Snecma

Aircelle Limited

Ntn-Snr Roulements

Guillaume Lefort

Guy Bernard Vauchel

Jerome Collier

Pierre-Alain Chouard

Marc Patrick Tesniere

Pierre-Alain Jean-Marie Philippe Hugues Chouard

Nicolas Hillereau

Francois Conte

Thibaud Jean-Baptiste Guibert

Richard Masson

Patrick Dunleavy

Jean-Philippe Joret

Guilhem Seize

Patrice Dhainault

Vincent Pallanchard

Aurélien Bonnaudet

Regis Fassier

Andre Bruno Denis Baillard

Cyprien Teillou

Anne-Laure Gibouin

Thibaut Francois Roux

Guy Azam

Ivan Goudet

David Calatraba

Florian Caporale

Jean-Baptiste Guibert Thibaud

Thibaut François Roux

Jérôme Collier

Pierre-Alain Jean-Marie Philippe Hugue Chouard

André Bruno Denis Baillard

François Raymond Conte

The invention relates to a bearing cage for a bearing of the type comprising a first ring having a first bearing race, a second ring having a second bearing race, rolling bodies positioned in an annular rolling volume between the first and the second bearing races in such a way as to enable a relative rotation between the first and second rings around a reference axis of the bearing, the cage comprising cells for housing rolling bodies, the cage being characterised in that it comprises an interface for coupling with a maneuvering member, such that when the maneuvering member is engaged with the coupling interface, the bearing cage is capable of being rotationally driven by the maneuvering member in a predetermined direction with respect to the reference axis.

Bearing cage, associated assembly and associated mounting and dismantling methods

The rolling bearing for a blade root includes an outer ring () and an inner ring (). An inner space () is defined between the inner surface () of the outer ring () and the outer surface () of the inner ring (). At a distal end (), the inner space () is closed off by a distal sealing system () between the outer ring and the inner ring. A system () for retaining the distal sealing system () includes a retaining body (), and a thread/tapping system provided on a peripheral assembly surface of the retaining body and on a peripheral surface of the facing inner or outer ring. The retaining body () is screwable into a retention position in which an axial abutment surface () of the retaining body forms an axial stop for the distal sealing system longitudinally (B), in the proximal-&#x3e;distal direction.

Rolling bearing for blade root and manufacturing method, system, oscillating system, and rotating system comprising such a bearing

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

The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure () that defines, together with an inner concentric structure () for surrounding the downstream portion of the turbojet, an annular flow channel (), characterised in that a portion at least of said inner structure () is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.

Nacelle for the jet engine of an aircraft

The present invention relates, on the one hand, to a nacelle () for a double flow turboreactor () comprising a front air intake section (), a median section () intended for surrounding a fan () of the turboreactor and a rear section (), said rear section having an internal structure () intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon () intended to be connected to a fixed structure () of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.

Structural nacelle

The nacelle () comprises an air intake () upstream of the turbojet engine (), a middle section () an internal casing () of which is intended to surround a fan () of the turbojet engine (), and a downstream section () comprising an external structure (which is rigidly connected to a downstream part of the casing () of the fan () so as to support the turbojet engine () and has means of attachment to a strut () intended to be connected to a fixed structure () of an aeroplane.

Bypass turbojet engine nacelle

A turbojet suspended from an aircraft mast is disclosed. The turbojet includes a front fan, an intermediate casing downstream of the fan with an outer shroud and a hub connected together by radial arms, and an exhaust casing with an outer shroud, the two casings being aligned on one and the same axis XX. The mast includes a structural strut assembly of elongated shape. The strut assembly is attached upstream rigidly to the outer shroud of the intermediate casing by a front attachment including a device for transmitting the axial and lateral forces and downstream by a rear attachment to the exhaust casing.

Turbojet suspended from an aircraft mast

The present invention relates to an isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the same axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing. It is characterized in that the plane formed by the two links of the rear attachment is inclined with respect to the plane of the exhaust casing.

Suspension for mounting a turbojet engine on an aircraft

An integrated propulsive turbofan engine system includes a downstream cylindrical nacelle structure in two parts. The first of the two parts is fixed and fastens engine attachment elements and an intermediate casing to the aircraft. The second of the two parts may move between a closed position used during operation and an open position during maintenance when access to engine components is needed.

Integrated propulsive system comprising a bypass turbojet engine

A propulsion system for an airplane having an integrated pylon includes a bypass turbojet and a nacelle. The nacelle has a downstream cylindrical part which is rigid and is attached at its upstream end to an intermediate case of the engine. This downstream cylindrical part also includes a longitudinal beam for attaching rods to secure the engine to the airplane.

Propulsion system with integrated pylon

Growing community of inventors

Paris, France

Guillaume Lefort