A compressed gas ejection assembly (10) for a rotating wing aircraft blade (2) comprises a compressed gas passage (114) adapted to allow a substantially constant mass flow through the compressed gas ejection assembly (10) across at least a portion of the width of the compressed gas ejection assembly (10).

    Un ensemble d'éjection de gaz comprimé (10) pour une pale d'aéronef à voilure tournante (2) comprend un passage de gaz comprimé (114) conçu pour permettre un écoulement massique sensiblement constant à travers l'ensemble d'éjection de gaz comprimé (10) sur au moins une partie de la largeur de l'ensemble d'éjection de gaz comprimé (10).


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    Title :

    OPTIMISED NOZZLE GEOMETRY


    Additional title:

    GÉOMÉTRIE DE BUSE OPTIMISÉE


    Contributors:

    Publication date :

    2021-02-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B05B Sprühvorrichtungen , SPRAYING APPARATUS / F15D FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS , Strömungsdynamik, d.h. Verfahren oder Vorrichtungen zum Beeinflussen der Strömung von Gasen oder Flüssigkeiten



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