A novel engine concept for a small adaptive cycle engine, using hybrid electric components , the "electric Hybrid Adaptive Cycle Engine" (eHACE) was developed. This concept consists of an electrically driven fan, a single spool core engine with a directly driven generator and variable nozzles for the core engine and the bypass stream. The electric energy for the fan is mainly supplied by the generator but can be enhanced by a battery storage. With this setup, the engine can be adapted for different flight conditions, ether to optimize for maximum thrust or for minimum fuel consumption. The eHACE is modelled using NPSS and a parametric study is conducted to determine the optimal engine settings for various flight mission points, resulting in initial sizing parameters for components specifically designed for the concept. In comparison to a small turbojet engine the eHACE can deliver increased thrust or reduced fuel consumption, depending on the engine setting.     «

A novel engine concept for a small adaptive cycle engine, using hybrid electric components , the "electric Hybrid Adaptive Cycle Engine" (eHACE) was developed. This concept consists of an electrically driven fan, a single spool core engine with a directly driven generator and variable nozzles for the core engine and the bypass stream. The electric energy for the fan is mainly supplied by the generator but can be enhanced by a battery storage. With this setup, the engine can be adapted for differ...     »