跨声速轴流压气机的失速发展机理

Three-dimensional multi-passage numerical simulations on the NASA Rotor 37 were conducted to investigate the evolution process of rotating stall in the transonic axial compressor. The development of the shock and the spillage flow and their impacts on the stall process were analyzed minutely. The results show that only one oblique shock was observed in the passage under peak efficiency condition, and the oblique shock evolved into a detached shock under stall condition. The tip leakage vortex broke down after interacting with the detached shock. With the axial development of the broken tip leakage vortex, because of the adverse pressure gradient, a significant vortex was formed in the middle of the passage. At the beginning of the stall process, the spillage flow appeared intermittently under the influence of the periodical evolution of the blockage region. Accompanied by the decrease of the flow rate, the blockage region extended gradually. At the same time, the spillage flow existed during the whole periodical evolution process of the blockage region, which can be treated as the onset of a rapid deterioration of the flow field.