Safran Aircraft Engines

Morgan Balland

Hélène Mazet

Jean-Yves Picart

Antoine Robert Alain Brunet

Christophe Scholtes

Baghdad Achbari

Florent Robert André Godin

Abdelkader Benyahia

Alban Francois Louis

Guillaume Claude Georges Philippe Linassier

Loïc Jeunesse

Eric Cerutti

Simon Amodeo

Simon Amoedo

An inlet cone for an aircraft turbomachine, having at least one first portion made of a first material, referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is being driven to rotate.

Inlet cone for an aircraft turbomachine

An aircraft propulsion unit is described. The unit may include a gas generator with a fan surrounded by a casing. A nacelle may extend around the casing and define an annular compartment with the casing wherein some equipment may be housed. An air inlet may be configured so a ventilation air flow penetrates inside the compartment. An air outlet may be configured so a ventilation air flow is evacuated from the compartment. The propulsion unit may also include an air flow adjustment regulator. The air flow adjustment regulator may be configured to maintain a nominal value of the ventilation air flow circulating through at least one of the air inlet and of the air outlet under nominal operating conditions, and to reduce the value of this ventilation air flow when a fire is detected inside the compartment.

Aircraft propulsion unit and process for reducing a ventilation air flow in the aircraft propulsion unit

An anti-icing system for a turbine engine vane extending between an outer casing and an inner casing defining a passage, the system includes an injector device for injecting a jet of air into the passage upstream from the vane, the injector device including a first injection orifice for injecting the jet of air, the first orifice passing through one member selected from the outer casing and the inner casing, and being located in such a manner that, at a first speed of the engine wherein a stream of air flows generally in the passage along a first direction, the first orifice and a leading edge of the vane are substantially in alignment along the first direction, the first orifice is spaced apart from the junction between the leading edge of the vane and the member through which the first orifice passes by a distance of at least 10 mm, and preferably of about 15 mm.

Anti-icing system for a turbine engine vane

A device for de-icing a wall of a leading edge of a turbine engine, the leading edge being adapted to cooperate with a downstream guide vane subjected to a flow of fluid, the device including: a first fluid flow device provided along an upper zone of the downstream guide vane so as to guide the fluid to the wall of the leading edge, and a second fluid flow device provided along a lower zone of the downstream guide vane so as to evacuate the fluid from the leading edge, wherein the first fluid flow device is arranged such that the wall of the leading edge is impacted by the fluid along a non-orthogonal direction.

Device for de-icing a leading edge of a turbine engine by slanting notches

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Moissy-Cramayel, France

Morgan Balland