A hybrid propulsion system for use with an aircraft includes a gas turbine engine, at least one propulsor, and an electric power system. The electric power system is coupled to the gas turbine engine to generate electrical energy and the propulsor to provide electrical energy to drive the propulsor. The electric power system includes a thermal management system configured to cool a heat load generated by the electric power system.
Aircraft hybrid propulsion system including cold plate for a high density power converter
2023-11-07
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |