Safran Aircraft Engines

Snecma

Noel Robin

Ceddric Beljambe

Jacky Novi Mardjono

Georges Jean Xavier Riou

Francois Marie Paul Marlin

Romain Plante

Florian Gaudry

Frederic Dautreppe

An aircraft casing structure including a shroud surrounding the engine and made up of a plurality of sectors; a plurality of radial arms, each mounted between two adjacent shroud sectors and each having a base; and a plurality of fasteners for fastening the shroud sectors on the bases of the radial arms; the fasteners including a plurality of plates each mounted flush in a respective groove of corresponding shape in a shroud sector, and a set of headed bolts held captive in the plate by a difference of diameter between their shanks and their threads, a set of captive nuts being fastened to the bases to provide a secure connection between the shroud sectors and the radial arms by each nut receiving the thread of a respective captive bolt of the set of headed bolts.

Casing structure interposed between the engine and the nacelle having a mounting plate with bolts

A casing structure interposed between the engine and the nacelle of an aircraft, the structure including a shroud surrounding the engine having an engine axis and including a stationary portion and a plurality of sectors; a radial arm providing the connection to the nacelle; fasteners for securing the plurality of shroud sectors to one another or to the radial arm; and the fasteners include two series of holes formed in two parallel side walls of the shroud sectors for the purpose of receiving two respective series of bolts, each passing through a corresponding set of orifices of an adjacent shroud sector or of an adjacent radial arm, a hinge arranged between each of the shroud sectors and the stationary portion of the shroud to enable the shroud sectors to be pivoted in individual manner about a common pivot axis perpendicular to the side walls arranged along the engine axis.

Casing structure interposed between the engine and the nacelle having pivoting shroud sectors

A case structure interposed between the engine and the nacelle of the aircraft is provided. The case structure includes: a ferrule surrounding the engine and including a plurality of segments; at least one radial arm ensuring connection to the nacelle; and a plurality of attachment devices for securing the plurality of ferrule segments together or with at least one radial arm. The plurality of attachment devices includes an articulation device configured for ensuring coupling of the lifted-rotated-pushed type ensuring after disengagement of the ferrule segment, its pivoting about a pivot axis parallel to a longitudinal axis of the engine and then its blocking in a disengagement position.

Case structure interposed between the engine and the nacelle with jointed ferrule segments

A one-piece soundproofing panel which is attached within an circumferential air blower casing of a turbomachine, with an axis, in which circulates an airflow from upstream to downstream, is disclosed. The panel includes a circumferential rigid seat with a longitudinal cylindrical part, arranged to axially extend with respect to the axis A of the turbomachine, having an outside surface, intended to come to extend facing with an internal surface of the air blower casing, and an internal surface to which is applied a soundproofing coating; and an annular fastening flange, formed at the upstream end of the longitudinal cylindrical part, radially outwardly extending, the fastening flange being arranged to cooperate with a fastening flange of the air blower casing.

Growing community of inventors

Villejust, France

Noel Robin