In order to reduce losses of transonic cascade airfoil in a compressor,aerodynamic optimization was made to restrain shock intensity in the suction face and boundary layer separation.The aerodynamic behavior of the optimized airfoil was compared with the original airfoil in the same operating condition using numerical simulation method.The changing mechanism of the aerodynamic characteristic was outlined and explained.The optimized airfoil was found to have lower losses and wider working range.

关 键 词：跨音速压气机 叶型 气动优化 数值计算 

分 类 号：TH45[机械工程—机械制造及自动化]