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5.5 Partial Parallel Hybrid Clean-Sheet Design 93 duction in fuel flow with increasing π»ππ’π π, thus the change in aircraft mass becomes less pronounced during cruise. 5.5.2.4 Take-Off Performance Change Versus the Degree-of-Hybridization for Useful Power The evolution of the take-off performance according to increasing π»π π’π π was assessed in Por- net and Isikveren [31]. Take-off performance was analysed according to the assumption that the one engine inoperative (OEI) case results from a failure of the critical geared-turbofan only, whereas the electric fans are still operating according to the electric motor power avail- able and the off-design characteristics of the ducted fan. As the electrical fans produce a smaller thrust contribution during takeoff, a failure of the geared turbofan is the critical case. Moreover, this assumption can be legitimized by the knowledge that electrical components would exhibit a greater level of reliability. 110 100 90 80 70 60 50 40 30 20 10 0 0 10 20 30 40 50 60 Degree of hybridization for power, HpUSE [%] Study Settings: TOFL/TOFLATLeRs Point performance: takeβoff ISA, SL, Mach 0.2 T/WAEO Design range1300 n.mi T/WOEI ebattery = 1.5kWh/kg Figure 5.20: Takeoff field length, thrust-to-weight ratios of all-engine operational and one engine inoperative conditions against degree-of-hybridization for useful power for a design range of 1300 nm. Geared-turbofan cruise throttling [31]. Increasing the thrust contribution of the electric fans during take-off compared to the geared- turbofans enhances the OEI take-off performance. This is visualized by plotting in Figure 5.20 the evolution of the OEI thrust-to-weight ratio π/ππππππΈπΌ against π»ππ’π π at a given take-off condition (ISA, SL, M0.20). The variation of the ratio between the TOFL and the TOFL limitation of 2200 m stipulated by the ATLRS in Section 5.1 reflects the scenario employed for the sizing of the electric motors as discussed in Section 5.5.1.2. As the TOFL is not a critical sizing criterion up to an π»ππ’π π of 50%, it is an outcome of the overall siz- ing process. According to the other active sizing criteria, the TOFL increases up until the TOFL requirement defined in the ATLRS is reached. Consequently, the all engine operative Value in percent [%]PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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