A nacelle for an aircraft turbojet engine includes a fixed internal structure intended to receive an aircraft turbojet engine and an external structure. The fixed internal structure and external structure defines a flow channel for a secondary air flow. A set of lower and upper beams are linked together by the fixed internal structure. An external wall of the lower beam is designed to partially define an external aerodynamic surface of the nacelle, intended to come into contact with an outer air flow. The external wall of the lower beam is further designed to tolerate the damage caused by the outer air flow.
ENSEMBLE PROPULSIF POUR AÉRONEF À TRAÎNÉE AÉRODYNAMIQUE RÉDUITE
AIRCRAFT PROPULSION UNIT HAVING REDUCED AERODYNAMIC DRAG
FLUGZEUGTRIEBWERKSEINHEIT MIT VERRINGERTEM LUFTWIDERSTAND
2019-04-24
Patent
Electronic Resource
French
ENSEMBLE PROPULSIF POUR AERONEF, A TRAINEE AERODYNAMIQUE REDUITE
European Patent Office | 2019
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