All/More Electric Aircraft Engine & Airframe Systems - Turbo & Jet ...

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Reliability Block Diagram for Electro‐ Hydrostatic Primary Flight Control Actuation System The additional components are the electric system power supply, the electric motors and the controllers. Twin‐engine aircraft primary flight control actuation system reliability requirements of 1.00 E‐9 / flight‐hour, can be met by two separate electrical power systems out of three. Unclassified 38
Impact of Aircraft and Engine Design on the AEA Concept Implication The impact of the all or more electric technologies depends on the aircraft configuration, i.e.: Number of engines, Bypass ratio, Engine pressure ratio (PR), Turbine entry temperature (TET), Number of passengers, Aircraft range, Size of the aircraft. Unclassified 39
Page 1 and 2: The 9th Israeli Symposium on Jet En
Page 3 and 4: Evolution of the All/More Electric
Page 5 and 6: “Conventional” Philosophy (Cont
Page 7 and 8: “Conventional” Philosophy (Cont
Page 9 and 10: Effects of Takeoff on Aircraft Oper
Page 11 and 12: Effects of Bleed Air and Shaft Powe
Page 13 and 14: “Electric Aircraft” Philosophy
Page 17 and 18: “Electric Aircraft” Unclassifie
Page 19 and 20: “Electric Aircraft” Improved re
Page 23 and 24: Secondary Power Systems (SPS) Distr
Page 25 and 26: Conventional Secondary Power System
Page 27 and 28: Typical Power Level of Electrical L
Page 29 and 30: AC Power Generation & Regenerative
Page 31 and 32: B787 “Bleedless” System Archite
Page 33 and 34: B787 Hybrid Electrical Power Distri
Page 35 and 36: Conventional Vs. Electric ECS Conve
Page 37: Actuation System The four‐engine
Page 41 and 42: Impact of Aircraft and Engine Desig
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