The ECO-150 is a 150 passenger Environmentally COnscious tube-and-wing regional airliner concept which is characterized by a turboelectric distributed propulsion (TeDP) system embedded within the inboard section of the wing. Since 2008, the ECO-150 concept has served to promote a more complete understanding of TeDP performance, integration, design requirements, and system complexities. Early versions of the ECO-150 claimed superconducting electronics cooled by onboard liquid hydrogen (LH 2 ); however, the infrastructure requirements of such a system are far out of reach for near-term technology. In this most recent investigation, the ECO-150R was equipped with conventional electric machines suitable for NASA's N+2 timeframe. A recirculating liquid thermal management system (TMS) with ram air heat exchangers was integrated into the design to support the electric machines. Additionally, three-dimensional CFD analysis of the aircraft guided a redesign of the inboard wing and validated prior lower-order estimates for aero-propulsive efficiency and high lift performance. Component integration exercises within the updated configuration illuminated unexpected yet solvable packaging challenges. Mission performance analysis showed the ECO-150R concept to be at least as efficient as a currently operating airliner despite systematically conservative assumptions for the mass and efficiency of the advanced technologies and several unclaimed opportunities for design optimization. Ultimately, the research discussed in this paper strengthened the credibility of the ECO-150 concept and confirmed the feasibility of TeDP systems with conventional electric machines.
Nomenclatureaircraft total drag, lb f L = aircraft total lift, lb f M = Mach number T = aircraft total thrust, lb f TOFL = takeoff field length, ft TSFC = thrust specific fuel consumption, lb m /lb f /hr ∆T = difference in temperature, °R
Purpose -The purpose of this article is to provide an outline of the challenges of thermal management for more-electric, hybrid-electric and all-electric aircraft, and to notionally discuss potential solutions. Design/methodology/approach -A code algorithm was developed to facilitate architecture-level analysis of the coupled relationship between the propulsion system, the thermal management system, and the takeoff gross weight of aircraft with advanced propulsion systems. Findings -A variety of coupled relationships between the propulsion and thermal management systems are identified, and their impact on the conceptual design choices for electric aircraft are discussed qualitatively. Research limitations/implications -This conceptual article merely illuminates some driving factors associated with thermal management. The software is still in its adolescence and is experiencing ongoing development. Practical implications -Thermal regulation in electric aircraft is shown to be a topic that should be addressed in tandem with propulsion system architecture definition and component selection. High-power electronics are expected to emit an immense amount of heat, and the common avenues of heat dissipation could substantially impact the aircraft's weight, drag and performance. Conversely, strategic management of this waste heat could support subsystems or even produce additional thrust. Social implications -This paper aims to direct the attention of researchers and designers in the field of hybrid-or all-electric aircraft design toward the challenges and potential benefits of thermal management. Originality/value -This paper describes a novel conceptual design software and discusses its logic flow and implications.
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