弯曲动叶对跨音轴流压气机性能的影响

EFFECTS OF CURVED ROTOR ON THE PERFORMANCE OF AXIAL FLOW TRANSONIC COMPRESSOR

对具有弯曲动叶的跨音轴流压气机性能的数值研究表明,反弯曲动叶中通道激波沿径向倾斜角度最大,在顶部移向下游,在中部移向前缘,提高了失速裕度,但也增加了中部损失,反弯曲动叶级效率最低。正弯曲动叶中通道激波在顶部前移,失速裕度下降,通道激波近似为径向,负荷沿叶高分布均匀,气动效率最高。通道激波位置合理分布是弯曲动叶改型设计成功的关键。

The numerical simulation of the performance of axial flow transonic compressor shows that compared to the baseline, the passage shock in the negatively curved rotor moves downstream near the tip, which improves the surge margin of the compressor while moving upstream near the midspan, increasing the energy loss there, so the compressor stage with negatively curved rotor has the lowest efficiency. The surge margin of the compressor with positively curved rotor decreases as the passage shock moves upstream near the tip. The uniform distribution of aerodynamic load along the blade height due to the nearly radial distribution of passage shock makes the stage with positively curved rotor have the highest efficiency. The reasonable distribution of the shock in the rotor passage is the key of better use of curved rotor to improve the performance of axial flow transonic compressor.