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实验测量了某高速高负荷压气机叶栅两个马赫数(0.5884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0.5884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。
Experiments were carried out to measure a total of 8 (8,8 °, -6 °, -4 °, -1.69 °, 0 °, 2 °, 4 ° and 8 °) of a high speed and high load compressor cascade at two Mach numbers (0.5884 and 0.5) After a grid angle of attack of the flow field, the analysis of the loss characteristics with the angle of attack changes. The results show that the range of angle of attack of the low total pressure loss coefficient of the cascade is small with the designed Mach number of 0.5884. As the angle of attack deviates from the optimal angle of attack at both ends, the loss of cascade rapidly increases rapidly from 2 ° To 4 ° angle of attack, the flow field structure has changed, near the middle of the region also began a greater separation, while the proximal region of the angular separation but reduced, making the total pressure loss did not increase rapidly, but basically not As the angle of attack further increases to 8 °, it develops into a large-scale isolated flow with full leaf height. The wake velocity loss increases sharply and the total pressure loss increases sharply.