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Journade, Toulouse

Frederic Journade, Toulouse FR

Patent application numberDescriptionPublished
20080223983Method for Mounting an Aircraft Engine on a Rigid Structure of a Strut for Locking the Engine - The invention concerns a method to mount an aircraft engine on a rigid structure of an engine mount, comprising a securing step, on the structure, to secure an attachment body (09-18-2008
20080224018Engine Assembly for an Aircraft Comprising an Engine as Well as an Engine Mounting Stucture - An engine assembly including an engine mount, the engine mount including a rigid structure including a box and a mounting system positioned between the engine and the rigid structure. This mounting system includes an aft attachment. The assembly further includes a thermal protection system for the box, including a preferably ventilated duct forming a heat barrier and extending between the box and the engine. The duct extends rearward beyond the aft engine attachment.09-18-2008
20080245926Engine Assembly for an Aircraft Comprising an Engine as Well as an Engine Mounting Structure for Such an Engine - An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including an outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the outlet of the heat exchanger system is provided on an outlet pipe connected to the exchanger and passing through a structural block fixed on a box, between the box and the engine.10-09-2008
20080251633Engine Assembly for an Aircraft Comprising an Engine as Well as an Engine Mounting Structure for Such an Engine - An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including a second outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension.10-16-2008
20080272229Strut for Locking the Engine of an Aircraft - An engine mount for an aircraft engine. The engine mount includes a rigid structure forming a box closed at its forward end by a forward closure rib, and a mounting system including a forward engine attachment having an attachment body fixedly mounted on the rigid structure. The attachment body lies against a forward surface, and the engine mount includes at least one shear pin passing at least in part through the attachment body and forward closure rib.11-06-2008
20100170984ENGINE ASSEMBLY FOR AIRCRAFT WITH SLIDING NANCELLE - An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa.07-08-2010
20110079679DEVICE FOR LOCKING AN ENGINE ON AN AIRCRAFT PYLON - The device for locking an engine (04-07-2011
20110154831AIRCRAFT ENGINE ASSEMBLY COMPRISING A TURBOJET ENGINE WITH REINFORCING STRUCTURES CONNECTING THE FAN CASING TO THE CENTRAL CASING - An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing.06-30-2011
20110155847AFT PYLON FAIRING FOR AN AIRCRAFT ENGINE SUSPENSION SYSTEM - This invention relates to an aft pylon fairing (06-30-2011

Patent applications by Frederic Journade, Toulouse FR

Frédéric Journade, Toulouse FR

Patent application numberDescriptionPublished
20110197595ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING ATTACHMENTS FOR ENGINES OFFSET BELOW ON THE FAN FRAME - An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up thrust loads brought onto the fan frame, and arranged such that the third attachment passes through a first diametrical plane of the turbojet, the first and second attachments being disposed on one side and another of the first plane. The first and second forward engine attachments are respectively brought to the fan frame at two points, situated beyond the second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third attachment.08-18-2011

Jerome Journade, Toulouse FR

Patent application numberDescriptionPublished
20090292483DEVICE AND METHOD FOR DETERMINING A RUNWAY STATE, AIRCRAFT COMPRISING SUCH A DEVICE AND PILOTING ASSISTANCE SYSTEM USING THAT RUNWAY STATE - This invention relates to a device and a method for determining an airport runway state, as well as to the use of such a datum.11-26-2009
20100294890METHOD AND DEVICE FOR REDUCING THE INDUCED SPEEDS IN VORTICES IN THE WAKE OF AN AIRCRAFT - A method and a device for creating a continuous protected space along the path of an aircraft, in which protected space a maximum induced speed Vtc in a vortex of radius Rtc in the wake of an aircraft is decreased by increasing the radius Rtc. The method includes a preliminary step of identifying changes in the aerodynamic configurations of the aircraft liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, —for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex, —carrying out, along the course of the aircraft, at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space.11-25-2010