Aircraft-engine integrated performance analysis of turbo-electric distributed propulsion
In order to explore the influence of the design parameters of the turbo-electric distributed propulsion(TeDP)system on mission fuel consumption,a performance model of the propulsion system and an integrated aircraft-engine evaluation model were established.The influences of the design parameters of the propulsion system on the weight and fuel consumption of the aircraft were studied based on a 150-seats civil aircraft concept.In addition,various operating strategies of battery were analyzed.The results showed that:there existed optimal values of turbine inlet temperature and relative power of electric system to achieve a minimum fuel consumption in mission profile;the energy use of battery should be prioritized to provide power supplementation when the load can't working at full power,which can achieve the reduction of fuel consumption using a battery with energy density higher than 400 W·h/kg.The integrated design method established can provide supports for the optimization design of the TeDP.
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