Patent application number | Description | Published |
20080223983 | Method 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 |
20080224018 | Engine 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 |
20080245926 | Engine 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 |
20080251633 | Engine 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 |
20080272229 | Strut 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 |
20100170984 | ENGINE 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 |
20110079679 | DEVICE FOR LOCKING AN ENGINE ON AN AIRCRAFT PYLON - The device for locking an engine ( | 04-07-2011 |
20110154831 | AIRCRAFT 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 |
20110155847 | AFT PYLON FAIRING FOR AN AIRCRAFT ENGINE SUSPENSION SYSTEM - This invention relates to an aft pylon fairing ( | 06-30-2011 |
20110203254 | GAS EJECTION CONE FOR AN AIRCRAFT TURBOJET EQUIPPED WITH A DEVICE FOR GENERATING TURBULENCE IN A PRIMARY FLOW LIMITING JET NOISE - A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body. | 08-25-2011 |
20110210229 | STRUCTURAL ROD INCORPORATING A VIBRATION FILTRATION MODE - A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material. | 09-01-2011 |
20110226893 | REAR PART OF AN AIRCRAFT COMPRISING A STRUCTURE FOR SUPPORTING ENGINES, CONNECTED TO THE FUSELAGE BY AT LEAST ONE BLOCKING ELEMENT UNDER COMPRESSION LOADING - A rear part of an aircraft including a support structure for supporting engines, passing through the fuselage, through first and second openings. The rear part includes a connection structure connecting the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The first and second connection mechanisms each include at least one blocking element of the support structure, under compression loading by being applied to the casing and to the support structure. | 09-22-2011 |
20110226894 | REAR PART OF AN AIRCRAFT COMPRISING A STRUCTURE FOR SUPPORTING ENGINES, EXTENDING THROUGH THE FUSELAGE AND CONNECTED THERETO BY AT LEAST ONE CONNECTING ROD - A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings. | 09-22-2011 |
20120006937 | REAR PART OF AN AIRCRAFT INCLUDING AN ENGINE SUPPORT STRUCTURE ASSEMBLED SO AS TO OSCILLATE ON THE FUSELAGE - A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings. | 01-12-2012 |
20120168558 | AIRCRAFT ASSEMBLY INCLUDING AN ELEMENT FOR MOUNTING AN ENGINE AND ASSOCIATED AIRCRAFT - An engine is mounted on a structure by an intermediate structure assembled by flanges, to the structure and to the engine, where a rigid structure connects the flanges. This arrangement enables design of the structure to be simplified while allowing a substantial overhang when it is sought to mount the engine by the plane of its center of gravity, while being obliged to move the mounting structure away from it. The intermediate structure is resistant to forces resulting from the overhang, and also allows assemblies that are favorable to a balanced transmission of forces to the structure and a satisfactory ability to filter vibrations. | 07-05-2012 |
20120175462 | AIRCRAFT ENGINE MOUNTING STRUCTURE, ASSEMBLY COMPRISING THIS STRUCTURE AND ASSOCIATED AIRCRAFT - An engine is suspended from a main linear portion of a structure mounted on a fuselage or a wing surface of an aircraft. A connection includes flat symmetrical wings at an angle to one another, to support an attaching flange on which the engine is mounted, directly or through a mounting element. The flat shape of the wings makes them easy to manufacture, and enables them to resist the forces satisfactorily. The intermediate element resists overhang forces of the mounting satisfactorily. Flexible connections filter the engine's vibrations and prevent irregular forces being transmitted. | 07-12-2012 |
20130105622 | AFT PYLON FAIRING FOR AIRCRAFT ENGINE SUSPENSION SYSTEM, COMPRISING A HEAT SHIELD CAPABLE OF EXPANDING FREELY | 05-02-2013 |