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Aerospace 2018, 5, 123 Aerospace 2018, 5, x FOR PEER REVIEW 13 of 21 Aerospace 2018, 5, x FOR PEER REVIEW 4.2. Configuration with Engine_3 13 of 21 The smallest gas turbine (Engine_3) is considered, in this last simulation, to investigate the The smallest gas turbine (Engine_3) is considered, in this last simulation, to investigate the feasibilityoffwoorrkkininggmoorereininelelcetcrtircicmmodoed,ew, withiththethaeimaimoforefdruedciuncginegmeismsiosnsiso.nIsn.FIinguFrieg1u6r,et1h6e, feasibility of working more in electric mode, with the aim of reducing emissions. In Figure 16, the thermodynamic cycle is shown at fixed point. thertmheordmyondaymniacmcyiclceyicsleshisowshnowatnfiaxtefidxpeodinpto.int. Figure 166..TThheermrmooddyynnaamicicccyycclelefoforrEEnnggininee__33aattththeeddeessigignnppooinintt.. Figure 6. Thermodynamic cycle for Engine_3 at the design point. The calculations with Engine_3 have been made (Figure 17) in the only case of minimum The calculations with Engine_3 have been made (Figure 17) in the only case of minimum fuel The calculations with Engine_3 have been made (Figure 17) in the only case of minimum fuel fuel consumption mode in cruise phase (Figure 18), avoiding a wide increase of TIT temperature, consumption mode in cruise phase (Figure 18), avoiding a wide increase of TIT temperature, not consumption mode in cruise phase (Figure 18), avoiding a wide increase of TIT temperature, not acceptable for turbine blades. acceptable for turbine blades. not acceptable for turbine blades. As is possible to observe, the degree of hybridization for energy, defined in (6), is equal to 30% higher than the value obtained with Engine2_SFCmin, equal to 2.3%. This implies a natural higher than the value obtained with Engine2_SFCmin, equal to 2.3%. This implies a natural higher than the value obtained with Engine2_SFCmin, equal to 2.3%. This implies a natural reduction ofCO andNO emissions,asunderlinedinTable5.Incontrast,thishybridconfigurationrequires reduct2ion of COx2 and NOx emissions, as underlined in Table 5. In contrast, this hybrid configuration reduction of CO2 and NOx emissions, as underlined in Table 5. In contrast, this hybrid configuration requires an energy significantly higher from the electric system and, consequently, an excessive requires an energy significantly higher from the electric system and, consequently, an excessive weight of the batteries on board that makes this configuration not acceptable in the current aircraft weight of the batteries on board that makes this configuration not acceptable in the current aircraft arrangement. arrangement. = (πΈπΈπΈπΈπΈπΈπ€π€πΈπΈπΈπΈ πππΈπΈπππππΈπΈπ€π€πΈπΈπΈπΈπππΈπΈ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ1 π€π€πΈπΈππ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3) π»π»πππΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3 = (πΈπΈπΈπΈπΈπΈπ€π€πΈπΈπΈπΈ πππΈπΈπππππΈπΈπ€π€πΈπΈπΈπΈπππΈπΈ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ1 π€π€πΈπΈππ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3)π‘π‘π‘π‘π‘π‘π‘π‘ πππππππ‘π‘ππ ππhππππππ Γ π»π»ππ π‘π‘π‘π‘π‘π‘π‘π‘ πππππππ‘π‘ππ ππhππππππ Γ (6) πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3 (πΈπΈπΈπΈπΈπΈπ€π€πΈπΈπΈπΈ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3) +(πΈπΈπΈπΈπΈπΈπ€π€πΈπΈπΈπΈ πππΈπΈπππππΈπΈπ€π€πΈπΈπΈπΈπππΈπΈ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ1 π€π€πΈπΈππ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3) (πΈπΈπΈπΈπΈπΈπ€π€πΈπΈπΈπΈ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3)πππ‘π‘πππππ‘π‘ππππ+(πΈπΈπΈπΈπΈπΈπ€π€πΈπΈπΈπΈ πππΈπΈπππππΈπΈπ€π€πΈπΈπΈπΈπππΈπΈ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ1 π€π€πΈπΈππ πΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈπΈ_3)π‘π‘π‘π‘π‘π‘π‘π‘ πππππππ‘π‘ππππ ππhππππππ πππ‘π‘πππππ‘π‘ππππ π‘π‘π‘π‘π‘π‘π‘π‘ πππππππ‘π‘ππππ ππhππππππ (6) 13 of 21 1600 1600 1200 1200 800 800 400 400 0 0 0 2000 0 2000 Time[s] 4000 6000 Time[s] 4000 6000 Engine1 Engine1 Engine3_SFCmin Engine3_SFCmin Figure 17. Power vs time of the Engine_3. Figure 17. Power vs time of the Engine_3. As is possible to observe, the degree of hybridization for energy, defined in (6), is equal to 30% As is possible to observe, the degree of hybridization for energy, defined in (6), is equal to 30% Powerrdelliviverred[[kW]]PDF Image | Turboprop Hybrid Electric Propulsion System
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