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B787 Air Systems Design Conventional ECS Unclassified B787 E‐ECS 34
Conventional Vs. Electric ECS Conventional ECS Electric ECS Engine bleed air delivered at 30 PSI / 400 °F. Electrical compressors delivered at 15 PSI / 200 °F determined by minimum temperature of ozone converter. Air cooled by air conditioning pack [pri & sec HEx + Air Cycle Machine (ACM)]. Cooled air enters cabin at 11.8 PSI / 60 °F. Much energy wasted as bleed air is delivered at excessive pressure and temperature. Physical interface with engine and potential for distributing air flow. Unclassified Air cooled by air conditioning pack [pri & sec HEx + Air Cycle Machine (ACM)], requires greater ram air mass flow. Cooled air enters cabin at 11.8 PSI / 60 °F. System only delivers the necessary air ‐ temperature limited by ozone converter characteristics. Note: ozone converters used only at Altitudes > xx,000 feet. Reduced interface with engine. 35
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: B787 Hybrid Electrical Power Distri
Page 37 and 38: Actuation System The four‐engine
Page 39 and 40: Impact of Aircraft and Engine Desig
Page 41 and 42: Impact of Aircraft and Engine Desig
Page 43 and 44: Impact of the AEA Concept Implicati
Page 45 and 46: More Electric Engine (MEE) Challeng
Page 47 and 48: IAI More “Electric Aircraft” B7

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