Abstract: Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point (4) able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points (4g, 4d) is positioned on the circumference of said annular rear end of the cold stream duct (7), said plurality of attachment points comprising either two points (4g, 4d) 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 (7) passes, and in that the turbojet engine is equipped with a rear suspension hoop (8) fixed to said attachment points and able to be fixed to the structure of the aircraft.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) 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 (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) 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.

Abstract: A bypass turbojet engine including a cylindrical cold stream flow path supported by link rods which are attached to a cylindrical outer shell ring of an exhaust case at attachment points. The attachment points for the exhaust case are crevice mounts including lugs that extend radially from the outer shell ring, a bore of the crevice mounts being directed in a direction of generatrices of the outer shell ring.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) 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 characterised 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 (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) 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.

Abstract: 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.

Abstract: Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point (4) able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points (4g, 4d) is positioned on the circumference of said annular rear end of the cold stream duct (7), said plurality of attachment points comprising either two points (4g, 4d) 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 (7) passes, and in that the turbojet engine is equipped with a rear suspension hoop (8) fixed to said attachment points and able to be fixed to the structure of the aircraft.

Abstract: 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.

Abstract: The invention relates to a method of manufacturing an assembly comprising a first structure (23), arranged to be rigidly connected to a housing of a turbojet engine, a second annular structure (21) surrounding the first structure, and a hyperstatic trellis of connecting rods (40a, 40b, 40c, 40d, 40e, 40f) maintaining the first structure (23) relative to the second (21), said method comprising a step of mounting said connecting rods of the hyperstatic trellis between said structures and being characterised in that it comprises a step for pre-stressing at least one of said connecting rods (40) to a pre-determined level, carried out before the mounting thereof between said structures. It also relates to a device which is suitable for mounting the pre-stressed connecting rods.

Abstract: 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.

Abstract: A method for creating a connecting element, arranged between two components of a structure, or a turbojet engine structure, which is subjected to compressive and/or tensile loadings and which includes a hollow shaft immersed, at least partially, in a stream of air flowing between the two components, the method including: dimensioning a width of the main cross section associated with the shaft of the connecting element in a direction orthogonal to the longitudinal axis of the shaft according to desired mechanical strength and desired mass, and according to characteristics of the airstream; and working an external surface of the shaft of the connecting element, at least over part of this surface, to give it a surface finish with an arithmetic mean roughness at least equal to 20 microns, to reduce drag of the connecting element thus dimensioned by comparison with a smooth connecting element of the same diameter.

Abstract: A bypass turbojet engine including a cylindrical cold stream flow path supported by link rods which are attached to a cylindrical outer shell ring of an exhaust case at attachment points. The attachment points for the exhaust case are crevice mounts including lugs that extend radially from the outer shell ring, a bore of the crevice mounts being directed in a direction of generatrices of the outer shell ring.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.