One embodiment is an inlet plenum assembly for a rotary aircraft (101, 201) that includes an inlet plenum defined on a first side by an inlet plenum wall (312) and on a second side by a forward firewall assembly (308), the forward firewall assembly (308) having an inlet aperture (310) configured to receive a drive shaft (314) to rotatably couple to an engine (302); and a seal (320) connected to the forward firewall assembly (308) via a seal retainer (900) disposed around a periphery of the inlet aperture (310). The forward firewall assembly (308) may further include a forward firewall upper portion (402) and a forward firewall lower portion (404), the forward firewall upper portion (402) configured to removably seat to the forward firewall lower portion (404). The seal retainer (900) may be attached to the forward firewall assembly (402) via a plurality of bolts (902) disposed around the periphery of the seal retainer (900). In some embodiments, the seal (320) is connected to an inlet duct of the engine (302).


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    Title :

    ENGINE INLET SYSTEM WITH INTEGRAL FIREWALL SEAL


    Additional title:

    TRIEBWERKSEINLASSSYSTEM MIT INTEGRIERTER FEUERSCHUTZWANDDICHTUNG
    SYSTÈME D'ENTRÉE DE MOTEUR AVEC JOINT COUPE-FEU INTEGRAL


    Contributors:

    Publication date :

    2020-06-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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