Disclosed is a turbomachine assembly comprising a nacelle having an air inlet and comprising a structure. A forward hood is fixed to the structure and extends backwards from the air inlet. An articulated hood is arranged in the upper part of the nacelle and at the rear of the forward hood and comprises a front edge arranged at the front of the articulated hood. A rear edge is arranged at the rearof the articulated hood. A joint is disposed at the front edge between the articulated hood and the structure and ensures a displacement of the articulated hood between a closed position and an open position. A locking system is arranged at the rear edge, and is mobile between a locked position and an unlocked position, where in the closed position, the front edge is under the forward hood. Because the hinged cover can be opened and closed easily and quickly, the nacelle reduces the technician's work. This arrangement also prevents the phenomenon of separation.
一种涡轮机组件(108),包括短舱(110),该短舱具有进气口且包括结构体(302);在前罩盖(110a),固定至结构体(302)且从进气口向后延伸;铰接罩盖(200),布置在短舱的上部部分中且在在前罩盖的后部处,且该铰接罩盖包括布置在其前部处的前部边缘(202)和布置在其后部处的后部边缘(204);联结部,布置在前部边缘(202)处、在铰接罩盖与结构体之间,且确保了铰接罩盖在关闭位置与打开位置之间的移位;以及锁定系统(400),布置在后部边缘(204)处,且在锁定位置与解锁位置之间可移动,在关闭位置中,前部边缘(202)处于在前罩盖(110a)下方。因铰接罩盖可以容易且快速地打开和关闭,短舱减轻了技术人员的工作。这种布置还避免了脱离(bailing)现象。
Aircraft turbine engine assembly comprising a hinged cover
包括铰接整流罩的飞行器涡轮机组件
2020-05-01
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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