Parametric study of the effects of a non-uniform flow on a circular section of a compressor blade cascade

This thesis presents a parametric study of the effects of distorted inflow on a circular section of a blade row, with the aim of investigating how variations in the incoming flow influence the aerodynamic behaviour and performance of the blades. The non-uniform inflow is generated by imposing a pressure deficit over a sector of the circumferential domain. The analysis is performed on a mid-span section of a transonic fan blade row, providing insights into the flow dynamics of the overall compressor under this type of distorted flow condition. Several outlet operating pressures are considered in order to investigate a range of conditions, while different sector amplitudes are analysed to assess varying levels of distortion severity. Integral performance parameters are evaluated over the last two revolutions of the simulation in order to consider only stable results. The results provide useful insights into mechanisms associated with non-uniform inflow conditions, contributing to a better understanding of blade row behaviour under realistic operating scenarios. The adopted quasi-2D configuration is intended to provide a preliminary assessment of the phenomenon, allowing meaningful results to be obtained before performing full three-dimensional simulations, thereby reducing computational cost and time.