Abstract: The cascade-type thrust reverser comprises a cowling in which there is formed an opening which, when in a direct thrust mode, is closed by a sliding cowl and which, in a thrust-reversal mode, is uncovered by the translation of the said sliding cowl, a fan duct being defined between an interior skin and an exterior skin, said exterior skin having a radius Re in the plane transversal to the longitudinal axis of the reverser and passing through the upstream end of the sliding cowl in the direct thrust mode, and said interior skin having, downstream of this upstream plane, a maximum radius Ri in a plane parallel to the upstream plane, the upstream end of the said sliding cowl substantially blocking the fan duct upstream of the said downstream plane in a thrust-reversal mode, the said radius Re being less than the radius Ri.

Abstract: The cascade-type thrust reverser comprises a cowling in which there is formed an opening which, when in a direct thrust mode, is closed by a sliding cowl and which, in a thrust-reversal mode, is uncovered by the translation of the said sliding cowl, a fan duct being defined between an interior skin and an exterior skin, said exterior skin having a radius Re in the plane transversal to the longitudinal axis of the reverser and passing through the upstream end of the sliding cowl in the direct thrust mode, and said interior skin having, downstream of this upstream plane, a maximum radius Ri in a plane parallel to the upstream plane, the upstream end of the said sliding cowl substantially blocking the fan duct upstream of the said downstream plane in a thrust-reversal mode, the said radius Re being less than the radius Ri.

Abstract: The thrust reverser for a turbo-fan engine is comprised of: a plurality of oors located in openings radially spaced in a shroud enclosing the engine and canalizing the jet flow from the engine, the doors being adapted to be pivoted, within a fixed structure, from a stowed position, in which they do not interfere with the jet flow, to a deployed position in which they block the jet flow and deflect it through the openings; an actuator having a body attached to the fixed structure and a rod attached to the center of each pivoting door for moving the door from the stowed position to the deployed position, and vice versa; and sealing elements comprising a main seal provided on the fixed structure and a separate annular seal located around the actuator body, the sealing elements mating with each door, when in the stowed position, and with the fixed structure to prevent pressure leakage of the jet flow.

Abstract: The thrust reverser has an external cowl and a fixed engine core cowl, defining together an annular duct through which high bypass fan air is driven rearwardly. The external cowl has a section adapted to be translated between forward and rearward positions, under control of linear actuators. The translating section includes openings fitted with doors pivotally mounted on the translating section and linked to the engine core cowl so that the translating section translating movement in a rearwardly direction causes the doors to pivot from a stowed position in which they close the openings and a deployed position in which they block the annular duct. The thrust reverser includes only two such doors, the surface area occupied by each door representing more than 30% of the peripheral surface area of the inner wall of a portion of the translating section limited by the vertical planes including the upstream end of the translating section and the pivot axis of the door, respectively.

Abstract: The invention relates to a thrust reverser for a bypass jet engine that reverses the fan flow. The thrust reverser is installed in the fixed outer cowl and is comprised of pivoting doors that block the fan flow in order to create reverse thrust. A translating annular nozzle is located aft of the pivoting doors in the stowed position, preventing in flight inadvertent deployment. When the nozzle are translated aft, the doors are free to pivot and, at the same time, the section of the fan nozzle can be adjusted to produce more or less fan flow.

Abstract: A thrust reverser with pivoting doors for a jet aircraft engine, with a system for security against in-flight deployment of a thrust reverser. The system has two independent locking assemblies, the first being a primary lock and the second being a safety lock that is positioned away from the first lock to avoid damage from a ruptured piece of the engine turbine disk. The first lock is hydraulically controlled and the second lock is electrically controlled and entirely independent, thus assuring an in-flight inadvertent deployment will not occur as a result from failures, faulty commands or inadequate maintenance.

Abstract: A thrust reverser comprised of two pivoting doors for engines mounted on an aircraft rear fuselage. For thrust reversal, the two pivoting doors are rotated into the mixed flow by two actuators, one actuator per door. On the extremities of each pivoting door, efflux flow turning devices are installed. These devices are removable boxes comprised of deflectors that can be oriented to turn the flow. Two boxes are required for each pivoting door.

Abstract: The invention relates to thrust reversers with doors for a jet engine. The upstream edge of the reverser doors is equipped with a deflecting structure consisting of a rigid frame (10, 12, 13) fixed to the door and delimiting a space (14) capped by a stiffener (15). In the space (14) are housed vanes (16) with aerodynamic profile in the form of a wing which is inclined by an angle a with respect to the plane of the frame (10, 12, 13) in order to orient laterally the flow of the gases which is diverted by the reverser. This arrangement makes it possible to reduce, or even to prevent, re-ingestion by the engine of the diverted gases, or interference of the latter with the wing structure of the aircraft.