The invention relates to a propulsion rotor assembly (B). 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 aircraft like rotary wing aircraft.
Blade rotary assembly with aerodynamic outer toroid spoiler for a shrouded propulsion rotary assembly
Rotierende Blattanordnung mit aerodynamischem äußeren Toroidspoiler für eine ummantelte rotierende Antriebsanordnung
Ensemble rotatif de pale à aileron toroïde extérieur aérodynamique pour un ensemble rotatif de propulsion carénée
2016-09-07
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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