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Chapter 5 Integrated Performance of Hybrid- Electric Propulsion Systems With regards to the potential evolution of battery technology discussed in Section 2.2.3.1, fuel-battery hybrid-electric system is viewed as a promising topology towards the achieve- ment of the future aviation goals highlighted in Section 1. The feasibility and the potential benefits of fuel-battery propulsion system need to be assessed at aircraft level. The integrated performance of fuel-battery hybrid-electric propulsion system is examined in this chapter on the narrow-body transport aircraft segment represented by the class of the Airbus A320 or Boeing B737. By equipping the conventional gas-turbines with an electric motor powered by batteries, the retrofit of a narrow-body transport aircraft with a parallel hybrid-electric propulsion system is analysed first in Section 5.3. In order to gain more insights into the sizing heuristics and design axioms of hybrid-electric aircraft, the investigation of hybrid- electric narrow-body clean sheet designs are evaluated in Section 5.4 and in Section 5.5. In Section 5.4, the sizing and performance implications of a parallel hybrid-electric system are investigated by sizing the aircraft for increasing design ranges and according to different levels of battery technology. The integrated performance of a partial parallel hybrid-electric propulsion system is evaluated in Section 5.5 on a narrow-body transport aircraft featuring a quad-fan arrangement. The integrated performance are examined in terms of change in air- craft weight, potential block fuel reduction and change in vehicular efficiency. Moreover, the implications of hybrid-electric propulsion system on flight technique optimality are analysed. In view of the integrated performance, design heuristics and suitable market range segments are evaluated for the application of fuel-battery hybrid-electric narrow-body transport air- craft. 5.1 Aircraft Top-Level Requirements and Sizing Guidelines The ATLRS, the design mission and the sizing guidelines specified for the design of the hybrid- electric transport concepts investigated in this chapter are highlighted in the following. For these aircraft studies, the YEIS is set to 2035. Consequently, the hybrid-electric propulsion 65PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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