The invention relates to an aircraft fluid anti-icing system. A fluid anti-icing system for an aircraft includes a chamber aft wall and a fluid delivery network. The chamber aft wall is secured to an inner surface of an inlet cover of a nacelle of an aircraft to define a chamber between the inner surface and a front surface of the chamber aft wall. The nacelle surrounds a rotor assembly of an aircraft propulsion system. The inlet cover defines a plurality of perforations through a thickness of the inlet cover. The perforation is fluidly connected to the chamber. A fluid delivery network is coupled to the chamber back wall and is configured to supply ice-resistant liquid into the chamber for the ice-resistant liquid to penetrate the perforations along the leading edge section of the inlet mask onto the outer surface of the inlet mask.

    本申请涉及飞行器流体防冰系统。一种用于飞行器的流体防冰系统包括腔室后壁和流体输送网络。腔室后壁固接到飞行器的短舱的入口罩的内表面,以在内表面与腔室后壁的前表面之间限定腔室。短舱围绕飞行器推进系统的转子组件。入口罩限定穿过入口罩的厚度的多个穿孔。穿孔流体地连接到腔室。流体输送网络联接到腔室后壁,并且被配置为将抗冰液体供应到腔室中,以供抗冰液体沿着入口罩的前缘区段穿透穿孔到入口罩的外表面上。


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    Title :

    Aircraft fluid anti-icing system


    Additional title:

    飞行器流体防冰系统


    Contributors:

    Publication date :

    2024-01-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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



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