The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.
NACELLE DE TURBORÉACTEUR D'AÉRONEF
AIRCRAFT TURBOJET ENGINE NACELLE
FLUGZEUGTURBOSTRAHLTRIEBWERKSGONDEL
26.06.2019
Patent
Elektronische Ressource
Französisch
Dispositif d'étanchéité pour nacelle de turboréacteur d'aéronef
Europäisches Patentamt | 2019
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