The present disclosure provides a device for de-icing an air intake lip of an aircraft turbojet engine nacelle. The de-icing device includes a de-icing circuit in which a heat transfer fluid, working in a two-phase form, circulates. The de-icing circuit includes at least one device for circulating the heat transfer fluid in the de-icing circuit, a system for heating the heat transfer fluid and configured to change the phase of the fluid to a vapor phase, and an inlet conduit that opens into the lip through a rear wall and injects the vapor phase fluid into the lip. The fluid changes phase when it condenses on the front wall of the lip to de-ice the lip.


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    Title :

    DEVICE FOR DE-ICING AN AIRCRAFT TURBOJET ENGINE NACELLE AIR INTAKE LIP


    Contributors:

    Publication date :

    2018-08-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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