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Aerospace 2018, 5, 123 3 of 21 Aerospace 2018, 5, x FOR PEER REVIEW 3 of 21 entry-into-service 2035, are discussed in [20]. As previously mentioned, the present paper investigates previously mentioned, the present paper investigates the feasibility of the hybrid propulsion system the feasibility of the hybrid propulsion system for a regional aircraft, considering different turboprop for a regional aircraft, considering different turboprop sizes and performance; the impact of electric sizes and performance; the impact of electric power-train has been analyzed in terms of number of power-train has been analyzed in terms of number of non-revenue passengers. non-revenue passengers. 2. Choice of Hybrid Propulsion Conffiiguration Dependingonthevariantoffhybrriideelleeccttrriiccaairirccrraaftftccoonnssidideereredd,,ththeeththruruststmmayaybebeprporvoivdieddedvivaia acocmombibniantaiotinonofogfagsastuturbrbininesesaannddeelelecctrtircicaallpprrooppuulslsoorrss,,oorroonllyviiattheellectricalpropulsors,oronly viathethermalengiinedurriinggaassppeeccifiificcseseggmmeennttooffththeeflfligihgth.tO. nOenoefotfhtehmeomstostigsnigifnicifiancatnbtenbefnitesfiotsf aofhayhbryibdricdoncfoingfiugrautrioantioisntihsethfleeflxiebxiilbitiylitiynionpoepraetriaotnio.nT.heThtoeptolpoogliocgailcoapltoipontisonfosrfothrethaeppaplipcalitcioantionf eolfeectlreictrdicrivdersivteosthtoetphreopurolspiounlssioynstesmystoefmairocfrafirtscrarfetsmaarienmlyatiwnoly:stewrioe:ssaenrdiepsarnadlleplahryabllreildh.Iynbrthide. sInertiheessceorniefisgcuornafitigounr,athioenp,trhoepeplrloepreslhlearftshisafotnislyondlryivdernivebnybtyhethelecletrcitcrimcmototrosr.sI.nInggeenneerraal,l,tthegas turbine is used to either charge the batteries or provide auxiilliiary powerr tto driive tthe ellecttrriicc mottorr.. This, combined with the need for a generator, implies that this topology is heavier than a parallel one. IInttheepaarraallelelltotoppoolologgyy,,ththeeininteternrnaallccoommbbuustsitoionnenengginineeanadndthteheprporpoeplelellreraraerecocnonencetectdedvivaia raigridgidshsahfta.ftT.hTishsishasfhtatfutrtnusrnthsethreotrortorf othfetheleecltercictrimcomtort/ogre/ngeernateorrattohrrothurgohugwhhiwchiicthpiatspseas,seas, sahsoswhonwin iFnigFuigreur1e. 1A. nAandavdavnatangtaegoefotfhtihsiscocnofnigfiugruartaiotinonisisththatatititrreequirireess onlly two propulsion devices, where either the electric motor and/orr the gas turbine can be downscaled, determining a weight reducttiionwiitthrreessppeecctttotoththeeseserireisescoconnfifgiugruartaiotino.nR. Regeagradridnigngthtehheyhbyrbidripdapralrlaelleplopwoewr-etra-tirnaionf oanf anircariarfctr,atfht,etohpeeorapteinragtimngodmeoisdqeuiistequdiftfeerdeinfftewreintht wreistphecretstpoeacutttoomaoutitvoemaoptpivleicatpiopnli:ciantifoanc:t,indufeactto, dthueehtiogthhpeohwigehrpreoqwueirerdeqduiriendgdthueriflnightht,eufsliugahltl,y,utshueaelllye,cthriecemleocttorricmoodteorismnodtefeiassnibolte.feasible. For the above reasons, with the aim of investigating a new low CO2 emission propulsion system 2 for arreeggioionnaallaiaricrrcarfatftutrubrobporporpopenegningein, ea,parpaallreallhleylbhryidbrciodnficognufriagtuiornatisonchiossecnhoinsetnheinprtehsenptrwesoernkt. wInoprka.rtIincuplar,titchuelahry,btrhied hpyobwreidr-tproaiwnepr-etrfaoirnmpaenrcfoerims aconncesidiserceodnsaidceormedbianecdomboidnedumriondgetadkuer-ionfgf taankde-colifmfabnpdhcalsime,banpdhaosnel,yatnhdeotunrlbyitnheemtuordbeindeumrinogdecrduuisreinagncdrulainsedaingd.lDanudriing.crDuuisrein,igfcthrueirseq,uifirthede preoqwueireidsbpeolwowertihsebpeolowerthoeftphoewmeraxoifmthuemmeaffixcimienucmyepfoficniteonfcythpeotiunrtboinfeth,tehteudrbififneere,nthcedofiftfhereepnocweoerf tchaen pboewueser dcatno brecuhsaergdetothrecbhaattregreytphaecbkaattnedrythpeaceknearngdy tchaenebneeurgsyedcafonrbteaxuisinedg fmorodtaextioinog. mode too. Figure 1. Hybrid parallel conffiiguration. 3. Modeling of Propulsion System 3. Modeling of Propulsion System As said above, a hybrid parallel configuration was selected. Initially, some numerical As said above, a hybrid parallel configuration was selected. Initially, some numerical investigations are carried out by using a commercial code able to simulate the flight mission, comparing investigations are carried out by using a commercial code able to simulate the flight mission, fuel consumption and pollutant emissions of the original turboprop with the other two smaller, comparing fuel consumption and pollutant emissions of the original turboprop with the other two working in hybrid configuration. In a second phase, the battery pack’s weight is calculated through an smaller, working in hybrid configuration. In a second phase, the battery pack’s weight is calculated optimization procedure through the use of MATLAB. through an optimization procedure through the use of MATLAB. 3.1. Base ConfigurationPDF Image | Turboprop Hybrid Electric Propulsion System
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