A nacelle inlet (200) may comprise an aft bulkhead (210), an attachment ring (220) extending in an aft direction from the aft bulkhead (210), an acoustic liner (230) disposed radially inward from the attachment ring (220), the acoustic liner (230) comprising a proximal skin (232), a distal skin (234), and a core (236) disposed between the proximal skin (232) and the distal skin (234), and a shroud (250) extending longitudinally between a forward side (252) of the shroud (250) and an aft side (254) of the shroud (250) and extending circumferentially between a first end of the shroud (250) and a second end of the shroud (250), wherein the shroud (250) defines a plenum (240) disposed between the acoustic liner (230) and the shroud (250), the plenum (240) is in fluid communication with the core (236) via perforations (235) in the distal skin (234). The plenum (240) may serve to attenuate low frequency noise known as "buzz saw" tones and/or alleviate pressure resonance conditions that may cause structural damage to the engine fan blades.


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    Title :

    INLET DEEP CAVITY FLUTTER LINER


    Additional title:

    FLATTERAUSKLEIDUNG FÜR DEN EINLASS EINES TIEFEN HOHLRAUMS
    DOUBLURE DE FLOTTEMENT DE CAVITÉ PROFONDE D'ENTRÉE


    Contributors:

    Publication date :

    2020-03-18


    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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