Study of Hybridization Level for Propulsion System in Multi-Megawatt Turboprop Aircraft

Abstract This paper presents a comprehensive approach to the sizing of parallel hybrid propulsion systems for multi-megawatt aircraft, with a specific focus on baseline turboprop aircraft. By exploring key performance variables such as power distribution, system efficiency, or fuels and aircraft weights. The study provides a detailed analysis of how these factors influence overall hybrid aircraft performance. Special attention is given to the impact of these variables on range and fuel consumption, aiming to quantify potential fuel savings and range improvements under different operating conditions. The paper investigates the level of hybridization at various phases of flight, such as take-off, climb, cruise, and descent, seeking to optimize the distribution of power between the electric power train (fuel cell sizing) and gas turbine propulsion systems. By evaluating different scenarios and performance sensitivities, the study aims to identify optimal design strategies for enhancing both efficiency and sustainability in future aircraft propulsion systems. The findings contribute to a better understanding of how hybrid-electric technologies can be integrated into next-generation turboprop aircraft, with implications for reducing emissions and quantify impact on top level aircraft requirement.