An inside vessel arrangement (5) is fixedly secured in a stator hollow structure (8) and has at least one enlarged static circumference housing (20), and an aerodynamic outer toroid spoiler (18) has an outer external surface (35) complementary to the static circumference housing (20). The aerodynamic outer toroid spoiler (18) radially secured to each of outer tips (23) of rotor blades (10) of a driven rotor system (7). A torus air gap (G) is provided, so that an outer laminar flux (56) is admitted simultaneously with an inlet inner stream (54) and guided through the torus air gap (G), with the inlet main stream and outer laminar flux being converged to merge together in single outlet control airflow (C). The invention typically applies e.g. to vehicles (A) such as aircrafts like rotary wing aircrafts.


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    Titel :

    Blade rotary assembly with aerodynamic outer toroid spoiler for a shrouded propulsion rotary assembly


    Beteiligte:

    Erscheinungsdatum :

    2016-09-27


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / B64C AEROPLANES , Flugzeuge




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