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Turboprop Hybrid Electric Propulsion System

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Turboprop Hybrid Electric Propulsion System ( turboprop-hybrid-electric-propulsion-system )

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Aerospace 2018, 5, 123 Aerospace 2018, 5, x FOR PEER REVIEW Engine Model Table 3. Gas turbine parameters. Table 3. Gas turbine parameters. 11 of 21 11 of 21 Air mass flow (kg/s) Pressure ratio 4.1. Configurations with Engine_2 6.7 6.0 12.1 12.5 5.3 11.0 MaExngPionweeMr (okdWel) Weight (kg) PW120A14(9E1ngine1) Eng1i2n6e8_2 417 270 Max Power (kW) 1491 1268 930 Power density (kW/kg) 3.6 4.7 3.7 Weight (kg) 417 270 251 ESFC (kg/kWh) 0.286 0.267 0.300 Power density (kW/kg) 3.6 4.7 3.7 Air mass flow (kg/s) 6.7 6.0 5.3 ESFC (kg/kWh) 0.286 0.267 0.300 Pressure ratio 12.1 12.5 11.0 PW120A (Engine1) Engine_2 Engine_3 Engin93e0_3 251 4.1. Configurations with Engine_2 A first comparison between the Engine_2 and the PW120 gas turbine (Engine1) has been made, in terms of fuel consumption and emissions. The hybrid configuration with Engine_2 presents two − − − − the gas turbine (Engine_2) keeps the same shaft power of the Engine1 (900 kW), which could A first comparison between the Engine_2 and the PW120 gas turbine (Engine1) has been made, in terms of fuel consumption and emissions. The hybrid configuration with Engine_2 presents two different operating conditions during the cruise phase: different operating conditions during the cruise phase: the gas turbine (Engine_2) keeps the same shaft power of the Engine1 (900 kW), which could allow the use of a permanent magnet synchronous electrical motor (PMSM) only during the allow the use of a permanent magnet synchronous electrical motor (PMSM) only during the take-off phase; take-off phase; the gas turbine (now named Engine2_SFCmin) delivers a lower power that corresponds to the the gas turbine (now named Engine2_SFCmin) delivers a lower power that corresponds to the minimum specific fuel consumption of 760 kW (Figure 13). In this case, the electrical motor makes minimum specific fuel consumption of 760 kW (Figure 13). In this case, the electrical motor up for the power gap (Figure 14). makes up for the power gap (Figure 14). Figure 13. Speciiffiic fuel consumption vs power delivered at cruise altitude (5516 m). Engine_2. The results obtainedinFigure11,,ofthepowerdelliivered,,areuseffullttobuiilldtthehybrriidssysstteem.. InFigure1155,,ththeespspeceicfiicficfufeuleclocnosnusmupmtipotnio(nBS(FBCSF)Cis)shisoswhnowinnthineTth/eOTa/nOdacrnudiscerpuhisaesepsh:ainsebso:tihncbaostehs, cwaistehs,smwiatlhlesrmgalsleturrgbaisnetu(rEbningein(eE_n2gained_E2nagnidneE2n_gSiFnCem2_iSnF),Ctmheinv)a,ltuheivsalluweaiyssahlwigahyesrhthigahnetrhtehaonethoef othneEonfgitnhe1.EAnsgienxep1e.ctAeds, eaxtptheectcerdu,isaetpthaesec,raulioseweprhvaaselu,eaislobwtaerinevdalwueithisthoebEtanigniende2w_SiFthCmthine Ewnitghinre2sp_SeFctCtmo itnhewEitnhgirneesp_2e.ct to the Engine_2. A comparison in terms of NOx and CO22 amounttssiiss rreporrtteed iin Table 4, where the changes in percentage respect to the base case (Engine1) are written. The variation ∆Δ2% and ∆Δ2_SFCmin% are calculated for each ffllight phase to individuate the critical situation. From the results carried out, it is clear how Engine_2 and,, especiallly, Engine2_SFCmin,, foresee the use of a larger battery pack to the detriment offtthheeppayaylolaodad. A. As esxepxepcetecdte,da,saigsniigfinciafnictainmtpirmovperomvenmt einteirnmtseormf esxhoafuesxtheamuisstsieomnsiscsoiounlds cboeualcdhbievaecdhbieyvewdobrkyinwgoirnkihnygbirnidhcyobnrfiidgcuornatfiognu,reavtieon,deuvreingdtuhreincgrutihse cprhuaise.phase.

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