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Safran Nacelles patents


Recent patent applications related to Safran Nacelles. Safran Nacelles is listed as an Agent/Assignee. Note: Safran Nacelles may have other listings under different names/spellings. We're not affiliated with Safran Nacelles, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "S" | Safran Nacelles-related inventors


Supply device for an electric actuator system

The present disclosure relates to a nacelle for an aircraft turbofan engine and an aircraft that includes a nacelle that includes a supply device for supplying electric power to an electric actuator system allowing movement of a mobile member for deflecting a stream between a first position parallel or substantially parallel to the flow of the stream and a second position allowing the flow of the stream to be deflected so as to modify the path of the stream in one direction and/or the speed of the stream.. . ... Safran Nacelles

Acoustic attenuation panel made of an oxide ceramic composite material with a core made of an electrochemically-converted metal material

The present disclosure relates to a method for producing an acoustic attenuation panel having two outer skins made from a composite material with a ceramic matrix containing a fibrous reinforcement. The skins are assembled on each side of a central honeycomb core having walls forming acoustic cavities produced by at least partial electrochemical conversion of aluminum into aluminum oxide. ... Safran Nacelles

Porous ceramic material obtained by weaving and acoustic panel including such a material

The present disclosure concerns a porous body made of a ceramic-matrix composite material for an acoustic attenuation panel and a method of manufacturing the porous body. The porous body includes a plurality of interwoven ceramic fibers, a metal oxide matrix, and a plurality of channels interwoven with the ceramic fibers and interconnected together. ... Safran Nacelles

Acoustic attenuation structure with a plurality of attenuation degrees for a propulsion assembly of an aircraft

The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. ... Safran Nacelles

Thrust reverser for a nacelle of an aircraft turbojet engine

A thrust reverser for a nacelle of an aircraft turbojet engine is provided that includes a thrust reverser cowl movable along a direction parallel to a longitudinal axis of the nacelle and a variable section outlet nozzle extending from the thrust reverser cowl. The thrust reverser further includes an actuator, a first locking device to lock the thrust reverser cowl, a second locking device to lock the variable section outlet nozzle, and a reset lever. ... Safran Nacelles

Locking device for pivoting cowls of a thrust reverser

The present disclosure provides a device for locking a first cowling and a second cowling of a thrust reverser of an aircraft propulsion assembly. The cowlings are mounted such that each cowl pivots around a longitudinal axis between a closed flight position and an open maintenance position. ... Safran Nacelles

Composite panel and aircraft turbojet engine nacelle comprising such a panel

The present disclosure relates to a composite panel having a sandwich structure formed by a central core having a primary cellular structure, for example, of the honeycomb type, sandwiched between two skins. The primary cellular structure includes an array of main cells. ... Safran Nacelles

Method for manufacturing a preform made of woven reinforcement fibers having a variable cross-section

The present disclosure provides a method for manufacturing a preform made of reinforcement fibers woven in a longitudinal direction. The preform is impregnated with resin in order to form an elongated element having a variable transverse cross-section. ... Safran Nacelles

Thrust reverser for nacelle of aircraft turbofan

A thrust reverser for a nacelle of an aircraft turbojet engine includes at least one movable thrust reverser cowl, a means for locking the cowl, a variable section outlet nozzle, and at least one actuator including an actuator rod. The thrust reverser is provided with a resilient coupler comprising a body which is rigidly connected to the thrust reverser cowl and a resilient return and abutment device that engages with the actuating rod of the actuator such as to resiliently return the nozzle to a neutral position. ... Safran Nacelles

Aircraft turbojet engine nacelle

The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.. ... Safran Nacelles

Nacelle rear assembly for a turbojet engine comprising a suspension cradle

The present disclosure provides a rear nacelle assembly for a turbojet having at least one thrust reversal device to redirect air circulating from upstream to downstream in a flow path of a turbojet and a mast that connects the nacelle to a structure of an aircraft. In one form, the thrust reverser device includes a cradle having a first longeron and a second longeron extending longitudinally opposite sides of the mast. ... Safran Nacelles

Nacelle rear assembly for a turbojet engine comprising a cradle for a core-type mast

The present disclosure provides a nacelle rear assembly for turbojet engine including at least one thrust reverser device to redirect air flow circulating from upstream to downstream in a flow path of the turbojet engine and a mast to link the nacelle to a structure of the aircraft. In one form, the nacelle extends longitudinally from forth to back along an axis and includes a cradle fastened on the mast. ... Safran Nacelles

Acoustic attenuation panel for a turbojet engine nacelle

An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. ... Safran Nacelles

Tooling adapted for brazing a set of parts

The present disclosure relates to a brazing tooling for the manufacture of a part, and in particular to a tooling adapted for brazing a set of metallic parts, in particular a composite panel, in an enclosure of a brazing furnace. The tooling includes a first mold element and a second mold element clasped together and a bearing device. ... Safran Nacelles

08/24/17 / #20170241924

Method of characterizing the thermal ageing of composite materials, in particular composite materials having an organic matrix

The present disclosure relates to a method of characterizing the thermal ageing of a part made of composite material, in particular a composite material having an organic matrix. The method includes taking from the part a sample of composite material, subjecting the sample to modulated temperature differential calorimetry, determining, from the curve representing the total heat flow component associated with irreversible phenomena, the temperature at which a local extremum appears, this local extremum being characteristic of the thermal ageing, and determining the thermal ageing of the composite material by comparing the temperature at which the local extremum appears with a reference chart.. ... Safran Nacelles

08/17/17 / #20170232693

Method of repairing a perforated skin of a panel using a doubler

The present disclosure relates to a method of repairing a damaged portion of a perforated skin of a panel using a doubler made of composite material which is designed to be applied to the damaged portion of the perforated skin. The method includes at least one step in which a sealing film is applied to the damaged portion of the perforated skin in order to temporarily seal the perforations in the skin, and a step in which the doubler is produced over the previously deposited sealing film.. ... Safran Nacelles

08/10/17 / #20170226931

Assembly of an inner fixed structure of a turbojet engine nacelle and of a thermal protection

The present disclosure relates to an assembly of an inner fixed structure of a turbojet engine nacelle and of a thermal protection, said structure including an inner face, on which the thermal protection is added, and an outer face constituting a portion of the inner surface of a cold flow path, the assembly including at least one channel put in fluid communication the inner face and the outer face of the structure.. . ... Safran Nacelles

07/20/17 / #20170203378

Method for producing an especially large aeronautical part

The present disclosure relates to a method for producing a final metal part for a nacelle of a turbojet. The method includes brazing at least two parts, one being an inner part having an inner surface and the other being an outer part having an outer surface. ... Safran Nacelles

06/29/17 / #20170184023

Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle

A device for fastening a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle is provided. The device includes an acoustic shroud, a first flange coupled to the fan casing, a second l-shaped flange having a base coupled to the acoustic shroud, and a collar linked to the first flange. ... Safran Nacelles

06/22/17 / #20170175308

Preform for a curved composite stiffener for an axisymmetric part such as a collar

The present disclosure concerns a preform for a curved composite stiffener for an axisymmetric part such as a shroud, including at least one web and at least one flange curved about an axis of revolution of the preform and defining a substantially “t” or an “i” shaped section. In one form, the preform includes a web and a flange, wherein the web includes a plurality of warp yarns circumferentially oriented relative to the axis of revolution of the preform, and a plurality of weft yarns oriented radially relative to said axis, and the flange includes a plurality of warp yarns circumferentially oriented relative to the axis of revolution of the preform, and a plurality of weft yarns substantially parallel to said axis.. ... Safran Nacelles

06/22/17 / #20170174353

Propulsion unit for an aircraft and method for opening a movable cowl of said propulsion unit

A propulsion unit for an aircraft is provided. The propulsion unit includes a stationary unit having at least one cowl pivotally mounted on an axis collinear with a longitudinal axis of the propulsion unit between an operating position or a maintenance position allowing access to the turbojet engine for regular maintenance operations and irregular maintenance operations. ... Safran Nacelles

05/11/17 / #20170129616

Method for installing a de-icing system on an aircraft, involving the application of layers of material in the solid and/or fluid state

A method for installing a de-icing system on the skin of an aircraft element is provided, which involves applying to the skin several independent layers of solid and/or fluid materials which are hardened in succession, and which comprise at least one layer of controlled electrical resistivity material, which takes electrodes that conduct an electric current originating from an external source, which is flanked on each side by layers of an electrically insulating material.. . ... Safran Nacelles

05/04/17 / #20170122204

Front lip of a turbofan engine nacelle comprising hot-air bores upstream from acoustic panels

A front lip of a turbofan engine nacelle is provided, defined at the rear by a partition wall, the lip comprising an annular de-icing space including a tube for supplying hot air in order to de-ice the outer walls thereof, said lip also including acoustic panels arranged on the wall thereof substantially radially facing the axis of the nacelle. The front lip includes hot-air outlet bores/piercings which are arranged between the front end of the lip and said acoustic panels, which allow a flow of hot air, from said annular space, forming a substantially regular film which covers said acoustic panels with a boundary layer in order to heat said acoustic panels.. ... Safran Nacelles

04/27/17 / #20170114751

Rear frame for a thrust reverser structure with diversion grids

The present disclosure relates to the field of aircraft nacelles and concerns thrust reverser devices. More particularly, the present disclosure concerns a rear frame for a thrust reverser structure with a cascade vane of an aircraft nacelle, the nacelle comprising at least two longitudinal beams. ... Safran Nacelles

04/13/17 / #20170101895

Aircraft propulsion assembly

The disclosure relates to an aircraft propulsion assembly comprising a bypass turbojet engine equipped with a nacelle, the bypass turbojet engine including a structure defining a first part of a secondary flow path for channelling secondary flow, and the nacelle having a structure defining a second part of the secondary flow path. The structure of the nacelle defining the second part of the secondary flow path is arranged such that the first part and the second part of the secondary flow path are angularly offset around a longitudinal axis of the engine when the engine is shut down/stopped.. ... Safran Nacelles

03/30/17 / #20170089297

Turbojet nacelle provided with a thrust reverser, including cut-outs to avoid the movable slat of an aircraft wing

The disclosure relates to a turbofan nacelle including a thrust reverser, the thrust reverser including a movable cover moving back from a closed position in which the thrust is not reversed to an open position for uncovering cascades that reverse the direction of the flow of cold air which is diverted from the annular stream of secondary air, the movable cover including a radially outer portion intended for being adjacent to a leading edge of a wing of an aircraft. The movable cover includes on the radially outer portion at least one cut-out intended for avoiding interference with a movable slat of the leading edge of the wing of the aircraft, as well as a panel for closing the cut-out, the closing panel including a stationary portion at least partially covered by an upstream portion of the movable cover when the movable cover is in the open position.. ... Safran Nacelles

03/23/17 / #20170082064

Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors

The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. ... Safran Nacelles








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