高亚音速大折转角叶型内激波结构与损失分析  

Analysis of Shock Structure and Loss in High Subsonic Stationary Cascades with Large Camber Angle

作　　者：侯宪科 姜斌[2] 

机构地区：[1]通用电气-哈动力-南汽轮能源服务(秦皇岛)有限公司,河北秦皇岛066206 [2]哈尔滨工程大学动力与能源工程学院,黑龙江哈尔滨150001

出　　处：《节能技术》2013年第3期213-216,238,共5页Energy Conservation Technology

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.

关 键 词：压气机 激波结构 叶型损失 大折转角 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]