Cryogenic and Non-Cryogenic Hybrid Electric Distributed Propulsion with Integration of Airframe and Thermal Systems to Analyze Technology Influence

A design iteration of ESAero's ECO-150 split wing turboelectric distributed propulsion (TeDP) concept is proposed to incorporate recent lessons learned in synergistic configuration opportunities, propulsion and thermal management system research and tool development, and aeropropulsive benefits reported by Lockheed Martin. Non-cryogenic and cryogenic/superconducting components will be included in three separate propulsion system architectures: one cooled via conventional "warm" coolant, one cryogenically cooled with a cryocooler system, and one cryogenically cooled with a liquid hydrogen blow-down system. The effort will begin with an interagency collaborative "Brainernet" brainstorming session to identify and assess technology and concept drivers and opportunities. Detailed configuration, aerodynamics, performance, and mission analysis will complement the effort, culminating in three flagship TeDP or hybrid electric distributed propulsion (HEDP) concepts which embody the propulsion-airframe-thermal integration (PATI) paradigm. A 2D and 3D CFD evaluation of the integrated propulsor will validate the physics-based aerodynamics and propulsor analysis tools. The lessons learned from the effort will establish a conceptual design roadmap for HEDP aircraft that are sensitive to PATI factors while also identifying path-critical technologies and design driving parameters for the propulsion and thermal management systems.