A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module. The gas turbine engine further comprises a first electric machine that is rotationally connected to the turbine module, and an electrical energy storage unit. The gas turbine engine is configured to generate a maximum dry thrust T (N). The first electric machine is configured to generate a maximum electrical power PEM1 (W). The electrical energy storage unit has an energy storage capacity E (Wh), a maximum charge rate C (h-1), and a maximum discharge rate D (h-1). The electrical energy storage unit is configured to store electrical energy that may be generated by the first electric machine.
AN IMPROVED GAS TURBINE ENGINE
VERBESSERTER GASTURBINENMOTOR
MOTEUR À TURBINE À GAZ AMÉLIORÉE
2023-03-15
Patent
Elektronische Ressource
Englisch