Abstract:
With growing environmental concerns, hydrogen is being promoted as a clean fuel of the
future for sustainable aircraft application. In this context, a multi-parametric optimization
and gas path analysis of a civil turbofan aeroengine operating on hydrogen fuel has been
presented in this thesis. Key design parameters including the bypass ratio, fan and
compressor pressure ratios, turbine inlet temperature, and mass flow rate of the air have
been evaluated in GasTurb software to obtain an optimal performance and gas path design of the aeroengine. A comparative analysis has been performed between the baseline hydrogen fueled turbofan (based on the General Electric GE90 high-bypass turbofan) and the optimized hydrogen fueled turbofan aero-engines at cruise condition as design point. As a result, the optimized hydrogen fuel-based turbofan aero-engine delivered a 4.88% decrease in thrust-specific fuel consumption and an increase in thermal efficiency by 5.53%. Furthermore, an optimized gas path for an aeroengine operating on hydrogen fuel exhibits a 6.35% smaller core area and a shorter engine length by 10.84% compared to the baseline. A theoretical and engineering platform for design and valuation of hydrogen fueled civil turbofans is thus established.
