Tianyu Pan

TL;DR: In this article, a new design of casing treatment (axisymmetric arc-shaped slot casing treatment) is investigated to enhance the stall margin of a transonic compressor whose instability is initiated by partial surge.

TL;DR: The results indicate that the phase difference and the angle of attack are highly correlated with the unsteady fluid field around the dragonfly’s wings and body, which determines the generation of aerodynamic forces.

TL;DR: In this article, a non-uniform stator loss reduction design strategy was employed to make a redistribution of stator incidence at the compressor off-design working point so as to reduce the potential separation loss and enhance the stage aerodynamic performance.

TL;DR: In this article, the detailed stall evolution was studied using full-annulus unsteady simulations, which correctly predicted several key characteristics observed in the previous experiments: (1) the stall precursor is initiated in the stator hub region; (2) the initial disturbance is axisymmetric; (3) asymmetric rotating disturbance is developed afterwards.

TL;DR: In this paper, the effect of inlet blade loading on the rotating stall inception process is carried out on a single-stage low-speed axial compressor, and the temporal pressure signals from the six high response pressure transducers are used for the analysis.