CFD study of the response to inlet distortion of a quasi-2D transonic fan cascade

This thesis presents a Computational Fluid Dynamics (CFD) study of the aerodynamic response of a quasi-two-dimensional transonic fan cascade subjected to an inlet flow distortion. The numerical investigation focuses on analyzing the impact of non-uniform inlet conditions on the cascade performance and flow field characteristics. First a steady single passage simulation is performed to study the correct RANS model to be applied, then full annulus unsteady simulations are performed to capture the interaction between inlet distortions, shock structures, boundary layer behavior, and loss generation. Key aerodynamic parameters such as pressure distribution, total pressure loss, isentropic efficiency and flow deviation are evaluated and compared with a reference uniform inlet condition. The results provide insight into the sensitivity of transonic fan cascades to inlet distortions and contribute to a better understanding of the underlying flow mechanisms relevant to modern aero-engine applications (BLI propulsion).