一种飞行器涡轮机短舱的进气管(1),包括唇缘(2)、下游部(3)以及将唇缘(2)与下游部(3)分隔的内隔壁(5),所述唇缘(2)限定出环形腔(24),下游部(3)包括下游内壁(31)和下游外壁(32),进气管(1)包括用于将热气流(Fac)送入环形腔(24)的输气管(4),通道口(51)形成于内隔壁(5),排气口(34)形成于下游外壁(32),排气管(6)安装在所述下游部(3)中以排放所述热气流(Fac)并包括与内隔壁(5)连接的第一端(7、9)、与下游外壁(32)连接的第二端(8)以及包括至少一个柔性部分的主体(61)。

    Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    飞行器涡轮发动机短舱的进气管


    Erscheinungsdatum :

    15.07.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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