An aircraft system is provided that includes a propulsor rotor, an electric machine and a gas turbine engine. The electric machine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust duct. The exhaust duct extends longitudinally along the electric machine. The exhaust duct extends partially circumferentially about the electric machine between opposing circumferential sides of the exhaust duct.
EXHAUST DUCT FOR HYBRID AIRCRAFT POWERPLANT
CONDUIT D'EVACUATION POUR UN GROUPE MOTOPROPULSEUR D~AERONEF HYBRIDE
2024-06-23
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
AIRCRAFT PROPULSION SYSTEM HAVING HYBRID-ELECTRIC POWERPLANT AND COMBUSTION POWERPLANT
Europäisches Patentamt | 2020
|AIRCRAFT PROPULSION SYSTEM HAVING HYBRID-ELECTRIC POWERPLANT AND COMBUSTION POWERPLANT
Europäisches Patentamt | 2020
|