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Aerospace 2018, 5, 123 4 of 21 3.1. Base Configuration Aerospace 2018, 5, x FOR PEER REVIEW Aerospace 2018, 5, x FOR PEER REVIEW 4 of 21 The first simulations have been made considering the standard configuration currently used The first simulations have been made considering the standard configuration currently used to The first simulations have been made considering the standard configuration currently used to to obtain a reference behavior in terms of emissions and performance. The reference aircraft used obtain a reference behavior in terms of emissions and performance. The reference aircraft used to obtain a reference behavior in terms of emissions and performance. The reference aircraft used to to simulate a new electric hybrid propulsion system is the ATR 42-300. This aircraft gives room simulate a new electric hybrid propulsion system is the ATR 42-300. This aircraft gives room to a simulate a new electric hybrid propulsion system is the ATR 42-300. This aircraft gives room to a to a maximum of 48 passengers, can carry a maximum payload of 4640 kg, and the max take-off maximum of 48 passengers, can carry a maximum payload of 4640 kg, and the max take-off weight maximum of 48 passengers, can carry a maximum payload of 4640 kg, and the max take-off weight weight (MTOM) is 16,900 kg. The ATR 42-300 is propelled by two PW120A turboprop engines with (MTOM) is 16,900 kg. The ATR 42-300 is propelled by two PW120A turboprop engines with a (MTOM) is 16,900 kg. The ATR 42-300 is propelled by two PW120A turboprop engines with a a maximum power of 1491 kW each [21], characterized by a large diffusion in regional air transport maximum power of 1491 kW each [21], characterized by a large diffusion in regional air transport maximum power of 1491 kW each [21], characterized by a large diffusion in regional air transport industry, thanks to its reliability and profitability. industry, thanks to its reliability and profitability. industry, thanks to its reliability and profitability. The main specification data of PW120A performances are reported in Table 1: The main specification data of PW120A performances are reported in Table 1: The main specification data of PW120A performances are reported in Table 1: Table 1. Engine1 (PW120) features. Table1. Engine1 (PW120) features. 4 of 21 Max T/O Power Overall Table1. Engine1 (PW120) features. T/O Power Compressor ComprMessaosrsMFlaosws Max T/O Overall T/O Power at BSFC (T/O) Max Cruise MMaxax Cruise Max T/O Overall T/O Power at Max atSeaLevel Pressure atSeaLevel BSFC(T/O) MaxCruise Power at Sea Pressure Ratio ◦ Compressor Mass Sea Level (kg/kWh) Power (kW)CruiseTTIIT( C) Power at Sea Pressure Ratio Sea Level Cruise TIT Flow(T//O))((kkgg/s/s)) Flow (T/O) (kg/s) Level (kW) (T/O) (kW) (kg/kWh) Power (kW) (°C) Level (kW) (T/O) (kW) (°C) 1491 12.1 1342 0.286 1231 1193 6.7 (kW) Ratio(T/O) (kW) (kg/kWh) Power(kW) BSFC (T/O) Max Cruise 1491 12.1 1342 0.286 1231 1193 1193 6.7 6.7 1491 12.1 1342 0.286 1231 The turbine inlet temperature (TIT) at the maximum power take-off condition was also The tuturrbbinineeinilnetlettemtepmerpaetruarteu(rTeIT()TaITt )thaetmtahxeimuamxipmouwmer ptaokwe-eorfftcaokned-oitfifoncownadsitailosno uwnaksnoawlsno, unknown, but it was assumed ◦to be 100 °C greater than the maximum cruise TIT [22]. In Figures 2 ubuntknitowans, bausstuitmwedastaossbuem1e0d0 toCbgere1a0t0e°rCthgarneatheretmhanxitmheumacxriumisuemTIcTru[i2s2e].TIITn[F22ig].uIrnesF2igaunreds32, and 3, the PW120 gas turbine scheme and the thermodynamic cycle at the design point are reported, athnedP3,Wth1e20PWga1s20tugrabsintuerbscinhemsceheamndeatnhdettherthmeormdyondaymnaicmciycclyeclaetatthteheddeseisgignnppooininttarereported, respectively; the results are obtained assuming that the engine is a two spool turboprop, with a respectively; the results are obtained assuming that the engine is a two spool turboprop, with a booster on high spool. Figure 2. Gas turbine scheme. Figure 2. Gas turbine scheme. Figure 3. Thermodynamic cycle at the design point. Figure 3. Thermodynamic cycle at the design point. booster on high spool. To realize a flight cycle at the design point of PW120A (named in the following Engine1), the To realize a flight cycle at the design point of PW120A (named in the following Engine1), the input data in Table 2 have been considered. input data in Table 2 have been considered. Table2. Input data for simulation of the “Engine1 at design point” and of the “power flight profile”. Table2. Input data for simulation of the “Engine1 at design point” and of the “power flight profile”.PDF Image | Turboprop Hybrid Electric Propulsion System
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