Safran Aircraft Engines

Snecma Société Anonyme

Arnaud Langlois

Laurent Jablonski

Régis Eugène Henri Servant

Vivien Mickaël Courtier

Vincent Joudon

Clément Cottet

Pierre-Alain Francis Claude Sebrecht

Rémi Roland Robert Mercier

Sébastien Claude Cochon

Fabrice Michel François René Aubert

Sébastien Cochon

A de-icing device to supply de-icing air to a turbomachine separation nozzle extending along a longitudinal axis, the turbomachine comprising: a separation nozzle positioned downstream from a turbomachine fan and comprises an internal casing and an external casing which form a separation between a primary flow vein for a primary stream and a secondary flow vein for a secondary stream, the internal casing and the external casing defining an inter-vein space; turbomachine guide vanes secured by screws to the internal casing, the screws extend into the inter-vein space, the de-icing device positioned in the inter-vein space and comprising an air inlet; an air outlet; a plurality of channels extending from the air inlet toward the air outlet; the channels arranged in relation to one another such that they extend from the air inlet toward the air outlets, passing between the screws for securing the guide vanes.

Device for de-icing a turbomachine nozzle

An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; —a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.

Aircraft turbine engine comprising variable pitch propeller blades

A turbine engine compressor includes a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring capable of pivoting axially in relation to the casing, where the linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole in the control ring, where at least one of the holes in the control ring serves for insertion of the pins of the linking members, is oblong in shape and extends in the circumferential direction in order to allow movement of the pin in the oblong hole, during rotation of the control ring.

Turbine engine compressor, in particular of an aeroplane turboprop or turbofan

Growing community of inventors

Moissy Cramayel, France

Arnaud Langlois