In the modern aviation, the turbofan engines are widely used, particularly in the commercial sector. Constant improvements in terms of thermodynamic and propulsive efficiency are essential to reduce in-flight emissions and operational costs. To achieve this outcome, every primary component of the propulsive system must be specifically designed and optimized. With this as the primary objective, an axial turbine is analyzed in this study. These machines are involved into the extraction of energy from a flowing stream of hot gas. As the fluid proceeds, flowing through the turbine, the rotation blading extracts work in the form of mechanical energy. Since the process is not ideal, various types of energy dissipation occur which include not only thermodynamic losses due to irreversibilities in the cycle but also aerodynamic losses and mechanical friction.