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70 5 Integrated Performance of Hybrid-Electric Propulsion Systems size the hybrid-electric propulsion system under the constraint of MTOW. Aircraft market study targeting an YEIS 2035 [125] showed that a 900 nm stage length will cover 79% of all world-wide flights in the 180-200 seats segment. This stage length was identified as the maximum utilization stage length of the retrofitted aircraft. Aiming for minimum fuel burn consumption at maximum utilization stage length, this off-design range was selected to size the hybrid-electric propulsion system. An identical flight profile as described in Section 5.1 was attributes to the off-design mission. To maximize the benefits, the batteries are utilized only during the block mission. The mission reserves are flown with fuel only. 5.3.1 Hybrid-Electric Propulsion System Model The aircraft is equipped with advanced geared turbofan engines. The geared turbofan model was developed according to the methods presented in Section 3.2.3.1. It features a bypass ratio of 18 at flow path sizing conditions occuring at TOC conditions under MCL rating. At ISA, FL350, π0.78 conditions and maximum thrust settings, the πππΉπΆ yields 13.25 g/kN/s. In order to facilitate the flexibility required for the hybridization of the propulsion system, it was decided to decouple the integrated geared turbofan power plant model into a modular arrangement of a turboshaft engine and a geared ducted fan device that in combin- ation feature the same properties as the reference geared turbofan. Therefore, a two-spool turboshaft engine model with a booster mounted to the power shaft was set up in GasTurb [95]. Turboshaft intake conditions were iterated to simulate the presence of the frontal geared fan, both, at design and off-design conditions. Turboshaft nozzle pressure ratio was iterated to yield adequate values of core residual thrust. The resulting turboshaft engine model was successfully verified against the reference geared turbofan model taking into account the temperature, pressure and corrected mass flow values at important thermodynamic stations. The turboshaft was integrated at aircraft level according to the methods described in Section 3.2.3.3. The geared ducted fan device was captured using the ducted fan model introduced in Section 3.2.3.2. As part of the integrated aircraft study, the ducted fan and turboshaft engine models were matched appropriately. 5.3.2 Sizing and Integrated Performance Analysis The sizing and integrated performance of the retrofit aircraft equipped with a parallel hybrid- electric propulsion system is assessed in the following. The analysis aims at exploring the design space related to the implementation of the parallel hybrid-electric propulsion system at aircraft level. The objective is to size the system in order to achieve the largest reduction in block fuel against the reference aircraft. The design parameters and constraints involved in the sizing of the hybrid-electric propulsion system are indicated in Figure 5.3. In this figure, the relative change in block fuel compared to the reference aircraft is assessed by sizing and utilizing the electric motor for cruise only. The other segments like takeoff, climb and the reserves are performed with the conventional combustion engines only. The design parameters indicated are the total installed maximal power of the electric motor ππΈπ,πππ₯ and the power setting of the electric motor in cruise. 0% meaning that the electric motor isPDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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