Gas turbines, particularly those in aircraft propulsion, represent a cutting-edge engineering field. Although advances in cooling technologies and materials have led to mechanical efficiency above 90 percent, economic and physical constraints limit future increases. As a result, improving machine performance still heavily relies on minimising aerodynamic losses. Among these, secondary-flow-induced losses — arising from the complex interaction between the main passage flow and endwall boundary layers — still represent a challenge in the design phase. Despite empirical correlations and simplified models, no comprehensive analytical framework currently exists to quantify accurately these losses across different design configurations. This thesis develops a Python-based computational tool that automates the three-dimensional aerodynamic analysis of turbine cascades through NUMECA Cadence FINETurbo software.