Turbojet engine nacelle including a device for absorbing circumferential stresses

摘要

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.

主权项

1. A nacelle for a turbojet engine of an aircraft, including:
a fan case surrounding a fan upstream from the turbojet engine, said fan case being surrounded by an external fan cowl and being attached on a pylon for supporting the nacelle; an internal structure positioned upstream from the fan case and surrounding the turbojet engine; and a thrust reverser positioned downstream from the fan case and comprising a cowl defining with the internal structure a ring shaped vein for letting through an airflow, said cowl delimiting an external line of said ring shaped vein and including two removable half cowls respectively having upper edges equipped with hinges that bin the two removable half cowls on the pylon, said hinges being shaped as to allow pivoting of the two removable half cowls between closed and open positions around respective longitudinal axes forming two hinge lines; and a device for absorbing circumferential stresses connecting together the upper edges of the two removable half cowls, said stress absorbing device being shaped so as to lock the two removable half cowls in the closed position when said stress absorbing device occupies a locking configuration and for allowing the opening of the two removable half cowls when said stress absorbing device occupies an unlocking configuration, wherein said stress absorbing device is positioned under an upstream portion of the pylon, upstream from the hinges of the two removable half cowls on the pylon, and is inserted between the external line of the ring shaped vein and the two hinge lines said stress absorbing device being exclusively attached to the two removable half cowls in order to allow the opening of the two removable half cowls independently of the opening/closing of the external fan cowl, said stress absorbing device including at least one actuator equipped with a rod slidably mounted on a hollow body between a retracted position in the body and a deployed position out of the body, said rod having a first end permanently attached on the upper edge of one of the two removable half cowls and a second opposite end extending in the body, said body having a first end provided with an orifice for letting through the rod and a second opposite end permanently attached on the upper edge of the other removable half cowl, wherein the actuator further includes a locking/unlocking system cooperating with the rod in order to lock/unlock the rod in the retracted position, said actuator being an actuator system with constant links, wherein said actuator is permanently attached on both two removable half cowls of the thrust reverser.