An aircraft propulsion system includes a propulsive fan assembly configured for assembly into an aircraft structure, the propulsive fan assembly that includes a fan rotatable about a fan axis, an inlet duct assembly (34) disposed within the aircraft fuselage, the inlet duct assembly (34) that includes an upper inlet duct (36) with an upper inlet opening (38) and a lower inlet duct (40) with a lower inlet opening (42). The upper inlet duct (36) and the lower inlet duct (40) merge into a common inlet duct (46) forward of the propulsive fan assembly, and an outlet duct (44) is disposed aft of the propulsive fan assembly.
BOUNDARY LAYER DUCTED FAN PROPULSION SYSTEM
GRENZSCHICHTKANALGEBLÄSEANTRIEBSSYSTEM
SYSTÈME DE PROPULSION À VENTILATEUR À COUCHE LIMITE CANALISÉE
2025-07-02
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS |