Patent application number | Description | Published |
20090165463 | Fixing System for a Component of a Turbojet Pod - The invention concerns a fixing system for at least one component of a pod of a turbojet on an engine strut to which the pod is attached and comprising at least one coupling zone provided by the component capable of co-operating with at least one complimentary coupling zone provided by the strut, and fixing means for providing with complementary fixing means a rigid and detachable connection between said component and the strut. The invention is wherein the fixing means and the complementary fixing means are capable of slightly pivoting relative to each other, as well as relative to a corresponding pod. | 07-02-2009 |
20110108357 | ACOUSTIC PANEL FOR AN EJECTOR NOZZLE - The invention relates to an acoustic panel ( | 05-12-2011 |
20120217372 | ASSEMBLY FOR HOLDING THE INTERFACE OF STATIONARY OUTER STRUCTURE OF A NACELLE AND HOUSING OF A JET ENGINE - The invention relates to an assembly for holding the interface of a stationary outer structure ( | 08-30-2012 |
20130234447 | LOCKING DEVICE WITH MECHANICAL DETECTION OF CLOSING AND OPENING - A locking device includes a bolt capable of engaging with a corresponding hook, the bolt being mounted against a resilient return spring that tends to return the bolt into a spaced apart position. The locking device further includes a detection linkage, which is moveable between a first position and a second position. In the first position, the linkage enables unlocking of the bolt and the hook. In the second position, the linkage engages with a portion of the locking pair so as to block the unlocking. | 09-12-2013 |
20130263600 | ASSEMBLY INCLUDING A REVERSE THRUST DEVICE AND SYSTEM FOR ACTUATING SAID DEVICE - A reverse thrust device and a system for actuating the reverse thrust device is provided by the present disclosure. The device includes at least one cowl that is translatably mounted in a direction substantially parallel to a longitudinal axis of a nacelle. The actuation system includes an actuation means that is capable of activating translational and rotational movement of the cowl and a panel of a nozzle. The actuation system also includes a downstream locking means for the nozzle and the cowl. The downstream locking means includes at least two reversible states, one of the states being a locked state in which the downstream locking means is suitable for locking the panel of the nozzle into a position for varying the section for outputting the nozzle with the cowl. | 10-10-2013 |
20130280052 | NACELLE FOR A BYPASS TURBOFAN ENGINE - A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal. | 10-24-2013 |
20140000238 | LOCKING/UNLOCKING DEVICE FOR A THURST REVERSER WITH A SLIDING COVER AND ADAPTIVE NOZZLE FOR AIRCRAFT ENGINE NACELLE | 01-02-2014 |
20140245716 | TWIN-DOOR THRUST REVERSER - A thrust reverser for a turbojet aircraft engine nacelle includes a pair of twin doors including an upstream door and a downstream door which is connected to the upstream door by a connecting rod. The thrust reverse also includes an actuating cylinder for operating the upstream door between a direct jet position in which the two doors are closed and a reversed jet position in which the two doors are open and deflects a portion of a cold air stream flowing inside the nacelle. A locking system of the thrust reverser locks the upstream and downstream doors relative to one another by the operation of the actuating cylinder alone. | 09-04-2014 |
20140291066 | AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural. | 10-02-2014 |
20140360158 | TWIN-DOOR THRUST REVERSER - A thrust reverser for aircraft turbojet engine nacelle includes at least one upstream door and a downstream door. The upstream and downstream doors move in concert between a direct jet position and a reverse jet position. In the direct jet position, two doors are closed, and in the reverse jet position the two doors are open and able to deflect a part of a cold air flow circulating inside the nacelle. The thrust reverser further includes a curved downstream edge of the upstream door to make adapted a part of cold air flow circulating between an upper camber of the upstream door and a lower camber of the downstream door. | 12-11-2014 |
20140369812 | TURBINE ENGINE NACELLE FITTED WITH A HEAT EXCHANGER - A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle. | 12-18-2014 |
20150030445 | NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE - A nacelle for a turbojet engine has a longitudinal axis and a rear section including an annular vein formed by a wall of a fixed internal structure and a wall of an external structure. The nacelle includes a device for modulating the cross-section of a space formed by the annular vein. The device includes an injector to inject an auxiliary flow of a gas so as to vary the orientation or speed of the auxiliary flow, a suction orifice for drawing in part of the injected auxiliary flow, and an internal auxiliary flow return area in one or more walls. In particular, the internal return area allows the circulation of part of the injected auxiliary flow and the drawn-in auxiliary flow | 01-29-2015 |
20150030446 | NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE - The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced. | 01-29-2015 |