Snecma

Safran Aircraft Engines

Francois Robert Bellabal

Thomas Alain Christian Vincent

Guilhem Seize

Nicolas Marc Florent

Mathieu Ange Poisson

Francois Gallet

Olivier Renon

Thomas Vincent

Thomas Gerard Riviere

Bypass turbojet engine comprising a fan casing () at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct () which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point () able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points () is positioned on the circumference of said annular rear end of the cold stream duct (), said plurality of attachment points comprising either two points () that are diametrically opposed on said circumference or at least three points that form a polygon through which the axis of symmetry of the cold stream duct () passes, and in that the turbojet engine is equipped with a rear suspension hoop () fixed to said attachment points and able to be fixed to the structure of the aircraft.

Turbojet engine suspension using a double rear support

A method of manufacturing an assembly including a first structure which is arranged to be rigidly connected to a housing of a turbojet engine; a second annular structure surrounding the first structure; and a hyperstatic trellis of connecting rods which maintains the first structure relative to the second structure, is provided. The method includes mounting the connecting rods of the hyperstatic trellis between the structures; and pre-stressing at least one of the connecting rods to a pre-determined level, which is carried out before the mounting thereof between the structures.

Method of producing suspension for a structure in a turbojet engine using a hyperstatic trellis with pre-stressed link elements

A suspension structure for suspending a turboprop including two unducted propellers from a structural element of an aircraft, the structure including a suspension frame for fastening to a structural element of the aircraft and including a main beam extending parallel to a longitudinal axis of the turboprop, the suspension frame being fastened to an air intake structure of the turboprop by an attachment frame.

Suspension structure for suspending a turboprop having two unducted propellers from a structural element of an aircraft with rigid fastening of the air intake structure

The invention relates to a bypass turbojet comprising an exhaust housing having a central hub () and connecting means () that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means () extends between the hub () and the area () for securing the exhaust housing to the structure () of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.

Isostatic suspension of a turbojet by rear double support

A hyperstatic truss including connecting rods, used for suspension of a first ring, forming part of an engine case, inside a second ring concentric to the first ring, the connecting rods being secured at one end to the first ring and at the other end to the second ring. The tensile stiffness of the connecting rods is greater than the compressive stiffness thereof. The truss for example can be used for suspension of a ducted-fan turbine engine with an elongate bypass duct.

Hyperstatic truss comprising connecting rods

A turbojet includes an intermediate casing outer shroud connected to a front suspension and a primary structure connected to a rear suspension; the shroud and the primary structure are held in a coaxial relationship by arms with at least some of the arms being shaped and/or arranged to deform in response to thrust from the turbojet by creating a deforming torque between the shroud and the primary structure in opposition to opposing stress generated by the thrust.

Lateral turbojet improved in order to limit the deformation thereof

An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow jet engine that is concentric relative to the outer ring of the exhaust casing, and at least one first and second linking arm or rod forming a hyperstatic link by being attached by one end to the outer ring of the exhaust casing and, by the other end, to the structural ring. The link formed by the first linking arm or rod is configured to break when a predetermined load is exceeded, and the second linking arm or rod is configured to form a force-transmission path between the rings when the link is broken.

Link between the exhaust casing and a structural ring of the fan duct of a jet engine

A suspension system including a front suspension plane located at an intermediate turboshaft engine casing and connecting same to a pylon, a rear suspension plane located at an exhaust casing of the turboshaft engine and connecting same to the pylon, and a failsafe intermediate suspension plane located between the front and rear planes and including at least one connecting rod connecting the turboshaft engine having a structural outer casing to the pylon, the connecting rod mounted on the turboshaft engine with a predetermined clearance that renders the connecting rod inoperable while the suspension system of the rear plane is operating. The connecting rod is advantageously arranged between the outer casing and the pylon, and an element made of a flexible material is combined with the connecting rod to create the predetermined clearance by an elastically deformable nature thereof.

Turboshaft engine attached to a pylon of the fuselage of an aircraft by a failsafe suspension system

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.

Growing community of inventors

Fontainebleau, France

Francois Robert Bellabal