Snecma

Safran Aircraft Engines

Guilhem Seize

Thomas Alain Christian Vincent

Guillaume Glemarec

Francois Robert Bellabal

Richard Masson

Patrick Dunleavy

Olivier Renon

Guillaume Lefort

Quentin Matthias Emmanuel Garnaud

Jacky Raphael Michel Derenes

Julien Pavillet

Hervé Jean Albert Mouton

Lambert Olivier Marie Demoulin

Clarisse Savine Mathilde Reaux

Thomas Gérard Daniel Riviere

Jean-Baptiste Vignes

Audrey Grede

Thomas Vincent

Eric Francois Michel Maingre

Benoit Bernard René Leclerc

Thibaut Francois Roux

François Robert Bellabal

Thomas Alain Vincent

Thomas Gerard Riviere

Francois Bellabal

Eric François Michel Maingre

Thibaut François Roux

Jacky Raphaël Michel Derenes

François Bellabal

The invention relates to an assembly between an aircraft pylon () and a turbomachine () of longitudinal axis (X), the pylon () and the turbomachine () each comprising front and rear longitudinal regions, the assembly comprising a rear support () configured to connect the rear region of the turbomachine () to the rear region of the pylon (), the assembly being characterized in that the rear support () comprises a sliding pivot connection arranged between the rear region of the turbomachine () and the rear region of the pylon (), so as to allow the turbomachine () only translational and rotational movements along and about the longitudinal axis (X) and along and about a vertical axis (Z) and a rotational movement about a transverse axis (Y).

Assembly between an aircraft pylon and a turbomachine

The invention relates to a turbomachine () extending along an axis (X), comprising a high-pressure body with a high-pressure compressor () coupled in rotation to a high-pressure turbine (), and a low-pressure body including a low-pressure compressor () coupled in rotation to a low-pressure turbine (), an upstream casing () located upstream of the high-pressure compressor (), and means of suspension () for the turbomachine (), intended for attaching the turbomachine () to an aircraft pylon ().

Turbomachine comprising a means of suspension

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.

Turbojet engine cold stream flow path suspended from the exhaust case by radial crevice mounts and link rods

A heat shield device for a yoke suspending an engine from an aircraft is provided. The device includes panels able to be fixed to the yoke, at least one of the panels extending radially in the direction of the axis of the engine, and a component configured to be fixed to the engine and including a groove shaped in such a way that the lower end of the panel can be inserted into it.

In-line removable heat shield for a turbomachine suspension yoke

A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibers. In one embodiment, the beam takes a form of a circle arc.

Beam for suspending a turboshaft engine from an aircraft structure

A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.

Metallic annular connection structure for aircraft turbomachine

A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.

Dual-flow turbomachine for aircraft, including structural means of rigidifying the central casing

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

A system for measuring fatigue of a component of an aircraft subject to mechanical stresses includes: a plurality of stress sensors mounted on the component, each sensor being configured to detect a predetermined mechanical stress threshold and to deliver a data signal representative of exceeding of the threshold; and a mechanism for recording the data and the sensors configured to detect different stress thresholds so as to make it possible to calculate, on the basis of the data recorded by the system, an estimation of fatigue of the component due to the mechanical stresses. It is thus possible to optimize overhaul of the components.

System and method for measuring fatigue for mechanical components of an aircraft and aircraft maintenance method

Growing community of inventors

Cachan, France

Guilhem Seize