喉道对压气机超声叶栅流态及性能的影响

doi:10.7527/S1000-6893.2016.0195

Abstract

Abstract:

To have a better understanding of the flow mechanism of the supersonic cascade, the effect of throat on supersonic cascade's shock-wave configuration and performance is studied through numerical simulation and theoretical analysis. Cascade ARL-SL19, Cascade CM-1.2 and Cascade SM-1.5 are taken as the object of the study. The results show that there are two kinds of steady working states for the supersonic cascade:starting state and overflow state. When the inlet Mach number is high, the supersonic cascade works in the starting state; when the Mach number is low, the supersonic cascade works in the overflow state. There is a Mach number range, and the supersonic cascade works in the state the same as the previous state. The aerodynamic throat is determinant in near stall pressure-ratio for the C-shaped supersonic cascade with divergent channel at lower supersonic, but the real throat is determinant for S-shaped supersonic cascade with convergent channel. If it is caused by the aerodynamic throat, the overflow achieves less loss and greater margin, and the inlet Mach number and the flow angle are influenced by the outlet pressure. If it is caused by the real throat, the overflow achieves more loss and smaller margin, and the cascade still works in the unique incidence.

Key words: supersonic cascade, cascade throat, starting state, overflow state, shock-wave structure, unique flow angle

CLC Number:

V231.3

JIANG Xiong, QIU Ming, FAN Zhaolin. Effect of supersonic compressor cascade throat on flow pattern and cascade performance[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(3): 120308-120308.

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Effect of supersonic compressor cascade throat on flow pattern and cascade performance

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