A nacelle (2) of an aircraft engine (3) comprises an anti-icing protection system (1), and the nacelle (2) comprises an inner shroud (5), and an air inlet lip (7) forming a leading edge of the nacelle(2); the protection system comprises a heat exchanger arrangement (11) comprising at least one heat pipe (12) configured for transferring heat (14) emitted by a heat source to the inner shroud (5).

    一种包括防冰保护系统(1)的飞行器发动机(3)的短舱(2),所述短舱(2)包括内护罩(5)、形成所述短舱(2)的前缘的进气口唇缘(7),所述保护系统包括热交换器装置(11),所述热交换器装置包括至少一个热管(12),所述至少一个热管被配置成用于将热源所发射的热量(14)传递至所述内护罩(5)。


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    Titel :

    AIRCRAFT ENGINE NACELLE COMPRISING ICE PROTECTION SYSTEM


    Weitere Titelangaben:

    包括防冰保护系统的飞行器发动机的短舱


    Beteiligte:
    PORTE ALAIN (Autor:in) / PONS FRANCOIS (Autor:in) / ALBET GREGORY (Autor:in) / ZEBIAN MAXIME (Autor:in)

    Erscheinungsdatum :

    2020-04-28


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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