The numerical simulation research of civil aviation engineer internal flow stability

Abstract Steady three-dimensional numerical simulations have been used for the civil aviation engineer model to research internal flow stability. A comparison of the numerical method with empirical data validates the accuracy of CFD predictions, revealing a high level of agreement between the two. The simulation of the internal flow field indicates that the tip leakage vortex retains its form in the downstream area beyond the shock wave, achieving peak efficiency, while maintaining a stable vortex vector direction. When the vortex nears a stall condition, vigorous interaction between the vortex and the shock wave leads to the disintegration of the vortex, resulting in a spiral formation. The presence of a low-energy fluid region at the rotor blade’s tip is attributed to the intrusion of the leakage vortex, which may trigger flow instability. The characteristics of this phenomenon resemble those of rotational instability, highlighting the intricate nature of the flow dynamics.