The invention relates to an internal structure (22) for a nacelle (18) of a turbomachine (10), designed to surround at least part of a nacelle capable of receiving a gas generator (14) of the turbomachine (10), said internal structure (22) comprising a ventilation cavity (30) of said nacelle, said ventilation cavity (30) being provided with a main ventilation outlet (32) and an auxiliary ventilation outlet (34) separate from said main ventilation outlet (32), the internal structure (22) comprises a closing member (40) movable relative to the ventilation cavity (30) between a flow position and a closed position in which the closing member (40) closes the auxiliary ventilation outlet (34) to a greater extent than in the flow position.

    用于涡轮机(10)的短舱(18)的内部结构(22),该内部结构被设计为围绕能够接收该涡轮机(10)的气体发生器(14)的舱室的至少一部分,所述内部结构(22)包括所述舱室的通风空腔(30),所述通风空腔(30)设置有主通风出口(32)以及与所述主通风出口(32)分开的辅助通风出口(34),所述内部结构(22)包括关闭构件(40),所述关闭构件能相对于所述通风空腔(30)在流动位置与关闭位置之间移动,在所述关闭位置中,所述关闭构件(40)比在所述流动位置中更大程度地关闭所述辅助通风出口(34)。


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    Titel :

    Internal structure for nacelle of turbomachine


    Weitere Titelangaben:

    用于涡轮机的短舱的内部结构



    Erscheinungsdatum :

    12.04.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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