摘要
本文采用组合多项式曲线构造了具有高亚音进口条件的大折转角压气机静叶叶型,探索了进一步提高跨音速压气机负荷时,静叶根部区域可能存在的激波结构和损失特征。采用数值模拟方法对不同条件下的高亚音速大折转角压气机叶栅流场进行了数值模拟,结果表明:叶栅内的激波结构与进口马赫数、攻角以及叶型的转角等参数密切相关。通过对叶栅出口的损失分析发现,激波与附面层相互作用改变了原有附面层内的损失分布规律,形成了由激波强度和位置所决定的沿叶片表面法线方向大小基本不变的高损失区域,叶型损失的大小和激波与吸力面最低压力点之间的相对位置密切相关。
Combined polynomial curve was selected to form the profile of compressor stator with large turn-ing angel in this paper to explore the shock structure and loss characteristic near the region of stator hub when aerodynamic loads increase further for transonic stage of compressor. The flow filed in high subsonic stationary cascades with large camber angle is investigated with different conditions by numerical simula-tion methods. The results show that the shock structure in cascades is relied on inlet Mach number, inci- dence angle and camber angle. The interaction between shock and boundary layer change the loss distri- bution laws of boundary layer, and a high loss region determined by the intensity and position of shock which is constant along the normal direction of blade surface is shown through the loss analysis at cascade outlet. The profile loss is associated intimately with relative position between the shock and lowest pres-sure position on suction surface.
出处
《节能技术》
CAS
2013年第3期213-216,238,共5页
Energy Conservation Technology
关键词
压气机
激波结构
叶型损失
大折转角
compressor
shock structure
profile loss
large camber angle
