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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


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. In one form, the method includes the step of simultaneously including a reduction... 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,... 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... 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... 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... Safran Nacelles

System for installing and removing a propulsion unit on a pylon of an aircraft

The present disclosure concerns a system for installing and removing a propulsion unit on a pylon of an aircraft, a propulsion unit of the type including a nacelle and a turbojet engine, the turbojet engine being linked on the pylon by at least one front suspension and one rear suspension.... Safran Nacelles

Apparatus for supporting a nacelle of an aircraft engine

Apparatus for supporting a nacelle of an aircraft engine is provided by the present disclosure. In one form, the apparatus includes a frame, a supporting structure extending from the frame, and a structure for attaching a nacelle, which is rotatably mounted on the supporting structure and can be rotated about... 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. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped... 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... Safran Nacelles

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... Safran Nacelles

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... Safran Nacelles

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... Safran Nacelles

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. The method further... Safran Nacelles

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... Safran Nacelles

Propulsion unit for an aircraft and 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... Safran Nacelles

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... Safran Nacelles

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... Safran Nacelles

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... Safran Nacelles

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. The rear frame is intended... Safran Nacelles

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... Safran Nacelles

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... Safran Nacelles

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... Safran Nacelles








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