中文摘要：

实验测量了某高速高负荷压气机叶栅两个马赫数（o5884和0．5）下-8°、6°、-4°、-1．69°、0°、2°、4°和8°共8个攻角的栅后流场，分析了其损失特性随着攻角的变化规律。结果表明：设计马赫数05884下，该叶栅低总压损失系数对应的攻角范围较小，随着攻角往两端偏离最优攻角，叶栅损失很快就急剧增加；从2°到4°攻角，流场结构发生了改变，近叶中区域也开始发生了较大的分离，而近端区的角区分离反而减小，使得总压损失未迅速增加，而是基本不变；随着攻角进一步增大到8°，发展成了全叶高的大尺度分离流动，尾迹速度亏损急剧增大，总压损失也急剧增大。

英文摘要：

The flow features behind a high-speed high-loading compressor cascade was mea- sured under two Mach number conditions （0.5884 and 0.5） both at 8 incidences （-8°, -6°, -4°, -1.69°, 0°, 2°, 4° and 8°）, and the total pressure loss coefficient versus incidence angle was analyzed. It is found that the effective operating range is quite small under tile design Mach immber conditions （Ma = 0.5884）, the performance deteriorates seriously as the incidence deviates from the design condition. The flow structure changes when the incidence switches from 2° to 4°; considerable separation occurs in the mid-span region and the corner separation decreases reversely, resulting in the nearly invariable loss scale rather than speedy increasing. When the incidence increases to 8°, the corner separation no longer stokes in the endwall-caseade corner, but spreads along the spanwise as whole passage stall, with the wake velocity decay and the total pressure loss coefficient increasing dramatically.