Design of Hydrogen Solid Oxide Fuel Cells in Blended-Wing–Body Aircraft

This paper presents the design methodology for integrating a hydrogen solid oxide fuel cell/gas turbine (SOFC/GT) propulsion system into a blended-wing–body (BWB) aircraft and tube-and-wing (T&W) configurations for 365 and 162 passengers. The design methodology utilizes aircraft sizing and modeling tools that encompass aerodynamic properties, structural design, and powertrain integration. The proposed hydrogen BWB and T&W aircraft are compared against conventional models like the B777-300ER and B737-800. Key results indicate significant reductions in fuel consumption and emissions. For instance, the hydrogen BWB aircraft, on average, exhibits a 56% reduction in Megajoule of fuel energy consumption per passenger-kilometer compared to conventional aircraft. The analysis highlights the environmental benefits, with [Formula: see text] equivalent emissions per passenger-kilometer being significantly lower for hydrogen-powered models. The total takeoff weight per passenger for the hydrogen BWB-365 is 714 kg, compared to 916 kg for the conventional B777-300ER. Hydrogen aircraft configurations, on average, also show a 21% increase and 99.48% decrease in [Formula: see text] and [Formula: see text] emissions. Moreover, hydrogen BWB configurations exhibit reduced emissions compared to hydrogen T&W despite higher takeoff weights. This study underscores the potential of hydrogen SOFC/GT systems and BWB configurations to enhance efficiency and reduce the environmental impacts for future aircraft.