Abstract: A gas ejection duct with acoustic treatment provided with at least one wall referred to as an “acoustic” wall for coming into contact with the gas. The acoustic wall comprises an inner skin and an outer skin that are spaced apart at least in part by a space, the acoustic wall including at least one internal mesh in the space, the mesh defining a plurality of cavities. Each cavity has the shape of a parallelepiped, each mesh extending longitudinally in a direction referred to as the “fabrication” direction that presents an acute angle greater than or equal to a predetermined angle relative to a horizontal plane, each of the inner and outer skins presenting an acute angle of inclination greater than or equal to the at least one predetermined angle relative to the horizontal plane.

Abstract: A gas ejection duct with acoustic treatment provided with at least one wall referred to as an “acoustic” wall for coming into contact with the gas. The acoustic wall comprises an inner skin and an outer skin that are spaced apart at least in part by a space, the acoustic wall including at least one internal mesh in the space, the mesh defining a plurality of cavities. Each cavity has the shape of a parallelepiped, each mesh extending longitudinally in a direction referred to as the “fabrication” direction that presents an acute angle greater than or equal to a predetermined angle relative to a horizontal plane, each of the inner and outer skins presenting an acute angle of inclination greater than or equal to the at least one predetermined angle relative to the horizontal plane.

Abstract: A front attachment device for attaching an aircraft engine to an aircraft pylon includes an upper brace fitted with elements rigidly fastened to the pylon and first and a second connecting rods, each connected to the engine, via a first ball joint connection at one end portion and to the upper brace via a second ball joint connection on the other end portion. The device further includes in each connecting rod a third stand-by link. The first and second connecting rods are interchangeable with each other.

Abstract: A suspension of the turbo fan engine to an aircraft pylon, includes a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking device with a pivot pin. Two thrust rods are each connected by an end to the lever and including at the other end of the fastening device to the engine. The linking device is composed on the central portion of the lever, of two parallel branches apart from one another, and on the fitting, of a central fastening tab, whereas the fastening tab and both branches are held together by dint of the pivot pin.

Abstract: A turbine engine mount to a pylon of an aircraft includes a bracket arranged to be attached to the pylon, and a lever attached in its central part to the bracket via a first connection and two thrust links each joined aft to the lever by a second connection. The lever includes a central part with two arms, and the bracket includes an integral attachment lug placed between the two arms and connected to the arms via a pivot pin to form the first connection. The lever is laterally connected to the bracket via pivot pins passing through the lever and mounted with a clearance to form connections on standby.

Abstract: A rear attachment suspension or device of a turbo engine to an aircraft pylon includes an upper brace fitted with a pylon fastening device and hinged by second ball joint connections, first and second rocker bars transversal to the longitudinal axis of the engine on both sides of the axis of the engine and a third rocker bar disposed there between. The rocker bars are linked to the engine by first ball joint connections. The first and second rocker bars each include a third stand-by link and the upper brace is formed of a beam fixed rigidly to the pylon. The rocker bars are designed to ensure their interchangeability, thereby reducing the risks of error during assembly.

Abstract: The present invention pertains to turbine engine mounting onto an aircraft pylon, comprising a bracket (12) arranged to be attached to the pylon, a lever (15;15?) attached in its central part (150;150?) to the bracket by first connection means (150-130) with a pivot pin (136;136?) and two thrust links (20,22; 20?,22?) each joined aft to the lever by second connection means (200-155, 220-157; 200?-155?; 220?-157?) and including engine attachment means at the forward end, characterized in that the first connection means (150-130) consists of two parallel arms (151,153) spaced apart on central part (150) of the lever, cooperating with an attachment lug (130) integral with the bracket via a pivot pin, and lever (15,15?) comprises two third side connection means on standby (155-135, 157-137; 155?-135?; 157?-137?) with bracket (12,12?). The invention provides for simplified mounting with improved safety.

Abstract: The present invention relates to a suspension of the turbo fan engine to an aircraft pylon, including a fitting (12) arranged to be attached to a pylon, a lever (15) fastened in its central portion (150) to the fitting via a linking means with a pivot pin (150P), and two thrust rods (20, 22) each connected by an end to the lever and including at the other end of the fastening means to the engine. It is characterised in that said linking means is composed on said central portion (150) of the lever, of two parallel branches (151, 152) apart from one another, and on the fitting, of a central fastening tab (133), whereas the fastening tab and both branches are held together by dint of said pivot pin (150P).

Abstract: The present invention relates to a rear attachment suspension or device of a turbo engine (1) to an aircraft pylon including an upper brace (12) fitted with pylon fastening means, whereon are hinged by second ball joint connections (163, 183), three rocker bars transversal to the longitudinal axis of the engine, a first (16) and a second (18) rocker bars on both sides of the axis of the engine and a third rocker bar (17) between both of them, the rocker bars being themselves linked with the engine by first ball joint connections (161, 181). The suspension is characterised in that the first (16) and second (18) rocker bars each include a third (167, 187) stand-by link and in that the upper brace (12) is formed of a beam (120) fixed rigidly to the pylon.

Abstract: The present invention relates to an attachment device, in particular a front attachment device, for attaching a turbo engine (1) to an aircraft pylon including an upper brace (12, 12′) fitted with rigid fastening means to the pylon, a first (16) and a second (18) connecting rods, each connected to the engine, via a first ball joint connection (161, 181; 161′, 181′), on the one hand, and to the upper brace (12, 12′) via a second ball joint connection (165, 185; 165′, 185′), on the other hand. The device is characterised in that each connecting rod (16, 18) includes a third stand-by link (167, 187; 176′, 187′).