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 4.9 Comparison of aircraft parameters of redesigned aircraft with A320 51 The new Thrust specific fuel consumption is calculated by dividing the new fuel mass flow rate by the total thrust found in (4.35). 𝑇𝑆𝐹𝐶 , is then inserted in the DOC calculation to find the positive effects of this propulsion concept over the previous concepts. 𝑇 (%)=𝑇 −𝑇 (4.47) 𝑇 𝑇 , (%)= 1+ 𝑇 (%) (4.48) 𝜂/ As mentioned previously, the turbofan engine has a limitation in terms of power extraction with shaft power off-take. It is assumed that the turbofan engine produces extra power to sup- ply shaft off-take power. In order to calculate the extra power required by the engine to pro- duce the required shaft power, certain parameters are required that can only be provided by the manufacturer. This might lead to a complicated task. Since the Equation (4.47) and (4.48) are ratios and both (engine and motor) would have the same local airspeed, one can assume that (4.48) is accurate. Parameter Wing surface area (𝑚 ) Maximum take-off mass (𝑘𝑔) Operating empty mass (𝑘𝑔) Wing loading (𝑘𝑔⁄𝑚 ) Cruise Altitude (𝑓𝑡) A320 aircraft value 122.4 73500 41244 600.49 39000 Redesigned aircraft value 110 71334 41244 647 37808 Deviation − 10% − 2.9% 0% + 7.7% −3% Table 4.9 contains the parameters of the A320 aircraft along with the deviation. Similar to the propeller driven aircraft, the results show less than 10% of deviation. Also, the cruise altitude is very close to the actual value of A320. This proves that the PreSTo tool for propeller driven aircraft was the cause of major deviation in cruise altitude in chapter 4.2.7.

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