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8 2 Hybrid-Electric Technology State-of-the-Art and Beyond considered [16] to draw the advantages of each of the system in order to achieve greater system performance to the detriment however of a greater system complexity. 2.1.2 Parallel Hybrid System In a parallel system, the electric motor and the combustion engine are both mounted on the shaft of the propulsive device [20]. A common parallel system approach is realized by installing an electric motor on the low-pressure compressor shaft of a gas-turbine in order to support its operations [25–27]. The source of electrical energy and power to drive the electric motor can be provided by battery or fuel-cell. Parallel hybrid system powered by batteries will be the focus of aircraft sizing and integrated assessment in Section 5.3 and Section 5.4. If integrated to an existing gas-turbine, the concurrent utilization of the electric motor influences the operational characteristics of the gas-turbine. As a result the gas-turbine can be forced to operate into part-load leading to a degradation of its efficiency [27]. The change in gas-turbine efficiency due to different part-power operations resulting from the utilization of an electric motor is demonstrated in Section 5.3. In addition, the change in the operating line of the gas-turbine components can reduce the surge margin. Moreover, detailed system integration analysis are required for the implementation of an electric motor in the environment of a gas-turbine. Another recent approach for a parallel system is the so-called “integrated system” [28, 29]. It consists of electrifying part of the core cycle of a gas-turbine. For instance, the electrification of the high-pressure compressor stages of a gas-turbine was proposed by Schmitz and Hornung [30]. Still in a pioneering phase, few publications are currently available on this topic. 2.1.3 Partial Hybrid System In a partial hybrid system, at least one propulsive device is driven conventionally by a com- bustion engine while the other propulsive devices are driven directly by electrical motors [20]. In order to overcome the challenges related to the operation and integration of a parallel system, a partial parallel hybrid system was proposed by Pornet and Isikveren [31]. The electric motor and the propulsive device named “electrical fan” is integrated in addition to the combustion based engines as indicated in Figure 2.2. Fuel-cells or batteries can be se- lected as energy and power source to drive the electric motors. The integrated performance analysis of this partial parallel hybrid system is assessed in Section 5.5. In view of improv- ing the overall vehicular efficiency, the electrical fans can be distributed to take advantage of distributed propulsion technology through tight aero-propulsive-structural integration. In addition to the potential benefits gained by distributing the electrical fans, this approach of- fers numerous advantages compared to mounting the electric motor on the low-pressure shaft of the gas-turbine. In this partial parallel hybrid system, the design and the operation of the conventional and electrical system are independent. The complex implications resulting from the interactions between the electric motor and the gas-turbine operations are consequently avoided. Moreover, the overall efficiency of the propulsion system can be optimized by op- erating the conventional and the electrical system close to their peak efficiencies. Finally,PDF Image | Conceptual Design Methods Hybrid-Electric Transport Aircraft
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