公开(公告)号：US08869506B2

公开(公告)日：2014-10-28

申请号：US13692227

申请日：2012-12-03

Applicant: Aircelle

Inventor： Jean-Philippe Joret ,  Peter Segat ,  Guy Bernard Vauchel ,  Georges Alain Bouret

IPC: F02K1/80 ,  F02K1/70 ,  B64D29/06 ,  F02K1/76

CPC classification number: F02K1/70 ,  B64D29/06 ,  F02K1/766

Abstract: A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl.

Abstract translation: 提供了一种用于飞机的涡轮喷气发动机的机舱，其包括风扇壳体，位于风扇壳体上游的内部结构以及位于风扇壳体下游的推力反向器。 推力反向器包括限定外线（LE）的整流罩，并包括两个可拆卸的半罩。 用于吸收周向应力的装置被成形为当半罩处于闭合位置时，一方面将其锁定在锁定构型上，另一方面允许半罩在占据解锁构造时允许打开半罩。 应力吸收装置位于塔架的上游部分的下方，并且仅仅安装在半罩上，以允许独立于外部风扇罩的打开/关闭而打开两个半罩。