An apparatus 10 for improving heat transfer through a leading portion 10 of an aircraft engine. The apparatus includes a wall 16 that is defined by the leading portion 10. A surface 22 is defined by the wall 16 and the surface 22 defines a channel 30 through the leading portion 10 of the aircraft engine. The apparatus includes a nozzle 34 fluidly connected to the channel 30, to direct bleed air therein. Pits 42 are defined in the surface 22 of the channel 30 such that the bleed air can flow across the pits 42.


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    Titel :

    DIMPLED NACELLE INNER-SURFACE FOR HEAT TRANSFER IMPROVEMENT


    Weitere Titelangaben:

    GENOPPTE INNENOBERFLÄCHE EINER GONDEL ZUR VERBESSERUNG DER WÄRMEÜBERTRAGUNG
    SURFACE INTÉRIEURE DE NACELLE ALVÉOLÉE POUR AMÉLIORER LE TRANSFERT DE CHALEUR


    Beteiligte:

    Erscheinungsdatum :

    2017-11-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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