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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion

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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion ( comparison-concepts-classic-jet-propulsion-turbo-electric-pr )

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5.2.3 Overall Comparison Table 5.4 Comparison of aircraft parameters and different aircraft configurations 69 TH-10%-Scholz TH-15%-Scholz TH-16%-Scholz TH-18%-Scholz TH-18%-Turbomatch TH-16%-Turbomatch TH-15%-Turbomatch TE-18%-Scholz TH-10%-Turbomatch TE-16%-Scholz TE-18%-Turbomatch TE-15%-Scholz TE-16%-Turbomatch TE-10%-Scholz TE-15%-Turbomatch TE-10%-Turbomatch π’Žπ‘­ -15% -7% -6% -3% -1% -2% -2% -2% -5% -5% 0% -6% -1% -14% -1% -4% DOC TSFC 0% -24% 0% -12% 0% -10% 0% -5% 0% -2% +1% -5% +1% -5% +1% -5% +1% -10% +1% -10% +1% -3% +1% -13% +2% -5% +2% -26% +2% -7% +3% -13% 𝑻𝑻𝑢 ⁄𝒏𝑬 π’Žπ‘Άπ‘¬ π’Žπ‘΄π‘»π‘Ά +3% +4% +3% +1% +2% +2% +1% +2% +1% +1% +1% +1% +1% +1% +1% +1% +2% +2% +1% +2% +2% +2% +3% +2% +3% +4% +3% +3% +4% +3% +2% +3% +2% +3% +5% +4% +3% +4% +3% +6% +8% +6% +3% +5% +4% +6% +8% +6% Table 5.6 provides a detailed comparison electric/hydraulic propulsion system with A320 aircraft. The comparison is given in % of de- viation from the values of the reference aircraft. The main parameters used to identify the best candidate are fuel burn and DOC as they align with objectives of this research. From the pre- vious sections it is noticeable that TH/TE-10% aircraft have a lower fuel mass, but they can- not be considered due to their turbofan engine operation %. When comparing the inefficiency of TH/TE-18% and improbability of TH/TE-10%, TH/TE-15% & 16% are observed to be good candidates. However, from Figure 5.12, TH/TE-15% is also eliminated. Therefore TH/TE-16% can be considered as ideal candidates and specifically TH-16%-Scholz can be chosen as the best candidate. TH-16%-Scholz is 2% more heavier than A320 in terms of op- erating empty mass but reduces the TSFC by 10%. The benefits of TH are already mentioned in the previous sections. The accuracy of Scholz method can be questioned of all the aircraft analysed for partial turbo-

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