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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion

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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion ( comparison-concepts-classic-jet-propulsion-turbo-electric-pr )

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Table 3.3 Parameter Power 𝑃 , Fuel flow rate 𝑚̇ Turbine Entry Temperature 𝑇 Overall Pressure Ratio 𝑂𝑃𝑅 Europrop TP400 engine parameters 32 6 5 4 3 2 1 0 y = 0.0002x + 2.2507 0 2000 4000 6000 8000 10000 Power (kW) 12000 Figure 3.9 Turboprop engine length statistic 𝑚 =0.211 ∙𝑃, +43.876 (3.20) 𝑙 = 0.0002 ∙ 𝑃 , + 2.2507 (3.21) The data (Koppe 2012) from over 15 turboprop engines were used to plot Figure 3.8 and 3.9 with linear correlation. The R-squared value for Figure 3.8 is 65%. It commonly said that a minimum of 70% is a good value. For the purpose of this thesis, it is assumed that the value of R-squared is optimum. Once the power required is calculated, (3.20) and (3.21) can be used to calculate the turboprop engine mass (𝑚 ) and length (𝑙 ). The engine mass can lat- er be utilized to calculate the operating empty mass of the aircraft. A crucial parameter of the turboprop engine that is required for aircraft design is the Power Specific Fuel Consumption (𝑃𝑆𝐹𝐶). The PSFC is unique to an engine and is provided by the engine manufacturer. Ac- cording to Koppe (2012), it can be approximated for an engine using the Overall Pressure Ra- tio (𝑂𝑃𝑅), Turbine Entry Temperature (𝑇 ) and the required static sea-level take-off power (𝑃 , ). Since, each of these parameters are different for each engine, the Europrop TP 400 engine is used as a benchmark. Europrop TP 400 was selected because it produces thrust high thrust and it is one of the most recently developed aircraft. Value 8200 kW 0.41625 kg/s 1550 K 25 Engine Length (m)

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