Patent application number | Description | Published |
20080197233 | Engine Mounting Structure For an Aircraft - An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body. | 08-21-2008 |
20080217467 | Assembly For Aircraft Comprising a Wing System Element as Well as an Attachment Mast - An assembly for an aircraft including a wing element, a suspension pylon, a mechanism of attaching the pylon onto the element, including two forward half-attachments, each including a shackle and configured to resist forces applied along a vertical direction. The shackle is mounted firstly articulated onto a first fitting fixed to a forward spar of the element extending along the direction of the width, and is secondly mounted articulated onto a second fitting fixed to the rigid structure of the pylon. The two shackles are arranged in the same plane parallel to the direction of the width. | 09-11-2008 |
20080217502 | Monolithic Framework Engine Mounting Structure - A structure for an aircraft engine assembly suspension pylori. The pylori includes a monolithic frame, manufactured for example by casting or welding, covered with mechanically assembled skins. Advantageously, stiffeners are mechanically fixed to points through which forces are applied. The dual structure makes it possible to take advantage of integration during manufacturing while respecting safety criteria due to mechanical assemblies. | 09-11-2008 |
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 |
20080237394 | Engine Mounting Structure Interposed Between an Aircraft Wing System and Said Engine - A device for suspension of an engine, configured to be inserted between an aircraft wing and the engine. The device includes a rigid structure and a forward aerodynamic structure mounted fixed on the structure through a suspension mechanism. The forward aerodynamic structure is configured to carry engine fan casings and to be inserted between the rigid structure and the wing. The suspension mechanism includes at least one adjustable length connecting rod of which one end is mounted on the rigid structure, and the other end is mounted on the forward aerodynamic structure. | 10-02-2008 |
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 |
20080272230 | Engine Assembly for Aircraft - An aircraft engine assembly including a turbojet engine, an engine mount, and a plurality of engine attachments. The engine attachments include first and second forward attachments fixed to a fan case and located symmetrically in relation to a plane defined by a longitudinal axis of the turbojet engine and a vertical direction thereof, both forward attachments configured to transfer loads exerted in a longitudinal direction of the turbojet engine and in the vertical direction thereof. Moreover, each of the two forward attachments includes a shear pin mounted on the case and going through two walls of a clevis fixed on the engine mount. | 11-06-2008 |
20080296430 | System For Connecting a Crossbar to an Aircraft Engine Pylon - An arrangement configured to connect an evener bar onto a rigid structure of an aircraft engine mount, including a pin system slidingly mounted in a first passageway of a bracket to permit its displacement along a first longitudinal axis, in a first direction from a normal extended position to a retracted position in which the pin system is retracted within this same bracket, and conversely. The arrangement also includes a pin extending member carried by the system and configured to be moved parallel to the longitudinal axis, in a second direction from a normal retracted position to an extended position in which the pin extending member is joined to the system and projects beyond the system, and conversely. | 12-04-2008 |
20080315033 | Turbojet Engine Mounting Structure For Aircraft - A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively. | 12-25-2008 |
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 |
20100193627 | ASSEMBLY FOR AN AIRCRAFT INCLUDING A WING ELEMENT AND A SUSPENSION PYLON - The invention relates to an assembly for an aircraft comprising a wing element ( | 08-05-2010 |
20100209254 | VANE FOR AIRCRAFT TURBINE ENGINE RECEIVER, PROVIDED WITH TWO HOLLOW CORES LODGED IN ONE ANOTHER - The invention relates to a vane ( | 08-19-2010 |
20100215498 | BLADE FOR TURBOMACHINE RECEIVING PART, COMPRISING AN AIRFOIL PART INCLUDING A MECHANICAL FUSE - The invention refers to a blade ( | 08-26-2010 |
20100215499 | BLADE RETAINING DEVICE FOR TURBO MACHINE PROPELLER - The invention concerns an aircraft turbomachine propeller comprising a plurality of blades ( | 08-26-2010 |
20110197595 | ENGINE 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 |
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 |
20110233326 | 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 two openings distributed on either side of a vertical median plane of the aircraft. The support structure includes a first half-structure and a second half-structure respectively extending through the first and second fuselage openings, the first and second half-structures being joined to each other so that they can be disassembled in an inside space defined by the fuselage. | 09-29-2011 |
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 |
20120070287 | PROPELLER FOR AN AIRCRAFT TURBINE ENGINE COMPRISING A VANE RETAINING RING MOUNTED ABOUT THE HUB - A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter. | 03-22-2012 |
20120080554 | AIRCRAFT ENGINE ATTACHMENT PYLON COMPRISING TWO FRONT WING SYSTEM ATTACHMENTS WITH ORTHOGONAL SHEARING PINS - The present invention relates to an aircraft assembly ( | 04-05-2012 |
20120080555 | TAKE-UP DEVICE FOR THRUST FORCES WITH CONNECTING RODS FOR AIRCRAFT ENGINE ATTACHMENT PYLON, INTEGRATING THREE ALIGNED BALL JOINTS - The present invention relates to a take-up device for thrust forces ( | 04-05-2012 |
20120111995 | ENGINE ASSEMBLY FOR AN AIRCRAFT THE ENGINE ATTACHMENT STRUT OF WHICH INCLUDES A STRUCTURAL CASE FORMING AN INTERNAL RADIAL DELIMITATION OF THE SECONDARY FLOW - An engine assembly for an aircraft including a dual-flow turbomachine and an attachment strut. The turbomachine includes a structural case extending downstream of the hub of an intermediate casing, the case contributing to the internal radial delimitation of a passage for a secondary flow of the turbomachine. Also, the primary structure includes a structural case, assembled on the structural case and positioned directly downstream of the structural case such that it also contributes to the internal radial delimitation of the passage for the secondary flow. The primary structure also includes an offset structure positioned in the passage, and configured to connect the case to an element of the aircraft. The structural case also includes a thrust reversal system. | 05-10-2012 |
20120111996 | ASSEMBLY FOR AN AIRCRAFT COMPRISING A TURBOMACHINE ATTACHMENT STRUT OF WHICH THE MEANS FOR ATTACHMENT TO THE WING ARE ARRANGED IN A T SHAPE - An assembly for an aircraft including: a mechanism attaching a primary structure of an attachment strut to a wing, forming an isostatic system; an attachment housed in a leading edge of the wing and configured to only take up forces exerted along the transverse and longitudinal directions; and an attachment including a connecting rod extending rearwardly, of which one end is connected to the primary structure and the other end is connected to the wing element, the connecting rod being offset along the vertical direction of the attachment. | 05-10-2012 |
20120121417 | BLADE-RETAINING DEVICE FOR TURBOMACHINE PROPELLER - An aircraft turbomachine propeller including multiple blades assembled on a hub rotating around an axis of rotation of the propeller, that can reduce risks of loss of the blade following impact of a foreign body. At least one blade includes a recess opening radially towards the inside in the area of the base of this blade. A retaining device includes a moving retaining mechanism positioned in the recess and configured to be moved from a retracted position to a deployed blade-retaining position, and vice versa. | 05-17-2012 |
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 |