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67 The partial turbo-hydraulic/electric propulsion concept was studied by implementing these propulsion architectures in an aircraft with the requirements of A320 aircraft. In Figure 5.12, the total mass of the propulsion system is plotted against the various aircraft configurations. As mentioned previously the TH and TE are abbreviations for Turbo-hydraulic and Turbo- electric propulsion system. The values of percentages from 10% to 18% is the amount of thrust produced by the turbofan engine of the take-off thrust. The two types of methods to de- termine kp, are named as Scholz and Turbomatch. The turbofan engine operation % is also mentioned beside every aircraft concept. The turbo- fan engine operation % should be less than 140% in order to observe a realistic view with the existing technology. Therefore, in the above graph, the bars in red indicate that, it is above the required operation %. The black bars represent that the aircraft are slightly above the required level and orange bars indicate that the aircraft are within the requirement. Observing the Figure 5.12, one can deduce that turbo-hydraulic engines generally weight less than turbo-electric engines. However, the turbo-electric engines have a reduced operation % compared to alternate option. This is the result of high efficiency of the electric motor and components. Although, operation % of turbofan and engine mass of both the kp methods are equal with equal thrust levels, the TSFC of the aircraft differ. This will be explained further in this chapter. One can deduce that with the decrease in thrust level, the mass of the propulsion systems increases. As the thrust produced by the turbofan engine decreases, the motor must provide the remaining required thrust. If the thrust produced by the motor increases, it also re- quired to size the motor and its components according to the lager requirement. Thus, de- creasing the thrust produced by the turbofan engine increase the mass of the overall propul- sion system. Figure 5.13 compares the mass breakdown of the complete propulsion system. The pie chart on the left represents the composition when thrust level is 10% as opposed to 18% on the right. This comparison was made for partial turbo-hydraulic propulsion system. It is evident that contribution of mass for motor and its components decrease from 27% to 7%. However, the total mass of the propulsion system slightly decreases between the two figures. Figure 5.13 Comparison of propulsion systems for thrust levels of 10% and 18%PDF Image | Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion
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