<p>This study examines the conceptual design of a next-generation hydrogen-fueled turbofan engine, focusing on potential technological advancements beyond 2030. The primary objective is to evaluate the impact of different heat exchanger configurations on thrust-specific fuel consumption, engine mass, and core size. The study utilizes the Aircraft Propulsion System Simulation program, developed by Bauhaus Luftfahrt, to validate engine performance models and assess the impact of hydrogen as a fuel. A hydrogen-powered engine, comparable in size and thrust output to the PW1100G is analyzed based on key operating parameters. Additionally, the study examines the integration of hydrogen pre-conditioning heat exchangers and the optimization of the thermodynamic cycle to enhance efficiency and overall engine performance. The findings indicate a 2.5% reduction in thrust-specific fuel consumption, resulting in a 5% improvement in overall engine efficiency when transitioning from kerosene to hydrogen. This efficiency gain is accompanied by a 6% increase in bypass ratio, resulting in a more compact engine core. A detailed analysis of heat exchanger placement reveals that a recuperator heat exchanger achieves lower fuel consumption, compared to an intercooler. Specifically, placing the heat exchanger at the nozzle reduces thrust-specific fuel consumption by an additional 3%. Hydrogen-fueled turbofan engines offer significant potential for improving propulsion efficiency and enabling higher bypass ratios. The recuperator heat exchanger strikes an optimal balance between fuel efficiency and technological readiness, making it a strong candidate for future hydrogen-powered aircraft.</p>