An engine assembly (20) for an aircraft propulsion system (10) includes a gas turbine engine (22), a gearbox (24), and a first drive shaft (30). The gas turbine engine (22) includes an engine output shaft (64), an air intake (34), and a compressor (44). The air intake (34) includes an air intake body (86) forming an air inlet (88), an air outlet (90), and an air plenum (92) extending between and connecting the air inlet (88) and the air outlet (90). The air plenum (92) extends circumferentially about the engine output shaft (64) between and to a first circumferential end (104) of the air intake (34) and a second circumferential end (106) of the air intake (34). The first circumferential end (104) and the second circumferential end (106) form a circumferential gap (108). The compressor (44) is connected in fluid communication with the air intake (34). The gearbox (24) includes a gear assembly (68) operably connected to the engine output shaft (64). The first drive shaft (30) is operably connected to the gear assembly (68). The first drive shaft (30) extends through the circumferential gap.


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    Title :

    AIR INTAKE FOR AN AIRCRAFT PROPULSION SYSTEM ENGINE ASSEMBLY


    Additional title:

    LUFTEINLASS FÜR EINE MOTORANORDNUNG EINES FLUGZEUGANTRIEBSSYSTEMS
    ENTRÉE D'AIR POUR ENSEMBLE MOTEUR DE SYSTÈME DE PROPULSION D'AÉRONEF


    Contributors:

    Publication date :

    2025-03-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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