间隙变化对压气机静叶叶栅气动性能的影响

doi:10.7527/S1000-6893.2016.0066

Abstract

Abstract:

In this paper, a linear compressor cascade is used to experimentally investigate the influence of clearance variation on the flow structures and cascade aerodynamic performance at the highly negative angle of attack, design condition and corner stall condition. The association between the flow structure and cascade performance is also analyzed. The experimental results show that the influence of clearance variation on flow structures and cascade performance is different at different working conditions. At highly negative angle of attack, a pair of three-dimensional separation vortexes near the pressure-side leading edge is originated from the end wall in different clearance cascades. With the increase of clearance size, the cascade total pressure loss decreases, and the clearance side cascade turning ability is slightly increased. At design condition, a slight corner separation exists between blade suction surface and end wall. By bringing in a small clearance (0.2% span), corner separation is first aggravated. As the clearance size continues to increase, the corner separation can be eliminated, and leakage vortex is formed. With the increase of clearance size, the cascade total pressure loss first increases, then decreases and finally goes up again. The elimination of corner separation will improve clearance side cascade flow turning ability. At corner stall condition, the introduction and increase of clearance can impair and eliminate the corner stall structure, and thus the cascade loss decreases and reaches the minimum value with a 0.5% span clearance size. But the cascade loss almost remains the same as clearance continues to increase. Flow structures at both enwalls can influence each other as clearance varies, and the change trends of performance near two end walls are opposite. By comparing the overall cascade aerodynamic performance at all working conditions, the 0.5% span clearance cascade shows an optimal performance.

Key words: compressor, linear cascade, stator, aerodynamic performance, off-design condition, leakage flow

CLC Number:

V211.7

WANG Zinan, GENG Shaojuan, ZHANG Hongwu. Influence of clearance variation on aerodynamic performance of a compressor stator cascade[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(11): 3304-3316.

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Influence of clearance variation on aerodynamic performance of a compressor stator cascade

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