An inlet arrangement for a propulsion system includes an actuator (64), a linkage (62) and an inlet assembly (32, 3). The inlet assembly (32, 3) includes (1) a lip (2, 35, 40), (2) a cowl (42) extending downstream from the lip (2, 35, 40), the cowl (42) defining an external surface (72, 74) of the inlet assembly (32, 3), (3) an inlet duct (44) extending downstream from the lip (2, 35, 40), the inlet duct (44) disposed radially inward of the cowl (42), and (4) a movable component associated with the lip (2, 35, 40), the cowl (42), or the inlet duct (44). An outer surface (72) of the inlet duct (44) and an inner surface (74) of the cowl (42) define a gap (76) therebetween. The linkage (62) is disposed in the gap (76) and coupled with the moveable component. The linkage (62) is configured to move within the gap (76) and to move the moveable component when the linkage (62) moves. The actuator (64) is coupled with the linkage (62) and moves the linkage (62) when the actuator (64) is actuated. The actuator (64) is mounted remotely from the inlet assembly (32, 3).


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    Title :

    INLET ARRANGEMENT, A PROPULSION SYSTEM, AND AN AIRCRAFT


    Additional title:

    EINLASSANORDNUNG, ANTRIEBSSYSTEM UND FLUGZEUG
    AGENCEMENT D'ENTRÉE, SYSTÈME DE PROPULSION ET AÉRONEF


    Contributors:

    Publication date :

    2023-08-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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