An apparatus for providing foreign object debris protection and anti-icing capabilities to an air intake of an aircraft engine 12. The apparatus includes a frame 53 having at least a portion configured to conduct fluids. A tube 74 is positioned such that different portions of the frame 53 are fluidly connected. There is a discharge outlet 65 defined within the frame 53 that is configured to discharge fluids from the frame 53 into the air intake. An inlet 63 is defined within the frame 53 and is fluidly connected to a compressor section 39 of the aircraft engine 12. In this manner, air from the compressor section 39 of the aircraft engine 12 can flow through the inlet 63, through the tube 74, and through the discharge outlet 65, to return to the compressor section 39 of the aircraft engine 12.


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    Titel :

    INTERNALLY HEATED ENGINE INLET SCREEN FOR AIRCRAFT ENGINES


    Weitere Titelangaben:

    INTERN BEHEIZTES MOTOREINLASSSIEB FÜR FLUGZEUGTRIEBWERKE
    ÉCRAN D'ENTRÉE D'UN MOTEUR CHAUFFÉ INTÉRIEUREMENT POUR MOTEURS D'AÉRONEF


    Beteiligte:

    Erscheinungsdatum :

    20.09.2017


    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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