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Aerospace 2018, 5, 123 5 of 21 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. Aerospace 2018, 5, x FOR PEER REVIEW 5 of 21 Table 2. Input data for simulation of the “Engine1 at design point” and of the “power flight profile”. Nominal Spool Speed 29,800 rpm Input Data for Engine1 Input Data for Flight Power Calculation Input Data for Engine1 Input Data for Flight Power Calculation Altitude 0 12.1 Zero-Lift Drag Coefficient 0.025 11.08 0.85 0.025 11.08 0.85 Nominal Spool Speed 29,800 rpm Input Data for Simulation Input Data for Simulation Altitude 0 12.1 Zero-Lift Drag Coefficient Overall Pressure Ratio (T/O) Aspect Ratio Overall Pressure Ratio (T/O) Aspect Ratio Compressor Mass Flow (T/O) 6.7 kg/s Oswald Factor Compressor Mass Flow (T/O) 6.7 kg/s Oswald Factor Mach Number 0.166 Wing Area 54.5 m2 2 54.5 m Mach Number BurnerBEuxirtnTeermEpxietrTateumrepe(TraITtu)re(TIT) 0.166 Wing Area MaxMimauxmimTuamkeT-aOkfef-WOfefigWhetight 16,90016,900 Burner BEuffircniernEcyfficiency Burner Pressure Ratio Burner Pressure Ratio 0.97 Fuel Heating Value 43.1 MJ/kg Fuel Heating Value 43.1 MJ/kg Overboard Bleed 0.2 Overboard Bleed 0.2 HP Spool Mechanical Efficiency 0.99 HP Spool Mechanical Efficiency 0.99 LP Spool Mechanical Efficiency 0.98 LP Spool Mechanical Efficiency 0.98 1191393C°C 0.09.9595 0.97 ◦ Starting from the single cycle design point, some off-design simulations have been performed. Starting from the single cycle design point, some off-design simulations have been performed. Naturally, if more accurate simulations of a specific engine are desired, then special compressor and Naturally, if more accurate simulations of a specific engine are desired, then special compressor and turbine maps should be used. Unfortunately, the company has never declared the component maps of the PW100 series, so there are different ways to obtain these maps with an admissible accuracy. turbine maps should be used. Unfortunately, the company has never declared the component maps of the PW100 series, so there are different ways to obtain these maps with an admissible accuracy. In fact, it is important to underline that, because of the lack of knowledge of the real component maps, In fact, it is important to underline that, because of the lack of knowledge of the real component maps, it can be possible to obtain estimated maps to try to minimize the gap from the real ones. In order to it can be possible to obtain estimated maps to try to minimize the gap from the real ones. In order estimate the component maps, it is possible by either scaling maps of other components with similar to estimate the component maps, it is possible by either scaling maps of other components with characteristics or computerizing data from the PW120 compressor and turbine maps present in similar characteristics or computerizing data from the PW120 compressor and turbine maps present in literature (Figures 4–6). literature (Figures 46). The simulation of the engine during the descent, approach, and landing phase are carried out The simulation of the engine during the descent, approach, and landing phase are carried out with the consideration that the engine control system, which is dependent on the throttle lever angle, with the consideration that the engine control system, which is dependent on the throttle lever angle, guarantees that the certified spool speeds, temperatures, and pressures are not exceeded during both guarantees that the certified spool speeds, temperatures, and pressures are not exceeded during both the transient and steady state operation. The diagram in Figure 7 shows the comparison between the the transient and steady state operation. The diagram in Figure 7 shows the comparison between the Figure 4. HP compressor map of the Engine1. thermodynamic cycle at the take-off, and during the cruise, with an altitude of 5516 m and a flight thermodynamic cycle at the take-off, and during the cruise, with an altitude of 5516 m and a flight velocity of 0.333 Mach. velocity of 0.333 Mach.PDF Image | Turboprop Hybrid Electric Propulsion System
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