Simulation and Performance Investigation of Turbo-electric Distributed Propulsion System

摘要

The evolution of new concepts in aircraft propulsion system is required keeping the view on increasing global effects due to growing air traffic in every year. Many studies and researches have been initiated towards development of new aircraft configurations and propulsion systems. One of the most promising concepts in this field is Turbo-electric Distributed Propulsion (TeDP) configuration with superconducting electric machinery. However the enabling technologies for the effective implementation of TeDP for future generation aircraft have only been developed to low technology readiness levels (TRLs). In this research paper, the methodology for design point optimization of TeDP system parameters is discussed for both podded and embedded propulsor system configurations by using turbofan gas turbine based power plant as core engine and ducted fans as propulsors. The performance optimization is carried out for low TSFC and arrived to an optimum TeDP layout with the cycle parameters viz. Thrust Split, propulsor FPR, propulsor Mass Flow, gas turbine BPR, gas turbine FPR and gas turbine Mass Flow. The performance of the TeDP system is then investigated in comparison with conventional propulsion system for similar thrust class by keeping the same OPR and TET of the main gas turbine engines.