缝式与槽式耦合机匣处理影响压气机性能的研究

Slots and Groove Coupled Casing Treatment for a Transonic Compressor

以NASA Rotor 67为研究对象,首先设计出一个性能较好的轴向缝机匣处理,然后在缝的不同位置处开周向槽,对比分析该耦合机匣处理与轴向缝结构对跨音速压气机的影响。结果表明:原始轴向缝使压气机稳定裕度增大17.51%,但导致最高效率降低了0.54%。在轴向缝的基础上加周向槽,可以增大机匣处理的射流量,并能进一步扩大压气机的稳定裕度。其中,将槽加在缝的尾端时,效果最好,可以使裕度增大22.35%,效率降低0.72%。

The coupled casing treatments have been designed for NASA Rotor 67.These casing treatments can be regarded as the addition of a circumferential groove with the same depth as the basis axial slots,where the groove is located at different relative positions to the slots.According to the numerical results,with the basis axial slots,the stall margin of the compressor was increased by17.51%and the peak efficiency was decreased by 0.54%.With the addition of the single groove on the basis of axial slots,the stall margin has been extended further.When the groove was added at the end of the slots,the best effects can be obtained.With this structure,the stall margin can be increased by 22.35%and the peak efficiency was decreased by 0.72%.