Innovative approaches for reducing CO₂ emissions of aviation engines part 4: Turbine Exhaust Driven Thermal cycle TED-T

Innovative approaches for significantly reducing the aviation Greenhouse Gas (GHG) emission need to be evaluated based on simple calculation methodology, viz. Numerical Propulsion System Simulation (NPSS) that can be easily and reliably executed by an academic research group with guidance provided by a panel of experts from industry, FAA, NASA, DOE and DOD. Part 1 of the series of papers gives a list of the proposed advanced Brayton cycles for undertaking an extensive study under the FAA program. Part 2 of the series of papers shows that good agreement was achieved between the NPSS calculations and engine data of several engines, including the aero-engines CFM56, CF6-80C, GE90, and industrial engines LM6000 and LMS100 with and without recuperation. Several engine configurations were analyzed in Part 3 leading to selection of the most promising configurations for the follow-on conceptual design effort by potential OEM. In the present paper, extension of the advanced Brayton cycle is considered by introducing an LP Turbine Exhaust Driven Thermal (TED-T) cycle to provide heat source for a closed supercritical CO₂ cycle for running either a propulsion system or an electric generator.