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.


    Access

    Download


    Export, share and cite



    Title :

    OPTIMISED NOZZLE GEOMETRY


    Contributors:

    Publication date :

    2022-09-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B05B Sprühvorrichtungen , SPRAYING APPARATUS / B64C AEROPLANES , Flugzeuge / 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



    OPTIMISED NOZZLE GEOMETRY

    LESLIE MARTIN / MALLON PATRICK / RICE MICHAEL | European Patent Office | 2022

    Free access

    OPTIMISED NOZZLE GEOMETRY

    MARTIN LESLIE / MALLON PATRICK / RICE MICHAEL | European Patent Office | 2021

    Free access

    Optimised nozzle geometry

    LESLIE MARTIN / MALLON PATRICK / RICE MICHAEL | European Patent Office | 2025

    Free access


    Optimised Tooth Flank Geometry for High Performance Transmissions

    Fehling, Robert / Donin, Rolland | SAE Technical Papers | 2007