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)。

    Internal structure for a turbomachine nacelle, the internal structure being intended to surround at least one part of a compartment capable of receiving a gas generator of the turbomachine, the internal structure comprising a ventilation cavity of said compartment, the ventilation cavity being provided with a main ventilation outlet and an auxiliary ventilation outlet separate to the main ventilation outlet, the internal structure comprising a shut-off member movable relative to the ventilation cavity between a flow position and a shut-off position in which the shut-off member shuts off the auxiliary ventilation outlet to a greater extent than in the flow position.


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    Titel :

    用于涡轮机的短舱的内部结构


    Erscheinungsdatum :

    08.07.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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