Safran Aircraft Engines

Snecma

Frédéric Paul Eichstadt

Bruno Albert Beutin

Bellal Waissi

Antoine Elie Hellegouarch

Thierry Kohn

Alexandre Alfred Gaston Vuillemin

Quentin Matthias Emmanuel Garnaud

Romain Jean-Claude Ferrier

Brice Marie Yves Emile Le Pannerer

Nora El Ghannam

Jean-Louis Bertrand

Nicolas Maurice Hervé Aussedat

François Leglaye

Florent Luc Lacombe

Joel Mathieu

Elric Georges André Fremont

Jacky Raphaël Michel Derenes

A rear part for a turbojet engine includes a variable-geometry nozzle in which a convergent flap is provided with a lever supporting a bearing roller arranged axially between an upstream bearing wall and a downstream bearing wall, which are rigidly secured to a movable part capable of moving axially on command with respect to an upstream stator structure in such a way that the bearing roller is free to move with respect to the upstream and downstream bearing walls in a radial direction. During a downstream movement of the movable part, the upstream bearing wall pushes the lever to pivot a downstream end of the convergent flap towards the longitudinal axis. Operation of the drive mechanism for moving the movable part can thus be optimized while limiting the size and the mass of the mechanism for controlling the flaps.

Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls

An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.

Aircraft engine assembly with a supply path to an inter-flow compartment tank of turbine engine

Bypass turbine engine, comprising a gas generator surrounded by a nacelle and connected to the latter by tubular arms, a primary flow duct within the gas generator being externally delimited by a first annular casing of the gas generator, and a bypass flow duct of a secondary flow around the gas generator being internally delimited by a second annular casing of the gas generator and externally by a third annular casing of the nacelle, the second and third casings being connected together by at least some of the tubular arms, characterized in that it comprises at least one lubricant tank located in the annular space that extends between the first and second casings, and lubricant supply means of the tank or of each tank that comprise at least one supply line extending from the or each tank to at least one filler opening located at the level of the third casing, passing within at least one of said arms connecting the second and third casings.

Turbomachine with double flow and its lubricant reservoir

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Fontainebleau, France

Frédéric Paul Eichstadt