Safran Aircraft Engines

Alexis Pereira

Thierry Kohn

Bruno Albert Beutin

Benissa Boujida

Zoltan Zsiga

Benjamin Lemenand

A support assembly for supporting a main accessory gearbox of an aircraft turbine engine, the accessory gearbox including gears and supporting at least one item of equipment driven by the gears. The support assembly can include a structure for connecting and supporting the turbine engine to a pylon of the aircraft including: an intermediate axial portion for attachment to the pylon, having an upper end that defines a linking interface with the pylon, the intermediate axial portion bearing suspension rods, which are intended to be connected to the turbine engine; a front axial portion extending forward of the intermediate portion and having at least one suspension member configured to be connected to the turbine engine; and a rear axial portion extending rearwards of the intermediate portion and supporting the main accessory gearbox.

Assembly for supporting an accessory gearbox of an aircraft turbine engine

A drive pinion of an air/oil separator of an accessory gearbox of a turbomachine, the air/oil separator being configured to be supplied at the input by an air flow to de-oil and to supply at the output, on the one hand, a de-oiled air flow and, on the other hand, an oil flow by centrifugation, the pinion being configured to drive the separator rotationally along an axis of rotation, the pinion being mounted facing a passage opening of the separator, the pinion comprising at least one guiding opening traversing the web plate defining at least one guiding surface inclined with respect to the axis of rotation in such a way as to guide along the axis an air flow to de-oil into the separator or a de-oiled air flow out of the separator via the guiding opening of the pinion.

Drive pinion of an air-oil separator of a turbomachine accessory gearbox

The invention relates to a jet pump collector comprising a convergent duct extending along the longitudinal axis (AX) and comprising an intake opening for a fluid to be withdrawn, this convergent duct having a restriction shape terminated by a reduced end having a smaller cross-section than its intake opening. This convergent duct is equipped with a tube () orientated perpendicular to the longitudinal axis longitudinal (AX), this tube () comprising an outer portion extending outside of the convergent duct and being terminated by an intake opening () for a propulsion fluid, and an inner portion extending in the convergent duct and comprising a plurality of distribution openings () for the propulsion fluid which are orientated towards the reduced end.

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Moissy-Cramayel, France

Alexis Pereira