Safran Aircraft Engines

Snecma

Kaelig Merwen Orieux

Thierry Georges Paul Papin

Regis Eugene Henri Servant

Jean-Marc Claude Perrollaz

Francois Marie Paul Marlin

Cedric Zaccardi

Lise Lacroix

Marc-Antoine Anatole Got

Virginie Guilbert

Yacine Cheraga

Frederic Jacques Eugene Goupil

Remi Roland Robert Mercier

Philippe Verseux

An annular intermediate casing for a turbomachine through which an aerodynamic airstream circulates, including a radially internal shroud, a radially external shroud, at least one stator blade including a vane with a leading edge, and at least one aero-dynamic member which is formed of a structural arm extending radially at least in part between the radially internal shroud and the radially external shroud. The aerodynamic member includes a leading edge which is aligned with the leading edge of the stator blade in one plane and which is borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic airstream, the profiled portion, the structural arm, the radially internal shroud and the radially external shroud being monobloc.

Intermediate flow-straightening casing with monobloc structural arm

A vaned ring for a turbomachine stator includes an outer shell, a vane having a vane head, and two platforms arranged circumferentially on either side of the vane head, and fixed on a radially inner face of the outer shell by detachable fasteners. The vane head has first conical seatings bearing on respective second conical seatings of the two platforms so as to prevent a displacement of the vane radially inwards and along the circumferential direction. The vaned ring includes a frangible pin including a base mounted on the outer shell and a head projecting radially inwards with respect to the outer shell and having a head surface forming, vis-&#xe0;-vis a top surface of the vane head, a stop opposing a displacement of the vane radially outwards.

Vaned ring for turbomachine stator having vanes connected to an outer shell by conical seating and frangible pin

The invention relates to a guide vane intended to be mounted in a turbine engine between an inner shroud () and an outer shroud (), comprising a longitudinal straightening body () for an air flow extending between a first end () intended to be positioned at the inner shroud () and a second end () intended to be positioned at the outer shroud (), the longitudinal straightening body having an aerodynamic profile defined by a leading edge () and a trailing edge () in the flow direction of the air flow, and by a camber line () extending from the leading edge () to the trailing edge (). It further comprises a first attachment heel () and a second attachment heel () positioned in the continuation of the longitudinal body () at the first end () and the second end () respectively, the first () and second () attachment heels being planar elements arranged parallel with respect to one another, each attachment heel () being arranged at a distance from the leading edge () and from the trailing edge ().

Turbine engine flow guide vane with removable attachment

A case of a turbomachine including an inner wall of revolution coaxial with a principal longitudinal axis of the turbomachine, an acoustic insulation structure installed inside the inner wall of revolution that has an annular principal shape centred on the longitudinal axis, and an abradable annular element, wherein the abradable element is fixed on an inner annular face of the acoustic insulation structure.

Turbomachine case comprising an acoustic structure and an abradable element

A turbomachine fan frame including a central hub, a plurality of radial vanes installed on the hub and distributed around the hub, each vane including an inner radial end root at which the vane is fixed to the hub, a plurality of flow stream reconstitution platforms, each platform being installed between the roots of two adjacent vanes and radially at a distance from the hub, wherein each platform is fixed to the hub by at least one support element associated with the platform, the support element located between the associated platform and the hub and located between the roots of two adjacent vanes.

Turbomachine fan frame comprising improved attachment means

A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.

Growing community of inventors

Fontaine le Port, France

Kaelig Merwen Orieux