Class / Patent application number | Description | Number of patent applications / Date published |
248554000 | AIRCRAFT ENGINE SUPPORT | 34 |
20080197262 | 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 two lateral brackets each including a longitudinal portion in contact with an inner face of the lateral panel associated with it and mounted fixed on the same inner face, and a transverse portion including an attachment interface for the aft attachment body, the transverse portion configured to pass through a recess formed on the associated lateral panel. | 08-21-2008 |
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 |
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 |
20080230675 | Two-Shackle Aircraft Engine Attachment - An aft attachment for an aircraft engine assembly. The attachment has a double boomerang structure including two three-point shackles that are duplicated: only four attachment points are present at the engine mount and two at the engine, the failsafe function being ensured by the dual structure. This attachment design does not sacrifice safety criteria, while providing a more lightweight structure. | 09-25-2008 |
20080296469 | SYSTEM FOR TRANSPORTING A GAS TURBINE ENGINE - A transport system suited for transporting a turbine engine mounted to an engine docking unit is provided. The transport system is capable of adjusting the attitude of the docking unit in at least the lateral and longitudinal directions relative to the engine to facilitate the loading and unloading of the turbine engine to and from the transport system. | 12-04-2008 |
20080315064 | SUSPENSION FOR SUSPENDING A TURBINE ENGINE FROM THE STRUCTURE OF AN AIRCRAFT - The present invention relates to the suspending of a turbine engine from the structure of an aircraft using a beam with means of attachment to said structure and at least one link rod articulated via one end to a journal secured to the beam and via the other to a fitting secured to the turbine engine. This suspension is one wherein the journal is mounted on the beam via a flexible coupling formed of two preloaded laminated, elastomer and metal, cylinders. | 12-25-2008 |
20090101787 | Gas Turbine Engine Systems Involving Rotatable Annular Supports - Gas turbine engine systems involving rotatable annular supports are provided. In this regard, a representative support assembly for a gas turbine engine includes: a rotatable member having a first end located about a first annulus; and a stationary member located about a second annulus; the first end of the rotatable member being rotatably coupled with the stationary member, with at least a portion of the first annulus being coextensive with at least a portion of the second annulus, the first end being operative to rotate locally with respect to a corresponding portion of the stationary member. | 04-23-2009 |
20090278021 | Device for removing and installing aircraft components - The invention relates to a modular device for removing and installing aircraft power plant components comprising a modular frame ( | 11-12-2009 |
20090309005 | Thrust mounting arrangement - Mounting of gas turbine engines in aircraft requires use of thrust struts associated with mountings. It is important should there be failure that a load path is maintained. Furthermore, on a wing or in-situ inspection is highly desirable with respect to reducing maintenance costs. Of particular concern is failure as a result of cracking both sideways and vertical which may result in loss of all load paths through the mounting. By provision of independent cranks which are associated through crank pivots in apertures of the cranks and then articulation about central pivots provided in apertures and a central element along with pivot association of the struts through pivots created about apertures in the cranks load paths are maintained. By independent provision of the cranks sideways and vertical cracking cannot cause failure in both load paths to the arrangement from the struts. Furthermore, gaps between the cranks and the mounting and in particular snubber surface can be monitored to indicate component failure. | 12-17-2009 |
20100155566 | METHOD AND APPARATUS FOR MOUNTING AND DISMOUNTING AN AIRCRAFT ENGINE - Apparatus and method for removing an aircraft engine. A method includes mounting a frame assembly in supported connection with a support member of an associated aircraft. The frame assembly includes a frame member, a movable assembly mounted in movable relationship to the frame member, and a plurality of engine winches mounted in supported connection with the movable member. Each engine winch has an associated engine cable operably connected thereto. The movable assembly is movable between forward and rearward positions. The method further includes supporting the weight of at least a portion of an aircraft engine with the engine cables and moving the movable member relative to the frame member to displace the portion of the aircraft engine. | 06-24-2010 |
20120080582 | SPIGOT-TYPE FASTENER PROVIDED WITH AT LEAST ONE MEANS FOR MEASURING THE FORCE GENERATED BY AN AIRCRAFT ENGINE - The invention relates to a spigot-type fastener ( | 04-05-2012 |
20120119056 | BEAM FOR SUSPENDING A TURBOSHAFT ENGINE FROM AN AIRCRAFT STRUCTURE - A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibres. In one embodiment, the beam takes a form of a circle arc. | 05-17-2012 |
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 |
20120248284 | SUPPORTING STRUCTURE FOR THRUST REVERSER, IN PARTICULAR HAVING CASCADES - The present invention relates to a supporting structure ( | 10-04-2012 |
20120286125 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE, COMPRISING BLOCKS FOR CLAMPING AN ENGINE ATTACHMENT WITH A WEDGE EFFECT - A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane. | 11-15-2012 |
20120286126 | SUSPENSION RODS FOR THE BYPASS FLOW DUCT OF A TURBOJET WITH ECCENTRIC BALL JOINTS - Device for assembly of a connecting rod ( | 11-15-2012 |
20130037688 | TURBOJET ENGINE FAN DUCT SUSPENSION USING CONNECTING RODS WITH ELASTOMER BUSHING - Device for adjusting the length of a connecting rod and consisting of a bushing positioned inside an eye of the said connecting rod, the said bushing comprising at least one element in which there is made a bore to act as a support for a pivot pin intended to pass through the eye, characterized in that the said element is a cylinder made of a metallic material covered by a cylinder made of an elastomeric material so as to form with the metallic cylinder a cylinder homothetic with the previous one, the generatrices of the said cylinders being oriented in a direction that is inclined with respect to the longest length of the said connecting rod. | 02-14-2013 |
20130153739 | APPARATUSES AND SYSTEMS WITH VERTICALLY AND LONGITUDINALLY OFFSET MOUNTING FLANGES - A flanged apparatus includes an apparatus body and a flanged mount, which includes a support pylon, a first mounting flange and a second mounting flange. The support pylon includes a first pylon segment, a second pylon segment and a routing notch. The first pylon segment is cantilevered from the apparatus body, and extends to the first mounting flange. The second pylon segment is cantilevered from the first pylon support, and extends from the first mounting flange to the second mounting flange. The routing notch extends vertically between the first pylon segment and the second pylon segment. The first mounting flange and the second mounting flange extend laterally from the support pylon, and the first mounting flange is separated from the second mounting flange by a longitudinal distance and a vertical distance. | 06-20-2013 |
20130193298 | GAS TURBINE ENGINE MOUNTING STRUCTURE WITH SECONDARY LOAD PATH - A connection for mounting an aircraft engine to an aircraft pylon has a plate to be bolted to a portion of an aircraft engine, and a body extending rearwardly from the plate. The body has a main pivot attachment to a balance beam, which has thrust links pivotally attached to the balance beam. A back-up connection is included between the balance beam and the body such that the back-up connection allows normal pivoting movement of the balance beam relative to the body without contact at the back-up connection. | 08-01-2013 |
20130233997 | TURBINE ENGINE CASE MOUNT - A mount for a turbine engine has a semi-circular yoke with a first leg and a second leg. The mount also has a stanchion with a cylindrical section attached to the yoke, and a conical section attached to the cylindrical section. A mounting bracket is attached to the conical section. | 09-12-2013 |
20140021325 | Transport securing device of an aircraft gas turbine - The present invention relates to a transport securing device of an aircraft gas turbine with a securing element, which at its two end areas is each provided with a first and a second connecting element, with the first connecting element being designed to be suitable for fastening to a front suspension device and the second connecting element being designed to be suitable for fastening to a rear suspension device of an aircraft gas turbine. | 01-23-2014 |
20140027602 | HYBRID HINGE AND LATCH BEAM - A hybrid beam for support of a nacelle panel of a jet engine is disclosed. The beam is comprised of a first longitudinal composite panel and a second longitudinal composite panel, wherein the first longitudinal composite panel is integrally affixed to the second longitudinal composite panel along a longitudinal edge. The composite panels form a composite beam structure that is substantially open with a cross-section that is generally “L-shaped”. A plurality of hinge stations are affixed to a first side of the first longitudinal composite panel and at least one track guide is disposed on a second side of the first longitudinal composite panel. The track guides receive a head portion of a slider that is fixed to the translating jet engine nacelle panel. Each hinge station further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam. | 01-30-2014 |
20140061426 | SECONDARY LOAD PATH FOR GAS TURBINE ENGINE - A waiting link to support an engine on an aircraft includes a body portion including a first body portion opening, a second body portion opening, and a space therebetween. A first bearing is received in the first body portion opening and moveable in a generally vertical direction. A second bearing is received in the second body portion opening. The first and second bearings include a first and second bearing opening, respectively, that receives a first and second attachment member, respectively, that secures the body portion to a first and second structure, respectively. A cam is located in the space. The cam is pivotable between a first position and a second position. The waiting link does not provide a load path when the cam is in the first position, and when a primary load path fails, the waiting link provides the load path when the cam is in the second position. | 03-06-2014 |
20140084129 | ASSEMBLY FOR MOUNTING A TURBINE ENGINE CASE TO A PYLON - An assembly for mounting a turbine engine case to a pylon. The assembly includes a beam and a shackle. The shackle includes a plurality of side segments, and an intermediate segment that is engaged rotatably to the beam. Each of the side segments has a fastener aperture and a slot. The fastener aperture extends through the respective side segment. The slot extends laterally into the respective side segment. | 03-27-2014 |
20140145060 | COMPOSITE BEAM FOR TURBOJET ENGINE NACELLE SUPPORT STRUCTURE - A longitudinal beam for a turbojet engine nacelle support structure is provided. The longitudinal beam is primarily made from composite materials and in the shape of an L and includes a longitudinal web contacting with an attachment pylon of the nacelle and a sole. More specifically, the sole produces a receiving part capable of cooperating directly or indirectly by embedding with an end of an associated front frame. | 05-29-2014 |
20140374566 | ATTACHMENT PYLON FOR AN UNDUCTED FAN - A pylon configured to secure a turbine engine to a structural element of an aircraft, the pylon including a streamlined profile defined by two opposite faces and extending longitudinally between a leading edge and a trailing edge, and at least a first one of the two faces presenting at least locally a succession of non-through hollows and of bumps. | 12-25-2014 |
20150021455 | TURBINE ENGINE SUPPORT PART OF HYBRID STRUCTURE - A turbine engine support part including a main structure made of composite material and a reinforcing secondary structure made of metal and integrated in the main structure, the secondary structure presenting a geometrical shape and dimensions configured to impart mechanical strength to the support part in event of the main structure being destroyed. | 01-22-2015 |
20150136935 | GAS TURBINE ENGINE STAND - A gas turbine engine stand ( | 05-21-2015 |
248557000 | Resilient | 6 |
20090032673 | FLEXIBLE SUSPENSION FOR TURBINE ENGINE - The present invention relates to a suspension for suspending a turbine engine from the structure of an aircraft, comprising a beam with a first element accepting means of attachment to said structure and a second element accepting means of attachment to the turbine engine. It is one wherein the beam comprises at least a first plate and a second plate, which plates are intended to be positioned transversely with respect to the axis of the engine and joined together by a layer of elastomer, the first plate being secured to the first element and the other plate to the second element. | 02-05-2009 |
20100116965 | ISOLATED AXIAL SUPPORT STRUT FOR SUPPORTING AN AXIAL LOAD AND AXIAL SUPPORT STRUT ISOLATOR - A support strut includes a strut isolator with a first strut end member and a second strut end member, the second strut end distal from the first strut end. The first strut end member includes an outer rigid housing with an inner cavity. The second strut end member includes an inner rigid member extending into the outer rigid housing inner cavity and includes an inertial track extending in a direction from the first strut end towards the second strut end. The inertial track has a first entrance end proximate the first strut end and a second entrance end proximate the second strut end. The isolator includes a first outer tubular elastomer disposed between the outer rigid housing and the inner rigid member. The isolator includes a second inner end tubular elastomer disposed between the outer rigid housing and the inner rigid member proximate the second strut end. The isolator includes a third inner end tubular elastomer, the third inner end tubular elastomer disposed between the outer rigid housing and the inner rigid member proximate the first strut end. The isolator includes an isolator fluid in a first variable volume fluid chamber proximate the second strut end and the second track entrance end, and in a second variable volume fluid chamber proximate the first strut end and the first track entrance end. Movement of the first strut end member in a first strut direction towards the second strut end member plungers the fluid from the second variable volume chamber through the track towards the first variable volume chamber, and an opposite movement of the first strut end member in a second direction away from the second strut end plungers the fluid from the first variable volume chamber through the track towards the second variable volume chamber. | 05-13-2010 |
20110084192 | AIRCRAFT AUXILIARY POWER UNIT SUSPENSION SYSTEM FOR ISOLATING AN AIRCRAFT AUXILIARY POWER UNIT - The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency. | 04-14-2011 |
20110180684 | METHOD AND APPARATUS FOR CONTROLLING AN ELASTOMERIC DAMPER - A method of controlling an elastomeric damper. The damper is heated by passing an electric current through the damper or through a heating element in contact with the damper said heating causing a decrease in stiffness of the damper. The elastomeric damper may comprise an elastomeric material filled with electrically conductive particles, and the damper may be heated by passing an electric current through the elastomeric material. Alternatively the damper may be heated using a discrete resistive heating element, such as a coil embedded within the elastomeric damper or wound around it. | 07-28-2011 |
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 |
20160009403 | METHOD AND APPARATUS FOR REDUCING HIGH TRANSIENT MOUNT LOAD IN AIRCRAFT ENGINE MOUNTING SYSTEMS | 01-14-2016 |