A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.
NACELLE D'UN ENSEMBLE PROPULSIF D'AÉRONEF COMPORTANT UNE PLURALITÉ D'ÉLÉMENTS AMORTISSEURS ENTRE UNE PARTIE AVANT ET UNE PARTIE PRINCIPALE, ET ENSEMBLE PROPULSIF D'AÉRONEF ASSOCIÉ
AIRCRAFT PROPULSION ASSEMBLY NACELLE HAVING A PLURALITY OF SHOCK ABSORBING ELEMENTS BETWEEN A FRONT PART AND A MAIN PART, AND ASSOCIATED AIRCRAFT PROPULSION ASSEMBLY
GONDEL EINER FLUGZEUGANTRIEBSANORDNUNG MIT MEHREREN DÄMPFUNGSELEMENTEN ZWISCHEN VORDEREM UND HAUPTTEIL UND ZUGEHÖRIGER FLUGZEUGANTRIEBSANORDNUNG
2020-08-12
Patent
Electronic Resource
French
PARTIE ANTERIEURE DE NACELLE D'UN ENSEMBLE PROPULSIF D'AERONEF COMPORTANT UN ELEMENT AMORTISSEUR
European Patent Office | 2020
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