A gas turbine engine comprises a rotatable component, such as a fan, and an engine casing 200 disposed about the rotatable component. The engine casing includes a casing treatment comprising a plurality of grooves 222, 224, 226, 228, 230 and a plurality of acoustic chambers 282, 284, 286, 288, each of the grooves has a groove depth, and each of the acoustic chambers has a chamber depth. Two of the grooves 256, 266 are associated with one of the acoustic chambers 286. The chamber depth may be based on the groove depth with one of the other grooves associated with a second of the acoustic chambers and the acoustic chambers having different acoustic configurations. Alternatively, a total depth of each of the grooves and the associated acoustic chamber is substantially the same, the number of acoustic chambers being less than the number of grooves, and the two of grooves being defined between a leading and the trailing edge of an aerofoil of the rotatable component.


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    Titel :

    Acoustic engine casing for gas turbine engine


    Beteiligte:
    SHAILESH KUMAR (Autor:in) / JYOTICHANDRA JINGADE (Autor:in) / MOHAMMED QIZAR (Autor:in) / MAHMOUD MANSOUR (Autor:in) / MICHAEL BARTON (Autor:in) / WILLIAM SCHUSTER (Autor:in) / JOHN GUNARAJ (Autor:in) / DAVID HANSON (Autor:in) / SWARNA SINHA SRINATH (Autor:in)

    Erscheinungsdatum :

    09.07.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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