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❊❧❡❝tr✐❝ ❉r✐✈❡s ❢♦r Pr♦♣✉❧s✐♦♥ ❙2st❡♠ ♦❢ ❚r❛♥s♣♦rt ❆✐r❝r❛❢t ✶✸ ✶✵✳✺✼✼✷✴✻✶✺✵✻ Figure 4. Design chart for hybrid-electric propulsion system in cruise [21] a limiting factor. The optimum sizing of the hybrid-electric propulsion system in view of achieving minimum fuel burn, indicated in the chart by HYCcruise, results in selecting the maximum power of the electric motor which can be used at 100% under the constraint of the 20% SOC limit of the battery. In the context of this analysis, the optimum sizing results in a 13% block fuel reduction compared to the baseline aircraft by installing a total electric motor power of 6 MW and 8400 kg of batteries. Further investigation presented in [21] demonstrated a potential block fuel reduction of 16% when utilizing the electric motor during climb and cruise. The prospects in block fuel reduction depend strongly on the assumption made in terms of battery technology level. For a battery speciïnˇA ̨c energy of 1000 Wh/kg at cell-level,results shown that the potential reduction block fuel were reduced by almost 50% compared to results obtained for 1500 Wh/kg [21]. In view of examining the sizing effects resulting from the integration of hybrid-electric propulsion at aircraft level and of investigating the potential market range application of hybrid-electric aircraft, clean sheet design of hybrid-electric aircraft need to be considered. 4.3. Hybrid-electric clean sheet design A hybrid-electric clean sheet design was investigated on a twin engine narrow body transport aircraft by Pornet et al. [22]. The topological approach of the hybrid-electric propulsion system is identical to the one presented in Section 4.2. Driving an electric motor on the low-pressure shaft has strong influences on the gas-turbine operational characteristics as highlighted in Section 2.1.2. These aspects become more predominant with increasing electric motor power. In order to not modify the contemporary design heuristics of the gas-turbine and to avoid the negative operational influence of the electric motor, the operational strategy selected in this design was to switch-off the gas-turbine during cruise while the electric motor drives by itself the shaft of the propulsor. By equipping only one gas-turbine with an electric motor, the useful degree-of-hybridization Hpuse achieved during cruise is 50%.PDF Image | Electric Drives for Propulsion System of Transport Aircraft
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