An engine inlet (10) for efficient operation at both design Mach number and off-design Mach numbers employs a variable geometry caret inlet (10) having a principal compression ramp (22) extending rotatably attached at a first hinge line (36). The principal compression ramp (22) is rotatable from a low Mach position to a design Mach position. A diffuser ramp (24) is engaged by the principal compression ramp (22) at an interface (26) and is rotatably mounted at a second hinge line (38). The diffuser ramp (24) is rotatable oppositely to the principal compression ramp (22) to maintain contact at the interface (26). A compression ramp filler (28) is mounted interior to the principal compression ramp (22) and engages the principal compression ramp (22) with a compression scrub surface (29). A diffuser ramp filler (32) is mounted interior to the diffuser ramp (24) and engages the diffuser ramp (24) with a diffuser scrub surface (33).


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    Titel :

    SUPERSONIC AIR INLET WITH TWO ADJUSTABLE RAMPS


    Weitere Titelangaben:

    ÜBERSCHALL-LUFTEINLASS MIT ZWEI EINSTELLBAREN RAMPEN
    PRISE D'AIR SUPERSONIQUE À DEUX RAMPES RÉGLABLES


    Beteiligte:
    HUYNH THUY (Autor:in)

    Erscheinungsdatum :

    03.07.2024


    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



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