跨声速压气机转子旋转失速现象的非定常模拟

doi:10.7527/S1000-6893.2017.721524

Abstract

Abstract:

To investigate the mechanism of the stall inception of transonic compressor rotor,an annulus unsteady numerical simulation is performed. Results show that the stall inception of this rotor is spike-type. "Rotating instability" (RI) occurs in the tip region when the compressor is operating in the low mass flow region. During the compressor's throttling, the mass flow rate through the rotor decreases, and the amplitude of the tip vortex oscillation increases significantly. Under near stall condition, the "radial vortex" of the RI cells causes large blockage in the tip region, leading to a spillage of tip-clearance flow to the adjacent blade passage ahead of the rotor leading edge intermittently. When the compressor is throttled further, the blade loading exceeds its maximum, and the higher static pressure pushes the fluid originating from the tip-clearance region of one blade to move across the blade passage into the neighboring passage by passing around the trailing edge. When these flow events (spillage of tip-leakage flow at the leading edge and tip-clearance backflow at the trailing edge) occur at the same time, spike disturbance is generated. The formation of the stall inception is the "radial vortex", which moves circumferentially along the leading edge line.

Key words: transonic compressor, unsteady flow, rotating stall, spike disturbance, rotating instability

CLC Number:

V235.13

FU Lei. Unsteady simulation of rotating stall in a transonic compressor rotor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(S1): 721524-721524.

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Unsteady simulation of rotating stall in a transonic compressor rotor

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