Safran Aircraft Engines

Safran

Rémi Roland Robert Mercier

Laurent Jablonski

Thomas Alain De Gaillard

Philippe Gérard Edmond Joly

Régis Eugène Henri Servant

Jean-Marc Claude Perrollaz

Alexandre Bernard Marie Boisson

François Jean Comin

Anthony Lafitte

Arnaud Langlois

Alexis Thomas Chaboud

Fabrice Michel François René Aubert

Foucault De Francqueville

Naoufel Ben Salem

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

A method for manufacturing a panel including a plurality of partitions defining cells covered by at least one skin, the skin being formed by draping fibrous structures impregnated with a thermoplastic material on the upper edges of the partitions by automatic placement of fibers, the upper edges of the partitions and the fibrous structures being joined together with the aid of a localized heating device at the moment they are placed in contact, the method wherein the fibrous structures are draped with a draping tension on the interface between each edge of a partition and the deposited fibrous structure applying a shear stress of between 50% and 80% of the maximum shear stress before rupture of the interface.

Draping a skin of thermoplastic material on a multicellular body

A control ring for controlling discharge gates for an aircraft turbine engine extends around a casing of the turbine engine and includes a connector for connecting to the gates. The control ring includes metal sectors and composite material sectors. The metal sectors may be connected to one another by the composite material sectors and the connector may be carried by the metal sectors.

Discharge door control ring for aircraft turbomachine and turbomachine comprising the same

The invention relates to a bladed disk () of a fan, comprising: a hub () comprising an outer radial platform () designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades () comprising a root () connected to the platform (), a leading edge () and a trailing edge (), a groove formed in the platform () around part of the root () of each blade () in an area adjacent to the leading edge () and/or the trailing edge (), and a joint () placed in the groove () in such a way that it extends in the extension of the radially outer face () of the platform () in order to ensure a continuity of the inner flow stream.

Bladed disk flexible in the lower part of the blades

A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of radial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.

Turbmachine fan disc

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Moissy-Cramayel, France

Rémi Roland Robert Mercier