Abstract: A turboprop engine includes a power jet mounted coaxially to the engine axis (X-X?), and has a fan case and a gas ejecting system provided with two afterbody half-cowlings (10b) each of which is pivotable around an axis (A2) between open and closed positions, wherein the half-cowlings are connected to the downstream of the fan case through a ‘V-blade/V-groove’ system. In a first embodiment, the pivot axes (A2) make an angle ?>3° to the engine axis (X, X?) and a joint plane (Z2-Z2) between the afterbody half-cowlings and the downstream of the fan case makes to the plane (Y, Y?) perpendicular to the engine axis (X, X?) an angle ? in such a way that the difference between the angle ? and the angle ? is less than or equal to 3°. In the other embodiment, the axes are converged to each other in a downstream direction.

Abstract: A turboprop engine includes a power jet mounted coaxially to the engine axis (X-X?), and has a fan case and a gas ejecting system provided with two afterbody half-cowlings (10b) each of which is pivotable around an axis (A2) between open and closed positions, wherein the half-cowlings are connected to the downstream of the fan case through a ‘V-blade/V-groove’ system. In a first embodiment, the pivot axes (A2) make an angle ?>3° to the engine axis (X, X?) and a joint plane (Z2-Z2) between the afterbody half-cowlings and the downstream of the fan case makes to the plane (Y, Y?) perpendicular to the engine axis (X, X?) an angle ? in such a way that the difference between the angle ? and the angle ? is less than or equal to 3°. In the other embodiment, the axes are converged to each other in a downstream direction.

Abstract: The invention discloses an aeroengine nacelle afterbody of the type comprising a common nozzle for exhausting the mixed hot and cold gases originating respectively from the fan duct and from the aeroengine combustion chamber, the said nozzle having a longitudinal axis more or less coincident with the axis of the said engine. The common exhaust nozzle consists of two half-nozzles which are more or less symmetric with respect to a plane containing the said longitudinal axis, the said half-nozzles being, on the one hand, individually hinged via one of their longitudinal edges to a support structure hanging down from the wing structure or from the fuselage of the aircraft and, on the other hand, lockable together along their opposite longitudinal edges.

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 invention discloses an aeroengine nacelle afterbody of the type comprising a common nozzle for exhausting the mixed hot and cold gases originating respectively from the fan duct and from the aeroengine combustion chamber, the said nozzle having a longitudinal axis more or less coincident with the axis of the said engine. The common exhaust nozzle consists of two half-nozzles which are more or less symmetric with respect to a plane containing the said longitudinal axis, the said half-nozzles being, on the one hand, individually hinged via one of their longitudinal edges to a support structure hanging down from the wing structure or from the fuselage of the aircraft and, on the other hand, lockable together along their opposite longitudinal edges.

Abstract: A pivoting door type thrust reverser assembly for a dual flow engine incls a fixed cowling construction with a front body portion (9) and a rear body portion (12) joined by longitudinal beams (10,11) and defining reversal chambers in each of which a door (7) is pivotably received. The door pivot pins (17) are carried by two pairs of struts (15,16) such that the pivot pins are spaced from the engine axis X-X'.

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: Thrust reverser for a jet engine of the type with doors equipped with auxiliary flaps. The invention relates to thrust reversers with doors 13 having a front deflector 15. The door is equipped, on its inner face, with one or two auxiliary flaps 16 articulated about axles 17 and controlled by a lever 21 articulated on the door at 22 and stressed into a retracted flap position by means of a spring 24. At the end of closure of the door, the end 31 of the lever interacts with a stop 33 which ensures that the lever tilts and that the flap 16 moves away from the door 13.