Aircelle Limited

Andre Baillard

Guy Bernard Vauchel

Pierre Caruel

Jean-Philippe Joret

Peter Segat

Georges Alain Bouret

Emmanuel Piel

Odile Lefeu

Frédéric Joubert

Peter Sagat

A method for assessing damage to a composite material covered with a polyurethane-type paint is provided. Two separate criteria are measured on a spectrogram obtained by infrared spectrometry, thereby characterizing thermal ageing of the paint, each separate criteria being a measurement on a curve of a spectrum of the spectrogram of a height of a particular peak, thereby giving two independent assessments of the thermal ageing. Then, the two separate criteria are combined together in order to obtain a result of a level of the damage.

Method for assessing the damage to a paint-covered composite material, measuring two separate criteria on the spectrogram

The invention relates to an assembly for a turbojet engine which includes a pylon () and a nacelle supported by said pylon (). Said nacelle () includes a grid thrust reverser () including an integral cowl mounted so as to slide on rails (), which are arranged on both sides of said pylon (), between a direct jet position and a thrust reversal position. Said assembly is characterized in that it includes means () for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon () and the cowl.

Assembly for an aircraft turbojet engine comprising a thrust reversal cowl

The invention relates to a bent connecting rod () for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point () that are designed so as to enable the pivotal movement of the connecting rod () relative to said first and second assemblies, respectively, the bent connecting rod () being suitably positionable such that the bend () is located upstream from said flow relative to said second pivot point (), said second pivot point () being suitably built into the second movable assembly, characterized in that the bent connecting rod () includes at least two portions () linked together by at least one self-aligning means ().

Bent connecting rod fitted with at least one self-aligning means

A thrust inverter for a turbojet engine nacelle includes an outer movable cowl and a front frame. The outer movable cowl translates between a closed position and a thrust inversion position and also moves to a supporting position in which the outer movable cowl is hinged and guided by a guiding member located on a pylon. In particular, the front frame holding cascade vanes is mounted downstream from an air blower housing, and part of the front frame is detachably connected to the air blower housing. The front frame is translatable along the guiding member once the front frame is detached from the air blower housing.

Thrust inverter with translatable cascade vanes having detachable front frame

The invention relates to a propulsion assembly for an aircraft, that comprises: a turbojet engine () including a fan casing () and an engine casing (); a pylon for holding said turbojet engine (); and a device for suspending said turbojet engine under the pylon, that comprises two front suspension connecting rods (), two rear suspension connecting rods (), and a thrust acceleration connecting rod () extending between the front portion () of said engine casing () and the pylon in a plane containing the axis (A) of said turbojet engine (). An additional connecting rod () extends between said fan casing () and said pylon in a direction substantially parallel to that of the axis (A) of said turbojet engine.

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Bretteville du Grand Caux, France

Andre Baillard